CN110131210A

CN110131210A - Turbogenerator with composite blading

Info

Publication number: CN110131210A
Application number: CN201910106740.6A
Authority: CN
Inventors: N.J.克雷; G.C.格梅因哈德特; D.D.沃德; D.W.克拉尔; 林玟玲
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2018-02-08
Filing date: 2019-02-02
Publication date: 2019-08-16
Also published as: US20190242399A1

Abstract

The present invention relates to the turbogenerators for having composite blading.Specifically, a kind of blade for turbogenerator includes composite core, composite core be limited to axially extended between leading edge and rear with limit chordwise and radially extend between root and tip with limit spanwise on the pressure side and suction side.Composite core is formed by two kinds of materials with heterogeneity.

Description

Turbogenerator with composite blading

Technical field

Turbogenerator includes installing to axis and providing structural support by the rotating member of shield and shell wrapping, shield and shell It is guided with the air stream for passing through machine.Present disclosure relates generally to a kind of turbogenerator with fan section, and has Body, one of rotating member is the fan blade with composite core.Fan blade may include installing to the metal of composite core Edge member.

Background technique

Fan blade and other rotating members (e.g., including compressor and turbine) rotation, the wherein tip of respective members Pass through very close to shield or shell.During some events, for example, bird sucks gas-turbine unit, blade may contact shield Or shell.In addition, blade can be discharged from gas-turbine unit, i.e. " fan blade falls off " during at least some such events (FBO).Such event usually causes the destruction of other components to the shield or shell and gas-turbine unit of blade.It destroys also Gas-turbine unit be may cause with smaller capability operation, to need repairing.

Summary of the invention

On the one hand, this disclosure relates to a kind of airfoil for turbogenerator, airfoil includes composite core, compound Core have axially extended between leading edge and rear with limit chordwise and radially extend between root and tip with Limit spanwise and with spanwise length on the pressure side and suction side, the first part of composite core radially extend small from root In spanwise length 100% and formed by the first material, the second part of composite core is adjacent to first part and limits tip at least It a part and is formed by the second material, the second material has the adaptability to changes lower than the first material and with different from the first material Ingredient.

On the other hand, this disclosure relates to a kind of blade for turbogenerator, blade includes internal composite core, interior Portion's composite core have axially extended between leading edge and rear with limit chordwise and between root and tip radially Extend with limit spanwise and with spanwise length on the pressure side and suction side, the first part of composite core from root radially It extends less than the 100% of spanwise length and is formed by the first material, the second part of composite core adjacent to first part and limits tip At least part and formed by the second material, the second material have the adaptability to changes lower than the first material and with the first material Different ingredients.

Another aspect, this disclosure relates to a kind of method for being used to form blade, blade has composite core and in root It is radially extended between tip to limit spanwise and there is spanwise length, this method includes to form composite core first Point and second part, so that first part is extended radially outward 100% less than spanwise length from root, make second part from end The tip is radially inwardly extending to encounter first part, and first part is linked to second part to form fuse (fuse).

A kind of airfoil for turbogenerator of technical solution 1., the airfoil include:

Composite core, the composite core, which has, to be axially extended between leading edge and rear to limit chordwise and in root and end Radially extended between the tip with limit spanwise and with spanwise length on the pressure side and suction side；

100% less than the spanwise length is radially extended from the root and the composite core that is formed by the first material First part；

The second part of the composite core, adjacent at least part of the first part and the restriction tip and by second Material is formed, and second material is with the adaptability to changes lower than first material and has different from first material Ingredient.

The airfoil according to technical solution 1 of technical solution 2., wherein first material is that have to be greater than or wait In the conformable material of 1% adaptability to changes, and second material is with the less submissive of the adaptability to changes less than or equal to 1% Material.

The airfoil according to technical solution 1 of technical solution 3., wherein the adaptability to changes that second material has Less than the 85% of the adaptability to changes of first material.

The airfoil according to technical solution 1 of technical solution 4., wherein the second part is from the first part It radially extends and reaches the 5% of the spanwise length.

The airfoil according to technical solution 1 of technical solution 5., wherein second material has greater than 10Msi's Elasticity modulus.

The airfoil according to technical solution 1 of technical solution 6., wherein first material has 5Msi to 20Msi Between elasticity modulus.

The airfoil according to technical solution 1 of technical solution 7., further includes the first part and the second part Between fuse to limit frangible region.

The airfoil according to technical solution 7 of technical solution 8., wherein the fuse is interlocking, interweaves, docking Or one of lap joint.

The airfoil according to technical solution 1 of technical solution 9. further includes at least part extension along the tip Tip cap.

The airfoil according to technical solution 9 of technical solution 10., wherein the tip cap is in the chordwise At least 50% along the tip extends.

The airfoil according to technical solution 10 of technical solution 11., wherein tip described in the tip cap 100% extends.

The airfoil according to technical solution 1 of technical solution 12., wherein first material or second material At least one of be composite material.

The airfoil according to technical solution 12 of technical solution 13., wherein second material is epoxy resin fibre Tie up material.

The airfoil according to technical solution 1 of technical solution 14., further includes being formed by least two different materials Preceding edge strip.

The airfoil according to technical solution 14 of technical solution 15., wherein the preceding edge strip includes leading edge frangible region.

A kind of blade for turbogenerator of technical solution 16., the blade include:

Internal composite core, the internal composite core have axially extended between leading edge and rear with limit chordwise and Radially extended between root and tip with limit spanwise and with spanwise length on the pressure side and suction side；

The second part of the composite core, adjacent at least part of the first part and the restriction tip and by second Material is formed, second material have the adaptability to changes lower than first material and it is different from first material at Point.

The blade according to technical solution 16 of technical solution 17., wherein the adaptability to changes that second material has Less than the 85% of the adaptability to changes of first material.

The blade according to technical solution 16 of technical solution 18., wherein second material has greater than 10Msi's Elasticity modulus.

The blade according to technical solution 16 of technical solution 19., wherein first material has 5Msi to 20Msi Between elasticity modulus.

The blade according to technical solution 16 of technical solution 20. further includes the first part and the second part Between fuse to limit frangible region.

The blade according to technical solution 20 of technical solution 21., wherein the fuse is interlocking, interweaves, docking Or one of lap joint.

The blade according to technical solution 16 of technical solution 22. further includes at least part extension along the tip Tip cap.

The blade according to technical solution 16 of technical solution 23., wherein first material or second material At least one of be composite material.

The airfoil according to technical solution 16 of technical solution 24. further includes being formed by least two different materials Preceding edge strip.

The airfoil according to technical solution 24 of technical solution 25., wherein the preceding edge strip includes leading edge frangible region.

A kind of method for being used to form blade of technical solution 26., the blade have composite core and root and tip it Between radially extend with limit spanwise and have spanwise length, which comprises

Form first part and the second part of the composite core；

The first part is set to extend radially outward 100% less than the spanwise length from the root；

The second part is set to encounter the first part from the tip is radially inwardly extending；And

The first part is linked to the second part to form fuse.

The method according to technical solution 26 of technical solution 27., wherein forming the fuse includes by described the A part interlocking interweaves, docking or one of overlaps to the second part.

The method according to technical solution 26 of technical solution 28. further includes that tip cap is made to surround the tip at least A part extends.

The method according to technical solution 26 of technical solution 29., wherein forming the second part includes by rigidity Non-compliant material forms the second part.

The method according to technical solution 26 of technical solution 30. further includes forming preceding edge strip, and the preceding edge strip has Manufactured first part and be made of the material different from the material that the first part is made and have than the first part The second part of low elasticity modulus.

Detailed description of the invention

In the accompanying drawings:

Fig. 1 be include fan blade turbine engine components schematic diagram.

Fig. 2 is the enlarged perspective of the fan blade from Fig. 1.

Fig. 3 is the section view of the III-III interception along the tip of the fan blade from Fig. 2.

Fig. 4 is the modification according to the section of Fig. 3 of the other side of disclosure.

Fig. 5 is another modification according to the section of Fig. 3 of the another aspect of disclosure.

Fig. 6 is the modification according to the fan blade from Fig. 2 with preceding edge strip of the one aspect of disclosure.

Fig. 7 is the preceding edge strip according to the fan blade for Fig. 6 of the other side of disclosure.

Parts List

10 engines

12 center lines

14 fan components

16 cabins

18 engine cores

20 low pressure compressors

22 high pressure compressors

24 burner assemblies

26 high-pressure turbines

28 low-pressure turbines

30 fan blade

32 rotor disks

34 air inlet sides

36 exhaust sides

38 armature spindles

40 air

42 first parts

44 second parts

45 gaps

46 leading edges

48 rears

50 roots

52 tips

54 tip caps

Edge strip before 56

58 trailing-edge strips

60 dovetail keys

62 composite cores (62,162)

64 first parts

66 second parts

68 fuses

70 frangible regions

74 first materials

76 second materials

78 on the pressure side

80 suction sides

145 gaps

146 leading edges

148 rears

150 roots

152 tips

154 tip caps

Edge strip before 156

156a first part

156b second part

158 trailing-edge strips

160 dovetail keys

162 composite cores

163 leading edge fuses

164 first parts

165 leading edge frangible regions

166 second parts

168 fuses

170 frangible regions

174 first materials

176 second materials

178 on the pressure side

180 suction sides

246 leading edges

252 tips

Edge strip before 256

256a first part

256b second part

256c Part III

263 leading edge fuses

265 leading edge frangible regions

268 fuses

270 frangible regions

274 first materials

276 second materials

278 on the pressure side

280 suction sides

290 root portions

292 second ends

294 third ends

296 the 4th ends.

Specific embodiment

The aspect of disclosure described herein is directed to a kind of blade of turbogenerator, specifically fan blade, wherein Fan blade includes the composite core made of at least two different materials.Two kinds of materials have heterogeneity, wherein closest to wind The material of rest part of the material of the tip of fan leaf than composite core is made is less submissive.The frangible region of blade is limited to fuse Device is formed in the region around the position between two kinds of materials.The portion for the blade that frangible region allows to be formed by less submissive material Divide and is easy to disconnect with rest part during (passing through non-limiting example) FBO event.

For diagrammatic purposes, present disclosure will be described referring to the fan blade in turbogenerator.Although illustrated as wind Fan leaf, it should be appreciated that disclosure as described herein is equally applicable to other blades in engine.Further, it will be appreciated that The aspect of disclosure described herein is without being limited thereto, and blade can be implemented within the engine as described herein, including but not It is limited to turbojet, turbo-propeller, turbine wheel shaft and turbofan.The aspect of disclosure described herein can have There is general applicability, e.g., other mobile applications and non-moving industry, business and house in vaned non-aircraft engine Using.

As used herein, term " preceding " or " upstream " refer to that edge is moved towards the direction of motor inlet or component is compared In another component relatively closer to motor inlet.The term " rear " or " downstream " used together with " preceding " or " upstream " refers to court The outlet of engine or direction compared to another component relatively closer to engine export.In addition, it is as used herein, it uses Language " radial direction " " radially " refers to the size extended between the central longitudinal axis of engine and engine periphery.For example, such as Used herein, term " in groups " or " one group " element can be any amount of element, including only one.

All directions indicate (for example, radially, axially, proximal and distal, it is upper and lower, upward, downward, left and right, lateral, preceding, Afterwards, top, bottom, top, lower section, vertical, horizontal, clockwise, counter-clockwise, upstream, downstream, front, rear etc.) it is only used for knowing Other purpose understands present disclosure to facilitate reader, and does not generate the aspect especially with regard to disclosure described herein Position, orientation or the limitation used.Connection indicates that (for example, attachment, connection, connection and connection) will broadly understand, and can Including a series of relative movement between the intermediate member and element between elements, unless otherwise instructed.Therefore, connection table Show be not necessarily meant to refer to two elements be directly connected and with each other in fixed relationship.For illustration purposes only, and its is attached for exemplary diagram Size, position, sequence and the relative size reflected in figure is alterable.

Fig. 1 shows the exemplary turbine engine component 10 with the longitudinal axis for limiting engine centerline 12.Wind Fanning component 14, cabin 16 and turbogenerator core 18 may include in turbine engine components 10.

Turbogenerator core 18 includes the low pressure compressor 20 for being arranged to axial series flow relationship, high pressure compressor 22, combustion Burner component 24, high-pressure turbine 26 and low-pressure turbine 28.

Fan component 14 includes the array of the fan blade 30 extended radially outward from rotor disk 32.Propeller for turboprop unit Part 10 has air inlet side 34 and exhaust side 36.Fan blade 30 and low-pressure turbine 28 are linked together with armature spindle 38.Fan group Part 14 and engine core 18 are positioned at least partially in cabin 16.

In operation, air 40 flows through fan component 14, and the delivery of first part 42 of air stream across compressor 20, 22, wherein the first part 42 of air stream is further compressed and is delivered to burner assembly 24.From burner assembly 24 Therefore hot combustion product (not shown) generates motor power for driving turbine 26,28.The sky being discharged from fan component 14 The second part 44 of air-flow is used to bypass around turbogenerator core 18.

Fig. 2 is the schematic diagram of the fan blade 30 of the fan component 14 for turbogenerator 10.Fan component 14 can be determined Position is in cabin 16, with the gap 45 formed between each fan blade 30 and cabin 16.Each fan blade 30 can have the wing Type part cross sectional shape, and axially extend between leading edge 46 and rear 48 to limit chordwise, and in root 50 and tip It is radially extended between 52 to limit spanwise.Spanwise length (L) is to measure from root 50 to tip 52 along spanwise Maximum length.Fan blade 30 may include at least part of tip cap 54 for limiting the fan blade 30 at tip 52.Pass through Non-limiting example, tip cap 54 are formed by titanium mesh.Alternatively, tip cap 54 can be by being convenient for fan group as described herein Any material of the operation of part 14 is formed.

Preceding edge strip 56 can limit at least part of the leading edge 46 of fan blade 30.Trailing-edge strip 58 can limit fan blade 30 Rear 48 at least part.Preceding edge strip 56 and trailing-edge strip 58 can be by the operations convenient for fan component 14 as described herein Any metal material is formed, including but not limited to titanium alloy, steel alloy or nickel alloy.During operation, it may occur however that due to It is destroyed caused by foreign object contact or extreme difference in temperature.Preceding edge strip 56 and trailing-edge strip 58 provide 46 He of leading edge at protection fan blade 30 Rear 48 is during operation from this destruction.

Fan blade 30 may also include dovetail key 60, convenient for fan blade 30 is attached to rotor disk 32.Composite core 62 It can extend from dovetail key 60, and provide light weight internal structure to fan blade 30.The entirety of composite core 62 is shown in dotted line, and can It axially extends between leading edge 46 and rear 48 and is radially extended between root 50 and tip 52.It is contemplated that compound Core 62 limits the major part of fan blade 30, and can have hollow inside or solid interior.It also conceives, composite core limits whole A fan blade 30.

Composite core 62 includes the first part 64 formed by the first material and the second part 66 that is formed by the second material.The A part 64 extends less than the 100% of spanwise length (L) from root 50 towards tip 52.Fuse 68 is formed in the chance of first part 64 To 66 place of second part.Second part 66 is radially extended from fuse 68 towards tip 52, and can limit tip 52 at least A part.It also conceives, second part 66 can extend up to the 5% of spanwise length (L) along spanwise.

First material and the second material can be composite material, be glass or carbon fiber composite by non-limiting example. First material and the second material can be the other suitable composite material with heterogeneity, as long as the first material has than second The higher adaptability to changes of material.Adaptability to changes can be about the original knot of material when being hit or in addition undergoing external force about material The amount of structure bending or deformation.Adaptability to changes is the ratio between new length and the original length when undergoing external force, and is therefore no unit 's.Improved strain ability is equivalent to high deformation amount of the object relative to object primitive form.According to the one of disclosure A aspect, improved strain ability be equivalent to object than with lower adaptability to changes object it is submissiveer or have greater flexibility.Cause This, the object with lower adaptability to changes is more fragile, and tends to rupture by deformation and fragmentate rather than deform.It is being disclosed herein The one aspect of content, the adaptability to changes of the second material less than the first material adaptability to changes 85%.Pass through non-limiting reality Example, the first material can have 1.6% adaptability to changes, and the second material has the adaptability to changes less than 1.3%.It also conceives, The adaptability to changes of first material is greater than 1%, and the adaptability to changes of the second material is less than or equal to 1%.In either a program, the is formed Second material of two parts 66 has the adaptability to changes lower than the first material for forming first part 64.

It also conceives, the first material has the adaptability to changes higher than the second material and the springform lower than the second material Amount.Elasticity modulus quantify first part 64 or second part 66 along axis deformation trend (when opposite power applies along the axis When).In other words, elasticity modulus can quantify the rigidity of material.Object with Large strain ability and low elastic modulus be it is submissive and Relatively flexible material.

However, also conceiving, the first material can have the elasticity modulus equal with the second material, and still keep higher and answer Change ability.In the case, it is therefore possible to use carry out the bigger power of use than disconnecting the second material with similar elastic modulus Disconnect the first material.By non-limiting example, some ceramic fibres can have similar elasticity modulus, but have than carbon fiber Low adaptability to changes.In such situation, the first material will be made of carbon fiber, and the second material will be by ceramic fibre system At.In another non-limiting example, the first material can be intermediate modulus fibre, such as IM7 or T800 carbon fiber, and second Material can be formed by the fiber of high elastic modulus, such as HM63 or M55J carbon fiber.According to the aspect of disclosure, formed First material of first part 64 is submissiveer than the second material or flexible.More particularly, the second material of second part 66 is formed Expect more fragile compared to the first material or more crisp.

During operation, the contact with foreign object can cause fan component 14 to carry out moving around armature spindle 38, this can cause FBO as previously described.Due to discontinuous, at least part of restriction tip 52 of the ingredient between tip 52 and composite core 62 Second part 66 can disconnect.Fuse 68 and peripheral region limit frangible region 70, wherein disconnection can by non-limiting example Occur at fuse 68 or close to any position around fuse 68.Adaptability to changes the difference is that ensure enable it is frangible Area 70.Component difference between first material and the second material can help to enable frangible region 70.The controlled disconnection ensures, The smallclothes of fan blade 30 rather than entire fan blade 30 are sucked during FBO by engine 10.Therefore, the FBO the case where Under, it may occur however that the safe shutdown of engine.

Fig. 3 is the amplification section view along the frangible region 70 shown in the line III-III from Fig. 2.In disclosure One aspect, formed composite core 62 first part 64 the first material 74 as described herein than as described herein second Material 76 is submissiveer.First material can be the fibrous composite with resin.First material 74 can have 5Msi to 20Msi Elasticity modulus between (34 arrive 140Gpa).

In the one aspect of disclosure described herein, the second material 76 for forming second part 66 is non-compliant material Material.It is non-compliant to mean the rigid material with very little or none elasticity, remain less than the adaptability to changes of the first material 74.It is non-soft It can be the combination of composite fibre, carbon fiber, epoxy resin fiber or both along material, wherein second part 66 is laminated compound Object.It is contemplated that the elasticity modulus of the second material 76 is greater than 10Msi(65GPa), and preferably greater than 20Msi(140Gpa).

In one non-limiting example, the first material 74 can be for 10Msi(65Gpa) elasticity modulus compound (compound of relatively low range rigidity), and the second material 76 can be for 20Msi(200GPa) elasticity modulus it is another multiple It closes object (high rigidity compound).The discontinuous of ingredient between tip 52 as described herein and composite core 62 is limited to have Two kinds of compounds of dual extension-compression modulus.

Fuse 68 as described herein is shown as having generally flat profile, it should be understood, however, that fuse 68 can have Bending, broken or change in elevation profile.By this method, second part 66 can be in wing chord along the range (X) that spanwise extends Direction passes in and out page variation.As it was noted above, range (X) is to reach 5% length (Fig. 2) of spanwise length (L).It also conceives It is, depending on the method for first part 64 to be connected to second part 66, the changeable width of fuse 68 as described herein It spends (W) (perpendicular to the size of range (X)).Method for connecting first part 64 and second part 66 may include but be not limited to Soldering, welding and adhesive combine.

Tip cap 54 as described herein may be formed on the two sides of composite core 62 as shown in the figure.It is contemplated that tip Cap 54 is created as surrounding 100% continuous piece of composite core 62 at tip 52, or (passes through in any suitable method Non-limiting example, soldering, welding and adhesive combination) it is bound to two discrete items of composite core.Tip cap 54 may be formed at Fan blade 30 as shown in the figure on the pressure side 78 and 80 the two of suction side on.It also conceives, tip cap 54 is in chordwise On along tip 52 at least 50% extend.

It is used to form blade as described herein (by non-limiting example, the fan blade 30 with composite core 62) Method may include first part 64 and the second part 66 to form composite core 62.In forming first part 64, make first part 64 from root 50(Fig. 1) extend radially outward until be less than spanwise length (L) 100%.In forming second part 66, make Second part 66 encounters first part 64 from tip 52 is radially inwardly extending.Forming second part may also include by such as herein The rigid non-compliant material forms second part 66.By non-limiting example, method can be with the business manufacturer of blade Method is consistent, wherein the fibrous composite with resin is used for first part 64.By non-limiting example, manufacturing method can be wrapped Include autoclave, pressing mold or RTM(resin transfer molding).By non-limiting example, second part 66 can be ceramic fibre or carbon Fiber has the adaptability to changes low compared to first part 64 as described herein.

First part 64 is linked to second part 66 to form fuse 68.Connection may include first part 64 and second Divide 66 one of interlocking, intertexture, docking or overlap joint.In one non-limiting example, before linking tip cap 54 or In same step, method may include laminated and solidification second part 66, laminated and solidification first part 64, then links them Together.It also conceives, solidification can occur in same step.In the other side of disclosure, the first material 74 and second material 76 can be woven to and transit to the second material 76 from the first material 74 and then using injecting resin and tip cap 54 cured preform constructions.It should be understood that it includes all that these processes, which are not, and it is conceivable that linking portion as described herein To form other processes of fuse 68.Therefore, by non-limiting example, fuse 68 is interlocking, interweaves, docks or overlap One of connector.This method may also include tip cap 54 as described herein and extend around at least part of tip 52.

Fig. 4 is putting according to the frangible region 170 for composite core 162 of the other side of disclosure described herein Big view.Frangible region 170 is substantially similar to frangible region 70, therefore similar portion will indicate the like numeral for increasing by 100, wherein It should be understood that the description of the similar portion of frangible region 70 is suitable for frangible region 170, unless otherwise noted.Tip cap 154 can be along pressure One of side 178 or suction side 180 are formed, by non-limiting example, only along suction side 180 as shown in the figure.

Fig. 5 is putting according to the frangible region 270 for composite core 262 of the other side of disclosure described herein Big view.Frangible region 270 is substantially similar to frangible region 70, therefore similar portion will indicate the like numeral for increasing by 200, wherein It should be understood that the description of the similar portion of frangible region 70 is suitable for frangible region 270, unless otherwise noted.Composite core 262 limits pressure Both side 278 and suction side 280.In this nonlimiting example, tip cap does not surround any part of fan blade 30, and multiple It closes core 262 and limits entire fan blade 30.

Fig. 6 is the fan according to the fan component 14 for turbogenerator 10 of the other side of disclosure The schematic diagram of blade 130.Fan blade 130 is substantially similar to fan blade 30.Therefore, similar portion will indicate increase by 100 Like numeral, wherein it will be understood that, the description of the similar portion of fan blade 30 is suitable for fan blade 130, unless in addition finger Out.

Preceding edge strip 156 can be provided along the leading edge 146 of fan blade 130.Preceding edge strip 156 can mount to fan blade 130 Composite core 162.Preceding edge strip 156 may include first part 156a and second part 156b, and wherein first part 156a is along span side Extend to the region of the root 150 from neighbouring fan blade 130 along leading edge 146 towards tip 152.The first part of preceding edge strip 156 156a can be formed by any metal material of the operation convenient for fan component 14 as described herein, including but not limited to titanium alloy Such as Ti64, steel alloy or nickel alloy.The first part 156a of preceding edge strip 156 can be formed by material, the material be with range from The metal material of the elasticity modulus of 15Msi to 40Msi.In some aspects of disclosure, elasticity modulus can range from 15 To 30Msi.Elasticity modulus quantify first part 156a or second part 156b along axis deformation trend (when opposite power was along should When axis applies).In other words, elasticity modulus can quantify the rigidity of material.Object with relatively low elasticity modulus is bigger Flexible or toughness material.

Second part 156b is radially inwardly extending from tip 152 towards first part 156a in the spanwise direction.Leading edge is molten Disconnected device 163 is formed in first part 156a and encounters second part 156b place.Pass through non-limiting example, leading edge fuse 163 It is formed using banjo fixing butt jointing or lap joint.By non-limiting example, first part 156a and second part 156b can make With soldering, welding or adhesive in conjunction with being bound to each other.First part 156a can be attached to second part by certain methods 156b is such as, but not limited to brazed, welding and adhesive combine.The second part 156b of preceding edge strip 156 can be by convenient for as herein The material of the operation of the fan component 14 and the elasticity modulus having less than the first part 156a for forming preceding edge strip 62 Any metal material is formed.Second part 156b can be formed by the material different from the material for forming first part 156a.Second Part 156b can be metal, including but not limited to titanium alloy such as CPTi and aluminium alloy.The second part 156b of preceding edge strip 156 It can be formed by the metal material of the elasticity modulus with range from 5Msi to 15Msi.In the other side of disclosure, The elasticity modulus for forming the material of second part 156b is smaller than the 80% of the value to form the material of first part 156a.

In the one aspect of disclosure, both preceding edge strip 156 and composite core 162 include frangible region 165 and 170. Leading edge frangible region 165 and the frangible region of composite core 162 170 limit the part of fan blade 130, in blade and cabin 116 or Foreign object (passing through non-limiting example) is flexible when contacting or can disconnect.By non-limiting example, as described earlier in this article, connect Touching may occur during FBO.Frangible region 165,170 as described herein ensures that when contacting with cabin 16 or foreign object, part is broken It splits enough to small and safely by engine.Then, the safe shutdown of engine 10 is possible after FBO.

Preceding edge strip 156, trailing-edge strip 158 and blade tips cap 154 can be attached to composite core 162 by certain methods, such as But it is not limited to soldering, welding and adhesive to combine.Preceding edge strip 156 can along the radical length (L) of fan blade 130 a part or It is as shown in the figure it is substantially all radially.Preceding edge strip 156 can be in chordwise along the axial width of fan blade 30 (W) a part as shown in the figure substantially all axially extends.

Fig. 7 is the preceding edge strip 256 according to the other side of disclosure described herein.Preceding edge strip 256 substantially class Edge strip 156 before being similar to.Therefore, similar part will indicate the like numeral for increasing by 100, wherein it should be understood that the phase of preceding edge strip 156 It is suitable for preceding edge strip 256 like the description of part, unless specified otherwise herein.

Preceding edge strip 256 may include Part III 256c.The first part 256a of preceding edge strip 256 is in the spanwise direction first Extend between end or root portion 290 and second end 292, to limit as described herein for the leading edge 246 of blade 30 It is most of.Second part 256b is made of the material different from first part 256a and Part III 256c.More particularly, the portion The elasticity modulus having is divided to be lower than the elasticity modulus that the material of first part 256a or Part III 256c is made.Second part 256b is extended radially outward between third end 294 and the 4th end 296 from second end 292 along spanwise.

Part III 256c is extended radially outward from the 4th end 296 in the spanwise direction.Part III 256c can be limited At least part for the tip 252 of blade 30 as described herein.Part III 256c can by with first part or second The different material in part is made.It also conceives, Part III 256c is made of material identical with first part 256a.Pass through Soldering, welding or adhesive knot can be used in non-limiting example, first part 256a, second part 256b and Part III 256c Conjunction method is combined together.Before second part 256b can be defined between first part 256a and Part III 256c Edge fuse 263, wherein leading edge frangible region 265, which can limit, is used for as described herein around the leading edge fuse 263 of blade 30 Region.It is contemplated that leading edge fuse 263 is formed by two banjo fixing butt jointings as shown in the figure or multiple lap joints.

As described herein be used to form blade 30 method may also include to be formed before edge strip 156,256, with by with First part 156a, 256a made of the different material of material of second part 156b, 256b, and wherein second part is made 156b, 256b have the elasticity modulus lower than first part 156a, 256a.

With formed during to have the associated benefit of the fan blade of non-uniform composite core include extreme event by It is broken to control fan blade.Material at the periphery of blade is become into the elasticity modulus different from the rest part of blade material It is broken to allow for controlled fan blade.By locally changing the elasticity modulus of the material at blade tips, as described herein Fuse produces, this will allow blade tips to fail under weight friction load.

By non-limiting example, during FBO, blade selectively failure is made to can help to engine during operation The cost savings in other regions.The groove being currently known being located in holding shell internal diameter (the usually nested place of blade) may occur The removal of filling system.This will reduce total weight and leads to cost savings.

It is not describing to a certain extent, the different characteristic and structure of various embodiments can be by expectations and combination with one another. A unshowned feature, which is not to be construed as it, in all embodiments not may be present, but only for describe it is simple and It does so.Therefore, the various features of different embodiments can be mixed and matched by expectation to form new embodiment, regardless of whether New embodiment is directly described.All combinations or displacement as described herein are covered by present disclosure.

This written description has used example to disclose the present invention, including optimal mode, and also makes any technology of this field Personnel can practice the present invention, including make and use any device or system, and execute any method being incorporated to.The present invention Patentable scope be defined by the claims, and may include other examples that those skilled in the art expects.If it is such its Its example has not different from the structural detail of the written language of claim, or if they include the book with claim Equivalent structural elements of the face language without essential difference then it is expected such other examples within the scope of the claims.

Claims

1. a kind of airfoil for turbogenerator, the airfoil include:

2. airfoil according to claim 1, wherein first material is with the adaptability to changes more than or equal to 1% Conformable material, and second material be with less than or equal to 1% adaptability to changes less submissive material.

3. airfoil according to claim 1, wherein the adaptability to changes that second material has is less than first material The 85% of the adaptability to changes of material.

4. airfoil according to claim 1, wherein the second part is radially extended from the first part to be reached The 5% of the spanwise length.

5. airfoil according to claim 1, wherein second material has the elasticity modulus greater than 10Msi.

6. airfoil according to claim 1, wherein first material has the springform between 5Msi to 20Msi Amount.

7. airfoil according to claim 1 further includes the fuse between the first part and the second part To limit frangible region.

8. airfoil according to claim 7, wherein the fuse is interlocking, interweaves, in docking or lap joint One.

9. airfoil according to claim 1 further includes the tip cap extended along at least part of the tip.

10. airfoil according to claim 9, wherein the tip cap is in the chordwise along the tip At least 50% extends.