JP2016509651A - Energy efficiency improvement device for turbomachinery - Google Patents

Abstract

Methods and apparatus that disclose conformal vortex generation techniques that enable improved energy efficiency and controllability in many respects in turbomachines or devices that perform aerodynamic / hydraulic Newtonian fluid flow processes.

Description

  The present invention improves the energy efficiency and / or performance envelope of an apparatus by using a new hydrodynamic structure of an aerodynamic / hydraulic Newtonian fluid-flow apparatus and a conformal vortex generator (CVG). Related to the field of ability. Such novel applications of intrinsic or integrated CVG include actuator cascades, foil cascades and flow-control surfaces in dynamic turbomachinery such as mobile turbine engines, static power generation turbines, helicopters, blades , And other Newtonian fluid-flow applications, generally operate at various locations and roles.

  For example, the additional CVG used in Helicopter Corrosion Prevention System (EPS) can be mounted and matched to smaller, more complex and esoteric turbomachinery structures with very fast radial acceleration on the order of tens of thousands of gravity This is not feasible and this requires a new inherent intrinsic or integrated CVG method that requires a high robust cascade and performance environment such as high temperature and sharp edged input surfaces Because. The additional CVG is conveniently attached with adhesive to the existing foil or body surface design, post-manufacturer, where the original foil or body surface design-intent and engineering considerations are the most preferred of the benefits of CVG Was not considered for binding. In contrast, integrated CVG technology is included in the design process and engineering for the design of new foil or fluid-flow control surfaces, which is not possible with the additional CVG technology. Allow new combinations of control range, energy efficiency and manufacturing options.

  A gas turbine engine is in fact a well-known example of a complex turbomachine using various ranges of Newtonian fluid-flow, thermodynamics, materials and physical techniques applied to fluid-flow processing equipment. Each series of functional blocks allows some input fluid-flow, processes this fluid in several ways, and then outputs this fluid at the interface to the next stage of the engine. The initial air inlet is the first fluid input interface and any cooling or hot section exhaust nozzle completes the final fluid output interface in the ambient atmosphere. For turbine engines using the well-known Brayton cycle, the efficiency is the difference between the fluid peak operating temperature vs. the final outlet temperature difference in the compressor, turbine, combustor and inlet guide vane (IGV), flow ducting and outlet nozzle gas paths. Related to well-known theoretical thermodynamic cycle performance of ratio and flow efficiency, or energy loss.

  In the present disclosure, the fluid-flow taught herein is for a working Newton “fluid”, a typical atmosphere or other gas, but many CVG technology embodiments also have Reynolds number (Re) When reached, it is effective for liquid or mixed phase conditions. This is known to be true because in turbomachinery and equipment, numerous foils and flow designs for gas fluid-flow use labeling materials and methods to observe scalable fluid-flow effects. For example, to be scaled, tested and flow visualized for convenience in a water tank. In the following, “fluid-flow” is applicable to the Newtonian gas phase and / or liquid phase because the hydrodynamics are actually adjusted by the fluid-flow conditions and the Re number.

  Engine compressor and turbine blade stator and rotor disk designs as an array of foils in the cascade are optimized for aerodynamic performance, engine geometry and mass flow. Since the initial stage operates in close proximity to the cooler inlet fluid temperature, the compressor and possible bypass-fan stage and ducting “cooling section” operate in a less demanding environment. In these cooling sections, flow improvers reduce the complexity of high gas temperatures, oxidation or other issues affecting material strength to create common rotation, flow, aeroelasticity, vibration, fatigue and pressure stress. I don't have it. The compressor stage can absorb about 60% + of the total fuel-energy provided and is extracted by the turbine stage. The remaining usable turbine output energy and efficiency improvements in jet exhaust nozzle impact have a significant impact on the useful output work available.

Description of prior art

  Low Pressure Turbine (LPT) Stage: In many modern concentric-shaft engine designs, the LPT stage typically energizes from the mass flow of the “hot section” gas in the combustor after it is exhausted while inducing a pressure drop. And this energy is guided through the innermost shaft drive shaft to the bypass fan, shaft load and / or initial compressor stage.

  The LPT stage blade load and the Zweifel load factor increase as the cascade robustness, lower blade count, engine size, weight and cost change, and the impact / reaction foil empty in the turbine cascade. Problems arise with mechanics. In the lower Re-number “off-design”, the rotor and stator blades have a thick boundary layer (BL), turbulent fluid-transition, fluid-flow separation in the lower momentum BL layer, total fluid- Unfavorable suction-face pressure gradients can be experienced that induce flow separation bubbles and loss of energy efficiency.

  McQuilling is a well-known Pratt and Whitney Inc. in his paper, “Design and Validation of a High-lift Low-Pressure Turbine Blade”. His proposed “high lift” (and front-loaded) LPT blades, including an improved ヅ Weifel coefficient for common examples such as the “Pack-B” blade design The design teaches that an operating envelope extreme or “off-design” is possible without using any additional flow modification methods to combat flow separation or blade stalling.

  Here, blade foil front-loading optimization allows the suction-face pressure recovery to diffuse for longer chord distances, improving fluid-flow, low energy and low momentum. The disadvantageous pressure gradient is reduced while reducing the separation of the lower BL. In this case, the reaction to the basic blade fluid-flow, unstable upstream wake, etc. can be designed to be improved over the prior art, but ultimately the combined performance improvement will reduce this design blade load. Flow optimization techniques must be used to reduce drag and separation, especially in off-design at performance envelope limits.

  Fluid-flow variants and effects are described, for example, by Rouser in his paper, “Use of Dimpled To Suppress Boundary Separation On A Low Pressure Turbine Turbine. This variation and effect is also intended to reactivate the lowest BL level and prevent adverse pressure gradient effects and fluid-flow separation from the foil surface. First, it includes many types of surface structures and methods that are used to generate vortex flow and to circulate energy from the higher momentum fluidized bed to the lower layer (adjacent to the foil surface).

  Well-known vortex generators (VG) used to improve foil flow fall into many categories that differ in their effectiveness and benefits. Projecting devices such as ramps, angled vanes, riblets, wheeler ramp vortex generators and the like produce beneficial vortices but tend to lower drag and flow separation losses Generate extra drag while attempting to change the flow conditions. In addition, these protruding devices recover energy from a more active upper layer of the BL that becomes free stream or thicker at a lower Re number, but then protrudes higher onto a thinner BL at a higher Re number. Thus, a high induced drag is caused at such a performance point. These devices are characterized, for example, by having a substantial BL thickness height in the range of 35-100% or more of the maximum BL in VG.

  Widely so that concave or soaked VG and micro VG, such as Ogee submersible, wheeler channel or even dimples, generate less added drag than protruding VG below BL depth Have been studied and taught. These devices have variable geometry or height in steps or ramps in the code direction. Ozzy submersible devices show their vertices towards the incoming fluid-flow and do not match the foil profile. In some micro VGs that are low in BL, a complex series of applications is required to generate sufficient vortex energy, and such close-proximity applications are performance in a rotating environment such as a blade. Disadvantageous.

  Dimples typically reduce drag by suppressing large flow separation bubbles, as taught by Rouser (eg, golf balls are used to fly farther due to low drag). Simple and omnidirectional. However, dimple diverging vortices are complex, with low optimal strength or ability to couple much free stream fluid-flow energy to the lower BL.

  The dimples for BL control are complex because their performance is sensitive to geometry and Re number where the vortex mode predominates. Blade-type VGs, for example, with respect to the actual LPT blade Re number, these are very small on the order of millimeters, thus resulting in a very sharp, fine and elaborate structure, and high temperature oxidation exhaust There is a further problem in that gas is subject to particle corrosion and damage. Further problems include the mechanical impact on blade fatigue due to point stress concentrations during blade warping and the risk of these sharp objects facing maintenance personnel.

  Ramp-inlet (eg, wheeler with aft facing step, upward ramp flow) and ramp-outlet type (eg, Ozzy submersible, downward ramp flow with forward facing step) VG also has energy Has a potential shock wave with other secondary flow structures such as cross flow or spanned horseshoe vortices that redirect the energy from being strongly coupled into the exit cord direction vortex.

  In the NASA study, a typical VG generates a vortex that typically maintains a multiple of about 40 VG height backwards along the cord length by a distance of about 30 times the VG height in the flow direction. It shows that it will be circulated to higher energy layer.

  Rouser teaches other non-VG methods of BL flow control as shown in FIG. 10 (belonging to McCormick), such as a passive porosity-surface device, and this passive porosity-surface. In the apparatus, a higher pressure is generated and injected on the surface of the low pressure region prior to separation through an array of holes or injection slots or steps. This provides an effect similar to Coanda or other lift enhancement or blown-flap type methods or other suction methods used to stabilize the BL region. Of course, one of the problems with jet fluid injection is that as BL speed decreases, jet "lift-off" or flow momentum is balanced to avoid jet "lift-off" or flow separation, or the flow Re is varied. Yes, and in addition, the local BL collapses to form a horseshoe vortex around the leading edge (LE) of the jet fluid-flux column or stream before it is driven close to the blade surface. It is.

  Hybrid Laminar Flow Control (HLFC) reported for Boeing 787 aircraft, for example, vertical stability using intake air from a passive source to improve control flow separation during single-engine operation (instead of VG) Use porous suction-surface technology for BL control of the vessel LE. The porous pore / mesh suction surface has strength problems with the composite structure and has problems with the environment blocking the inlet, the loss of viscous energy, and the force required to induce suction.

  Stephens US 2,800,291, Wheeler US 4,455,045 and US 5,058,837, Rinker US 7,900,871 and many other all documents show increased height from the underlying foil surface A ramp with a peak, teaching an add-on ramp style VG or similar individual shape variant starting from a thin (non-zero) inlet edge in fluid-flow and extending backwards Yes. Geometrically or topographically, the device does not match the surface of the underlying foil in any interpretation. As taught by Stephens '291, abnormally grown or equivalent VG structures such as Rinker' 871 cannot act as a drag that decreases at a low angle of attack (AoA) on the foil or body surface. Here, “low angle of attack (AoA)” means, for example, a substantial fluid-flow separation on the foil or body surface upstream of the normal final outlet flow separation in a TE that meets the flow-fluid outlet, or Kutta-Jawkowski condition. For example, it is defined as a range including positive, zero, and negative AoA under an angular magnitude with no stall or separation bubble. In most foils, the range of +/− 4 degrees AoA satisfies this condition, but is not limited to this, and in various cases it may be a larger range and approach the stall AoA. Schenk US Pat. No. 4,354,648 teaches an array of protruding low-profile BL tripping devices to generate BL turbulence and reduce airfoil flow-separation on the vanes. Because the Schenk '648 device is not zero inlet-height and does not perfectly match the foil surface, it induces drag from horseshoe vortex or turbulence even if this device is proposed smaller than prior art VG It will be. Small size, discontinuity or point coverage and non-directional turbulence are not efficient BL reactivation methods.

  US Pat. No. 5,088,665 to Vijgen et al., “To Improve Lift and Drag Characteristics”, Triangular / Sawtooth Array of Elements or Foil Trailing Edge (TE) variants with appendages after TE of sawtooth panels. Teaches. The addition of the remaining active aerodynamic elements outside the physical range of the original base foil does not add CVG on the foil surface in front of the TE and within the physical range or boundary of the original foil. Obviously different. Fritz US8,083,488 also teaches serrated add-on panels at TE and is distinct and patentable against Vijgen's' 665. Shibata US 6,830,436 adds a “tooth shape” or serrated shape in TE for both noise reduction and increased efficiency by modifying the trailing von Karman Street vortex sheet. Wind turbine blades are taught and claimed. Gliebe US 6,733,240 also teaches and claims a serrated TE array on a turbofan blade to improve fluid mixing and reduce noise, and Young US 3,153,319 and The same aerodynamic effects and results are used as taught in US Pat. No. 6,612,106 to Balzer. Gliebe's 240 does not teach drag reduction below the reference design and is easily added on the pre-TE foil to obstruct linear TE and get drag reduction above the reference configuration and other improvements. This is clearly distinguished from CVG.

  In Godsk US 7,914,259, as shown in FIG. 3, there are several sequences along the wind turbine blades to extend the reference non-stall AoA from about +10 degrees to about +16 degrees with VG added. Of discontinuous prior art VG. FIG. 4 of Godsk '259 shows a well-known problem with discontinuous ramps and blades VG, which is a low AoA and a blade attached to the VG to a +10 degree reference stall AoA. The criterion is that it has a higher drag coefficient (Cd) than an unmodified blade.

  Wortman US Pat. No. 5,069,402 includes a C-130 tail section upgrade to prevent or reduce flow separation (similar to stall) from surfaces that have high AoA or branching efficiently from the fluid-flow stream line. Teaching to generate a normal large downstream eddy and high induced drag by utilizing a prior art large blade type VG to generate a swirl that propagates along a bifurcated-flowing surface such as a sweepsweeper doing. The Wortman '402 technology blade VG itself develops considerable form- drag, but acts to lower the greater downstream separation drag, effectively when these VGs induce drag In some scenarios, where there appears to be a total drag-decrease and alters other significantly separated or stalled flows, it can only be seen when the drag is relatively reduced.

  The ramps and blades VG tend to generate higher non-sustained vortices in BL that are not tied to the foil surface. The dimples and bumps produce eddy currents, but they are not very efficient or activated, and the bumps are higher as the Re number changes and the BL becomes thinner It has the same issue as the blade VG that will induce excessive drag in BL.

Martin, a AIAA paper such McVeigh in "passive control of the compressible dynamic stall" small blade VG about a blade _{C d} of about 0.01 0.015 were used to helicopter rotor blades in FIG. 27 It teaches to increase dynamic stall and blade pitch moment due to VG increasing blade stall AoA while increasing rotor power requirement by about 50%. McVeigh US 7,748,958 claims such a VG structure and method for reducing dynamic blade stall / pitch moment, but based on published test results and known flow physics, It is not possible to request the addition of a general drag reduction ability.

  Volino's NASA research report “Synthetic vortex generator jets used for separation control on low-pressure turbine airfoils” teaches active separation control using synthetic vortex generator jets (VGJs). Thus, the vortex is generated by pulsing an angular jet flow into the BL that partially induces a chordal vortex flow and serves in a manner similar to a normal VG that reduces flow separation bubbles. The Volino approach does not require a constant source of activated blower fluid-flow that consumes the energy it generates, and its design is a pulse type without net-flow sound generation. It is unique in that it produces a jet flow. The interaction of the fluid jet with the higher BL flow and the momentum layer creates a vortex state, which also creates drag while attempting to spread energy into the BL region that extends more widely in the span direction.

  However, all these prior art techniques to improve airfoil or LPT blade flow and reduce segregation are even larger so that the real world rotating environment convects vortices outward in the foil span direction at the boundary layer It has an issue in that it adds further complex conditions. This tends to rotate the vortex that is not tightly bound to this surface outwardly after the physically defined generation point (radially on the chip side) with a higher BL fluid-flow pattern, The blade then accelerates in a curved path and, in addition, the vortex tends to move downstream, so there is no substantial force acting to bring the vortex closer to the blade, so the vortex is convectively on top of the BL However, this is due to the fact that any secondary flow in the span direction can be intercepted and strongly collapses outward.

  In this case, the beneficial intention of the chordal vortex generated earlier on the cord to reactivate the BL and reduce flow separation and drag is actually negative, as shown by Martin et al. To act partially across the free stream (more to the vortex axis in the span direction) in a chaotic fashion that tends to increase the drag by increasing the subsequent BL while affecting the separation Eddy currents precess. This effect has been clearly explained for helicopter rotor blades operating at about 1,200 gravitational accelerations at the tip and at much lower centripetal acceleration than the LPT cascade operating environment. Prior art eddy current generators that act or convect eddy currents on the BL are generally disadvantageous in a rotating environment, as shown by Martin et al.

  Aft-facing steps for free stream flow are captured as taught by Calvert and Wong in the AAAA paper “Aerodynamic Impact of Helicopter Blade Corrosion Coating”. It is known that eddy currents are generated and therefore fluid losses and flow disturbances occur. These are, as on UH-60 helicopter LE corrosion protection strips (EPS), that the span vortex for a simple aft-facing step (ie at 90 degrees to fluid-flow) is reduced by the blade operating point. It teaches that it is known to increase blade drag by + 5% or more.

  In the case of UH-60, for example, an aft-facing step of ~ 0.5 mm height and 5 m length means a captured spanwise step-vortex filament having an aspect ratio of about 10,000, In a mechanical situation such a very elongated vortex filament structure is not dynamically stable. For example, in the LE part of a rotating foil such as a helicopter, there are numerous mechanisms that strongly disturb the BL level fluid flow. Spanwise (or generally radial) secondary upper-BL flow is angled across the EPS step so that the shear force is driven outward on the lower BL momentum layer and is angular to the foil cord It tends to flow as there is. This will provide a strong step-breakup impetus along the centripetal acceleration in the viscous-attached BL layer that tracks the foil motion and, depending on the measurement, may be angular to the span The step-vortex section can be continuously disengaged with a vortex section that can be precessed and perturbed to thicken the subsequent BL on the foil and increase drag loss. A Tollmien-Schlictig (TS) sound pressure wave develops in the laminar-flow region upstream of LE, amplifies, and flows to the rear side to help transition to BL turbulence so that the vortex stream can be bent into a U shape In addition, these disturbances also affect the step-vortex stability and the shedding frequency. It was unforeseeable that an after-facing step device could be used to generate drag reduction against a reference or unmodified fluid-flow surface, reduce energy loss, and improve fluid-flow efficiency It is a result.

  All other known prior art, such as Stephens' 291, Wheeler '045 and' 837, Rinker '871, Vijgen' 665, etc., generally have a triangular shape and apparent visual similarity While the vortex generator configuration is typically shown, aerodynamic analysis readily shows that such a configuration and effect is clearly different from the new technology CVG.

  High Pressure Turbine (HPT) Stage: Nickel-based superalloys cannot withstand high gas temperatures directly as the turbine inlet temperature (TIT) increases from the combustor, making the engine lighter and improving fuel consumption (SFC) And other methods to actively cool engine components under operating loads and maintain their shape and strength were required. A typical design uses a bleed compressor cooling air to cool the combustor, HPT stator and rotor, and the duct surface to the point where the flow temperature is safely reduced, and minimizes cooling energy costs. For example, a ceramic thermal barrier coating (TBC) can be used. TBC reduces cooling conditions and associated energy costs due to increased surface thermal resistance, but maintains sufficient cooling so that the base metal does not soften or these alloy crystal alignments do not shift. The remaining heat flux must be removed.

  HPT cooling: In hot section ducts, excessive and hot gas excessive mix-down or turbulent flow in the lower BL duct surface and blades (both rotor and stator) are on the component surface under hot gas flow. On the other hand, the heat flux load is increased and the cooling condition is increased. Such disadvantageous fluid-flow separation and turbulent flow both have problems in efficiency (drag) and thermal durability.

  An example of the prior art is the Howald US Pat. No. 3,527,543 patent which teaches surface film-cooling utilizing holes on the blade to provide internal air cooling on the blade surface. Bird et al. US Pat. No. 5,193,975 teaches a turbine blade having an internal cooling passage, a pink ring and a TE slot cooling air exhaust. If the main flow and cooling flow rate are not matched and the slot flow separation edge is not tapered to a very (subtle) sharp edge, then the disadvantageous vortex will be formed perpendicular to the flow, so that the discharge slot straight-edge Are typically disadvantageous to drag. Zelesky's US 5,378,108 teaches a TE series slot modified to optimally distribute TE cooling flow and thin TE formed solely by suction-face wall thickness to minimize drag doing. The Green, US Pat. No. 5,374,162 teaches a blade LE fountainhead cooling that is effective in changing the input flow angle. US Pat. No. 7,011,502 to Lee et al. Teaches a LE bridge casting arrangement with a pin mesh and a cooling outlet slot, which is disadvantageous if the matched fluid flow is not matched and the edges are sharp. It still has the problem of linear edges that will have a span vortex.

  Shih and Na's ASME paper “Increasing Thermal Insulation by Using Upstream Lamps—Cooling Efficiency” is achieved by using a lamp in front of the cooling jet outlet hole instead of VG in the jet hole or coupled to the jet hole. It teaches improving the cooling efficiency of adiabatic membranes up to three factors. Here, the span direction (crossing the free stream flow) vortex captured after the ramp causes the coolant mass to cross the flow span and improve the cooling laterally or in the span direction and the jet It acts to alter the cooling fluid jet flow by disrupting the unfavorable leading horseshoe vortex of the jet so that it diffuses before the exit hole. This ramp / jet configuration shows about 3 times more effective adiabatic cooling due to the ramp, but is mentioned earlier in that the form or pressure drag increases relative to the flat plate baseline. Such a protruding lamp structure is disadvantageous. A lamp that protrudes into a hotter gas layer also requires a mass to which TBC is added, as mentioned.

  Thus, Shih and Na ramps and step ideas, where trapped spanwise vortices aid the diffusion of cooling fluid, trade cooling improvements against adverse fluid flow drag efficiency and viscous losses. As reported by NASA, Wheeler VG. Teaches a smaller upstream jet of “anti-vortex” pairs that act to minimize the adverse kidney vortex of the main cooling jet flow. As in Heidmann's “Numerical Study of Anti-Vortex Film Cooling Design with High Blow Ratio”, modeling for the lamp was configured to generate only the span vortex without the cord vortex at the ramp edge. This method has been attempted to diffuse adiabatic cooling in the span direction and avoid jet-liftoff where jet flow is separated from the surface, but is taught as a combination to reduce foil drag loss and turbine drag efficiency. Not.

  Turbulators are also formed inside the coolant pipe flow as triangles, ramps, chevrons, etc., and tortuous cooling passages inside the cooled high pressure turbine (HPT) rotor blade, stator and hot gas flow surface. In this case, the heated surface BL fluid is backed up in the cooling core fluid flow in order to maximize heat transfer or heat transfer and cooling efficiency despite the drag induced by the flow geometry unlike CVG. Configured to provide maximum flow turbulence for mixing. Here, the surface step or chevron vortex and the turbulent-guiding structure are configured to be aerodynamically adjacent together so that when the vortex state disappears, the cooling fluid is not reorganized into a smoother flow. Obviously this is not a fluid-flow low-drag operation, but is actually enhanced so that flow BL separation improves heat transfer by the working fluid, and these prior art structures are clearly CVG and Is different.

  HPT thermal barrier performance: Terry US 2,757,105 and Haskell US 5,260,099 teach the value of engine blade coating, and Driver patent US 4,303,693 teaches the value of plasma spray coating. doing. Kojima et al. US Pat. No. 5,630,314 teaches a “tile” or cylindrical thermal barrier coating (TBC) for turbine blades, and Nissley et al. US Pat. No. 5,705,231 describes gas turbine temperatures. It teaches pre-cracked or segmented plasma spray type ceramic coatings with good wear and spalling resistance. Nissley and the prior art also improve ceramic adhesion, improve thermal expansion coefficient matching, provide a transfer layer that is easy to handle, and are typically used for high mechanical and thermal stress components, such as nickel super It teaches the value of diffusion or surface bonded coatings (eg, MCrAlY, aluminide, alumina, etc.) to provide increased thermal oxidation protection to the base layer of the alloy.

  Spengler et al., US Pat. No. 4,576,874, applied one or more ceramic TBC layers to a turbine blade to improve durability, especially when circulated in a cooler state, the ceramic was in tension and cracked. And teach applying ceramics at elevated temperatures closer to operating conditions so that less spalling occurs. US Patent No. 6,224,963 to Strangman teaches TBC laser segmentation to reduce spalling problems when the coating section is mechanically worn or damaged. Therefore, important issues for applying TBC to turbine stages are to ensure maximum resistance to thermal loads, inertial loads and chemical corrosion effects, and to the maximum matching of different thermal expansion coefficients and mechanical Resistance to damage and spalling.

  Compressor performance: The efficiency of the compressor is important, and the stator and rotor blades will now operate close to these free separation conditions, gaining higher diffusion factors, higher rotation angles and higher blade loads However, the inherent BL control that can delay fluid flow-separation allows higher pressure rise per stage. In addition, the compressor ensures that the flow separation propagating between multiple stages (stator / rotor disk pairs) completes fluid-flow failure, surging / power loss and localized damage to machinery. Has problems that can lead to it.

Foil suction-on-face fluid-flow jets can be used to reduce flow separation.
The compressor rotor and stator blades are thinner and less cambered sections than, for example, turbine stage foils, so the addition of an internal flow gallery to allow fluid-flow harvesting for the jet Is a manufacturing challenge, but in general many central blade materials are close to the neutral stress axis, so some can be removed without much negotiated section inertia or strength. Of course, small flow ducts are sensitive to clogging and can still induce horseshoe vortices and still experience lift-off if not controlled. Smaller jet engines often use centrifugal type compressors in the high pressure stage before the combustor.

  Fan stage: Fan motor blades or actuator discs are hot at a high number of thrust ratios, eg 5-10. 1-cooling to bypass the engine core, torque from the LPT to increase section thrust- A blade-type fluid-flow structure that typically converts to section thrust, typically made of high strength titanium or fiber reinforced plastic (FRP). For example, FRP blades made of carbon fiber and epoxy or other resin (and even metal blades) are subject to LE corrosion from rain, hail or sand or other inhaled small FOD objects, and even scattered volcanic ash. It is easy to generate and is contoured very three-dimensionally for the most favorable aerodynamic performance and laminar flow.

  Examples such as the 123 ″ /3.1 m diameter GE90 composite fan are recessed to provide a capability to absorb and survive FOD objects such as corrosion protection and bird impact. bonded-on) A blade with a composite 3D-shaped titanium machined LE strip is used.

  The interface between the LE EPS strip and the aft composite structure can be developed by vibration or stress-induced edge separation or erosion, and is a point that inevitably has a small gap that allows unfavorable spanwise vortices. The preferred flush strip minimizes the painted surface immediately after the transition that can peel off during operation, impeding air flow and causing additional drag and energy loss. Provides corrosion protection.

  For example, all devices of serrated foil or body TE, such as Gliebe '240, Stephens' 291 item 13, are on the aeroelastic surface of essentially the thinnest foil TE under stress. It also introduces mechanical stress concentration points that can be sites for fatigue-crack initiation and propagation.

  Noise and LEBU: Cooling / Hot Duct Flow Mixing: Young's 319 is much more to increase flow mixing, break flow vortices and reduce flow velocity gradients and noise generation mechanisms in jet engine hot exhaust flow Types of sawtooth configurations and similar 3D devices are taught. Balzer '106 teaches an exhaust nozzle chevron extension to improve exhaust flow mixing so as to reduce engine noise. The Boeing 787 nacelles use Balzer '106 type saw blades to reduce engine noise, but the resulting flow is not on the BL attached to the aerodynamic body surface. Acting at the free stream boundary between the cooling and hot fluid-fluid streams, these vortices are therefore simply used for fluid-mixing to reduce the diverged acoustic noise spectrum. Such a configuration does not improve BL flow re-laminarization, but reduces drag but increases drag, as can be expected for vortex flows that simply induce vortex fluid-flow momentum and loss. It has been reported.

  Fluid Ducting at Engine Core: In patent application US2011 / 0300342, the metal substrate is surrounded by raised vertical parts (walls) and then machined into a prior art type top-coated ceramic TBC. An array of pockets or blind recesses that can be further modified by mechanical coining / deformation to form an overhang grip that is fixedly secured and designed to maintain and stabilize this TBC. Can be concave to form. This is a derivative of the prior art that “tils” the ceramic into smaller sections to capture and maintain the cracked section of the TBC, thus minimizing spalling and TBC losses.

  Lutjen's' 342 teaches that the lower flat portion 50 of the recess is clearly labeled so that it is perpendicular to the lip sidewall 54. This design works so that the taught perpendicular crossing of the mechanical section that is under load and vibrates (in other words, a small radius of mixing or transition) reduces fatigue life and provides a point at which material cracking begins. There is an issue of forming a stress concentrator. Excellent and differently formed sidewalls with the largest possible root radius form a stronger load-bearing beam extension from the load surface and also support this surface; Helps minimize vibration modes and bending or deflection, and significantly increases the additional local moment of inertia. Of course, large flow control surfaces that are curved in a simple or combined manner can withstand the force and inertial loads of pressure and resist aeroelastic effects, but having lip sidewalls is structurally efficient (all Lutjen's prior art is eliminated, making it useful to improve (size vs. total intensity at total mass).

The warpage stress induced by vibration is detrimental to reliable TBC “tile” attachment.
In addition, Lutjen's formed retaining lip items 28 and 28 'are typically the thinnest point in the final bounded smooth TBC coating (as in FIGS. 5 and 6), and therefore It serves to carry the greatest heat load that is made through the TBC from the hot gas above. Here, the concave side wall 54 of Lutjen's inherently straight side has a larger wall root radius and therefore does not provide minimal thermal resistance to the underlying cooling fluid or gas, which is the most favorable metal strength and strain. / Not the optimal heat transfer configuration to maintain the lip (wall top) metal area at the lowest possible temperature for creep resistance and the highest thermal stress. Lutjen '342 teaches TBC protection applied primarily to static ducting surfaces, but allows TBC to be added to other items that require TBC protection, Only the technical advantages are taught, not the absolute surface or morphological drag reducing properties.

  Wentherstrom US Pat. No. 4,076,454 teaches the addition of a blade VG on the inlet ducting in an axial compressor. He does not teach or claim reduced ducting drag as a feature and this VG is a fluid-flow that does not separate on the downstream blade without any drag reduction benefits in the ducting or diffuser section Is charged to act to maintain. Flow deformation from static rotor inlet ducting is taught while the vortex indirectly improves the flow separation characteristics of the downstream rotary compressor blade.

  Nacelle and adhering pylon: The entry of a working fluid such as a gas into a modern turbofan engine in a Boeing 737-600, eg, CFM-56, is finely processed by the surrounding nacelle and most nacelles Acts as an initial internal divergence-duct or diffuser to slow down the incoming fluid-the first stage fan section and the compressor stage make the cascade blade tips not supersonic and high loss Operate without generating supersonic or Mach shock waves. High nails / nacelle AoA, some nacelle initial internal divergent fluid-flow is separated from inner nacelle wall, which is a disadvantageous condition, or the amount control of diffuser flow used is limited to avoid this Or active suction control must be added to the relaxed flow separation on the duct interior surface before the fan blades. Cooling section ducting coming out of the fan section will move through the mixing duct that diverges on the inner and outer duct surfaces and is subject to flow issues such as Taylor-Gertler (TG) on the concave section. obtain. Crossing other aircraft vortex-wakes can also cause problems such as transfer flow adhesion and surge through the engine.

  Boeing 737-600, Airbus 319 and C-17 both teach modern examples of engine nacelles using large blades or vane VG at approximately 2 and / or 10 o'clock after the inlet LE outside the nacelle. However, as minimum flow disruption and turbulent loss are required, the external fluid-flow around the upper nacelle surface at high AoA remains attached, while on the attached pylon and under the subsequent vane. It will ensure that it flows properly backwards up. When cruising, these VGs do not require eddy currents, become at a minimum AoA, and minimize form drag, but always exhibit additional morphology and wet surface skin drag. Overall, such a configuration is not the minimum drag configuration that generates vortices to improve nacelle / pylon / blade / body flow interactions.

  Since the nacelle / engine pylon is yet another area of flow interface issues and drag due to interference and secondary effects, fairing is required to control drag and fluid-flow losses. This is true for all aerodynamic bodies and devices that are mounted outside the wing or fuselage, such as structures such as pylon mounted fuel tanks, wing tip tanks or other pods or VOR blade antennas. In these bodies and devices, aircraft pitch, yaw and secondary flow vortices can cause adverse lift, flow separation, dynamic instability and flow interactions and drag. These issues also appear in hydrodynamic examples such as hydrofoils with mounting legs, links, and the like.

  Leon, US 5,156,362 teaches a retractable blade type VG for engine nacelle flow separation control. This blade upper edge coincides with nacelle and stream flow during retraction. During activity, this VG surface is angled with respect to the flow and does not coincide with the nacelle surface and will induce drag during cruising, but this is a reversible and mechanically complex feature. This is why it is used. This blade VG, when deployed, has a high BL thickness at a height to obtain maximum upper-BL free-stream fluid-flow to induce a strong vortex effect.

  Improved energy efficiency and capacity for turbomachinery, devices and processes that contain Newtonian fluid-flow, process this flow in some manner of CVG-based fluid-flow deformation technology, and output this fluid-flow It is an object of the present invention to provide Processing refers to the addition or extraction of energy or work from this Newtonian fluid-flow and / or the deflection and modification of fluid-flow velocity, pressure and / or momentum.

The intent of this new integrated CVG technology embodiment is to be “green” to reduce energy usage and associated carbon dioxide emissions.
Unlike the prior art, the new technology, integrated CVG, is an effective VG design, especially in cascaded rotating environments with low drag at low AoA values. The integrated CVG effect can be enhanced with foils or blades to passively induce additional BL fluid-flow energy for larger suction-face aft foils, but the pressure-face gained thereby The use of fluid-flow, or other fluid source, allows the separation to be further delayed through the flow control path towards the suction face to benefit stall or fluid-flow separation performance.

  The CVG can be configured to output fluid-flow mixing and reduce flow noise without additional drag and energy loss. Engine nacelles, pylons, and other aerodynamic body interfaces and surfaces are areas where drag reduction and improved flow control technology are also helped by new CVG technology.

  Centrifugal compressors, homogeneously mixed flow type impellers and diffusers, fluid pumps, turbochargers, etc. are helped with BL flow control to minimize fluid-flow separations using a new integrated CVG technology This new integrated CVG technology reduces fluid-flow drag, flow separation / cavitation, and generated acoustic noise on the impeller and diffuser blade and the fluid-flow control structure.

  Improvements in flow ducting and, for example, engine s-ducts, are substantially equivalent to general Newtonian fluid-flow (both internal and external flow) in pipes or other types of fluid-flow conduits or surface limiting means. As a case, the CVG flow control method taught herein allows for adoption on walls, surfaces, pipes, ducts and any flow control structure currently used for prior art fluid-flow control surfaces.

  The novel CVG produces a continuous vortex without a significant energy consuming lateral flow structure and convects the maximum and selectable flow energy down the downstream fluid-flow surface side that resists separation It flows in the eddy current which tends. This beneficially alters any surface and BL fluid-flow to provide resistance to flow separation and lower absolute drag when operating in non-separated flow regimes and / or off-design situations. And provide an excellent way to demonstrate this reduced drag. The basic integrated CVG structure accounts for these characteristics and significantly improves the prior art in many application locations and embodiments when integrated on the surface with an engine or fluid-flow controller. Can be configured as follows.

All drawings are not to scale, but are illustrated in detail in the features of many alternative embodiments for illustrative purposes.
FIG. 1a depicts a portion of a low pressure turbine stator or rotor blade with integrated CVG. FIG. 1b shows a pressure-face diagram of the surface detail of the LPT integrated CVG, and FIG. 1c is a view from the suction or top face containing the optional blade-tip CVG and secondary CVG.

  FIG. 2a illustrates a further example of a low pressure turbine stator or rotor blade with an integrated CVG, where the root end cross-section cut is optional with a flow control jet with an extended suction-face and a step-vortex expansion groove An embodiment added in FIG. FIG. 2b illustrates an optional control-jet fluid source pickup with pressure-face CVG valley and / or tip collection point. FIG. 2c shows a cross-section of the angular suction-face-after-facing CVG step, including detailed airflow.

  FIG. 3 illustrates an LPT stator or rotor blade having a root hub fillet and is modified and omitted by an asymmetric extended CVG step configuration as well as a bounded hub end-wall CVG. The CVG chip is doubled and shows a peak.

  FIG. 4a shows an example of a suction-face portion and a cross-sectional incision of a low pressure compressor (LPC) stator or rotor blade with an integrated ogival version of CVG with options for additional jet flow control. The figure will be described in detail. FIG. 4b shows a portion of the LPC stator or rotor blade pressure-face that includes a pressure-face CVG valley and / or a control-jet fluid source pickup that is optional from the tip collection point. FIG. 4b also shows an Ogibal pressure-face CVG array version with other pitches and offsets from the suction-face CVG array.

  FIG. 5a illustrates in detail an example of a fan blade suction face with a metal LE corrosion protection strip and an optional tip elastic weight integrated lift enhancement tab (eLET) to remove tip loads. FIG. 5b illustrates in detail one example of a fan blade pressure face with optional internal CVG, elastically integrated lift enhancement tabs (eLETs), tip CVG, and an example configuration for additional jet-flow control. To do.

  FIG. 6a illustrates an optional flow control, cooling jet, and secondary CVG array, illustrating in detail an example of a cooled high pressure turbine stator or rotor blade suction-face portion with integrated CVG. FIG. 6b shows an optional CVG array with a flow control and cooling jet, a secondary CVG array, a TE pin cooling exhaust-slot array, and a TE cooling enhanced tab array with a TE pressure or rotor pressure-face.

  FIG. 7 illustrates in detail the centrifugal impeller with CVG integrated in the flow control surface and the optional diffuser vane.

  FIG. 8 details the engine nacelle, pylon, and vane device showing where the CVG can be used to improve energy efficiency.

  Figures 9a and 9b illustrate in detail a fluid-flow duct example with an added CVG array to improve flow and energy efficiency.

  FIG. 10a shows integrated CVG steps and ribs that are embossed on the duct surface and optimized with the integrated polygon structure on the indicated “inner surface”. These polygons are reinforced with a minimum material weight, composed of a large radius (not right angle) rib-base for high thermal conductivity and beam strength against the inner cooling flow, and the opposite of this panel The side has an external fluid-flow CVG step array (not shown), such as the TBC CVG in FIG. 10b.

  FIG. 10b illustrates an alternative version of the duct (or blade) surface of FIG. 10a with fluid-flow on this TBC side, with additional TBC applied and interlocked to the polygon array.

  FIG. 11a is a cutaway view of a combustor design in which CVG was used to provide lower drag and energy loss, and improved fuel injection and mixing. FIG. 11b shows an alternative embodiment using a modification of the ceramic body, wall and CVG array to form a rich-burn pore volume.

  The best mode for carrying out the present invention is an example of a turbofan jet engine, which has many typical features that can gain performance gains by applying an appropriately configured integrated CVG. Teaches various areas and application methods. Turbofan engines provide numerous examples for useful integrated CVG applications because they use numerous hydrodynamic surfaces that handle Newtonian fluid-flows to generate useful work and effects. This example is just one form of fluid-flow machine that uses gas as the working fluid, but most CVG methods account for speed, pressure, Reynolds number, fluid phase (gas / liquid state transition) and flow viscosity. Easily applied to many useful examples using liquid phase or mixed phase Newtonian physical fluids, for example, to obtain similar improvements for drag and separation / cavitation reduction by scaling the geometry to Can be done.

  Item 1 of FIG. 1a is an isolated low-pressure turbine (LPT) rotor or stator blade that includes a profile consisting of deep camber for reaction and shock and diffusion action, where a rotor or stator disk is typically used in a cascade device. The root-end of the stylized example of "bucket" is described. For simplicity of expression, this example is typically twisted and / or twisted and / or to provide a radially constant reaction velocity profile and secondary flow control from mixing rotor (reaction) and stator (diffuser) foils. Not tapered. Blade root fittings, hubs and tip end-walls, and adjacent overlapping blades and upstream actuator disks are also omitted for clarity, but in the final design as known to those skilled in the art of cascade fluid dynamics. Is used. Item 2 is the convex suction-face downstream surface and the concave pressure-face downstream surface is region 3. This fluid or hot gas arrives at a designed blade input angle that defines a local foil or surface-actuated AoA, and this flow is due to geometry and hydrodynamic forces at the LE stagnation line 4 and suction and pressure-face Divided above. In the case of a rotor disc case, after working on the blade foil (towards the suction-face side) and generating a force vector, the working fluid exits at the output exit angle designed at the trailing edge 5 (TE). . Blade lift, which is resolved tangentially around the turbine rotor axis, generates torque output from the input fluid-flow energy, and the resolved vector component in the rear axial direction provides additional pressure across the cascade section. Drag or energy that causes loss and disadvantageous momentum loss.

  The on-design input angle for the upstream input fluid source and the output angle for output fluid transmission after CVG processing define the peak amount of energy that can be extracted from the fluid-flow of the input fluid source in the cascade section, where Assume that the flow of this section at its operating point is configured for minimal energy loss due to flow turbulence, separation and viscous losses.

  With some flow conditions that are sub-optimal, e.g. lower Re numbers, the suction face will experience flow separation after pressure minimization, which will increase cascade losses, It will reduce efficiency and increase engine SFC. While crossing the concave pressure-face 3, fluid stress from centripetal acceleration can also induce energy loss and BL thickening, for example, from a TG vortex structure. Cooling is generally not required for LPT blades because the gas flow is significantly cooled through the HPT turbine section and the temperature is lower than, for example, a nickel superalloy blade material is safely handled.

  To help improve flow across the suction-face, re-activate the boundary layer, the BL streamline, so that fluid fluid-flow mass deceleration begins to cross the local surface due to fluid conditions It is beneficial to have sufficient momentum so that this streamline flows adjacent to the blade and is attached at an adverse pressure recovery gradient after the suction pressure-peak line 10. In order to provide more flow energy to the very lowest layer downstream of the BL on the suction face, the upper conformal vortex generator (CVG) array 6 is essentially integrated into the front of the suction face in the accelerated flow region or Built and designed and built, this structure accelerates a portion of the incoming free-stream fluid-flow energy into a pair of powerful counter-rotating vortices that flow backward from the array of upper CVG chips 7 Designed to transform, this can provide suction-face separation control similar to conventional VGs that cannot actually be used in such complex flows and small geometry environments.

  The integrated upper CVG valley point 8 is located in the cord direction so that the fluid-flow entering from the suction-face flow inlet 9 intercepts the pair of bifurcated angular aft-facing step edges 24 of FIG. Or become experienced. This high velocity flow is either parallel or tangential to the suction-face flow inlet 9 blade surface or foil design-intention and down so that this flow is along the top edge contour of the step. Since it cannot rotate sharply, it undergoes fluid separation (step shear separation region 27 in cross section of FIG. 2c) along and below the intercepting top edge of this step, all in the lower fluid-fluidized bed.

  Such an intentionally angled step-down flow separation mechanism is such that the separated lower energy and the bottom BL draw fluid-fluid mass part along the step bottom edge and on the upper CVG chip 7 side. The flow begins to wind in a confined and free-flowing step-vortex, item 25 of FIG. 2c. The step-vortex consisting of the incoming fluid momentum layer at the bottom of this sheared or broken lowest energy then meets and counters the opposite rotating vortex from the other side of the tip, which Along with the surface, it flows backward in the filament state of a counter-rotating vortex pair tightly bound to the surface. The incoming non-shear flow momentum layer and the upper side, which are not entrained in this step vortex, will continue to be continuous as a high energy outlet flow 23 passing over the upper part of the step vortex structure, and then the initial downward velocity element Step exit-streamline reattachment position as currently higher energy and thinner BL with reduced transition turbulence, U-shaped vortex structure and drag loss in such downstream BL region between CVG chips Reattached downstream to the surface at 28 (FIG. 2). Thus, the CVG step geometry acts as a “BL-slicer” to generate beneficial vortex flow, but also provides a controllable BL relaminarization effect downstream of many step widths between chips. Especially for surfaces that are not deformed with zero and low positive and negative AoA.

  This is an additional drag reduction mechanism where the traditional VG does not appear, because the traditional VG increases the drag at zero and low positive and negative AoA values, where the VG AoA expansion capability is not active. It is because it has been. The approach BL flow velocity vector diagram 33 shows a normal BL slope from a low surface velocity, increasing higher in the BL. Downstream of this step, the exit BL velocity vector diagram 34 shows that these lower BL layers are separated into step-vortices and have greater velocity and improved adhesion than the lowest entry layer that is discharged through the CVG tip vortex-pair. Indicates that it has performance. The conceptual top of the BL or free stream is shown as streamline Vtop.

  The CVG step-vortex 25 is continuously predictable along the optimal mass-accumulation length and angle and flows backwards in a controlled manner, e.g., captured by a long spanning after-facing step. It is different from disordered vortex flow. The primary tip-vortex pair of the CVG tip is very strong, geometrically stable and efficient from the total shear flow region of the fluid sheet that intercepts or traverses the CVG step along the width of the embodiment. Harvest fluid energy, fluid mass and momentum. The filaments of this CVG tip-vortex pair can also affect the downstream BL in which they are enclosed, break the formed fluid-flow separation bubbles and structures, and depending on the foil design, blade stall- It can work like AoA with a higher conventional VG in that AoA can be significantly extended by about +5 degrees. The adjacent region of this BL is affected by the passage of an active CVG tip-vortex filament, and the extra fluid-flow energy tends to suppress the U-shaped vortex and this adjacent BL region from becoming thicker. It is in. Such CVGs extend the control range of AoA or local fluid-flow surfaces that can be processed with reduced energy loss from the reference surface configuration.

  Up to the separation point, the blade surface design of this new technology will have a “normal or ideal” geometric surface design that ensures efficient fluid-flow entry, and before this step any upstream Note that it does not induce additional drag or horseshoe vortex. A ramp-style, wheeler or blade-type VG that attempts to generate vortex at this point must deviate from the correct or ideal blade shape, and is a constant distance within the higher BL flow while generating drag. It will only attack inefficiently.

  Because the integrated CVG element or array can efficiently define the desired LE entry surface or foil geometric design for new design criteria after this step as well as the ideal foil design. Surface design will efficiently obtain this surface with such new integrated CVG design intent. In this manner, the newly designed foil or surface becomes the correct fluid-flow setup in the critical laminar flow LE section with respect to the original foil design, and the aft section is reduced inward by the step offset. For added CVG to foils or surface designs not formed or tuned for CVG addition, this LE entry section is effectively thickened by an additional CVG array film / step thickness, for example, twice this application area. ,Collapse.

  Conformal eddy current generators are processed by working on the lowest boundary layer across the aft-facing step (at a certain height), and even with extremely high centripetal acceleration and secondary flow faces above the BL level, It produces a chorded, continuous primary tip-vortex filament that is contiguously bound by these central chordwise low pressure joint stagnation lines so that it is in close contact with the downstream blade surface.

  On a helicopter rotor blade with 1,200 gravity radial tip acceleration and 700 fps velocity, the CVG tip vortex-pair stagnation line captures surface dust and on the blade with a strong radial force and other secondary air flow face As it remains in the cord direction, it effectively “prevents” this dust and the lowest BL flow, which completely removes dust from the blades without using this new technology, CVG technology. Is removed through flow visualization. Such a strong step and chordal vortex flow distribution is how the CVG efficiently transports energy from the higher entering fluid-flow momentum layer and spreads in the chord and span directions to form a flow separation bubble. It will be described whether it is useful to control an arbitrary aft region to be separated (for example, on the trailing edge 5 side).

  Primary CVG tip-vortex pair and step-vortex flow will have many associated secondary vortices and eddies that tend to make pressure and momentum similar, flow shear is a CVG structure and step, and This structure and step aft are minimized.

  Along the CVG step, dust accumulation teaches that the step face and base are also stagnation regions, and some lowest level lower momentum BL flow transports the primary tip-vortex pair Once separated, this residual higher, higher energy and higher momentum layer is slightly downstream so that it reattaches as a new, more active downstream BL trapped between the CVG chips. Teaches that an efficient flow path can be found. The primary CVG vortex pair can be made small, can be in a geometric size range of steps and BL thickness, and is generally not exposed to free stream or secondary flow on top of the abstract BL Pay attention to. This is because the CVG vortex can be sufficiently submerged at the lowest level of BL, and this CVG vortex is at least more persistent in geometries downstream than those reported by NASA, for example, due to other mechanisms. It is allowed to be on the order of a reasonable and efficient size. There is no incoming flow loss-generated horseshoe vortex between the CVG elements in the array.

  Most other VG structures have high drag (eg protruding ramp type), are structurally sensitive (vane type) and geometric to a limited range of operable Re flow regimes It generates limited low-energy vortices (eg, dimples) that are constrained in shape and do not produce persistent and submerged vortices or are affected by secondary flow and effects. Prior art active flow control devices on blades, such as horned jets and synthetic flow jets, can re-activate the boundary layer to reduce flow separation, but energy loss horseshoe or It induces a kidney-shaped vortex, affects only a limited range of flow relative to the fixed point, is generally more complex, and has a significant drag reduction against the reference undeformed geometry Not shown.

  Reactivating CVG's BL region aft reduces the attack-free (low drag) angle of attack AoA by only about +5 degrees before the separation bubble eventually forms and drag increases while lift decreases. Allow the blade to expand. Such an improved AoA extension of the A-curve occurs in other test foils and teaches that this fluid-flow physics is well applied to blade geometry and Re number. Such improvements to LPT blades have a design rotation-angle of the new blade cascade design that is more compact and has a smaller Zwiel factor for turbine and / or compressor cascade designs with fewer stages. It is possible to increase).

  A more valuable feature of such new CVG technology is that blade drag is significantly reduced by about -5% to -10% at the same lift and AoA from zero incident angle closer to the stall angle compared to the baseline. It is a point to do. This is due to the fact that the reactivated suction-face BL is also thinned at a higher speed, thus generating less turbulence-fluid loss while generating lift. CVG array vortex flow and BL activation are passive and occur in a very efficient manner and do not adversely affect the designed blade drag performance, but reduce performance across the fluid-flow range Decrease performance.

  For the integrated lower CVG array 11, an example of a lower CVG valley section is indicated as 12, and also a blade foil profile so as to form an angular after-facing step in the same manner as the upper CVG array 6. Enter inside. This pressure-face has different chord pressure and velocity profiles, but the lower CVG valley section 12 is configured in a manner similar to the example in the upper CVG array 6 with respect to the upper CVG valley section 8.

  Through testing on the foil, some of the blade drag improvements improve the flow on the foil pressure-face and prevent the formation of the TG vortex from the stress due to the concave centripetal flow, for example, the lower CVG array 11 Moreover, the point that it comes out by including is taught. The lower CVG array 11 also acts to thin the downstream pressure-face BL layer, which reduces turbulence and drag.

  Although this blade can be designed to work with either one or both CVG arrays, the suction-face CVG array is a problem known in the main prior art of LPT blade suction-face flow separation. Have one of these.

  In a cascade, for example, a shock wave from a suction-face pressure recovery flow is a flow through the blade, especially if the thickness of the blade TE structure induces a blade-pass flow-choking and thereby a shock wave with constant fluid-flow. Can be disrupted. Intentional CVG vortex flow that affects Shock Boundary Layer Interaction (SBLI) with lambda-foot shock separation can be used to mitigate shock and energy loss on foils, fluid-flow control surfaces and ducts .

  Effective CVG configurations and designs benefit from the fact that they work well for a wide range of geometries and can be tailored to meet specific requirements. Tests show that as CVG geometry is changed, this result is generally within a range of smooth changes without fast fluctuations or singularities, in other words, they behave well with a large range of design conditions. It shows that. Since CVG always starts at the bottom of the BL, they do not attack the outside of the BL with any practical Re value.

  The vortex state starts with a Re number of about 300 in standard atmosphere, and beneficially about 30,000 is sufficient energy. From about Re 30,000 to 500,000 where the LPT blade can operate, the CVG can be configured to provide improvements. From Re numbers 500,000 to over 10 million, for example, CVG is very effective on isolated foil and body sections and hydrodynamic structures containing rotating components. The CVG step may be a small part of the BL height at the operating position and still produce very strong and useful fluid-flow control capability, but at the Re operating point, which is transformed into a very common case, It can also be usefully used as a larger part of the local BL thickness or even several times.

  A conformal vortex generator or CVG has (a) a low-loss approach configuration matched to the entry surface-flow streamline, and (b) such shear flow along the output surface, (c) accumulated. Step-Communicating to the exit point to remove vortex shear flow-Intercept flow-Inclined after-facing step to induce the lowest level of ingress fluid-flow to shear in the vortex And (d) broadly described as a fluid-flow deformation element designed to allow the incoming high energy non-shear layer balance to be rebuilt as a new downstream boundary layer with higher energy Can be done.

  The CVG flow-angular step is typically configured with an angle of about 22 degrees in the span direction (relative to air as the working Newtonian fluid) with respect to the streamline vector of the local input flow, but some performance It operates around such approximate nominal values with changes, and such exact angle depends on the working fluid conditions. Thus, the CVG step angle can be adjusted to be optimized for different local flow directions as well as integrated into the flow at the hub and tip end-walls and the like.

  The CVG step is typically paired with a chevron or triangular structure at the rear tip while the tip is facing backwards to produce a persistent and stable exit tip-vortex pair, and the CVG step It can be combined with a variable offset array of many adjacent CVG step edge structures having varying angles, step shapes, step heights and step lengths to allow deformation of flow vectors and states. This CVG design shape allows for precise control of fluid-flow in different respects for surface areas constructed with fluid flow. A CVG can be configured with a characteristic step height, length and angle for a given surface shape, and for example, a local angle of about 22 degrees for a 50 mm wide LPT blade cord, for example. Fluid-flow intercept, triangular shape, 3 mm step length, 100 μm (micrometer) step height, selected around the expected Re value and high velocity laminar transition region for typical blade foil sections May be located.

  These shape starting point values can be easily changed and optimally verified by a series of actual blade step tests and performance measurements, but due to their small size and operating stress, they are practical for additional CVGs in this LPT environment Not right. The CVG step height is adjustable with respect to the width range and steps against the design operating range of the Re value while refusing to make a reasonable level of incoming lower BL flow a primary chordal vortex. It is configured to generate a sufficient vortex state along the edge. Such a CVG design process is also beneficial for fixed stator blade arrays to reduce drag and increase rotational-angle capability before off-design separation with variable Re values becomes a problem. Can be used.

  It is known that a span step along the foil surface perpendicular or at 90 degrees to the flow typically captures a confused span step vortex and increases the drag by about + 5% relative to the reference unmodified blade. And the most preferred case is when this step is about 22 degrees to flow with about -10% drag reduction, eg when dismantled in the CVG segment, but these numbers It is not limited to. Interestingly, the test shows the worst case drag that is greater than the 90 degree (previous afterfacing step edge) case when the CVG step is about 60 degrees to flow and this step accumulated length is long. This is because, at some point, the step vortex is overdriven by the accumulated low energy fluid mass with step-vortex magnitude and flow capacity, and begins to expand to obstruct the incoming streamlines, so We show that this CVG mechanism is even worse than the linear spanning afterfacing step, which is disadvantageous to drag. Lower drag is a core design goal, but having the ability to generate both controlled increases and decreases in drag is a novel fluid-flow modification tool in many precise ways. So that it can be used as

  The mechanical and manufacturing sharpness and definition of the CVG structure is not particularly critical, but the step top-edge is “the sharper” (minimum radius) and the ingress flow is the minimum secondary eddy. More stable and predictable. The CVG valley can also be simply configured with a radius, and the CVG tip can also be configured with a radius or other geometry that is sharp or has minimal performance sensitivity. The bottom transition of this step relative to the output surface is at the stagnation point along with other secondary stress vortices and can be set with a suitable radius fillet that does not interfere with the top-edge shear function of the step.

  For both cast and forged, assembled or machined parts formed with any combination of processing, materials or manufacturing methods, both assembling and minimizing vibrational and bending mode stress concentrations during operation In order to relieve stress, it is beneficial to form the radius of the bottom edge of the step. At the top edge of this step, the body etc.-deformation rate and deformation line are typically clear.

  Positioning the CVG in a high acceleration and / or vibration environment is that they are spatially configured on the same opposing surface to avoid reflection points and structures consistent with the tuned vibration mode. Optimized. So a regular array on one face is optimized by adjusting the individual CVG elements, tip and valley positions, CVG step length (effectively defined pitch) and angle in a non-uniform manner. Although this reduces blade vibration response and does not enhance unwanted blade bending, coupled and excited vibration and mechanical resonance modes. This can also be done for both blade faces to cause increased fatigue issues so that the blade deformation rate is not consistently concentrated between the suction and pressure positions.

Item 21 of FIG. 3 shows an example of an asymmetric suction-face CVG “V-form” having a left-side angle that is more acute than the right-side angle, which makes the CVG asymmetric in a slightly different manner, Be able to handle BL flow on the side. This BL mass flow to the left side is effectively further narrowed and the step-separated BL flow to the left tip-vortex is consequently smaller and less with the left tip-vortex having a lower force. On the right side of this CVG, the broader intercept of the incoming flow means that the right tip-vortex will be larger and stronger to accommodate. The balance between the force and vortex state vector and magnitude between these two asymmetric counter-rotating tip vortices is changed so that they flow further on the left side on the suction face and they break up after TE As a result, the remaining clockwise swirl state magnitude is balanced and the blade inner and root ends are assumed to be in the position of item 1 shown in FIG. For example, this is matched to the clockwise “or polarity” of the regular effective blade vortex lift sum, as shown in FIG. Depending on the final structure of the residual swirl state, it is possible to affect the bottom or on the body lift coefficient C _L. In such a configuration, when the pressure-face CVG is changed in the opposite direction (in other words, the CVG left side is wider when viewed from above), this is also effectively induced to wake-circulation lift - now applied aggressively vortex sum, increasing C _L. Drag reduction due to relaminating CVG BL is altered by small vortex position variations, but essentially the same reactivated mass flow occurs per unit width of the BL entry width, Note that it is still valid among CVG chips. The passage of the modified tip-vortex pair affects the streaming vortex conditions that occur in the BL regions that are immediately adjacent to each other and changes the combined lift vortex states from these regions.

  FIG. 1c shows a close-up detail view of a set of CVG items. The triangle represented by the vertices A-B-C is an example of a V-shaped CVG. As an example, the BL entering from the width A-B is divided, and the cut lower BL fluid mass is determined as step A. It moves backward along both -C and BC, and is operated to evacuate it with a pair of vortices that flow later from tip C. If a CVG is used as an additional example, for example on a helicopter LE EPS system, the smallest and most reasonable CVG element can be a CVG section of width AB, with suction and pressure continuously mounted around the LE section. -Includes a face CVG and can then be used as a combined array of many of these basic CVG structures. Simply, a CVG is typically made of an array of many combinations of CVG tip sections that can be mounted adjacently on a hydrodynamic body to alter flow. Small practical gaps between attached CVG elements have minimal effect compared to CVG effectiveness and performance improvements. Additionally, these larger CVG arrays are configured to be convenient to handle, apply and combine alignment properties and layers that exhibit wear as they corrode with fluid-flow.

  FIG. 1a describes the individual CVG elements as basically triangles, but this example is merely for ease of illustration, and in fact the most preferred performance is used for NACA low loss diving inlets. With step edges in a fundamentally ogival form. These NACA inlets also generate edge vortices to slow the inlet flow but have slightly different geometries and are not arranged in an array to reduce morphological drag or reactivate BL And very different from the new integrated CVG technology, except that vortex flow and optimized hydrodynamic geometry are used, with a step height several times the local BL width .

  The Ogibar CVG configuration typically follows a slight upstream position and more acute angles compared to the triangular step line, so that it deviates from the triangular step-line when approaching this tip. This extends the limit of the usable upstream surface of this position-cumulative step confined by a defined aft-facing step-vortex flow. This incoming separated fluid-flow mass accumulates along an angular step, and the aft section tends to contain more mass, increase the vortex magnitude and velocity, and the incoming fluid-flow Tend to grow further. If the step vortex grows too large from the shear fluid mass, this tends to affect the non-shear step that flows out at these locations—the primary step—the vortex structure 25 is further collapsed and the external step— There is a tendency to extend the vortex layer or to adversely break this step vortex to some components. Step-vortex 25 in the cross-sectional view of FIG. 2c shows a slightly upward extension to emphasize the effect of this vortex location over step height and geometry.

  This optionally provides a step-vortex expansion groove 13 formed in an optimal position under the step-vortex path to accommodate the step-vortex extension by fluid-mass accumulation in some embodiments. It means that it is beneficial to do. This is an obstacle and energy loss to a non-shearing outflow that is reattached as a new BL downstream for a given step height, excessive impact outside the growing step-vortex diameter To avoid. In CVG chips, these extended grooves (or other shaped trenches) can be merged or paralleled in opposing steps to reduce deformation at higher fluid-flow. The eddy current expansion groove 14 can extend by an aft amount and can provide a guide for the flowing tip-vortex pair. This vortex expansion improvement allows the separation of a larger mass of fluid-flow entering at a given step height while allowing stronger downstream BL reactivation and tip-vortex flow. Although structural impacts of these material removals are considered against foils or aerodynamic / hydraulic surfaces, in many cases, for example, assembly of 3D surface structures, which are forgings, is a section inertia cross section, Stiffness and surface mechanical properties can be improved. The step-vortex 25 has many secondary flow structures and eddies, such as an upper step eddy structure 30 and a step shear-homogenization eddy 32 that act to balance inertia and shear forces.

  Adding the optional step shear guide 35 section as an optimally shaped and assembled ridge further suppresses the step shear-homogenization eddy 32 and lowers the flow loss from the eddy or secondary vortex. And helps to form a spatial cutoff edge for backward expansion of the step-vortex 25 with variable Re conditions.

  In the additive CVG embodiment, the replaceable additive CVG EPS material can be elastic heavy integration, plastic, resin, metal, metal film, ceramic coating substrate, carbon fiber, carbon-carbon, silicon carbide or metal fiber matrix or ceramic metrics composite A material (CMC) or other material combination is applied to a composite or FRP material or metal helicopter rotor blade, or vane LE, etc., and the expansion grooves 13, 14 are in partial height steps and CVG alignment marks Along, for example, it can be molded or integrated into the foil or body surface with either a suction or pressure CVG step. The additional CVG EPS film can then be applied in mechanical alignment to these integrated CVG characteristics to generate a combined step characteristic and CVG functionality. The FRP (composite) surface or, for example, a metal rotor blade or vane / stationary foil LE can be integrated into the LE by any assembly means, in which case corrosion or paint damage from dust, rain, etc. is an important issue As such, the combined CVG combination with add-on and field-exchangeable additional CVGs further protects the LE surface to maintain energy efficient laminar or low turbulent flow. preferable.

  CVGs cascaded in adjacent aerodynamic spaces must generally provide the most favorable combined benefits due to eddy current interactions. In particular, if not properly separated from the rotating surface, vortex flow and flow must be tightly controlled spatially so as not to interfere, or separated in the flow direction to minimize disturbances. Wake interactions from upstream stators, rotors and other transition disturbances are less problematic in performance because these are larger structures than CVG tip vortices and are typically outside the BL, and flow is limited to extreme Re In order to be able to operate efficiently against the value, the flow can spread across a number of small CVG elements that can “take” or absorb this vortex, rotational or shock flow energy. Periodic oscillations measured on helicopter blades only about 30% through the flight envelope and NP rms deformation reduction teaches that CVG can operate very efficiently through flow perturbations and large periodic flow extremes of AoA .

  A controlled amount of fluid mass in the lower BL layer can be effectively separated from the incoming surface flow (and not accepted by the CVG tip-vortex pair), and this can be a porous aerodynamic surface or a suction stripper Note that using step edges or slots is an effective target for active suction BL control systems. Many prior art active systems have been abandoned due to clogging problems, and the CVG used in this position for BL control is dominated by the addition of CVG tip vortices to extend the surface control effect , Again comes to lower the drag. This can be shown by using an attached CVG on the LE of the deep-codefoil LE-like wing in front of the Piper PA-31 Navajo aileron, which gives the Aileron control authority at the wing stall. This is to improve, lower aircraft stall speed, and increase cruise speed. This is an example of a non-rotating fluid-flow environment such as an LPT / Fan / LPC stator, whereas a helicopter rotor or propeller / prop-rotor has a step length of about 20 mm for a foil cord of about 180 mm. Is an example of rotating fluid-flow control, such as LPT / Fan / LPC rotor blades, utilizing a 300-500 μm step height but with different stiffness, aspect ratio, etc.

  In combination with LPT rotor and integrated CVG that can be used additionally for stator blades and other methods of controlling integrated flow, fluids that add or jet fluid-flow and BL momentum in or after the CVG step. -Use a fluid jet. These jets may be active from a fluid pressure source, such as prior art synthetic jets, or more after being properly routed to the suction side surface via an array of paths, passages and plenums. It may be foil pressure-face fluid incorporated around the high pressure or lower face CVG array 11.

  The cross-sectional view of FIG. 2c shows an aft angle jet fluid injection port 37 and / or measurement orifice that can carry fluid-flow at an appropriate pressure and flow rate from an injection plenum 38 to an output surface such as 2. The addition of a low drag fluid-flow injection cavity 36 at the surface after the after-facing step edge 24 and between the CVG tips is an optional feature and improves fluid-flow performance. Adding a fluid jet in this manner with an aft angle (advancing into an optionally formed cavity) of the outlet high energy flow 23 to suppress jet-lift-off with high blowing and flow momentum ratios. Utilizing a portion of the lower velocity vector helps to spread the jet fluid stream in the lateral direction and in the flow direction. The jet-jet is such that the contoured form of the fluid-flow injection cavity 36 and the branching outlet fluid-flow branch further to the BL reactivation capability (as in the prior art Coanda effect or slot blowing technology). Allowing the added energy of the fluid to be placed at the lowest BL position close to the surface, the best performance is when there is minimal velocity difference / shear and turbulence in the merged outlet high energy flow 23 It becomes. The advantage of combining CVG with the jet or suction port is that such an inherent drag reducing CVG structure can be used efficiently with increased flow, further improving fluid-flow performance.

  Since the aft angle fluid injection port 37 is under the outlet high energy flow 23, the dynamic pressure here is lower than the BL stagnated at the lowest level, and the designed jet mass fluid-flow volume is A low pressure at the injection plenum 38 can be provided efficiently. Due to the effect of the lower outlet high pressure flow 23, lower pressure flow and larger volume capacity are allowed for the larger sized jet fluid injection port 37 and are less subject to clogging with debris. It is also possible to use a number of example jet fluid ejection ports 37 arranged on this surface or arranged to transfer into one or more example fluid-flow cavities 36 between CVG chips, Because of the selection specification, there is a larger fluid-flow that spreads in the lateral direction, and can still be used even if it is partially occluded, and there will be other alternating and extra jet orifices active.

  Such jet flow enhancement can be used to utilize additional fluid-flow energy to help control BL separation and drag, and the injection plenum 38 can be a pressure-face CVG valley section 12, or Low-drag fluid pick-up optimally close to the high-pressure stagnation point, such as a filtered compressor bleed or auxiliary air source, or a pulsating acoustic pressure source, or even a net-zero mass-flow method It can be transferred by a pressure-face fluid transmission port 39 located at point 40.

  Using a low drag fluid pick-up point 40 as a suitable pressure fluid source is an example of beneficially coupling the surface of other parts of the 3D fluid-flow structure, and the size of the port and plenum is the pressure difference. It is configured to provide a correctly measured fluid-flow. Additional fluids for jets-Jet fluid momentum can be fixed or non-variable pressure if derived from a fluid source with variable off-design and Re values, with flow energy varying from surface or pressure with surface and engine flow and speed conditions Generally follows variable Re conditions without the need for any optional flow or pressure regulation to avoid jet-lift-off, which can occur if a fluid-flow source is used to activate the jet. To do. This pressure face fluid, which is effectively incorporated, acts as an active suction BL control on the pressure face.

  On the rotating foil or body surface, the example of the jet fluid injection port 37 is configured to be designated slightly outward at the plenum starting point so as not to accept heavier dust and debris flowing outward at the plenum, and A large angle or path deflection can be coupled to an example of an injection plenum 38 having a shroud-type or backflow entry port that causes the jet to rotate and enter and become unoccluded. Such inertia-separated dust and debris generally move outward in the centripetal environment (or due to flow pressure / momentum in the stator foil case) and then a suitable plenum rejection tip close to the TE. An orifice 41 is optionally discharged. The plenum rejection tip orifice 41 can be larger and centripetal acceleration to control the self-cleaning process by partially plugging the discharge orifice (without throwing away excessive fluid-flow) at a sufficient operating speed. As the rotor blades are decelerated to an idle state, a simple force-control mechanism opens this self-cleaning port to the maximum while fluid-flow is still ejected through the turbine stage. Allow damping of excessively large particle accumulation.

  A low drag local source of pressure fluid taken from the low drag fluid pick-up point 40 around the pressure-face lower CVG array 11 via the fluid transmission port 39 is a high momentum moving past the higher BL flow. It is configured not to take in energy fragments or dust.

  (A Jet Fluid-Supply or BL Suction Pair) Alternate Pressure-Face Configuration for Jet-Blowing is a Second Example of Pressurized Injection Plenum 38 Separated from the Example of a Plenum Transferring Suction-Face Jet This is a version of the jet fluid injection port 37 that is transported by the pressure-face fluid pick-up section 39 located in the opposite direction with a low drag fluid pick-up point 40. This allows, for example, a jet fluid pressure source configured to be separated from filtered compressor bleed air to increase pressure-face separation capability.

  These pressure-transfer blowing-jet methods additionally improve downstream BL momentum for both suction and pressure surfaces, and a further alternative is to recover additional lower energetic fluid mass from between the CVG tips. In addition, the fluid-flow injection cavity 36, the injection plenum 38, etc. are coupled to the fluid suction source to provide a downstream BL with increased momentum.

  A slot or 3D-shaped flow convection structure can be selected instead of a round hole for the jet fluid injection port 37, for example, and the method selected can increase assembly difficulty and mechanical integrity of the foil or blade. Consider. The injection plenum 38 prevents centripetal force induced pressure gradients from overdriving the outer CVG fluid-flow injection cavity 36 region or starving the inner CVG fluid-flow injection cavity 36 region. It can be assembled into multiple separated spanning sections while feeding the separated CVG regions. The size of the jet fluid ejection port 37 can also be varied along the blade span to further improve the fluid ejection flow due to the pressure gradient. To assemble the example injection plenum 38 hollow, material mass-removal near the body or foil centerline does not significantly reduce section inertia or bending strength, but reduces blade, turbine and engine weight.

  FIG. 3 shows an LPT blade connected in route 1 to a turbine hub wall 45 having a wall fillet 49, showing other possible combined variations of the CVG embodiment. Item 20 shows the longer CVG v-section in an array. Item 42 describes a CVG tip cut short in the span direction to widen the tip-vortex pair separation. This also includes a larger amount of included tip width BL that can flow and mix directly into the tip-vortex pair and be surrounded by the tip vortex to enhance this vortex.

  Item 43 shows a CVG chip that has been modified to also generate two wide spaced apart counter-rotating vortex pairs.

  In such a deformation, an additional set of CVG steps with a smaller acute angle and contained inside produces a smaller counter-rotating tip vortex bound to a larger outer tip vortex. This now widens the area affected by the two primary and two secondary streaming tip vortices.

  Item 44 shows an additional tip deformation that creates two primary tip vortices in the middle under the CVG step and then produces a smaller tip width at the CVG vertex with two small secondary tip vortices.

  In all these cases, the corresponding width of the CVG step in the span direction precisely controls the mass flow within each vortex structure while allowing a controllable flow effect.

  CVG structures and arrays can be used around the perimeter of LPT cascade 3D blade paths and entry surfaces, such as wall CVG array 46, to improve rotor or stator drag and flow. In a rotating rotor blade environment, a series of examples of CVG are disadvantageous for drag performance due to eddy current interference with angular secondary flow, but in multiple cascade configurations with optimal spacing and offset, or secondary flow separation In some cases for other purposes such as deformation, it can be used on the stator.

  A symmetric or asymmetrical second array CVG 47 (stepped down into the body) at the trailing edge 5 deforms the blade wake and lifts it because the blade wake is generally immediately on the surface before the TE outlet flow. / Can be used on any one of suction and / or pressure-face to improve vortex conditions. In the case of a rotor, these are less affected in the rotational environment than, for example, the CVG used as the second column close to the upper CVG array 6 or 11.

  Possible tip connection end-wall and blade path root-end blade root platform, constant radius type 3D ducting flow surface and fillet, CVG drag to reduce BL relaminization, and It can also benefit from reduced flow separation induced by secondary flow, such as blade vortex flow.

  LPT “squealer” tip end or outer tip shroud surface often wears and expands due to strong operating heat changes, and occasionally makes contact with the tip-seal tip-seal shroud and duct surface, polishing the tip path And designed to clear. There is a greater pressure differential and secondary tip flow at the tip-gap over temperature, and the tip-seal shroud surface has a BL and secondary flow that is driven by a high relative fluid-flow tip velocity.

  The LPT “squealer” tip end or the end of the outer tip shroud surface can use an integrated tip-end CVG array 48, with the tip designated downstream in the local relative fluid-flow direction, and This allows the removal and release of the adjacent low energy shroud BL and reactivation so as to reduce the loss and drag of both the shroud and tip structure. The tip-end of the tip-end CVG array 48 flows in the blade-tip pressure-differential pressure-face side, and this step-vortex is now placed across the tip end-flow. Collapse the blade tip-vortex structure as a more consistent and powerful flow structure.

  Turbine stages, surfaces and ducts now also have a fluid-flow large wet-surface region with a thickened BL flow on the suction and pressure fluid-flow face, integrated CVG BL relaminarization Operates to reduce morphological drag and fluid-flow losses and reduce wake momentum defects. CVG tip-vortex flow strength, surface deposition and velocity allow new mechanisms that allow continuous and rapid re-establishment of the flow deposited after periodic upstream wake disturbances. This is also similar for other flow sections such as compressor stages, combustors, ducts and the like.

  The LPT turbine blade design taught herein has lower drag and fluid-flow and energy loss, improved flow reliability, greater operating tolerance for off-design conditions, lower stiffness and greater per stage It can be used to optimize new turbine designs and configurations of rotor, stator and duct passages with rotational angles.

  Alternatively, these new technology blades can be configured with lower drag losses and provide improved engine drag performance and lower energy losses within current long-lived engine investments. It can be applied as a “plug compatible” upgrade element that matches the interface geometry and flow angle to the current turbine stage at service update intervals. Therefore, while a new integrated CVG type LPT design can take advantage of this new CVG technology, to improve the SFC of current engine investments, improve the low Re flow separation margin and lower drag It is also possible to provide older technology blades in the current LPT stage cascade, such as the CFM-56 turbofan engine, to create “plug-compatible” LPT blades that function and replace properly. Is possible. LPT rotors and stator blades are one of the lowest risk deformation areas in turbofan engines.

  Instead, these CVG array embodiments and techniques allow wind turbines (such as Godsk '259) where stall AoA and operating envelopes can be increased without increased drag, and indeed blade and surface energy losses can be reduced. It can be used for blades or other similar fluid-flow regions such as propellers. Despite the foil design, aspect ratio and stiffness etc. differing from these mentioned LPT cascade embodiments, an integrated CVG can also be configured on these fluid-flow control surfaces.

  Axial compressors: Axial compressor stages are very thin and fine-edged high-speed transonic foil bodies (reaction-buckets) to allow momentum transmission and maximum compression efficiency within the fluid-flow at each stage. Typically not designed). These foils or blade sections benefit from CVG applications integrated in the same general manner, as shown for LPT turbine foils. Extending the axial compressor rotor and stator stall AoA capability at on-design rotation angles is to improve compressor surge (and surface stall and separation) margins. LPTs or other turbine stages are not prone to experience as bad as such cascading failure or surge mechanisms of axial compressors.

  FIG. 4 illustrates a typical example of an isolated axial compressor blade body 50. Compressor Low Pressure Compressor (LPC), Intermediate Pressure Compressor (MPC) and High Pressure Compressor (HPC) pressure stages have varying blade lengths, varying routes, depending on disk area, local flow and pressure requirements It may have a tip diameter (or “compressor line”). The rotor and stator foil use slightly different geometries because the stator acts as a diffuser to restore stage pressure, but CVG does not have all these fluid-flow control surfaces as taught for the LPT stage. It can be used in a similar manner for gain-like gain.

  The suction CVG array 51 inherent in the axial compressor is essentially integrated or assembled on the front portion of the foil suction face, and this structure is one of the free-stream flow energy entering at the input rotation-angle. Is designed to convert the section into a pair of strong counter-rotating CVG chip vortices that can flow backward from an array of axial compressor suction CVG chips 53 and provide suction-face separation control similar to conventional VGs, This is because conventional VGs cannot be used as low drag or drag-reduction in such a rotating body fluid-flow environment. Similarly, the pressure CVG array 52 inherent in the axial compressor is integrated or assembled on the front of the foil pressure face, and such a structure is free-stream fluid-flow entering at an input rotational angle. Designed to convert a portion of the energy into a pair of strong counter-rotating CVG tip vortices that flow backwards from an array of axial compressor pressure CVG tips 54.

  The version of the integrated CVG configuration shown in FIG. 4 is generally a symmetrical Ogibal-edge triangular configuration in a repeating pattern, and these cross the span and end-wall of the blade path The steps in the fillet and the overall CVG geometry LPT surface treatment and embodiments can be configured and varied in the same manner as previously taught.

  Optional step-vortex extension groove 55, tip-vortex extension groove 56, and step shear guide 57 can be integrated into both faces to improve step vortex capability, as taught for the LPT stage. .

  Surge or flow separation margins are achieved by adding an integrated CVG that basically extends the foil stall AoA capability, along with detailed fluid-flow improvements, such as in the LPT stage, with extended laminar flow performance and drag reduction. improves. In addition, compressor improvements are affected by adverse pressure gradient flow velocity reductions and flow separation bubbles, especially in the rear suction-face region, with low drag fluid-flow injection capability within the lowest level of BL. It is possible by using the unique capabilities of CVG to provide.

  For simplicity, only one complete example optional fluid ejection cavity 58 is shown integrated and optimally configured between the CVG chips, and this represents more flow activation of the downstream BL. Is supplied with appropriately activated fluid-flow from a 3D-angular jet flow injection port 59 at a defined pressure and mass-flow velocity. This utilizes the initial lower vector of the exit high energy flow for the CVG step to avoid jet-liftoff at high blowing and flow momentum ratios and minimize any LE horseshoe or kidney shape vortex, And help to spread the jet flow stream in the flow direction. Numerous examples of fluid ejection cavities 58 and jet flow ejection ports 59 can be distributed across the foil suction surface and, in the example of an injection plenum 60, are coupled to a pressurized supply of jet fluid. The fluid transfer port 61 and the low drag fluid collection feature 64 may be coupled to the injection plenum 60 and / or the tip collection port 63 to provide a local jet fluid source. The jet and plenum fluid-flow increasing capability is configured in the same manner as the LPT stage. Also, fluid ingress from other sources can be selectively pre-cooled to increase fluid density, routed or tip connected to alternative jet fluid sources such as rear stage compressor bleed air, for example. This is possible with the example of the injection plenum 60.

  The tip-end CVG array 62, which is equivalent to the integrated tip-end CVG array 48 for LPT, can be used for tips facing the compressor tip-seal shroud even though the blade section is very thin.

  These improvements to the axial compressor generally reflect this method and configuration taught for LPT stages, and improved surge resistance margin, increased stage pressure ratio, increased rotation-angle, lighter weight Allow low cost compressor stage combinations. Since the compressor absorbs about 60% of the energy consumed by the engine, efficiency improvements at these stages have a significant impact on overall engine efficiency and engine SFC.

  Fan stage: The fan cascade, for example, typically operates at a lower temperature than the HPT / LPT cascade, requires a larger and higher CVG step height, and uses a fine LE section like an LPC or HPC blade. I don't have it. FIG. 5 shows the profile of a unique fan blade suction-face 70 typically provided in the blade LE region and protected from corrosion at the blade LE portion by a pierced adhesive titanium or other metal LE EPS strip 71. Detailed view is shown. In order to minimize the flow disturbance, the metal EPS transition 72 is in essential contact with the transition joint edge, but in operation, a very small gap inevitably causes a disadvantageous BL tripping opportunity. And corrosive debris passing through these component transitions can reduce fan cascade energy efficiency and further damage critical laminar flow performance over time, paint protector from blade surface behind LE And tends to corrode materials.

  A CVG treated blade 73 is shown on a pressure-face with a CVG EPS overlay 74, which overlays the current undeformed item 70 without any other blade deformation required for the current fan blade cascade. And 71 can be combined. This CVG EPS overlay 74 lowers the required engine power for fan blade drag and input torque and given thrust, and higher stall for improved response and resistance to flow collapse in off-design conditions Provide AoA and reduce the supersonic fluid-flow shock and loss with fan blade tip (by using CVG tip-vortex flow to disrupt SBLI lambda-foot BL separation mechanism), consumable and optional Operates on both suction and pressure faces to reduce blade erosion with certain field replaceable elements. Utilizing the CVG tip-vortex to disrupt the SBLI Lambda-Foot BL separation mechanism and phenomenon, any feasible to induce sufficient vortex conditions while also providing extended AoA and relaminating drag reduction Even fluid-flow vortices and Re can be performed on all other foils, blades and fluid-flow body surfaces.

  The CVG EPS overlay 74 can be operated at the operated step height, which means that the exit high energy flow backwards relative to the CVG step has a higher density than a fluid-flow such as, for example, air. And on the following post-step surface 75 with initial down-vector post-step flow, debris and sand etc. and not having enough energy to rotate down , Followed by a more elaborate blade body with a clear loft and outer centrifugal and secondary flow. The reduced surface corrosion effect on the paint and material after this step is feasible for CVG treated foil and body surfaces.

  Additional types of CVG overlay 74 are elastic heavy-integrated, plastic, metal, ceramic coated substrates, carbon fiber, carbon-carbon, silicon carbide or metal fiber matrix or ceramic with the required mechanical and thermal durability It can be made of matrix composite (CMC) or other material, formed by any molding process to aerodynamically match the current blade LE, and bonded to the blade or aerodynamic body surface. The CVG EPS overlay 74 can be formed as a single CVG element, but for large spans and curved LE blades, select a geometry section that can be varied so that the CVG is easily applied continuously in adjacent sections. Can be assembled with. Any blade fluid-flow discontinuities must be paired prior to CVG addition to produce the most favorable results.

  Utilizing an asymmetric or variable-pitch and geometric CVG structure allows the CVG flow modifying action to vary across the span, eg, in the region of subsequent local shock generation, the CVG pitch differs from the SBLI effect. It can become even finer around this location to produce the greater density of the tip-vortex filament example to do, and in particular does not concentrate solely on optimizing drag reduction. Reducing body fluid-flow impact allows for reduced energy loss and / or improved latitude in operating regime and on-design operating envelope conditions.

  The newly designed fan blade foil or body surface can be configured differently without the protective LE sawtooth shape linear to the prior art EPS components and to fully utilize the CVG improvement. This can provide some weight savings prior to applying the CVG EPS overlay 74 to obtain the benefits of CVG, since the prior art metal LE EPS section may be thicker than the blade body material. Yet another new design choice forms a partial step-height integrated CVG array in the LE volume that overlaps in alignment with the matched interchangeable CVG EPS overlay 74, which can be thinner and lighter. It is to be.

  The newly designed fan blades also include step-vortex expansion grooves 76, tip-vortex expansion grooves 77, step shears, which are added to the LPT blade, for example, with a pressurized fluid-flow source, plenum, jet, etc. Benefits can be obtained from the combination of guide 78 and fluid-flow injection cavity 83. These are shown as a single example in FIG. 5b on the pressure-face and / or they can also be applied to the suction face. These grooves and structures provide greater improvements and CVG alignment and alignment marks on wider cords without requiring excessive step height and CVG thickness and weight, and CVG EPS overlay 74, and / or , Allowing the possibility of additional separation control for any additional integrated CVG step structure gain. This also minimizes the step height effect on the downstream foil or aerodynamic body surface design.

  The integrated CVG and EPS strip combination, which reduces fan blade drag and blade torque input, for example, by about -10%, offers a significant improvement in SFC and efficiency, which is why modern fan disks are hot section nozzle thrust This is because the cooling bypass-nozzle thrust output is more typically 5-10 times or more.

  The replaceable and removable CVG EPS component of the LE design combination also better protects the following blade surface and, as LE wear accumulates, this component is one of the most sensitive parts of the blade. In order to disrupt fluid-flow and BL, replacement in the test state is valuable and helps.

  The newly designed CVG treated blade 73 can have a symmetric or asymmetric sawtooth TE CVG array 79 integrated in the cord behind and in front of the trailing edge (the tip facing the aft). The CVG step sawtooth shape integrated into the body does not adversely damage body strength, mass distribution, flutter margin and aeroelasticity in such a thin, high stress TE region. Body pressure-on the face, the fluid-flow can be designed to be close to the TE or not separated by the TE, so in this region the CVG has a thickening BL but is limited by the TE region surface thickness In order to work at the designed step height, it has a reasonable fluid-flow momentum.

  The upstream CVG EPS overlay 74 is generally expanded and moved slightly outward by the TE CVG array 79 when reaching the TE region due to the higher level of centripetal secondary flow and the CVG effect. I will provide a. In this case, in close proximity to the TE Kutta-Jawkowski condition to define and control the body wake fluid-flow structure merge, the moved upstream CVG tip-vortex filaments lead to effective body circulation-defined lift. , TE wake vortex state vector—cannot get an opportunity to unfavorably rotate in the span direction before being fitted to the whole. The TE array 79 adds a chip-vortex filament that is activated almost directly to the TE wake, and additionally uses an asymmetric CVG configuration, more particularly from either one or both of pressure and suction surfaces. Allow direct eddy current state vector matching with implied combination body-lift tip-vortex wake direction or opposite signal, allowing geometrically controlled CL changes at low AoA. In this manner, CVG can be usefully used to affect the body fluid-flow wake. The combination of these improved CVG EPS methods and performance improvements is also valuable for open-rotor turbofan concepts, helicopter rotors and conventional propeller blades that share a range of fluid-flow concepts and design methods. Integrated.

  This new TE CVG array 79 array is different from Gliebe's '240 patent, Fritz' 488 patent, Vijgen '665 patent, Shibata' 436 patent, Young '319 patent, Balzer' 106 patent, etc. Because this arrangement is a surface structure and treatment that is inherently compact and inherently within the body range and before the original body TE, and this arrangement (prior art that induces only eddy current energy loss). Unlike non-optimized non-surface vortexes) wake flow-mixing between aft-facing CVG tips to reduce BL fluid-flow loss and essentially reduce drag noise while using drag-reduction structures Acts to increase, change body-lift circulation, and pressure and / or suction Scan is because that can be independently configured for both. The TE CVG array 79 aft facing tips can be positioned and offset so that they effectively mesh immediately beyond the TE and minimal interrelation before they are mated in TE wake vortex conditions. Cause interference.

  The suction face can use the TE CVG array 79, but is less efficient at larger AoAs that induce a thick aft BL region with low energy or separation bubbles or fluid-flow separation. These CVG improvements, as taught herein, are more effective with non-rotating foils and surface bodies with Newtonian fluid-flow in the same manner to gain, and generally for any rotation. Can be used.

  The fan blade tip code section should be thick enough to use a tip-to-end CVG array 82, equivalent to the integrated tip-to-end CVG array 48 for LPT, at the tip facing the fan tip-seal shroud. Have. Additionally, the fan-tip to shroud gap change with temperature is less than the turbine section, and the tip-end CVG is useful in nacelle-ducting BL flow control on the surface proximate to the fan tip.

In many of the foil or body design, and _{C L,} and change the ratio of _{C L} versus _{C d,} in order to lower the _{C d} ratio, a lot of work attempts to use a well-known Ganitabu (Gurney Tabs) However, this theoretical work tends to inaccurately predict the impact of tabs applied to foils and bodies with Newtonian fluid-flow at actual Re values. An elastic heavy-integrated lift-enhanced tab, eLET 80, such as a 3D-shaped block, is shown coupled at approximately the middle-span of the pressure-face of the CVG treated blade 73 proximate to the TE. eLET 80 is typically but most preferably made with a portion of a span width of 15% to 30% of the total span, and fluid-flow velocity and lift contribution are important. Used from inside the tip on the rotating body. The eLET 80 is not limited to this value, but can typically be configured as a block, vane or dual-vane structure at a height between 0.5% and 3% of the local code width. The setback from TE to eLET 80 is typically about 0% to 500% of the device height, and the best results are for a setback of typically -100% of the device height. It is.

  The eLET 80 serves to generate a spanwise set of strong counter-rotating vortices trapped between the eLET 80 and the TE edge position. These transverse vortex filaments act on the suction-face TE flow, tend to deflect this flow downward at the TE, and change the local span section TE utta-Jawkowski condition. This additional TE downward fluid-flow acceleration beneficially changes the adverse suction-face pressure recovery gradient (which reduces BL turbulent zone thickness and drag), and effectively increases the local code AoA and lift. Act on.

  eLET 80 is implemented as a flexible, strong, low-mass elastic heavy-integrated material so as not to add excessive mass in the foil or body aft and TE sections, reduce stability, and not swing margins, Effectively transparent to the body placed under TE. In addition, essentially essential such as propellers, rotors and blades-due to the aeroelastic effect and vibration mechanics of the flexible foil, the non-compliant mass added to the TE region is Reliable without shear forces of distributed and non-concentrated local adhesive bonds, allowing a strong acceleration force to be distributed to allow sufficient load-sharing in the adhesive and not concentrating the adhesive at the forward slip point Cannot adhere well. For this reason, non-compliant materials (in other words, inelastic heavy integration) are problematic to add in such challenging environments and, once done, produce strong body material fatigue issues. The problem of vibration stress concentration and bending on the underlying body is generated. The creation of similar branching trailing edge (DTE) structures will face the same real-world challenges.

  The small length section of one or more examples of eLET 80 is that normally-unfavorably trapped spanwise vortex filaments have extended outlets where they must accumulate and exit fluid-flow mass And this typically occurs at a rate of approximately 1,600 Hz, which is typically noted as a fluid-flow diagnostic acoustic-signature when eLET 80 is used, and of a segment or section Teaching the new importance of vortex filament relaxation pathways using application strategies. In each instance of eLET 80, an additional improvement creates a partial section-cut that is mostly in the cord direction through the unit, and mechanical damage is limited to the partial section, effectively providing a rip-stop function. It is.

  The very slight angle to the form of eLET 80 that supports the inner or outer end is that the vortex filament outflow is added to or subtracted from the TE wake as an integrated vortex vector that generates the final body-circulation and lift. When aligned, it can be controlled in a direction that preferably deviates from one body end. The eLET 80 body, for example, bending slightly back on both sides from the center, allows the fluid-flow mass to be processed by eLET 80 while the central transverse vortex acts to increase wash flow to improve lift. In order to be controlled as a geometric part, the vortex filaments in the stream direction are allowed to fall out of the TE wake and balance.

  The eLET 80 can be used with or without the CVG EPS overlay 74 or TE CVG array 79, but for reasons of dynamic stability, combine at least the integrated CVG method and the CVG EPS overlay 74. It is preferable to use it. The TE CVG array 79 has been applied previously or can be used for sections between eLET 80 examples. The configuration of FIG. 5b, which is an example of a TE CVG array 79 with two shown between one example of eLET 80, is not limited, but illustrates that CVG can be configured across a span or part of a surface in combination with other features. .

  The tip unloading eLET 81 is shown as a small tab on the blade suction-face 70 tip TE and can be added to reduce the AoA lift of the code section in this foil area, and the tip from the pressure face to the suction face- There is no major hindrance to vortex flow, especially on the open blade, which acts to greatly deform the foil tip-vortex flow. In the case of helicopter rotor blades, this tab version acts to increase the spanwise load inside the heavily loaded tip, and the reduced and delayed local tip-vortex flows out into the disk flow and the blade vortex flow Less susceptible to interaction (BVI) transfer force loads, disturbances and generation of acoustic signatures. Loading the disc on the inside also reduces part of the lift bending moment and span deformation load due to the structure of the foil.

  eLET 80 LE forward-step entry face induced span vortex is closely matched to aft-step face vortex, thus challenging adhesive bond bonding capability with highly shocking fluid-flow vortex and Re value As such, there will actually be a minimum cord-wise pressure or aft force load that could not be expected on eLET 80. The inlet and outlet spanwise vortex filaments roughly balance and elastically protect the TE mass of elastically integrated TE from the expected ingress fluid-flow dynamic shock-pressure. The result is that the primary adhesion challenge is strong radial acceleration. Tests for aircraft propellers are generally possible, for example, as a 12ghp to 10ghp reduction in cruise SFCs, for example, for an approximately -18% reduction in energy savings for a Lycoming IO-540 engine and a Hartzell variable pitch (VP) propeller combination. Demonstrate similar material capability and performance deformation.

  The elastic heavy-integrated material applied as eLET 80 with these high accelerations and fluid-flow velocity fields is novel and semi-intuitive compared to the prior art, but is practically valid There are obvious improvements and new abilities that prove to be. In the case of in-flight surface icing, the eLET 80 material adapts, and here the load simply exceeds the ability to deposit moisture in a thin layer, allowing for enhanced ice transfer and constant detachment, most Large structural threats come from LE ice that deviates from the inner ice protection system that continuously strips small deposits before they significantly affect propeller performance. Adaptive and rigid deformation and elastic shape recovery characteristics and application methodology to resist section lip-stop damage to eLET 80 are new to foil and body surfaces such as blades, rotors, fan disks and propellers. Tolerant design capability.

  The IGV behind the fan stage and in front of the compressor inlet can also use add-on or built-in CVG to reduce drag, and the extended AoA capability allows mechanical IGV motion to be fluid-flowing. To ensure that it does not stall dynamically. Stator blades that lead to cooling section ducting that eliminates the swirling fan duct cooling duct flow can reduce drag and extend AoA, and can also use CVG. For example, additional IGVs in the compressor, combustor outlet, other aerodynamic supports and load bearing struts use CVG with the same advantages already disclosed for any fluid-flow surface. be able to.

  Increased surface flow from pressure-face pickup or other fluid sources such as cooled compressor bleed-air to improve fan blades, operating AoA and drag performance over the LPT cascade already noted It can also be used for newly designed fan blades with structures equivalent to LPT jet fluid injection port 37, fluid-flow injection cavity 36 and injection plenum 38 combined with larger fan blades. Such an integrated CVG array method of increasing jet fluid injection ports can also be extended to newly designed helicopter rotor blades, propellers and even fixed foil or vane surfaces with appropriate geometry scaling.

  Jet engine power-cores (compressors, combustors and turbines) using CVG for improvement (as prior art) LPT output-shafting (to drive the fan disk cascade for jet cooling duct thrust) Or similar power extraction stages) or like propellers, rotor systems, power generators, pumps or compressors used in industrial scale chemical processing systems such as cooling, natural gas pipelines or refineries In addition, it may be formed in a turbo-shaft configuration for driving an external load or transmission drive.

  HPT Turbine Blade: FIGS. 6a and 6b are representative views of an HPT blade 90 having a deep reaction-bucket type foil section and extract energy from the fluid-stream entering from the combustor to either the upstream compressor stage or Installed components that operate in the same manner as previously taught LPT blades to power a load, or a lower face CVG array integrated with an integrated integrated upper face CVG array 91 109. The integrated HPT CVG is configured for AoA expansion and drag reduction to reduce fluid-flow separation / turbulence and to mix-down the heat load. Integrated CVG made in the base metal provides the greatest HPT blade strength, but is new in the cascade as multi-part HPT blades can be fabricated to provide all the other required properties It is also possible to have a high temperature LE CVG array that includes a suitable silicon carbide or metal fiber matrix or ceramic matrix composite (CMD) 3D structure that works with the HPT LE of the design.

  For the IGV or first HPT stator and first HPT rotor disk, the combustor exit temperature is typically above the nickel superalloy melting point so that these surfaces are fluid cooled. The cooling jet root 93 is located at the LE of the stator and rotor blades and is supplied with cooling fluid (typically HPC bleed air at a cooler of, for example, -650 degrees Celsius) from the root cooling plenum 94. This source has sufficient angulated jets and flow mass to cool and protect the foil LE, which then provides additional surface cooling and heat into the foil wake. -Flows divided around pressure and suction face to reject flux and heat load. The foil surface is at the lowest local temperature and moves higher in the free stream fluid-flow at BL, causing the temperature to rise closer to the combustor peak temperature. Separation turbulence and fluid-flow Any excess turbulence on the surface of the foil or body, such as a separation bubble, is typically removed by mixing and cooling the hot fluid and temperature layers to cool the surface safely Increase the heat flux that must be done.

  Prior art foil surfaces include additional torsional galleries moving into additional downstream angular cooling jet arrays, plenum cooling inner-face skins, and inner pin grid 107 and TE cooling outlet slots 92. To be cooled. Such challenges must have jet surface cooling fluid-flow suitable without excessive turbulence and thermal mix-down, jet-lift-off, and efficient surface cooling and buffering from hot fluids Must be spread to.

  CVG provides a low drag method to provide a well-diffused cooling fluid jet that is effective at the lowest BL level, as used optionally in LPT bodies, simply to improve separation control . An aft-angular jet fluid injection port 95 or measurement orifice is located between the CVG tips 98 and allows cooling fluid-flow to flow from, for example, the upper CVG cooling injection plenum 104 at the rear surface of the after-facing step 97. -Can be carried into the flow injection cavity 96; Adding a cooling fluid jet in this aft angle manner into the formed cavity reduces the initial downflow of high energy flow in the CVG step to suppress jet-liftoff at high blowing and cooling flow momentum ratios. Velocity vectors are utilized to help diffuse the cooling fluid stream laterally and at the lowest cooler level in the downstream BL. The second lower CVG cooling jet plenum 106 also provides higher pressure cooling fluid to the adjacent blade surface and jet fluid at the pressure or lower face CVG array 109 in the same position as the HPT suction face. Examples of injection port 95 and transport to related structures.

  In order to cool the step-vortex mass-flow, an additional step-vortex cooling injection port 99 may be located at the bottom of the CVG valley. A tip-vortex cooling injection port 105 may be included in the base of the CVG tip 98 to provide extra cooling to the CVG tip-vortex filament to lower the heat flux to the downstream surface. Other prior art techniques such as internal tortuous cooling passages, turbulence generators, TE and chip “squealer” cooling exhaust and pin grid 107 are integrated CVG, internal passages and internal skins to cool the HPT surface. Can be used with flow. Efficient use of an optimized cooling fluid-flow with a lower flow mass to remove heat flux improves engine efficiency because compressor input energy is required to obtain the cooling fluid-flow. The surface of such an HPT stage can use any prior art oxidation reducing coating, other metallurgical methods, alloys for low and high cycle creep, and the like.

  Step-vortex expansion groove 100, tip-vortex expansion groove 101, and step shear guide 102 adjust for step-vortex mass flow capacity to balance the surface mechanical strength conditions and design step size. To allow, it can optionally be integrated with HPT suction and / or pressure CVG (for LPT section).

  Mitigation of addition from high heat flux can be provided by TBC, for example in the LE section, these typical ceramic surface layer coatings at the expense of increased mass and risk of coating crushing, loss of protection and surface loss. Reduce the surface thermal conductivity to reduce the flux. With integrated CVG and jet / injection cavities that provide efficient surface cooling and dispersion means, the foil downstream section of the CVG step does not seem to require much added mass and complexity in large areas of the TBC. is there.

  CVG can also be used to provide an additional low-drag jet fluid injection port cooling structure for the foil at the balance of rotor, stator end-wall and fillet in cascade passages and ducting surfaces. Yes, and adds the ability to cool below BL in areas of adverse secondary flow that resists collapse due to, for example, blade path-vortex. Fillet surfaces can use CVGs with jet fluid ejection ports on these contoured surfaces. The integrated CVG tip-vortex also provides a measure of SBLI control capability and can be configured to alter the passage-vortex, impact and secondary flow.

  A secondary integrated CVG array 103 on the pressure-face close to the TE cooling outlet slot 92 is used as the second row, for example, in front of the blade TE, close to the upper CVG array 91. Because it is less affected than integrated CVG, it can be used to minimize blade wake and improve lift / vortex conditions. A lift and TE cooling enhancement tab array 108 may be added before the TE cooling exit slot 92, such an option allows the modification of both blade active AoAs and with or without the array 103, the TE Along the slot 92 to help spread the cooling flow. The tab array 108 may use “bent” or angled tabs as shown. A secondary integrated CVG array 103 can also be added to the suction-face of the HPT blade.

  Intermediate pressure turbines (IPT) may also require cooling, which can be designed like HPT blades to improve cooling and drag losses. The CVG shown here and associated design characteristics can be integrated in any combination, example and location, along with prior art methods of blade and surface design to provide optimum performance. CVG treated HPT blades can be used again as an example in, for example, steam turbines, with usefully improved fluid-flow and efficiency, and LE surface coating materials are corrosion inhibitors that can also be combined with CVG structures. Note that it can be used for: Lofting and removal of corrosive particles and materials downstream from the CVG step also helps protect the downstream flow surface. In a steam turbine, the incoming fluid-flow is from a combustor / steam source, and no compressor is required, and the turbine power obtained in large quantities can drive other loads.

  Centrifugal Compressors: In the final HPC stage, many smaller compressors and pumping devices, for example jet engines, are centrifugal type impellers with compact, high compression ratio, weight efficiency, robust and low complexity equipment For this reason, this centrifugal impeller is used. There are many fluid-flow analogies between axial flow, mixing-flow and centrifugal compressors and pumps, and centrifugal blades and vane cascades on impellers route and tip diameters along the impeller axis towards the outlet. Increasing, the outlet flow can be fully radial or mixed (partially as an axial flow) into the downstream ducting and / or diffuser structure.

  Centrifugal compressors (liquid Newtonian fluids—pumps when flow is used) are suction-impeller tips, diffuser guides—vanes, vanes (or blades) and other fluid surfaces that cause fluid-flow performance problems and energy loss— Face flow separation can be experienced. Many impeller vanes are aft-swept at the exit flow angle so as to be less aggressive to tip momentum transfer and flow, so as to reduce fluid-flow separation stress at the blade exit-angle. The

  Flow separation or exfoliation bubbles in the low pressure region of Newtonian working fluids such as liquid water or ammonia will eventually cause rapid or supersonic bubbles from strong supersonic shocks and acoustic waves-structural collapse, cavitation and potential damage. While adding additional complexity, it presents itself as a transition from a liquid state to a vapor / gas phase with an entrained physical bubble structure.

  Adding a CVG integrated along the fluid-flow and streamline on the suction-face and other flow surfaces of the centrifuge allows control of the gas-phase fluid-flow separation bubble and previously cascaded Reduce the drag and turbulent BL flow losses. In fluid fluid-flow in the suction region, the fine CVG vortex-filaments grow and form with a fluid volume that drops under the liquid and vapor-pressure transition before they grow to a size that can cause cavitation damage. Intercept the vapor bubbles that do and collapse. This bubble collapse also reduces the resulting impact energy and acoustic signature, and the vortex filaments act to diffuse, reflect and attenuate the impact pressure and acoustic waves in the working fluid.

  FIG. 7 shows a typical open form centrifugal impeller surface and hub inner wall 120 with typical features found in most open form impeller versions. This example shows a central impeller inlet flow guide 121 guiding the LE of an array of impeller foils or inducer vanes 122 as the compressor rotates in a counterclockwise direction when viewed in the inlet flow guide 121. Have. The incoming axial fluid-flow is effected by the axial rotation of the inducer vane 122 and is accelerated and continued across the hub inner wall 120 and then exits radially at a higher momentum and speed at the vane outlet tip 128. Optional final output fluid-collection method or volute, ducting, etc. to transport fluid-flow (only one example described for clarity), not shown for clarity Cross towards the array of diffuser guide vanes 129. This example of FIG. 7 also uses an additional split vane 132 to not choke the incoming flow faster with the inducer vane 122.

  The integrated inlet suction CVG array 124 is located on the suction side of the inducer vane 122 section near the vane inlet LE so that fluid-flow is not separated on the suction-face of the vane (or not hollowed out for liquid). Can be inherent. The integrated downstream suction CVG array 125 can be integrated when impeller geometry and streamlines are allowed for beneficial effects.

  To reduce the flow loss on the vane pressure face on the opposite side of each vane with the integrated pressure-face CVG array 123, for example, in a manner similar to other locations from the LE to the LPT blade, It is also possible to integrate an integrated pressure-face version of CVG that complements these operations. The location of these integrated CVG arrays will, for example, follow the structure, logic and procedure for the LPT blade, and then in geometry to be matched to the specific impeller geometry, flow angle and position Optimized. The illustrated CVG magnitudes and angles are simply expressed for discussion and do not limit the actual design chosen and optimized.

  The pump root or hub inner wall 120 is a large surface area of primary flow BL and some secondary flow of concave and convex surfaces between the suction and pressure faces of the same blade or vane passage. This surface may be affected by flow or cavitation problems in the suction region, and CVG BL relaminarization also reduces drag or cavitation, and the integrated inner wall pressure-inner wall downstream integrated with the face CVG array 127 The pressure-face CVG array 126 can be used as useful here, and any CVG can be slightly angled to best match the local fluid-flow streamline conditions. This figure clearly does not show the vanes for the hub blending fillet, but when the vane hub route becomes a fillet, the integrated CVG can mix these fillets and other on the adjacent surface. Merged with CVG.

  Stationary diffuser guide vane 129 foil or surface controls separation bubble loss from strong fluid-flow pulses and wake exiting high-speed vane outlet tip 128, if present, and also with dynamic flow outlet-angle and diffuser enabled AoA Therefore, an integrated diffuser suction CVG array 130 can be used. Since the impeller fluid-flow into which the diffuser guide vane 129 enters is configured to be vortex free and operates in stator mode with non-rotating flow, does this vane have a higher surface curvature for a more compact diffuser section? An integrated diffuser secondary suction CVG array 131 can also be used to reduce drag. The pressure-face of this diffuser guide vane 129 can have a similar integrated diffuser pressure CVG array to reduce flow separation and drag. Static ducting and piping flow sections around the array of blending fillets and diffuser guide vanes 129 can also use an integrated CVG to further control drag loss and flow separation.

  Also, although not shown in FIG. 7, the moving structure of the open-form impeller tip edge 133 is closely matched on the open-form impeller to ensure the lowest reverse flow from the downstream fluid volume. There is a matching 3D fixed or bounding tip-shroud duct control surface. These vane edges are equivalent to the open-form tip of the axial flow blade, and the closed-form centrifugal compressor impeller is equivalent to an axial flow cascade with continuously interconnected tip-shrouds. The passage is fully enclosed.

  The tip-end CVG array 134, which is functionally equivalent to the integrated tip-end CVG array 48 for LPT, can be used for vane tips facing the centrifugal compressor tip-seal shroud and has a very thin blade section. However, small CVGs can operate effectively at high speeds with small gaps having high shear forces. The heat load at the centrifugal compressor is less than at the turbine stage, and the tip expansion gap can be closer with lower losses.

  The tip-end CVG array 134 induces vortex filaments on the shroud surface closely matched to control BL deployment and flow at the vane velocity as it sweeps the shroud surface. There is a corner. The tip-end CVG array 134 step-down may intercept the vane tip end LE and may or may not cut, and in the form of a step that does not cut at the LE, the unique tip for the shroud seal gap is , CVG step-down is maintained at the tip LE as local gap flow occurs downstream of LE. As the compressor impeller of FIG. 7, the vane pressure-face is on the right side of the tip-end CVG array 134, the suction side is on the left side, these CVG tip-vortex filaments are on the left side along the tip code, and this Pressure-face suction-flow at downstream-distributed positions in the face direction and normal foil or tip-vortex flow on the body surface in the same direction at the body tip TE such as the tip corner joint of items 128 and 133 Occur. By applying a higher mass-accumulation step angle to some tip-end CVG arrays 134, the member (such as 60 degrees) passes through the tip-shroud gap and seal caused by pressure-face fluid. Constrained by these steps to act as a flow obstruction for the lost energy loss flow, it further allows the formation of overly large step-vortices.

  The bounding tip-shroud duct control surface can also have an array of CVGs provided on the surface in a radial or spiral pattern, for example, to control local BL flow under the influence of vane passages, and these are It can be used with or without the tip-to-end CVG array 134 and is formed such that this CVG pitch is not synchronized to the vane pitch, so as not to produce a consistent high-pressure wave or acoustic signature. With additional flow attachment capability, the angular additional flow-control jet 135 can be added after the CVG step to increase the momentum in the lower BL, and because the upstream impeller surface-flow is at a lower pressure, The pressure fluid source for this is taken from the compressor output flow and ducting into the plenum of the impeller core capable of distributing these fluid-flows on the surface CVG and through the impeller shaft, as required for the 135 example. (And can be cooled) and done. In the case of compressors and turbines, such injection jets can distribute cooling fluid derived from the higher pressure fluid source being cooled. Examples of optional step-expansion grooves and / or step shear guides can be added to the impeller, but are not shown for clarity on the drawing.

  A roughly centrifugal compressor can be reversed, for example, to operate as a radial inflow centrifugal turbine. In this case, the impeller torque input becomes an output, the suction and pressure faces change, and any CVG array can also be modified to provide the desired BL and flow variation. As a centrifugal or mixing-flow turbine, an example of an additional flow-control jet 135 can be used for surface film-cooling, for example HPT stators and rotor blades, as well as flow adhesion improvements.

  In a closed-configuration impeller, this tip shroud is connected to all vane tips to form a closed vane passage, in the same manner that CVG has already been discussed, for BL and separation control. All these internal flow surfaces and tip seal labyrinths can be used.

  Integrated CVG treatment for centrifugal vanes, impellers, and other fluid surfaces allows for increased inlet and outlet-flow rotation-angles, new, more compact and lightweight compressors, turbines, pumps, turbochargers And similar fluids—allowing the design of fluid structures or mechanically—on current designs with improved performance “drop-in” placement impellers, suction-faces or fluids— It can be used to simply reduce flow energy loss, TG vortex on concave face and BL thickness loss.

  The integrated CVG also has other centrifugal or mixed-flow type fluid-flow pumps, turbines, propellers and industrial processes-compressors such as gas compressors (eg ammonia cooling, natural gas pipeline compressors), water Useful for jets and pumps or water or other liquid turbines.

  A turbocharger is an example of a centrifugal turbine that uses a pair of centrifugal flow compressors and turbine impellers to extract fluid-flow energy and add this energy to the fluid-flow of the centrifugal compressor. The device can use an integrated CVG that is tuned for local flow conditions as a new design to improve efficiency and operation.

  Nacelle structure: An engine nacelle is an example of a generally cylindrical fluid-body that is attached to a fuselage or vane via a pylon, attachment device or attachment link that has a mutual fluid-fluid effect. On such an attached flow-body, any adverse pitch and yaw against the incoming fluid-flow can generate considerable drag and turbulent flow due to, for example, flow separation on the downstream suction surface. obtain. The engine nacelle is integrated with the engine inlet and outlet fluid-flow to ensure correct inlet and outlet conditions for the enclosed engine.

FIG. 8 shows a generally cylindrical nacelle body 140 attached to a vane body 141 having an attached pylon 142. In the turbofan engine example, fan blade cascade 143 is shown at the nacelle inlet after duct diffusion has occurred at the nacelle LE and the inlet cooling duct section.
An integrated nacelle LE CVG array 144 is shown in the LE to improve flow adhesion and reduce drag at both the nacelle inner duct and / or outer surface. This LE CVG array 144 may also increase with superposition of matching and replaceable EPS CVG elements when surface erosion and / or durability becomes an issue.

  Further integrated fan inlet CVG array 145 is shown to improve duct flow into the fan blade cascade tip, reducing the need for active suction BL control at the fan tip inlet location.

  Similar integrated CVG arrays can be designed in both faces of internal cooling ducting to ensure that flow separation is avoided on convex and concave duct faces and turbulent BL drag reduction is minimized. . These integrated ducting CVGs allow higher duct surface 3D curvature or shorter duct and engine size for new designs. A series of CVGs can be used on these large surfaces at appropriate intervals where the chip vortex filaments are expanded before they explode or BL flow results in separation bubbles or excessive thickness loss. This defines the closest suitable CVG interval and hydrodynamically defined separation. Since most modern nacelle new designs are molded with composite structures, it is easy to combine integrated CVG arrays in design and fabrication for improved energy efficiency and performance.

  In the cooling duct exit nozzle, an integrated cooling duct exit CVG array 146 on the external and / or internal surface is provided in front of the local cooling duct TE in order to improve drag mixing, cooling exhaust and fan exit noise signature as well as drag reduction. It is also possible to be inherent. At the hot section nozzle outlet, a similar integrated hot duct outlet CVG array 147 can be used in front of the local TE and / or exhaust cone to improve flow mixing and eddy breakup and improve exhaust noise signature with drag reduction. 148 can be integrated into the external and / or internal duct surfaces. To break strong hot exhaust cracking, the additional low drag thin cylindrical ring of eddy breaking CVG array 149 allows the vortex filament to transmit more acoustic noise and shock to the wake transition. Before being evacuated, the vortex filament is directed into an expanding hot exhaust eddy to break up and destroy the eddy, for example, an expanded exhaust flow stream between the exhaust cone 148 and the hot section duct TE Can be added. With the support struts for the eddy breaking CVG array 149 and exhaust flow, the turbine aft support struts can also have a CVG array integrated to add additional vortex filaments for exhaust noise operation.

  The nacelle attachment link or pylon 142 uses a pylon LE CVG array 150 added to reduce drag and improve flow around the (mainly vertical) pylon surface using fluid mixing fillets on the support vanes and nacelle body. Can also have. The vanes may have an integrated vane LE CVG array 151 and a secondary vane CVG array 152 (especially at the pressure face).

  Other structures attached through links or pylons can also use CVG to control flow separation during flight, eg for closed inlet flow-body such as fuel tanks or weather-radar pods etc. The front body is a nose chip such as a fan spinner 153. An angular CVG array 153 can also be used because 153 eventually rotates with an angular inlet airflow. The nose tip may have a nose cap that matches a suitable angular CVG or may be designed with a nose CVG array integrated to reduce drag.

  These attached flow-body structures are also in the form of closed (and / or open end) “inside-out” ducts, with efficient primary fluid-flow and losses on the “outer” flow surface. . In some cases, a flow-body embodiment with predefined dynamics and / or total energy is like a flow-body like propellant, or a “Virgin Galactic“ Spaceship One ”that separates from the launch platform. In addition, it needs to be separated or dropped for glide. In these cases as well, CVG applications can improve adhesion and / or separation, and fluid-flow dynamics and flow-body energy efficiency (in other words, range) of motion, and improved trajectory and / or path stability. Allow sex.

  Duct flow path: Many parts of the surface of most fluid-flow devices, such as jet engines, are ducting surfaces to guide the fluid-flow to the optimal design position in and out of other fluid-flow processing sections These are limited to the flow rotation-angle or flow-direction in which they can be introduced before inducing fluid-flow separation or BL thickness causing energy loss. These ducts or piping, as well as the external 3D surface, become another flow device that can be improved to an integrated CVG. FIG. 9a shows a typical fluid-flow duct 160 that is similar to many conditions in the example of fluid-flow surface, ducting and piping.

  The cutaway section shows a duct seam 161 at the flow direction change, and a smaller diameter upstream duct 165 is placed inside the downstream duct 166 in an optimal position to seal the improved pipe or duct joint. To complete, it has an internal duct CVG array 162 structure integrated at its TE end that is merged, for example, by swaging and brazing or welding. This is one design embodiment that allows ducts or piping transitions with an integrated CVG array inside, which, as already disclosed, is a free stream fluid-flow foil or other body surface In the same manner as for, when the surface or duct changes direction or diameter, it acts to reduce flow separation and drag on the convex surface of the downstream duct or pipe and to reduce drag on the concave surface. Depending on the method of manufacture of the duct or pipe, material, diameter, wall thickness and section geometry, for example, multiple stamping, forging, forming and machining steps can be performed on the inner surface or on the outside of the body surface. For example, it can be used to join CVG arrays at optimal locations on the outer surface.

  FIG. 9b is introduced into a slightly larger diameter constant cross-section duct or straight section of piping and is swaged or otherwise attached in a most preferred position with a duct insertion CVG tip 183 that directs fluid-flow downstream. A duct insertion CVG array 182 is shown. In this case, the duct insertion inlet 184 has a very thin and sharp edge so as to minimize the inlet flow disturbance, and the duct insertion inlet surface 185 has a very shallow angle rearward with respect to the step thickness point 186. Have. Such long low angle duct convergence provides minimal flow change and disturbance before reaching the correct step-height duct matching section at step thickness point 186 before entering the CVG step. An optional duct insertion slit 187 allows a slightly folded duct insertion CVG array 182 to be inserted into the duct and extended to a fixed position to work together or make the mounting method for fastening the device easier to use. Can be introduced. With this array, stream direction gaps are tolerated and have minimal performance impact. Between the step thickness point 186 and the tip 183, this flow is parallel to the average duct surface and across the CVG step is the optimal surface to obtain the most favorable flow shear and downstream BL reactivation. Stabilize when having a vector. The core contribution of these duct CVG arrays includes the case where the array surrounds the entire duct periphery, between the fluid-flow input and the output plane cross section, between the maximum cross-flow limit of the V-form CVG array. This means that the array operates continuously across the entire duct surface BL flow captured by the array in that there is no unmodified BL. In cases where the CGV array is less optimal that does not have space in the stream direction for a constant step height section (which negates the primary gain), such a continuous cross-flow BL modification function is of these types. Distinguish from prior art isolated VG groupings of modified CVG arrays. The use of the duct insertion slit 187 is essentially helical with this duct insertion CVG array 182 having a CVG capture angle changed to a helical angle so as to capture the duct wall BL flow at an optimum angle. So that it can be manufactured. When this spiral is applied more than one revolution, there is a reduction in efficiency due to the disappearance rate of the upstream vortex filament before meeting the next downstream CVG v-form step. This means that a series of ducted CVG arrays 182 in the flow direction must be optimally spaced to obtain the most favorable effect.

  Applying CVG to the inner pipe and duct surfaces can also be done with spray-on or molded coating materials that can be bent into the correct surface geometry and applied or treated when processed or worn. These coatings can be made of multiple layers and provide mechanical and corrosion / chemical protection for the underlying duct or pipe surface.

  Yet another flow control option is a duct flow transition that allows ducting to introduce a large flow-rotation, which is for the prior art internal flow-rotation vane 163, but these structures do not provide fluid flow. -Introduce drag to act like a foil cascade to change flow. The flow-rotating vane CVG array 164 can be integrated into the suction and / or pressure face of the flow-rotating vane 163 to reduce drag before flow separation and allow larger duct or pipe rotation-angles, and Newer, for example, pipe, duct or s-duct designs are possible with a more compact geometry and / or lower energy loss.

  It also enhances and improves the strength and mechanical efficiency of the cooling ducting panel components in larger duct surfaces and transitions that require thermal resistance, and CVG integration and strong, non-cracking TBC It is possible to emboss a tile-shaped pattern of, for example, triangles, squares, hexagons or other polygons that allow the option to add a coating.

  FIG. 10a shows a cross-section of a wall duct stamped or embossed with interlocking hexagonal cells that may optionally have integrated CVG step functionality. The downstream smooth duct surface 170 in contact with the fluid-flow (on the opposing face in FIG. 10a) is located below and to the left of the embossed CVG step array 172 (downstream).

  Embossing is clearly distinguished at the base intersection of the sharp-radius vertical wall (Lutjen '342 patent) to remove heat flux initially from the upstream inner floor 174 and downstream inner floor 175. A vertical with a main wall-supporting route alternation radius 171 (with such a radius greater than right angle and up to the wall height) to produce an interlocking array of beam sections with a greater moment of inertia and the least stress concentration The wall 173 is raised. The top of the vertical wall 173 can be further deformed to make the sharp wall edge compact in the lip and increase resistance to handling damage and edge stiffness. The cooling air can flow across the edges of the vertical walls 173 to remove heat with excellent thermal conductivity and mix-down below the wall and interior floor surface. Depending on the alloy used (preferably at metal plastic temperature, which also allows proximity control of material temperature distribution, surface oxidation and minimum compression / embossing die force to minimize material collapse due to forming stress. Most preferably en-vacuo) embossing or effective forging. It is also possible to generate these surface arrays and steps, for example, in other input casting processes, explosion / hydraulic die forming, etc.

  The creation of such an improved duct panel section of FIG. 10a also allows the TBC to be integrated into the non-smooth face side. FIG. 10 b shows an embossed upstream duct panel region 176 with a lid upstream TBC blanket 177 facing the hot fluid-flow, with the downstream TBC blanket 179 covering the downstream duct panel 180 as a TBC CVG array 178. Will lead to. Note that the hot fluid-flow is against the TBC side of such an arrangement and in the direction of flow with the opposite side of the part similarly formed in FIG. 10a. This embodiment utilizes, for example, a hexagonal array of vertical walls 173 and a shaped top to keep the TBC sub-sections fixed, such as a closed TBC element 181. The TBC coating can be any of the well-known TBC application methods, materials, and inter-coating. The cracking of the thinner TBC section during the example of the closed TBC element 181 maintained can be controlled by the TBC application temperature of the metal substrate. This presets the mechanical stress with a different coefficient of thermal expansion between the vertical wall 173 integrated with the substrate and the TBC sub-section or sheet. This can be uniformly allowed within the example of a closed TBC element 181 that is set between operating temperatures or cooling conditions to suppress TBC cracking or that maintains the coating on the failure. After the TBC coating, the step region can be processed or worn to provide the most preferred step edge of the TBC material for the TBC CVG array 178, and the rest of the TBC surface is similarly treated for surface uniformity. obtain.

  An angled additional duct flow jet 189 may be provided downstream of the steps of the TBC CVG array 178 or embossed CVG step array 172, such jet (or jet array) being the surface to which it is fixed. Thus, for example, surface film-cooling fluid-flow and / or additional BL activation flow can be performed from a pressurized fluid-flow source under the step region, as taught for LPT stator foils.

  Examples of optional step-expansion grooves and / or step shear guides may be added to the duct surface at the CVG step, but are not shown for clarity of the drawing.

  Although FIGS. 10a and 10b show essentially flat panels, such a process can also be applied to surface arrays and steps having a 3D curvature for application to sections for any ducting surface shape. These hexagonal features can use the most preferred CVG flow-angle of about 22 degrees at the downstream edge, and triangular or diamond shapes can be used for smaller TBC sections, but higher for wall-to-floor sections Incurs a metal mass ratio. These duct sections may be about 0.5 mm to 3 mm thick, but this is not a limiting condition, depending on operating pressure, etc. Wall, floor, polygon type and size and TBC thickness are design requirements It can be adjusted as necessary to meet the conditions.

  Cooling turbine blades can use these polygonal maintenance features to secure the LE surface TBC against high inertia loads, where a fountain head arrangement is required for LE cooling. This can be penetrated after TBC coating and stepping, etc., and post-step blade cooling of the TBC-free surface can be achieved through cooling flow, for example, the jet flow injection port 95 with an aft angle, internal blade skin cooling and TE Introduced by a cooling slot.

  Pipeline pipes, general purpose tubing, nozzles, etc. can be combined or mated with CVGs that are appropriately spaced to reduce surface drag and energy efficiency. In spiral-welded or rolled pipes, the embossed or machined internal CVG can be easily integrated with any suitable fabrication method prior to roll forming or welding. The CVG repeat separation is large enough, relaminarization can occur, the tip-vortex flow can be expanded, or the result is disadvantageous to drag as in prior art turbulators or conventional VG arrays.

  Conformal vortex combustor: FIG. 11a shows a general arrangement of annular compact and efficient conformal vortex combustor or gas-generator designs using an integrated CVG to provide an improved design. It is shown as a partial sectional view in which the segments are inclined. The combustor is provided as an oxidizer to generate an accelerated fluid-flow from which work can be extracted and / or to burn the fuel input in an exothermic reaction that is controlled to produce heat, and the compressor Can accommodate the output.

  The external combustor pressure wall 200 is connected to the HPC casing through the input interface 201 (which is connected to the HPC at the exterior and interior walls), and the combustor is typically in the highest pressure region of the device, thus ensuring high pressure integrity. The output interface 202 is connected to the HPT casing to maintain. Combustor input guide vane 203 and combustor output guide vane 204 act to form a range around the combustor sub-segment in terms of overall combustor array and volume. These combustor guide vanes 203 and 204 can optionally be twisted at an angle to the axial flow to diffuse the HPC output flow (using 203) and to be part of the stator structure to avoid vortexing. And / or combustor flow power-angle can also be defined in a radial dimension, sufficient to allow optimal flow power-angle design directly within the HPT first rotor cascade. It can effectively act as a compact and integrated HPT inlet stator blade (utilizing 204) with cooled vanes.

  The combustor inlet fluid-flow mass enters through the opening E at a speed and temperature defined by the HPC (and possible variable outlet guide vanes), then the upper bypass opening F, the lower bypass opening H and the rich- Divided into three streams flowing in the burn combustor opening G.

  The combustor input CVG array 205 is designed to suppress such duct flow-separation, reduce drag, and allow for such a flow-efficient and / or more compact inlet flow design. A point is added around the inside of the entrance opening E.

  The portion of the mass flow thus designed at the opening G is divided into steps from the combustor lower (and upper) mixer CVG array 207 into the step and vortex filament flow, the lower CVG combustor guide 213 and the upper CVG combustion. It flows between the vessel guide 225. Next, the rich mixing frame-front is in immediate contact with the completion of fuel oxidation, after a predetermined time, with extra bypass air added and combustion producing lower nitric oxide. Proceed into lean-burn opening J, which is completed smoothly in two lean-burn steps. The final combustion / oxidation of the fuel is completed at the transition time leaving the opening K around the output interface 202.

  At the exit from opening I, on the TE of CVG combustor guides 213 and 225, an array of upper and lower frame stabilization tabs 216 captures the spanning vortex of the combustion fuel at the front and rear faces of these tabs. Acts to hold. The spanned outlet vortex of the frame stabilization tab 216 also increases the TE wash flow and is efficient to help mix-down the bypass opening air from the ducts F and H into the lean burn opening J volume. Acts as a lift and drag change Gurney tab. Tab gap 215 is added to also organize a small amount of cord-wise rich-burn vortex filaments that exit into opening J to mix with the bypass air and continuously complete the lean-burn cycle. Together with the LPT and fan blade LET, these frame stabilization tabs 216 are angled or separated, unlike those perpendicular to fluid-flow.

  As the fluid-flow velocity increases at the combustor input (and then into the volume of opening I), the initial abundant frame-front is localized fluid so that duct diffusion matches the frame propagation velocity at these physical conditions. Retract backwards into the opening I volume until balanced with speed. This defines the minimum diffusion (surface curvature) required in the aft section of opening I for frame stability, and at maximum flow vortex this frame front is in front of the frame stabilization tab 216 and TE exit. Should. The ratio of the sizes of the openings E, G and I effectively controls the speed of fuel mixing with the reach burn volume in relation to the HPC output speed. The ratio of openings F and H to G controls the flow volume for rich-burn versus bypass, cooling and lean-burn air for the combustor. The transverse vortex filaments on the front and rear faces of the mechanically rigid frame stabilization tab 216 are also very stable when the igniter array 227 element disappears, as a flow disturbance-blocked backup ignition source. Works. The upper CVG cooling flow duct 226 and the lower CVG cooling flow duct 212 are connected to the upper CVG duct body 224 and the lower CVG duct because the rich-burn volume generates a lot of heat on the local flow surface and frame stabilization tabs 216 and TE. Added individually to the body 214. The cooling fluid-flow in these upper and lower CVG cooling ducts is constituted by a lower cooling inlet opening 221 defined by, for example, a lower combustor guide 213 and a lower CVG duct body 214. Outlet cooling air from these CVG cooling flow ducts 226 and 212 makes an angle in the mass inflow at opening J. These cooling ducts are included in the body of the CVG combustor guide because they are thicker fluid-control foils in the combustor ducting, but if these guide foils are thin enough to be adequately cooled Thus, the outer guide flow surface can cool these foils without the need for internal cooling ducts. The example combustor embodiment of FIG. 11a is generally symmetric with respect to its mid-plane, so that the finely paired items are in some cases to provide more drawing clarity. Note that although omitted, in fact, this is illustrated by the symmetric design intent of the particular embodiment.

  Most combustor energy release occurs at the boundary volume of opening J at the completion of fuel lean-burn, and lower wall cooling surface 217 and upper wall cooling surface 220 are exposed to such combustor heat from the combustor outer pressure. Added to protect the surface, and these structures intercept a small amount of fluid with ducts F and H as film-cooling media. To protect the example surface of the combustor output guide vane 204 on both sides, a shield such as a side cooling surface 219 is added, and these are also ducts (from before the CVG combustor body) as film-cooling media. Intercept the inlet fluid with F and H. The examples of cooling surfaces 217, 220 and 219 can be made using well-known TBCs on the surface shown in the boundary volume of opening J or as CMC panels to reduce heat flux and oxidative damage. Optionally, a drag-reducing CVG array, such as a lower cooling surface CVG array 218 on both faces, can be used to lower the drag. The TBC prior art can also be used, for example, on a small amount of combustor guides 213 and 225 surfaces to lower the local heat flux within the combustor surface, and this energy is used for HPT sections for useful work. It can be used for combustor output. The duct-flow concept of FIGS. 9a, 9b, 10a and 10b can also optionally be used as a fine improvement on any surface with this combustor to improve flow and reduce drag.

  The pilot fuel plenum 208 and the primary fuel flow plenum 211 are supplied with filtered, pressurized, fuel-flow arranged in a certain order, and separated angles that conduct the fuel flow into the mixer CVG array 207 step region. A pilot fuel jet 209 and a primary fuel jet 210. The pilot fuel jet 209 is smaller and can be injected close to the CVG valley to ensure liquid fuel particle collapse and atomization with a strong step vortex filament that overcomes fuel viscosity and cohesion, and then A portion of the rich fuel mix will flow backward into the CVG tip-vortex and into a region where the downstream velocity reduction relative to the flame propagation velocity will allow ignition. In this manner, higher energy output is required that can have a high fluid-flow velocity in the step region of the mixer CVG array 207 that provides high vortex mixing intensity later in the opening I and delays the initial combustion heat. When done, pressure in the primary fuel flow plenum 211 similarly pushes fuel through the example of the primary fuel jet 210 and into the step region of the mixer CVG array 207. This example shows an angular primary fuel jet 210 that is closest to the CVG tip region, and this fuel portion is injected or diffused into the highest vortex filament to be burned. Utilizing one or more fuel injection arrays to vary the flow rate when required allows for better tailoring of the fuel flow for variable operating loads or required heat generation. In fact, jets are other configuration sizes, geometries, and examples that are moved to other locations, but have benefited from the low-drag fuel injection and mixing benefits improved by utilizing an integrated CVG array vortex. Still get. CVG arrays allow a low drag system to add many coupled smaller fuel-flow jets with strong mixing and liquid-particle breakup. The combustor can also use fuels such as natural gas (methane) or hydrogen, where vortices do not disrupt sticky liquid droplets but ensure the most favorable possible input-fluid / fuel mixing. .

  Liquid fuel flow vaporization-energy can be used to balance the operational cooling of the mixer CVG array 207 step, fuel plenum, jet and adjacent area, to control or isolate downstream heat flux conduction, etc. It can be improved by changing the material and design.

  FIG. 11b has an additional interface CVG array 229 embedded in the body transition after the fuel jet to reduce heat conduction into the fuel plenum, eg, 213 as a ceramic insert, ceramic after-body 228 and This is a cut-away cross-sectional view of a part of the downstream body, such as 225 and 216. Attached ceramic after-body 228 after the deformed 213 and 225 foils supporting the flow in opening F and H ducts and rich burn opening I eliminates the need for CVG cooling flow ducts 226 and 212, etc. Allows a simplified design. The igniter array 227 conductor is integrated or wired into the ceramic or CMC body, or through a hole from a core volume with a refractory metal such as tungsten, for example, while sparking out to the second conductor or cooling wall section. Can be). A cornered additional combustor injection jet 230 is shown in the CVG step of the interface CVG array 229 on the top or exterior surface of the ceramic after-body 228. Since the pressure at opening F / H and opening I can be varied and balanced in relation to the input pressure at opening E, the inlet bleed from upstream to slightly pressurize the core of the ceramic after-body 228 And then rejecting such cooling flow through the example of the combustor injection jet 230 and fluid-flow BL momentum on the opening H and / or opening I side of the ceramic after-body 228. Can be improved. The example of the combustor injection jet 230 may also be applied to the outer duct surface inlet CVG array 222 and the inner duct surface CVG array 223. Examples of optional step-expansion grooves and / or step shear guides can be added to the ceramic after-body 228, but are not shown for clarity of the drawings.

  The modified version of FIG. 11b of the 213 and 225 foils is shown as a thin wall casting and fuel plenum, and these items can be either rigid or manufactured in any combination fabrication method to provide the correct flow geometry. Can be done. The additional interface CVG array 229 may have valleys and chips that are offset from the mixer CVG array 207 or at different pitches to increase fuel mixing.

  The fuel injection pressure is controlled to ensure proper jet flow at the required operating load, and any liquid fuel that enters will not drop under vapor pressure until the fuel jet exits, so the liquid fuel flow will be vapor-locked ( Vapor-lock).

  Other examples of CVG arrays are included on other combustor surfaces that are beneficial in reducing combustor drag, and mixer CVG array 207 is preferred to ensure sufficient mixing and associated vortex turbulence It is clearly used as a large step structure and is used to reduce secondary drag. Preferably, intermediate-surface CVG array 206, external duct surface inlet CVG array 222, and internal duct surface CVG array 223 are also optionally added on the upper and lower surfaces to reduce the overall surface drag from the flow surface. , A wide tolerance range of Re values is allowed so as not to cause flow separation losses at the combustor and ducting surfaces.

  Combustors arranged (with possible ceramic after-body 228) for the most favorable flow in a single combustor formed by the external combustor pressure wall 200, drawing new geometry and the like It is possible to have a single example of guide 213 or more than one example of a pair of combustor guides 213 and 225. If the core design is more efficient for the design volume available in this embodiment, the combustor guide 213 from the essentially constant-radius (from the engine shaft axis) shown in FIG. And 225/228 can be modified to a design that is matched to be symmetric with a circle (more like the venturi tube example). Combustor guides 213 and 225 and mixer CVG array 207 can also be configured radially to be effectively aligned in a radial direction, with a combination of high pressure turbine inlet stator vanes having included fuel injection openings and combustion volumes Works in the same way. Examples of CVG combustor designs are for other flow styles such as flow ducts and combustor paths that are folded and flipped, as found, for example, in Allison 250, PW300 and other smaller sized turbine engines. Can be easily deformed.

  For example, other combustor styles such as liquid-fuel and oxidizer combustors improve flow and mixing interfaces and ducting / piping, with some working fluids likely to be colder before the flame front combustion point. Supply centrifugal turbo-pump (with optional integrated impeller CVG) for applications such as liquefied oxygen rockets or propulsion machines and high speed before ignition and expansion through exhaust nozzle to generate thrust It is also possible to use such a CVG vortex flow-mixing strategy that requires fine mixing at the same time. Such types of combustors may be in the form of mixer plates with flow injection holes, which provide outlet vortex filaments to improve combustion and mixing stability when fuel flow is throttled or varied. Can have a CVG embedded on the periphery to provide.

  A further combustor embodiment is a solid-fuel device in which fuel is stored in a pressure containment or (effectively) semi-closed duct / tube structure. Combustion proceeds with an oxidant flow mixed in solid fuel or an oxidant flow introduced (as in a Rutan / Virgin Galactic engine with N2O) and is an effectively processed input fluid-flow. ) Active combustion products are transmitted through the outlet nozzle output so as to form thrust. The containment / duct walls and / or nozzles are processed relative to the duct CVG embodiment of FIG. 10 above to have a CVG that provides a low-drag outlet flow surface-interface that appears as fuel is consumed. The TBC can then be coupled along a cooling jet added to, for example, an HPT turbine blade. The surface drag loss and impact on conventional conical / bell shaped or commercial Aerospike style type exhaust nozzle flow surfaces can be improved and / or deformed with CVG configured for this purpose. The contact ignition fluid mixing chamber acts like a combustion furnace and can utilize CVG or with attached nozzles.

  Fuel supply lines, pumps, igniters and other accessories, etc., are mostly standardized, but are not explicitly shown, and follow the general form and function of known prior art.

  FIGS. 11a and 11b are representative and not to scale, open fluid-flow separation and balance, fluid transition time, component size and example and location are compact, high performance, low emissions and energy efficiency. Based on the basic concept of using a drag-reduction integrated CVG for improved total drag reduction, fuel atomization and mixing in a typical combustor, to meet the design goals for the operating environment and fuel etc. Can be widely modified as required. FIGS. 11a and 11b may be, for example, an example of a CFM-56 combustor, or the general size of a segment, but the size and length, etc. as required for a particular gas-generator application. Can be adjusted larger or smaller. If the total internal surface area of the new technology conformal eddy current combustor is configured similar to the prior art combustor, it will provide significant absolute drag reduction and loss over the prior art design, and reliable combustion Allows the ability to design duct paths and foil sections for the correct branching / diffusion and flow velocities.

  As taught herein to improve the fluid-flow of the device, these surprisingly diverse ranges of high temperature and / or high stress example types are simply not possible with prior art eddy current generator approaches. Unexpected results and capabilities of fundamentally integrated CVG applications that are impractical or impossible. At most basic common levels, all cited embodiments and variations will achieve a certain level of gain, such as improved energy efficiency and / or extended control range, not possible with the prior art. Newtonian fluid-uses a new conformal vortex generator that processes or manipulates flow.

  Thus, while the disclosed information describes in detail preferred embodiments of the present invention, no material limitations are intended to the scope of the claimed invention, and certain features and modifications designed to those skilled in the art are Considered to be combined here. As a result, rather than being strictly limited to the features disclosed for the preferred embodiment, the scope of the present invention is described and specifically described in the following appended claims.

  The present invention improves the energy efficiency and / or performance envelope of an apparatus by using a new hydrodynamic structure of an aerodynamic / hydraulic Newtonian fluid-flow apparatus and a conformal vortex generator (CVG). Related to the field of ability. Such novel applications of intrinsic or integrated CVG include actuator cascades, foil cascades and flow-control surfaces in dynamic turbomachinery such as mobile turbine engines, static power generation turbines, helicopters, blades , And other Newtonian fluid-flow applications, generally operate at various locations and roles.

  For example, the additional CVG used in Helicopter Corrosion Prevention System (EPS) can be mounted and matched to smaller, more complex and esoteric turbomachinery structures with very fast radial acceleration on the order of tens of thousands of gravity This is not feasible and this requires a new inherent intrinsic or integrated CVG method that requires a high robust cascade and performance environment such as high temperature and sharp edged input surfaces Because. The additional CVG is conveniently attached with adhesive to the existing foil or body surface design, post-manufacturer, where the original foil or body surface design-intent and engineering considerations are the most preferred of the benefits of CVG Was not considered for binding. In contrast, integrated CVG technology is included in the design process and engineering for the design of new foil or fluid-flow control surfaces, which is not possible with the additional CVG technology. Allow new combinations of control range, energy efficiency and manufacturing options.

  A gas turbine engine is in fact a well-known example of a complex turbomachine using various ranges of Newtonian fluid-flow, thermodynamics, materials and physical techniques applied to fluid-flow processing equipment. Each series of functional blocks allows some input fluid-flow, processes this fluid in several ways, and then outputs this fluid at the interface to the next stage of the engine. The initial air inlet is the first fluid input interface and any cooling or hot section exhaust nozzle completes the final fluid output interface in the ambient atmosphere. For turbine engines using the well-known Brayton cycle, the efficiency is the difference between the fluid peak operating temperature vs. the final outlet temperature difference in the compressor, turbine, combustor and inlet guide vane (IGV), flow ducting and outlet nozzle gas paths. Related to well-known theoretical thermodynamic cycle performance of ratio and flow efficiency, or energy loss.

  In the present disclosure, the fluid-flow taught herein is for a working Newton “fluid”, a typical atmosphere or other gas, but many CVG technology embodiments also have Reynolds number (Re) When reached, it is effective for liquid or mixed phase conditions. This is known to be true because in turbomachinery and equipment, numerous foils and flow designs for gas fluid-flow use labeling materials and methods to observe scalable fluid-flow effects. For example, to be scaled, tested and flow visualized for convenience in a water tank. In the following, “fluid-flow” is applicable to the Newtonian gas phase and / or liquid phase because the hydrodynamics are actually adjusted by the fluid-flow conditions and the Re number.

  Engine compressor and turbine blade stator and rotor disk designs as an array of foils in the cascade are optimized for aerodynamic performance, engine geometry and mass flow. Since the initial stage operates in close proximity to the cooler inlet fluid temperature, the compressor and possible bypass-fan stage and ducting “cooling section” operate in a less demanding environment. In these cooling sections, flow improvers reduce the complexity of high gas temperatures, oxidation or other issues affecting material strength to create common rotation, flow, aeroelasticity, vibration, fatigue and pressure stress. I don't have it. The compressor stage can absorb about 60% + of the total fuel-energy provided and is extracted by the turbine stage. The remaining usable turbine output energy and efficiency improvements in jet exhaust nozzle impact have a significant impact on the useful output work available.

Description of prior art

  Low Pressure Turbine (LPT) Stage: In many modern concentric-shaft engine designs, the LPT stage typically energizes from the mass flow of the “hot section” gas in the combustor after it is exhausted while inducing a pressure drop. And this energy is guided through the innermost shaft drive shaft to the bypass fan, shaft load and / or initial compressor stage.

  The LPT stage blade load and the Zweifel load factor increase as the cascade robustness, lower blade count, engine size, weight and cost change, and the impact / reaction foil empty in the turbine cascade. Problems arise with mechanics. In the lower Re-number “off-design”, the rotor and stator blades have a thick boundary layer (BL), turbulent fluid-transition, fluid-flow separation in the lower momentum BL layer, total fluid- Unfavorable suction-face pressure gradients can be experienced that induce flow separation bubbles and loss of energy efficiency.

  McQuilling is a well-known Pratt and Whitney Inc. in his paper, “Design and Validation of a High-lift Low-Pressure Turbine Blade”. His proposed “high lift” (and front-loaded) LPT blades, including an improved ヅ Weifel coefficient for common examples such as the “Pack-B” blade design The design teaches that an operating envelope extreme or “off-design” is possible without using any additional flow modification methods to combat flow separation or blade stalling.

  Here, blade foil front-loading optimization allows the suction-face pressure recovery to diffuse for longer chord distances, improving fluid-flow, low energy and low momentum. The disadvantageous pressure gradient is reduced while reducing the separation of the lower BL. In this case, the reaction to the basic blade fluid-flow, unstable upstream wake, etc. can be designed to be improved over the prior art, but ultimately the combined performance improvement will reduce this design blade load. Flow optimization techniques must be used to reduce drag and separation, especially in off-design at performance envelope limits.

  Fluid-flow variants and effects are described, for example, by Rouser in his paper, “Use of Dimpled To Suppress Boundary Separation On A Low Pressure Turbine Turbine. This variation and effect is also intended to reactivate the lowest BL level and prevent adverse pressure gradient effects and fluid-flow separation from the foil surface. First, it includes many types of surface structures and methods that are used to generate vortex flow and to circulate energy from the higher momentum fluidized bed to the lower layer (adjacent to the foil surface).

  Well-known vortex generators (VG) used to improve foil flow fall into many categories that differ in their effectiveness and benefits. Projecting devices such as ramps, angled vanes, riblets, wheeler ramp vortex generators and the like produce beneficial vortices but tend to lower drag and flow separation losses Generate extra drag while attempting to change the flow conditions. In addition, these protruding devices recover energy from a more active upper layer of the BL that becomes free stream or thicker at a lower Re number, but then protrudes higher onto a thinner BL at a higher Re number. Thus, a high induced drag is caused at such a performance point. These devices are characterized, for example, by having a substantial BL thickness height in the range of 35-100% or more of the maximum BL in VG.

  Widely so that concave or soaked VG and micro VG, such as Ogee submersible, wheeler channel or even dimples, generate less added drag than protruding VG below BL depth Have been studied and taught. These devices have variable geometry or height in steps or ramps in the code direction. Ozzy submersible devices show their vertices towards the incoming fluid-flow and do not match the foil profile. In some micro VGs that are low in BL, a complex series of applications is required to generate sufficient vortex energy, and such close-proximity applications are performance in a rotating environment such as a blade. Disadvantageous.

  Dimples typically reduce drag by suppressing large flow separation bubbles, as taught by Rouser (eg, golf balls are used to fly farther due to low drag). Simple and omnidirectional. However, dimple diverging vortices are complex, with low optimal strength or ability to couple much free stream fluid-flow energy to the lower BL.

  The dimples for BL control are complex because their performance is sensitive to geometry and Re number where the vortex mode predominates. Blade-type VGs, for example, with respect to the actual LPT blade Re number, these are very small on the order of millimeters, thus resulting in a very sharp, fine and elaborate structure, and high temperature oxidation exhaust There is a further problem in that gas is subject to particle corrosion and damage. Further problems include the mechanical impact on blade fatigue due to point stress concentrations during blade warping and the risk of these sharp objects facing maintenance personnel.

  Ramp-inlet (eg, wheeler with aft facing step, upward ramp flow) and ramp-outlet type (eg, Ozzy submersible, downward ramp flow with forward facing step) VG also has energy Has a potential shock wave with other secondary flow structures such as cross flow or spanned horseshoe vortices that redirect the energy from being strongly coupled into the exit cord direction vortex.

  In the NASA study, a typical VG generates a vortex that typically maintains a multiple of about 40 VG height backwards along the cord length by a distance of about 30 times the VG height in the flow direction. It shows that it will be circulated to higher energy layer.

  Rouser teaches other non-VG methods of BL flow control as shown in FIG. 10 (belonging to McCormick), such as a passive porosity-surface device, and this passive porosity-surface. In the apparatus, a higher pressure is generated and injected on the surface of the low pressure region prior to separation through an array of holes or injection slots or steps. This provides an effect similar to Coanda or other lift enhancement or blown-flap type methods or other suction methods used to stabilize the BL region. Of course, one of the problems with jet fluid injection is that as BL speed decreases, jet "lift-off" or flow momentum is balanced to avoid jet "lift-off" or flow separation, or the flow Re is varied. Yes, and in addition, the local BL collapses to form a horseshoe vortex around the leading edge (LE) of the jet fluid-flux column or stream before it is driven close to the blade surface. It is.

  Hybrid Laminar Flow Control (HLFC) reported for Boeing 787 aircraft, for example, vertical stability using intake air from a passive source to improve control flow separation during single-engine operation (instead of VG) Use porous suction-surface technology for BL control of the vessel LE. The porous pore / mesh suction surface has strength problems with the composite structure and has problems with the environment blocking the inlet, the loss of viscous energy, and the force required to induce suction.

  Stephens US 2,800,291, Wheeler US 4,455,045 and US 5,058,837, Rinker US 7,900,871 and many other all documents show increased height from the underlying foil surface A ramp with a peak, teaching an add-on ramp style VG or similar individual shape variant starting from a thin (non-zero) inlet edge in fluid-flow and extending backwards Yes. Geometrically or topographically, the device does not match the surface of the underlying foil in any interpretation. As taught by Stephens '291, abnormally grown or equivalent VG structures such as Rinker' 871 cannot act as a drag that decreases at a low angle of attack (AoA) on the foil or body surface. Here, “low angle of attack (AoA)” means, for example, a substantial fluid-flow separation on the foil or body surface upstream of the normal final outlet flow separation in a TE that meets the flow-fluid outlet, or Kutta-Jawkowski condition. For example, it is defined as a range including positive, zero, and negative AoA under an angular magnitude with no stall or separation bubble. In most foils, the range of +/− 4 degrees AoA satisfies this condition, but is not limited to this, and in various cases it may be a larger range and approach the stall AoA. Schenk US Pat. No. 4,354,648 teaches an array of protruding low-profile BL tripping devices to generate BL turbulence and reduce airfoil flow-separation on the vanes. Because the Schenk '648 device is not zero inlet-height and does not perfectly match the foil surface, it induces drag from horseshoe vortex or turbulence even if this device is proposed smaller than prior art VG It will be. Small size, discontinuity or point coverage and non-directional turbulence are not efficient BL reactivation methods.

  US Pat. No. 5,088,665 to Vijgen et al., “To Improve Lift and Drag Characteristics”, Triangular / Sawtooth Array of Elements or Foil Trailing Edge (TE) variants with appendages after TE of sawtooth panels. Teaches. The addition of the remaining active aerodynamic elements outside the physical range of the original base foil does not add CVG on the foil surface in front of the TE and within the physical range or boundary of the original foil. Obviously different. Fritz US8,083,488 also teaches serrated add-on panels at TE and is distinct and patentable against Vijgen's' 665. Shibata US 6,830,436 adds a “tooth shape” or serrated shape in TE for both noise reduction and increased efficiency by modifying the trailing von Karman Street vortex sheet. Wind turbine blades are taught and claimed. Gliebe US 6,733,240 also teaches and claims a serrated TE array on a turbofan blade to improve fluid mixing and reduce noise, and Young US 3,153,319 and The same aerodynamic effects and results are used as taught in US Pat. No. 6,612,106 to Balzer. Gliebe's 240 does not teach drag reduction below the reference design and is easily added on the pre-TE foil to obstruct linear TE and get drag reduction above the reference configuration and other improvements. This is clearly distinguished from CVG.

  In Godsk US 7,914,259, as shown in FIG. 3, there are several sequences along the wind turbine blades to extend the reference non-stall AoA from about +10 degrees to about +16 degrees with VG added. Of discontinuous prior art VG. FIG. 4 of Godsk '259 shows a well-known problem with discontinuous ramps and blades VG, which is a low AoA and a blade attached to the VG to a +10 degree reference stall AoA. The criterion is that it has a higher drag coefficient (Cd) than an unmodified blade.

  Wortman US Pat. No. 5,069,402 includes a C-130 tail section upgrade to prevent or reduce flow separation (similar to stall) from surfaces that have high AoA or branching efficiently from the fluid-flow stream line. Teaching to generate a normal large downstream eddy and high induced drag by utilizing a prior art large blade type VG to generate a swirl that propagates along a bifurcated-flowing surface such as a sweepsweeper doing. The Wortman '402 technology blade VG itself develops considerable form- drag, but acts to lower the greater downstream separation drag, effectively when these VGs induce drag In some scenarios, where there appears to be a total drag-decrease and alters other significantly separated or stalled flows, it can only be seen when the drag is relatively reduced.

  The ramps and blades VG tend to generate higher non-sustained vortices in BL that are not tied to the foil surface. The dimples and bumps produce eddy currents, but they are not very efficient or activated, and the bumps are higher as the Re number changes and the BL becomes thinner It has the same issue as the blade VG that will induce excessive drag in BL.

Martin, a AIAA paper such McVeigh in "passive control of the compressible dynamic stall" small blade VG about a blade _{C d} of about 0.01 0.015 were used to helicopter rotor blades in FIG. 27 It teaches to increase dynamic stall and blade pitch moment due to VG increasing blade stall AoA while increasing rotor power requirement by about 50%. McVeigh US 7,748,958 claims such a VG structure and method for reducing dynamic blade stall / pitch moment, but based on published test results and known flow physics, It is not possible to request the addition of a general drag reduction ability.

  Volino's NASA research report “Synthetic vortex generator jets used for separation control on low-pressure turbine airfoils” teaches active separation control using synthetic vortex generator jets (VGJs). Thus, the vortex is generated by pulsing an angular jet flow into the BL that partially induces a chordal vortex flow and serves in a manner similar to a normal VG that reduces flow separation bubbles. The Volino approach does not require a constant source of activated blower fluid-flow that consumes the energy it generates, and its design is a pulse type without net-flow sound generation. It is unique in that it produces a jet flow. The interaction of the fluid jet with the higher BL flow and the momentum layer creates a vortex state, which also creates drag while attempting to spread energy into the BL region that extends more widely in the span direction.

  However, all these prior art techniques to improve airfoil or LPT blade flow and reduce segregation are even larger so that the real world rotating environment convects vortices outward in the foil span direction at the boundary layer It has an issue in that it adds further complex conditions. This tends to rotate the vortex that is not tightly bound to this surface outwardly after the physically defined generation point (radially on the chip side) with a higher BL fluid-flow pattern, The blade then accelerates in a curved path and, in addition, the vortex tends to move downstream, so there is no substantial force acting to bring the vortex closer to the blade, so the vortex is convectively on top of the BL However, this is due to the fact that any secondary flow in the span direction can be intercepted and strongly collapses outward.

  In this case, the beneficial intention of the chordal vortex generated earlier on the cord to reactivate the BL and reduce flow separation and drag is actually negative, as shown by Martin et al. To act partially across the free stream (more to the vortex axis in the span direction) in a chaotic fashion that tends to increase the drag by increasing the subsequent BL while affecting the separation Eddy currents precess. This effect has been clearly explained for helicopter rotor blades operating at about 1,200 gravitational accelerations at the tip and at much lower centripetal acceleration than the LPT cascade operating environment. Prior art eddy current generators that act or convect eddy currents on the BL are generally disadvantageous in a rotating environment, as shown by Martin et al.

  Aft-facing steps for free stream flow are captured as taught by Calvert and Wong in the AAAA paper “Aerodynamic Impact of Helicopter Blade Corrosion Coating”. It is known that eddy currents are generated and therefore fluid losses and flow disturbances occur. These are, as on UH-60 helicopter LE corrosion protection strips (EPS), that the span vortex for a simple aft-facing step (ie at 90 degrees to fluid-flow) is reduced by the blade operating point. It teaches that it is known to increase blade drag by + 5% or more.

  In the case of UH-60, for example, an aft-facing step of ~ 0.5 mm height and 5 m length means a captured spanwise step-vortex filament having an aspect ratio of about 10,000, In a mechanical situation such a very elongated vortex filament structure is not dynamically stable. For example, in the LE part of a rotating foil such as a helicopter, there are numerous mechanisms that strongly disturb the BL level fluid flow. Spanwise (or generally radial) secondary upper-BL flow is angled across the EPS step so that the shear force is driven outward on the lower BL momentum layer and is angular to the foil cord It tends to flow as there is. This will provide a strong step-breakup impetus along the centripetal acceleration in the viscous-attached BL layer that tracks the foil motion and, depending on the measurement, may be angular to the span The step-vortex section can be continuously disengaged with a vortex section that can be precessed and perturbed to thicken the subsequent BL on the foil and increase drag loss. A Tollmien-Schlictig (TS) sound pressure wave develops in the laminar-flow region upstream of LE, amplifies, and flows to the rear side to help transition to BL turbulence so that the vortex stream can be bent into a U shape In addition, these disturbances also affect the step-vortex stability and the shedding frequency. It was unforeseeable that an after-facing step device could be used to generate drag reduction against a reference or unmodified fluid-flow surface, reduce energy loss, and improve fluid-flow efficiency It is a result.

  All other known prior art, such as Stephens' 291, Wheeler '045 and' 837, Rinker '871, Vijgen' 665, etc., generally have a triangular shape and apparent visual similarity While the vortex generator configuration is typically shown, aerodynamic analysis readily shows that such a configuration and effect is clearly different from the new technology CVG.

  High Pressure Turbine (HPT) Stage: Nickel-based superalloys cannot withstand high gas temperatures directly as the turbine inlet temperature (TIT) increases from the combustor, making the engine lighter and improving fuel consumption (SFC) And other methods to actively cool engine components under operating loads and maintain their shape and strength were required. A typical design uses a bleed compressor cooling air to cool the combustor, HPT stator and rotor, and the duct surface to the point where the flow temperature is safely reduced, and minimizes cooling energy costs. For example, a ceramic thermal barrier coating (TBC) can be used. TBC reduces cooling conditions and associated energy costs due to increased surface thermal resistance, but maintains sufficient cooling so that the base metal does not soften or these alloy crystal alignments do not shift. The remaining heat flux must be removed.

  HPT cooling: In hot section ducts, excessive and hot gas excessive mix-down or turbulent flow in the lower BL duct surface and blades (both rotor and stator) are on the component surface under hot gas flow. On the other hand, the heat flux load is increased and the cooling condition is increased. Such disadvantageous fluid-flow separation and turbulent flow both have problems in efficiency (drag) and thermal durability.

  An example of the prior art is the Howald US Pat. No. 3,527,543 patent which teaches surface film-cooling utilizing holes on the blade to provide internal air cooling on the blade surface. Bird et al. US Pat. No. 5,193,975 teaches a turbine blade having an internal cooling passage, a pink ring and a TE slot cooling air exhaust. If the main flow and cooling flow rate are not matched and the slot flow separation edge is not tapered to a very (subtle) sharp edge, then the disadvantageous vortex will be formed perpendicular to the flow, so that the discharge slot straight-edge Are typically disadvantageous to drag. Zelesky's US 5,378,108 teaches a TE series slot modified to optimally distribute TE cooling flow and thin TE formed solely by suction-face wall thickness to minimize drag doing. The Green, US Pat. No. 5,374,162 teaches a blade LE fountainhead cooling that is effective in changing the input flow angle. US Pat. No. 7,011,502 to Lee et al. Teaches a LE bridge casting arrangement with a pin mesh and a cooling outlet slot, which is disadvantageous if the matched fluid flow is not matched and the edges are sharp. It still has the problem of linear edges that will have a span vortex.

  Shih and Na's ASME paper “Increasing Thermal Insulation by Using Upstream Lamps—Cooling Efficiency” is achieved by using a lamp in front of the cooling jet outlet hole instead of VG in the jet hole or coupled to the jet hole. It teaches improving the cooling efficiency of adiabatic membranes up to three factors. Here, the span direction (crossing the free stream flow) vortex captured after the ramp causes the coolant mass to cross the flow span and improve the cooling laterally or in the span direction and the jet It acts to alter the cooling fluid jet flow by disrupting the unfavorable leading horseshoe vortex of the jet so that it diffuses before the exit hole. This ramp / jet configuration shows about 3 times more effective adiabatic cooling due to the ramp, but is mentioned earlier in that the form or pressure drag increases relative to the flat plate baseline. Such a protruding lamp structure is disadvantageous. A lamp that protrudes into a hotter gas layer also requires a mass to which TBC is added, as mentioned.

  Thus, Shih and Na ramps and step ideas, where trapped spanwise vortices aid the diffusion of cooling fluid, trade cooling improvements against adverse fluid flow drag efficiency and viscous losses. As reported by NASA, Wheeler VG. Teaches a smaller upstream jet of “anti-vortex” pairs that act to minimize the adverse kidney vortex of the main cooling jet flow. As in Heidmann's “Numerical Study of Anti-Vortex Film Cooling Design with High Blow Ratio”, modeling for the lamp was configured to generate only the span vortex without the cord vortex at the ramp edge. This method has been attempted to diffuse adiabatic cooling in the span direction and avoid jet-liftoff where jet flow is separated from the surface, but is taught as a combination to reduce foil drag loss and turbine drag efficiency. Not.

  Turbulators are also formed inside the coolant pipe flow as triangles, ramps, chevrons, etc., and tortuous cooling passages inside the cooled high pressure turbine (HPT) rotor blade, stator and hot gas flow surface. In this case, the heated surface BL fluid is backed up in the cooling core fluid flow in order to maximize heat transfer or heat transfer and cooling efficiency despite the drag induced by the flow geometry unlike CVG. Configured to provide maximum flow turbulence for mixing. Here, the surface step or chevron vortex and the turbulent-guiding structure are configured to be aerodynamically adjacent together so that when the vortex state disappears, the cooling fluid is not reorganized into a smoother flow. Obviously this is not a fluid-flow low-drag operation, but is actually enhanced so that flow BL separation improves heat transfer by the working fluid, and these prior art structures are clearly CVG and Is different.

  HPT thermal barrier performance: Terry US 2,757,105 and Haskell US 5,260,099 teach the value of engine blade coating, and Driver patent US 4,303,693 teaches the value of plasma spray coating. doing. Kojima et al. US Pat. No. 5,630,314 teaches a “tile” or cylindrical thermal barrier coating (TBC) for turbine blades, and Nissley et al. US Pat. No. 5,705,231 describes gas turbine temperatures. It teaches pre-cracked or segmented plasma spray type ceramic coatings with good wear and spalling resistance. Nissley and the prior art also improve ceramic adhesion, improve thermal expansion coefficient matching, provide a transfer layer that is easy to handle, and are typically used for high mechanical and thermal stress components, such as nickel super It teaches the value of diffusion or surface bonded coatings (eg, MCrAlY, aluminide, alumina, etc.) to provide increased thermal oxidation protection to the base layer of the alloy.

  Spengler et al., US Pat. No. 4,576,874, applied one or more ceramic TBC layers to a turbine blade to improve durability, especially when circulated in a cooler state, the ceramic was in tension and cracked. And teach applying ceramics at elevated temperatures closer to operating conditions so that less spalling occurs. US Patent No. 6,224,963 to Strangman teaches TBC laser segmentation to reduce spalling problems when the coating section is mechanically worn or damaged. Therefore, important issues for applying TBC to turbine stages are to ensure maximum resistance to thermal loads, inertial loads and chemical corrosion effects, and to the maximum matching of different thermal expansion coefficients and mechanical Resistance to damage and spalling.

  Compressor performance: The efficiency of the compressor is important, and the stator and rotor blades will now operate close to these free separation conditions, gaining higher diffusion factors, higher rotation angles and higher blade loads However, the inherent BL control that can delay fluid flow-separation allows higher pressure rise per stage. In addition, the compressor ensures that the flow separation propagating between multiple stages (stator / rotor disk pairs) completes fluid-flow failure, surging / power loss and localized damage to machinery. Has problems that can lead to it.

Foil suction-on-face fluid-flow jets can be used to reduce flow separation.
The compressor rotor and stator blades are thinner and less cambered sections than, for example, turbine stage foils, so the addition of an internal flow gallery to allow fluid-flow harvesting for the jet Is a manufacturing challenge, but in general many central blade materials are close to the neutral stress axis, so some can be removed without much negotiated section inertia or strength. Of course, small flow ducts are sensitive to clogging and can still induce horseshoe vortices and still experience lift-off if not controlled. Smaller jet engines often use centrifugal type compressors in the high pressure stage before the combustor.

  Fan stage: Fan motor blades or actuator discs are hot at a high number of thrust ratios, eg 5-10. 1-cooling to bypass the engine core, torque from the LPT to increase section thrust- A blade-type fluid-flow structure that typically converts to section thrust, typically made of high strength titanium or fiber reinforced plastic (FRP). For example, FRP blades made of carbon fiber and epoxy or other resin (and even metal blades) are subject to LE corrosion from rain, hail or sand or other inhaled small FOD objects, and even scattered volcanic ash. It is easy to generate and is contoured very three-dimensionally for the most favorable aerodynamic performance and laminar flow.

  Examples such as the 123 ″ /3.1 m diameter GE90 composite fan are recessed to provide a capability to absorb and survive FOD objects such as corrosion protection and bird impact. bonded-on) A blade with a composite 3D-shaped titanium machined LE strip is used.

  The interface between the LE EPS strip and the aft composite structure can be developed by vibration or stress-induced edge separation or erosion, and is a point that inevitably has a small gap that allows unfavorable spanwise vortices. The preferred flush strip minimizes the painted surface immediately after the transition that can peel off during operation, impeding air flow and causing additional drag and energy loss. Provides corrosion protection.

  For example, all devices of serrated foil or body TE, such as Gliebe '240, Stephens' 291 item 13, are on the aeroelastic surface of essentially the thinnest foil TE under stress. It also introduces mechanical stress concentration points that can be sites for fatigue-crack initiation and propagation.

  Noise and LEBU: Cooling / Hot Duct Flow Mixing: Young's 319 is much more to increase flow mixing, break flow vortices and reduce flow velocity gradients and noise generation mechanisms in jet engine hot exhaust flow Types of sawtooth configurations and similar 3D devices are taught. Balzer '106 teaches an exhaust nozzle chevron extension to improve exhaust flow mixing so as to reduce engine noise. The Boeing 787 nacelles use Balzer '106 type saw blades to reduce engine noise, but the resulting flow is not on the BL attached to the aerodynamic body surface. Acting at the free stream boundary between the cooling and hot fluid-fluid streams, these vortices are therefore simply used for fluid-mixing to reduce the diverged acoustic noise spectrum. Such a configuration does not improve BL flow re-laminarization, but reduces drag but increases drag, as can be expected for vortex flows that simply induce vortex fluid-flow momentum and loss. It has been reported.

  Fluid Ducting at Engine Core: In patent application US2011 / 0300342, the metal substrate is surrounded by raised vertical parts (walls) and then machined into a prior art type top-coated ceramic TBC. An array of pockets or blind recesses that can be further modified by mechanical coining / deformation to form an overhang grip that is fixedly secured and designed to maintain and stabilize this TBC. Can be concave to form. This is a derivative of the prior art that “tils” the ceramic into smaller sections to capture and maintain the cracked section of the TBC, thus minimizing spalling and TBC losses.

  Lutjen's' 342 teaches that the lower flat portion 50 of the recess is clearly labeled so that it is perpendicular to the lip sidewall 54. This design works so that the taught perpendicular crossing of the mechanical section that is under load and vibrates (in other words, a small radius of mixing or transition) reduces fatigue life and provides a point at which material cracking begins. There is an issue of forming a stress concentrator. Excellent and differently formed sidewalls with the largest possible root radius form a stronger load-bearing beam extension from the load surface and also support this surface; Helps minimize vibration modes and bending or deflection, and significantly increases the additional local moment of inertia. Of course, large flow control surfaces that are curved in a simple or combined manner can withstand the force and inertial loads of pressure and resist aeroelastic effects, but having lip sidewalls is structurally efficient (all Lutjen's prior art is eliminated, making it useful to improve (size vs. total intensity at total mass).

The warpage stress induced by vibration is detrimental to reliable TBC “tile” attachment.
In addition, Lutjen's formed retaining lip items 28 and 28 'are typically the thinnest point in the final bounded smooth TBC coating (as in FIGS. 5 and 6), and therefore It serves to carry the greatest heat load that is made through the TBC from the hot gas above. Here, the concave side wall 54 of Lutjen's inherently straight side has a larger wall root radius and therefore does not provide minimal thermal resistance to the underlying cooling fluid or gas, which is the most favorable metal strength and strain. / Not the optimal heat transfer configuration to maintain the lip (wall top) metal area at the lowest possible temperature for creep resistance and the highest thermal stress. Lutjen '342 teaches TBC protection applied primarily to static ducting surfaces, but allows TBC to be added to other items that require TBC protection, Only the technical advantages are taught, not the absolute surface or morphological drag reducing properties.

  Wentherstrom US Pat. No. 4,076,454 teaches the addition of a blade VG on the inlet ducting in an axial compressor. He does not teach or claim reduced ducting drag as a feature and this VG is a fluid-flow that does not separate on the downstream blade without any drag reduction benefits in the ducting or diffuser section Is charged to act to maintain. Flow deformation from static rotor inlet ducting is taught while the vortex indirectly improves the flow separation characteristics of the downstream rotary compressor blade.

  Nacelle and adhering pylon: The entry of a working fluid such as a gas into a modern turbofan engine in a Boeing 737-600, eg, CFM-56, is finely processed by the surrounding nacelle and most nacelles Acts as an initial internal divergence-duct or diffuser to slow down the incoming fluid-the first stage fan section and the compressor stage make the cascade blade tips not supersonic and high loss Operate without generating supersonic or Mach shock waves. High nails / nacelle AoA, some nacelle initial internal divergent fluid-flow is separated from inner nacelle wall, which is a disadvantageous condition, or the amount control of diffuser flow used is limited to avoid this Or active suction control must be added to the relaxed flow separation on the duct interior surface before the fan blades. Cooling section ducting coming out of the fan section will move through the mixing duct that diverges on the inner and outer duct surfaces and is subject to flow issues such as Taylor-Gertler (TG) on the concave section. obtain. Crossing other aircraft vortex-wakes can also cause problems such as transfer flow adhesion and surge through the engine.

  Boeing 737-600, Airbus 319 and C-17 both teach modern examples of engine nacelles using large blades or vane VG at approximately 2 and / or 10 o'clock after the inlet LE outside the nacelle. However, as minimum flow disruption and turbulent loss are required, the external fluid-flow around the upper nacelle surface at high AoA remains attached, while on the attached pylon and under the subsequent vane. It will ensure that it flows properly backwards up. When cruising, these VGs do not require eddy currents, become at a minimum AoA, and minimize form drag, but always exhibit additional morphology and wet surface skin drag. Overall, such a configuration is not the minimum drag configuration that generates vortices to improve nacelle / pylon / blade / body flow interactions.

  Since the nacelle / engine pylon is yet another area of flow interface issues and drag due to interference and secondary effects, fairing is required to control drag and fluid-flow losses. This is true for all aerodynamic bodies and devices that are mounted outside the wing or fuselage, such as structures such as pylon mounted fuel tanks, wing tip tanks or other pods or VOR blade antennas. In these bodies and devices, aircraft pitch, yaw and secondary flow vortices can cause adverse lift, flow separation, dynamic instability and flow interactions and drag. These issues also appear in hydrodynamic examples such as hydrofoils with mounting legs, links, and the like.

  Leon, US 5,156,362 teaches a retractable blade type VG for engine nacelle flow separation control. This blade upper edge coincides with nacelle and stream flow during retraction. During activity, this VG surface is angled with respect to the flow and does not coincide with the nacelle surface and will induce drag during cruising, but this is a reversible and mechanically complex feature. This is why it is used. This blade VG, when deployed, has a high BL thickness at a height to obtain maximum upper-BL free-stream fluid-flow to induce a strong vortex effect.

  Improved energy efficiency and capacity for turbomachinery, devices and processes that contain Newtonian fluid-flow, process this flow in some manner of CVG-based fluid-flow deformation technology, and output this fluid-flow It is an object of the present invention to provide Processing refers to the addition or extraction of energy or work from this Newtonian fluid-flow and / or the deflection and modification of fluid-flow velocity, pressure and / or momentum.

The intent of this new integrated CVG technology embodiment is to be “green” to reduce energy usage and associated carbon dioxide emissions.
Unlike the prior art, the new technology, integrated CVG, is an effective VG design, especially in cascaded rotating environments with low drag at low AoA values. The integrated CVG effect can be enhanced with foils or blades to passively induce additional BL fluid-flow energy for larger suction-face aft foils, but the pressure-face gained thereby The use of fluid-flow, or other fluid source, allows the separation to be further delayed through the flow control path towards the suction face to benefit stall or fluid-flow separation performance.

  The CVG can be configured to output fluid-flow mixing and reduce flow noise without additional drag and energy loss. Engine nacelles, pylons, and other aerodynamic body interfaces and surfaces are areas where drag reduction and improved flow control technology are also helped by new CVG technology.

  Centrifugal compressors, homogeneously mixed flow type impellers and diffusers, fluid pumps, turbochargers, etc. are helped with BL flow control to minimize fluid-flow separations using a new integrated CVG technology This new integrated CVG technology reduces fluid-flow drag, flow separation / cavitation, and generated acoustic noise on the impeller and diffuser blade and the fluid-flow control structure.

  Improvements in flow ducting and, for example, engine s-ducts, are substantially equivalent to general Newtonian fluid-flow (both internal and external flow) in pipes or other types of fluid-flow conduits or surface limiting means. As a case, the CVG flow control method taught herein allows for adoption on walls, surfaces, pipes, ducts and any flow control structure currently used for prior art fluid-flow control surfaces.

  The novel CVG produces a continuous vortex without a significant energy consuming lateral flow structure and convects the maximum and selectable flow energy down the downstream fluid-flow surface side that resists separation It flows in the eddy current which tends. This beneficially alters any surface and BL fluid-flow to provide resistance to flow separation and lower absolute drag when operating in non-separated flow regimes and / or off-design situations. And provide an excellent way to demonstrate this reduced drag. The basic integrated CVG structure accounts for these characteristics and significantly improves the prior art in many application locations and embodiments when integrated on the surface with an engine or fluid-flow controller. Can be configured as follows.

All drawings are not to scale, but are illustrated in detail in the features of many alternative embodiments for illustrative purposes.
FIG. 1a depicts a portion of a low pressure turbine stator or rotor blade with integrated CVG. FIG. 1b shows a pressure-face diagram of the surface detail of the LPT integrated CVG, and FIG. 1c is a view from the suction or top face containing the optional blade-tip CVG and secondary CVG.

  FIG. 2a illustrates a further example of a low pressure turbine stator or rotor blade with an integrated CVG, where the root end cross-section cut is optional with a flow control jet with an extended suction-face and a step-vortex expansion groove An embodiment added in FIG. FIG. 2b illustrates an optional control-jet fluid source pickup with pressure-face CVG valley and / or tip collection point. FIG. 2c shows a cross-section of the angular suction-face-after-facing CVG step, including detailed airflow.

  FIG. 3 illustrates an LPT stator or rotor blade having a root hub fillet and is modified and omitted by an asymmetric extended CVG step configuration as well as a bounded hub end-wall CVG. The CVG chip is doubled and shows a peak.

  FIG. 4a shows an example of a suction-face portion and a cross-sectional incision of a low pressure compressor (LPC) stator or rotor blade with an integrated ogival version of CVG with options for additional jet flow control. The figure will be described in detail. FIG. 4b shows a portion of the LPC stator or rotor blade pressure-face that includes a pressure-face CVG valley and / or a control-jet fluid source pickup that is optional from the tip collection point. FIG. 4b also shows an Ogibal pressure-face CVG array version with other pitches and offsets from the suction-face CVG array.

  FIG. 5a illustrates in detail an example of a fan blade suction face with a metal LE corrosion protection strip and an optional tip elastic weight integrated lift enhancement tab (eLET) to remove tip loads. FIG. 5b illustrates in detail one example of a fan blade pressure face with optional internal CVG, elastically integrated lift enhancement tabs (eLETs), tip CVG, and an example configuration for additional jet-flow control. To do.

  FIG. 6a illustrates an optional flow control, cooling jet, and secondary CVG array, illustrating in detail an example of a cooled high pressure turbine stator or rotor blade suction-face portion with integrated CVG. FIG. 6b shows an optional CVG array with a flow control and cooling jet, a secondary CVG array, a TE pin cooling exhaust-slot array, and a TE cooling enhanced tab array with a TE pressure or rotor pressure-face.

  FIG. 7 illustrates in detail the centrifugal impeller with CVG integrated in the flow control surface and the optional diffuser vane.

  FIG. 8 details the engine nacelle, pylon, and vane device showing where the CVG can be used to improve energy efficiency.

  Figures 9a and 9b illustrate in detail a fluid-flow duct example with an added CVG array to improve flow and energy efficiency.

  FIG. 10a shows integrated CVG steps and ribs that are embossed on the duct surface and optimized with the integrated polygon structure on the indicated “inner surface”. These polygons are reinforced with a minimum material weight, composed of a large radius (not right angle) rib-base for high thermal conductivity and beam strength against the inner cooling flow, and the opposite of this panel The side has an external fluid-flow CVG step array (not shown), such as the TBC CVG in FIG. 10b.

  FIG. 10b illustrates an alternative version of the duct (or blade) surface of FIG. 10a with fluid-flow on this TBC side, with additional TBC applied and interlocked to the polygon array.

  FIG. 11a is a cutaway view of a combustor design in which CVG was used to provide lower drag and energy loss, and improved fuel injection and mixing. FIG. 11b shows an alternative embodiment using a modification of the ceramic body, wall and CVG array to form a rich-burn pore volume.

  The best mode for carrying out the present invention is an example of a turbofan jet engine, which has many typical features that can gain performance gains by applying an appropriately configured integrated CVG. Teaches various areas and application methods. Turbofan engines provide numerous examples for useful integrated CVG applications because they use numerous hydrodynamic surfaces that handle Newtonian fluid-flows to generate useful work and effects. This example is just one form of fluid-flow machine that uses gas as the working fluid, but most CVG methods account for speed, pressure, Reynolds number, fluid phase (gas / liquid state transition) and flow viscosity. Easily applied to many useful examples using liquid phase or mixed phase Newtonian physical fluids, for example, to obtain similar improvements for drag and separation / cavitation reduction by scaling the geometry to Can be done.

  Item 1 of FIG. 1a is an isolated low-pressure turbine (LPT) rotor or stator blade that includes a profile consisting of deep camber for reaction and shock and diffusion action, where a rotor or stator disk is typically used in a cascade device. The root-end of the stylized example of "bucket" is described. For simplicity of expression, this example is typically twisted and / or twisted and / or to provide a radially constant reaction velocity profile and secondary flow control from mixing rotor (reaction) and stator (diffuser) foils. Not tapered. Blade root fittings, hubs and tip end-walls, and adjacent overlapping blades and upstream actuator disks are also omitted for clarity, but in the final design as known to those skilled in the art of cascade fluid dynamics. Is used. Item 2 is the convex suction-face downstream surface and the concave pressure-face downstream surface is region 3. This fluid or hot gas arrives at a designed blade input angle that defines a local foil or surface-actuated AoA, and this flow is due to geometry and hydrodynamic forces at the LE stagnation line 4 and suction and pressure-face Divided above. In the case of a rotor disc case, after working on the blade foil (towards the suction-face side) and generating a force vector, the working fluid exits at the output exit angle designed at the trailing edge 5 (TE). . Blade lift, which is resolved tangentially around the turbine rotor axis, generates torque output from the input fluid-flow energy, and the resolved vector component in the rear axial direction provides additional pressure across the cascade section. Drag or energy that causes loss and disadvantageous momentum loss.

  The on-design input angle for the upstream input fluid source and the output angle for output fluid transmission after CVG processing define the peak amount of energy that can be extracted from the fluid-flow of the input fluid source in the cascade section, where Assume that the flow of this section at its operating point is configured for minimal energy loss due to flow turbulence, separation and viscous losses.

  With some flow conditions that are sub-optimal, e.g. lower Re numbers, the suction face will experience flow separation after pressure minimization, which will increase cascade losses, It will reduce efficiency and increase engine SFC. While crossing the concave pressure-face 3, fluid stress from centripetal acceleration can also induce energy loss and BL thickening, for example, from a TG vortex structure. Cooling is generally not required for LPT blades because the gas flow is significantly cooled through the HPT turbine section and the temperature is lower than, for example, a nickel superalloy blade material is safely handled.

  To help improve flow across the suction-face, re-activate the boundary layer, the BL streamline, so that fluid fluid-flow mass deceleration begins to cross the local surface due to fluid conditions It is beneficial to have sufficient momentum so that this streamline flows adjacent to the blade and is attached at an adverse pressure recovery gradient after the suction pressure-peak line 10. In order to provide more flow energy to the very lowest layer downstream of the BL on the suction face, the upper conformal vortex generator (CVG) array 6 is essentially integrated into the front of the suction face in the accelerated flow region or Built and designed and built, this structure accelerates a portion of the incoming free-stream fluid-flow energy into a pair of powerful counter-rotating vortices that flow backward from the array of upper CVG chips 7 Designed to transform, this can provide suction-face separation control similar to conventional VGs that cannot actually be used in such complex flows and small geometry environments.

  The integrated upper CVG valley point 8 is located in the cord direction so that the fluid-flow entering from the suction-face flow inlet 9 intercepts the pair of bifurcated angular aft-facing step edges 24 of FIG. Or become experienced. This high velocity flow is either parallel or tangential to the suction-face flow inlet 9 blade surface or foil design-intention and down so that this flow is along the top edge contour of the step. Since it cannot rotate sharply, it undergoes fluid separation (step shear separation region 27 in cross section of FIG. 2c) along and below the intercepting top edge of this step, all in the lower fluid-fluidized bed.

  Such an intentionally angled step-down flow separation mechanism is such that the separated lower energy and the bottom BL draw fluid-fluid mass part along the step bottom edge and on the upper CVG chip 7 side. The flow begins to wind in a confined and free-flowing step-vortex, item 25 of FIG. 2c. The step-vortex consisting of the incoming fluid momentum layer at the bottom of this sheared or broken lowest energy then meets and counters the opposite rotating vortex from the other side of the tip, which Along with the surface, it flows backward in the filament state of a counter-rotating vortex pair tightly bound to the surface. The incoming non-shear flow momentum layer and the upper side, which are not entrained in this step vortex, will continue to be continuous as a high energy outlet flow 23 passing over the upper part of the step vortex structure, and then the initial downward velocity element Step exit-streamline reattachment position as currently higher energy and thinner BL with reduced transition turbulence, U-shaped vortex structure and drag loss in such downstream BL region between CVG chips Reattached downstream to the surface at 28 (FIG. 2). Thus, the CVG step geometry acts as a “BL-slicer” to generate beneficial vortex flow, but also provides a controllable BL relaminarization effect downstream of many step widths between chips. Especially for surfaces that are not deformed with zero and low positive and negative AoA.

  This is an additional drag reduction mechanism where the traditional VG does not appear, because the traditional VG increases the drag at zero and low positive and negative AoA values, where the VG AoA expansion capability is not active. It is because it has been. The approach BL flow velocity vector diagram 33 shows a normal BL slope from a low surface velocity, increasing higher in the BL. Downstream of this step, the exit BL velocity vector diagram 34 shows that these lower BL layers are separated into step-vortices and have greater velocity and improved adhesion than the lowest entry layer that is discharged through the CVG tip vortex-pair. Indicates that it has performance. The conceptual top of the BL or free stream is shown as streamline Vtop.

  The CVG step-vortex 25 is continuously predictable along the optimal mass-accumulation length and angle and flows backwards in a controlled manner, e.g., captured by a long spanning after-facing step. It is different from disordered vortex flow. The primary tip-vortex pair of the CVG tip is very strong, geometrically stable and efficient from the total shear flow region of the fluid sheet that intercepts or traverses the CVG step along the width of the embodiment. Harvest fluid energy, fluid mass and momentum. The filaments of this CVG tip-vortex pair can also affect the downstream BL in which they are enclosed, break the formed fluid-flow separation bubbles and structures, and depending on the foil design, blade stall- It can work like AoA with a higher conventional VG in that AoA can be significantly extended by about +5 degrees. The adjacent region of this BL is affected by the passage of an active CVG tip-vortex filament, and the extra fluid-flow energy tends to suppress the U-shaped vortex and this adjacent BL region from becoming thicker. It is in. Such CVGs extend the control range of AoA or local fluid-flow surfaces that can be processed with reduced energy loss from the reference surface configuration.

  Up to the separation point, the blade surface design of this new technology will have a “normal or ideal” geometric surface design that ensures efficient fluid-flow entry, and before this step any upstream Note that it does not induce additional drag or horseshoe vortex. A ramp-style, wheeler or blade-type VG that attempts to generate vortex at this point must deviate from the correct or ideal blade shape, and is a constant distance within the higher BL flow while generating drag. It will only attack inefficiently.

  Because the integrated CVG element or array can efficiently define the desired LE entry surface or foil geometric design for new design criteria after this step as well as the ideal foil design. Surface design will efficiently obtain this surface with such new integrated CVG design intent. In this manner, the newly designed foil or surface becomes the correct fluid-flow setup in the critical laminar flow LE section with respect to the original foil design, and the aft section is reduced inward by the step offset. For added CVG to foils or surface designs not formed or tuned for CVG addition, this LE entry section is effectively thickened by an additional CVG array film / step thickness, for example, twice this application area. ,Collapse.

  Conformal eddy current generators are processed by working on the lowest boundary layer across the aft-facing step (at a certain height), and even with extremely high centripetal acceleration and secondary flow faces above the BL level, It produces a chorded, continuous primary tip-vortex filament that is contiguously bound by these central chordwise low pressure joint stagnation lines so that it is in close contact with the downstream blade surface.

  On a helicopter rotor blade with 1,200 gravity radial tip acceleration and 700 fps velocity, the CVG tip vortex-pair stagnation line captures surface dust and on the blade with a strong radial force and other secondary air flow face As it remains in the cord direction, it effectively “prevents” this dust and the lowest BL flow, which completely removes dust from the blades without using this new technology, CVG technology. Is removed through flow visualization. Such a strong step and chordal vortex flow distribution is how the CVG efficiently transports energy from the higher entering fluid-flow momentum layer and spreads in the chord and span directions to form a flow separation bubble. It will be described whether it is useful to control an arbitrary aft region to be separated (for example, on the trailing edge 5 side).

  Primary CVG tip-vortex pair and step-vortex flow will have many associated secondary vortices and eddies that tend to make pressure and momentum similar, flow shear is a CVG structure and step, and This structure and step aft are minimized.

  Along the CVG step, dust accumulation teaches that the step face and base are also stagnation regions, and some lowest level lower momentum BL flow transports the primary tip-vortex pair Once separated, this residual higher, higher energy and higher momentum layer is slightly downstream so that it reattaches as a new, more active downstream BL trapped between the CVG chips. Teaches that an efficient flow path can be found. The primary CVG vortex pair can be made small, can be in a geometric size range of steps and BL thickness, and is generally not exposed to free stream or secondary flow on top of the abstract BL Pay attention to. This is because the CVG vortex can be sufficiently submerged at the lowest level of BL, and this CVG vortex is at least more persistent in geometries downstream than those reported by NASA, for example, due to other mechanisms. It is allowed to be on the order of a reasonable and efficient size. There is no incoming flow loss-generated horseshoe vortex between the CVG elements in the array.

  Most other VG structures have high drag (eg protruding ramp type), are structurally sensitive (vane type) and geometric to a limited range of operable Re flow regimes It generates limited low-energy vortices (eg, dimples) that are constrained in shape and do not produce persistent and submerged vortices or are affected by secondary flow and effects. Prior art active flow control devices on blades, such as horned jets and synthetic flow jets, can re-activate the boundary layer to reduce flow separation, but energy loss horseshoe or It induces a kidney-shaped vortex, affects only a limited range of flow relative to the fixed point, is generally more complex, and has a significant drag reduction against the reference undeformed geometry Not shown.

  Reactivating CVG's BL region aft reduces the attack-free (low drag) angle of attack AoA by only about +5 degrees before the separation bubble eventually forms and drag increases while lift decreases. Allow the blade to expand. Such an improved AoA extension of the A-curve occurs in other test foils and teaches that this fluid-flow physics is well applied to blade geometry and Re number. Such improvements to LPT blades have a design rotation-angle of the new blade cascade design that is more compact and has a smaller Zwiel factor for turbine and / or compressor cascade designs with fewer stages. It is possible to increase).

  A more valuable feature of such new CVG technology is that blade drag is significantly reduced by about -5% to -10% at the same lift and AoA from zero incident angle closer to the stall angle compared to the baseline. It is a point to do. This is due to the fact that the reactivated suction-face BL is also thinned at a higher speed, thus generating less turbulence-fluid loss while generating lift. CVG array vortex flow and BL activation are passive and occur in a very efficient manner and do not adversely affect the designed blade drag performance, but reduce performance across the fluid-flow range Decrease performance.

  For the integrated lower CVG array 11, an example of a lower CVG valley section is indicated as 12, and also a blade foil profile so as to form an angular after-facing step in the same manner as the upper CVG array 6. Enter inside. This pressure-face has different chord pressure and velocity profiles, but the lower CVG valley section 12 is configured in a manner similar to the example in the upper CVG array 6 with respect to the upper CVG valley section 8.

  Through testing on the foil, some of the blade drag improvements improve the flow on the foil pressure-face and prevent the formation of the TG vortex from the stress due to the concave centripetal flow, for example, the lower CVG array 11 Moreover, the point that it comes out by including is taught. The lower CVG array 11 also acts to thin the downstream pressure-face BL layer, which reduces turbulence and drag.

  Although this blade can be designed to work with either one or both CVG arrays, the suction-face CVG array is a problem known in the main prior art of LPT blade suction-face flow separation. Have one of these.

  In a cascade, for example, a shock wave from a suction-face pressure recovery flow is a flow through the blade, especially if the thickness of the blade TE structure induces a blade-pass flow-choking and thereby a shock wave with constant fluid-flow. Can be disrupted. Intentional CVG vortex flow that affects Shock Boundary Layer Interaction (SBLI) with lambda-foot shock separation can be used to mitigate shock and energy loss on foils, fluid-flow control surfaces and ducts .

  Effective CVG configurations and designs benefit from the fact that they work well for a wide range of geometries and can be tailored to meet specific requirements. Tests show that as CVG geometry is changed, this result is generally within a range of smooth changes without fast fluctuations or singularities, in other words, they behave well with a large range of design conditions. It shows that. Since CVG always starts at the bottom of the BL, they do not attack the outside of the BL with any practical Re value.

  The vortex state starts with a Re number of about 300 in standard atmosphere, and beneficially about 30,000 is sufficient energy. From about Re 30,000 to 500,000 where the LPT blade can operate, the CVG can be configured to provide improvements. From Re numbers 500,000 to over 10 million, for example, CVG is very effective on isolated foil and body sections and hydrodynamic structures containing rotating components. The CVG step may be a small part of the BL height at the operating position and still produce very strong and useful fluid-flow control capability, but at the Re operating point, which is transformed into a very common case, It can also be usefully used as a larger part of the local BL thickness or even several times.

  A conformal vortex generator or CVG has (a) a low-loss approach configuration matched to the entry surface-flow streamline, and (b) such shear flow along the output surface, (c) accumulated. Step-Communicating to the exit point to remove vortex shear flow-Intercept flow-Inclined after-facing step to induce the lowest level of ingress fluid-flow to shear in the vortex And (d) broadly described as a fluid-flow deformation element designed to allow the incoming high energy non-shear layer balance to be rebuilt as a new downstream boundary layer with higher energy Can be done.

  The CVG flow-angular step is typically configured with an angle of about 22 degrees in the span direction (relative to air as the working Newtonian fluid) with respect to the streamline vector of the local input flow, but some performance It operates around such approximate nominal values with changes, and such exact angle depends on the working fluid conditions. Thus, the CVG step angle can be adjusted to be optimized for different local flow directions as well as integrated into the flow at the hub and tip end-walls and the like.

  The CVG step is typically paired with a chevron or triangular structure at the rear tip while the tip is facing backwards to produce a persistent and stable exit tip-vortex pair, and the CVG step It can be combined with a variable offset array of many adjacent CVG step edge structures having varying angles, step shapes, step heights and step lengths to allow deformation of flow vectors and states. This CVG design shape allows for precise control of fluid-flow in different respects for surface areas constructed with fluid flow. A CVG can be configured with a characteristic step height, length and angle for a given surface shape, and for example, a local angle of about 22 degrees for a 50 mm wide LPT blade cord, for example. Fluid-flow intercept, triangular shape, 3 mm step length, 100 μm (micrometer) step height, selected around the expected Re value and high velocity laminar transition region for typical blade foil sections May be located.

  These shape starting point values can be easily changed and optimally verified by a series of actual blade step tests and performance measurements, but due to their small size and operating stress, they are practical for additional CVGs in this LPT environment Not right. The CVG step height is adjustable with respect to the width range and steps against the design operating range of the Re value while refusing to make a reasonable level of incoming lower BL flow a primary chordal vortex. It is configured to generate a sufficient vortex state along the edge. Such a CVG design process is also beneficial for fixed stator blade arrays to reduce drag and increase rotational-angle capability before off-design separation with variable Re values becomes a problem. Can be used.

  It is known that a span step along the foil surface perpendicular or at 90 degrees to the flow typically captures a confused span step vortex and increases the drag by about + 5% relative to the reference unmodified blade. And the most preferred case is when this step is about 22 degrees to flow with about -10% drag reduction, eg when dismantled in the CVG segment, but these numbers It is not limited to. Interestingly, the test shows the worst case drag that is greater than the 90 degree (previous afterfacing step edge) case when the CVG step is about 60 degrees to flow and this step accumulated length is long. This is because, at some point, the step vortex is overdriven by the accumulated low energy fluid mass with step-vortex magnitude and flow capacity, and begins to expand to obstruct the incoming streamlines, so We show that this CVG mechanism is even worse than the linear spanning afterfacing step, which is disadvantageous to drag. Lower drag is a core design goal, but having the ability to generate both controlled increases and decreases in drag is a novel fluid-flow modification tool in many precise ways. So that it can be used as

  The mechanical and manufacturing sharpness and definition of the CVG structure is not particularly critical, but the step top-edge is “the sharper” (minimum radius) and the ingress flow is the minimum secondary eddy. More stable and predictable. The CVG valley can also be simply configured with a radius, and the CVG tip can also be configured with a radius or other geometry that is sharp or has minimal performance sensitivity. The bottom transition of this step relative to the output surface is at the stagnation point along with other secondary stress vortices and can be set with a suitable radius fillet that does not interfere with the top-edge shear function of the step.

  For both cast and forged, assembled or machined parts formed with any combination of processing, materials or manufacturing methods, both assembling and minimizing vibrational and bending mode stress concentrations during operation In order to relieve stress, it is beneficial to form the radius of the bottom edge of the step. At the top edge of this step, the body etc.-deformation rate and deformation line are typically clear.

  Positioning the CVG in a high acceleration and / or vibration environment is that they are spatially configured on the same opposing surface to avoid reflection points and structures consistent with the tuned vibration mode. Optimized. So a regular array on one face is optimized by adjusting the individual CVG elements, tip and valley positions, CVG step length (effectively defined pitch) and angle in a non-uniform manner. Although this reduces blade vibration response and does not enhance unwanted blade bending, coupled and excited vibration and mechanical resonance modes. This can also be done for both blade faces to cause increased fatigue issues so that the blade deformation rate is not consistently concentrated between the suction and pressure positions.

Item 21 of FIG. 3 shows an example of an asymmetric suction-face CVG “V-form” having a left-side angle that is more acute than the right-side angle, which makes the CVG asymmetric in a slightly different manner, Be able to handle BL flow on the side. This BL mass flow to the left side is effectively further narrowed and the step-separated BL flow to the left tip-vortex is consequently smaller and less with the left tip-vortex having a lower force. On the right side of this CVG, the broader intercept of the incoming flow means that the right tip-vortex will be larger and stronger to accommodate. The balance between the force and vortex state vector and magnitude between these two asymmetric counter-rotating tip vortices is changed so that they flow further on the left side on the suction face and they break up after TE As a result, the remaining clockwise swirl state magnitude is balanced and the blade inner and root ends are assumed to be in the position of item 1 shown in FIG. For example, this is matched to the clockwise “or polarity” of the regular effective blade vortex lift sum, as shown in FIG. Depending on the final structure of the residual swirl state, it is possible to affect the bottom or on the body lift coefficient C _L. In such a configuration, when the pressure-face CVG is changed in the opposite direction (in other words, the CVG left side is wider when viewed from above), this is also effectively induced to wake-circulation lift - now applied aggressively vortex sum, increasing C _L. Drag reduction due to relaminating CVG BL is altered by small vortex position variations, but essentially the same reactivated mass flow occurs per unit width of the BL entry width, Note that it is still valid among CVG chips. The passage of the modified tip-vortex pair affects the streaming vortex conditions that occur in the BL regions that are immediately adjacent to each other and changes the combined lift vortex states from these regions.

  FIG. 1c shows a close-up detail view of a set of CVG items. The triangle represented by the vertices A-B-C is an example of a V-shaped CVG. As an example, the BL entering from the width A-B is divided, and the cut lower BL fluid mass is determined as step A. It moves backward along both -C and BC, and is operated to evacuate it with a pair of vortices that flow later from tip C. If a CVG is used as an additional example, for example on a helicopter LE EPS system, the smallest and most reasonable CVG element can be a CVG section of width AB, with suction and pressure continuously mounted around the LE section. -Includes a face CVG and can then be used as a combined array of many of these basic CVG structures. Simply, a CVG is typically made of an array of many combinations of CVG tip sections that can be mounted adjacently on a hydrodynamic body to alter flow. Small practical gaps between attached CVG elements have minimal effect compared to CVG effectiveness and performance improvements. Additionally, these larger CVG arrays are configured to be convenient to handle, apply and combine alignment properties and layers that exhibit wear as they corrode with fluid-flow.

  FIG. 1a describes the individual CVG elements as basically triangles, but this example is merely for ease of illustration, and in fact the most preferred performance is used for NACA low loss diving inlets. With step edges in a fundamentally ogival form. These NACA inlets also generate edge vortices to slow the inlet flow but have slightly different geometries and are not arranged in an array to reduce morphological drag or reactivate BL And very different from the new integrated CVG technology, except that vortex flow and optimized hydrodynamic geometry are used, with a step height several times the local BL width .

  The Ogibar CVG configuration typically follows a slight upstream position and more acute angles compared to the triangular step line, so that it deviates from the triangular step-line when approaching this tip. This extends the limit of the usable upstream surface of this position-cumulative step confined by a defined aft-facing step-vortex flow. This incoming separated fluid-flow mass accumulates along an angular step, and the aft section tends to contain more mass, increase the vortex magnitude and velocity, and the incoming fluid-flow Tend to grow further. If the step vortex grows too large from the shear fluid mass, this tends to affect the non-shear step that flows out at these locations—the primary step—the vortex structure 25 is further collapsed and the external step— There is a tendency to extend the vortex layer or to adversely break this step vortex to some components. Step-vortex 25 in the cross-sectional view of FIG. 2c shows a slightly upward extension to emphasize the effect of this vortex location over step height and geometry.

  This optionally provides a step-vortex expansion groove 13 formed in an optimal position under the step-vortex path to accommodate the step-vortex extension by fluid-mass accumulation in some embodiments. It means that it is beneficial to do. This is an obstacle and energy loss to a non-shearing outflow that is reattached as a new BL downstream for a given step height, excessive impact outside the growing step-vortex diameter To avoid. In CVG chips, these extended grooves (or other shaped trenches) can be merged or paralleled in opposing steps to reduce deformation at higher fluid-flow. The eddy current expansion groove 14 can extend by an aft amount and can provide a guide for the flowing tip-vortex pair. This vortex expansion improvement allows the separation of a larger mass of fluid-flow entering at a given step height while allowing stronger downstream BL reactivation and tip-vortex flow. Although structural impacts of these material removals are considered against foils or aerodynamic / hydraulic surfaces, in many cases, for example, assembly of 3D surface structures, which are forgings, is a section inertia cross section, Stiffness and surface mechanical properties can be improved. The step-vortex 25 has many secondary flow structures and eddies, such as an upper step eddy structure 30 and a step shear-homogenization eddy 32 that act to balance inertia and shear forces.

  Adding the optional step shear guide 35 section as an optimally shaped and assembled ridge further suppresses the step shear-homogenization eddy 32 and lowers the flow loss from the eddy or secondary vortex. And helps to form a spatial cutoff edge for backward expansion of the step-vortex 25 with variable Re conditions.

  In the additive CVG embodiment, the replaceable additive CVG EPS material can be elastic heavy integration, plastic, resin, metal, metal film, ceramic coating substrate, carbon fiber, carbon-carbon, silicon carbide or metal fiber matrix or ceramic metrics composite A material (CMC) or other material combination is applied to a composite or FRP material or metal helicopter rotor blade, or vane LE, etc., and the expansion grooves 13, 14 are in partial height steps and CVG alignment marks Along, for example, it can be molded or integrated into the foil or body surface with either a suction or pressure CVG step. The additional CVG EPS film can then be applied in mechanical alignment to these integrated CVG characteristics to generate a combined step characteristic and CVG functionality. The FRP (composite) surface or, for example, a metal rotor blade or vane / stationary foil LE can be integrated into the LE by any assembly means, in which case corrosion or paint damage from dust, rain, etc. is an important issue As such, the combined CVG combination with add-on and field-exchangeable additional CVGs further protects the LE surface to maintain energy efficient laminar or low turbulent flow. preferable.

  CVGs cascaded in adjacent aerodynamic spaces must generally provide the most favorable combined benefits due to eddy current interactions. In particular, if not properly separated from the rotating surface, vortex flow and flow must be tightly controlled spatially so as not to interfere, or separated in the flow direction to minimize disturbances. Wake interactions from upstream stators, rotors and other transition disturbances are less problematic in performance because these are larger structures than CVG tip vortices and are typically outside the BL, and flow is limited to extreme Re In order to be able to operate efficiently against the value, the flow can spread across a number of small CVG elements that can “take” or absorb this vortex, rotational or shock flow energy. Periodic oscillations measured on helicopter blades only about 30% through the flight envelope and NP rms deformation reduction teaches that CVG can operate very efficiently through flow perturbations and large periodic flow extremes of AoA .

  A controlled amount of fluid mass in the lower BL layer can be effectively separated from the incoming surface flow (and not accepted by the CVG tip-vortex pair), and this can be a porous aerodynamic surface or a suction stripper Note that using step edges or slots is an effective target for active suction BL control systems. Many prior art active systems have been abandoned due to clogging problems, and the CVG used in this position for BL control is dominated by the addition of CVG tip vortices to extend the surface control effect , Again comes to lower the drag. This can be shown by using an attached CVG on the LE of the deep-codefoil LE-like wing in front of the Piper PA-31 Navajo aileron, which gives the Aileron control authority at the wing stall. This is to improve, lower aircraft stall speed, and increase cruise speed. This is an example of a non-rotating fluid-flow environment such as an LPT / Fan / LPC stator, whereas a helicopter rotor or propeller / prop-rotor has a step length of about 20 mm for a foil cord of about 180 mm. Is an example of rotating fluid-flow control, such as LPT / Fan / LPC rotor blades, utilizing a 300-500 μm step height but with different stiffness, aspect ratio, etc.

  In combination with LPT rotor and integrated CVG that can be used additionally for stator blades and other methods of controlling integrated flow, fluids that add or jet fluid-flow and BL momentum in or after the CVG step. -Use a fluid jet. These jets may be active from a fluid pressure source, such as prior art synthetic jets, or more after being properly routed to the suction side surface via an array of paths, passages and plenums. It may be foil pressure-face fluid incorporated around the high pressure or lower face CVG array 11.

  The cross-sectional view of FIG. 2c shows an aft angle jet fluid injection port 37 and / or measurement orifice that can carry fluid-flow at an appropriate pressure and flow rate from an injection plenum 38 to an output surface such as 2. The addition of a low drag fluid-flow injection cavity 36 at the surface after the after-facing step edge 24 and between the CVG tips is an optional feature and improves fluid-flow performance. Adding a fluid jet in this manner with an aft angle (advancing into an optionally formed cavity) of the outlet high energy flow 23 to suppress jet-lift-off with high blowing and flow momentum ratios. Utilizing a portion of the lower velocity vector helps to spread the jet fluid stream in the lateral direction and in the flow direction. The jet-jet is such that the contoured form of the fluid-flow injection cavity 36 and the branching outlet fluid-flow branch further to the BL reactivation capability (as in the prior art Coanda effect or slot blowing technology). Allowing the added energy of the fluid to be placed at the lowest BL position close to the surface, the best performance is when there is minimal velocity difference / shear and turbulence in the merged outlet high energy flow 23 It becomes. The advantage of combining CVG with the jet or suction port is that such an inherent drag reducing CVG structure can be used efficiently with increased flow, further improving fluid-flow performance.

  Since the aft angle fluid injection port 37 is under the outlet high energy flow 23, the dynamic pressure here is lower than the BL stagnated at the lowest level, and the designed jet mass fluid-flow volume is A low pressure at the injection plenum 38 can be provided efficiently. Due to the effect of the lower outlet high pressure flow 23, lower pressure flow and larger volume capacity are allowed for the larger sized jet fluid injection port 37 and are less subject to clogging with debris. It is also possible to use a number of example jet fluid ejection ports 37 arranged on this surface or arranged to transfer into one or more example fluid-flow cavities 36 between CVG chips, Because of the selection specification, there is a larger fluid-flow that spreads in the lateral direction, and can still be used even if it is partially occluded, and there will be other alternating and extra jet orifices active.

  Such jet flow enhancement can be used to utilize additional fluid-flow energy to help control BL separation and drag, and the injection plenum 38 can be a pressure-face CVG valley section 12, or Low-drag fluid pick-up optimally close to the high-pressure stagnation point, such as a filtered compressor bleed or auxiliary air source, or a pulsating acoustic pressure source, or even a net-zero mass-flow method It can be transferred by a pressure-face fluid transmission port 39 located at point 40.

  Using a low drag fluid pick-up point 40 as a suitable pressure fluid source is an example of beneficially coupling the surface of other parts of the 3D fluid-flow structure, and the size of the port and plenum is the pressure difference. It is configured to provide a correctly measured fluid-flow. Additional fluids for jets-Jet fluid momentum can be fixed or non-variable pressure if derived from a fluid source with variable off-design and Re values, with flow energy varying from surface or pressure with surface and engine flow and speed conditions Generally follows variable Re conditions without the need for any optional flow or pressure regulation to avoid jet-lift-off, which can occur if a fluid-flow source is used to activate the jet. To do. This pressure face fluid, which is effectively incorporated, acts as an active suction BL control on the pressure face.

  On the rotating foil or body surface, the example of the jet fluid injection port 37 is configured to be designated slightly outward at the plenum starting point so as not to accept heavier dust and debris flowing outward at the plenum, and A large angle or path deflection can be coupled to an example of an injection plenum 38 having a shroud-type or backflow entry port that causes the jet to rotate and enter and become unoccluded. Such inertia-separated dust and debris generally move outward in the centripetal environment (or due to flow pressure / momentum in the stator foil case) and then a suitable plenum rejection tip close to the TE. An orifice 41 is optionally discharged. The plenum rejection tip orifice 41 can be larger and centripetal acceleration to control the self-cleaning process by partially plugging the discharge orifice (without throwing away excessive fluid-flow) at a sufficient operating speed. As the rotor blades are decelerated to an idle state, a simple force-control mechanism opens this self-cleaning port to the maximum while fluid-flow is still ejected through the turbine stage. Allow damping of excessively large particle accumulation.

  A low drag local source of pressure fluid taken from the low drag fluid pick-up point 40 around the pressure-face lower CVG array 11 via the fluid transmission port 39 is a high momentum moving past the higher BL flow. It is configured not to take in energy fragments or dust.

  (A Jet Fluid-Supply or BL Suction Pair) Alternate Pressure-Face Configuration for Jet-Blowing is a Second Example of Pressurized Injection Plenum 38 Separated from the Example of a Plenum Transferring Suction-Face Jet This is a version of the jet fluid injection port 37 that is transported by the pressure-face fluid pick-up section 39 located in the opposite direction with a low drag fluid pick-up point 40. This allows, for example, a jet fluid pressure source configured to be separated from filtered compressor bleed air to increase pressure-face separation capability.

  These pressure-transfer blowing-jet methods additionally improve downstream BL momentum for both suction and pressure surfaces, and a further alternative is to recover additional lower energetic fluid mass from between the CVG tips. In addition, the fluid-flow injection cavity 36, the injection plenum 38, etc. are coupled to the fluid suction source to provide a downstream BL with increased momentum.

  A slot or 3D-shaped flow convection structure can be selected instead of a round hole for the jet fluid injection port 37, for example, and the method selected can increase assembly difficulty and mechanical integrity of the foil or blade. Consider. The injection plenum 38 prevents centripetal force induced pressure gradients from overdriving the outer CVG fluid-flow injection cavity 36 region or starving the inner CVG fluid-flow injection cavity 36 region. It can be assembled into multiple separated spanning sections while feeding the separated CVG regions. The size of the jet fluid ejection port 37 can also be varied along the blade span to further improve the fluid ejection flow due to the pressure gradient. To assemble the example injection plenum 38 hollow, material mass-removal near the body or foil centerline does not significantly reduce section inertia or bending strength, but reduces blade, turbine and engine weight.

  FIG. 3 shows an LPT blade connected in route 1 to a turbine hub wall 45 having a wall fillet 49, showing other possible combined variations of the CVG embodiment. Item 20 shows the longer CVG v-section in an array. Item 42 describes a CVG tip cut short in the span direction to widen the tip-vortex pair separation. This also includes a larger amount of included tip width BL that can flow and mix directly into the tip-vortex pair and be surrounded by the tip vortex to enhance this vortex.

  Item 43 shows a CVG chip that has been modified to also generate two wide spaced apart counter-rotating vortex pairs.

  In such a deformation, an additional set of CVG steps with a smaller acute angle and contained inside produces a smaller counter-rotating tip vortex bound to a larger outer tip vortex. This now widens the area affected by the two primary and two secondary streaming tip vortices.

  Item 44 shows an additional tip deformation that creates two primary tip vortices in the middle under the CVG step and then produces a smaller tip width at the CVG vertex with two small secondary tip vortices.

  In all these cases, the corresponding width of the CVG step in the span direction precisely controls the mass flow within each vortex structure while allowing a controllable flow effect.

  CVG structures and arrays can be used around the perimeter of LPT cascade 3D blade paths and entry surfaces, such as wall CVG array 46, to improve rotor or stator drag and flow. In a rotating rotor blade environment, a series of examples of CVG are disadvantageous for drag performance due to eddy current interference with angular secondary flow, but in multiple cascade configurations with optimal spacing and offset, or secondary flow separation In some cases for other purposes such as deformation, it can be used on the stator.

  A symmetric or asymmetrical second array CVG 47 (stepped down into the body) at the trailing edge 5 deforms the blade wake and lifts it because the blade wake is generally immediately on the surface before the TE outlet flow. / Can be used on any one of suction and / or pressure-face to improve vortex conditions. In the case of a rotor, these are less affected in the rotational environment than, for example, the CVG used as the second column close to the upper CVG array 6 or 11.

  Possible tip connection end-wall and blade path root-end blade root platform, constant radius type 3D ducting flow surface and fillet, CVG drag to reduce BL relaminization, and It can also benefit from reduced flow separation induced by secondary flow, such as blade vortex flow.

  LPT “squealer” tip end or outer tip shroud surface often wears and expands due to strong operating heat changes, and occasionally makes contact with the tip-seal tip-seal shroud and duct surface, polishing the tip path And designed to clear. There is a greater pressure differential and secondary tip flow at the tip-gap over temperature, and the tip-seal shroud surface has a BL and secondary flow that is driven by a high relative fluid-flow tip velocity.

  The LPT “squealer” tip end or the end of the outer tip shroud surface can use an integrated tip-end CVG array 48, with the tip designated downstream in the local relative fluid-flow direction, and This allows the removal and release of the adjacent low energy shroud BL and reactivation so as to reduce the loss and drag of both the shroud and tip structure. The tip-end of the tip-end CVG array 48 flows in the blade-tip pressure-differential pressure-face side, and this step-vortex is now placed across the tip end-flow. Collapse the blade tip-vortex structure as a more consistent and powerful flow structure.

  Turbine stages, surfaces and ducts now also have a fluid-flow large wet-surface region with a thickened BL flow on the suction and pressure fluid-flow face, integrated CVG BL relaminarization Operates to reduce morphological drag and fluid-flow losses and reduce wake momentum defects. CVG tip-vortex flow strength, surface deposition and velocity allow new mechanisms that allow continuous and rapid re-establishment of the flow deposited after periodic upstream wake disturbances. This is also similar for other flow sections such as compressor stages, combustors, ducts and the like.

  The LPT turbine blade design taught herein has lower drag and fluid-flow and energy loss, improved flow reliability, greater operating tolerance for off-design conditions, lower stiffness and greater per stage It can be used to optimize new turbine designs and configurations of rotor, stator and duct passages with rotational angles.

  Alternatively, these new technology blades can be configured with lower drag losses and provide improved engine drag performance and lower energy losses within current long-lived engine investments. It can be applied as a “plug compatible” upgrade element that matches the interface geometry and flow angle to the current turbine stage at service update intervals. Therefore, while a new integrated CVG type LPT design can take advantage of this new CVG technology, to improve the SFC of current engine investments, improve the low Re flow separation margin and lower drag It is also possible to provide older technology blades in the current LPT stage cascade, such as the CFM-56 turbofan engine, to create “plug-compatible” LPT blades that function and replace properly. Is possible. LPT rotors and stator blades are one of the lowest risk deformation areas in turbofan engines.

  Instead, these CVG array embodiments and techniques allow wind turbines (such as Godsk '259) where stall AoA and operating envelopes can be increased without increased drag, and indeed blade and surface energy losses can be reduced. It can be used for blades or other similar fluid-flow regions such as propellers. Despite the foil design, aspect ratio and stiffness etc. differing from these mentioned LPT cascade embodiments, an integrated CVG can also be configured on these fluid-flow control surfaces.

  Axial compressors: Axial compressor stages are very thin and fine-edged high-speed transonic foil bodies (reaction-buckets) to allow momentum transmission and maximum compression efficiency within the fluid-flow at each stage. Typically not designed). These foils or blade sections benefit from CVG applications integrated in the same general manner, as shown for LPT turbine foils. Extending the axial compressor rotor and stator stall AoA capability at on-design rotation angles is to improve compressor surge (and surface stall and separation) margins. LPTs or other turbine stages are not prone to experience as bad as such cascading failure or surge mechanisms of axial compressors.

  FIG. 4 illustrates a typical example of an isolated axial compressor blade body 50. Compressor Low Pressure Compressor (LPC), Intermediate Pressure Compressor (MPC) and High Pressure Compressor (HPC) pressure stages have varying blade lengths, varying routes, depending on disk area, local flow and pressure requirements It may have a tip diameter (or “compressor line”). The rotor and stator foil use slightly different geometries because the stator acts as a diffuser to restore stage pressure, but CVG does not have all these fluid-flow control surfaces as taught for the LPT stage. It can be used in a similar manner for gain-like gain.

  The suction CVG array 51 inherent in the axial compressor is essentially integrated or assembled on the front portion of the foil suction face, and this structure is one of the free-stream flow energy entering at the input rotation-angle. Is designed to convert the section into a pair of strong counter-rotating CVG chip vortices that can flow backward from an array of axial compressor suction CVG chips 53 and provide suction-face separation control similar to conventional VGs, This is because conventional VGs cannot be used as low drag or drag-reduction in such a rotating body fluid-flow environment. Similarly, the pressure CVG array 52 inherent in the axial compressor is integrated or assembled on the front of the foil pressure face, and such a structure is free-stream fluid-flow entering at an input rotational angle. Designed to convert a portion of the energy into a pair of strong counter-rotating CVG tip vortices that flow backwards from an array of axial compressor pressure CVG tips 54.

  The version of the integrated CVG configuration shown in FIG. 4 is generally a symmetrical Ogibal-edge triangular configuration in a repeating pattern, and these cross the span and end-wall of the blade path The steps in the fillet and the overall CVG geometry LPT surface treatment and embodiments can be configured and varied in the same manner as previously taught.

  Optional step-vortex extension groove 55, tip-vortex extension groove 56, and step shear guide 57 can be integrated into both faces to improve step vortex capability, as taught for the LPT stage. .

  Surge or flow separation margins are achieved by adding an integrated CVG that basically extends the foil stall AoA capability, along with detailed fluid-flow improvements, such as in the LPT stage, with extended laminar flow performance and drag reduction. improves. In addition, compressor improvements are affected by adverse pressure gradient flow velocity reductions and flow separation bubbles, especially in the rear suction-face region, with low drag fluid-flow injection capability within the lowest level of BL. It is possible by using the unique capabilities of CVG to provide.

  For simplicity, only one complete example optional fluid ejection cavity 58 is shown integrated and optimally configured between the CVG chips, and this represents more flow activation of the downstream BL. Is supplied with appropriately activated fluid-flow from a 3D-angular jet flow injection port 59 at a defined pressure and mass-flow velocity. This utilizes the initial lower vector of the exit high energy flow for the CVG step to avoid jet-liftoff at high blowing and flow momentum ratios and minimize any LE horseshoe or kidney shape vortex, And help to spread the jet flow stream in the flow direction. Numerous examples of fluid ejection cavities 58 and jet flow ejection ports 59 can be distributed across the foil suction surface and, in the example of an injection plenum 60, are coupled to a pressurized supply of jet fluid. The fluid transfer port 61 and the low drag fluid collection feature 64 may be coupled to the injection plenum 60 and / or the tip collection port 63 to provide a local jet fluid source. The jet and plenum fluid-flow increasing capability is configured in the same manner as the LPT stage. Also, fluid ingress from other sources can be selectively pre-cooled to increase fluid density, routed or tip connected to alternative jet fluid sources such as rear stage compressor bleed air, for example. This is possible with the example of the injection plenum 60.

  The tip-end CVG array 62, which is equivalent to the integrated tip-end CVG array 48 for LPT, can be used for tips facing the compressor tip-seal shroud even though the blade section is very thin.

  These improvements to the axial compressor generally reflect this method and configuration taught for LPT stages, and improved surge resistance margin, increased stage pressure ratio, increased rotation-angle, lighter weight Allow low cost compressor stage combinations. Since the compressor absorbs about 60% of the energy consumed by the engine, efficiency improvements at these stages have a significant impact on overall engine efficiency and engine SFC.

  Fan stage: The fan cascade, for example, typically operates at a lower temperature than the HPT / LPT cascade, requires a larger and higher CVG step height, and uses a fine LE section like an LPC or HPC blade. I don't have it. FIG. 5 shows the profile of a unique fan blade suction-face 70 typically provided in the blade LE region and protected from corrosion at the blade LE portion by a pierced adhesive titanium or other metal LE EPS strip 71. Detailed view is shown. In order to minimize the flow disturbance, the metal EPS transition 72 is in essential contact with the transition joint edge, but in operation, a very small gap inevitably causes a disadvantageous BL tripping opportunity. And corrosive debris passing through these component transitions can reduce fan cascade energy efficiency and further damage critical laminar flow performance over time, paint protector from blade surface behind LE And tends to corrode materials.

  A CVG treated blade 73 is shown on a pressure-face with a CVG EPS overlay 74, which overlays the current undeformed item 70 without any other blade deformation required for the current fan blade cascade. And 71 can be combined. This CVG EPS overlay 74 lowers the required engine power for fan blade drag and input torque and given thrust, and higher stall for improved response and resistance to flow collapse in off-design conditions Provide AoA and reduce the supersonic fluid-flow shock and loss with fan blade tip (by using CVG tip-vortex flow to disrupt SBLI lambda-foot BL separation mechanism), consumable and optional Operates on both suction and pressure faces to reduce blade erosion with certain field replaceable elements. Utilizing the CVG tip-vortex to disrupt the SBLI Lambda-Foot BL separation mechanism and phenomenon, any feasible to induce sufficient vortex conditions while also providing extended AoA and relaminating drag reduction Even fluid-flow vortices and Re can be performed on all other foils, blades and fluid-flow body surfaces.

  The CVG EPS overlay 74 can be operated at the operated step height, which means that the exit high energy flow backwards relative to the CVG step has a higher density than a fluid-flow such as, for example, air. And on the following post-step surface 75 with initial down-vector post-step flow, debris and sand etc. and not having enough energy to rotate down , Followed by a more elaborate blade body with a clear loft and outer centrifugal and secondary flow. The reduced surface corrosion effect on the paint and material after this step is feasible for CVG treated foil and body surfaces.

  Additional types of CVG overlay 74 are elastic heavy-integrated, plastic, metal, ceramic coated substrates, carbon fiber, carbon-carbon, silicon carbide or metal fiber matrix or ceramic with the required mechanical and thermal durability It can be made of matrix composite (CMC) or other material, formed by any molding process to aerodynamically match the current blade LE, and bonded to the blade or aerodynamic body surface. The CVG EPS overlay 74 can be formed as a single CVG element, but for large spans and curved LE blades, select a geometry section that can be varied so that the CVG is easily applied continuously in adjacent sections. Can be assembled with. Any blade fluid-flow discontinuities must be paired prior to CVG addition to produce the most favorable results.

  Utilizing an asymmetric or variable-pitch and geometric CVG structure allows the CVG flow modifying action to vary across the span, eg, in the region of subsequent local shock generation, the CVG pitch differs from the SBLI effect. It can become even finer around this location to produce the greater density of the tip-vortex filament example to do, and in particular does not concentrate solely on optimizing drag reduction. Reducing body fluid-flow impact allows for reduced energy loss and / or improved latitude in operating regime and on-design operating envelope conditions.

  The newly designed fan blade foil or body surface can be configured differently without the protective LE sawtooth shape linear to the prior art EPS components and to fully utilize the CVG improvement. This can provide some weight savings prior to applying the CVG EPS overlay 74 to obtain the benefits of CVG, since the prior art metal LE EPS section may be thicker than the blade body material. Yet another new design choice forms a partial step-height integrated CVG array in the LE volume that overlaps in alignment with the matched interchangeable CVG EPS overlay 74, which can be thinner and lighter. It is to be.

  The newly designed fan blades also include step-vortex expansion grooves 76, tip-vortex expansion grooves 77, step shears, which are added to the LPT blade, for example, with a pressurized fluid-flow source, plenum, jet, etc. Benefits can be obtained from the combination of guide 78 and fluid-flow injection cavity 83. These are shown as a single example in FIG. 5b on the pressure-face and / or they can also be applied to the suction face. These grooves and structures provide greater improvements and CVG alignment and alignment marks on wider cords without requiring excessive step height and CVG thickness and weight, and CVG EPS overlay 74, and / or , Allowing the possibility of additional separation control for any additional integrated CVG step structure gain. This also minimizes the step height effect on the downstream foil or aerodynamic body surface design.

  The integrated CVG and EPS strip combination, which reduces fan blade drag and blade torque input, for example, by about -10%, offers a significant improvement in SFC and efficiency, which is why modern fan disks are hot section nozzle thrust This is because the cooling bypass-nozzle thrust output is more typically 5-10 times or more.

  The replaceable and removable CVG EPS component of the LE design combination also better protects the following blade surface and, as LE wear accumulates, this component is one of the most sensitive parts of the blade. In order to disrupt fluid-flow and BL, replacement in the test state is valuable and helps.

  The newly designed CVG treated blade 73 can have a symmetric or asymmetric sawtooth TE CVG array 79 integrated in the cord behind and in front of the trailing edge (the tip facing the aft). The CVG step sawtooth shape integrated into the body does not adversely damage body strength, mass distribution, flutter margin and aeroelasticity in such a thin, high stress TE region. Body pressure-on the face, the fluid-flow can be designed to be close to the TE or not separated by the TE, so in this region the CVG has a thickening BL but is limited by the TE region surface thickness In order to work at the designed step height, it has a reasonable fluid-flow momentum.

  The upstream CVG EPS overlay 74 is generally expanded and moved slightly outward by the TE CVG array 79 when reaching the TE region due to the higher level of centripetal secondary flow and the CVG effect. I will provide a. In this case, in close proximity to the TE Kutta-Jawkowski condition to define and control the body wake fluid-flow structure merge, the moved upstream CVG tip-vortex filaments lead to effective body circulation-defined lift. , TE wake vortex state vector—cannot get an opportunity to unfavorably rotate in the span direction before being fitted to the whole. The TE array 79 adds a chip-vortex filament that is activated almost directly to the TE wake, and additionally uses an asymmetric CVG configuration, more particularly from either one or both of pressure and suction surfaces. Allow direct eddy current state vector matching with implied combination body-lift tip-vortex wake direction or opposite signal, allowing geometrically controlled CL changes at low AoA. In this manner, CVG can be usefully used to affect the body fluid-flow wake. The combination of these improved CVG EPS methods and performance improvements is also valuable for open-rotor turbofan concepts, helicopter rotors and conventional propeller blades that share a range of fluid-flow concepts and design methods. Integrated.

  This new TE CVG array 79 array is different from Gliebe's '240 patent, Fritz' 488 patent, Vijgen '665 patent, Shibata' 436 patent, Young '319 patent, Balzer' 106 patent, etc. Because this arrangement is a surface structure and treatment that is inherently compact and inherently within the body range and before the original body TE, and this arrangement (prior art that induces only eddy current energy loss). Unlike non-optimized non-surface vortexes) wake flow-mixing between aft-facing CVG tips to reduce BL fluid-flow loss and essentially reduce drag noise while using drag-reduction structures Acts to increase, change body-lift circulation, and pressure and / or suction Scan is because that can be independently configured for both. The TE CVG array 79 aft facing tips can be positioned and offset so that they effectively mesh immediately beyond the TE and minimal interrelation before they are mated in TE wake vortex conditions. Cause interference.

  The suction face can use the TE CVG array 79, but is less efficient at larger AoAs that induce a thick aft BL region with low energy or separation bubbles or fluid-flow separation. These CVG improvements, as taught herein, are more effective with non-rotating foils and surface bodies with Newtonian fluid-flow in the same manner to gain, and generally for any rotation. Can be used.

  The fan blade tip code section should be thick enough to use a tip-to-end CVG array 82, equivalent to the integrated tip-to-end CVG array 48 for LPT, at the tip facing the fan tip-seal shroud. Have. Additionally, the fan-tip to shroud gap change with temperature is less than the turbine section, and the tip-end CVG is useful in nacelle-ducting BL flow control on the surface proximate to the fan tip.

In many of the foil or body design, and _{C L,} and change the ratio of _{C L} versus _{C d,} in order to lower the _{C d} ratio, a lot of work attempts to use a well-known Ganitabu (Gurney Tabs) However, this theoretical work tends to inaccurately predict the impact of tabs applied to foils and bodies with Newtonian fluid-flow at actual Re values. An elastic heavy-integrated lift-enhanced tab, eLET 80, such as a 3D-shaped block, is shown coupled at approximately the middle-span of the pressure-face of the CVG treated blade 73 proximate to the TE. eLET 80 is typically but most preferably made with a portion of a span width of 15% to 30% of the total span, and fluid-flow velocity and lift contribution are important. Used from inside the tip on the rotating body. The eLET 80 is not limited to this value, but can typically be configured as a block, vane or dual-vane structure at a height between 0.5% and 3% of the local code width. The setback from TE to eLET 80 is typically about 0% to 500% of the device height, and the best results are for a setback of typically -100% of the device height. It is.

  The eLET 80 serves to generate a spanwise set of strong counter-rotating vortices trapped between the eLET 80 and the TE edge position. These transverse vortex filaments act on the suction-face TE flow, tend to deflect this flow downward at the TE, and change the local span section TE utta-Jawkowski condition. This additional TE downward fluid-flow acceleration beneficially changes the adverse suction-face pressure recovery gradient (which reduces BL turbulent zone thickness and drag), and effectively increases the local code AoA and lift. Act on.

  eLET 80 is implemented as a flexible, strong, low-mass elastic heavy-integrated material so as not to add excessive mass in the foil or body aft and TE sections, reduce stability, and not swing margins, Effectively transparent to the body placed under TE. In addition, essentially essential such as propellers, rotors and blades-due to the aeroelastic effect and vibration mechanics of the flexible foil, the non-compliant mass added to the TE region is Reliable without shear forces of distributed and non-concentrated local adhesive bonds, allowing a strong acceleration force to be distributed to allow sufficient load-sharing in the adhesive and not concentrating the adhesive at the forward slip point Cannot adhere well. For this reason, non-compliant materials (in other words, inelastic heavy integration) are problematic to add in such challenging environments and, once done, produce strong body material fatigue issues. The problem of vibration stress concentration and bending on the underlying body is generated. The creation of similar branching trailing edge (DTE) structures will face the same real-world challenges.

  The small length section of one or more examples of eLET 80 is that normally-unfavorably trapped spanwise vortex filaments have extended outlets where they must accumulate and exit fluid-flow mass And this typically occurs at a rate of approximately 1,600 Hz, which is typically noted as a fluid-flow diagnostic acoustic-signature when eLET 80 is used, and of a segment or section Teaching the new importance of vortex filament relaxation pathways using application strategies. In each instance of eLET 80, an additional improvement creates a partial section-cut that is mostly in the cord direction through the unit, and mechanical damage is limited to the partial section, effectively providing a rip-stop function. It is.

  The very slight angle to the form of eLET 80 that supports the inner or outer end is that the vortex filament outflow is added to or subtracted from the TE wake as an integrated vortex vector that generates the final body-circulation and lift. When aligned, it can be controlled in a direction that preferably deviates from one body end. The eLET 80 body, for example, bending slightly back on both sides from the center, allows the fluid-flow mass to be processed by eLET 80 while the central transverse vortex acts to increase wash flow to improve lift. In order to be controlled as a geometric part, the vortex filaments in the stream direction are allowed to fall out of the TE wake and balance.

  The eLET 80 can be used with or without the CVG EPS overlay 74 or TE CVG array 79, but for reasons of dynamic stability, combine at least the integrated CVG method and the CVG EPS overlay 74. It is preferable to use it. The TE CVG array 79 has been applied previously or can be used for sections between eLET 80 examples. The configuration of FIG. 5b, which is an example of a TE CVG array 79 with two shown between one example of eLET 80, is not limited, but illustrates that CVG can be configured across a span or part of a surface in combination with other features. .

  The tip unloading eLET 81 is shown as a small tab on the blade suction-face 70 tip TE and can be added to reduce the AoA lift of the code section in this foil area, and the tip from the pressure face to the suction face- There is no major hindrance to vortex flow, especially on the open blade, which acts to greatly deform the foil tip-vortex flow. In the case of helicopter rotor blades, this tab version acts to increase the spanwise load inside the heavily loaded tip, and the reduced and delayed local tip-vortex flows out into the disk flow and the blade vortex flow Less susceptible to interaction (BVI) transfer force loads, disturbances and generation of acoustic signatures. Loading the disc on the inside also reduces part of the lift bending moment and span deformation load due to the structure of the foil.

  eLET 80 LE forward-step entry face induced span vortex is closely matched to aft-step face vortex, thus challenging adhesive bond bonding capability with highly shocking fluid-flow vortex and Re value As such, there will actually be a minimum cord-wise pressure or aft force load that could not be expected on eLET 80. The inlet and outlet spanwise vortex filaments roughly balance and elastically protect the TE mass of elastically integrated TE from the expected ingress fluid-flow dynamic shock-pressure. The result is that the primary adhesion challenge is strong radial acceleration. Tests for aircraft propellers are generally possible, for example, as a 12ghp to 10ghp reduction in cruise SFCs, for example, for an approximately -18% reduction in energy savings for a Lycoming IO-540 engine and a Hartzell variable pitch (VP) propeller combination. Demonstrate similar material capability and performance deformation.

  The elastic heavy-integrated material applied as eLET 80 with these high accelerations and fluid-flow velocity fields is novel and semi-intuitive compared to the prior art, but is practically valid There are obvious improvements and new abilities that prove to be. In the case of in-flight surface icing, the eLET 80 material adapts, and here the load simply exceeds the ability to deposit moisture in a thin layer, allowing for enhanced ice transfer and constant detachment, most Large structural threats come from LE ice that deviates from the inner ice protection system that continuously strips small deposits before they significantly affect propeller performance. Adaptive and rigid deformation and elastic shape recovery characteristics and application methodology to resist section lip-stop damage to eLET 80 are new to foil and body surfaces such as blades, rotors, fan disks and propellers. Tolerant design capability.

  The IGV behind the fan stage and in front of the compressor inlet can also use add-on or built-in CVG to reduce drag, and the extended AoA capability allows mechanical IGV motion to be fluid-flowing. To ensure that it does not stall dynamically. Stator blades that lead to cooling section ducting that eliminates the swirling fan duct cooling duct flow can reduce drag and extend AoA, and can also use CVG. For example, additional IGVs in the compressor, combustor outlet, other aerodynamic supports and load bearing struts use CVG with the same advantages already disclosed for any fluid-flow surface. be able to.

  Increased surface flow from pressure-face pickup or other fluid sources such as cooled compressor bleed-air to improve fan blades, operating AoA and drag performance over the LPT cascade already noted It can also be used for newly designed fan blades with structures equivalent to LPT jet fluid injection port 37, fluid-flow injection cavity 36 and injection plenum 38 combined with larger fan blades. Such an integrated CVG array method of increasing jet fluid injection ports can also be extended to newly designed helicopter rotor blades, propellers and even fixed foil or vane surfaces with appropriate geometry scaling.

  Jet engine power-cores (compressors, combustors and turbines) using CVG for improvement (as prior art) LPT output-shafting (to drive the fan disk cascade for jet cooling duct thrust) Or similar power extraction stages) or like propellers, rotor systems, power generators, pumps or compressors used in industrial scale chemical processing systems such as cooling, natural gas pipelines or refineries In addition, it may be formed in a turbo-shaft configuration for driving an external load or transmission drive.

  HPT Turbine Blade: FIGS. 6a and 6b are representative views of an HPT blade 90 having a deep reaction-bucket type foil section and extract energy from the fluid-stream entering from the combustor to either the upstream compressor stage or Installed components that operate in the same manner as previously taught LPT blades to power a load, or a lower face CVG array integrated with an integrated integrated upper face CVG array 91 109. The integrated HPT CVG is configured for AoA expansion and drag reduction to reduce fluid-flow separation / turbulence and to mix-down the heat load. Integrated CVG made in the base metal provides the greatest HPT blade strength, but is new in the cascade as multi-part HPT blades can be fabricated to provide all the other required properties It is also possible to have a high temperature LE CVG array that includes a suitable silicon carbide or metal fiber matrix or ceramic matrix composite (CMD) 3D structure that works with the HPT LE of the design.

  For the IGV or first HPT stator and first HPT rotor disk, the combustor exit temperature is typically above the nickel superalloy melting point so that these surfaces are fluid cooled. The cooling jet root 93 is located at the LE of the stator and rotor blades and is supplied with cooling fluid (typically HPC bleed air at a cooler of, for example, -650 degrees Celsius) from the root cooling plenum 94. This source has sufficient angulated jets and flow mass to cool and protect the foil LE, which then provides additional surface cooling and heat into the foil wake. -Flows divided around pressure and suction face to reject flux and heat load. The foil surface is at the lowest local temperature and moves higher in the free stream fluid-flow at BL, causing the temperature to rise closer to the combustor peak temperature. Separation turbulence and fluid-flow Any excess turbulence on the surface of the foil or body, such as a separation bubble, is typically removed by mixing and cooling the hot fluid and temperature layers to cool the surface safely Increase the heat flux that must be done.

  Prior art foil surfaces include additional torsional galleries moving into additional downstream angular cooling jet arrays, plenum cooling inner-face skins, and inner pin grid 107 and TE cooling outlet slots 92. To be cooled. Such challenges must have jet surface cooling fluid-flow suitable without excessive turbulence and thermal mix-down, jet-lift-off, and efficient surface cooling and buffering from hot fluids Must be spread to.

  CVG provides a low drag method to provide a well-diffused cooling fluid jet that is effective at the lowest BL level, as used optionally in LPT bodies, simply to improve separation control . An aft-angular jet fluid injection port 95 or measurement orifice is located between the CVG tips 98 and allows cooling fluid-flow to flow from, for example, the upper CVG cooling injection plenum 104 at the rear surface of the after-facing step 97. -Can be carried into the flow injection cavity 96; Adding a cooling fluid jet in this aft angle manner into the formed cavity reduces the initial downflow of high energy flow in the CVG step to suppress jet-liftoff at high blowing and cooling flow momentum ratios. Velocity vectors are utilized to help diffuse the cooling fluid stream laterally and at the lowest cooler level in the downstream BL. The second lower CVG cooling jet plenum 106 also provides higher pressure cooling fluid to the adjacent blade surface and jet fluid at the pressure or lower face CVG array 109 in the same position as the HPT suction face. Examples of injection port 95 and transport to related structures.

  In order to cool the step-vortex mass-flow, an additional step-vortex cooling injection port 99 may be located at the bottom of the CVG valley. A tip-vortex cooling injection port 105 may be included in the base of the CVG tip 98 to provide extra cooling to the CVG tip-vortex filament to lower the heat flux to the downstream surface. Other prior art techniques such as internal tortuous cooling passages, turbulence generators, TE and chip “squealer” cooling exhaust and pin grid 107 are integrated CVG, internal passages and internal skins to cool the HPT surface. Can be used with flow. Efficient use of an optimized cooling fluid-flow with a lower flow mass to remove heat flux improves engine efficiency because compressor input energy is required to obtain the cooling fluid-flow. The surface of such an HPT stage can use any prior art oxidation reducing coating, other metallurgical methods, alloys for low and high cycle creep, and the like.

  Step-vortex expansion groove 100, tip-vortex expansion groove 101, and step shear guide 102 adjust for step-vortex mass flow capacity to balance the surface mechanical strength conditions and design step size. To allow, it can optionally be integrated with HPT suction and / or pressure CVG (for LPT section).

  Mitigation of addition from high heat flux can be provided by TBC, for example in the LE section, these typical ceramic surface layer coatings at the expense of increased mass and risk of coating crushing, loss of protection and surface loss. Reduce the surface thermal conductivity to reduce the flux. With integrated CVG and jet / injection cavities that provide efficient surface cooling and dispersion means, the foil downstream section of the CVG step does not seem to require much added mass and complexity in large areas of the TBC. is there.

  CVG can also be used to provide an additional low-drag jet fluid injection port cooling structure for the foil at the balance of rotor, stator end-wall and fillet in cascade passages and ducting surfaces. Yes, and adds the ability to cool below BL in areas of adverse secondary flow that resists collapse due to, for example, blade path-vortex. Fillet surfaces can use CVGs with jet fluid ejection ports on these contoured surfaces. The integrated CVG tip-vortex also provides a measure of SBLI control capability and can be configured to alter the passage-vortex, impact and secondary flow.

  A secondary integrated CVG array 103 on the pressure-face close to the TE cooling outlet slot 92 is used as the second row, for example, in front of the blade TE, close to the upper CVG array 91. Because it is less affected than integrated CVG, it can be used to minimize blade wake and improve lift / vortex conditions. A lift and TE cooling enhancement tab array 108 may be added before the TE cooling exit slot 92, such an option allows the modification of both blade active AoAs and with or without the array 103, the TE Along the slot 92 to help spread the cooling flow. The tab array 108 may use “bent” or angled tabs as shown. A secondary integrated CVG array 103 can also be added to the suction-face of the HPT blade.

  Intermediate pressure turbines (IPT) may also require cooling, which can be designed like HPT blades to improve cooling and drag losses. The CVG shown here and associated design characteristics can be integrated in any combination, example and location, along with prior art methods of blade and surface design to provide optimum performance. CVG treated HPT blades can be used again as an example in, for example, steam turbines, with usefully improved fluid-flow and efficiency, and LE surface coating materials are corrosion inhibitors that can also be combined with CVG structures. Note that it can be used for: Lofting and removal of corrosive particles and materials downstream from the CVG step also helps protect the downstream flow surface. In a steam turbine, the incoming fluid-flow is from a combustor / steam source, and no compressor is required, and the turbine power obtained in large quantities can drive other loads.

  Centrifugal Compressors: In the final HPC stage, many smaller compressors and pumping devices, for example jet engines, are centrifugal type impellers with compact, high compression ratio, weight efficiency, robust and low complexity equipment For this reason, this centrifugal impeller is used. There are many fluid-flow analogies between axial flow, mixing-flow and centrifugal compressors and pumps, and centrifugal blades and vane cascades on impellers route and tip diameters along the impeller axis towards the outlet. Increasing, the outlet flow can be fully radial or mixed (partially as an axial flow) into the downstream ducting and / or diffuser structure.

  Centrifugal compressors (liquid Newtonian fluids—pumps when flow is used) are suction-impeller tips, diffuser guides—vanes, vanes (or blades) and other fluid surfaces that cause fluid-flow performance problems and energy loss— Face flow separation can be experienced. Many impeller vanes are aft-swept at the exit flow angle so as to be less aggressive to tip momentum transfer and flow, so as to reduce fluid-flow separation stress at the blade exit-angle. The

  Flow separation or exfoliation bubbles in the low pressure region of Newtonian working fluids such as liquid water or ammonia will eventually cause rapid or supersonic bubbles from strong supersonic shocks and acoustic waves-structural collapse, cavitation and potential damage. While adding additional complexity, it presents itself as a transition from a liquid state to a vapor / gas phase with an entrained physical bubble structure.

  Adding a CVG integrated along the fluid-flow and streamline on the suction-face and other flow surfaces of the centrifuge allows control of the gas-phase fluid-flow separation bubble and previously cascaded Reduce the drag and turbulent BL flow losses. In fluid fluid-flow in the suction region, the fine CVG vortex-filaments grow and form with a fluid volume that drops under the liquid and vapor-pressure transition before they grow to a size that can cause cavitation damage. Intercept the vapor bubbles that do and collapse. This bubble collapse also reduces the resulting impact energy and acoustic signature, and the vortex filaments act to diffuse, reflect and attenuate the impact pressure and acoustic waves in the working fluid.

  FIG. 7 shows a typical open form centrifugal impeller surface and hub inner wall 120 with typical features found in most open form impeller versions. This example shows a central impeller inlet flow guide 121 guiding the LE of an array of impeller foils or inducer vanes 122 as the compressor rotates in a counterclockwise direction when viewed in the inlet flow guide 121. Have. The incoming axial fluid-flow is effected by the axial rotation of the inducer vane 122 and is accelerated and continued across the hub inner wall 120 and then exits radially at a higher momentum and speed at the vane outlet tip 128. Optional final output fluid-collection method or volute, ducting, etc. to transport fluid-flow (only one example described for clarity), not shown for clarity Cross towards the array of diffuser guide vanes 129. This example of FIG. 7 also uses an additional split vane 132 to not choke the incoming flow faster with the inducer vane 122.

  The integrated inlet suction CVG array 124 is located on the suction side of the inducer vane 122 section near the vane inlet LE so that fluid-flow is not separated on the suction-face of the vane (or not hollowed out for liquid). Can be inherent. The integrated downstream suction CVG array 125 can be integrated when impeller geometry and streamlines are allowed for beneficial effects.

  To reduce the flow loss on the vane pressure face on the opposite side of each vane with the integrated pressure-face CVG array 123, for example, in a manner similar to other locations from the LE to the LPT blade, It is also possible to integrate an integrated pressure-face version of CVG that complements these operations. The location of these integrated CVG arrays will, for example, follow the structure, logic and procedure for the LPT blade, and then in geometry to be matched to the specific impeller geometry, flow angle and position Optimized. The illustrated CVG magnitudes and angles are simply expressed for discussion and do not limit the actual design chosen and optimized.

  The pump root or hub inner wall 120 is a large surface area of primary flow BL and some secondary flow of concave and convex surfaces between the suction and pressure faces of the same blade or vane passage. This surface may be affected by flow or cavitation problems in the suction region, and CVG BL relaminarization also reduces drag or cavitation, and the integrated inner wall pressure-inner wall downstream integrated with the face CVG array 127 The pressure-face CVG array 126 can be used as useful here, and any CVG can be slightly angled to best match the local fluid-flow streamline conditions. This figure clearly does not show the vanes for the hub blending fillet, but when the vane hub route becomes a fillet, the integrated CVG can mix these fillets and other on the adjacent surface. Merged with CVG.

  Stationary diffuser guide vane 129 foil or surface controls separation bubble loss from strong fluid-flow pulses and wake exiting high-speed vane outlet tip 128, if present, and also with dynamic flow outlet-angle and diffuser enabled AoA Therefore, an integrated diffuser suction CVG array 130 can be used. Since the impeller fluid-flow into which the diffuser guide vane 129 enters is configured to be vortex free and operates in stator mode with non-rotating flow, does this vane have a higher surface curvature for a more compact diffuser section? An integrated diffuser secondary suction CVG array 131 can also be used to reduce drag. The pressure-face of this diffuser guide vane 129 can have a similar integrated diffuser pressure CVG array to reduce flow separation and drag. Static ducting and piping flow sections around the array of blending fillets and diffuser guide vanes 129 can also use an integrated CVG to further control drag loss and flow separation.

  Also, although not shown in FIG. 7, the moving structure of the open-form impeller tip edge 133 is closely matched on the open-form impeller to ensure the lowest reverse flow from the downstream fluid volume. There is a matching 3D fixed or bounding tip-shroud duct control surface. These vane edges are equivalent to the open-form tip of the axial flow blade, and the closed-form centrifugal compressor impeller is equivalent to an axial flow cascade with continuously interconnected tip-shrouds. The passage is fully enclosed.

  The tip-end CVG array 134, which is functionally equivalent to the integrated tip-end CVG array 48 for LPT, can be used for vane tips facing the centrifugal compressor tip-seal shroud and has a very thin blade section. However, small CVGs can operate effectively at high speeds with small gaps having high shear forces. The heat load at the centrifugal compressor is less than at the turbine stage, and the tip expansion gap can be closer with lower losses.

  The tip-end CVG array 134 induces vortex filaments on the shroud surface closely matched to control BL deployment and flow at the vane velocity as it sweeps the shroud surface. There is a corner. The tip-end CVG array 134 step-down may intercept the vane tip end LE and may or may not cut, and in the form of a step that does not cut at the LE, the unique tip for the shroud seal gap is , CVG step-down is maintained at the tip LE as local gap flow occurs downstream of LE. As the compressor impeller of FIG. 7, the vane pressure-face is on the right side of the tip-end CVG array 134, the suction side is on the left side, these CVG tip-vortex filaments are on the left side along the tip code, and this Pressure-face suction-flow at downstream-distributed positions in the face direction and normal foil or tip-vortex flow on the body surface in the same direction at the body tip TE such as the tip corner joint of items 128 and 133 Occur. By applying a higher mass-accumulation step angle to some tip-end CVG arrays 134, the member (such as 60 degrees) passes through the tip-shroud gap and seal caused by pressure-face fluid. Constrained by these steps to act as a flow obstruction for the lost energy loss flow, it further allows the formation of overly large step-vortices.

  The bounding tip-shroud duct control surface can also have an array of CVGs provided on the surface in a radial or spiral pattern, for example, to control local BL flow under the influence of vane passages, and these are It can be used with or without the tip-to-end CVG array 134 and is formed such that this CVG pitch is not synchronized to the vane pitch, so as not to produce a consistent high-pressure wave or acoustic signature. With additional flow attachment capability, the angular additional flow-control jet 135 can be added after the CVG step to increase the momentum in the lower BL, and because the upstream impeller surface-flow is at a lower pressure, The pressure fluid source for this is taken from the compressor output flow and ducting into the plenum of the impeller core capable of distributing these fluid-flows on the surface CVG and through the impeller shaft, as required for the 135 example. (And can be cooled) and done. In the case of compressors and turbines, such injection jets can distribute cooling fluid derived from the higher pressure fluid source being cooled. Examples of optional step-expansion grooves and / or step shear guides can be added to the impeller, but are not shown for clarity on the drawing.

  A roughly centrifugal compressor can be reversed, for example, to operate as a radial inflow centrifugal turbine. In this case, the impeller torque input becomes an output, the suction and pressure faces change, and any CVG array can also be modified to provide the desired BL and flow variation. As a centrifugal or mixing-flow turbine, an example of an additional flow-control jet 135 can be used for surface film-cooling, for example HPT stators and rotor blades, as well as flow adhesion improvements.

  In a closed-configuration impeller, this tip shroud is connected to all vane tips to form a closed vane passage, in the same manner that CVG has already been discussed, for BL and separation control. All these internal flow surfaces and tip seal labyrinths can be used.

  Integrated CVG treatment for centrifugal vanes, impellers, and other fluid surfaces allows for increased inlet and outlet-flow rotation-angles, new, more compact and lightweight compressors, turbines, pumps, turbochargers And similar fluids—allowing the design of fluid structures or mechanically—on current designs with improved performance “drop-in” placement impellers, suction-faces or fluids— It can be used to simply reduce flow energy loss, TG vortex on concave face and BL thickness loss.

  The integrated CVG also has other centrifugal or mixed-flow type fluid-flow pumps, turbines, propellers and industrial processes-compressors such as gas compressors (eg ammonia cooling, natural gas pipeline compressors), water Useful for jets and pumps or water or other liquid turbines.

  A turbocharger is an example of a centrifugal turbine that uses a pair of centrifugal flow compressors and turbine impellers to extract fluid-flow energy and add this energy to the fluid-flow of the centrifugal compressor. The device can use an integrated CVG that is tuned for local flow conditions as a new design to improve efficiency and operation.

  Nacelle structure: An engine nacelle is an example of a generally cylindrical fluid-body that is attached to a fuselage or vane via a pylon, attachment device or attachment link that has a mutual fluid-fluid effect. On such an attached flow-body, any adverse pitch and yaw against the incoming fluid-flow can generate considerable drag and turbulent flow due to, for example, flow separation on the downstream suction surface. obtain. The engine nacelle is integrated with the engine inlet and outlet fluid-flow to ensure correct inlet and outlet conditions for the enclosed engine.

FIG. 8 shows a generally cylindrical nacelle body 140 attached to a vane body 141 having an attached pylon 142. In the turbofan engine example, fan blade cascade 143 is shown at the nacelle inlet after duct diffusion has occurred at the nacelle LE and the inlet cooling duct section.
An integrated nacelle LE CVG array 144 is shown in the LE to improve flow adhesion and reduce drag at both the nacelle inner duct and / or outer surface. This LE CVG array 144 may also increase with superposition of matching and replaceable EPS CVG elements when surface erosion and / or durability becomes an issue.

  Further integrated fan inlet CVG array 145 is shown to improve duct flow into the fan blade cascade tip, reducing the need for active suction BL control at the fan tip inlet location.

  Similar integrated CVG arrays can be designed in both faces of internal cooling ducting to ensure that flow separation is avoided on convex and concave duct faces and turbulent BL drag reduction is minimized. . These integrated ducting CVGs allow higher duct surface 3D curvature or shorter duct and engine size for new designs. A series of CVGs can be used on these large surfaces at appropriate intervals where the chip vortex filaments are expanded before they explode or BL flow results in separation bubbles or excessive thickness loss. This defines the closest suitable CVG interval and hydrodynamically defined separation. Since most modern nacelle new designs are molded with composite structures, it is easy to combine integrated CVG arrays in design and fabrication for improved energy efficiency and performance.

  In the cooling duct exit nozzle, an integrated cooling duct exit CVG array 146 on the external and / or internal surface is provided in front of the local cooling duct TE in order to improve drag mixing, cooling exhaust and fan exit noise signature as well as drag reduction. It is also possible to be inherent. At the hot section nozzle outlet, a similar integrated hot duct outlet CVG array 147 can be used in front of the local TE and / or exhaust cone to improve flow mixing and eddy breakup and improve exhaust noise signature with drag reduction. 148 can be integrated into the external and / or internal duct surfaces. To break strong hot exhaust cracking, the additional low drag thin cylindrical ring of eddy breaking CVG array 149 allows the vortex filament to transmit more acoustic noise and shock to the wake transition. Before being evacuated, the vortex filament is directed into an expanding hot exhaust eddy to break up and destroy the eddy, for example, an expanded exhaust flow stream between the exhaust cone 148 and the hot section duct TE Can be added. With the support struts for the eddy breaking CVG array 149 and exhaust flow, the turbine aft support struts can also have a CVG array integrated to add additional vortex filaments for exhaust noise operation.

  The nacelle attachment link or pylon 142 uses a pylon LE CVG array 150 added to reduce drag and improve flow around the (mainly vertical) pylon surface using fluid mixing fillets on the support vanes and nacelle body. Can also have. The vanes may have an integrated vane LE CVG array 151 and a secondary vane CVG array 152 (especially at the pressure face).

  Other structures attached through links or pylons can also use CVG to control flow separation during flight, eg for closed inlet flow-body such as fuel tanks or weather-radar pods etc. The front body is a nose chip such as a fan spinner 153. An angular CVG array 153 can also be used because 153 eventually rotates with an angular inlet airflow. The nose tip may have a nose cap that matches a suitable angular CVG or may be designed with a nose CVG array integrated to reduce drag.

  These attached flow-body structures are also in the form of closed (and / or open end) “inside-out” ducts, with efficient primary fluid-flow and losses on the “outer” flow surface. . In some cases, a flow-body embodiment with predefined dynamics and / or total energy is like a flow-body like propellant, or a “Virgin Galactic“ Spaceship One ”that separates from the launch platform. In addition, it needs to be separated or dropped for glide. In these cases as well, CVG applications can improve adhesion and / or separation, and fluid-flow dynamics and flow-body energy efficiency (in other words, range) of motion, and improved trajectory and / or path stability. Allow sex.

  Duct flow path: Many parts of the surface of most fluid-flow devices, such as jet engines, are ducting surfaces to guide the fluid-flow to the optimal design position in and out of other fluid-flow processing sections These are limited to the flow rotation-angle or flow-direction in which they can be introduced before inducing fluid-flow separation or BL thickness causing energy loss. These ducts or piping, as well as the external 3D surface, become another flow device that can be improved to an integrated CVG. FIG. 9a shows a typical fluid-flow duct 160 that is similar to many conditions in the example of fluid-flow surface, ducting and piping.

  The cutaway section shows a duct seam 161 at the flow direction change, and a smaller diameter upstream duct 165 is placed inside the downstream duct 166 in an optimal position to seal the improved pipe or duct joint. To complete, it has an internal duct CVG array 162 structure integrated at its TE end that is merged, for example, by swaging and brazing or welding. This is one design embodiment that allows ducts or piping transitions with an integrated CVG array inside, which, as already disclosed, is a free stream fluid-flow foil or other body surface In the same manner as for, when the surface or duct changes direction or diameter, it acts to reduce flow separation and drag on the convex surface of the downstream duct or pipe and to reduce drag on the concave surface. Depending on the method of manufacture of the duct or pipe, material, diameter, wall thickness and section geometry, for example, multiple stamping, forging, forming and machining steps can be performed on the inner surface or on the outside of the body surface. For example, it can be used to join CVG arrays at optimal locations on the outer surface.

  FIG. 9b is introduced into a slightly larger diameter constant cross-section duct or straight section of piping and is swaged or otherwise attached in a most preferred position with a duct insertion CVG tip 183 that directs fluid-flow downstream. A duct insertion CVG array 182 is shown. In this case, the duct insertion inlet 184 has a very thin and sharp edge so as to minimize the inlet flow disturbance, and the duct insertion inlet surface 185 has a very shallow angle rearward with respect to the step thickness point 186. Have. Such long low angle duct convergence provides minimal flow change and disturbance before reaching the correct step-height duct matching section at step thickness point 186 before entering the CVG step. An optional duct insertion slit 187 allows a slightly folded duct insertion CVG array 182 to be inserted into the duct and extended to a fixed position to work together or make the mounting method for fastening the device easier to use. Can be introduced. With this array, stream direction gaps are tolerated and have minimal performance impact. Between the step thickness point 186 and the tip 183, this flow is parallel to the average duct surface and across the CVG step is the optimal surface to obtain the most favorable flow shear and downstream BL reactivation. Stabilize when having a vector. The core contribution of these duct CVG arrays includes the case where the array surrounds the entire duct periphery, between the fluid-flow input and the output plane cross section, between the maximum cross-flow limit of the V-form CVG array. This means that the array operates continuously across the entire duct surface BL flow captured by the array in that there is no unmodified BL. In cases where the CGV array is less optimal that does not have space in the stream direction for a constant step height section (which negates the primary gain), such a continuous cross-flow BL modification function is of these types. Distinguish from prior art isolated VG groupings of modified CVG arrays. The use of the duct insertion slit 187 is essentially helical with this duct insertion CVG array 182 having a CVG capture angle changed to a helical angle so as to capture the duct wall BL flow at an optimum angle. So that it can be manufactured. When this spiral is applied more than one revolution, there is a reduction in efficiency due to the disappearance rate of the upstream vortex filament before meeting the next downstream CVG v-form step. This means that a series of ducted CVG arrays 182 in the flow direction must be optimally spaced to obtain the most favorable effect.

  Applying CVG to the inner pipe and duct surfaces can also be done with spray-on or molded coating materials that can be bent into the correct surface geometry and applied or treated when processed or worn. These coatings can be made of multiple layers and provide mechanical and corrosion / chemical protection for the underlying duct or pipe surface.

  Yet another flow control option is a duct flow transition that allows ducting to introduce a large flow-rotation, which is for the prior art internal flow-rotation vane 163, but these structures do not provide fluid flow. -Introduce drag to act like a foil cascade to change flow. The flow-rotating vane CVG array 164 can be integrated into the suction and / or pressure face of the flow-rotating vane 163 to reduce drag before flow separation and allow larger duct or pipe rotation-angles, and Newer, for example, pipe, duct or s-duct designs are possible with a more compact geometry and / or lower energy loss.

  It also enhances and improves the strength and mechanical efficiency of the cooling ducting panel components in larger duct surfaces and transitions that require thermal resistance, and CVG integration and strong, non-cracking TBC It is possible to emboss a tile-shaped pattern of, for example, triangles, squares, hexagons or other polygons that allow the option to add a coating.

  FIG. 10a shows a cross-section of a wall duct stamped or embossed with interlocking hexagonal cells that may optionally have integrated CVG step functionality. The downstream smooth duct surface 170 in contact with the fluid-flow (on the opposing face in FIG. 10a) is located below and to the left of the embossed CVG step array 172 (downstream).

  Embossing is clearly distinguished at the base intersection of the sharp-radius vertical wall (Lutjen '342 patent) to remove heat flux initially from the upstream inner floor 174 and downstream inner floor 175. A vertical with a main wall-supporting route alternation radius 171 (with such a radius greater than right angle and up to the wall height) to produce an interlocking array of beam sections with a greater moment of inertia and the least stress concentration The wall 173 is raised. The top of the vertical wall 173 can be further deformed to make the sharp wall edge compact in the lip and increase resistance to handling damage and edge stiffness. The cooling air can flow across the edges of the vertical walls 173 to remove heat with excellent thermal conductivity and mix-down below the wall and interior floor surface. Depending on the alloy used (preferably at metal plastic temperature, which also allows proximity control of material temperature distribution, surface oxidation and minimum compression / embossing die force to minimize material collapse due to forming stress. Most preferably en-vacuo) embossing or effective forging. It is also possible to generate these surface arrays and steps, for example, in other input casting processes, explosion / hydraulic die forming, etc.

  The creation of such an improved duct panel section of FIG. 10a also allows the TBC to be integrated into the non-smooth face side. FIG. 10 b shows an embossed upstream duct panel region 176 with a lid upstream TBC blanket 177 facing the hot fluid-flow, with the downstream TBC blanket 179 covering the downstream duct panel 180 as a TBC CVG array 178. Will lead to. Note that the hot fluid-flow is against the TBC side of such an arrangement and in the direction of flow with the opposite side of the part similarly formed in FIG. 10a. This embodiment utilizes, for example, a hexagonal array of vertical walls 173 and a shaped top to keep the TBC sub-sections fixed, such as a closed TBC element 181. The TBC coating can be any of the well-known TBC application methods, materials, and inter-coating. The cracking of the thinner TBC section during the example of the closed TBC element 181 maintained can be controlled by the TBC application temperature of the metal substrate. This presets the mechanical stress with a different coefficient of thermal expansion between the vertical wall 173 integrated with the substrate and the TBC sub-section or sheet. This can be uniformly allowed within the example of a closed TBC element 181 that is set between operating temperatures or cooling conditions to suppress TBC cracking or that maintains the coating on the failure. After the TBC coating, the step region can be processed or worn to provide the most preferred step edge of the TBC material for the TBC CVG array 178, and the rest of the TBC surface is similarly treated for surface uniformity. obtain.

  An angled additional duct flow jet 189 may be provided downstream of the steps of the TBC CVG array 178 or embossed CVG step array 172, such jet (or jet array) being the surface to which it is fixed. Thus, for example, surface film-cooling fluid-flow and / or additional BL activation flow can be performed from a pressurized fluid-flow source under the step region, as taught for LPT stator foils.

  Examples of optional step-expansion grooves and / or step shear guides may be added to the duct surface at the CVG step, but are not shown for clarity of the drawing.

  Although FIGS. 10a and 10b show essentially flat panels, such a process can also be applied to surface arrays and steps having a 3D curvature for application to sections for any ducting surface shape. These hexagonal features can use the most preferred CVG flow-angle of about 22 degrees at the downstream edge, and triangular or diamond shapes can be used for smaller TBC sections, but higher for wall-to-floor sections Incurs a metal mass ratio. These duct sections may be about 0.5 mm to 3 mm thick, but this is not a limiting condition, depending on operating pressure, etc. Wall, floor, polygon type and size and TBC thickness are design requirements It can be adjusted as necessary to meet the conditions.

  Cooling turbine blades can use these polygonal maintenance features to secure the LE surface TBC against high inertia loads, where a fountain head arrangement is required for LE cooling. This can be penetrated after TBC coating and stepping, etc., and post-step blade cooling of the TBC-free surface can be achieved through cooling flow, for example, the jet flow injection port 95 with an aft angle, internal blade skin cooling and TE Introduced by a cooling slot.

  Pipeline pipes, general purpose tubing, nozzles, etc. can be combined or mated with CVGs that are appropriately spaced to reduce surface drag and energy efficiency. In spiral-welded or rolled pipes, the embossed or machined internal CVG can be easily integrated with any suitable fabrication method prior to roll forming or welding. The CVG repeat separation is large enough, relaminarization can occur, the tip-vortex flow can be expanded, or the result is disadvantageous to drag as in prior art turbulators or conventional VG arrays.

  Conformal vortex combustor: FIG. 11a shows a general arrangement of annular compact and efficient conformal vortex combustor or gas-generator designs using an integrated CVG to provide an improved design. It is shown as a partial sectional view in which the segments are inclined. The combustor is provided as an oxidizer to generate an accelerated fluid-flow from which work can be extracted and / or to burn the fuel input in an exothermic reaction that is controlled to produce heat, and the compressor Can accommodate the output.

  The external combustor pressure wall 200 is connected to the HPC casing through the input interface 201 (which is connected to the HPC at the exterior and interior walls), and the combustor is typically in the highest pressure region of the device, thus ensuring high pressure integrity. The output interface 202 is connected to the HPT casing to maintain. Combustor input guide vane 203 and combustor output guide vane 204 act to form a range around the combustor sub-segment in terms of overall combustor array and volume. These combustor guide vanes 203 and 204 can optionally be twisted at an angle to the axial flow to diffuse the HPC output flow (using 203) and to be part of the stator structure to avoid vortexing. And / or combustor flow power-angle can also be defined in a radial dimension, sufficient to allow optimal flow power-angle design directly within the HPT first rotor cascade. It can effectively act as a compact and integrated HPT inlet stator blade (utilizing 204) with cooled vanes.

  The combustor inlet fluid-flow mass enters through the opening E at a speed and temperature defined by the HPC (and possible variable outlet guide vanes), then the upper bypass opening F, the lower bypass opening H and the rich- Divided into three streams flowing in the burn combustor opening G.

  The combustor input CVG array 205 is designed to suppress such duct flow-separation, reduce drag, and allow for such a flow-efficient and / or more compact inlet flow design. A point is added around the inside of the entrance opening E.

  The portion of the mass flow thus designed at the opening G is divided into steps from the combustor lower (and upper) mixer CVG array 207 into the step and vortex filament flow, the lower CVG combustor guide 213 and the upper CVG combustion. It flows between the vessel guide 225. Next, the rich mixing frame-front is in immediate contact with the completion of fuel oxidation, after a predetermined time, with extra bypass air added and combustion producing lower nitric oxide. Proceed into lean-burn opening J, which is completed smoothly in two lean-burn steps. The final combustion / oxidation of the fuel is completed at the transition time leaving the opening K around the output interface 202.

  At the exit from opening I, on the TE of CVG combustor guides 213 and 225, an array of upper and lower frame stabilization tabs 216 captures the spanning vortex of the combustion fuel at the front and rear faces of these tabs. Acts to hold. The spanned outlet vortex of the frame stabilization tab 216 also increases the TE wash flow and is efficient to help mix-down the bypass opening air from the ducts F and H into the lean burn opening J volume. Acts as a lift and drag change Gurney tab. Tab gap 215 is added to also organize a small amount of cord-wise rich-burn vortex filaments that exit into opening J to mix with the bypass air and continuously complete the lean-burn cycle. Together with the LPT and fan blade LET, these frame stabilization tabs 216 are angled or separated, unlike those perpendicular to fluid-flow.

  As the fluid-flow velocity increases at the combustor input (and then into the volume of opening I), the initial abundant frame-front is localized fluid so that duct diffusion matches the frame propagation velocity at these physical conditions. Retract backwards into the opening I volume until balanced with speed. This defines the minimum diffusion (surface curvature) required in the aft section of opening I for frame stability, and at maximum flow vortex this frame front is in front of the frame stabilization tab 216 and TE exit. Should. The ratio of the sizes of the openings E, G and I effectively controls the speed of fuel mixing with the reach burn volume in relation to the HPC output speed. The ratio of openings F and H to G controls the flow volume for rich-burn versus bypass, cooling and lean-burn air for the combustor. The transverse vortex filaments on the front and rear faces of the mechanically rigid frame stabilization tab 216 are also very stable when the igniter array 227 element disappears, as a flow disturbance-blocked backup ignition source. Works. The upper CVG cooling flow duct 226 and the lower CVG cooling flow duct 212 are connected to the upper CVG duct body 224 and the lower CVG duct because the rich-burn volume generates a lot of heat on the local flow surface and frame stabilization tabs 216 and TE. Added individually to the body 214. The cooling fluid-flow in these upper and lower CVG cooling ducts is constituted by a lower cooling inlet opening 221 defined by, for example, a lower combustor guide 213 and a lower CVG duct body 214. Outlet cooling air from these CVG cooling flow ducts 226 and 212 makes an angle in the mass inflow at opening J. These cooling ducts are included in the body of the CVG combustor guide because they are thicker fluid-control foils in the combustor ducting, but if these guide foils are thin enough to be adequately cooled Thus, the outer guide flow surface can cool these foils without the need for internal cooling ducts. The example combustor embodiment of FIG. 11a is generally symmetric with respect to its mid-plane, so that the finely paired items are in some cases to provide more drawing clarity. Note that although omitted, in fact, this is illustrated by the symmetric design intent of the particular embodiment.

  Most combustor energy release occurs at the boundary volume of opening J at the completion of fuel lean-burn, and lower wall cooling surface 217 and upper wall cooling surface 220 are exposed to such combustor heat from the combustor outer pressure. Added to protect the surface, and these structures intercept a small amount of fluid with ducts F and H as film-cooling media. To protect the example surface of the combustor output guide vane 204 on both sides, a shield such as a side cooling surface 219 is added, and these are also ducts (from before the CVG combustor body) as film-cooling media. Intercept the inlet fluid with F and H. The examples of cooling surfaces 217, 220 and 219 can be made using well-known TBCs on the surface shown in the boundary volume of opening J or as CMC panels to reduce heat flux and oxidative damage. Optionally, a drag-reducing CVG array, such as a lower cooling surface CVG array 218 on both faces, can be used to lower the drag. The TBC prior art can also be used, for example, on a small amount of combustor guides 213 and 225 surfaces to lower the local heat flux within the combustor surface, and this energy is used for HPT sections for useful work. It can be used for combustor output. The duct-flow concept of FIGS. 9a, 9b, 10a and 10b can also optionally be used as a fine improvement on any surface with this combustor to improve flow and reduce drag.

  The pilot fuel plenum 208 and the primary fuel flow plenum 211 are supplied with filtered, pressurized, fuel-flow arranged in a certain order, and separated angles that conduct the fuel flow into the mixer CVG array 207 step region. A pilot fuel jet 209 and a primary fuel jet 210. The pilot fuel jet 209 is smaller and can be injected close to the CVG valley to ensure liquid fuel particle collapse and atomization with a strong step vortex filament that overcomes fuel viscosity and cohesion, and then A portion of the rich fuel mix will flow backward into the CVG tip-vortex and into a region where the downstream velocity reduction relative to the flame propagation velocity will allow ignition. In this manner, higher energy output is required that can have a high fluid-flow velocity in the step region of the mixer CVG array 207 that provides high vortex mixing intensity later in the opening I and delays the initial combustion heat. When done, pressure in the primary fuel flow plenum 211 similarly pushes fuel through the example of the primary fuel jet 210 and into the step region of the mixer CVG array 207. This example shows an angular primary fuel jet 210 that is closest to the CVG tip region, and this fuel portion is injected or diffused into the highest vortex filament to be burned. Utilizing one or more fuel injection arrays to vary the flow rate when required allows for better tailoring of the fuel flow for variable operating loads or required heat generation. In fact, jets are other configuration sizes, geometries, and examples that are moved to other locations, but have benefited from the low-drag fuel injection and mixing benefits improved by utilizing an integrated CVG array vortex. Still get. CVG arrays allow a low drag system to add many coupled smaller fuel-flow jets with strong mixing and liquid-particle breakup. The combustor can also use fuels such as natural gas (methane) or hydrogen, where vortices do not disrupt sticky liquid droplets but ensure the most favorable possible input-fluid / fuel mixing. .

  Liquid fuel flow vaporization-energy can be used to balance the operational cooling of the mixer CVG array 207 step, fuel plenum, jet and adjacent area, to control or isolate downstream heat flux conduction, etc. It can be improved by changing the material and design.

  FIG. 11b has an additional interface CVG array 229 embedded in the body transition after the fuel jet to reduce heat conduction into the fuel plenum, eg, 213 as a ceramic insert, ceramic after-body 228 and This is a cut-away cross-sectional view of a part of the downstream body, such as 225 and 216. Attached ceramic after-body 228 after the deformed 213 and 225 foils supporting the flow in opening F and H ducts and rich burn opening I eliminates the need for CVG cooling flow ducts 226 and 212, etc. Allows a simplified design. The igniter array 227 conductor is integrated or wired into the ceramic or CMC body, or through a hole from a core volume with a refractory metal such as tungsten, for example, while sparking out to the second conductor or cooling wall section. Can be). A cornered additional combustor injection jet 230 is shown in the CVG step of the interface CVG array 229 on the top or exterior surface of the ceramic after-body 228. Since the pressure at opening F / H and opening I can be varied and balanced in relation to the input pressure at opening E, the inlet bleed from upstream to slightly pressurize the core of the ceramic after-body 228 And then rejecting such cooling flow through the example of the combustor injection jet 230 and fluid-flow BL momentum on the opening H and / or opening I side of the ceramic after-body 228. Can be improved. The example of the combustor injection jet 230 may also be applied to the outer duct surface inlet CVG array 222 and the inner duct surface CVG array 223. Examples of optional step-expansion grooves and / or step shear guides can be added to the ceramic after-body 228, but are not shown for clarity of the drawings.

  The modified version of FIG. 11b of the 213 and 225 foils is shown as a thin wall casting and fuel plenum, and these items can be either rigid or manufactured in any combination fabrication method to provide the correct flow geometry. Can be done. The additional interface CVG array 229 may have valleys and chips that are offset from the mixer CVG array 207 or at different pitches to increase fuel mixing.

  The fuel injection pressure is controlled to ensure proper jet flow at the required operating load, and any liquid fuel that enters will not drop under vapor pressure until the fuel jet exits, so the liquid fuel flow will be vapor-locked ( Vapor-lock).

  Other examples of CVG arrays are included on other combustor surfaces that are beneficial in reducing combustor drag, and mixer CVG array 207 is preferred to ensure sufficient mixing and associated vortex turbulence It is clearly used as a large step structure and is used to reduce secondary drag. Preferably, intermediate-surface CVG array 206, external duct surface inlet CVG array 222, and internal duct surface CVG array 223 are also optionally added on the upper and lower surfaces to reduce the overall surface drag from the flow surface. , A wide tolerance range of Re values is allowed so as not to cause flow separation losses at the combustor and ducting surfaces.

  Combustors arranged (with possible ceramic after-body 228) for the most favorable flow in a single combustor formed by the external combustor pressure wall 200, drawing new geometry and the like It is possible to have a single example of guide 213 or more than one example of a pair of combustor guides 213 and 225. If the core design is more efficient for the design volume available in this embodiment, the combustor guide 213 from the essentially constant-radius (from the engine shaft axis) shown in FIG. And 225/228 can be modified to a design that is matched to be symmetric with a circle (more like the venturi tube example). Combustor guides 213 and 225 and mixer CVG array 207 can also be configured radially to be effectively aligned in a radial direction, with a combination of high pressure turbine inlet stator vanes having included fuel injection openings and combustion volumes Works in the same way. Examples of CVG combustor designs are for other flow styles such as flow ducts and combustor paths that are folded and flipped, as found, for example, in Allison 250, PW300 and other smaller sized turbine engines. Can be easily deformed.

  For example, other combustor styles such as liquid-fuel and oxidizer combustors improve flow and mixing interfaces and ducting / piping, with some working fluids likely to be colder before the flame front combustion point. Supply centrifugal turbo-pump (with optional integrated impeller CVG) for applications such as liquefied oxygen rockets or propulsion machines and high speed before ignition and expansion through exhaust nozzle to generate thrust It is also possible to use such a CVG vortex flow-mixing strategy that requires fine mixing at the same time. Such types of combustors may be in the form of mixer plates with flow injection holes, which provide outlet vortex filaments to improve combustion and mixing stability when fuel flow is throttled or varied. Can have a CVG embedded on the periphery to provide.

  A further combustor embodiment is a solid-fuel device in which fuel is stored in a pressure containment or (effectively) semi-closed duct / tube structure. Combustion proceeds with an oxidant flow mixed in solid fuel or an oxidant flow introduced (as in a Rutan / Virgin Galactic engine with N2O) and is an effectively processed input fluid-flow. ) Active combustion products are transmitted through the outlet nozzle output so as to form thrust. The containment / duct walls and / or nozzles are processed relative to the duct CVG embodiment of FIG. 10 above to have a CVG that provides a low-drag outlet flow surface-interface that appears as fuel is consumed. The TBC can then be coupled along a cooling jet added to, for example, an HPT turbine blade. The surface drag loss and impact on conventional conical / bell shaped or commercial Aerospike style type exhaust nozzle flow surfaces can be improved and / or deformed with CVG configured for this purpose. The contact ignition fluid mixing chamber acts like a combustion furnace and can utilize CVG or with attached nozzles.

  Fuel supply lines, pumps, igniters and other accessories, etc., are mostly standardized, but are not explicitly shown, and follow the general form and function of known prior art.

  FIGS. 11a and 11b are representative and not to scale, open fluid-flow separation and balance, fluid transition time, component size and example and location are compact, high performance, low emissions and energy efficiency. Based on the basic concept of using a drag-reduction integrated CVG for improved total drag reduction, fuel atomization and mixing in a typical combustor, to meet the design goals for the operating environment and fuel etc. Can be widely modified as required. FIGS. 11a and 11b may be, for example, an example of a CFM-56 combustor, or the general size of a segment, but the size and length, etc. as required for a particular gas-generator application. Can be adjusted larger or smaller. If the total internal surface area of the new technology conformal eddy current combustor is configured similar to the prior art combustor, it will provide significant absolute drag reduction and loss over the prior art design, and reliable combustion Allows the ability to design duct paths and foil sections for the correct branching / diffusion and flow velocities.

  As taught herein to improve the fluid-flow of the device, these surprisingly diverse ranges of high temperature and / or high stress example types are simply not possible with prior art eddy current generator approaches. Unexpected results and capabilities of fundamentally integrated CVG applications that are impractical or impossible. At most basic common levels, all cited embodiments and variations will achieve a certain level of gain, such as improved energy efficiency and / or extended control range, not possible with the prior art. Newtonian fluid-uses a new conformal vortex generator that processes or manipulates flow.

  Thus, while the disclosed information describes in detail preferred embodiments of the present invention, no material limitations are intended to the scope of the claimed invention, and certain features and modifications designed to those skilled in the art are Considered to be combined here. As a result, rather than being strictly limited to the features disclosed for the preferred embodiment, the scope of the present invention is described and specifically described in the following appended claims.

Cross-reference for related applications:
This application is a part of US national phase application US2011 / 0006165 filed on July 8, 2010, which is a regular application derived from US provisional application 61 / 224,481 filed on July 10, 2009. This is a continuation application and was filed on July 9, 2010 as international application PCT / IB2010 / 001885.

Claims (33)

In a method applied to a Newtonian fluid-flow aerodynamic / hydraulic processor to improve operating energy efficiency and / or design fluid-flow control range,
(I) input fluid source means for providing a source of the Newtonian fluid-flow and carrying a portion of the input fluid source;
(Ii) Process the Newtonian fluid-flow portion by using the incoming Newtonian fluid-bottom of the flow mass-flow with the most rolled up part of the boundary layer-angular step-down. A fluid-flow modifying surface used by the Newtonian fluid-flow aerodynamic / hydraulic processor having at least one conformal vortex generator means in communication with the portion;
(Iii) an active backward streaming tip tightly bound on the output surface-a stepped and free flowing step-vortex carried in a vortex filament and / or the streaming tip-vortex filament An output fluid interface means for providing a higher energy boundary layer thinning and / or relaminating effect on the output surface downstream of the flow-angular step-down adjacent to
Have
The application of the conformal vortex generator means may reduce the Newtonian fluid-flow energy loss by reducing downstream flow separation and / or thinning the downstream boundary layer, thereby reducing the fluid-flow control range. And applied to a Newtonian fluid-flow aerodynamic / hydraulic processor, characterized in that it provides improved operating energy efficiency and / or design operating capability.   The conformal eddy current generator is integrated and inherent, made of the same material, and integrated and manufactured within the fluid-flow modifying surface, allowing a new operating capability design. Item 2. The method according to Item 1.   The method of claim 2, wherein the integrated conformal eddy current generator is configured during a design and / or test process for improved performance.   The fluid-flow modifying surface is a member of a group comprising fluid-flow ducting means, bypass-fan means, compressor means, pump means, combustor means, rotor foil, stator foil, propeller means or turbine means. Using at least one conformal vortex generator means on the fluid-flow modifying surface to improve energy efficiency by reducing fluid-flow drag and / or extending operating capability. The method of claim 1, characterized in that   The fluid-flow modifying surface member does not protrude into the incoming free stream flow and is downstream of the conformal vortex generator means configured to not generate further flow or energy loss due to flow collision. Additional use of an angular jet fluid injection port connected by a plenum means to a fluid source of appropriate pressure to inject fluid-flow into the boundary layer to add additional momentum. The method according to claim 4, wherein:   The angled jet fluid ejection port is configured to provide resistance to clogging from debris, and an additional grouping of fluid ejection ports can optionally be used. Item 6. The method according to Item 5.   The angular jet fluid injection port is configured to inject fluid-flow momentum into the lower boundary layer with the aid of a velocity and / or pressure gradient induced downstream of the conformal vortex generator. 7. A method according to claim 6, characterized in that it discharges into a fluid-flow injection cavity.   The method of claim 6, wherein the angular jet fluid ejection port ejects fluid into a fluid-flow ejection cavity configured to increase fluid diffusion capability.   7. A method according to claim 6, characterized in that said angular jet fluid injection port adds cooling fluid in a boundary layer which acts to cool the downstream surface of said conformal vortex generator means. .   The member of the fluid-flow modifying means steps downstream of the conformal vortex generator means to guide the fluid-mass expansion of the free-stream flow vortex filament so as to avoid excessive collisions outwards- The method according to claim 4, wherein an expansion groove and / or a step shear guide is additionally used.   The fluid-flow modifying surface member generates a tip-positioned free-stream flow vortex filament tightly bound to the surface and / or suppresses loss-induced thickness in the downstream boundary layer region Use the first said conformal vortex generator means proximate to the leading edge, and further change the surface vortex state and / or improve the energy efficiency on the surface adjacent to the trailing edge. 5. Method according to claim 4, characterized in that two equiangular vortex generator means are used downstream.   The fluid source at a suitable pressure coupled to the angular jet fluid ejection port by plenum means is disposed on the fluid-flow modifying surface such that the suitable pressure allows maximum jet fluid flow velocity and momentum. 6. The method of claim 5, wherein the method is configured to vary with fluid-flow velocity.   The fluid-flow modifying surface member generates a tip-positioned free-stream flow vortex filament tightly bound to this surface and / or a loss-induced thickness of the downstream boundary layer region on the surface Is used in addition to the conformal vortex generator means, which inhibits fluid-flow through the gap and reduces the energy loss and / or gap fluid-flow loss in relative motion. 5. A method according to claim 4, characterized in that it is applied facing the gap between the flow surfaces.   The fluid-flow modifying surface member uses the conformal vortex generator configured to be entrained in the fluid-flow with sufficient energy to cause debris to cause mechanical damage, and downstream impact and 5. Method according to claim 4, characterized in that it tends to clean the next surface so as to minimize corrosion damage.   The integrated conformal eddy current generator provides unique alignment marks and reference alignments for additional mounting of thinner and / or lighter removable conformal eddy current controller components to be matched A combined conformal vortex generator having a structure and / or increased step height that includes protection from the matched thinner and / or lighter removable conformal vortex generator components The method of claim 2, wherein the method is configured as a partially step-height integrated conformal eddy current generator array to form   The fluid-flow injection cavity connected to the angular jet fluid injection port connected to the fluid source of the appropriate pressure by the plenum means is from the lower boundary layer to improve downstream fluid-flow. 8. A method according to claim 7, characterized in that it uses a suction to withdraw fluid-flow and is assisted by the velocity and / or pressure gradient induced downstream of the conformal vortex generator.   A second instance angular jet fluid injection port applied to the fluid-flow body surface as a plenum instance with a first fluid-flow injection cavity, an angular fluid injection port and a suction And a fluid-flow injection cavity configured to communicate plenum fluid-flow and located in a lower local-pressure region of the fluid-dynamic body surface, thereby extracted from the first example injection cavity Fluid is injected as a relatively high pressure fluid through the second injection cavity to improve downstream fluid-flow of the second instance and is induced downstream of the conformal vortex generator of the second instance. Body fluid-flow performance and energy Characterized in that to improve over efficiency The method of claim 16.   The fluid-flow modifying surface combustor member generates a tip-positioned free-stream flow vortex filament tightly bound to this surface and / or a loss-induced thickness of the downstream boundary layer region on the surface Combined integrated turbine input stator flow guide surface with low energy loss to produce higher efficiency and / or compact combustor design using the integrated conformal vortex generator means to suppress The method of claim 4, further configured as follows.   The Newtonian fluid-flow aerodynamic / hydraulic processor is a gas turbine engine using at least fluid-flow ducting means, compressor means, combustor means and turbine means, wherein at least one included The fluid-flow modifying surface further uses conformal vortex generator means to improve energy efficiency by reducing fluid-flow drag and / or extending operating capability. Item 5. The method according to Item 4.   The combustor member of the fluid-flow modifying surface is tightly tied to the combustor surface with the addition of outlet nozzle means as output fluid transmission means to form a nozzle exhaust fluid-flow that generates thrust. Generate tip-positioned free stream flow vortex filaments and / or suppress loss-induced thickness of downstream boundary layer region on the combustor surface; generation of conformal vortex flow configured on the combustor surface 5. A method according to claim 4, characterized by using vessel means.   The outlet nozzle means for forming the exhaust fluid-flow generates a tightly-tipped tip-positioned free-stream flow vortex filament on the nozzle surface and / or nozzle exhaust fluid-flow drag and / or energy Using additional conformal eddy current generator means configured on the nozzle surface to reduce loss and extend nozzle actuation capability, to suppress loss-induced thickness of the downstream boundary layer region on the nozzle surface. 21. A method according to claim 20, characterized.   An associated angular jet fluid injection port adds cooling fluid-flow in the boundary layer that acts to cool the downstream surface and induces downstream of the conformal vortex generator means applied to the nozzle surface The method according to claim 21, characterized in that it is assisted by a controlled speed and / or pressure gradient.   The conformal vortex generator means comprises a design of the fluid-flow modified surface for the new actuation capability including increased separation-free angle of attack range and / or increased blade rotation angle and / or fewer stages. The method according to claim 2, wherein:   The Newtonian fluid-flow aerodynamic / hydraulic processor comprises at least one integrated conformal eddy current generator in a duct or pipe connected to the output means to control fluid-flow drag and energy loss. 2. Method according to claim 1, characterized in that at least input connection means connected to the means are used.   The method of claim 4, wherein the fluid-flow modifying surface compressor and turbine member are combined to form a turbocharger embodiment.   The fluid-flow modifying surface fluid-flow ducting means member is configured as a flow-body surface having a closed and / or open end, wherein in operation with application of the conformal vortex generator means, 5. Method according to claim 4, characterized in that the flow-body symmetric drag and / or asymmetric yaw-induced force is reduced.   The flow-body is transferred to free-flight with a predetermined kinetic energy, and improved energy efficiency and / or fluid-flow kinetics allows extended range and / or path stability, 27. The method of claim 26.   The member of the fluid-flow modifying surface may be able to detune and / or avoid mechanical resonance modes and / or vibration modes and / or consistent reflection points that are tuned to minimize bending. 5. The method according to claim 4, characterized in that one or more examples of the conformal eddy current generator varying along the surface and / or configured with non-uniform spatial geometry are used.   The fluid-fluid ducting means embosses closed-end geometry cells having a wall-supporting root intersection radius larger than the diameter of the perpendicular intersection so as to form a duct surface with optimal beam intensity and thermal conductivity. 5. A method according to claim 4, characterized in that the surface area is closed to include fluid-flow using a defined wall. In a Newtonian fluid-flow aerodynamic / hydraulic processor with improved operating energy efficiency and / or design fluid-flow control range,
(I) an input fluid source providing the Newtonian fluid-flow source and carrying a portion of the input fluid source;
(Ii) Process the Newtonian fluid-flow portion by using the incoming Newtonian fluid-bottom of the flow mass-flow with the most rolled up part of the boundary layer-angular step-down. A fluid-flow modifying structure used by the Newtonian fluid-flow aerodynamic / hydraulic processor having at least one conformal vortex generator in communication with the portion;
(Iii) an active backward streaming tip tightly bound on the output surface-a stepped and free flowing step-vortex carried in a vortex filament and / or the streaming tip-vortex filament An output fluid interface that provides a higher energy boundary layer thinning and / or relaminating effect on the output surface downstream of the flow-angular step-down adjacent to
Have
The application of the conformal vortex generator means may reduce the Newtonian fluid-flow energy loss by reducing downstream flow separation and / or thinning the downstream boundary layer, thereby reducing the fluid-flow control range. Newtonian fluid-flow aerodynamic / hydraulic processor characterized in that it provides improved device operating energy efficiency and / or design operating capability.   The conformal eddy current generator is integrated and inherent, made of the same material, and manufactured integrally within the fluid-flow modifying surface, allowing for the design of new operating capabilities. The apparatus of claim 30.   The conformal vortex generator is configured to generate hydraulic vortex filaments that act to suppress cavitation bubble development to minimize damage and / or noise arising from cavitation. The apparatus of claim 30.   31. The conformal vortex generator is configured to generate a hydrodynamic vortex filament that acts to alter the propagation of acoustic waves so as to suppress the generated noise. The device described in 1.

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