RU2642203C2 - Method and system of aero/hydrodynamic control of newtonian fluid flow in radial turbomachine - Google Patents

Abstract

FIELD: machine engineering.

SUBSTANCE: method and system for aero/hydrodynamic control of newtonian fluid flow in the radial turbomachine which use conformal vortex generators is described.

EFFECT: improvement of energetic efficiency and possibility to control various points in turbo-compressor or processing device for aero/hydrodynamic treatment of newtonian fluid flow.

32 cl, 21 dwg

Description

CROSS REFERENCE TO RELATED APPLICATIONS

[0001] This application is a partial continuation of the national stage of US patent application No. US 2011/0006165 A1, filed July 8, 2010, which is a regular application isolated from provisional application US No. 61 / 224,481, filed July 10, 2009, also filed as an international application PCT / IB 2010/001885 on July 9, 2010.

FIELD OF TECHNOLOGY

[0002] The present invention relates to the field of processing devices for aero / hydrodynamic processing of a Newtonian fluid stream and to the ability to increase their energy efficiency and / or line operating modes when using the new design of the fluid dynamics of a conformal vortex generator (CVG). This new application of integrated or integrated conformal vortex generators typically operates in various places and functions, such as active disks, cascades of aerodynamic surfaces and flow control surfaces in dynamic turbines, such as mobile turbine engines, stationary turbines for energy, helicopters, wings and in other cases Newtonian fluid flow applications.

BACKGROUND

[0003] Additional conformal vortex generators used, for example, in a helicopter erosion protection system (EPS) cannot be used and matched with small complex and intricate turbine designs with very large radial acceleration of the order of tens of thousands of gravitational units "g", which require new inherently built-in or integrated conformal vortex generators for profile gratings with a high duty cycle and withstanding harsh environmental conditions such as high e temperature, and the input surface with sharp edges. Additional conformal vortex generators are bonded using an adhesive to the existing aerodynamic surface or surface structure of the fuselage after the manufacturing stage, when the initial aerodynamic surface or the surface of the fuselage according to the design plan or engineering analysis is not configured to better combine the advantages of the conformal vortex generator. On the other hand, the well-known built-in conformal vortex generator is included in the design and engineering process for a new aerodynamic surface or design of a surface fluid flow control, as a result of which it can be possible to create new combinations of performance, characteristics, ranges of regulation of the fluid flow, energy efficiency and selection of manufacturing methods impossible with an additional conformal vortex generator.

[0004] A gas turbine engine is a well-known example of a complex turbomachine that uses a wide range of Newtonian fluid flow, thermodynamics, materials, and physical methods of application to a real fluid flow processing device. Each of the successive function blocks receives a certain fluid inlet stream, processes this fluid in some way, and then transfers this fluid through an interface to the next engine stage. The source air inlet is a first mating device for introducing a fluid, and any exhaust nozzles of a cold or hot section complete the processing of the fluid by discharging an output mating device (s) into the surrounding atmosphere. For turbine engines that use the well-known Brighton cycle, efficiency is assessed by the well-known characteristics of the thermodynamic cycle of the ratio of the peak operating temperature of the fluid to the final differences in the outlet temperature and flow efficiency or energy loss in the compressor, turbine, combustion chamber, and inlet guide vane (IGV ), the gas path of the sewer and the outlet nozzle.

[0005] This application describes fluid streams that are Newtonian "working fluid" fluids, typically atmospheres or other gases, but many conformal eddy generator implementations are also suitable for liquids or mixed phases when the Reynolds number (Re) needs to be considered. It is known that many aerodynamic surfaces and structures for gas flows in turbomachines and devices are measured, tested and visualized for convenience, for example, in water tanks using marking materials and methods for observing the measurable effects of fluid flows. In this application, the term "fluid stream" is applied to any Newtonian gas and / or liquid phases, since the dynamics of the fluid is governed by the actual conditions of the fluid flow and Reynolds numbers.

[0006] The design of the stator and rotor disks of the compressor blades and the engine turbine as a matrix of aerodynamic surfaces in the profile grid are optimized for aerodynamic characteristics, geometric shapes of the engine and mass flows. The “cold section” of the compressor and the possible stages of the bypass fan and the air duct operate under slightly softened environmental conditions, as the early stages operate closer to lower inlet fluid temperatures. The flow enhancements in these cold sections do not have the complexity associated with the influence of high temperature gas on the strength of materials, oxidation, or other problems to compose common rotational, flow, aeroelastic, vibrational, fatigue, and pressure-related stresses. The compressor stages can absorb approximately 60% or more of the total amount of energy provided by the fuel, which is extracted by the stages of the turbine. Increasing the efficiency of the remaining available energy at the turbine outlet and the pulse of the exhaust nozzle have a great influence on the available output useful work.

BACKGROUND

[0007] Low pressure turbine stages (LPT): In many modern concentric shaft engine designs, the low pressure turbine stage typically extracts energy from the mass flow of gases exiting the “hot section” of the combustion chamber, inducing a pressure drop, and conducts this energy through the most internal axial drive shaft to the bypass fan, shaft loads and / or compressor initial stages.

[0008] When loading the blades and increasing the load factors of Zweifel steps of the low pressure turbine to change the cascade fill factor, reduce the number of blades, engine size, its weight and cost, a problem arises with the aerodynamics of aerodynamic reactive surfaces in the turbine grill. With low Reynolds numbers “deviating” from design conditions, rotor and stator vanes may experience undesirable pressure gradients on the suction surface, which induce thickening of the boundary layer (BL), transition to a turbulent fluid flow, separation of the fluid flow in the lower impulse parts boundary layer, common areas of disruption of the fluid flow and loss of energy efficiency.

[0009] McQuilling writes in his dissertation, “Designing and Evaluating the Lift Force of a Low Pressure Turbine Blade,” that “high lift” blades (and frontal load) designs for low pressure turbines, similar to his proposed L2F blade with improved Zweifel coefficients compared with common examples similar to the well-known Pratt and Whitney Inc “Pack-B” blade designs, can be constructed without additional flow modification methods to counteract the separation or stall of the blade at extreme values of the operating range or "deviation from design conditions".

[0010] In this case, optimizing the front load of the aerodynamic surface of the blade allows the pressure recovery of the suction surface to extend over a longer chord distance, so that an undesirable pressure gradient decreases with an improvement in the fluid flow and a decrease in the separation of the lower energy and small momentum of the lower boundary layer . In this case, the main fluid flows along the blade, reactions to unstable upstream vortex traces, etc. can be designed with an improvement over the prior art, but the ultimate combined performance improvement should be optimized based on the design load on the blade, and also using flow improvement methods to reduce aerodynamic drag and separation, in particular when deviating from design conditions within areas of changing characteristics.

[0011] Examples and effects of modifying a fluid flow are summarized and described, for example, by Rouser in the dissertation “Use of Dimples to suppress boundary layer separation on a low pressure turbine blade” "), and include many types of surface structures and methods used mainly to generate vortex flows and transfer energy from the layers of the stream with a higher momentum to the lower layers (closer to the aerodynamic surface) to resume the energy supply to the lowest e levels of the boundary layer and preventing undesirable effects of the pressure gradient and flow of fluid from the airfoil compartment.

[0012] Known vortex generators (VGs) used to improve aerodynamic surface flows are divided into specific categories with various effects and advantages. Protruding devices such as inclined elements, inclined blades, grooves, wheeler inclined vortex generators and the like create suitable vortices, but at the same time generate additional aerodynamic drag, despite the fact that they tend to change the flow conditions of the boundary layer, in particular , to reduce losses due to stall and a decrease in aerodynamic drag. In addition, these protruding devices take energy from the higher energy upper layers of the thickened boundary layer or undisturbed flow at lower Reynolds numbers, but then pass upward over the thinner boundary layer at higher Reynolds numbers and cause high induced aerodynamic drag at this characteristic point. These devices are characterized as having heights that make up a significant part of the thickness of the boundary layer, for example, in the range of 35-100% or more of the maximum thickness of the boundary layer in a traditional vortex generator.

[0013] Submerged or recessed vortex generators and micro-vortex generators such as the Wheeler S-shaped submerged channel or even recesses with a depth shorter than the depth of the boundary layer, have been extensively investigated and in testing showed generation with reduced added aerodynamic drag compared to the protruding vortex generator. These devices have a varying geometric shape or height of the step or inclined element in the direction along the chord. The vertices of the S-shaped submerged devices are oriented towards the incoming fluid stream and do not correspond to the profile of the aerodynamic surface. For some microvortex generators located in the lower levels of the boundary layer, the difficulty of serial application is the need to generate a vortex with sufficient energy, and in a rotating medium, for example, on a blade, such an application in the immediate vicinity worsens performance.

[0014] The recesses are usually a simple and omnidirectional device, such as described by Rouser, which reduces aerodynamic drag by suppressing increased stall bubbles (used, for example, to increase the range of golf balls due to reduced aerodynamic drag). However, the vortices formed by the recess have a complex structure with less than optimal intensity or the ability to transfer a large amount of energy of an unperturbed fluid flow to the lower boundary layer.

[0015] The recesses for controlling the boundary layer are complex because the characteristics are sensitive to the geometric shape and Reynolds number, in which vortex modes are predominant. A traditional vortex-type vortex generator has an additional problem, for example, when the Reynolds numbers of real low-pressure turbine blades, such generators become very small and have a size of the order of several millimeters, which corresponds to very sharp, thin and fragile structures, which are also subject to erosion under the influence of flying particles and damage by oxidation under the influence of hot exhaust gases. Additional problems are the mechanical fatigue of the blade due to the concentration of local stresses during the bending of the blade and also the danger posed by these sharp objects to the operating staff.

[0016] Inclined inlet (eg, Wheeler, upwardly inclined flow and backward-facing step) and oblique outlet (eg, S-shaped submerged, downwardly inclined flow and forward-facing step) conventional swirl generators also form other secondary flow patterns and potential shock waves, such as a transverse flow or sweep-shaped horseshoe-shaped vortices that deflect energy from the strict direction of movement of the vortices along the chord.

[0017] A NASA study shows that traditional vortex generators produce vortices that typically exist with movement in the direction of flow over distances of approximately 30 heights of the traditional vortex generator, at best up to about 40 heights of the traditional vortex generator in the rear direction along the length of the chord and end up convecting away from the aerodynamic surface into layers with high energy.

[0018] Rouser also describes other methods without using a vortex generator to control the boundary layer flow, as shown in FIG. 10 (attributed to McCormick), in the form of passive porous surface devices in which air under pressure is supplied to the surface of a low-pressure region before being separated through a matrix of holes or injection slots or steps. Such approaches realize effects similar to the Coanda effect, or increase the lifting force by other methods or using a flap with blowing of the boundary layer, or other suction methods used to stabilize the region of the boundary layer. Of course, one of the problems associated with jet injection of a fluid is to balance the impulses of the boundary layer and the nozzle to prevent jet “peeling” or stalling of the stream while decreasing the velocity of the boundary layer or changing the Reynolds number of the stream, moreover, the local boundary layer is destabilized with the formation of a horseshoe the vortex around the leading edge (LE) of the column of the jet fluid stream or jet before it can be brought closer to the surface of the blade.

[0019] The hybrid laminar flow control (HLFC) described in the Boeing 787 airliner uses a well-known porous suction surface to control the boundary layer at the leading edge of the vertical stabilizer to improve flow stall control (instead of traditional swirl generators), for example, with one running engine using air intake from a passive source. The use of a porous suction surface containing openings / cells faces the problem of clogging the entrances with debris, viscous energy losses, energy consumption to induce suction, along with a compromise regarding the strength of the composite structure.

[0020] Stephens in US patent No. 2,800,291, Wheeler in US patent No. 4,455,045 and 5,058,837, Rinker in US patent No. 7,900,871 and many others describe options for additional inclined vortex generators or similar discrete forms that start from a thin (non-zero) input edge and then pass back into the fluid stream in the form of an inclined element with an apex having an increased height above the underlying aerodynamic surface. Geometrically or morphologically, these devices are not conformal to the underlying aerodynamic surface in any interpretation. As described in Stephens '291, swells or equivalent vortex generator designs such as those described in Rinker' 871 cannot act as a drag reducing agent at a low angle of attack (AOA) of the aerodynamic surface or the fuselage surface. In this application, the term "low angle of attack" is defined as the included range of positive, zero and negative angles of attack, below which there are no significant separation of the fluid flow (for example, stalls) or separation bubbles on the aerodynamic surface or the surface of the fuselage located upstream of any conventional end compartments of the outlet stream, for example, the outlet stream of the fluid, or at the trailing edge, where the Kutta-Zhukovsky conditions are met. For most aerodynamic surfaces, the range of angles of attack of +/- 4 ° could meet this condition, but is not limited to the indicated limits, and in some cases, an increased range close to the angle of attack of the stall can be used. Schenk, in US Pat. No. 4,354,648, describes arrays of protruding low-profile boundary layer turbulence devices for generating turbulence in the boundary layer and reducing the separation of the flow from the aerodynamic surface of the wing. For Schenk '648, the input height of the device is not zero, and the devices themselves are not completely conformal to the aerodynamic surface, so that they induce aerodynamic drag as a result of horseshoe-shaped vortices and turbulence, even though vortex generators having reduced sizes compared to the dimensions of known vortex generators.

[0021] Having a small size, discontinuous or having a point-like zone of action and undirected turbulence is not an effective way of reenergizing the boundary layer.

[0022] Vijgen et al. In US Pat. No. 5,088,665 describe a modification in the trailing edge (TE) of an aerodynamic surface with the addition of a serrated panel or matrix of triangular / gear elements to "improve the lift and drag characteristics". The addition of additional active aerodynamic elements extending outward beyond the physical extent of the original based aerodynamic surface is a significant difference from the addition of conformal vortex generators to the aerodynamic surface in front of the trailing edge and inside the original physical length or boundary of the aerodynamic surface. Fritz in US patent No. 8,083,488 also describes an additional panel with serrations in the trailing edge, which is different from Vijgen '665 and is patentable. Shibata in Patent No. 6,830,436 describes and claims a wind turbine blade with “serrations” or serrations added to the trailing edge to reduce noise and increase efficiency by changing the back pocket vortex track. Gliebe in US Pat. No. 6,733,240 also describes and claims a serrated trailing edge on a turbofan blade to improve flow mixing and reduce noise, and uses the same aerodynamic effect and obtains the same results as Young described in US Pat. No. 3,153,319 and Balzer in U.S. Patent No. 6,612,106. Gliebe '240 does not describe a decrease in aerodynamic drag below the original design, which violates the linear trailing edge and is clearly different from conformal vortex generators, which are simply added to the aerodynamic surface in front of the trailing edge to reduce aerodynamic drag compared to the original configuration, and other improvements.

[0023] Godsk in US Pat. No. 7,914,259 describes the use of several rows of well-known discrete vortex generators located along the blades of a wind generator to expand the initial subsurface angle of attack from about + 10 ° to about + 16 ° with added vortex generators, as shown in FIG. 3 in the drawings to his patent. Godsk '259 in its FIG. 4 shows a known problem with discrete inclined and vortex generators embedded in the blades that operate at low angles of attack and up to about + 10 ° the initial angle of attack of the stall, and the blade equipped with a vortex generator has a higher drag coefficient (C _d ) than the original unmodified shoulder blade.

[0024] Wormian, in US Pat. which actually have a high angle of attack, or a departure from the fluid flow lines, which usually create downstream turbulence and high induced aerodynamic drag occurrence. The paddle vortex generators described in Wormian '402, during operation, themselves develop a significant shape-dependent aerodynamic drag, but reduce a much larger part of the aerodynamic drag of the compartment downstream, so that they provide an overall positive balance for reducing aerodynamic drag, but at the same time in fact, these vortex generators induce aerodynamic drag and can only manifest themselves as a means to relative drag reduction in the scenario Changes another substantially separated or shear flow.

[0025] Inclined and blade vortex generators tend to generate unstable vortices passing into the upper levels of the boundary layer, which are not limited to the near-surface region of the aerodynamic surface. Depressions and bulges create vortices that are not highly efficient or high-energy, and bulges have the same problem as scapular vortex generators, which consists in inducing excessive aerodynamic drag in the upper levels of the boundary layer when the Reynolds numbers change and the boundary layer is thinner.

[0026] Martin, McVeigh, et al. In the article "Passive Control of Compressible Dynamic Stall" in the AIAA journal writes with reference to its FIG. 27 that the reduced vortex vane generators used on helicopter rotor blades increase the C _d blades from about 0.01 to about 0.015, which significantly increases the requirement for rotor power by about 50% while reducing the moments of dynamic stall and pitch of the blades due to the vortex generators increasing the angle of attack of the stall. McVeigh in US patent No. 7,748,958 claims this design of a vortex generator and a method for reducing the moment of dynamic stall / pitch of a blade, but cannot declare the addition of an absolute decrease in aerodynamic drag based on published measurement results and facts known in flow physics.

[0027] Volino, in NASA's Synthetic Vortex Generator Jets used to control the compartment on the aerodynamic surfaces of low pressure turbines research report, describes the active compartment management using synthetic vortex generator jets (VGJs) in which vortices are generated by pulsating oblique jet jets flows introduced into the boundary layer, in which vortex flows are partially induced, directed along the chord and facilitating in a manner similar to traditional vortex generators It is, reducing bubbles stalling. The Volino approach is unique in that the proposed design creates pulsed jet flow regimes without a clean acoustic generation flow to eliminate the need for a constant source of energy to energize the fluid flow of the blower machine, which increases the cost of energy generation. The interaction of the fluid from the nozzle with the upper flow of the boundary layer and the layers having a large momentum generates a turbulence, but also causes aerodynamic drag in its tendency to simultaneously spread energy, widely distributed over the span, to the following regions of the boundary layer.

[0028] However, all known devices designed to improve flows along the aerodynamic surface or blades of low pressure turbines and reduce separation, face the problem that the real rotating medium creates additional difficult conditions under which vortices can be generated in the upper levels of the boundary layers and convect outward in the direction of the sweep of the aerodynamic surface. This is due to the fact that the centripetal force tends to rotate the vortices loosely coupled to the surface outward (radially toward the end of the blade) after passing the physically specified generation point to higher levels of the fluid flow of the boundary layer, since there is no significant pressure these vortices are closer to the blade when they are accelerated along a curved path, and also, additionally, because the vortices tend to move lower along the flow, they can convection Vat to the top of the boundary layer, may cross any disposed spanwise blade secondary flows and also rapidly escape to the outside.

[0029] In this case, the preferred tendency of the vortices directed along the chord generated earlier on the chord to energize the boundary layer and reduce flow stall and aerodynamic drag actually becomes undesirable, as shown by Martin et al., And the vortices precess to act partially at an angle to undisturbed flow (the axis of the vortex is more oriented in the direction of the sweep) in a chaotic manner, resulting in a tendency to thicken the next boundary layer and increase aerodynamics eskogo resistance without any impact on the department. This effect has been clearly demonstrated on helicopter rotor blades operating at an acceleration of approximately 1200 g (gravitational units) at the ends of the blades, which is significantly lower than in the lattice environment of a low-pressure turbine. Known vortex generators that excite or convect vortices above the boundary layer are generally undesirable for use in a rotating medium, as shown by Martin et al.

[0030] Backward steps transverse to the undisturbed flow are known to generate trapped vortices and therefore cause fluid loss and flow disturbances, as described by Calvert and Wong in the article “Aerodynamic Effects of Helicopter Blade Anti-Erosion Covers” in AIAA. They describe that swirling swirls in a simple backward-facing step (i.e., at an angle of 90 ° to the fluid flow), such as that made on the erosion protection strip (EPS) of the leading edge of the UH-60 helicopter blade, as is known increase the aerodynamic drag of the blade to approximately + 5% or more, depending on the operating conditions of the blade.

[0031] In the case of UH-60, for a backward-facing step, for example, ~ 0.5 mm high and 5 m long, one can assume a trapped, sweeping stream formed by a step vortex with an aspect ratio of approximately 10,000, and in the case of hydrodynamics this is a very fine structure vortex jet is dynamically unstable. In the part of the leading edge of a rotating aerodynamic surface, such as, for example, a helicopter blade, there are many mechanisms that intensively upset the fluid flows at the level of the boundary layer. Secondary flows passing along the span of the blade (or generally radially) above the boundary layer tend to activate external shear forces that act on the lower momentum layers of the boundary layer, so that they flow at an angle to the chord of the aerodynamic surface and, therefore, at an angle to the step erosion protection systems. This flow configuration provides the fundamental reason for the decay of the vortex formed by the step along with centripetal acceleration on the viscously attached layers of the boundary layer, which preserve the trail of the aerodynamic surface, which can cause sections of the vortex formed by the step to be continuously lost in the vortex sections, which can precess with an inclination to the blade span and disturb and thicken the next boundary layer on the aerodynamic surface, as well as increase the loss of aerodynamic sop rotation, as it turned out. Acoustic Tollmien-Schlichting (TS) pressure waves develop in the leading edge upstream of the flow of laminar flow regions, amplify, propagate backward and contribute to the transition to boundary layer turbulence and hairpin-like vortex flows, and these disturbances also affect the stability of the vortex formed by the step and the discharge frequency . The unexpected result is that you can use the backward-facing step arrangement to reduce aerodynamic drag, reduce energy loss and increase the efficiency of the fluid flow over the original or unmodified surface of the fluid flow.

[0032] Stephens' 291, Wheeler '045 and' 837, Rinker '871, Vijgen' 665 and the like, and all other known sources usually show vortex generators, generally having triangular shapes with obvious visual similarity, but aerodynamic research shows that their shape and effects are clearly different from the new conformal vortex generators according to the present invention.

[0033] High pressure turbine stages (HPT): As the turbine inlet temperature (TIT) rises (the temperature of the fluid from the combustion chambers), resulting in improved, lightweight engines and optimized specific fuel consumption (SFC), a point is reached, in which no high-alloy nickel-based alloy can directly withstand the temperature of hot gases, and there is a need for other methods of efficient cooling and maintaining the shape and strength of engine components under the influence of heat zok. Typical designs use the extraction of cooling air from a compressor to cool the combustion chamber, stators and rotors of high-pressure turbines and duct surfaces to a point where the flow temperature is reduced to safe values, and a ceramic heat-insulating coating (FA) can also be used, for example minimize energy costs for cooling. The heat-insulating coating reduces the cooling requirements and energy costs associated with it, since the surface thermal resistance increases, but the remaining heat flux must be removed so that the main metal components remain sufficiently cold and do not reach the softening or destruction temperature of their crystalline structure.

[0034] High pressure turbine cooling: It is known that on the surfaces of the duct of the hot section and the blades (rotor and stator) intensive mixing or turbulization of higher and hotter gas flows with the lower boundary layer occurs, which causes an increased heat flow load on the surface of the components, exposed to the flow of hot gas, and therefore, these components need increased cooling. Thus, unwanted separation of the fluid stream and turbulence lead to problems that reduce efficiency (increase aerodynamic drag) and deteriorate heat resistance.

[0035] Examples of known solutions to these problems can be found in Howald in US Pat. No. 3,527,543, which describes film cooling of a surface using holes in a blade to transfer internal cooling air to the surface of the blade. In Bird et al., US Pat. No. 5,193,975 describes a turbine blade with internal cooling channels, pin cooling and the discharge of cooling air through slots in the trailing edge. Ejecting slots with rectangular edges are usually undesirable, since they increase aerodynamic drag by forming an undesirable vortex passing at right angles to the flow, if the speeds of the main flows and the cooling flow are not matched, and the flow-separating edge of the slot has no narrowing to obtain a sharp (very thin) edges. Zelesky in US Pat. No. 5,378,108 describes a series of slots in the trailing edge, modified to optimally distribute cooling flows along the trailing edge, and a thin trailing edge, the thickness of which is determined only by the wall thickness of the suction surface, to minimize aerodynamic drag. Green in US Pat. No. 5,374,162 describes cooling using a fountain head at the leading edge of the blade, which is effective for changing the angles of the inlet stream. Lee et al. In US Pat. No. 7,011,502 describe a bridge-molded device at the leading edge with pin grids and cooling outlet slots, but the outlet slots still pose a linear edge problem associated with unwanted swirl propagation along the span if fluid flows are not merging aligned and the edges are not sharp.

[0036] Shih and Na, in an article entitled “Increasing adiabatic film-cooling efficiency by using an upstream ramp”, published in ASME, describe an almost three-fold improvement in adiabatic the effectiveness of film cooling by using an inclined element in front of the outlet of the cooling nozzle instead of vortex generators embedded inside the nozzles or near the nozzle holes. In this case, a whirlwind passing along a span (across an unperturbed flow), trapped behind an inclined element, modifies the flow of cooling fluid ejected by the nozzle by destabilizing the undesired leading horseshoe-shaped vortex formed by the nozzle in such a way that it spreads the cooling mass along the span of the flow and in front of the nozzle exit for improved lateral or wide cooling. This inclined nozzle configuration shows about a three-fold increase in adiabatic cooling efficiency due to the inclined element, but the protruding inclined structure, as indicated above, is undesirable in this form, or the aerodynamic pressure resistance increases over the flat initial structure. The inclined element passing into the layers of hot gas also requires an additional mass of heat insulating coating, as the authors indicate.

[0037] So, the idea of the inclined element and stage proposed by Shih and Na with swirling swirls promoting the spread of the cooling fluid pays for the improvement of cooling with undesirable loss of efficiency due to increased aerodynamic resistance to the fluid flow and viscosity loss. The inclined element was simulated to generate only swirling vortices without any vortices directed along the chord at the edges of the inclined element, similar to the Wheeler vortex generator. Heidmann, according to NASA, in an article "A Numerical Study of Anti-Vortex Film Cooling Designs at High Blowing Ratio" describes a numerical study of film cooling structures based on a high-blow-up vortex (anti-vortex) pair. a vortex-antivortex pair formed by nozzles having a reduced size located upstream of the stream, which minimizes unwanted kidney-like vortices of the main stream of the cooling nozzle. This method is an attempt to propagate along the span of adiabatic cooling and prevent jet peeling, in which the jet stream is separated from the surface, but not disclosed as a combination that reduces losses due to aerodynamic drag of the aerodynamic surface or increases the efficiency of reducing the aerodynamic drag of the turbine.

[0038] The turbulators can also be made in the form of triangles, inclined elements, chevrons, etc. located in the flow paths of the cooling fluid in pipelines and internal serpentine cooling channels of the cooled rotor and stator vanes and surfaces streamlined by the flow of hot gas in the turbines high pressure (НРТ). In this case, the geometric shape of the flow, in contrast to conformal vortex generators, is formed to provide maximum flow turbulence for mixing heated fluids of the surface boundary layer with the main cooling fluid flows to maximize heat transfer or thermal conductivity and increase cooling efficiency regardless of the induced aerodynamic drag. In this case, vortex-generating steps or chevrons and turbulence-inducing structures formed in the surface are aerodynamically close to each other, so that the cooling fluid does not reorganize into smooth smooth flows as a result of the decay of the vortices. It is clear that this approach does not provide low drag when handling fluid flows, and the separation of the boundary layer of turbulent flow actually increases with improved heat transfer of the working fluid, so that these known designs are clearly different from conformal eddy generators.

[0039] Thermal insulation characteristics of a high pressure turbine: Terry in US Pat. No. 2,757,105 and Haskell in US Pat. No. 5,260,099 describe coatings for engine blades, and Driver in US Pat. No. 4,303,693 describes a plasma jet coating method. Kojima et al. In US Pat. No. 5,630,314 describe a “tile” or column heat insulating coating (FA) for turbine blades, and Nissley et al. In US Pat. No. 5,705,231 describe a method of manufacturing a ceramic coating by plasma spraying a pre-ground or segmented ceramic material that allows you to create a heat-insulating coating having high wear resistance and resistance to cracking at temperatures of the gas turbine. Nissley and well-known sources also describe an intermediate diffusion method or surface bonding layer (for example, of MCrAlY alloy, aluminide, alumina, etc.) to improve ceramic adhesion, improve the matching of thermal expansion coefficients, create a plastic transition layer and provide an improved protection against thermal oxidation of the base layer, for example, from nickel heat-resistant alloys commonly used in components withstanding high mechanical and thermal loads.

[0040] Spengler et al. In US Pat. No. 4,576,874 describe the application of one or more ceramic layers of a heat insulating coating to a turbine blade to increase wear resistance and, in particular, the use of ceramics at high temperatures close to operating temperatures, resulting in cyclic repetition of the transition to a colder state, ceramics under the action of tensile loads are less prone to cracking and cracking. Strangman, in U.S. Patent No. 6,224,963, describes laser segmentation of a heat insulating coating to mitigate cracking problems due to abrasion or mechanical damage to a coating section. Thus, an important problem of using a heat-insulating coating in the steps of a turbine is the resistance to mechanical damage, cracking and the best coordination of incommensurable coefficients of thermal expansion to ensure the best resistance to thermal and inertial loads, as well as chemical corrosion effects.

[0041] Compressor characteristics: compressor efficiency is an important characteristic of its operation, and the inherent control of the boundary layer, which can delay the separation of the fluid flow and, thus, enable the stator and rotor blades to work closer to uncontrolled separation conditions and, thus, achieve higher diffusivity, increased rotation angle and increased load on the blade, as a result of which the possibility of applying increased pressure on every step. In addition, there may be a problem with the compressor, namely, that a stall of the flow that propagates between many stages (pairs of stator / rotor disks) can lead to complete destruction of the fluid flow structure, surge / loss of power and, in extreme cases, to damage equipment.

[0042] In order to reduce flow stalls, fluid nozzles located on a suction aerodynamic surface can be used. The rotor and stator blades of the compressor are much thinner and less curved than, for example, the aerodynamic surfaces of the turbine stages, so the addition of internal flow channels to enable the selection of the fluid flow for the nozzles is difficult to manufacture, but in general most of the central material of the blade concentrated near the neutral axis of stresses, so that some of the material can be removed without significant deterioration of the inertial properties of the section or its Nost. Of course, reduced flow paths are more susceptible to clogging, and another problem remains that the nozzles can induce horseshoe-shaped vortices that can cause delamination if they are not controlled. In low-power jet engines, centrifugal compressors are often used, located in high pressure stages in front of the combustion chambers.

[0043] Fan stage: The fan rotor blades or actuator-drive disks are usually made of high-strength titanium or fiberglass (FRP), since the bladed structures for the fluid flow usually convert the torque of the low-pressure turbine stages to draft for the cold section, which bypasses an engine core for increasing traction of a hot section with a high traction gain of, for example, 5-10: 1. Fiberglass blades made, for example, of carbon fiber and epoxy resin or other resins (and even metal blades), are susceptible to erosion of the leading edge from rain, hail, sand or other absorbed small foreign damaging objects (FOD) and even carried by air volcanic ash, and are highly profiled in three-dimensional space (3D) to improve aerodynamic performance and laminar flows. For example, in a fan made of composite materials for a GE90 engine with a diameter of 123 inches / 3.1 m, which uses blades with a machined titanium having a complex volumetric shape buried in the leading edge and connected to it to provide protection against erosion and the ability to accept and withstand the effects of foreign damaging objects, such as, for example, birds.

[0044] The mating device between the strips of the erosion protection system at the leading edge and the rear composite structure is a point that inevitably contains small gaps that can expand due to vibration or stress induced edge destruction of the adhesive joint or erosion and then create the possibility of undesired passing by the swirl scale. Preferably, the flush front edge strip provides minimal erosion protection for the painted surface immediately behind the transition, which subsequently, during use, can bend and destabilize airflows and cause additional aerodynamic drag and energy loss.

[0045] All devices with a serrated aerodynamic surface or trailing edge of the body, such as those described for Gliebe '240, or Stephens' 291 in paragraph 13, also introduce stress concentration points on the tense and necessarily the thinnest trailing edge of the aerodynamic aeroelastic surface , which as a result can become places of fatigue initiation and propagation of cracks.

[0046] Noise and Large Vortex Destruction (LEBU): Mixing Cold / Hot Air Duct Flows: Young '319 describes many types of gear and similar volumetric devices for increasing flow mixing, breaking flow vortices, and therefore reducing flow velocity gradients, as well as mechanisms of noise in the jet exhaust hot gases. Balzer '106 describes chevron exhaust nozzle extensions that improve mixing of the exhaust gas flow to reduce engine noise. In the engine nacelle of a Boeing 787, the gear elements described in Balzer '106 are used to reduce engine noise, but the resulting flows do not act in the boundary layer pressed against the aerodynamic surface of the body, but on the boundary of the unperturbed flow between the cold fluid flow and the hot fluid flow so that these vortices are used in mixing the flow only to reduce the emitted noise from the acoustic spectra. Such a configuration is reported to reduce noise, but increase aerodynamic drag, which is expected for vortices that do not improve the relaminarization of the boundary layer flow, but simply induce a vortex momentum of the fluid flow and cause losses.

[0047] Flow channels in the engine core: Lutjen et al. Describe in US patent application No. 2011/0300342 a metal substrate that can be profiled to form a matrix of recesses or blind holes surrounded by raised vertical parts (walls), which then further modify mechanical embossing / deformation for the formation of overhanging protrusions, which are intended for subsequent mechanical closure, retention and stabilization of the known having a top layer of ceramic insulating coating. This design stems from known methods for “laying ceramic tiles” in small sections to capture and hold cracked sections of the heat insulating coating, so that splintering and loss of heat insulating coating is minimized.

[0048] For Lutjen '342, it is described that in its arrangement, the lower flat portion 50 of the recess is specially formed at right angles to the side wall 54 of the protrusion. This design has the disadvantage that the specified connection at a right angle (i.e., having a small radius of rounding or transition) of the loaded and vibrating mechanical sections forms a stress concentrator, which helps to reduce the fatigue life and forms a point for the beginning of potential cracking of the material. The above and various formed side walls with increased radii of the recess provide the opportunity to significantly increase the added local moment of inertia and form a stronger load-bearing beam expansion of the loaded surface, which also supports this surface and helps to minimize vibration and bending or deflection modes. Of course, enlarged flow control surfaces that are bent by simple or complex methods will resist applied pressure forces and inertial loads, as well as resist aeroelastic effects, but the presence of the side walls of the protrusion improves structural efficiency (overall strength in all measurements in relation to the total mass ), which is usable and discarded by Lutjen. The bending stress induced by vibration is undesirable for reliable fixing of the “tile” of the insulating coating.

[0049] Furthermore, as Lutjen describes, the formed projection retaining elements 28 and 28 'are typically at the thinnest point in the final shaped smooth heat-insulating coating (as shown in Lutjen's Figures 5 and 6) and thus bear the largest thermal loads transferred from above through the heat-insulating coating from hot gases. In this case, as described by Lutjen, the substantially straight side walls 54 of the recess do not provide minimal thermal resistance to the cooling fluid or the gas beneath them, unlike the base of the wall in the recess with an increased radius, and thus are not the optimal heat transfer configuration to maintain the metal areas of the protrusion (the top of the wall) at the highest temperature stresses, at the lowest possible temperature, at which the metal has maximum strength and minimal distortion ix / maximum creep resistance. Lutjen '342 describes that a protective heat-insulating coating is applied mainly to static sewer surfaces, but it is possible to apply this heat-insulating coating to other elements that require a protective heat-insulating coating, but Lutjen describes only thermal benefits, and does not describe the absolute properties of reducing the aerodynamic resistance of a surface or profile.

[0050] Wennerstrom in US Pat. No. 4,076,454 describes the addition of blade vortex generators to an inlet duct in an axial compressor. He does not describe and cannot declare a reduction in canalizing aerodynamic drag as a feature, and vortex generators are declared to help maintain unseparated fluid flows on blades located downstream without any advantage of reducing drag in an air duct or diffusers. Modification of the flow from a static rotary inlet air duct is described as the presence of vortices, which indirectly improve the stall characteristic downstream of the compressor rotor blades.

[0051] Gondola and mounting pylon: Inlet of a working fluid, i. E. gases into a modern turbofan engine, such as the CFM-56, mounted on a Boeing 737-600 airliner, is closed by a surrounding nacelle, and most of the nacelles act as the original internal deflecting duct or diffuser to slow the incoming fluid flow so that the fan section the first stage and the compressor stage could work without the ends of the cascade vanes becoming supersonic and generating high-loss supersonic or Mach shock waves. At a high angle of attack of the wing / nacelle, some of the initial internal deviating nacelle fluid flow may be separated from the inner walls of the nacelle, which is an undesirable condition, or some of the diffuser flow control used must be limited to prevent this condition, or an active suction control must be added to the inner surface of the duct to contain flow stalls in front of the fan blades. The air of the cold section, leaving the fan section, goes into a combination of diverging then converging ducts on the inner and outer surfaces of the duct, so that it can be exposed to flow factors such as Taylor-Goertler (TG) vortices on the concave sections. The intersection of the vortex traces of another aircraft can also cause problems with the sticking of an unstable flow and surging, etc., throughout the engine.

[0052] In modern engine nacelles of Boeing 737-600, Airbus 319 and C-17 airliners, large-sized vane or vane vortex generators are used located at a position of approximately 2 hours and / or 10 hours on the dial behind the outer front leading edge of the nacelle in order to so that the external fluid flows around the upper surfaces of the nacelle with a high angle of attack adhere to the surface and flow properly behind the mounting pylons, as well as under the rest of the wing and on top of the wing, as required for minimum destabilization of flow and losses due to turbulence. In flight at cruising speed, these vortex generators have a minimum angle of attack, since vortices are not required, so that they meet minimized profile drag, but always cause additional aerodynamic drag of the shape and wet surface of the skin. In general, this configuration is not a configuration with minimal aerodynamic drag to generate vortices to improve the interaction of the gondola / pylon / wing / fuselage flows.

[0053] The pylons connecting the nacelle to the engine represent another area of problems for the flow coupler and aerodynamic drag due to contact and side effects requiring the fairing to control fluid loss and aerodynamic drag. This applies to all attached external aerodynamic bodies and devices, for example, wings or fuselage, such as fuel tanks suspended on a pylon, fuel tanks mounted in wing end fairings or other transition devices or structures, such as VHF omnidirectional whip antennas a beacon in which the pitch and yaw of the aircraft, as well as the vortices of the secondary flows, can cause undesirable lifting forces, stall, dynamic instabilities and interactions current and wind resistance. These problems are also present in hydrodynamic examples, such as a hydrofoil with attached struts or rods, etc.

[0054] Leon, in US Pat. No. 5,156,362, describes a paddle-type displacement vortex generator for controlling the stall of an engine nacelle flow. The upper edge of the blade is conformal to the nacelle and the jet stream when the vortex generator is in the retracted position. In the active position, the surface of the vortex generator blade is at an angle to the flow and is not conformal to the surface of the nacelle, i.e., in cruise flight it induces aerodynamic drag, which is why a shifting and mechanically complex feature is used. The height of this blade vortex generator is a large number of thicknesses of the boundary layer and collects the maximum energy of the unperturbed fluid flow above the boundary layer to induce stable vortex effects in the released position.

SUMMARY OF THE INVENTION

[0055] An object of the present invention is to increase the energy efficiency and productivity of turbines, devices and methods by which a Newtonian fluid stream is introduced, processed using a conformal vortex generator based on a technology for changing a fluid stream, and then this fluid stream is released . Processing means adding or extracting energy or work from this Newtonian fluid stream, and / or deviating and modifying the velocities, pressures and / or momentum of the fluid stream. The task of the implementation options of the present invention is to create a new environmentally friendly built-in conformal vortex generator and reduce energy use and the associated emission of carbon dioxide. The technical result is to improve operational energy efficiency and / or expand the design range of regulation of the fluid flow.

[0056] In contrast to the state of the art, the new integrated conformal vortex generator uses an efficient circuit of a traditional vortex generator in a rotating lattice environment, which lowers aerodynamic drag, in particular, at low angles of attack. The effects of the integrated conformal vortex generator can be improved on aerodynamic surfaces or vanes to passively induce additional energy of the boundary layer fluid flow over the increased aerodynamic surface of the back of the suction surface to further delay separation by using a fluid stream collected from the injection surface or other fluid sources along flow control paths, which are then directed to a suction surface for improving the performance of stalling or separating the fluid stream.

[0057] Conformal vortex generators may be configured to improve output mixing of the fluid stream and reduce flow noise without inducing added aerodynamic drag and energy loss. The engine nacelle, pylons, and other aerodynamic mating devices and fuselage surfaces are an area in which the reduction in aerodynamic drag and advanced flow control methods also provide the advantage of a new conformal vortex generator.

[0058] Centrifugal compressors, as well as smooth mixed-flow impellers and diffusers, fluid pumps, turbochargers, and the like, provide an advantage by controlling the boundary layer flow, which minimizes fluid flow separations by using a new integrated conformal vortex generator, which reduces the aerodynamic resistance of the fluid flow, stall / cavitation and acoustic noise generated on the impeller and diffuser blades and related structures controlling eye fluid.

[0059] The present disclosure describes improvements in flow sewerage and, for example, S-shaped ducts of an engine, which are an actual case of general Newtonian fluid flows in a pipe or other type of channel for a fluid flow or surface restriction means (both for internal and and external flows), which provide the possibility of implementing flow control methods by means of a conformal vortex generator for use on walls, surfaces, in pipelines, ducts, and any structures flow control applications currently used for known surfaces controlling fluid flow.

[0060] New conformal vortex generator designs generate constant vortices without significant energy-consuming transverse flow patterns and transfer maximum and selectable flow energy to vortices, which tend to convect to downstream fluid flow surfaces that prevent flow stall. This provides an excellent way to advantageously change any surface and boundary layer of fluid flows to provide stall resistance, lower absolute aerodynamic drag and maintain this reduced aerodynamic drag when operating in non-separated flow modes and / or situations deviating from design conditions. The basic design of the integrated conformal vortex generator demonstrates these properties, and being integrated in engines or devices and surfaces for controlling fluid flow, can be implemented with the possibility of significant improvement of the prior art in numerous applications and implementations.

BRIEF DESCRIPTION OF THE DRAWINGS

[0061] All of the drawings are not necessarily scaled, but show in detail many additional features of the embodiments for illustrative purposes.

[0062] FIG. 1a shows a portion of the stator of a low pressure turbine or rotor blade with an integrated integrated conformal eddy generator. In FIG. 1b shows a view of the discharge surface of a low-pressure turbine with details of an integrated conformal vortex generator, and FIG. 1c shows a view of a suction or top surface, including additional conformal eddy generators embedded in the edge of the blade and secondary conformal eddy generators.

[0063] FIG. 2a shows the details of another example of a low pressure turbine stator or rotor blade with an integrated integrated conformal vortex generator, with a root end cut, showing one example of an embodiment of the optional addition of nozzles controlling the expanded fluid flow from the suction surface and grooves for expanding the vortex formed by the stage. In FIG. 2b shows an additional intake channel (s) of a fluid source for a control nozzle that draws fluid from a minimum point of a conformal vortex generator embedded in the discharge surface and / or collection points in the region of the blade end. In FIG. 2c shows a sectional view of the backward-facing step of a conformal vortex generator integrated in an inclined suction surface with details of air flows.

[0064] FIG. Figure 3 shows the stator or rotor blade of a low-pressure turbine with cowl cowl fairings and also shows the modified, cropped, doubled and peak ends of the conformal vortex generator, along with asymmetric and expanded configurations of the stage of the conformal vortex generator, as well as the conformal vortex generators embedded in the end wall of the profile.

[0065] FIG. 4a shows an example of a portion of the suction surface of a stator or rotor blade of a low pressure compressor (LPC) with cut-in built-in conformal vortex generators with a section showing embodiments of elements for additional jet flow control. In FIG. 4b shows a portion of the discharge surface of the stator or rotor vanes of a low-pressure compressor with an additional intake channel (s) of the fluid source for the control nozzle that draws fluid from the minimum point of the conformal vortex generator integrated into the discharge surface and / or from the sampling points in the tip region. In FIG. 4b also shows a pointed version of a conformal vortex generator matrix embedded in the discharge surface, with different pitch and offsets from the conformal vortex generator matrix on the suction surface.

[0066] FIG. 5a shows an example of a suction surface of a fan blade with a metal strip for erosion protection of the leading edge and an additional end elastomeric lifting force-improving trimmer (eLET) to reduce the load on the blade end. In FIG. 5b shows an example of a blower fan surface with additional built-in conformal eddy generators, elastomeric lift-enhancing trimmers (eLET's), end conformal eddy generators, as well as an example configuration for additional jet flow control.

[0067] FIG. 6a shows an example of a portion of the suction surface of a cooled stator or rotor blade of a high pressure turbine with an integrated integral conformal vortex generator, further showing flow control and cooling nozzles and a secondary matrix of the conformal vortex generator. In FIG. 6b shows the injection surface of the stator or rotor of the high-pressure turbine and the matrix of the integrated conformal vortex generator, as well as additional flow control and cooling nozzles, the matrix of the secondary conformal vortex generator, the matrix of pin cooling outlet slots of the trailing edge and the matrix of trimmers that improve the cooling of the trailing edge.

[0068] FIG. 7 shows a centrifugal impeller and an additional diffuser vane with a built-in conformal vortex generator on flow control surfaces.

[0069] FIG. 8 shows an engine nacelle, a pylon and a wing arrangement showing places where conformal eddy generators can be installed to increase energy efficiency.

[0070] FIG. 9a and 9b show examples of a fluid flow duct with conformal vortex generator matrices added to improve flow and increase energy efficiency.

[0071] FIG. 10a shows the steps of the integrated conformal vortex generator and the ribs extruded into the panel of the duct surface and optimized using the integrated polygonal structures shown “inside the surface”. These polygons are equipped and reinforced with ribbed bases with a larger radius (non-rectangular) to provide bending strength and increased thermal conductivity for internal cooling flows with a minimum material weight, the opposite side of this panel containing a matrix of steps of the resulting conformal vortex generator (not shown) operating in an external fluid stream similar to a conformal vortex generator matrix embedded in the heat insulating coating shown in FIG. 10b.

[0072] FIG. 10b shows an alternative version of the surface of the duct (or vanes) shown in FIG. 10a, with an additional heat-insulating coating applied and integrated into the polygonal matrix, with fluid flows now flowing along this side of the heat-insulating coating. Also shown are nozzles that improve film cooling and adhesion of the boundary layer flow.

[0073] FIG. 11a shows a sectional view of a combustion chamber structure using conformal vortex generators to reduce aerodynamic drag and energy loss, and improve fuel injection and mixing. In FIG. 11b, an alternative embodiment is shown in which, as an option, a ceramic body, walls and a conformal vortex generator matrix are used to limit the volume of the opening for combustion of the enriched mixture.

DETAILED DESCRIPTION OF THE INVENTION

[0074] The best embodiment of the present invention is an example of a turbofan jet engine that covers many typical fields and applications that can provide an advantage by using a properly configured integrated conformal vortex generator (CVG). The turbofan engine provides a very large number of examples for integrated conformal vortex generators (CVGs) suitable for use in various applications, since it contains numerous hydrodynamic surfaces that control Newtonian fluid flows to perform useful work and generate usable effects. This example is just one form of a gas-and-gas dynamic machine in which gas is used as a working fluid, but most of the applications for a conformal vortex generator can simply be adapted to many useful devices that use a liquid phase or a mixed phase of Newtonian physical fluids, and can provide such improvements, for example, to reduce aerodynamic drag and separation / cavitation by geometric scaling to calculate Ia: velocity, pressure, Reynolds, fluid phase (the transitions between the states of gas-liquid) flows and viscosities.

[0075] FIG. 1a, reference numeral 1 denotes the shank of a stylized example of an insulated “basket” of a rotor or stator blade of a low pressure turbine (LPT) with an asymmetric profile for reaction and momentum and diffuser action, which are usually cascaded around the circumference of the rotor or stator disk. For simplicity of presentation, this example does not have twisting and / or narrowing, as in a typical blade, to provide: a radial profile of the rate of constant reaction from combinations of rotor wings (reaction) and stator (diffuser), as well as additional flow control. The blade shank attachments, the sleeve and end faces, and adjacent overlapping vanes and upstream drive disks are also omitted for clarity, but are used in the final structure, as is known to those skilled in the art of cascade aerodynamics. Position number 2 denotes the convex surface of the rarefaction zone located downstream, and the concave working surface located downstream of the stream is indicated by position number 3. Fluid or hot gases arrive at the calculated input angle of the blade, which defines the local aerodynamic surface or working angle surface attack, and the flow is divided above the surface of the rarefaction zone and under the working surface due to the geometry and hydro-gas-dynamic forces acting on the line of 4 critical points n front edge. For the case of the rotor disk, after performing work on the wings of the blade and generating force vectors (towards the side of the rarefaction zone), the working fluid comes out at a calculated exit angle in the region of the trailing edge 5 (TE). The lifting forces of the blade, which are decomposed into the tangential components acting around the axis of the turbine rotor, generate the output torque from the energy of the fluid input stream, and the decomposed vector component acting in the rear axial direction is the aerodynamic drag or harmful loss of energy and momentum, which causes an additional pressure drop on the cascade section.

[0076] The estimated input angle for the upstream fluid input source and the output angles for delivering the output fluid after processing with the conformal vortex generator determine the peak amount of energy that can be extracted from the fluid input from the fluid source in the cascade section, under the assumption that the flow in this section is configured to minimize energy losses caused by its turbulence, compartments, and viscous losses at a given operating point.

[0077] Under certain flow conditions, for example, at low Reynolds numbers deviating from the optimal values, in the rarefaction zones, the flow separates after the minimum pressure region, resulting in increased cascade losses, decreased efficiency and increased specific fuel consumption of the engine. The fluid stress due to centripetal acceleration during the intersection of the concave working surface 3 can also cause energy loss and thickening of the boundary layer, for example, the formation of Taylor-Görtler vortices. Cooling is usually not required for low-pressure turbine blades, since the gas flow is significantly cooled when passing through the turbine sections of the high-pressure turbine, and therefore the temperatures are lower than, for example, the temperatures of the materials of the blades made of heavy-duty nickel alloy, which can be used without concern.

[0078] To facilitate the improvement of flows in the rarefaction zone, it is preferable to resume the energy supply in the flow lines in the boundary layer (BL) so that they have sufficient momentum to flow close to the blade into the region with an undesirable pressure selection gradient after the line 10 of the rarefaction peak when the deceleration of the mass flow of the fluid flowing along the local surface begins due to the flow state. To provide increased flow energy in the lowest layers downstream of the boundary layer in the rarefaction zone, the specified matrix 6 of the upper conformal vortex generator (CVG) is designed and manufactured as inextricably integrated or integrated into the front of the rarefaction zone in accelerated flow regions, and this design is designed with the possibility of converting the fraction of energy of the accelerated incoming free fluid flow into a pair of vortices intensively rotating in opposite directions, which flow back from the matrix of the upper ends 7 of the conformal vortex generator, and this can provide control of the separation of the rarefaction zone, like a traditional vortex generator, which in fact cannot be used in this environment of complex flows and reduced geometric shapes.

[0079] The minimum point 8 of the integrated upper conformal vortex generator is located along the chord, so that the incoming fluid flow in the rarefaction zone entrance region 9 intersects a pair of deflected inclined backward stepped edges 24 and experiences their action, as shown in FIG. 2a. This high-speed flow still remains parallel or tangential to the inlet surface of the blade or, according to the design concept, the aerodynamic surface in the region 9 of the entrance of the flow into the rarefaction zone and experiences separation (in the region 27 of the stepwise cutting separation, as shown in section in Fig. 2c) the lower layers of the fluid flow along the entire length and behind the intersecting upper edge of the steps, since the flow cannot make a sharp turn down and follow the contour of the edge of the upper stage.

[0080] This specific inclined step-lowering mechanism for separating the flow begins to twist part of the separated low-energy and lowest in the boundary layer of the incoming mass of the fluid flow into a coupled and free-flowing step vortex 25, as shown in FIG. 2c, which moves and flows along the lower edge of the step and back towards the tips 7 of the upper conformal vortex generator. Then, the indicated step vortex, consisting of cut off or layer-by-layer cut off low-energy inflowing incoming fluid layers, meets and balances with the vortex rotating in the opposite direction on the other side of the tip, and then they move backward in the opposite directions of the rotating vortex pairs connected with the surface along the chord of the blade. The incoming uncut impulse flow layer and the upper layer, which is not completely twisted into step vortices, continues to move backward as the emerging high-energy flow 23 on top and past the upper part of the structures forming the step vortex, and then together with the initial descending velocity component again approaches lower along the flow to the surface of the blade in the region 28 of the re-convergence of the flow after exiting the step structure (as shown in Fig. 2) in the form of a now more high-energy and its thin boundary layer with reduced transitional turbulence, hairpin-like vortex structures and loss of aerodynamic drag in this region of the boundary layer along the flow between the ends of the conformal vortex generator. Thus, the geometric shape of the stage of the conformal vortex generator acts on the boundary layer as a “slicer” to create useful vortices, but also provides controlled relaminarization of the boundary layer downstream in the step width region between the tips to reduce drag over the unmodified surface of the blade, in particular at zero and small positive and negative angles of attack.

[0081] The described construction is an additional drag reduction mechanism that is not available in traditional vortex generators, since it is known that they increase aerodynamic drag at zero and small positive and negative values of the angle of attack, at which the ability of the vortex generator to expand the angle of attack does not work. The diagram 33 of the flow velocity vector of the boundary layer in the inlet region shows the normal gradient of the boundary layer from a low surface velocity with a rise above the boundary layer. Scheme 34 of the velocity vector of the output stream of the boundary layer below the stage downstream shows that these lower boundary layers have a higher speed and improved ability to approach the lowest layers of the entrance region, separated into jets in a step vortex and then passed through the vortex pairs of the ends of the conformal vortex generator. The speed of the imaginary upper jet of the boundary layer or unperturbed jet is designated as Vtop.

[0082] The vortex 25 formed by the step of the conformal vortex generator flows back in the form of a continuous predictable and controlled flow along a curved path having an optimal length and angle for mass accumulation, in contrast to a trapped chaotic vortex formed, for example, by a long, long-facing backward-facing wing span step. The pairs of primary end vortices formed by the vortex-forming tips of the conformal vortex generator are very intense and geometrically stable; they efficiently select the energy of the flow, as well as the mass and momentum of the fluid, from entire regions of wide flow bands having a transverse velocity gradient that extend above the steps or intersect the steps of the conformal vortex generator along its width. The jets of the twin end vortices of the conformal vortex generator also act as a traditional vortex generator at large angles of attack, at which they affect the surrounding boundary layer downstream and can break any bubbles and stream structures formed as a result of the separation of the fluid flow, and also provide the possibility of a significant increase in the angle of attack of stall from the blade by about + 5 ° depending on the design of the aerodynamic surface. The regions adjacent to the boundary layer are affected by the passage of energetic jets of the end vortices of the conformal vortex generator, and the additional energy of the fluid flow also tends to suppress hairpin vortices and thicken the region adjacent to the boundary layer. Thus, a conformal vortex generator increases the angle of attack or the surface control range of the local fluid flow, which can be processed with reduced energy loss depending on the basic surface configuration.

[0083] It should be noted that, to the point of separation, this innovative blade surface design has a “normal or ideal” geometric surface design that provides an effective inlet region for the fluid flow so that it does not induce added aerodynamic drag or horseshoe vortices in front of the steps . Vortex generators of beveled, wheeler or blade types must generate vortices in this area to deviate from the correct or ideal shape of the blade and inefficiently add extra distance to the path of the upper flow of the boundary layer, creating aerodynamic drag.

[0084] Since the integrated elements or matrices of the conformal vortex generator effectively define the new constructive base desired surface of the leading edge entry region or the constructive geometric shape of the aerodynamic surface as equal to the ideal aerodynamic surface, behind the step, the rear surface structure is now effectively stepped into the surface thanks to this new built-in conformal design vortex generator. Thus, the newly designed wing or aerodynamic surface remains a means of setting the correct fluid flows in critical sections of the leading edge of the laminar flow, as in the original design of the aerodynamic surface, so that now the rear sections are upwardly deposited inward. Since the additional conformal vortex generators on the wing or aerodynamic surface structures are not configured or configured to add a conformal vortex generator, the section of the leading edge inlet region is effectively thickened and interrupted, for example, by the doubled additional thickness of the ribbon / step of the matrix of conformal vortex generators in the applied region.

[0085] Conformal vortex generators are unique in that they act orientedly and process the lowest boundary layers intersecting backward-facing steps (of any height) and generate constant main jets of end vortices along the chord, which are closely connected in their central mutual line of low-pressure critical points along the chord and, thus, remain in close contact with the surfaces of the scapula downstream even with extremely high centripetal accelerations and secondary flows above the boundary levels th layer.

[0086] The visualization of the flow shows that on a helicopter rotor blade with radial accelerations of the end of the blade 1200 g (11760 m / s ² ) and speeds of 700 ft / s (213.5 m / s), at which the lines of critical points of the vortex pair of conformal ends vortex generator capture surface dust and effectively “enclose” this and the lowest flows of the boundary layer, leaving them in the direction of the chord on the blade, under the influence of large radial forces and other secondary air flows that completely remove dust from the blades without using the proposed innovative conformal vortex generator. This distribution of a strong stepwise and vortex directed along the chord flow explains how a conformal vortex generator can efficiently take energy from higher incoming momentum-containing fluid flow layers and distribute it along the chord and along the blade profile, as well as facilitate the control of any posterior regions (i.e. e., passing towards the trailing edge 5), which tend to form a bubble separating the flow and stall. The main pairs of end vortices of the conformal vortex generator and step vortices have a certain number of secondary vortices and circular flows connected in them, which tend to progressively equalize pressures and momenta, so that flows with a transverse velocity gradient are minimized in the design of the conformal vortex generator and steps and behind them.

[0087] Dust accumulations along the steps of the conformal vortex generator indicate that the surfaces and bases of the steps are also areas of inhibition, and that after the fraction of the lowest level and low-momentum boundary layer flux is divided into flows that feed the pairs of primary end vortices , the remaining upper layers with higher energy and higher momentum, the layers can subsequently find the effective flow path slightly lower along the flow to restore convergence with the surface as new of having a higher energy flowing downstream the boundary layer trapped between the ends of the conformal vortex generator. It should be noted that the pairs of primary vortices of the conformal vortex generator can be made smaller and go beyond the range of the geometric dimensions of the step and the thickness of the boundary layer, and usually do not affect the undisturbed flow or secondary flows flowing above the upper part of the imaginary boundary layer. This makes it possible to completely immerse the vortices of the conformal vortex generator in the lowest levels of the boundary layer, and the indicated vortices of the conformal vortex generator are at least an order of magnitude more constant and effective with respect to the direction geometry downstream than the vortices generated by other mechanisms, according to reports, for example NASA. Between the elements of the conformal vortex generator in the matrix there are no horseshoe-shaped vortices of the input stream that generate losses.

[0088] Most of the other designs of vortex generators have high aerodynamic drag (for example, protruding stabilizers of inclined types), are structurally fragile (blade stabilizers), are limited by their geometrical shape in a limited range of Reynolds flow operating conditions, and they do not generate constant and submerged vortices or produce low-energy eddies (e.g. funnels) or eddies susceptible to secondary flows and influences. Known active devices for controlling the flow on the blades, such as nozzles for inclined and synthetic flows, can renew the energy supply to the boundary layer to reduce separation of the flow, but at the same time cause energy losses by inducing horseshoe or renal vortices and affect flows only in a limited range around fixed points and in general are more complex and do not provide a significant reduction in drag compared to the main unmodified geometric shape Oh.

[0089] The renewal of energy supply in the boundary layer region behind the conformal vortex generators provides the possibility of expanding the angle of attack (AoA) of the blade without stall (with a small frontal resistance) by approximately + 5 ° until the final formation of the regions of stall flow and an increase in aerodynamic drag while reducing lift . This advanced expansion of the A-angle of attack, occurring on various test aerodynamic surfaces, proves that the physics of fluid flow scales well for various geometrical shapes of the blade and Reynolds numbers. Such an improvement for low pressure turbine blades makes it possible to increase the estimated angle of rotation of the new design of the cascade of blades (increase the Zweifel coefficient) for the construction of a more compact turbine and / or compressor with a reduced number of stages in the blade grid, or this improvement can be used simply to allow expansion operational freedom of action with respect to new blade grids operating with a deviation from the design modes, or for a preferred combination of these features.

[0090] An additional valuable feature of the conformal vortex generator, which is new relative to the prior art, is that the drag of the blade compared to the original structures is significantly reduced by about -5% to -10% for the same lift and angle of attack from zero angle to a stall close to the corner. This is attributed to the fact that the boundary layer of the rarefaction zone with renewed energy supply also has a higher speed and becomes thinner and, therefore, generates less losses caused by turbulence in the fluid flow, while generating a lifting force. The vortices of the conformal vortex generator matrix and the increase in the energy of the boundary layer are passive and are generated in an extremely efficient way, and also do not adversely affect the design characteristics of the drag of the blade, but improve them by reducing them in the fluid flow range.

[0091] Regarding the integrated lower conformal vortex generator matrix 11, an example of a minimum point 12 of the lower conformal vortex generator is shown, the lower conformal vortex generator also having steps recessed into the profile of the aerodynamic surface of the blade to form an inclined backward step in the same manner as the matrix 6 upper conformal vortex generator. The working surface has different pressure and velocity profile along the chord, but the lower point 12 of the minimum of the conformal vortex generator is configured in the same way as the point 8 of the minimum of the upper conformal vortex generator, for example, in the matrix 6 of the upper conformal vortex generator.

[0092] Testing on aerodynamic surfaces shows that some improvement in the drag of the blade also occurs due to the inclusion of the matrix 11 of the lower conformal vortex generator, which improves flow along the working aerodynamic surface and prevents the formation of, for example, Taylor-Goertler vortices caused by stresses created by concave centripetal flows . The lower matrix 11 of the conformal vortex generator also contributes to the thinning of the boundary layer of the working surface downstream, as a result of which turbulence is reduced and aerodynamic drag is reduced.

[0093] It is possible to design a blade for working with either of the matrices or with both of the conformal vortex generator matrices, but the conformal vortex generator matrix in the rarefaction zone eliminates one of the main recognized problems of the prior art relating to the separation of the flow in the rarefaction zone of the low pressure turbine blade.

[0094] In the blade array, a shock wave, for example, caused by a pressure recovery stream in the rarefaction zone can form and destroy the interscapular passage flows, in particular, if the structural thickness of the trailing edge of the blade induces a throttling of the flow in the interscapular passage and causes the resultant compaction jumps in some fluid flows Wednesday. Scheduled eddy flows of a conformal vortex generator that collide with the interactions of the shock wave with the boundary layer (SBLI) in the areas of separation of the shock wave having a lambda foot can be used to soften shock loads and reduce energy losses on aerodynamic surfaces, as well as on surfaces that control fluid flow and in ducts.

[0095] The advantages of the configuration and construction of efficient conformal vortex generators are reinforced by the fact that they work well in a wide range of geometric shapes and can be easily modified to meet specialized requirements. The test shows that when the geometric shapes of the conformal vortex generator change, the results generally remain within the uniform range of changes without sharp fluctuations or singular points, i.e. they behave well in a wide range of design conditions. Since conformal vortex generators always begin at the base of the boundary layer, they do not invade the boundary layer from the outside for any practical Reynolds number.

[0096] The vortex begins with Reynolds numbers of approximately 300 in a standard atmosphere and acquires sufficient energy at approximately 30,000 preferably. Roughly from Reynolds numbers of 30,000 to 500,000 or more, at which the low pressure turbine blades can still work, conformal vortex generators can be tuned to provide improvement. From Reynolds numbers 500,000 to, for example, 10 million or more conformal vortex generators can be very effective for an isolated aerodynamic surface and fuselage sections, as well as aerodynamic structures, including rotating components. It should be noted that the steps of the conformal vortex generator can make up a reduced fraction of the height of the boundary layer in the working section and still create an effective and advantageous ability to control the fluid flow, but in the more general case and at various operating points of the Reynolds numbers, they can also be advantageously used with height steps, making up an increased proportion of the thickness of the boundary layer or even several times greater than the local thickness of the boundary layer.

[0097] A conformal vortex generator or CVG in a broad sense can be represented as a fluid flow changing element, the construction of which has the following distinctive features: (a) has a low-loss inlet region configuration that matches the directions of the surface stream jets in the inlet region; (b) comprises a backward flow intersecting flow at an angle to induce cutting of the lowest levels of the incoming fluid flow into a step vortex that connects this cut flow along the exit surface to (c) an exit point to remove the accumulated stepwise vortex shear flow, and (d ) provides the ability to balance incoming high-energy uncut recovery layers as a new boundary layer downstream with a higher energy.

[0098] Conformal vortex generator steps angled to the flow are typically configured at approximately an angle of 22 ° (for air as a working Newtonian fluid) along the wing span relative to the local vortex-free inlet vector, but may be within the tolerance range around this approximate nominal value with some shifts of characteristics, and the exact value of this angle depends on the conditions of the working fluid. Thus, any of the angles of the conformal vortex generator stage can be tuned for optimization for various local flow directions, such as flow directions in the areas of the hub and the tips of the blades, etc.

[0099] The steps of the conformal vortex generator with their rear ends are usually connected in chevron or triangle-like designs with the ends facing back, which then produce constant and stable pairs of output end vortices and which can be combined into matrices with a variable displacement of a certain number of adjacent stepped edge structures of the conformal vortex generator with changing angles, geometric shapes of the step, as well as step heights and step lengths to ensure changes in vectors and conditions input stream. The geometric shape of the conformal vortex generator design allows precise control of fluid flows at various points along the surface into which the vortex generator is integrated. A conformal vortex generator is configured for a given geometric surface shape with, for example, step height, length and angle, and, for example, for a chord of a turbine blade of a low pressure turbine with a width of 50 mm, for example, the following can be selected: intersection of the fluid flow at a local angle of about 22 °, triangular shape, step length 3 mm, step height 100 μm (microns) and location around high-speed transition regions of laminar flow for the expected values of the Reynolds number and a typical section of the aerodynamic surface of the blades and.

[00100] These values of the geometrical start point can be easily changed and then confirmed as optimal by the sequence of actual testing of the blade stage and measurement of characteristics, but it is practically impossible to add conformal vortex generators in this area of the low pressure turbine due to its small size and operating loads. The stage height of the conformal vortex generator is adjustable in a wide range and is capable of generating sufficient vorticity along the stepped edges in the calculated operating range of the Reynolds number with a simultaneous deviation to a noticeable level of the incoming lower flow of the boundary layer into the primary vortices directed along the chord. This method of constructing a conformal vortex generator can also preferably be used on a matrix of fixed stator vanes to reduce aerodynamic drag and increase the angle of rotation within limits limited by separation with deviation from the calculated value at various Reynolds numbers.

[00101] A wing span step that extends along a aerodynamic surface at a right angle or angle of 90 ° to the flow typically captures a chaotic span vortex formed by the wing and is known to increase aerodynamic drag by approximately + 5% for the base unmodified blade , and in the best case, this step is divided, for example, into segments of the conformal vortex generator, which are located at an angle of approximately 22 ° to the flow, with an approximate decrease in drag -10%, but not limited to these values. Interestingly, the tests show the most degraded aerodynamic drag for an angle greater than 90 ° (in the case of a linear backward edged edge), when the conformal vortex generator step extends at an angle of approximately 60 ° to the flow and the accumulation length of the step is large. This shows that at some point the step vortices are overexcited due to the accumulated mass of low-energy fluid at a certain size of the vortex formed by the step and the flow rate and begin to expand, becoming an obstacle to the jets of the incoming flow, and, thus, the mechanism of the conformal vortex generator becomes an undesirable cause of an increase in aerodynamic resistance to an even greater degree than a linear span wing located backward. Despite the fact that lowering the aerodynamic drag is a key design goal, the ability to create a quantitatively controlled increase and decrease in aerodynamic drag makes it possible to use conformal vortex generators as a new tool for modifying fluid flow in more precise ways.

[00102] The mechanical accuracy and manufacturing accuracy and the determination of conformal vortex generator designs are not particularly critical, but the sharper the upper edge of the step (the smaller the rounding radius of the angle), the greater the stability and predictability of the separation of flows in the inlet region and the lower the secondary turbulence. The minimum point of the conformal vortex generator can also be easily configured with a certain fillet radius, and the ends of the conformal vortex generator can be either sharp or can also be configured with some fillet radius or have a different geometric shape with minimal sensitivity. The transition from the base of the step to the exit surface is a critical region creating other vortices of secondary voltage, so that a flow around with a convenient radius can be specified that does not violate the shearing function of the upper edge of the step.

[00103] Since the molded, stamped, made manually or mechanically part can be formed as a result of any combination of processing methods, materials or manufacturing methods, preferably the radius of the lower edges of the step should contribute to both reducing stresses in the manufacture and minimizing concentrated vibrational stresses and modes during operation. The upper edge of the step is usually free of isotropic bulk stress and deflection lines.

[00104] Under conditions of high acceleration and / or vibration, the arrangement of conformal vortex generators can be optimized in which they are spatially configured on the same and opposite surfaces to prevent resonant vibrational modes, as well as points and structures of coherent reflection. Thus, a regular matrix on the surface can be optimized by adjusting the individual element of the conformal vortex generator, the position of the tip and the minimum point, the length of the step of the conformal vortex generator (effectively setting pitch) and angles in an individual way to upset the resonant vibration of the blade and reduce unwanted bending of the blade, as well related modes of excitation of vibration and mechanical resonance. This can also be done with respect to both surfaces of the blade in order to prevent a coherent concentration of the blade stress between the rarefaction zone and the discharge zone, and also to prevent fatigue failure.

[00105] In FIG. Figure 3 shows an example of an asymmetric conformal vortex generator 21 located in the rarefaction zone and having a V-shape, the left corner being sharper than the right corner to make this conformal vortex generator asymmetric and able to process the boundary layer flows from each side of the tip in various ways. The mass flow of the boundary layer on the left side is effectively narrower, so that the mass of the boundary layer separated by a step into the stripes flowing into the left-side end vortex is smaller, as a result of which a smaller and less powerful left-side end vortex is generated. On the right side of this conformal vortex generator, a wider intersection of the oncoming flow means that the right-hand end vortex, respectively, has an increased size and is more powerful. The balance of forces and vorticity vectors and the difference in power between the indicated two asymmetric end vortices rotating in opposite directions are now changed so that they flow more on the left side of the rarefaction zone, and since they disperse into the vortex wake after the trailing edge, the balance of the residual vortex values in this area it is more shifted in a clockwise direction, which corresponds to the clockwise direction of "or polarity" of the sum of the normal normal lifting forces of the vortex of the vanes weave, as shown in FIG. 3, assuming that in FIG. 3 shows the inner or root end of the scapula in region 1. Depending on the final configurations of the residual vorticity, it is possible to influence the coefficient C _{L of} the lifting force directed up or down by the body. For this configuration, if the conformal eddy generator integrated in the working surface changes in the opposite direction (i.e., the left-hand conformal eddy generator becomes wider when viewed from the vertex side), this also introduces a positive effective contribution of the lifting eddy force to the eddy wake caused by circulation and increases the coefficient C _L. It should be noted that the decrease in drag due to relaminarization of the boundary layer of the conformal vortex generator changes due to reduced shifts in the location of the vortex, but still remains effective between the ends of the conformal vortex generator, since the mass flows into which the resumed mass flows are essentially the same energy supply arise in the boundary layer. The passage of altered pairs of end vortices affects the flow vorticity generated directly in neighboring thickening regions of the boundary layer and, thus, changes the vorticity with lift, summed over these regions.

[00106] In FIG. 1c shows an enlarged view of a detail of a conformal vortex generator assembly. The triangle with vertices A, B, C shown in the drawing is one example of a conformal vortex generator having a V-shape, which acts as a single device for cutting an incoming boundary layer of width AB, moving the cut-off lower fluid mass of the boundary layer back along both steps A-C and B-C and pushing this mass in the form of double vortices flowing back from the tip C. If conformal vortex generators are used as an additional device, for example, in a protection system If you are from erosion of the leading edge of the helicopter blade, then the minimum suitable element of the conformal vortex generator may be a section of the conformal vortex generator with a width of AB and may include conformal vortex generators located in the rarefaction zone and in the working surface, permanently attached around the leading edge section, which can be used as a combined matrix of the set of the indicated main structures of the conformal vortex generator. For technological purposes, conformal vortex generators are usually produced in matrices of a plurality of combined sections of the ends of the conformal vortex generator, which can be mounted side by side on the aerodynamic body to change flows. Appropriately reduced gaps between the installed elements of the conformal vortex generator have minimal effects compared to the efficiency of the conformal vortex generator and performance improvements. In addition, these enlarged matrices of conformal vortex generators are made convenient for handling them, as well as their application and incorporation into them of leveling features and layers that will indicate wear, as they are abraded in the fluid flows.

[00107] In FIG. 1a, the individual elements of the conformal vortex generator are shown to be exceptionally triangular, but this example is provided only for ease of presentation, and in fact improved performance can be obtained using the substantially pointed shape of the step edges, such as that used in NACA for recessed low-loss air intakes. These NACA air intakes also produce edge vortices that slow down the input flows, but have slightly different geometric shapes and are not mounted in matrices to reduce the profile resistance or resume the energy supply to the boundary layer, and also have step heights many times greater than the depth of the local boundary layer. so that they are completely different from the proposed new integrated conformal vortex generator, except that it uses vortices and geometric shapes, optimizing nnye from the viewpoint of fluid dynamics stream.

[00108] The pointed shape of the conformal vortex generator differs from the triangular shape of the stepped lines when approaching the tips due to the typical continuation of the location located slightly upstream and a sharper angle compared to the line of the triangular step. This shape increases the length of the surface accessible upstream of the stream, accumulating a vortex formed by a step, limited by this location-defining backward-facing step. The mass of the incoming stripped fluid stream accumulates along the entire inclined stage, so that the rear sections include a large mass and tend to increase the size of the vortex and increase the speed, and also tend to increase ingrowth into the incoming fluid flows. If the vortex formed by the step grows much from the sheared mass of the fluid, in these local areas it will tend to act on the iridescent uncut steps formed by the step, which subject this primary structure 25 to the vortex formed by the step of the vortex and tend to lengthen the outer layers of the vortex formed by the step or to an undesirable splitting of a vortex formed by a step into several components. The vortex 25 formed by the step, shown in section in FIG. 2c, causes a slight upward expansion, emphasizing the influence of this local vortex exceeding the height of the step and the size of its geometric shape.

[00109] This means that, according to some of the embodiments, it is preferable to additionally provide a profiled groove 13 for expanding the vortex formed by the step in an optimal place below any of the paths formed by the vortex step to accommodate the specified expansion of the vortex formed by the step due to the accumulation of mass of fluid. This design avoids unnecessarily bulging outward the growing diameter of the vortex formed by the step, creating an obstacle for uncut iridescent flows and causing loss of energy of these flows, which again approach the surface as a new boundary layer downstream for a given step height. At the ends of the conformal vortex generator, these expanding grooves (or any profiled grooves) can merge or pass parallel in the direction from the steps and can be continued to some extent in the direction of the flow in the form of groove 14 to continue the end vortex and create a guide for the flow pairs of end vortices to reduce deformation of higher fluid flows. This improvement for expanding the vortex allows the stage with a given height to share the increased mass of incoming fluid flows, thereby providing the possibility of more intensive reenergization of the boundary layer and end vortices downstream. Regarding the aerodynamic surface or the aero / hydrodynamic surface, the structural effects of the indicated material removals are taken into account, but in many cases the fabrication of volumetric surface structures, for example by stamping, can improve sectional inertial cross-section, stiffness and surface mechanical properties. The vortex formed by the step 25 has a certain number of secondary flow structures and vortices, such as the upper vortex structure 30 formed by the step and the vortices 32 formed by the step, which equalize the shear, which act to equalize the inertial and shear forces.

[00110] Adding an additional stepwise cutting guide section 35 as an optimally formed and enlarged rib provides the possibility of additional suppression of the equalizing cutting vortices 32 formed by the step and reducing flow losses from vortices or secondary vortices, and also facilitates defining a spatial cutting edge for the backward extension of the step formed vortex 25 in conditions with a changing Reynolds number.

[00111] According to other embodiments of the conformal vortex generator, interchangeable additive material of a system can be used to protect the conformal vortex generator from erosion, such as an elastomer, plastic, resin, metal, metal film, ceramic-coated substrate, carbon fiber, carbon-carbon, silicon carbide or metal fiber matrix or ceramic matrix composite (CMC), or other combination of materials, made of a composite or fiberglass material, or metal of a helicopter rotor blade or wing leading edge, etc., wherein expansion grooves 13 and 14 can be molded or embedded into the aerodynamic surface or body surface in the steps of a conformal vortex generator located in any zone, for example, a vacuum zone or working zone, along with registration marks of the conformal vortex generator and steps of partial heights. Then, a filler film of the system for protection against erosion of the conformal vortex generator on top of the built-in elements of the conformal vortex generator described above to create combined features of the stage and the functional means of the conformal vortex generator can then be added to the mechanical register. A fiberglass (composite) surface or, for example, a metal rotor blade or a leading edge of a wing aerodynamic surface / a leading edge of a fixed aerodynamic surface can have these new features embedded using any manufacturing method into the leading edge, but in this case, because erosion and paint damage from dust and rain, etc. constitute a significant problem, combinations of integrated conformal vortex generators with additional conformal eddy generators that can be replaced in operating conditions are preferred for protecting leading edge surfaces to maintain a layered or low-turbulent low-energy flow.

[00112] Conformal vortex generators cascaded in a confined aerodynamic space may not usually provide the best combined benefits due to mutual vortex interference. Vortices and streams that are not properly spaced apart, in particular on a rotating surface, need tight spatial control to prevent mutual interference, or separation in the direction of flow to minimize disturbances in normal operation. The interactions of the vortex traces from the upstream flow of stators, rotors, and other sources of transient disturbances do not cause serious performance degradation, since they are much more significant structures than the end vortices of the conformal vortex generator and are usually located on the outside of the boundary layer, and the flows can propagate on top of a few reduced conformal vortex generator elements that can “collect” or absorb this vortex, rotational sludge and pulsed energy of the fluid, since they can operate efficiently beyond the critical Reynolds number. Measured cyclic vibration and non-linear polynomial (NP) rms voltage reduction on helicopter blades, which is approximately 30% over the entire space of flight modes, prove that conformal vortex generators can work very efficiently at large cyclic extreme values of angles of attack and flow disturbances.

[00113] It should be noted that the controlled amount of fluid mass of the lower part of the boundary layer is effectively separated from the input surface flow (and deviates in the pairs of end vortices of the conformal vortex generator), and this is essentially the goal of active boundary layer control systems in the rarefaction zone, in which porous aerodynamic surfaces are used, as well as the edges or slots of the strip steps located in the rarefaction zone. Many well-known active systems were rejected due to problems caused by plugging holes, so that the conformal vortex generators used in this zone to control the boundary layer are located higher with the addition of end vortices of the conformal vortex generator to increase surface control efficiency and also to reduce aerodynamic drag. The use of additional conformal vortex generators at the leading edge of aerodynamic surfaces with a deep chord, similar to the wing in front of the ailerons of the Piper PA-31 Navajo aircraft, which improve the control of ailerons when the flow is disrupted from the wing, reduce the stopping speed of the aircraft and increase the cruising speed. This can serve as an example of a non-rotating fluid flow, similar to the low pressure turbine / compressor / low pressure compressor stator, while a helicopter rotor or an airplane propeller / rotor is an example of a rotary fluid control, similar to a rotary the blade structure of a low-pressure turbine / compressor / low-pressure compressor, but with a different fill factor, elongation, etc., which use conformal vortex generators with step lengths of about 20 mm leaving and step heights of 300-500 μm for chords of the aerodynamic surface of about 180 mm, but these values are not limiting and depend on the Reynolds number and geometric shape.

[00114] According to another integrated flow control method in combination with integrated conformal vortex generators, which can be additionally used on rotor and stator vanes of a low pressure turbine, it is necessary to use fluid stream jets to introduce or add momentum to the fluid stream and the boundary layer in the region steps of a conformal vortex generator or after it. These jets can be activated by a source of fluid pressure as known synthetic jets, or they can be a fluid of a working aerodynamic surface collected around a pressure region or a conformal vortex generator matrix 11 of the lower surface, with corresponding passage through the matrix of paths, channels and pressure chambers to the surface on the side of the rarefaction zone.

[00115] In FIG. 2c, a cross-sectional view shows a backwardly inclined jet channel 37 for introducing a fluid and / or a measuring hole that can transmit fluid flows with the corresponding pressure and flow rate from the injection chamber 38 of the increased pressure to the outlet surface 2. Adding an injection cavity 36 for injecting a fluid stream with small frontal drag in the surface behind the rearward-facing edges 24 of the step and the location between the ends of the conformal vortex generator are additional features that improve fluid flow characteristics. The addition of a fluid jet in such a backwardly inclined manner (with an additional exit to the profiled cavity) provides the advantage that a part of the downwardly directed velocity vector of the output high-energy stream 23 is used to suppress jet peeling when blowing under high pressure and at high flow pulse ratios , and also promotes the spread of the reactive fluid flow in the lateral direction and in the flow direction. The contour shape and deviation of the fluid outlet from the injection cavity 36 for the fluid allows the energy of the reactive injection fluid to be added to the lowest portions of the boundary layer near the surface to facilitate additional energization of the boundary layer (similar to the well-known Coanda effect or methods of blowing through a gap), and advanced features are that there is minimal speed difference / slice and turbulence in the merging high-energy output 23. The advantage of combining a conformal vortex generator with an injection jet or suction port is that this structure of a conformal vortex generator with its inherent reduction in aerodynamic drag is effectively used with increasing flow rate to further improve the flow characteristics of the fluid.

[00116] Since the backwardly inclined fluid injection channel 37 is located below the high energy output stream 23, the dynamic pressure is lower than the pressure in the stagnant boundary layer at the lowest levels, so that a calculated fluid mass flow rate of the fluid stream can be effectively provided using reduced pressures in the injection chamber 38. The reduced pressure stream and large volumetric capacity due to the influence of the downward output high-energy flow 23 provide t the possibility of using the jet channel 37, having an increased size, for the injection of a fluid that is less at risk of blocking debris. It is also possible, but not necessary, to use a certain number of fluid injection channels 37 for supplying to the surface or into one or more cavities 36 for injecting a fluid flow located between the ends of the conformal vortex generator, so that a larger fluid flow the medium could spread laterally, and into other additional and backup jet openings, also accessible and active in case some of the openings are blocked ovannymi garbage.

[00117] This improvement due to the jet regime of the flow uses additional energy of the fluid flow and can be applied to facilitate control of the separation of the boundary layer and aerodynamic drag, moreover, the injection chamber 38 of the increased pressure can feed the channel 39 for transferring fluid from the working surface located in point 40 capture fluid with low drag, optimally close to the critical points of high pressure at point 12 of the minimum conformal eddy ra, incorporated in the work surface, or power injection chamber can be achieved by selecting the filtered air from the air compressor or auxiliary sources, or can even be used in methods of the zero mass flow rate, similar acoustic pulsating pressure source.

[00118] The use of a low-drag fluid capture point 40 as a fluid source of appropriate pressure is an example of a useful fluid communication of the surfaces of various parts of a volumetric structure for a fluid stream, with the channel and pressure chamber being selected to provide accurately measured fluid flows in relation to pressure differences. If the additional energy of the fluid flow for the jets is extracted from a fluid source, the pressure of which changes in accordance with the surface flow or the engine flow rate and velocity conditions with changes that go beyond the calculated modes and values of the Reynolds number, then the momentum of the jet fluid will generally accompany indicated variable values of the Reynolds number, without the need for additional flow or pressure control to prevent jet peeling that may occur If the jet is used to excite the fluid flow source is fixed or unchanging pressure. This selection of fluid from the working surface effectively acts as an active control of the boundary layer by suction on the working surface.

[00119] On the rotating aerodynamic surface or the surface of the casing, the fluid injection channel 37 can be connected to the injection chamber 38 of a high pressure by a bandaged or step input channel, which is configured to orient slightly outward at the start point of the pressure chamber, for general deviation of a heavy dust and debris penetrating externally into pressure chambers and not causing an increased change in the angle or deflection path, as well as entering the nozzle and blocking it. These inertia-separated dust and debris generally move outward in a centripetal environment (or under the influence of a pressure / flow impulse in the case of the aerodynamic surface of the stator) and then are additionally ejected from the corresponding end opening 41 of the deflecting chamber near the trailing edge. The end hole 41 of the deflecting chamber can be enlarged and can use centripetal accelerating forces to control self-cleaning by partially blocking the outlet at full operating speed (without wasting fluid flows), and when the rotor blade decelerates at idle, a simple force-controlled mechanism can open this self-cleaning channel to the maximum extent and provide the possibility of ejection of large accumulations of particles, in addition to the washing fluid flow Reda flowing through the turbine stage.

[00120] Having a small frontal resistance, a local source of pressure fluid taken through the channel 39 for transmitting fluid from a small frontal resistance point 40 of the fluid intake around the matrix 11 of the lower conformal vortex generator integrated in the working surface is configured to discharge having a high the momentum and energy of debris or dust, etc., moving past into higher flows of the boundary layer.

[00121] An alternative configuration of the working surface for jet blowing (as opposed to the jet source of fluid or suction of the boundary layer) can be created by making fluid intake passages 39 located on the working surface at a small fluid drag point 40 at a rearward direction as an embodiment of a jet injection channel 37 of a fluid supplied by a second injection chamber 38 under increased pressure, separated from the pressure chamber, odayuschey fluid jet in the dilution zone. This design allows a separately configured jet source of fluid under pressure, for example, to supply air from a compressor with a filter to increase the ability to separate the boundary layer of the working surface.

[00122] These pressure and jet blasting methods further improve the boundary layer momentum downstream for both the discharge zone and the working surface, and as an additional alternative, should provide fluid communication for the fluid injection cavity 36, injection chamber 38 high pressure, etc. with a suction source of fluid to extract additional mass of low-energy fluid from the region between the ends of the conformal vortex generator for the subsequent creation of a boundary layer with an increased impulse downstream.

[00123] For example, slots or other volumetric flow-conducting structures may be selected instead of round openings for the fluid injection channel 37, and the selected method takes into account the manufacturing difficulty and mechanical integrity of the aerodynamic surface or blade. The injection chamber 38 of the increased pressure can be made in several separate sections located on the wing span supplying individual regions of the conformal vortex generator to ensure that the induced pressure gradients facing the center of rotation do not leave the regions of the internal cavity 36 without sufficient supply for injection of the conformal fluid flow the vortex generator and do not overexcite the outermost regions of the cavity 36 for injection of the fluid flow of the conformal vortex generator. The dimensions of the fluid injection channel 37 can be changed along the span of the blade to also measure and equalize the unevenness of the fluid injection flows caused by pressure gradients. Removing the mass of material from areas near the casing or the axial line of the aerodynamic surface to form and manufacture the injection chamber (s) 38 of increased pressure almost does not reduce the inertia of the section or the bending strength, but reduces the weight of the blades, turbines and engines.

[00124] In FIG. 3 shows a blade of a low pressure turbine connected by a base 1 to a wall 45 of a turbine hub using a wall fillet 49, and other possible combined embodiments of a conformal vortex generator are shown. Position number 20 indicates the elongated V-shaped sections of the conformal vortex generator in the matrix. Position number 42 denotes the tip of the conformal vortex generator, which is clamped back in the direction of the span of the blade to expand the separation of pairs of end vortices. The blade also includes an increased amount of the boundary layer, having the width of the embedded tip and capable of flowing and mixing directly with the pairs of end vortices, which wrap the jets of the boundary layer and strengthen them.

[00125] Reference numeral 43 denotes the tip of the conformal vortex generator, also modified to create two wider separated pairs of vortices rotating in opposite directions. According to this embodiment, an additional set of acute-angled reduced and integrated conformal vortex generator steps generate reduced end vortices rotating in opposite directions, limited by large-sized external end vortices. This structure allows you to expand the area that is affected and processed by two primary and two secondary flow end vortices.

[00126] Reference numeral 44 denotes another embodiment of the tip, which creates two primary end vortices, partially extending below the stage of the conformal vortex generator, and contains tips of reduced width at the top of the conformal vortex generator, which generate two reduced secondary end vortices.

[00127] In all of these cases, the steps of the conformal vortex generator arranged along the span of the blade having the tightened width, precisely control the mass flow in each of the vortex structures, as a result of which the flow can be controlled. The structures and matrices of the conformal vortex generator can be located along the perimeter of the volumetric interscapular passages of the low pressure turbine lattice and on the input surfaces like the wall matrix 46 of conformal vortex generators to improve the aerodynamic drag of the rotor or stator and flows. In a rotating medium of a rotor blade, successive cascades of conformal vortex generators degrade aerodynamic drag due to vortex contact with inclined secondary flows, but can be used on a stator in multistage form with optimal separation and displacements, or in some cases for other purposes, such as secondary modifications stream splitting.

[00128] The symmetric or asymmetric second conformal matrix vortex generator 47 (stepped into the housing) in the trailing edge 5 can be used on any suction and / or working surfaces to change the vortex traces of the blade and improve the lifting force / vorticity, since they are located completely and directly on the surface in front of trailing edge outflows. In the case of a rotor, they are less susceptible to harmful effects in a rotating medium than conformal vortex generators, used, for example, as a second row near the matrix 6 or 11 of the upper conformal vortex generator.

[00129] Vane shank platforms, constant radius surfaces and volumetric flow-transmitting structures, as well as fairings at the root ends of the interscapular passages and possible end connections of the ends can also have the benefits of relaminarizing the boundary layer by means of a conformal vortex generator with a resulting reduction in aerodynamic drag and also reducing flow divisions induced by secondary flows similar to an interscapular vortex, etc.

[00130] The ends of the tips of the "indicator" of the low pressure turbine or the outer surfaces of the end brace are often abrasive and expand with intensive changes in operating temperatures, and are made with the ability to sometimes come into contact and abrasively clean the paths of the ends of the rotor blades passing with a small gap past the surfaces End seal and motor loop brace. In the resulting gaps of the rotor tips at high temperatures, large pressure drops and secondary end flows occur, and the surface of the end seal retaining elements contains a boundary layer and secondary fluid flows that pass by at high relative peripheral speeds.

[00131] In the surfaces of the ends of the tips of the "indicator" of a low pressure turbine or an external end brace, an integrated conformal vortex generator matrix 48 with end parts, with tips oriented in the direction of the flow in the local relative direction of the fluid flow, and such a construction can be used provides the ability to remove and eject the adjacent low-energy boundary layer of the bandage and reenergize to reduce losses and aerodynamic drag of the bandage structure and nchika. The end vortices formed by the matrix 48 of the conformal vortex generator with end parts flow towards the working surface of the pressure drop at the ends of the blades, and the vortex formed by the step is in the path of the flows formed by the end of the blade to destroy the end vortex of the blade, organized in the form of a more coherent and powerful structure flow.

[00132] The turbine stage vanes, surfaces and passages also have increased streamlined surface areas in the fluid flows with thickening of the boundary layer flows on the suction and discharge surfaces of the fluid, so that the integrated relaminarization of the boundary layer of the conformal vortex generator acts to reduce the profile resistance and loss of fluid flow environment, as well as to reduce the deficit momentum of the vortex wake. The intensity, adhesion of the flow to the surface, and the velocity of the end vortices of the conformal vortex generator allow us to create a new mechanism that provides the possibility of continuous and fast recovery of the attached flows after periodic disturbances of the vortex wake occurring upstream of the flow. This also applies to any other flow areas, such as compressor stages, combustion chambers, air ducts, etc.

[00133] The design methods of the blades for low pressure turbines described in this application can be used to optimize new gas turbine structures and configurations, passages in rotors, stators and ducts with low aerodynamic resistance and loss of flow and fluid energy, increased flow reliability, an extended range of deviations from operating conditions, a reduced duty cycle and an increased angle of rotation of the jet per stage.

[00134] According to another embodiment, these new vanes according to the present invention can be configured with reduced losses caused by aerodynamic drag, and can be used as “structurally compatible” update elements matching the geometry of the mating and flow angles in the stages of existing turbines during a service update to provide improved aerodynamic drag characteristics of the engine and reduced energy losses within the existing engine investment tel with a long service life. Thus, while new designs of low pressure turbines with integrated conformal vortex generators can take advantage of the conformal vortex generator according to the present invention, “structurally compatible” low pressure turbine blades that are accurately installed and function, and which replace the known vanes within the existing low pressure turbine stage grill, such as, for example, the CFM-56 turbofan engine, to expand the limits mproving branch flow with low Reynolds numbers and reduce aerodynamic drag, improve specific fuel consumption engines existing invested. The rotor and stator blades of a low-pressure turbine are one of the most low-risk areas of modernization in a turbofan engine.

[00135] Alternatively, these conformal vortex generator matrix embodiments and drawings may be used in other similar areas related to fluid flow, such as, for example, wind turbine blades (similar to those described by Godsk '259), or a propeller in which the stall angle of attack and the working dimensions can be increased without increasing aerodynamic drag, and in fact the blade and energy loss on the surface can be reduced. Even though the design of the aerodynamic surface, aspect ratio and fill factor, etc. are different in the above listed embodiments of the lattice of a low pressure turbine; integrated conformal vortex generators can also be made in these surfaces that control the flow of fluid.

[00136] An axial compressor. Axial compressor stages are usually designed with much thinner and sharper edges, high-speed transonic supersonic aerodynamic bodies (not in the style of a flow damper) to ensure maximum compression and momentum transfer to the fluid flows at each stage. These aerodynamic surfaces or sections of the blades may have the benefits of using the integrated conformal vortex generator in the same general way as described above for the aerodynamic surfaces of a low pressure turbine. The ability to expand the angle of attack of the stall of the rotor and stator of the axial compressor in the calculated rotation angles expands the boundaries of the surge characteristic of the compressor (and also reduces the stall from the surface and separation) and increases the resistance to flow disturbances, causing massive cascade splitting of the flow in subsequent stages. The low pressure turbine or other stages of the turbine do not exhibit significant exposure to the specified unwanted cascade separation or surge mechanism of axial compressors.

[00137] In FIG. 4 shows a stylized example of an insulated casing 50 of an axial compressor blade. Compressor stages (low-pressure compressor, medium-pressure compressor, and high-pressure compressor) can have varying blade lengths, interchangeable shank, and tip diameters (or “compressor lines”), selected depending on the requirements of disk area, local flow, and pressure. For the aerodynamic surfaces of the rotor and stator, slightly different geometrical shapes are used, since the stators act as diffusers to restore the stage pressure, but conformal vortex generators can be used in a similar way on all these fluid flow control surfaces and provide benefits similar to those described for low pressure turbine stages .

[00138] The suction matrix 51 of the conformal vortex generator integrated in the axial compressor is integrated or manufactured integrally with the front of the rarefaction zone of the aerodynamic surface, and this structure is designed to convert the energy fraction of the incoming undisturbed flow in the region of the input rotation angle into a pair of intense end vortices conformal vortex generator, rotating in opposite directions, which move back from the matrix of tips 53 of the suction conformal vortex a rotor integrated in an axial compressor, and which can provide separation control on a suction surface like a traditional vortex generator, which cannot be used as having a small drag or reducing the aerodynamic drag under these conditions of a rotating mass of a fluid flow. Similarly, the matrix 52 of the injection conformal vortex generator integrated in the axial compressor is integrated or integrally formed with the front part of the working aerodynamic surface, and this structure is designed to convert the energy fraction of the incoming undisturbed fluid stream in the region of the input rotation angle into a pair of intense end vortices of a conformal vortex generator rotating in opposite directions that move backward from the matrix of tips 54 of the pressure burner Nogo vortex generator built into the axial compressor.

[00139] The integrated conformal vortex generator may have the embodiments shown in FIG. 4, which are a generally repeating pattern of symmetrical pointed triangular shapes and can be configured and modified in the same manner as described above with respect to surface treatment of a low-pressure turbine and options for implementing steps and general geometric shapes of a conformal vortex generator across the blade span , at the ends and fairings of the interscapular passages. Optional expansion grooves 55 formed by the step vortex, end vortex expansion grooves 566 and the stepped shear guide 57 can be integrated on both surfaces to increase the productivity of the formed vortex step, as described above for the low pressure turbine stages.

[00140] The boundaries of surge or flow separation are expanded by the addition of built-in conformal vortex generators that greatly expand the ability to break off the aerodynamic surface, with fluid flow improvements described in detail with respect to low-pressure turbine stages, along with improved laminar flow characteristics and reduced drag. Further improvements of the compressor are possible by using the unique ability of conformal vortex generators to provide the ability to introduce a fluid flow with a small frontal resistance into the lowest levels of the boundary layer, in particular, in areas of the suction surface located downstream, subject to an undesirable decrease in the flow velocity under the influence of the pressure gradient and flow separation bubbles.

[00141] For simplicity of presentation, only one complete example of an additional fluid injection cavity 58 is optimally integrated and configured between the ends of the conformal vortex generator, said cavity being fed with corresponding energized fluid streams from the volumetric inclined fluid injection channel 59 for a given pressure injection and a mass flow rate to add an increased amount of energy to the boundary layer downstream. Such a design takes advantage of the initial downward vector of the output high-energy flow flowing over the steps of the conformal vortex generator to prevent jet peeling and to minimize any horseshoe-shaped or kidney-like vortices at the leading edge at high ratios of blowing and flow momentum, and also helps to spread the jet stream of the fluid in the lateral direction and direction of flow. A plurality of fluid injection cavities 58 and fluid injection paths 59 that can communicate with a pressurized injection fluid source, such as a pressure injection chamber 60, can be distributed across the suction aerodynamic surface. A fluid transfer channel 61 and a small frontal resistance fluid collection device 64 may be in fluid communication with the high pressure injection chamber 60 and / or the collection channel 63 located in the tip region to provide a localized fluid source of fluid. Means for increasing the jets and fluid flow in the pressure chamber are configured in the same manner as the stages of the low pressure turbine. The entry of fluid from another is possible, for example, using an injection chamber 60 of high pressure, connected in the shank or tips of the blade with an additional jet source of fluid, such as, for example, air taken from the downstream step compressor, which can also be further pre-cooled to increase fluid density.

[00142] The matrix 62 of a conformal vortex generator equipped with end elements, equivalent to the matrix 48 of the integrated conformal vortex generator with end elements for a low pressure turbine, can be used in the tips facing the end seal elements of the compressor retainer, despite the fact that the cross sections of the blades are very thin.

[00143] These axial compressor improvements generally reflect the methods and configurations described for the low pressure turbine stages and provide combinations of: extended surge resistance limits, increased compression ratios per stage, increased rotation angles, less expensive compressor stages with significantly reduced weight. Since the compressor consumes approximately 60% of the energy consumed by the engine, increasing the efficiency of these stages has a big impact on the overall efficiency of the engine and the specific fuel consumption of the engine.

[00144] Fan stage: fan grids usually operate at significantly lower temperatures, unlike, for example, high pressure turbine / low pressure turbine (HPD) turbines and have larger dimensions, they may require the use of conformal vortex generators with increased step heights and do not have to have the same thin sections of the leading edge as the blades of low-pressure compressors (LPC) or high-pressure compressors (HPC). In FIG. 5 shows details of the contours of a typical suction surface 70 of a fan blade of a known fan that is protected in the leading edge areas from erosion by an attached strip 71 of titanium or other metal, which is a system for protecting against erosion of the leading edge and which is usually installed and aligned in the area of the leading edge of the blade . To minimize flow disturbances, the metal transition 72 of the erosion protection system is essentially flush with the edge of the transition junction, but when used, inevitable microcaps open, causing the formation of an undesirable boundary layer that worsens potential, and erosive debris penetrating these transition microcracks tends to destruction of the protective paint and material on the surface of the blade behind the leading edge, which may further impair the critical characteristics of the laminar flow and for a long time and reduce the energy return of the fan grill.

[00145] In the drawing, a machined conformal vortex generator blade 73 is shown on the pressure side side with a system overlay 74 for erosion protection of the conformal vortex generator that can be attached over an existing unmodified part 70 and 71 without other blade modifications typically required for the known fan blade array. This overlay 74 of the conformal eddy generator erosion protection system is used on both the suction and discharge surfaces to: reduce the drag of the fan blade and input torque, as well as the engine power required for this traction; providing a higher stall angle of attack for improved dynamic response and increased resistance to flow destabilization in conditions beyond the limits of design conditions; reduction of supersonic shock loads of the fluid flow and losses in the tips of the fan blade (by using the end vortices of the conformal vortex generator to destabilize the interactions of the shock wave with the boundary layer (SBLI) in the areas of separation of the shock wave having a forked base (lambda-foot)) and reduce erosion blades using a consumable and alternatively made with the possibility of replacement in the field of a replaceable element. The use of end vortices of a conformal vortex generator to destabilize the mechanisms and phenomena of the interaction of a shock wave with a boundary layer (SBLI) in the areas of separation of a shock wave having a forked base is feasible on all other aerodynamic surfaces, the surfaces of the blades and the body, washed by the fluid flow, for any fluid flow rates and Reynolds numbers, which induce sufficient vorticity, while providing an extended angle at ki and a decrease in drag due to relaminarization.

[00146] The overlay 74 of the conformal vortex generator erosion protection system operates at the design stage heights, and this means that the output high-energy backward flow over the conformal vortex generator steps flows over the subsequent surface 75 located after the stage, and even with the initial downward direction of the flow vector in areas after the step, debris and sand and the like, having a higher density and momentum than, for example, a fluid stream like air, will not have enough energy to turn down, but they will continue their trajectory and will be subject to secondary flows and centrifugal outward forces and will freely rise above the thin body of the scapula. This effect of reduced surface erosion of paint and materials behind the steps is visible on aerodynamic surfaces and body surfaces equipped with conformal vortex generators.

[00147] The overlay 74 of the additive type conformal vortex generator erosion protection system may be made of elastomer, plastic, metal, ceramic coated material, carbon fiber, carbon-carbon, silicon carbide or metal fiber matrix, or ceramic matrix composite (CMC) or other material with the necessary mechanical and thermal strength, which can be processed by any processing method to aerodynamically match the existing leading edge of the blade with subsequent m attachment to the blade an aerodynamic surface or hull. The overlay 74 may be in the form of a single element of a conformal vortex generator, but in the case of long-span and curved leading edges, the blades of the conformal vortex generator can additionally be made from sections having different geometric shapes, which should smoothly transition into adjacent sections. Any inhomogeneities in the fluid flow of the blade must be streamlined before the addition of a conformal vortex generator to obtain improved results.

[00148] The use of conformal vortex generator structures with asymmetric or different pitch and geometric shapes makes it possible to change the flow modifying action of the conformal vortex generator across the span of the blade, so that, for example, in areas of subsequent localized generation of the shock wave, the conformal vortex generator pitch may be thinner around this place for generating an end vortex having an increased density of the elements of the end vortex jet to distinguish between interaction effects ystviya shock boundary layer, and not the exclusive focusing only on optimization of drag reduction. Reducing the shock loads of the fluid flow acting on the housing provides the opportunity to reduce energy losses and / or increase the range of operating modes and design operating conditions of the outer surface.

[00149] The newly designed aerodynamic surface of the fan blades or the surface of the casing can now be configured differently without linear protective recesses in the leading edge for components of the known erosion protection system and with all the benefits of conformal vortex generator improvements. Known metal sections of the leading edge erosion protection system may be denser than the material of the blade body, as a result of which some weight savings can be achieved before applying the system cover 74 to erosion protection of the conformal vortex generator to take advantage of the conformal vortex generator. Another choice of the new design should have a conformal vortex generator matrix integrated at a partial step height into the front edge volume, which then overlaps during installation with a matched removable cover plate 74, which in this case can be thinner and lighter.

[00150] The newly designed fan blades can also provide the advantage of the optional combinations added: grooves 76 for expanding the vortex formed by the step, grooves 77 for expanding the end vortex, step cutting guide 78 and cavity 83 for injecting a fluid flow with a pressure source of a fluid flow , a pressure chamber and nozzles and the like, for example, for a turbine blade of a low pressure. All of these elements are shown as single examples in FIG. 5b located on the pressure surface and / or they can also be applied on suction surfaces. These grooves and structures make it possible to use markings for mounting and alignment of the conformal vortex generator and, as an option, provide more significant improvements on wider chords of the blade without the need for excessive increase in the heights of the steps, as well as the thickness and weight of the conformal vortex generator, and, in addition, provide the possibility of additional control of separation in addition to the above advantages, in particular, by using lining 74 to protect against erosion of conf rmnogo vortex generator and / or any other stepped structures built conformal vortex generator. These grooves and structures also minimize the effect of the step height on the aerodynamic surface downstream or the aerodynamic structure of the body surface.

[00151] The combination of a built-in conformal vortex generator and an erosion protection strip that reduces the drag of the fan blade and the input torque of the blade, for example, by about -10%, provides a significant improvement in specific fuel consumption and increased efficiency, since a modern fan disk usually has 5-10 times cooler bypass outlet traction nozzle than section traction nozzle.

[00152] A removable and ablative component of the system for protecting the conformal vortex generator of the leading edge design combination also better protects the subsequent surface of the blade and is preferred because the accumulated wear of the leading edge destabilizes fluid flows and the boundary layer in one of the most sensitive parts of the blade, so replacement by inspection is mandatory.

[00153] The processed blade 73 of the new design, equipped with a conformal vortex generator, may contain a symmetric or asymmetric matrix 79 of the conformal vortex generator of the trailing edge embedded in the rear of the chord in front of the trailing edge (with the tips facing back), and the step of the built-in conformal vortex generator is not deepened into the surface jeopardizes body strength, mass distribution, flutter boundaries and aeroelasticity in this thin region of the trailing edge, subject to high stress Nij. On the working surface of the housing, the fluid flows can be configured so as not to separate until they come closer or touch the trailing edge, so that conformal vortex generators located in this region provide a momentum of the fluid flow, which thickens the boundary layer, but which is reasonably moderate for interacting with the boundary layer at calculated step heights limited by the thickness of the surface of the trailing edge region. An upstream overlay 74 to protect against erosion of the conformal vortex generator generates end vortices that generally expand when the trailing edge region is reached and are pushed out slightly by the conformal vortex generator matrix 79 embedded in the trailing edge due to the high-level centripetal secondary flows and the effect of the conformal vortex generator. In this case, which is close to the Kutta-Zhukovsky condition on the trailing edge, which defines and controls the merging of the fluid structure of the body trace of the body, the detached upstream stream of the stream of the end vortex of the conformal vortex generator does not receive the possibility of unwanted rotation along the span of the blade until they are included in the vector vorticity integrals of the vortex trace of the trailing edge, which leads to the effective lifting of the body, given by circulation. The matrix 79 of the conformal vortex generator embedded in the trailing edge adds energetic jets of the end vortex almost directly to the vortex trail of the trailing edge, so that the additional use of the shape of the asymmetric conformal vortex generator allows direct summation of the vortex vector, which matches the implied direction of the vortex trace formed by the tip of the vortex generator created by the body of the lifting force, or vice versa, which provides the possibility of modif ation geometrically managed coefficient C _L generated casing lift force, particularly at low angles of attack additive from any of the pressure surface and suction surface. Thus, conformal vortex generators can be used to influence the vortex traces of the body fluid flow. These advanced conformal eddy generator erosion protection methods and combination of performance improvements are also of great importance, integrated into the open-rotor turbofan concepts, helicopter rotors and traditional propeller blades, which share a range of fluid flow concepts and design methodologies.

[00154] The location of this new conformal vortex generator matrix 79 embedded in the trailing edge is different from that described by Gliebe '240, Fritz' 488, Vijgen '665, Shibata' 436, Young '319, Balzer' 106, etc. p., since it is a compact integral surface structure, and processing takes place completely inside the length of the body and in front of the original trailing edge of the body and acts to: reduce the loss of fluid flow of the boundary layer between the backward-facing ends of the conformal vortex generator (in contrast to the known non-optimized non-surface x eddies which induce only the vortex energy loss), increasing blending wake vortex flow to reduce flow noise while using substantially reducing aerodynamic resistance of the structure changes circulation lift force generated by the body, and can be configured independently to the pressure surface and suction surface. The backward-facing ends of the matrix 79 of a conformal vortex generator integrated in the trailing edge can be positioned and offset so that they generate jets of end vortices from the ends of the suction and discharge surfaces, which then effectively form an interdigital structure only outside the trailing edge and cause a minimum mutual influence before summation in the vortex of the vortex trace of the trailing edge.

[00155] In suction surfaces, a conformal vortex generator matrix 79 embedded in the trailing edge may be used, but efficiency decreases with increased angles of attack, which induces thicker backward regions of the boundary layer that have low energy, or flow separation bubbles or fluid flow separation. These improvements to the conformal vortex generator can generally be used with any rotation and with increased efficiency on non-rotating aerodynamic surfaces and body surfaces in Newtonian fluid flows in the same way to obtain the advantages described above in this application.

[00156] The sections of the chord of the tip of the fan blade are thick enough to use the matrix 82 conformal vortex generator with end elements equivalent to the end elements of the integrated matrix 48 conformal vortex generator for a low pressure turbine, in the region of the ends facing the bandage of the end seal of the fan. In addition, temperature changes in the gap between the tip of the fan and the bandage are smaller than those of the turbine sections, and conformal vortex generators with end elements facilitate the control of the flow of the boundary layer of the fairing contour on surfaces close to the ends of the fan.

[00157] With respect to various designs of the aerodynamic surface or the hull, numerous attempts have been made to use the known Gurney trimmers to change the coefficient C _L and the ratio C _L to C _d , as well as to reduce the ratio C _d , but theoretical work tends to incorrectly predict the impact of the trimmers applied to aerodynamic surfaces and aerodynamic bodies in a stream of Newtonian fluid at acceptable values of the Reynolds number. The elastomeric lift-increasing eLET 80 trimmer, made in the form of a volumetric block, is shown in the drawing as a blade 73 integrated with a conformal vortex generator near the trailing edge, which is fitted approximately in the middle of the span of the working surface. It should be noted that the eLET 80 trimmer is usually best embedded in the span width range from 15% to 30% of the full span, but this is not a limitation, and use the trimmer in the inner part of the rotating housing from the end, where the fluid flow rate and lift are significant. The eLET 80 trimmer is usually in the form of a block, blade or two-blade structure at a height between 0.5% and 3% of the width of the local chord, but this value is not a limitation. The offset of the eLET 80 trimmer from the trailing edge is approximately 0% to 500% of the height of the device, and the best overall results for the indentation are usually 100% of the height of the device.

[00158] The eLET 80 trimmer, when used, generates a set of intense vortices rotating in opposite directions along the wing span, packaged and trapped between the eLET 80 trimmer and part of the trailing edge edge. These transverse vortex jets act on the flows formed by the trailing edge of the suction surface and tend to deviate these flows downward after the trailing edge and changing the local conditions of Kutta-Zhukovsky in the wing span section. The additional downward acceleration of the fluid flow behind the trailing edge preferably changes the gradient of the unwanted pressure recovery of the suction surface (by reducing the thickness of the turbulent region of the boundary layer and aerodynamic drag) and also effectively increases the angle of attack of the local chord and lift.

[00159] The eLET 80 trimmer is made in the form of a flexible and durable, having a small mass of elastomeric material, which almost does not add excess weight to the rear and sections of the trailing edge of the aerodynamic surface or body and reduces the stability and borders of the flutter, and is also effectively mechanically transparent "with respect to the main body at the trailing edge. In addition, due to aeroelastic phenomena and vibrational dynamic regimes of an unconditionally flexible aerodynamic surface lying under the trimmer, such as propellers, rotors or blades, inappropriate mass added to the trailing edge cannot be reliably held without distributed and unfocused local adhesion-binding caused shear forces that allow adhesives to fully distribute the load caused by intense acceleration forces distributed over the entire surface area of the fastener, and do not focus them on points of increasing slip. For these reasons, incompatible materials (i.e. non-elastomeric) are undesirable for adding to this adverse environment, and if these incompatible materials are nevertheless added, they create a center of vibrational stresses and cause bending problems for the underlying body, resulting in intense fatigue case material. The manufacture of an expanding trailing edge (DTE) having a similar design faces the same practical common difficulties.

[00160] The reduced length sections of one or more eLET 80 trimmers ensure that normally unwanted sweep blades swirl jets have an expansion outlet when they accumulate and must lose mass flow of fluid, which usually occurs at a speed of approximately 1600 Hz, which commonly considered a diagnostic acoustic signature of fluid flows when using the eLET 80 trimmer and which emphasizes the innovative value of additional paths for vortex jets when used lzovanii segmented or partitioned application strategy. An additional improvement of each eLET 80 trimmer is to make partial sectional cuts, mainly directed along the chord through the block so that mechanical damage is limited by subsection, to effectively provide functional means to limit the gap.

[00161] A small angle at the inner end or the outer end of the eLET 80 trimmer design allows you to direct the vortex stream outflows in the preferred direction of drop from either end of the casing when combined with the vortex trace of the trailing edge by adding to the integrated vortex vectors or subtracting from the integrated vortex vectors generating clean body circulation and lift. A slight bend backwards on both sides, for example, from the center of the eLET 80 trimmer body, allows the streamlined dropping of the vortex jet and its balancing in the vortex trail of the trailing edge as a geometrical relative part of the masses of the fluid flow treated with the eLET 80 trimmer, while the central transverse the vortex increases the downward slope of the flow to increase lift.

[00162] It should be noted that the eLET 80 trimmer can be used with the trim 74 to prevent erosion from the conformal vortex generator or the conformal vortex generator matrix 79 embedded in the trailing edge or without trim 74, but for reasons of dynamic stability, it is preferable to use the trimmer in combination at least with a method of using a conformal vortex generator and lining 74 to protect against conformal eddy generator erosion. A trailing edge conformal vortex generator matrix 79 can be applied in front of the eLET 80 trimmer or can be used in sections between the elements of the eLET 80 trimmer. In FIG. 5b shows the configuration of two examples of a conformal vortex generator matrix 79 for trailing edge between one example of an eLET 80 trimmer, which is not a limitation, but indicates that conformal vortex generators can be configured in a span or surface portion in combination with other features.

[00163] A trimmer 81 provided with a discharge tip is shown as a reduced trimmer installed in a tip-mounted rear edge of the blade suction surface 70, which can be added to reduce the lift of the angle of attack of the chord section in this section of the aerodynamic surface and acts to significantly change the end vortex aerodynamic surface, in particular, on an open blade, which does not represent a large obstacle to the end vortex, which flows from the discharge surface to the suction surface. In the case of helicopter rotor blades, this trimmer option acts to increase the load across the entire span of the blade inside the highly loaded tips, and the reduced and delayed local end vortex is less prone to dropping into disk flows and creating loads caused by the forces of the transition process, disturbances and acoustic signatures as a result of interaction vortex blade (BVI). Loading on the inner part of the disk also reduces some of the lifting bending moment and deformation loads acting along the span of the blade on the structure of the aerodynamic surface.

[00164] The vortex induced by the wing span in the surface of the front step entrance region of the leading edge of the eLET 80 trimmer is closely matched by the vortex of the back step surface, so that there is an unexpected minimum resultant pressure along the chord or load created by the backward force on the trimmer eLET 80 for testing adhesive bond strength at significant shock fluid flow rates and Reynolds numbers. The inlet and outlet vortex jets along the blade span approximately balance and effectively protect the elastic masses of the trailing edge from the expected dynamic shock pressures created by incoming high-speed fluid flows. The consequence is that the initial adhesive test occurs at intense radial accelerations. The aircraft propeller test generally confirms similar material properties and possible performance improvements, for example, a decrease in specific fuel consumption at cruising speed of 12 gallons per hour to 10 gallons per hour (45.4-37.9 l), which is equivalent to approximately 18% energy savings, for example, using a combination of Lycoming IO-540 engine and Hartzell propeller (VP) with variable pitch.

[00165] The elastomeric material used for the eLET 80 trimmer at such high accelerations and fluid flow rates is new and paradoxical in comparison with the prior art, but there are obvious improvements and new properties that indicate that the practical use of this material is acceptable. In case of icing of the surface during flight, the eLET 80 trimmer material is flexible and provides the possibility of transitional build-up and permanent ice discharge, since the loads in this case exceed the binding force of almost thin layers of frozen moisture, so that the maximum danger to the structure arises from the ice dropping from the leading edge through internal de-icing systems that continuously dump small accumulations before they can have a significant effect on line providers propeller. The compatibility, well-grounded deformation and elastic characteristics of shape restoration, as well as the tolerable acceptable applied methodologies of section sections that limit damage, for the eLET 80 trimmer provide the possibility of using new structural structures on aerodynamic surfaces and body surfaces, such as vanes, rotors, fan disks and propellers etc.

[00166] The inlet guide apparatus behind the fan stage and in front of the inlet compressor can also use additional or built-in conformal vortex generators to reduce aerodynamic drag and expand the angle of attack, providing mechanical movement of the inlet guide apparatus to prevent dynamic stall of fluid flows. In the stator vanes leading to the cold section and transporting these de-turbulent outlet cold flows in the fan channel, conformal eddy generators can also be used to reduce drag and expand the angle of attack. Conformal vortex generators can be used in additional inlet guides of the apparatus, for example, in the outlet openings of the compressor and the combustion chamber and other aerodynamic accessories, as well as in load-supporting racks, with the same advantages already described for any surface washed by the fluid flow.

[00167] An increase in surface flow from the intake ducts of the injection surface or other fluid source, such as, for example, cooled air drawn from a compressor, can also be used on a new fan blade with structures equivalent to the injection channel 37 for low pressure turbine jet fluid , cavities 36 for injecting a fluid stream and an injection chamber 38 of increased pressure, scaled for an enlarged fan blade to improve the blade ki fan, operating angle of attack characteristics and aerodynamic drag, both for low-pressure turbine stage as described above. This matrix method of a built-in conformal vortex generator with increasing injection channels for jet fluid can also be extended to helicopter rotor blades of a new design, propellers, and even a fixed aerodynamic surface or wing surfaces with appropriate scaling of the geometric shape.

[00168] A jet engine generator (compressor, combustion chamber, and turbine) that uses conformal vortex generators for improvements can use the low-pressure turbine output transmission (or similar stage to extract power) to drive the fan disk cascade for cold jet thrust air duct (as in the prior art) or for configuration in a turboshaft gas turbine engine configuration for driving external load or gearboxes GOVERNMENTAL devices such as a propeller, a rotary system, power generator, pump or compressor, used for example for cooling, pumping natural gas or chemical process systems industrial scale, such refinery.

[00169] High pressure turbine blades: FIG. 6a and 6b show a blade 90 of a high-pressure turbine with a deep section of a bucket-shaped reactive aerodynamic surface, which has attached components or a conformal vortex generator matrix 91 integrated into the upper surface and a conformal vortex generator matrix 109 integrated in the lower surface, which operate in the same way as in the blade of a low-pressure turbine described above, to extract energy from the fluid flows coming from the combustion chamber and located above downstream flow powerful compressor stages or load. The integrated conformal vortex generators of the high pressure turbine are configured to reduce aerodynamic drag and expand the angle of attack to reduce separation / turbulence of the fluid flow and also to reduce heat loss. Integrated conformal vortex generators, mainly made on a metal base, provide maximum strength to the blades of the high pressure turbine, but since multilayer blades for high pressure turbines can be manufactured to provide all the disparate required characteristics, a high temperature conformal vortex generator matrix for the leading edge can also be used with the corresponding bulk structures based on silicon carbide or metal fiber structures and ceramic composite structures (CMC), mutually enclosed in the new design of the leading edge of the high-pressure turbine in the grid.

[00170] For the inlet guiding apparatuses or the first stator of the high pressure turbine and the first disk of the high pressure turbine rotor, the temperatures at the exit of the combustion chamber are higher than typical melting temperatures of the heavy-duty nickel alloy, so that these surfaces are cooled by the fluid. The cooling nozzle fountain head 93 is located at the leading edge of the stator and rotor blades and delivers cooled fluid (typically taken from the high-pressure compressor (HPC) air in the cooler, for example, ~ 650 ° C) from the fountain cooling chamber 94 of the high pressure. The fountain head has nozzles with sufficient inclination and provides sufficient mass flow for cooling and protecting the leading edge of the aerodynamic surface, and this fluid cooling medium is then separated and flows around the discharge and suction surfaces to provide additional cooling of the surface and deflect heat flux and thermal loads in the vortex wake aerodynamic surface. The aerodynamic surface has the lowest local temperature, and when moving higher in the boundary layer into the undisturbed fluid flows, the temperatures rise closer to the maximum temperatures of the combustion chamber. Any excess turbulence on the aerodynamic surface or the surface of the body, such as bubbles separating the flow of fluid and turbulence of the separation, usually mixes heat-resistant fluid with cooling and lowers the temperature of the layers, and also increases the heat flux that must be removed to allow cooling of the surfaces.

[00171] Known aerodynamic surfaces are further cooled by lining the inner surface, which is cooled by serpentine channels and pressure chambers, which supply cooling jets downstream to the additional inclined matrices, as well as internal pin grids 107 and cooling exit slots 92 at the trailing edge. The problem is solved by providing a sufficient surface, blown by cooling fluid flows without jet peeling, which generate sufficient turbulence and remove heat, as well as by ensuring the efficient propagation of cooling and isolation of the surface from the high-temperature fluid.

[00172] Conformal vortex generators provide a low drag resistance method for providing efficient and well-distributed cooling fluid injection to the lowest levels of boundary layers, which is additionally used for low pressure turbine casings to improve separation control. The inclined backward injection channel 95 for the jet fluid or the measurement hole can transfer cooling fluid flows, for example, from the injection chamber 104 of the high pressure cooling the upper conformal vortex generator to the cavity 96 for injection of the fluid flow, made in the surface behind the facing back to the stage 97 and located between the ends 98 of the conformal vortex generator. The addition of a cooling jet of fluid flowing out into the profiled cavity in such a backwardly inclined manner provides the advantage of the initial downward velocity vector of the output high-energy flow from the conformal vortex generator stage for suppressing jet peeling at high ratios of the momentum of the blowing and cooling flow and facilitates the spreading of the flow of cooling fluid into laterally and in the most cooled levels of the boundary layer downstream . The pressurized cooling injection chamber 106 of the second lower conformal vortex generator also delivers pressurized cooling fluid to the adjacent surfaces of the blade and the elements of the injection channel 95 for the jet fluid, as well as the associated pressure structures or the conformal vortex generator matrix 109 embedded in the lower surface , in locations located in the same manner as in the suction surface of a high pressure turbine.

[00173] To cool the mass flows of the vortex formed by the step, an additional cooling injection channel 99 for the vortex formed by the step can be located at the base of the minimum point of the conformal vortex generator. To add additional cooling to the jets of the end vortex of the conformal vortex generator for unloading heat flows on surfaces located downstream, the cooling injection channel 105 of the end vortex can be included in the base of the ends of the conformal vortex generator 98. Other known cooling means, such as internal serpentine cooling channels, turbulators, cooling ejection from the trailing edge and tip of the “indicator”, as well as pin grids 107, can be used in conjunction with built-in conformal vortex generators and flows in the inner passage and inner lining for cooling surfaces high pressure turbines. The efficient use of optimized cooling fluxes of the mass of the lower stream, which remove heat fluxes, improves the efficiency of the engine because it estimates the energy consumed by the compressor to extract the cooling fluxes of the fluid. For surfaces in this stage of the high-pressure turbine, any known oxidation-reducing coatings and other metallurgical methods and alloys for low-frequency and high-frequency creep, etc. can be used. The grooves 100 for expanding the vortex formed by the step, the grooves 101 for expanding the end vortex, and the stepped cutting guide 102 can also be additionally integrated (as in the low-pressure turbine section) into the suction and / or injection conformal vortex generators in the high-pressure turbine to allow for performance regulation the mass flow formed by the vortex stage, which meets the requirements for the mechanical strength of the surface and the size of the stage structure.

[00174] Additional exemption from high temperature flows can be achieved by means of a heat insulating coating (FA), for example, in leading edge sections, and these typical ceramic coating surface layers reduce the thermal conductivity of the surface to attenuate heat fluxes due to increased mass and the risk of flaky peeling of the coating, loss of protection and burnout of the surface. Using built-in conformal vortex generators and jet / injection cavities that provide an effective means for cooling the surface and dissipating heat, sections of the aerodynamic surface located downstream of the steps of the conformal vortex generator are less likely to require additional mass and complexity of the increased area of the heat-insulating coating.

[00175] In combinations of the ends of the rotor, stator, and fairings, conformal vortex generators can also be used on the surfaces of the cascade passages and piping systems to provide an additional low drag drag injection channel that cools structures related to aerodynamic surfaces and improves cooling below the boundary layer in areas of undesirable secondary flows that are resistant to destabilization, for example, interscapular vortices move, etc. Conformal vortex generators with injection channels for jet fluid made in these highly profiled surfaces can be used on the surfaces of fairings. The end vortices of the built-in conformal vortex generator also provide criteria for the effectiveness of controlling the interaction of the shock wave with the boundary layer (SBLI) and can be made with the possibility of changing the vortices in the passages, shock loads and secondary flows.

[00176] The matrix 103 of the secondary integrated conformal vortex generator located adjacent to the cooling exit slots 92 of the trailing edge on the working surface can be used to minimize the vortex traces of the blade and to improve the lifting force / vorticity, since it is located directly in front of the trailing edge of the blade, so that reduced undesirable effect than the integrated conformal vortex generator used as a second row near, for example, the matrix 91 of the upper conformal vortex Ator. Improving the lifting force and cooling of the trailing edge of the trimmer matrix 108 can be added in front of the cooling exit slots 92 in the trailing edge, and this option allows the effective angle of attack of the blade to be modified, and also helps to spread the cooling flow of the slot 92 along the trailing edge, with or without a matrix 103. In this matrix 108, “curved” or inclined trimmers may be used, as shown in the drawing. The secondary integrated conformal vortex generator matrix 103 may also be added to the suction surface of the high pressure turbine blade.

[00177] Intermediate pressure turbines (IPT) may also need cooling, and they can also be designed like high pressure turbine blades to reduce losses, aerodynamic drag and improve cooling. The conformal vortex generator and related design features described in this application can be integrated in any combinations, examples, and locations, along with well-known methods of using blade and surface designs to ensure optimal performance. It should be noted that a high-pressure turbine blade equipped with a conformal vortex generator can also be used as an embodiment, for example, in a steam turbine with useful improved fluid flows and improved efficiency, and the leading edge surface coating material can be used to protect against erosion, moreover said erosion protection may also include conformal vortex generator structures. Raising and removing erosive particles and material downstream from the steps of the conformal vortex generator also contribute to protecting the surface of the stream downstream. For steam turbines in which a fluid stream comes from a combustion chamber / steam source, a compressor is not necessary, so that the amount of extracted gas turbine power can be used to power other consumers.

[00178] Centrifugal compressor: Many small compressors and pumping devices, for example jet engines, use a centrifugal impeller in the final stage of the high-pressure compressor, because it is compact, provides a high compression ratio, is characterized by weight efficiency, increased strength and low complexity. There are many common properties with respect to fluid flow between axial, combined centrifugal-axial and centrifugal compressors and pumps, in which the centrifugal vane or impeller blades on the impeller have a shank and outer diameters increasing along the axis of the impeller to the outlet, and the output flows can be completely radial or mixed (partially axial) and flow into the piping system downstream and / or the diffuser structure.

[00179] Centrifugal compressors (and pumps, when using a Newtonian fluid stream in a liquid state) may suffer from disruption of the flow from the suction surface if: the tips of the impeller, diffuser vanes, vanes (or vanes) and any other streamlined surfaces cause problems, associated with fluid flow characteristics and energy loss. Many of the impeller blades are beveled backward at the corners of the outlet stream so as to act less aggressively on the transmission of the tip impulse and the streams to reduce the stresses of separating the fluid stream at the outlet angle of the blade. The separation of the flow or separation bubbles in the low-pressure regions of a Newtonian working fluid, such as liquid water or ammonia, manifests itself as a change in the state of the fluid from a liquid state to a vapor / gas phase in trapped physical bubble structures, adding the additional complexity of a possible rapid or supersonic collapse of a bubble structure , cavitation and potential damage mechanism as a result of a large supersonic shock load and acoustic waves.

[00180] Adding a built-in conformal vortex generator in series with the fluid flows and jets on the suction surfaces of the centrifugal device and other washable surfaces provides the ability to control the separation bubbles of the fluid stream in the gas phase and reduces drag and flow loss of the turbulent boundary layer, as described above in relation to gratings. For fluid flow in the liquid phase in the suction regions, thin vortex jets of a conformal vortex generator intersect and destabilize vapor bubbles that form and grow in the volumes of the fluid, lowering their pressure below the pressure of the transition of liquid into vapor, before they can grow to sizes that can cause cavitation damage. This destabilization of the bubbles also reduces the resulting shock energy and acoustic signatures, and the vortex jets also contribute to the propagation, reflection and reduction of shock pressure and acoustic waves in the working fluid.

[00181] In FIG. 7 shows the surface of a typical open-shaped centrifugal impeller and the inner wall 120 of the sleeve with stylized features that can be seen in an embodiment of the impeller having the most open shape. The impeller according to this embodiment comprises a central input flow guide 121 leading to the leading edge of the matrix of aerodynamic surfaces of the impeller or vanes 122 of the guide apparatus, the compressor rotating counterclockwise when viewed from the side of the input flow guide 121. The axial rotation of the blades 122 of the guide vane acts on the incoming axial fluid flows, as a result of which the fluid flows are accelerated and flow along the inner wall 120 of the sleeve and then exit radially with increased momentum and speed between the output ends of the 128 blades and in the transverse direction to the matrix of additional guides fixed-diffuser blades 129 (for clarity, only one blade is shown), which then feeds a fluid stream into a final sludge-collecting means and a spiral chamber, duct, and the like, which are not shown for clarity. In the example shown in FIG. 7, additional partial vanes 132 are also used to prevent premature throttling of the input streams on the vanes 122 of the guide vane.

[00182] An integrated inlet suction conformal vortex generator matrix 124 may be embedded in the suction surface of a portion of the vanes 122 of the guide vane adjacent to the inlet leading edge of the vane to reliably prevent the separation of fluid flows (or cavitation in the case of liquids) on the suction surface of the vanes. The matrix 125 of the integrated suction conformal vortex generator located downstream may also be integrated if the geometric shape of the impeller and the flow lines provide a positive effect. On the opposite side of each blade in the area of the matrix 123 of the conformal vortex generator integrated into the injection surface, a complementary version of the conformal vortex generators integrated in the injection surface can also be integrated, which operate in a similar manner and are located in places different from the leading edge, such as, for example, on a turbine blade low pressure, to reduce flow losses on the discharge surfaces of the blade. The location of these built-in conformal vortex generator matrices is selected based on the structure, logic and technology, for example, low-pressure turbine blades with subsequent optimization of the geometric shape, flow angles and locations to adapt and match the unique geometric shape of the impeller, and the best combinations are confirmed by the final tests on a real impeller and a centrifugal compressor, pump or gas turbine design. The dimensions of the conformal vortex generator and angles shown in the drawing are presented only as an illustration for discussion and are not a limitation for the actual selected and optimized designs.

[00183] The pump shank or sleeve inner wall 120 has an increased surface area of the primary flow boundary layer of the convex and concave surfaces and some secondary flows between the suction and discharge surfaces in the passages of the same vane or blade. This surface may be subject to the undesirable effect of flow or cavitation in the suction regions, and the relaminarization of the boundary layer of the conformal vortex generator also reduces drag or cavitation, so that the matrix 127 of the conformal vortex generator embedded in the injection surface of the inner wall and the matrix 126 of the conformal vortex generator embedded in the injection the surface of the inner wall located downstream can be used to improve the design in this case ae and generally in case of any conformal vortex generator, which can have a small inclination in order to best match the local conditions of the fluid flow lines. If the blade sleeve shanks are “licked”, the integrated conformal vortex generator can also be integrated into these cowls and may even merge with other conformal vortex generators embedded in adjacent surfaces, despite the fact that such conformal vortex generator merges onto the blade and cowl cowl in the drawing not explicitly shown.

[00184] In the aerodynamic profile or surface of the guide vane 129 of the fixed diffuser, if any, the matrix 130 of the suction conformal vortex generator integrated in the diffuser can also be used to control losses and separation bubbles caused by intense pulses of the fluid flow and vortex traces coming from moving with a high linear speed of the output tips of 128 blades at the output angles of the dynamic flow and effective angles of attack of the diffuser. Since the diffuser guide vane 129 can be configured to de-turbulize the fluid flows entering the impeller and operate in a stator mode with non-rotating flows, it can also use a matrix 131 of a secondary suction conformal vortex generator integrated into the diffuser to reduce aerodynamic drag or provide use surfaces with increased curvature to create a more compact diffuser. The discharge surface of the diffuser guide vane 129 may also contain similar matrices of the injection conformal vortex generator integrated into the diffuser to reduce flow stalls and also reduce aerodynamic drag. In the flow sections of the static system of air ducts and pipelines around the matrices in the guide vanes 129 and the mixing fairings of the diffuser, built-in conformal vortex generators can also be used to further control aerodynamic drag losses and stalls.

[00185] Also in FIG. 7, the matching volumetric fixed or connecting control surface of the channel formed between the bandage and the tips of the blade, which on the impeller with an open shape is closely aligned with the moving structure, and cleans the specified moving structure of the edges 133 of the ends of the open impeller to minimize the return flow of fluid from cavities downstream. These blade edges are equivalent to the open-shaped tips of the axial blades, and the closed-shaped impeller of the centrifugal compressor is equivalent to the shape of the axial grating with the ends continuously connected by means of the brace, so that the inner inter-blade passages are completely closed.

[00186] The end-conformal vortex generator matrix 134, which is the functional equivalent of the integrated conformal vortex generator matrix 48 with end elements for a low pressure turbine, can be used at the ends of the blades facing the end seal bandages of the centrifugal compressor, although the sections the blades are very thin, small conformal vortex generators can work efficiently at high speeds and reduced gaps with high shear forces. Thermal loads in centrifugal compressors are less than at the stages of the turbine, so that the gaps for thermal expansion of the tips can be reduced and losses are reduced.

[00187] The end-conformal vortex generator matrix 134 is oblique to induce vortex jets on a tightly aligned surface of the brace to control the development of its boundary layer and flows during rapid passage of the blade when it covers the surface of the brace. The stepped recess of the matrix 134 of the conformal vortex generator with end elements may or may not intersect and cut the leading edge of the blade end, and when the configuration of the step is not cut into the leading edge, the inherent sealing gap between the end and the retainer is maintained at the leading edge of the tip by lowering the conformal vortex generator below the flow of the leading edge in the flows of the local gap. According to the compressor impeller shown in FIG. 7, the injection surface of the blade is located to the right of the matrix 134 of the conformal vortex generator provided with end elements, and the suction side is located to the left of the matrix 134, so that these jets of the end vortex of the conformal vortex generator flow in distributed places along the end chord to the left and downstream from pressure surface to the suction surface, and in the same direction a normal end vortex of the aerodynamic surface or the surface of the body occurs in the trailing edge of the housing, such as the end angular connection of the elements 128 and 133. The use of an increased angle of the mass-accumulating step to some of the elements of the matrix 134 provided with end elements of a conformal vortex generator (such as, for example, 60 °) additionally allows the formation of a large-volume vortex formed by the step, which steps is limited to act as an obstacle to energy loss flows through the gaps between the end brace and the sealing elements caused by the fluid th injection surface.

[00188] The bounding surface of the end bandage channel control can also contain matrices of conformal vortex generators embedded in it, for example, in accordance with a radial or spiral pattern, for controlling the flows of the local boundary layer under the influence of bypassing the blade, and they can be used with the matrix 134 of conformal vortex generator equipped with end elements, or without it, and can be configured in such a way that the step of this conformal vortex generator is not synchronous with the pitch of the blade ti to prevent coherent excitation waves of high pressure or acoustic signatures. For added flow sticking ability, an oblique additional flow control injection nozzle 135 can be added after the conformal vortex generator stage to increase the momentum in the lower boundary layer, and the source of pressure fluid for this is collected (and possibly cooled) and transferred from the compressor and system output stream air ducts inside the impeller axis into the pressure chamber in the impeller core, which distributes these fluid flows by an integrated burner surface nym vortex generators as required to the nozzle 135, since the flow upstream surface of the impeller under reduced pressure. In compressor and turbine housings, this injection nozzle can distribute cooling fluid that is extracted from the cooled fluid source under increased pressure. Examples of additional step expansion grooves and / or step cutter guides may be added to the impeller, but are not shown for purposes of clarity.

[00189] A centrifugal compressor, to a first approximation, can be reversed to operate, for example, as a radial supply centrifugal turbine. In this case, the input torque of the impeller becomes output, and the suction and discharge surfaces are interchanged, and any conformal vortex generator matrices can also be replaced to provide the necessary modifications of the boundary layer and flow. In the case of a centrifugal or radial-axial turbine, examples of the additional flow control injection nozzle 135 can be used, for example, for stator and rotor blades of a high pressure turbine for film cooling of the surface, as well as to improve flow adhesion.

[00190] For a closed-shaped impeller, an end brace connects the ends of all the blades to form closed passages between the blades, so that conformal vortex generators can be used on all of these internal streamlined surfaces and labyrinths of the end seal and the like. to control the boundary layer and separation in the same ways already described above.

[00191] Installing an integrated conformal vortex generator on centrifugal blades, an impeller, and other streamlined surfaces makes it possible to increase the angles of rotation of the inlet and outlet flows to enable the construction of new, more compact and lightweight compressors, turbines, pumps, turbocompressors, and similar machines for fluid flow , or can only be used to reduce the energy loss of the suction surface or fluid flow, losses associated with the Taylor-Görtler vortex thickening of the boundary layer on the concave surface, in existing designs with a mechanically compliant, having improved characteristics placed at the place of a removable impeller.

[00192] The built-in conformal vortex generator is also suitable for use in other centrifugal or centrifugal pump types for pumping fluids, turbines, propellers and compressors, such as industrial process gas compressors (eg, ammonia refrigeration units or compressors for pipelines for natural gas), jet engines and pumps or turbines for water or other liquids.

[00193] In turbochargers, a combined centrifugal flow compressor and gas turbine impellers are used, as well as, for example, a centrifugal turbine that extracts energy from a fluid stream and adds this energy to a fluid stream in a centrifugal compressor, and an integrated conformal can be used in both types of centrifugal devices vortex generator adjustable in all respects for local flow conditions as a new project to increase efficiency and improve performance.

[00194] Gondola frameworks: An engine nacelle is an example of a generally cylindrical streamlined body attached to a fuselage or wing by means of a pylon, mounting device or mounting rod with mutual interactions of the fluid flow. Any undesired pitch and yaw with respect to the incoming fluid flows on this attached streamlined body can generate significant drag and turbulent flows due to flow disruptions, for example, on suction surfaces downstream. Engine nacelles are integrated into the engine's inlet and outlet fluid flows to provide accurate inlet and outlet conditions for a closed engine.

[00195] In FIG. 8 shows a generally cylindrical nacelle body 140 attached to the wing body 141 by a mounting pylon 142. As an example of a turbofan engine, the drawing shows a grill 143 of fan blades at the inlet of the nacelle after air dispersion in the region of the front edge of the nacelle and inlet sections of the cold air duct. As shown in the drawing, an integrated conformal vortex generator matrix 144 is integrated into the front edge of the nacelle to improve flow adhesion and reduce drag in the nacelle’s internal duct and on the outer surfaces. This matrix 144 of a conformal vortex generator integrated in the leading edge may also be supplemented by an overlay of matching and replaceable elements of the conformal vortex generator of the erosion protection system, if in this case surface erosion and / or durability are a problem.

[00196] The drawing shows an additional matrix 145 of a conformal vortex generator built into the inlet of the fan to improve the air supply to the ends of the fan blades and reduce the need to control the active absorption of the boundary layer at the inlet portion of the fan ends. Such matrices of the built-in conformal vortex generator can be constructed in both surfaces of the internal cold air duct system to eliminate flow stalls on the convex and concave surfaces of the duct and minimize the aerodynamic drag of the turbulent boundary layer. These conformal vortex generators integrated in the duct provide increased volumetric curvature of the duct surface or shortened ducts and reduced motor size for new designs. In such enlarged surfaces, a sequence of conformal vortex generators with appropriate spacing can be used, in which the jets of the end vortices expand before they burst, or before the flows of the boundary layer begin to show a tendency to separation bubbles or excessive loss of thickening. This approach defines the closest expedient separation of conformal vortex generators, and the separation determined by the dynamics of the fluid. Since the new designs of the most modern nacelle are molded composite structures, the matrices of the integrated conformal vortex generator can be included directly at the design and manufacturing stage to improve energy efficiency and functionality.

[00197] An outlet nozzle of the cold duct may also have a matrix 146 of the outlet conformal vortex generator of the cold duct, in particular, on the outer and / or inner surfaces in front of the local trailing edge of the cold duct to improve mixing of the streams, noise signatures of the cold exhaust and the fan outlet, and also to reduce drag. In the outlet hot section of the nozzle, a similar matrix 147 of the outlet conformal vortex generator integrated in the hot duct can be embedded in the outer and / or inner surfaces of the duct in front of the local trailing edge and / or in the protective cone 148 to improve flow mixing and breakdown of the vortices, as well as Improving exhaust noise signature with reduced drag. To stop the intense cracking of the hot exhaust, an additional thin cylindrical ring (s) of the matrix 149 of the destructive swirl of the conformal vortex generator can be added to the expanding output stream, for example, between the protective cone 148 and the trailing edge of the hot section of the duct to induce vortex jets into expanding clots hot exhaust swirls to destabilize and break down the swirls before they can transmit a large amount of acoustic o noise and shock effects in transient vortex traces. The support struts for this conformal vortex generator breakdown swirl matrix 149 and the turbine rear support struts in the exhaust gas streams may also include integrated conformal vortex generator matrices to add additional vortex jets to control exhaust noise.

[00198] In the mounting rack or pylon 142 of the nacelle, flow mixing fairings are used that are converted into supporting wings and the nacelle of the hull, and they may also include a conformal vortex generator matrix 150 integrated into the leading edge of the pylon to improve flow and reduce drag flow around the surface (mostly vertical) pylon. The wing may comprise a conformal vortex generator matrix 151 embedded in the leading edge of the wing and a secondary conformal vortex generator matrix 152 embedded in the wing (in particular, in the discharge surface).

[00199] In other structures attached by struts or pylons, conformal vortex generators can also be used to control flow stalls and flow around a body that is closed to incoming flows, such as, for example, a fuel tank or a weather radar container, and the like. as well as the front of the casing, which is a nose tip similar to a fan impeller coke 153. Since the coke 153 rotates with the resulting oblique inlet air flows, an oblique conformal vortex generator matrix can also be used in it. The nasal tips may have corresponding nasal caps with correspondingly inclined conformal vortex generators, or they may be designed with a matrix of an integrated nasal conformal vortex generator to reduce aerodynamic drag.

[00200] These attached streamlined body structures are also an effective form of closed (and / or open ends and) “turned inside out” ducts, with their primary fluid flows and losses on the “outer” streamlined surfaces. In some embodiments, a streamlined body having a given kinetic and / or total energy may require separation or firing to continue its free flight, such as the Spaceship One suborbital spacecraft built by Virgin Galactic, which is detached from the launch platform, or streamlined body like a shell. In these cases, the use of conformal vortex generators can also improve the energy efficiency of the streamlined body (i.e., the range) and the dynamic properties of the fluid stream, for example, adhesion and / or separation of the stream, and movement, which also provide the ability to achieve an improved trajectory and / or stability the way.

[00201] Duct flow paths: Most of the surfaces of most fluid flow treatment devices, such as a jet engine, consist of channeling surfaces directing fluid flows to the optimal locations of the structure in different sections and between them to process the fluid flow, these surfaces are limited by the angle of rotation of the flow or the direction of flow that they can enter before separation of the fluid flow or thickening of the boundary layer is induced I, causing energy loss. These ducts or pipelines, and even external volumetric surfaces, are other flow treatment devices that can be improved using an integrated conformal vortex generator. In FIG. 9a shows a typical duct or conduit 160 for a fluid stream that is analogous to a plurality of conditions in surfaces washed by a fluid stream, examples of an air conduit and conduit. The local cutout shows the seam 161 of the duct in the section of changing the direction of flow, and having a reduced diameter located upstream of the duct 165 contains a matrix 162 of an internal conformal vortex generator integrated into the duct structure at the end of the trailing edge, which then passes into the duct 166 downstream optimal location, and these ducts are connected, for example, by crimping and soldering or welding to seal and complete the connection of the improved pipeline or air water. The described construction is one implementation option that provides the possibility of constructing a duct or pipe transition equipped with an internal matrix of an integrated conformal vortex generator, and this transition reduces flow stalls and aerodynamic drag of convex surfaces located downstream of the duct or pipe, and also reduces drag on concave surfaces when surfaces or ducts change direction or diameter in the same way as a odinamicheskaya surface or other surface of the body in the undisturbed fluid stream as described above. Depending on the manufacturing method of the duct or pipe, material, diameters, wall thickness and geometric shape of the cross section, any number of stages, for example, stamping, forging, molding and machining, can be used to embed a conformal vortex generator matrix in an optimal place on the inner surfaces or outer surfaces if the fluid stream flows outside the surface of the body.

[00202] In FIG. 9b shows a matrix 182 of a conformal vortex generator integrated in an insert for an air duct that can be mounted in a straight section of a duct with a constant cross-section or a pipe with a slightly increased diameter and then crimped or otherwise secured in the best position with the tips of a conformal vortex generator 183 integrated in the insert for the duct facing upstream of the fluid. In this case, the input of the insert 184 has a very thin and sharp edge to minimize perturbation of the input stream, and the input surface 185 of the insert has a very small entry angle facing back to the point 186 of the step thickness. This long, low-angle duct convergence provides minimal flow variation and disturbance before it reaches the conformal duct section with the correct step height at 186 in the step thickness before entering the conformal vortex generator steps. An additional slot 187 for the duct insert can be used to facilitate the insertion of a slightly compressed conformal vortex generator matrix 182 into the duct with its subsequent expansion and fixing in place, or using the fastening method to fix the device in place. The flow directional gap in the matrix is acceptable and has minimal impact characteristics. It should be noted that between the step thickness point 186 and tip 183, the flow stabilizes as parallel to the middle surface of the duct and so that when the intersection of the steps of the conformal vortex generator has an optimal surface vector to obtain the best flow cutting and re-energization of the boundary layer downstream. The key feature of these matrices of the conformal vortex generator integrated into the duct is that they operate continuously across the entire flows of the boundary layer at the surface of the duct that they intersect, and also that there is no unmodified boundary layer between the maximum lengths of the transverse flow around the V-shape conformal vortex generator matrix, between the cross sections of the input and output planes of the fluid flow, including the case when the matrix limits the entire perimeter meter duct. In a less optimal case, in which the conformal vortex generator matrix does not have a streamlined cavity for the constant-height stage section (which neutralizes the initial advantage), this continuity of the function of modifying the transverse boundary layer layer distinguishes matrices of the modified conformal vortex generator of these types from the group of known discrete vortex generators. The use of the slot 187 of the insert for the duct also provides the possibility of alternative manufacturing matrix 182 conformal vortex generator embedded in the insert for the duct, essentially in the form of a spiral with the angles of intersection of the conformal vortex generator modified for the spiral angle so as to intersect the flows of the boundary layer along the walls of the duct under optimal angles. If the spiral contains more than one turn, the efficiency decreases depending on the decay rate of the upstream vortex jets before they collide with the next V-shaped steps of the conformal vortex generator located downstream. This means that applying the sequence of matrices 182 of the conformal vortex generator integrated in the duct insert in the direction of flow requires that these matrices are optimally spaced from each other for best results.

[00203] The use of conformal vortex generators in the inner surfaces of pipelines and ducts can also be accomplished by sputtering or molding coating materials that can be applied or applied in the form of a film on plastically curved, machined or sanded to achieve the correct geometric shapes of the surface. These coatings can be applied in several layers and can also be provided with mechanical and corrosion / chemical protection of the underlying surfaces of the duct or pipe.

[00204] Another embodiment of the flow control is the known use of the internal flow-turning blade 163 in the duct passages, which allows the introduction of an increased flow turn through the duct, but these designs introduce aerodynamic drag, since they act like a grating of aerodynamic surfaces to change the direction of flow of the fluid Wednesday. The flow-turning matrix 164 of the conformal vortex generator integrated into the blade can be integrated into the suction and / or injection surfaces of the flow-turning blade 163 to reduce aerodynamic drag and to increase the angle of rotation of the duct or pipe before flow stall, as well as to enable the creation of new designs, for example , piping, duct or S-channel with more compact geometric shapes and / or reduced energy losses.

[00205] On the surfaces of the enlarged ducts and passages, which may also be required to be heat resistant, a mosaic pattern may be minted, for example, of triangles, rectangles, hexagons or other polygons, which strengthen and increase the strength and mechanical efficiency of the cooled component of the sewer panel and provide the ability to integrate conformal vortex generators and the option of adding a firmly held and non-cracking insulating coating. In FIG. 10a shows a cross-section of a wall duct that has a stamping or embossing relief of interconnected hexagonal cells, which may additionally have the functionality of the steps of the built-in conformal vortex generator. Downstream, the smooth surface of the duct 170 (on the opposite surface, as shown in FIG. 10a), which is in contact with the fluid flows, is located to the left and bottom (downstream) of the matrix stage 172 of the relief conformal vortex generator. Embossing initially raises the vertical walls 173 with a substantial radius 171 of the root connection supporting the wall (with a radius that provides more than a right angle and is equal to the height of the wall), which creates an interconnected matrix of stringer sections, characterized by increased moments of inertia and the lowest stress center (which is clearly different from the sharp radii of the rectangular joints of the walls with the base described by Lutjen '342) and improved strength and heat resistance to remove heat fluxes from downstream of the inner flooring 174 and the inner flooring 175, located downstream. The vertices of the vertical walls 173 can also be further deformed to roll the sharp edges of the walls into the lip and increase the edge strength and resistance to damage during processing. Cooling air can flow through the edges of the vertical walls 173 to remove heat with good thermal conductivity and dissipate down to the surfaces of the walls and inner floor below. Depending on the alloy used, in order to minimize the destruction of the material due to the formation of stresses, it is better to use this embossing or an efficient stamping method at the ductility temperatures of the metal (preferably in vacuum), which also allows precise control of the temperature distribution in the material, oxidation of the surface and minimum press force during compression / embossing. These matrices and surface steps can also be created using other methods, for example, investment casting, blasting / hydraulic stamping, etc.

[00206] The manufacture of this improved section of the duct panel shown in FIG. 10a also provides the ability to integrate a heat insulating coating into non-smooth faces. In FIG. 10b shows a relief upstream region 176 of the duct panel with an upstream heat-insulating coating layer 177 facing the hot fluid stream that enters the conformal vortex generator matrix 178 embedded in the heat-insulating coating and then down to the layer 179 heat-insulating coating downstream of the closing panel 180 of the duct located downstream. It should be noted that the hot fluid stream flows along the side of the heat insulating coating in this arrangement, and is opposite to the side and flow direction of the similarly formed part shown in FIG. 10a. This embodiment takes advantage of, for example, a hexagonal matrix and molded vertices of the vertical walls 173 to reliably hold subsections of the heat insulating coating, such as the closed heat insulating coating element 181. The layer of heat insulating coating can be performed by any of the known methods of applying heat insulating coating, materials and mutual overlap. The cracking of thinner sections of the heat-insulating coating between the held closed elements 181 of the heat-insulating coating can be controlled by the temperature of application of the heat-insulating coating on a metal substrate. This design pre-sets the mechanical stress due to the different coefficients of thermal expansion between the substrate and the integrated vertical walls 173 and the subsections of the insulating coating or lamellae. They can be installed between operating temperature or cold conditions to block cracking of the heat insulating coating or to allow uniform separation of the coating into closed elements 181 of the heat insulating coating. After that, the heat-insulating coating covering the area of the step can be machined or ground to create improved edges of the steps of the heat-insulating coating material for the conformal vortex generator matrix 178 embedded in the heat-insulating coating, and the rest of the surface of the heat-insulating coating can also be processed to achieve surface uniformity.

[00207] An inclined additional nozzle 189 of the duct can be located downstream of the step matrix 178 of the conformal vortex generator integrated in the heat-insulating coating, or the step matrix 172 of the embossed conformal vortex generator, and this nozzle (or matrix of nozzles) can conduct means into the fluid stream for the formation of film cooling of the surface, and / or conduct a stream that additionally increases the energy of the boundary layer from the injection source of the fluid flow under the stage area, as ano, for example, the stator airfoil low pressure turbine, since this surface is stationary. Additional ducts can be added to the surfaces of the duct in the steps of the conformal vortex generator after the step and / or the stepped cutting guide, but they are not shown for purposes of clarity.

[00208] In FIG. 10a and 10b show a substantially flat panel, but this method can also be applied to surface matrices and steps with volumetric curvatures for use in sections of the sewer surface of any configuration. In these hexagonal features, the best conformal vortex generator flow angles can be used, for example, approximately 22 ° at the edges downstream, and triangular or rhombic shapes can be used for reduced sections of the heat-insulating coating, but this leads to an increased ratio of the mass of the metal in the walls to the mass metal in the sections of the flooring. The thickness of typical sections of the duct can be from about 0.5 mm to 3 mm, but this is not a limiting condition, depending on working pressures, etc., moreover, the wall, flooring, type and size of polygonality, as well as the thickness of the insulating coating can be selected according to design requirements.

[00209] In the cooled turbine blades, these polygonal holding features can be used to attach a heat-insulating coating to the surface of the leading edge that can withstand a high inertial load, and in this example, if a fountain head is required to cool the leading edge, it can penetrate after applying the heat-insulating coating and machining steps, etc. The surfaces of the non-insulating coating located after the stage can be cooled by means of cooling flows introduced, for example, by elements of the injection channel 95 for the fluid from the rear inclined nozzle, as well as by internal cooling of the blade skin and cooling slots of the trailing edge.

[00210] Pipes, tubing for general use, nozzles, and the like, may include appropriately spaced conformal vortex generators, or may be equipped with such vortex generators to reduce aerodynamic drag of the surface and increase energy efficiency. For a spiral welded or one-piece pipe, embossed or machined internal conformal vortex generators can be easily integrated using any suitable manufacturing method before spiral forming and welding. It should be noted that it is important that the separation between conformal vortex generators must be large enough so that relaminarization can occur and the end vortices can expand, otherwise the result will be an undesirable increase in aerodynamic drag, like a well-known turbulizer or a traditional vortex generator matrix.

[00211] Conformal vortex combustion chamber: FIG. 11a shows, in an oblique partial cross-section, the general arrangement of a subsegment of an annular compact and efficient conformal vortex combustion chamber or gas generator design that uses an integrated conformal vortex generator to provide an improved design. Combustion chambers may have the capacity of a compressor used as an oxidizing agent to burn fuel injected into a controlled exothermic reaction to generate heat and / or create an accelerated fluid stream from which work can be extracted.

[00212] The outer supporting wall 200 of the combustion chamber housing is connected to the high pressure compressor housing via an input mating device 201 (connecting the outer and inner walls to the high pressure compressor), and is also connected to the high pressure turbine housing by the output mating device 202 to maintain high pressure reliability since the combustion chamber is usually the region of the highest pressure in the device. The input guide vane 203 of the combustion chamber and the output guide vane 204 of the combustion chamber create peripheral continuity of this subsegment of the combustion chamber in the full matrix and volume of the combustion chamber. These guide vanes 203 and 204 of the combustion chamber can be further tilted with respect to axial flows and twisted and can be used as part of the stator structures to disperse and de-turbulize the output stream of the high pressure compressor (using vanes 203) and / or also to determine the output angles of the flow of the combustion chamber in a radial dimension, and thus effectively act as a compact integrated inlet stator vane for a high pressure turbine (using vanes 204) with sufficient cooling blades to enable optimal design of the angles of the output stream directly into a high pressure turbine first rotary grating.

[00213] The input mass of the fluid stream is supplied to the combustion chamber at a speed and temperature set by the high-pressure compressor (and possibly its output direction-changing blades) through the hole E and then dispersed and slowed down by the deflecting surfaces of the input of the combustion chamber, and then divided into three flows flowing into the upper bypass hole F, the lower bypass hole H and the combustion chamber opening G operating on the enriched mixture. A matrix 205 of a conformal vortex generator integrated in the combustion chamber inlet device is added along the inner perimeter of the inlet E at this point of the expanding scattering inlet to suppress air flow stalls, reduce aerodynamic drag, and make it possible to create a more streamlined and / or more compact design for the input stream, and the specified matrix can also be applicable to the air duct surfaces of the known combustion chamber.

[00214] The calculated fraction of the mass flow in the hole G flows between the lower combustion chamber guide 213 provided with a conformal vortex generator and the combustion chamber guide 225 provided with a conformal vortex generator, where fuel is introduced into the stage and the vortex jets flow from the conformal vortex generator matrix 207 embedded in the lower ( and upper) the mixer of the combustion chamber, and this enriched fuel mixture further slows down to the speed of the combustion front in the scattering region downstream of the hole I, where tsya initial combustion enriched mixture. Then, after a predetermined time, the combustion front of the enriched mixture passes into the hole J for the combustion of the lean mixture, where additional bypass air is added, and combustion smoothly ends directly in the second stage of combustion of the lean mixture, which then completes the oxidation of the fuel with the generation of low-nitrogen oxides. Final combustion / oxidation of the fuel ends at the moment of transition to the outlet K next to the outlet mating device 202.

[00215] At the exit from the opening I, in particular, on the trailing edges of the guides 213 and 225 provided with conformal vortex generators, the combustion matrices of the upper and lower combustion stabilizing trimmers 216 capture and hold vortexes of burning fuel spread along the width of the guide on the front and rear surfaces of these trimmers . Distributed along the width of the guide, the output vortices created by the combustion stabilizing trimmers 216 also act like Gurney trimmers that change the effective lifting force and aerodynamic resistance to further increase the bevel of the flow in the lower direction from the trailing edge and facilitate mixing of air from the openings of the bypass ducts F and H in the opening cavity J for burning lean mixture. Also, gaps 215 were added between trimmers to group the fraction of vortex jets directed along the chord after combustion of the enriched mixture leaving the hole J, for mixing with the secondary circuit and completing the continuous cycle of the lean mixture. As with the low-pressure turbine trimmer (LET) trimmer (LET) and fan blades, these combustion-stabilizing trimmers 216 can be tilted and positioned in a way other than perpendicular to the fluid flow.

[00216] If the flow rate of the fluid increases at the inlet of the combustion chamber (and, therefore, in the region of the opening I), the initial combustion front of the enriched mixture recedes back into the region of the opening I until the dispersion of the duct balances the local velocity of the fluid to match the flame propagation velocity in these physical conditions. This sets the minimum dispersion (surface curvature) required for the rear section of hole I to ensure combustion stability, and at maximum flow rates, the combustion front must be in front of the combustion stabilizing trimmers 216 and the trailing edge exit. The ratio of the hole sizes E, G and I effectively controls the speed of the fuel mixture in the combustion volume of the enriched mixture, as described above with respect to the output speed of the high-pressure compressor. The ratio of the openings F and H to G controls the flow rate for burning the enriched mixture, bypassing, cooling and burning the lean air mixture in the combustion chamber. The transverse vortex jets on the front and rear surfaces of the mechanically robust flame-stabilizing trimmers 216 also act as a very stable and flame-retardant backup ignition source when the elements of the igniter matrix 227 are turned off. Since the combustion volume of the enriched mixture generates a large amount of heat on the local streamlined surfaces and combustion stabilizing trimmers 216 and the trailing edge, the upper cooling flow path 226 equipped with the conformal vortex generator and the lower cooling flow path 212 provided with the conformal vortex generator are added to the adjacent upper conformal vortex regenerator adjacent to each other 224 air ducts and a lower body 214 of the air duct equipped with a conformal vortex generator, respectively. The flow of cooling fluid in said upper and lower cooling channels provided with a conformal vortex generator is configured, for example, by a lower cooling inlet 221 defined by a lower guide 213 of the combustion chamber and a lower duct 21 provided with a conformal vortex generator. The outlet cooling air from said cooling flow paths 226 and 212 provided with a conformal vortex generator is directed into the mass flows in the opening J. These cooling channels are integrated into the guide bodies of the combustion chambers provided with a conformal vortex generator, since they are thicker flow control aerodynamic surfaces in the air duct system of the combustion chamber, but if these guide aerodynamic surfaces are thin enough and cooling is sufficient, the outer ekaemaya flow guide surface able to cool the airfoils without the need for internal cooling channels. It should be noted that an embodiment of the combustion chamber, shown as an example in FIG. 11a is generally symmetrical about its mid-plane, so that reference numbers denoting paired elements are omitted in some cases for clarity of the drawing, but are actually implicitly present in accordance with the symmetrical design of this particular embodiment.

[00217] Most of the energy released in the combustion chamber occurs in the fluid flows in the volume bounded by the hole J at the end of the lean fuel combustion, so that the cooling surface 217 of the lower wall and the cooling surface 220 of the upper wall are added to shield the external pressurized surfaces of the combustion chamber from this intense heat, and these structures intersect part of the fluid in the ducts F and H as carriers of film cooling. To protect the surfaces of the outlet guide vanes 204 on both sides of the combustion chamber, screens are added, similar to the side cooling surface 219, which also intersect the incoming fluid in the air ducts F and H (from the area in front of the casing equipped with conformal vortex generators of the combustion chamber) as a film cooling medium. On the cooling surfaces 217, 220 and the surfaces of the elements 219, a known heat-insulating coating facing the volume bounded by the opening J can be used, or the coating can be made in the form of a ceramic matrix composite panel (CMC) to reduce heat fluxes and damage caused by oxidation, in which aerodynamic drag reducing matrices of the conformal vortex generator matrix similar to the lower cooling surface matrix 218 provided with nym vortex generators on both surfaces to reduce drag. The known heat-insulating coating can also be applied, for example, over part of the surfaces of the guides 213 and 225 of the combustion chamber to reduce local heat flux directed to the surfaces of the combustion chamber, and then this energy can be available at the output of the combustion chamber for transmission to the high-pressure turbine section for doing useful work. The channel flow concepts illustrated in FIG. 9a, 9b, 10a, and 10b can also be additionally used to improve any of the surfaces in a given combustion chamber to improve flow and reduce drag.

[00218] The ignition fuel chamber 208 of the high pressure and the primary fuel chamber 211 of the increased pressure are fed by ordered flows of filtered fuel and have a separate inclined ignition fuel nozzle 209 and the primary fuel nozzle 210, which conduct the fuel flows into the stepped regions of the matrix 207 equipped with a conformal vortex generator mixer. The flow of the fuel pilot nozzle 209 is reduced and can be introduced closer to the minimum point of the conformal vortex generator for reliable destabilization and atomization of liquid fuel particles by means of intense jets formed by the step of the vortex, overcoming the viscosity of the fuel and adhesion forces, and then part of this enriched fuel mixture is fed into the vortices. formed by the tips of the conformal vortex generator, and back to the region in which the decrease in velocity downstream to the speed of flame propagation providing a possibility of ignition. Thus, a high fluid flow rate is possible in the stepped regions of the matrix 207 equipped with a conformal vortex generator mixer, which provide high vortex mixing intensity and delay initial combustion in the opening I. If a higher output energy is required, the pressure in the increased pressure primary fuel chamber 211 in a similar manner pushes fuel through the primary fuel nozzle 210 into the stepped areas of the matrix 207 equipped with a conformal vortex generator mixer. This example shows that the inclined primary fuel nozzle 210 is located closest to the areas of the tip of the conformal vortex generator and injects or sprays a portion of the fuel into the highest vortex jets to ignite it. The use of two or more fuel injection matrices, as well as streamlining and changing fuel consumption, if necessary, provide the opportunity for improved regulation of fuel flows in accordance with changing workloads or the required amount of exothermally generated heat. Actual nozzles can have other configurations: dimensions, geometrical shape, and implementation options, and can be placed in various places that can take advantage of an improved, low-drag fuel injection and mixing by using vortices excited by matrices of the built-in conformal vortex generator. Conformal vortex generator matrices provide a path with low drag to add multiple combined reduced-sized nozzles for fuel flow with intensive mixing and grinding of liquid particles. Fuel gases such as natural gas (methane) or hydrogen and the like can also be used in this combustion chamber, in which the swirl does not break the associated liquid droplets, but provides the best fluid / fuel inlet mixing. The energy of evaporation of the liquid fuel stream can be used to balance working cooling, for example, the steps of the matrix 207 equipped with a conformal vortex generator mixer, high pressure fuel chambers, nozzles and adjacent areas, and can be increased by improving manufacturing methods, materials and design for controlling or separation of heat conduction downstream, etc.

[00219] In FIG. 11b shows a sectional example of an assembly of downstream housings 213, 225, 216 and the like, in the form of, for example, a ceramic insert, a ceramic tail 228 with an additional matrix 229 equipped with a conformal vortex generator of an interface device integrated in the transition part of the housing after the fuel nozzles, in order to reduce heat transfer to the high pressure fuel chambers, or this part located downstream, facing the hole I, may have a metal coating with a heat insulating layer and the like, for izheniya heat transfer through the matching surface 229 of the matrix embedded in the interface device conformal vortex generator. The attached ceramic tail portion 228, located behind the modified aerodynamic surfaces 213 and 225, supporting flows in the channels of the holes F and H and the combustion hole I of the enriched mixture, makes it possible to simplify the design by eliminating the need for cooling flow paths 226 and 212 equipped with a conformal vortex generator, etc. The conductive elements for the igniter matrix 227 can be embedded or laid in ceramic insulation or in a ceramic-matrix composite housing, or in openings leading from the main cavity, for example, of heat-resistant metal like tungsten, with a spark gap to the second conductor or section of the cooled wall, in as a result, a structure that can withstand very high combustion temperatures can be created. An additional oblique injection nozzle 230 of the combustion chamber is shown located in the stage of the conformal vortex generator of the matrix 229 equipped with the conformal vortex generator of the mating device of the upper or outer surface of the ceramic tail 228. Since the pressure in the F / H hole and the hole I can be changed and balanced relative to the inlet pressure in the hole E , can be carried out the introduction of the input sampled air and cooling the fluid from the upstream stream for a small injection into the core region of the ceramic tail portion 228 and subsequent deflection of this cooling stream through the injection nozzle 230 of the combustion chamber also to increase the momentum of the boundary layer of fluid flows on the side of the opening H and / or opening I of the ceramic tail portion 228. Examples of the injection nozzle 230 of the chamber combustion can also be applied to the input matrix 222 provided with a conformal vortex generator on the outer surface of the duct and the matrix 223 equipped with a conformal vortex generator on the inside enney surface of the duct. Additional expansion grooves after the step and / or stepped cutting guide may be added to the ceramic tail portion 228, but are not shown in the drawing for clarity.

[00220] Shown in FIG. 11b, versions of the modified aerodynamic surfaces 213 and 225 are in the form of thin-walled castings and high-pressure fuel chambers, these components can be solid or can be made using any combination of manufacturing methods to ensure the correct flow geometry. The additional matrix 229 of the conformal vortex generator integrated into the coupling device may have its offset of the minimum and tip points or a different step in the direction from the conformal vortex generator matrix 207 embedded in the mixer to improve fuel mixing. The fuel injection pressure is controlled to ensure the appropriate regimes of jet flows at the required working load, so that the pressure of the incoming liquid fuel of any type does not fall below its vapor pressure before the fuel is exhausted from the nozzles so that the steam plug does not block the fuel flows.

[00221] For other surfaces of the combustion chamber, other preferred embodiments of the conformal vortex generator matrices that reduce the aerodynamic drag of the combustion chamber can be used, and the conformal vortex generator matrix 207 integrated in the mixer is shown as a clearly higher step design since it is primarily used for reliable sufficient mixing of fuel and the formation of appropriate vortex turbulence, and performs the auxiliary function of reducing aerodynamic drag. The matrix 206 of the conformal vortex generator embedded in the middle part of the surface, and the matrix 222 of the conformal vortex generator embedded in the outer surface of the duct, and the matrix 223 of the conformal vortex generator embedded in the inner surface of the duct located on the upper and lower surfaces, respectively, are also additionally added to reduce the total aerodynamic drag of the surface from streamlined surfaces and providing a wider range of Reynolds numbers without induction the loss of stall in the combustion chamber and on the sewer surfaces.

[00222] More than one pair of combustion chamber guides 213 and 225 may be used, or a single combustion chamber guide 213 (possibly with a ceramic tail portion 228) may be used, configured to improve flows within a single combustion chamber bounded by the chamber supporting wall 200 combustion, determining the geometric shape of the structure, etc. The main structure can be modified essentially from the construction of a flat subsegment with a constant radius (from the axes of the motor shaft), as shown in FIG. 11a, to a structure with guides 213 and 225/228 of the combustion chamber merging into a circular symmetrical structure (similar to a venturi), if this embodiment is more effective for the available volumes of the structure. The guides 213 and 225 of the combustion chamber can also be configured radially to efficiently use the conformal vortex generator matrix 207 integrated in the mixer, aligned in the radial direction, and can act like combinations of the stator inlet blades of the high pressure turbine with integrated fuel injection holes and combustion chambers. Examples of the design of a combustion chamber equipped with a conformal vortex generator can be easily modified for other types of flow, such as folded and reversing flow paths and combustion chamber paths, such as, for example, in the PW300 turbine described in Allison '250 and other smaller turbines.

[00223] You can also use this conformal vortex generator vortex mixing strategy to improve the flow of both mixing mating devices and air ducts / pipelines in other types of combustion chambers, such as, for example, liquid fuel and oxidizing combustion chambers, and to power centrifugal turbopumps (with additional built-in into the impeller by conformal vortex generators) for applications such as a hydrogen / liquid-oxygen rocket or thruster, in which some of the working fluid sneeze environments are possible in the cryogenic condition before the ignition point of the flame front and require careful mixing at high speed before ignition and extending through the discharge nozzle for generating thrust. Combustion chambers of this type may be a plate-type mixer with holes for flow injection and may contain conformal vortex generators built into their perimeters to create vortex output jets to improve combustion stability and mixing when throttling or changing fuel flows.

[00224] Another embodiment is a solid fuel combustion chamber in which fuel is attached inside a pressure protective enclosure, or (actually) a semi-closed duct / pipe structure. Combustion is developed using an oxidizing agent mixed entirely with solid fuel, or using an injected oxidizing stream (similar to a Rutan / Virgin Galactic engine using N ₂ 0), and energy-based combustion products (in fact, the input fluid stream to be processed) pass through the outlet nozzle to create traction. The walls of the containment / duct and / or nozzle may be treated as in the previous embodiments of the conformal eddy-oscillator integrated in the duct shown in FIG. 10, to use conformal vortex generators to create a surface mating device for the output stream with a small frontal resistance, which manifests itself when fuel is consumed, and a heat-insulating coating can be integrated along with additional cooling nozzles, such as, for example, in a high-pressure turbine blade. Losses associated with surface aerodynamic drag and impact loads on the streamlined surfaces of a traditional conical / bell-shaped exhaust nozzle or a commercially available exhaust nozzle of the Aerospike type can be reduced by improving and / or modifying said surfaces using conformal vortex generators adapted for this purpose. Conformal vortex generators can also be used in a mixing chamber for self-igniting fuel, which acts like a combustion chamber, or they can be used in attached nozzles.

[00225] Fuel supply lines, pumps, ignitors and other auxiliary systems and the like are not shown in the drawings, since they are generally standard and correspond to the general form and functions of the prior art. In FIG. 11a and 11b show, in sectional view, the separation and the ratio of the fluid flow in the openings, the transport time of the fluid, the dimensions of the components and products and their location, which, if necessary, can be modified over a wide range to meet the design requirements for the working environment and fuels, etc., based on the fundamental concept of using the built-in conformal vortex generator to reduce aerodynamic drag to reduce aerodynamically resistance, improved fuel atomization and mixing in a compact combustion chamber having high performance, low emission and low power consumption. Shown in FIG. 11a and 11b, the overall dimensions of, for example, a CFM-56 combustion chamber or segment, can be scaled to increase or decrease size and length, etc., in accordance with the requirements of a particular gas generator application. If the total internal surface area of the new conformal vortex combustion chamber is configured similarly to the known combustion chamber, this new design provides the possibility of a significant absolute reduction in aerodynamic drag and loss compared to the known design and the ability to design the duct path and sections of the aerodynamic surface for accurate divergence / dispersion and flow rates to ensure reliable combustion.

[00226] These unexpectedly diverse ranges of types of high-temperature and / or high-strength embodiments described in this application for improving fluid flows in devices and increasing energy efficiency are an unexpected result and the actual possibility of using an integrated conformal vortex generator, which is simply not practical or impossible using a traditional well-known vortex generator. In all the embodiments and modifications described above, in their most fundamental general sense, a new conformal vortex generator is used to process or control Newtonian fluid flows to obtain a level of benefits such as improved energy efficiency and / or extended control ranges not possible in the prior art.

[00227] Thus, while the information disclosed in this application details preferred embodiments of the present invention, they are not intended to serve as material limitations on the scope of protection of the claimed invention, and any features and alternative designs that may be obvious to a person skilled in the art be considered included in this application. Therefore, instead of being limited to the specific features described in relation to the preferred embodiment, the scope of protection of the present invention is formulated and specifically described in the following claims.

Claims (38)

1. The method of aero / hydrodynamic regulation of the primary flow of Newtonian fluid in a radial turbomachine, containing: (i) means of the source of the primary input fluid medium for providing a source of the specified stream of primary Newtonian fluid and transmitting part of the specified stream of primary Newtonian fluid to (ii) a radial fluid-changing surface, through at least one conformal vortex generator that processes part of said primary Newtonian fluid stream, followed by transferring part of said processed Newtonian primary fluid stream to (iii) an outlet mating device for the fluid located downstream and containing a channel for introducing a fluid located in the specified output mating device for a fluid located downstream, while the specified channel for introducing a fluid transmits a secondary stream Newtonian fluid to the lowest levels of the boundary layer located downstream, and the specified stream of the secondary Newtonian fluid downstream of the specified vortex generator it reduces the energy level from the first energy to the second energy of the indicated lowest level of the boundary layer located downstream and / or reduces the temperature from a higher to a lower temperature level. 2. The method of claim 1, wherein said conformal vortex generator is an integral conformal vortex generator that is entirely integrated into a radial fluid flow surface, consists of the same material, and is made entirely within said radial fluid flow surface. 3. The method of claim 2, wherein said integrated conformal vortex generator is configured during the design and / or test process to achieve improved performance. 4. The method of claim 1, wherein said radial fluid flow-changing surface is an element of a group comprising channeling means for a fluid flow, a bypass fan, a compressor, a pump, a combustion chamber, a rotor aerodynamic surface, a stator aerodynamic surface, an air screw or a turbine, and uses at least one said conformal vortex generator on said radial fluid flow surface. 5. The method according to p. 4, according to which the specified channel for introducing a fluid is connected by a pressure chamber with a source of fluid for introducing a fluid flow and adding an additional impulse to the boundary layer downstream of the specified conformal vortex generator, which is designed so that doesn’t pass into incoming undisturbed streams. 6. The method according to p. 5, according to which the specified channel for introducing a fluid made with the possibility of providing resistance to clogging with garbage and uses additional channels for introducing a fluid. 7. The method according to p. 6, according to which the specified channel for introducing a fluid feeds the cavity for injection of a fluid stream, configured to introduce a pulse of the fluid flow into the lower boundary layers downstream of the specified conformal vortex generator. 8. The method according to p. 6, according to which the specified channel for introducing a fluid discharges the fluid into the cavity for injection of the fluid flow, configured to increase the performance of the distribution of the fluid. 9. The method according to p. 6, according to which the specified channel for introducing a fluid adds a cooled fluid to the boundary layer downstream of the specified conformal vortex generator. 10. The method according to p. 4, according to which in the specified element of the radial fluid flow-changing surfaces, an expansion groove after the step and / or a stepped cutting guide is used further downstream of said conformal vortex generator and configured to direct the mass distribution of the undisturbed fluid flowing vortex jets. 11. The method according to p. 4, according to which in the specified element of the radial fluid flow-changing surfaces, the first specified conformal vortex generator closest to the leading edge is used, which generates unperturbed flowing vortex jets in the tip region and / or suppresses the thickening of the specified boundary layer in the region below flow direction, and additionally used is located on the surface closest to the trailing edge of the surface downstream of the second conformal vortex generator. 12. The method of claim 5, wherein said fluid source connected by said pressure chamber has a pressure that varies based on a fluid flow rate along said radial fluid flow surface. 13. The method according to p. 4, according to which a conformal vortex generator is added to the indicated element of the radial fluid flow-changing surfaces, which generates unperturbed flowing vortex jets in the tip region and / or suppresses the thickening of the boundary layer in the region downstream of the surface flow, and which applied before the gap between the surfaces of the fluid flow with relative displacements. 14. The method according to p. 4, according to which in the specified element of the radial fluid-changing surfaces of the surfaces using the specified conformal vortex generator, which is designed in such a way that debris captured by the specified fluid flows with sufficient energy to cause mechanical damage freely rises from the next surface . 15. The method according to p. 2, according to which the specified built-in conformal vortex generator is made in the form of a partially stepped height matrix built-in conformal vortex generator, configured to provide registration marks and reference alignment for an additional conformal vortex generator. 16. The method according to p. 7, according to which the specified cavity for injection of a fluid stream connected to the specified channel for introducing a fluid connected using the specified pressure chamber, is configured to use suction to draw a fluid stream from these lower boundary layers . 17. The method according to p. 16, further comprising a pressure chamber transmitting a fluid stream from a first cavity for injecting a fluid stream, a channel for introducing a fluid and a pressure chamber to a second injection channel for introducing a fluid and a cavity for injecting a stream a fluid located in the reduced pressure region of the aerodynamic surface of the body. 18. The method according to p. 4, according to which the specified located in the combustion chamber element of the radial fluid flow-changing surfaces contains the specified integrated conformal vortex generator, which generates unperturbed flowing vortex jets in the tip region and / or suppresses the thickening of the boundary layer in the region downstream on the surface, and which is additionally made with the possibility of combining the built-in inlet flow guides of the turbine stator surfaces with reduced energy losses. 19. The method of claim 1, wherein said radial fluid flow changing surface is used by a gas turbine engine that uses at least channeling means for the fluid flow, a compressor, a combustion chamber, and a turbine. 20. The method according to p. 4, according to which the specified located in the combustion chamber element of said radial fluid-changing surfaces includes said conformal vortex generator made on the surface of the combustion chamber and having an output nozzle as a means for delivering an output fluid. 21. The method according to p. 20, according to which the specified output nozzle, forming the exhaust stream of the fluid, contains an additional conformal vortex generator made on the surface of the nozzle. 22. The method according to p. 21, according to which additionally use a channel for introducing a fluid for introducing into the boundary layer of a stream of chilled fluid, which acts to cool the surface downstream. 23. The method according to claim 1, wherein said radial fluid flow-changing surface is used by a processing device for aero / hydrodynamic processing of a Newtonian fluid flow having an inlet connected to at least one built-in conformal vortex generator located in the duct or pipe, which connected to the output. 24. The method according to p. 4, according to which located in the compressor and turbine, these elements of the fluid-changing surfaces are combined to form a turbocharger. 25. The method according to p. 4, according to which the specified element of the channeling means for the fluid flow of radial fluid-changing surfaces is a surface of a streamlined body with closed or open ends, configured to reduce symmetrical resistance forces on the specified streamlined body. 26. The method according to p. 25, according to which the specified streamlined body proceeds to free flight with a predetermined kinetic energy to improve energy efficiency or increase the range or stability of the path. 27. The method of claim 4, wherein said element of radial fluid flow-changing surfaces comprises said conformal vortex generator having an inhomogeneous spatial geometry. 28. The method of claim 4, wherein said channeling means for a fluid stream is a closed surface region configured to contain a fluid stream, said region comprising embossed walls of closed geometric cells with wall supporting shank radii that are larger than the connection radii at right angles. 29. System aero / hydrodynamic regulation of the flow of Newtonian fluid in a radial turbomachine, containing: (i) an inlet fluid source for providing a source of said Newtonian fluid stream and transmitting a portion of said inlet fluid from the source to (ii) a radial fluid-flow-changing structure used by said processing device for aero / hydrodynamic processing of a Newtonian fluid stream by at least one conformal vortex generator that is capable of processing a portion of said Newtonian fluid flow by using a flow-deflecting step reduction, which collapses part of the lowest boundary layer of mass of the incoming specified stream of Newtonian fluid with the following s transmission of said processed portion to (iii) an output mating device located downstream of said conformal vortex generator transmitting a portion of said Newtonian fluid stream to the lowest levels of the boundary layer located downstream. 30. The system of claim 29, wherein said conformal vortex generator is an integral conformal vortex generator that is integrally embedded in a radial fluid flow surface that is made of the same material and is made integrally with said radial fluid flow surface . 31. The system of claim 29, wherein said conformal vortex generator is configured to generate aerohydrodynamic vortex jets that suppress the development of cavitation bubbles. 32. The system of claim 29, wherein said conformal vortex generator is configured to generate aerohydrodynamic vortex jets that change the propagation of an acoustic wave.

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