SA05260324B1 - Turbine Case Reinforcement in A Gas Turbine Jet Engine - Google Patents

Abstract

Abstract: The present invention relates to a low or high pressure turbine case which is machined on its outer surface to form circumferential notches. The grooves may correspond to the internal locations of the seals of the blades, or to the hot spots that are marked, for example. A stiffener ring may contract with an interference fit in each groove by inducing the temperature differentials between the ring and the cage. The radially compressive circumferencial force exerted by each ring can prevent the low or high pressure turbine cage from expanding as it would otherwise. In some applications, the stiffening ring can improve blade tip clearance, offset "hot spots", stiffen the cage, improve case cooling, or may have other benefits, depending on the specific application. Embodiments, notches can be prevented. In an alternative embodiment, C-rings, or multiple segmented rings, may be coupled together by hydraulic, electrical or other means and may be actuated by a controller to exert an adjustable circumferential compressive force in the direction of the radius. Other incarnations are described and claimed.

Description

Y

Strengthening the turbine cage in a gas turbine jet engine

Turbine case reinforcement in a gas turbine jet engine Full description Background of the invention el «gas turbine jet engine dia iad The blade has played a prominent role in inter-stage sealing blade tip clearance TF since the late nineties. The reason for this is due to the engine design 0 “NY” surrounding casing inclines between the ends of the vanes and the surrounding cage clearance changes as a result, in particular, of changes in the loads applied to the thermal and mechanical structures The largest in size at present is land-based and aero turbine engines and the High Pressure Turbine Case (“11010”). Je The turbine cage has large diameters that make each of them Low Pressure Turbine Case (“LPTC”) low pressure, and each of them becomes non-round, which exacerbates adel expansion, more prone to expansion, the problem of vane tip clearance. LPTC and HPTC clearance value decreases in fs vo 3a “Specific Fuel Consumption (“SFC”) can lead to sudden decreases in specific fuel consumption and engine efficiency as well as increased capacities compressor stall margin Compressor shutdowns for atmospheric engines in terms of payload range and missions.Excitingly, improved clearance adjustment can improve land engines' life and flight time.

YYY¢

. Time-on-Wing ("TOW") for atmospheric engines. The decrease in the Exhaust Gas Temperature ("EGT") limit is the main reason for the removal of an aircraft engine from service. 5 TY The Federal Aviation Administration ("FAA") authorizes a specific BGT 3a for each aircraft engine. The EGT in ANA is used to determine how well JHPTC | is performing 0 And it is used from EGT to estimate the temperature of the disk temperature sa ill within 110170. Once the components are damaged and the clearance between the ends of the feathers and the sealant on the inner part of the cage is increased, the motor exerts more effort (and thus runs hot) to generate the same thrust thrust Once an engine reaches its BGT limit which indicates the high pressure turbine disk has reached its upper limit 0 temperature; The engine must be disassembled for maintenance. Undoubtedly; Ball's costs for major refurbishment of current large-scale commercial gas turbine jet engines could exceed $1 million. General description of the invention J The present invention is a method; Include: (a)_made then at least one notch mechanically circumferentially at a predetermined location dab outer surface of turbine case of a gas turbine jet engine and with turbine jet engine and (b) fitted washer Reinforcement of the stiffener ring in each of at least one of the aforementioned grooves by means of a contraction interference fit x, where Ln LS is a circumferential compressive force on the aforementioned turbine cage. gus The invention is also a device intended for use in a gas turbine jet engine; Where the apparatus comprises: a turbine cage having at least one ob diay outer surface machined peripherally within said outer surface of said turbine cage of said vo gas turbine jet engine at a predetermined location; And

¢ He reinforcing ring in each of at least one of the grooves mentioned by contraction-interfering pairing; Where lS is said stiffening ring, a circumferential force compressive on said turbine cage. Brief Explanation of Drawings 0 of Figure 1: A schematic diagram of the overall structure of a typical gas turbine jet engine. Figure Y: Shows a cross-sectional diagram of a low-pressure turbine cage for a typical gas turbine jet engine. Figure ¥ oops. Sectional diagram of a low-pressure turbine shear Ls, 01 of Y-shape equipped with stiffener rings in embodiment of the present description. Fig. 6 shows a sectional diagram of section a of the low pressure turbine cage of Fig. or which ab the stiffening ring is about to be installed in an embodiment of the present description. oA ve : shows a sectional diagram of a section of a low-pressure turbine cage from the stiffening ring about to be installed in another embodiment of the present description. Fig. + (od a sectional diagram of a section of a low Jail turbine cage) where the stiffener is installed in another embodiment of the present description. © VOSA : Shows a sectional diagram of a section of a low-pressure turbine cage of the stiffening ring mount in the AT embodiment of the present description. Figure A shows an improvement in clearance under the influence of an applied load in an embodiment of the present description. Shapes: lol

ld 8b and c: showing sectional diagrams of a section of a low-pressure turbine cage in which the stiffener was located on the low-pressure turbine cage by means of a hydraulic nut and secured by a locking nut in another embodiment of the present description.

0 os Ve is a schematic diagram of a low-pressure turbine cage in which the stiffening rings have been actuated by hydraulic means; electrical or other means in another embodiment of the present description. Figure 0 ds shows a cross-section diagram of a low-pressure turbine cage containing reinforcing rings. 0 | Detailed description

Returning now to figures; Where similar names and reference numbers refer to elements that are structurally similar and/or idl where oad Fig. 1 is a diagram of the overall structure of a typical gas turbine jet engine. Returning now to Figure 1, the gas turbine jet engine 011 contains a VY fan to draw air Vo into the fan structure 014 fan frame and works bela fs 011 high pressure compressor rotor Its blades and associated stators push air forcefully into the combustor +A combustor}¢, leading to an increase in the pressure and temperature of the incoming air. A high pressure turbine rotor, YY + high pressure turbine rotor, its blades and associated stator members are housed inside a Y cage. High pressure turbine case 111. Cd is also a low pressure turbine rotor 116 low pressure turbine rotor and its blades and stator members are inside the low pressure turbine case “VV low pressure turbine case” and the turbine works to recover energy from gas Je pressure le speed high- pressure, high velocity gas flowing from combustion chamber 018 and transported to the low-pressure turbine driveshaft

,-Y YA low pressure turbine shaft Yo

0s: Figure 1 is a sectional diagram of the low-pressure turbine cage of a typical gas turbine jet engine. And now back to the figure?; Bad A YY centerline extends along the center of the low-pressure turbine cage;10 (shown in cross-section) and rotor 056 (shown in cross-section) contains vane 018 oo associated with it and rotates around the axis of rotation along the central ball XY A savvy person in the technique will realize that there are usually many Gigs and stators inside the low-pressure turbine cage 104. However there are only 5 vanes. For the purpose of simplification, the designs of the ad ge de gl lag labyrinth seal desings differ in application. The internal diameter of the cages is as shown in the figure. The labyrinthine seals (And) 701 are aligned in cross section with the inner diameter of the low-pressure turbine cage 704, resulting in a shroud around each Ady 71 rotating blade. The shape of the 701 labyrinthine fluids is designed in such a way as to create air turbulence between the tips of each blade of the Bley 1 Sil corresponding to the .701 labyrinthine leak. The air turbulence acts as a barrier to prevent air from escaping and flowing around the edges of the YA Gi and it is recognized that leak fluids that perform similar functions are often referred to by other names. The vane tip clearance NAY© defined as the distance between the vane tip Yo A and the Labyrinth Seal 101 will change as the operating points of the motor change. The changes in the vane tip clearance, Lam 711, are from the mechanisms of replacement or deformation of both the stator and rotating components of the motor due to a number of loads placed on these components and expansion due to heat. The changes in the axial clearance (i.e. axially swaying) axis-symmetric clearance result from the regular loading © (extrusive pressure; thermal; internal pressure) applied to the fixed or rotating bearings that F

There is no uniform radial displacement, and the centrifugal and thermal loads are responsible for the largest radial variations in the feather tip clearance AY, and all wear and tear mechanisms can be classified 01 to 0 labyrinthine sealants have three main categories: rubbing (blade incursion on each other); .erosion JS 5 cthermal fatigue Engines with Eat clearances are selected in both high-pressure and low-pressure turbine cages to determine the amount of Si friction during its motion. Studies have shown that improved vane tip clearances in high- and low-pressure turbine cages can lead to significant reductions in the Jie cycle cost "LLC". A certain amount of vane tip clearance 71 between each ale labyrinthine leak 701 and vane tip A and vane tip clearance 111 decreases rapidly when the motor is accelerated for starting due to the centrifugal load placed on the rotor 1005 Also, the rapid heating of the Yo A Vo blades causes the rotating components to expand outward in the direction of the radius. In the meantime; The low-pressure turbine cage 0704 expands under heating, but at a slower rate. This phenomenon can occur at the lowest clearance of the YAY “pinch point.” When the low-pressure turbine cage 004 expands due to heating after the pinch point; The vane end clearance VY expands. In short, after expansion of the © low pressure turbine cage fag 904 the temperature of the rotor Yet rises (at a lower speed than in the case of the low pressure turbine cage 004 due to its mass) and the vane end clearance narrows 71. And when the engine approaches Als, the steady speed “cruise condition” de low pressure turbine cage et and the rotor Yat to Alla thermal equilibrium and the vane tip clearance remains YAY relatively stable.

A

During the 1711 running condition, it is possible to greatly benefit from narrowing the vane tip clearance at a steady speed. This often happens when it is possible to reach the largest decrease in On the other hand; In general, the SFC at minimal clearance should avoid friction. It usually maintains a minimum clearance and also maintains a value of 12601 without thrust generation to ensure thrust is generated. 0 to strive for control systems to achieve their specific precision.Therefore, many control systems aim to avoid friction on each side 711 to maintain minimum flight vane tip clearance. Engine temperatures usually play a role Great for determining 711 operational blade tip clearances. Both the cold efficiency and life of a gas turbine are directly affected by VY blade tip clearances and the narrower 7017 blade tip clearances can result in This reduces air leakage over the tips of the YA blades. This can increase turbine efficiency and allow the engine to meet performance and thrust targets with lower fuel burn ae and rotor entry temperatures of OF. Ji at lower temperatures + with the same performance as call hot section components can have a large sequential cycle life. Increasing the step-by-step cycle life of hot section components can increase the life of the motor (TOW) by increasing the time between regenerations. Ye The SFC and BGT of the motor are usually directly connected to the vane tip clearance ©1101. Studies (gaa) showed that for every 784 centimeter (cm) ++ .+ inch increase in HPTC bit clearance, the SFC increased by approximately 7001. While the BGT Zed increases by 1 °C, it is believed that a decrease in HPTC bit tip clearance by vor YEO cm (+ver inch) ins vo is believed to be approximately a decrease in SFC by 7) and a decrease in 207 by 01 degrees Celsius

Military engines show a slightly greater effect of HPTC vane tip clearance on SFC and EGT due to their higher operating speeds and temperatures compared to commercial engines (5S) and improvements can result in this much Significant savings in annual fuel and engine maintenance costs amounting to over hundreds of millions of dollars each year. Lower fuel consumption can also lead to lower engine total emissions (0 e). Current estimates are that Americans alone currently take 4 million flights each year [Y.A0 (airline trips per person). aly (Ah) used by 01 commercial aircraft has nearly doubled in recent decades (ADA). The increase in fuel consumption was responsible for the emission of carbon dioxide (60) by 717 out of the total transport sector emissions. Modern atmospheric engines emit 00 percent AY with approximately 778 percent water (HO) and 750.7 percent nitrogen oxide (NO) in addition to very small amounts of carbon monoxide (CO). ) 0 sulfur dioxide (SO) “imitate” etc. Air transport was responsible for 77.8 Tre (million tons) of the world's production of 0©0. Emissions from onshore engines 1000-8560 engines, particularly those used for power generation, contribute to certain values in addition to these total values. Clearly, burning fuel at a lower rate can significantly reduce emissions from both air and land engines. Y. Today's large commercial engines have a sequential cycle life (Cpa) that varies pS, usually ranging from 000 to 000 cycles. Mainly, the cycle life span is determined by the range to which the engine remains at the positive limit of EGT margin EGT 0051076. Newly overhauled engines are shipped so that they have a specific vane tip clearance ve created When running engines on cold and increases with time. And with the rise of the rack

1

engine operating clearances The engine generally works harder (and therefore runs hot) to perform the same work, but with less efficiency accordingly. This increase can be enhanced by the cooperating temperature, especially 7 for starting; Additional hot section component wear due to 0 thermal fatigue. al believes that maintaining the EGT limit for dad launch by maintaining tight vane tip clearances could increase the motor's stator cycle life. This can also lead to huge savings

Engine maintenance costs for several years due to large refurbishment costs. Previous attempts made for clearance control can generally be categorized

00 vane tip to two Lay “control schemes” active clearance control (“ACC”) and passive clearance control (“PCC”) A PCC system is defined as any system that sets the desired clearance at one point of operation” namely, the more critical transient condition (Ua) re-exploding manoeuvres; etc.). As for the ACC system

on the other hand; Defined as any system that allows independent adjustment of the desired vane tip clearance at more than one operating point. The problem that arises when using PCC systems is that the minimum clearance is too small. which is the point of stenosis; Which the system has to adapt to often leaves an undesirable amount of clearance during the longer flight segment at steady state (ie cruising).

Y. In typical PCC systems the expansion of the rotor, member and stator on each flight side is better matched; use of abrasive materials to reduce bit tip wear; The use of reinforcing materials and machining techniques to reduce or induce deformation of hot components to maintain or improve shroud roundness under extreme conditions (cextreme conditions 3a) and the like. Engine manufacturers started

engine manufacturers using thermal ACC systems late

01 The seventies and early eighties. These systems used air fans to cool the edges of the cage, resulting in lower cage diameters (HPTC) for the support flanges and the cover; Consequently, the clearance of the tip of the shisha decreases; During high speed driving conditions.

Gn All of the methods described above are believed to have significant drawbacks 1 their use. Some methods are quite expensive; Others achieve ci results, especially during high-speed driving situations where the greatest advantages are achieved or require cage operation due to the lack of the current possible high-temperature operating means; Which presents secondary problems when sealing and further complicates weight and mechanical issues. 1 shows a sectional diagram of the low-pressure turbine cage of Fig. 1 equipped with stiffeners in an embodiment of the present description. ads Fig. 11. Schematic of a cross-section of a low-pressure turbine cage of Fig. ¥ equipped with reinforcing rings in an embodiment of the present description. Referring now to Figs “* and 11; one or more of the features of the present description applied to gas turbine jet engines DADA or Vo may be incorporated into the design and construction of new gas turbine jet engines; For a variety of applications including air, marine and land transport engines. The attributes of the current description can be applied to HPTC and (LPTC) as 5 33h The attributes of the current description to a both on ©1107 and are not limited to LPTC The grooves are made FY which may be in many different geometric shapes as © will be described in detail below, typically by machining a circumference within the outer diameter of a 01 5 Low Pressure Turbine Case to match the locations of one or more of the 101 Labyrinth Seals locations. corresponding to one or more of the labyrinthine leak fluid locations 171; LT grooves can be made circumferentially at locations corresponding to the 'hot spots' that have been identified in the low-pressure turbine cage 704 by computer modeling. Lacolle

Computer modeling is done by monitoring surface temperatures or by visual inspections to look for cracks when the engine is being repaired. For current engines; The Yetet low pressure turbine cage is usually removed in order to repair cracks caused by these "hot spots". After these restorations; The e-grooves can be placed by weld repair using 0 machines and the external rings will then be interlocked and retracted into the grooves. It is recognized that the reinforcing rings can be placed at other locations in the turbine cage; Depending on the specific application. It is also understood that the sizes,; Dimensions. shapes; Materials and clearances may vary; Depending on the specific application.

vs. and in one embodiment; The Yet stiffeners (shown as a cross-section in Fig. “) are interlaced and contracted daly every groove 707 so that the stiffener 014 surrounds the circumferential groove YY as shown in Fig. Lag 11. The turbine cage is low Yet stress conical (JSD conical) each Fut stiffener may have a different diameter. In Alls the inner diameter of each veg stiffener is slightly less than the outer diameter of the corresponding groove FY Le Each stiffener Ft is heated starting with the stiffener of larger diameter φ and heating causes each stiffener Ff to expand, increasing the inner diameter to a diameter greater than the outer diameter of the corresponding groove FY Once the stiffener is placed © 4 In the furrow fy it

let it cool down; Which leads to its contraction with overlapping inside the corresponding furrow (HY). The figure shows; A schematic sectional diagram of section A of the low pressure turbine cage 0 Gy of Fig. 1 shows the stiffening loop approximately stationary in an embodiment of the present invention. Returning now to Figure 4; The YoY notch is machined circumferentially with a reverse taper ©7©:58©+_for a low-pressure turbine cage taper in one embodiment. The 407's taper angle will vary from cage to cage; Cus range from a value of just over zero for a cylindrical case to a fit dependent on the shape urd vo of a conical pally. The 04 reinforcing ring can be machined to a circumferential shape

a

on its inner diameter to align with the same taper. Although the reinforcing ring is paired

54 by interference and retraction on a low-pressure turbine cage (Yet the taper

Adds additional safety by preventing the reinforcing ring 04 from sliding axially on the low-pressure turbine cage 704. If the groove ¥ Fo is made flat without a taper; it will be

0 | There is an increased possibility of slippage occurring in some applications. When the reinforcing ring 4 is heated, it expands, resulting in the Says “f+ Ring Clearance” from the position of the

Reinforcement 904 as shown opposite Heel 405, groove 907. When the buttress has cooled

©04 its diameter shrinks and fixes itself circumferentially inside the groove Pe and at the air temperature casa and because of the smaller diameter of the inner surface of the reinforcing ring Yet relative to the diameter of the surface

0 outer notch FY produces contraction with overlapping pairing; Cun The reinforcing ring ©0064 exerts a radially compressive circumferential force on the

Low Pressure Turbine Cage 014 The low pressure turbine cage Yet applies a tensile circumferential force on the stiffening ring 5 . And in one of the embodiments

Downforce forces can be concentrated in the direction of the radius on the selected axis of rotation

0 at the YoY center line as shown schematically by the arrows in Fig. 11 and in one embodiment; Compressive forces in the radial direction are applied continuously around the perimeter

Complete the 00 groove and the Yetet turbine cage without stopping.

In one example; The outer diameter of the low pressure turbine cage may be 304 at

blade 706 and labyrinthine seal 11 177 cm (01)

ve inch). In one embodiment; Reinforcement ring 064 may be manufactured as a continuous or seamless solid member; as a unitary part or as a single piece; Formed by hammering or machining

Closed loop shape. In another embodiment, the Woof stiffener can be made using

a member in the form of an open collar and joining the ends together by welding; and for example; To create a closed collar shape. The 704 low-pressure turbine cage is made of superior alloy

dala as well as Inconel 718 YYA Jia cnickel-based super alloy ve

diff

Ve

Inconel 718 VYA by percussion process. Inconel 7004 Superalloy Reinforcement is a high strength composite alloy that can withstand high temperatures and mechanical stress at the surface; It is used in bls conditions, while severe mechanical stress appears in many gas turbine jet engines. It is understood that a stronghold ring can be made e | The turbine cage is made from a variety of materials + depending on the specific application. Heating an o-ring resulting in a 06 oF-ring clearance to a calculated temperature will cause the stiffening-ring to expand “0064 Stiffening Low-pressure turbine cage 04 at ambient air temperature Laie Catch 4 (°F) Alternatively, VY may be cooled at 1107°C (°C) or liquid nitrogen media Yet low pressure turbine cage

Another Yt to reach a temperature calculated to make the low pressure turbine cage diameter 0 at Fog temperature is adequate when the stiffener is 4 0 f shrinks. resulting in a loop clearance The loop clearance of 04 ;ed can be achieved approx. In the form of (QV) M70101 ambient air is masked by a combination of the low-pressure turbine cage 704 cooling and stiffening ring heating processes to bring each to different calculated temperatures. Increasing or decreasing the inner diameter oF of the stiffening ring 04 will produce a circumferential compressive force in the direction of the radius and greater or -1 less tensile stress as required by the particular application; And within the stress limits of the material from which the reinforcing ring is made 4? In addition, the low-pressure turbine cage can be machined in a second direction; Like the direction of the first Yet; such as the direction of the radius; The reinforcing ring can be made with an axis that is more or less perpendicular to the first direction. And since forming with machines © leaves continuous grooves; helical or cylindrical on machined surfaces; For each other, the manner cross-hatch describes the grooves on each surface in a manner that crosses the lines between the two surfaces and reduces the possibility of movement of frictional forces some; Which increases friction forces in that axial and rotational movement. Ley Fe may have the 906 reinforcing ring inside the groove which may be made of alloy Ff (set of grooves on the ve l vo stiffener

a nickel-base super alloy, for example; Harder than the set of grooves on the groove 907 of the low-pressure turbine cage 904; Typically made of ctitanium or in other low pressure turbine cages. It can be made of steel or aluminum, and the grooves of the nickel base super alloy create a dent or form an indentation in the grooves of titanium dtitanium steel 51661 or aluminum Aad) aluminum Alternatively; The reinforcing ring 04 may be welded simply by spot welding at one or more locations in the notch ¥ oF or bolted to one or more flange fixed in the notch (FY) to prevent the reinforcing ring “064” from turning Or in another way of movement relative to the notch

FY 0 0 and there may not be a need for automata in cross directions in this case. By placing the stiffening rings FF in the manner described; YY Blade Tip Clearance may be improved in some applications; Particularly during cruise operation of the engine in some applications 0 An engine designer may as a result; By designing the motor such that it has such a small vane tip clearance it would otherwise be appropriate for a particular motor design not to have such stiffening rings. It is also recognized that benefits can be exploited; other or different improvements advantages or other features alone or in combination; Depending on the specific application. In an application; The circumferential compressive force towards the radius (represented by arrows in Fig. 11) exerted by the stiffening rings 4 can prevent the low-pressure turbine cage 014 from expanding rill from heat © > as much as it would otherwise. In one aspect; The Yeti gussets act as a girdle that surrounds the turbine cage (Yet) to prevent it from expanding or going out of range. In another way, it strengthens the Yeti turbine cage. 7004 gussets can be made of the same material as the Yet low-pressure turbine cage. Or it may be made of a different material with a thermal expansion coefficient less than 0, which increases the compressive circumferential force towards the radius that

‎YYYE

It sheds a reinforcing ring of the same material as the cage when the temperature rises. Powers can be

The compactor is sufficient to form a groove in the turbine cage as in the NY groove and in many engine designs; Heat is mainly dissipated from the outside surface area of the low pressure turbine cage 004 by convection 1 Another benefit that can be achieved by adding stiffening rings 06 to the low pressure turbine cage 004 is that heat can be dissipated at a higher rate because the stiffening rings 904 can ile JS “cooling fins” resulting in lower operating temperatures Jala low-pressure turbine cage 0004. This cooling may also contribute to lower expansion and vane tip clearance 1 Smaller. Lady Ff stiffening rings can help keep ye 5 turning low pressure turbine cage 004 and again; It is recognized that benefits can be exploited; advantages of other or different improvements; or other features alone or in combination; depending on

specified application. Figure © shows a schematic sectional diagram of a low-pressure turbine cage section showing the reinforcing ring nearly stationary in another embodiment of the present description. Returning now to the figure ©ye, the sulcus i o.Y is made circumferentially so that it is in a chevron shape in one embodiment. The angle 904 may vary depending on the application. The reinforcing ring 504 is circumferential on its inner diameter so as to conform to the same heptagonal shape. Although the Reinforced Ring 004 is mated recessively telescoping onto the low pressure turbine cage (Yt), the seven-shape can add additional safety to prevent the Reinforced Ring from slipping off vo the low pressure turbine cage oY of When the reinforcing ring 004 is heated it cand which results in the clearance of the 04 Sy of the reinforcing ring position 004 as shown opposite Heel 047 in the groove 017 9. When the reinforcing ring 4 6 cools 9; its diameter shrinks and fixes itself circumferentially within the groove 07 9. At the ambient temperature and due to the smaller diameter of the inner surface of the reinforcing ring 004 relative to the diameter of the outer surface of the groove 07; a contraction with ve results in interfering pairing, whereby the reinforcing ring exerts 804 forces Circumferential compression in a half direction

VY

Diameter on low-pressure turbine cage 04 The low-pressure turbine cage exerts a circumferential tensile force on the stiffening ring 04. Figure +7 shows a cross-section diagram of the low-pressure turbine cage showing a stiffening ring installed in another embodiment of the present description. Returning now to Figure 76; allotment takes into account the weight added to Cus aero applications Cus aero applications 5 Engine; and make the reinforcing ring 04 so that it has one side; when installed as shown in

Yt is substantially cleaned from the outer surface of a low-pressure turbine cage (Fig. OV) and the notch 07* is machined by reverse-tapering as shown in the figure; In a cage the terpene is machined so that it becomes FY In addition; The YE low-pressure groove can be machined extra deep and/or wide; on Tot deeper; and/or introduce; The reinforcing ring is given 0 stress requirements a DU the basis of the engine to be retrofitted or retrofitted and compressive stress_ radial tensile circumferential stress radially compressive stress. A transverse diagram of a low pressure turbine cage section is shown 1 The figure shows the current description. Returning now to Figure 7; Custom AT Reinforcement Ring installed in Embodiment 0 for aerial applications; Where the weight added to the engine is taken into account; make a loop so that it has a side; When installed as shown in Figure 6; It is cleaned as 1/606 reinforcement 50.97 and a groove is made, Yet substantial, from the outer surface of the low-pressure turbine cage, as shown in Figure 0, to the low-pressure turbine cage, chevron shape, in the form of a seven-way mechanically, so that gets deeper and/or 007 in addition; The groove is made at .004 pressure x depth; and/or additional offer; On the basis of the intended engine Vo Relay Als introduce; And it is given. 0 Designed or retrofitted to meet circumferential tensile stress and radial compressive stress requirements. In addition to aerial or aircraft applications; It is recognized that the cleaning embodiment as well as other embodiments may be used in onshore or offshore applications

Lad sea ve

VA

A tech savvy person will realize that; In addition to reverse taper and 7 oF designs, groove and ring stiffener designs can be used as shown in figures from; to another to achieve the same or similar objectives. For example, Ae sta can be one or more; angular or wavy; so that the channel and ridge channel correspond to the notch having a ridge with one or more channels or ridges; angular or wavy in shape; on the inner surface of the stiffening ring. Alternatively; The sulcus and the stiffening ring have an inverted heptagonal shape. and in other incarnations; The groove may not be used. Several other such figures can be seen without departing from the scope of the present description. Figure A shows the clearance of the tip of a vane under the action of an applied load in an embodiment according to the present description. Returning now to figure A, the reinforcement ring, Wot, is paired as shown in the figure; retractably in the low-pressure turbine cage 7004 and the engine is now under the effect of an applied load eg during steady-speed operation. A labyrinthine seal draws a pally 0 low-pressure turbine Yet with an inner surface 809 and an outer surface At with continuous lines in the locations where the stiffening ring is missing and the diameter of the turbine cage - low pressure Yo f expands and the labyrinthine seal distances 701 off the vane 018 resulting in a wider vane tip clearance 1" ?. other than cad due to the compressive force towards the radius exerted by the stiffening ring Yet on the low pressure turbine cage oY rf the labyrinthine seal 01 at the location indicated as spectrum 701 the ring oF cf, inner surface 809 and outer surface 804 are for the low pressure turbine cage 1704; at the © locations indicated as CACY CFE spectrum and 804 thus the vane tip clearance YAY is reduced Thus according to one aspect of the present description, the amount of bale expansion caused by heating decreases in the LPTC and HPTC and thus the bit tip clearance improves. HPTC and LPTC reduce EGT aa and engine life. In general, for large gas turbine engines, decreases in vane tip clearance are believed to be 7.0"

1

It is approximately 100 784 cm (ver inch) which can result in a drop in SFC of 71 and a drop in EGT of 10 m. It is believed that improved bit tip clearance by this amount could save in fuel and maintenance costs in excess of hundreds of millions of dollars each year. Reduced fuel combustion could reduce aircraft emissions by 0, which currently constitute 770 lea) of CO emissions in the United States transportation sector and in the face of OAT could reduce vane tip clearances in Consistent running conditions to make a significant impact on the SFC and EGT limit and improve turbine efficiency. Furthermore, the increased outer surface area of the HPTC and LPTC cores can enhance cooling due to ring stiffeners; in die embodiments and result in lower -0 internal temperatures that extend engine cycle life. Also;(Say) an increase in payload per engine is achieved by improving vane tip clearance. Additional tons of payload can be carried per takeoff and landing. It is recognized that the features of the present description can easily replace costly passive clearance control options It is also recognized that a lack of roundness and a decrease in one or more factors of vane tip clearance “SFC 207” or polluted emissions can be induced using one or more of the features described in this statement. Fabrication of the stiffening ring from a material having a lower coefficient of thermal expansion than the coefficient of thermal expansion of the turbine cage material may facilitate the realization of one or more further reductions of these factors. installation

0 turbines cage and reinforcing ring of the same material. Figures (J*b; and 14c) show cross-section diagrams of a low-pressure turbine cage section having a reinforcing ring located on the low-pressure turbine cage with a hydraulic nut and a blocking nut for another embodiment. Now referring to Figure A, the volume is measured Reinforcement ring 04 to secure, without pressure, in close proximity to an outer vane, Yoh and xe seal, Maze 10; or as formerly known 'hot spot'; was placed in position.

Add

Y. suffixed; The 907 was threaded with the low-pressure turbine cage 04. It was

At of hydraulic nut 907 position 905 that meshes with the reinforcing ring of hydraulic nut 907; So that 09 piston expansion of the piston cd and in the form

Yo t pushes the reinforcing ring 904 towards the end of the larger diameter of the low-pressure turbine cage ally Yoh is attached to the inner vane Led and thus the reinforcing ring 04 is in the optimal position 0 resulting in an interference pair. The amount of expansion of the piston 01 is calculated for the labyrinthine leak. 06 to produce desired circumferential downforce by stiffening ring 1" hydraulic nut 9609 removed; lock nut ad tightened in Fig. and Yt threaded into place on low pressure turbine cage washer cif for lock nut 08 with stiffener 4 80 and so on 901 retainer retainer 0 stiffener 904 in place This process is repeated in several stages as required depending on the turbine design This embodiment can add excess weight and is appropriate significantly for onshore applications where weight is not a consideration. lila booster low pressure turbine having pall schematic diagram 01 the figure shows actuated by hydraulic, electronic, or other means in another embodiment As per the present description. - 0 Reinforcement Rings of 0001 Now referring to Fig. 10, the cage shall have the low pressure turbine located in predetermined locations to match the vane and/or Vert© type staggered seals. © “hot spots.” In this embodiment, the stiffeners do not have a type 0001. A notch can also be made for each stiffener with retraction with a low-pressure turbine cage, but the stiffeners are type 0001. © 100 mechanisms in a low-pressure turbine cage are © rings, preferably over continuous rings. Each end is connected so that when the YoY Actuator means with a Vo vf © actuating device a Relay Ring of type daa 001 is exerted; Each end of the stiffening ring is compressive force towards the radius on the low-pressure Jed turbine cage, and the inner surface of the stiffening ring can be plated ©; or furrow surface; Yo the first

AR

registered trademark) or one of the lubricating materials (Ake) Teflon® or both using the other Teflon to facilitate sliding when tightening. 011. The controller 011. 1 Electrical/Electronic Connections multiple temperature sensors transmits temperature readings from the 0 sensors located next to the ©100 type relay (not shown). It is also possible to steer a temperature and use these readings as EGT feedback from the LPTC temperature readings temperature and when temperature rises are monitored throughout the Veoh to the controls feedback temperature data #0011 the instrument processes Control 0001 low pressure turbine cage to pull together © 0014 and determine how much each end of the type 0 stiffening ring needs to exert a special circumferential compressive force on the low pressure turbine cage 0017 by a means of actuation to provide benefit suitable such as maintaining optimum bit tip clearance or equalizing 0001 pressure; "hot spot" effect; eg. from a loop of type ©; Var may be coupled in an alternative embodiment; AT embodiment (registered trademark). can be coated with Keviar® US Jie «non-metallic material (registered trademark)); or furrow surface; or both Ade) Keviar® inner surface of Kevlar (registered trademark) or some other lubricant to facilitate sliding with Teflon® using Teflon when stretched. vs. After describing multiple features; It is understood by those skilled in the technique that several widely different embodiments and applications will refer to themselves without departing from the scope of the present description.

Claims (1)

YY Claims method; Includes: 1-0 at specified location ui peripherally one JN on (YY) notch pb ada (1) Y of a turbojet engine (Ye £) turbine case prefabricated into an outer surface of a turbine cage v and ¢ () + +) gas turbine jet engine ¢ (oY) each groove (Ye £) stiffener ring Als reinforcement (b) o shrink interference fit one on The aforementioned minimum is by means of an interfering retraction pair 1 Adame 58 Compressor Roxdamla_(©04) where the aforementioned reinforcing ring is attached. (Yet) on the turbine cage compressive circumferential force A where the said installation also includes: ?- The method according to the aforementioned Clause 0 to increase its inner diameter from (001;) stiffener ring by heating the single Y stiffening ring (“07) notch that is greater than the outer diameter of the groove from the first value Ah to a value v at least mentioned at ambient temperature; 1 mentioned in the notch (07©) at least one (Ye) position of the stiffening ring o mentioned; and 1 mentioned to cool to ambient temperature (Yet) Leaving said stiffening ring V, which causes its inner diameter to decrease from said second value to at least one A (Foy) said first value; However, the aforementioned outer diameter of the groove 9 shrink interference fit the aforementioned Gand resists this from the aforementioned 01. VA, where the aforementioned fixation also includes: To reduce the outer diameter of the notch (Y+¢) turbine case Cooling of the Y turbine cage YY (WY) notch at least one mentioned from the first value to a second value that is less than £ the inner diameter of the stiffener ring (4,1) stated at ambient °; Placement of the Vet mentioned in the groove (207) of at least one 7 of the aforementioned; And A said turbine cage (;10) was left to heat to said 9 s ambient temperature; which causes the outer diameter of at least one notch (07") said ve to increase from the second said value to the first said value. However, the aforementioned inner diameter 1 of the aforementioned stiffening ring (Vf) resists this, which causes the aforementioned shrink interference fit VY. 0 — method according to claim 1 where said fixation also includes: Y heating said (V+£) stiffener ring to increase its inner diameter from r to a second value; ¢ Cool the said turbine case (;1010) to reduce the outer diameter of said at least one (YY) notch from the first value to a second value that is less than 1 mentioned second value of the said (304) stiffener diameter; v Place the said stiffening ring (Fe f) in at least one (YY) notch mentioned; A Allow said Yet to cool to ambient temperature; And | Pal left the said turbine (;10) to heat up to the said ambient temperature, Ve; 1 where the second stated value of said Fog VY is reduced to the first stated value; and the said second value of the outer diameter of the notch (207) yy at least one said said value shall be increased to the first said value; Which causes the aforementioned ¥ shrink interference fit. ‎YYY§ Y¢ where said machine-made also includes: 1 method in accordance with claim # 0 at least one mentioned mechanically peripherally within (©07) notch making the notch 1 ple said at a location corresponding to ( Y+¢) turbine case outer surface of the turbine cage v on the inner surface of the turbine cage (;10) mentioned. labyrinth seal ¢ where the mentioned mechanical manufacture also includes: 1 method according to the protection element - + 0 At least the mentioned one mechanically circumferentially within the (YY) notch made the said notch at a location corresponding to the spot of the (Y+¢) turbine case outer surface of the turbine cage 0 of the said turbine cage (;10). hot spot ¢ Load includes 1 method according to the element of protection Y 0 — in a predetermined manner corresponding to the aforementioned i (01); (4 Y) notch with the aforementioned v-shaped notch (©07) notch The making of the notch Cus V includes the method according to claim A-0 making it circumferentially at a predetermined location within the said outer surface of a cage 7 Whereas the aforementioned ¢ reverse taper with reverse taper (01); Least mentioned. (FY) A particular corresponding to the said reverse taper of the notch > the mentioned mechanically (©07) notch where making the notch V includes the method according to Claim 4-01 making it circumferentially at the previously specified location mentioned Inside the aforementioned outer surface of the Y cage and the aforementioned tchevron shape (Y + £) turbine case v made by the aforementioned Ll (Yo €) stiffener ring pia where it includes ¢ at least one (FY) on a certain inner diameter corresponding to the said heptagonal shape of the notch o Yr Yo . Mankur a (Ye ¢ ) stiffener ring, where the manufacture of the stiffening ring 1 includes the method according to the aforementioned 0-1 (304) of protection, mechanically making an upper surface for it so that when the reinforcing ring is fixed, the upper surface At least one OSM (4X) notch aforementioned in groove 1 aforementioned stiffening (304) becomes flush with the aforementioned outer surface (dala) aforementioned 1. (Y + £) turbine case for turbine cage ° (Yt) stiffener ring, where the manufacture of the reinforcing ring V includes the method according to the element of protection 11-1. nickel-base super alloy made of the aforementioned nickel-base super alloy Y (¥+) stiffener ring where The manufacture of the turbine case 1 includes the method according to the aforementioned VY 01 protection element, mechanically making it from a material that is different from the material from which the aforementioned turbine cage is made: gl, and the said material from which the turbine case 1 is made is less than Expansion coefficient of the aforementioned material The aforementioned expansion coefficient (001;) ¢. The aforementioned turbine cage (‘) is made of it ° VF 1 method according to Claim 1 where the making of the notch includes the aforementioned mechanically made within the said outer surface of the said (Y+£) turbine case in the first direction; Cua v A set of Coats grooves is machined on the outer surface 1 mentioned in the first mentioned direction; And ° where it includes the making of the stiffening ring (stiffener ring). The aforementioned 0 i made an internal surface 1 of it Li in a second direction 0 where a group of grooves are formed and smoothed on the aforementioned internal surface in the aforementioned second direction ¢ 0 whereby when cf the aforementioned external surface of the notch (07©) the one on YYy¢ said least and said inner surface of said stiffening ring (Ff) dae the ye is the said group of notches on said outer surface of the notch (FoF) “1 at least said one and said group of notches on the inner surface” aforementioned for the reinforcing ring (Yet) aforementioned Chas in a cross-lined manner with respect to vy to each other; This increases the frictional forces between at least one notch (FY) said ve and the reinforcing ring (8) (Y0) and reduces the possibility of rotation of the reinforcing ring (£ 0 2) yo said inside the notch (Fe Y) At least one mentioned. 0-1 daa device for use in a Cua “gas turbine jet engine” Y. The device includes: r turbine case (4,100) with an outer surface ( ¥+Y) notch ab 33a; : at least one machined peripherally within said outer surface of said turbine cage (;100) of said gas turbine jet engine at a predetermined position 1; and a v 45 stiffener ring (¢ + ¥) fixed in each of the A grooves (07©) at least one mentioned by means of the ¢shrink interference fit q 1 where Ail Zila hls (3204)_mentioned 558 compressive circumferential force 11 on said turbine cage (;10). Stiffener ring (£ +¥) mentioned to increase its inner diameter, r from the first value to a second value that is greater than the outer diameter (YY) notch ABN at least one mentioned at the ambient temperature, where after the stiffener ring is placed o Reinforcement (YE) mentioned in the groove (YoY) at least one oS ring is left YY'Y¢ to 1 Said (Yet) to cool down to said ambient temperature; Which causes v to decrease its inner diameter from said second value to said first value; A However, the said outer diameter of at least one of the aforementioned grooves (YY) resists this, which 9 causes said shrink interference fit. 11-0 Device pursuant to Clause 1? It also includes: Y is a means of cooling said (Y + £) turbine case to reduce the outer diameter 1 of at least one notch (07©) mentioned from the first value to a second value which is less ¢ than the inner diameter of the stiffening ring (Vr £) the aforementioned stiffener ring at ambient temperature” where after the aforementioned stiffening ring (hf) is placed in the groove (07”) of at least 1 aforementioned. Said turbine cage (Veg) is left to heat up to said ambient temperature v; which causes the outer diameter of one notch (TY) of one notch at said least A to increase from the second said value to the first said value; However, the aforementioned inner diameter 9 of the aforementioned UR resists this, which causes the aforementioned shrink interference fit 01. 17-1 The device pursuant to Clause 16 also includes: Y is a means of heating said (Yo £) stiffener ring to increase its inner diameter, r, from the first value to a second value; And A means of cooling said (Y 2) turbine case to reduce the outer diameter ° of at least one said (V4 Y) notch from the first value to a second value which is 1 less than the second value of the stiffening ring diameter (Ye £) the aforementioned stiffener ring; Where, after v, the aforementioned reinforcing ring (Fh E) is placed in the notch (YY), at least one aforementioned A, the aforementioned (Yet) reinforcing ring is left to cool to the ambient temperature and the turbine cage (4) is left £(Ye) said to heat up to said ambient temperature; command said YA of the second value (Ye £) which causes the inner diameter of the reinforcing ring Ve to decrease one over (YoY) said to the first said value; Increasing the outer diameter of the notch by the said less than 1" from the second mentioned value to the first mentioned value, which results in the said \Y. Protection Gay device YA 1 inside at least one outer surface WT mentioned circumferentially (VY) notch: said ile leak at a location corresponding to the (Y 2 £) turbine case mentioned for the turbine cage v (Yo £) on the inner surface of the turbine cage labyrinth seal labyrinthine ¢ where the said predetermined location is for making the notch 16 of protection Ga, device 11-1 at least one mentioned Fig. Automatically circumferential inside the outer surface (©07) notch: aforementioned at a location that matches the aforementioned hot spot (14) turbine case (10); hot spot (014) stiffener ring where The notch VE of protection Ga, device 71-01 notch so as to conform to the shape of the notch ui also mentioned shall have a predetermined shape and then made by at least 7 of the said one. (YY) y the said taper (VY) notch where the said VE has the device according to Clause 71-0 at least one mentioned; (YAY) inside the Li notch is made reverse taper said Y reverse taper adapt (04) The stiffener ring was done, and where the reinforcing ring has a v on the inner diameter of the reinforcing ring (04©) mentioned. for va Y a chevron shape made ui to be the shape of the notch (¥+¥) of at least the 1 mentioned; and 1 Heptagonal shape machined to match the inner diameter of the stiffener ring (v of ) 0 mentioned. (Vt ) stiffener ring Where the VE stiffener ring is the device according to the element of protection 7-1 also mentioned: Y Upper surface machined so that when said stiffening ring (Ff) 1 is set into at least one said (VY) notch said upper surface of said stiffening ring (7045) becomes level with said outer surface 1 of a cage The turbine case (;10) mentioned. (v 4 ) stiffener ring The reinforcing ring is made Cus VE; - the device according to protection element 1. nickel-base super alloy from the aforementioned Lf Lf (v-¢ ) stiffener ring wherein the stiffener VE-ring of the protection element a of the device—Yo 1—mentioned is machined from a material different from that of said turbine cage; The aforementioned material has a thermal expansion coefficient of (01;) turbine case Y that is less than the coefficient of expansion of the said material from which the aforementioned thermal expansion cage is made. (01;) ° -71 1 Device Ga, of protective element VE wherein at least one (Y¥+Y) notch of said Y of said turbine case (Y « ¢ ) has an outer surface made of Li identifies 7 groups of grooves arrayed facing first on the outer surface of said ui 1 of at least one said notch (YoY); And YYyYe Cua ° said Ve ( stiffener ring ) has an inner surface machined i ; defines a set of grooves arranged in the direction fb on said machined inner surface v of the stiffener ring (£ (Vo mentioned; A Whereas, when the said outer surface of the notch (eX) of one is paired with at least the said 9 and the said inner surface of the said (Fh f) stiffening ring in an interferometric manner 1 and contraction together, the said group of grooves on the outer surface, The aforementioned Vy for at least one notch (YY) mentioned and the aforementioned group of grooves located “on the aforementioned inner surface of the reinforcing ring (8) (Fr) aforementioned 5 Cia in a cross manner 7” lines relative to each other “andl”, which increases the forces Friction between at least one notch (FoF) said Ve and said stiffening ring (Yet) and reduces the possibility of ring rotation The stiffening (£ (Ye) mentioned within at least one notch (FY) mentioned.