CN110067772B - Aeroengine fan blade and manufacturing method thereof - Google Patents
Aeroengine fan blade and manufacturing method thereof Download PDFInfo
- Publication number
- CN110067772B CN110067772B CN201910426590.7A CN201910426590A CN110067772B CN 110067772 B CN110067772 B CN 110067772B CN 201910426590 A CN201910426590 A CN 201910426590A CN 110067772 B CN110067772 B CN 110067772B
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- metal
- solder
- fiber
- framework
- resin
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 16
- 239000002184 metal Substances 0.000 claims abstract description 83
- 239000000835 fiber Substances 0.000 claims abstract description 64
- 229910000679 solder Inorganic materials 0.000 claims abstract description 46
- 239000011347 resin Substances 0.000 claims abstract description 34
- 229920005989 resin Polymers 0.000 claims abstract description 34
- 238000005219 brazing Methods 0.000 claims abstract description 20
- 239000000945 filler Substances 0.000 claims abstract description 18
- 238000000034 method Methods 0.000 claims abstract description 11
- 238000010438 heat treatment Methods 0.000 claims abstract description 10
- 235000013290 Sagittaria latifolia Nutrition 0.000 claims abstract description 6
- 235000015246 common arrowhead Nutrition 0.000 claims abstract description 6
- 238000004804 winding Methods 0.000 claims abstract description 5
- 238000010146 3D printing Methods 0.000 claims description 4
- 238000001764 infiltration Methods 0.000 claims description 4
- 230000008595 infiltration Effects 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 4
- 238000003754 machining Methods 0.000 claims description 3
- 230000005855 radiation Effects 0.000 claims description 3
- 238000007788 roughening Methods 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 238000005253 cladding Methods 0.000 claims description 2
- 238000005488 sandblasting Methods 0.000 claims description 2
- 239000002131 composite material Substances 0.000 abstract description 8
- 238000009941 weaving Methods 0.000 abstract description 2
- 239000013585 weight reducing agent Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000007711 solidification Methods 0.000 description 2
- 230000008023 solidification Effects 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 238000005422 blasting Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 238000009736 wetting Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A method of making an aero-engine fan blade, comprising: s1, processing a metal framework, wherein the section of the metal framework is of a single arrow or double arrow head band hole arc structure; s2, setting brazing filler metal on the surface of a non-arrow part of the metal framework; s3, winding the fibers on the surface of the metal framework through holes on the metal framework so that the fibers form a fiber braid; s4, heating the solder to enable the solder to melt and infiltrate part of the fiber braid; and S5, impregnating resin on the non-impregnated solder part of the fiber woven body and curing the resin to form the fan blade of the aero-engine. In another aspect of the present invention, there is provided an aircraft engine fan blade comprising: the metal skeleton (100) and the solidified layer (200), wherein the solidified layer (200) comprises a brazing filler metal fiber solidified layer (201) and a fiber resin solidified layer (202). The weight of the aero-engine fan blade is reduced and the strength of the aero-engine fan blade is increased through the composite weaving and brazing method.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to an aero-engine fan blade and a manufacturing method thereof.
Background
Along with the continuous improvement of the thrust-weight ratio requirement of the aero-engine, the use frequency of the composite material is more and more, and the composite material has the characteristics of anisotropy, if the composite material is consistent with the stress direction of the blade, the composite material can bear extremely large load, has light weight and can effectively reduce the weight of the blade and even the whole engine, however, the fan blade of the engine is longer and longer, the blade with a tape laying method cannot meet the impact, the strength of the root of the integrally woven blade is insufficient, and the edge of the wide chord blade manufactured by the traditional method is weak in space and rigidity, and has high processing difficulty and high cost; the small blade has small structural size and thin blade, the weight reduction effect of the traditional design is not obvious, and the structural strength is reduced, so that the composite material is not beneficial to the use of the composite material on a low bypass ratio and high-rotation-speed engine.
Disclosure of Invention
First, the technical problem to be solved
Based on the technical problems, the invention provides the aero-engine fan blade and the manufacturing method thereof, and the weight of the aero-engine fan blade is reduced by the composite weaving and brazing method, and the strength of the aero-engine fan blade is increased.
(II) technical scheme
In a first aspect, the present invention provides a method for manufacturing an aero-engine fan blade, comprising: s1, processing a metal framework, wherein the section of the metal framework is of a single arrow or double arrow head band hole arc structure; s2, setting brazing filler metal on the surface of a non-arrow part of the metal framework; s3, winding the fibers on the surface of the metal framework through holes on the metal framework so that the fibers form a fiber braid; s4, heating the solder to enable the solder to melt and infiltrate part of the fiber braid; and S5, impregnating resin on the non-impregnated solder part of the fiber woven body and curing the resin to form the fan blade of the aero-engine.
Optionally, step S2 further includes, before: the surface of the non-arrowed portion of the metal skeleton is subjected to blasting or roughening treatment.
Optionally, step S5 further includes: the cured resin was polished to smooth the transition of the resin surface to the arrow surface.
Optionally, the solder is heated by a high temperature furnace or high temperature radiation.
Optionally, in step S2, a solder is sprayed or spread on the surface of the non-arrowed portion of the metal skeleton.
Optionally, the wetting and curing temperature of the resin is less than or equal to the temperature of the solder.
In a second aspect, the present invention provides an aircraft engine fan blade comprising: the metal framework 100 comprises an arc-shaped framework 102 and an arrow part 101, wherein a plurality of through holes 103 are formed in the arc-shaped framework 102, and the arrow part 101 is arranged at the windward end of the arc-shaped framework 102; the solidified layer 200 comprises a solder fiber solidified layer 201 and a fiber resin solidified layer 202, wherein the solder fiber solidified layer 201 comprises solder and fibers, is arranged on the surface of the arc-shaped framework 102 and is inserted into the holes 103; the fiber resin cured layer 202, which includes fibers and resin, is provided on the outer surface of the solder fiber cured layer 201.
Alternatively, the solder is in the form of a liquid, paste or ribbon.
Optionally, the metal skeleton (100) is machined using machining or 3D printing techniques.
Optionally, a metal cladding layer is provided on the surface of the arrow part (101) of the windward end. .
(III) beneficial effects
The invention provides an aeroengine fan blade and a manufacturing method thereof, which at least have the following technical effects:
(1) The arc-shaped framework and the arrow-shaped binding are integrally designed in the metal framework, so that the manufacturing difficulty of the binding is reduced, and the rigidity of the metal framework is enhanced;
(2) The brazing filler metal fiber solidified layer is formed by brazing filler metal and fibers, so that the bonding strength of the brazing filler metal fiber solidified layer and the metal framework is enhanced;
(3) The weight of the blade is reduced by adopting the hollowed-out metal framework.
Drawings
FIG. 1 schematically illustrates a method step diagram for fabricating an aircraft engine fan blade in accordance with an embodiment of the present disclosure;
FIG. 2 schematically illustrates a structural schematic of a metal skeleton 100 of an aircraft engine fan blade in accordance with an embodiment of the present disclosure;
FIG. 3 schematically illustrates a structural schematic of an aircraft engine fan blade according to an embodiment of the present disclosure;
FIG. 4 schematically illustrates a cross-sectional view of an aircraft engine fan blade according to an embodiment of the disclosure;
FIG. 5A schematically illustrates a structural schematic of a cured layer 200 of an aircraft engine fan blade in accordance with an embodiment of the present disclosure;
FIG. 5B schematically illustrates a cross-sectional view A-A of the cured layer 200 shown in FIG. 5A in accordance with an embodiment of the present disclosure;
FIG. 6 schematically illustrates a detailed cross-sectional view of an aircraft engine fan blade of an embodiment of the present disclosure.
Detailed Description
The present invention will be further described in detail below with reference to specific embodiments and with reference to the accompanying drawings, in order to make the objects, technical solutions and advantages of the present invention more apparent.
In one aspect, the present invention provides a method for manufacturing an aero-engine fan blade, referring to fig. 1, including: s1, processing a metal framework, wherein the section of the metal framework is of a single arrow or double arrow head hole arc structure; s2, setting brazing filler metal on the surface of a non-arrow part of the metal framework; s3, winding the fibers on the surface of the metal framework through holes on the metal framework so that the fibers form a fiber braid; s4, heating the solder to enable the solder to melt and infiltrate part of the fiber braid; and S5, impregnating resin on the non-impregnated solder part of the fiber woven body and curing the resin to form the fan blade of the aero-engine. Specific examples will be described in detail below.
S1, processing a metal framework, wherein the section of the metal framework is of a single arrow or double arrow head hole arc structure;
The metal skeleton 100 is processed by adopting a machining or 3D printing technology, referring to fig. 2, the metal skeleton 100 comprises an arrow part 101 and an arc skeleton 102, a plurality of through holes 103 are formed in the arc skeleton for weight reduction, the cross section of the arrow part 101 is in an arrow shape, and at least one arc end of the arc skeleton is arranged, namely, the metal skeleton 100 is in a single arrow shape or a double arrow shape, and the arrow end is the front edge of a blade and the metal wrapping edge are integrated. The surface of the arcuate skeleton may be provided with a plurality of projections 104. The metal backbone 100 is the core carrier of the entire aero-engine fan blade.
S2, setting brazing filler metal on the surface of a non-arrow part of the metal framework;
The surface of the non-arrowed portion of the metal skeleton 100 is also required to be sandblasted or roughened before the solder is provided to the surface of the non-arrowed portion of the metal skeleton 100 to increase the surface roughness, facilitating the interfacial bonding of the solder and the metal skeleton 100.
Spraying liquid brazing filler metal or paste or band brazing filler metal on the surface after sand blasting or roughening.
S3, winding the fibers on the surface of the metal framework through holes on the metal framework so that the fibers form a fiber braid;
The fiber is wound and inserted on the surface of the metal framework 100 through the holes on the metal framework 100 to form a fiber braid, and the fiber braid has a certain thickness for carrying out subsequent two-stage infiltration.
S4, heating the solder to enable the solder to melt and infiltrate part of the fiber braid;
And (3) melting the solder by heating the metal skeleton 100 at an elevated temperature, or heating the whole obtained in the step (S3) in a high-temperature environment, such as a high-temperature heating furnace, high-temperature radiation or other heating modes, so that the melted solder and the fibers of the fiber woven body, which are close to the side of the metal skeleton 100, infiltrate to form a solder fiber solidified layer 201. So that the solidified layer 201 of solder fibers and the metal armature 100 are firmly bonded together by the solder.
And S5, impregnating resin on the non-impregnated solder part of the fiber woven body and curing the resin to form the fan blade of the aero-engine.
And infiltrating resin into the non-infiltrated solder part of the fiber woven body, and solidifying the resin, wherein the infiltration and solidification temperature of the resin is less than or equal to the temperature of the solder in order that the infiltration and solidification of the resin do not influence the solder. The fiber braid is not infiltrated with the brazing filler metal part and resin to form a brazing filler metal resin solidified layer 202, the surface of the brazing filler metal resin solidified layer 202 finally forms a blade basin and a blade back of the fan blade, and the operations such as spraying, polishing, finishing and the like are carried out on the fiber braid to enable the surface of the brazing filler metal resin solidified layer 202 to smoothly transition with the arrow radian, so that the fan blade of the aeroengine is formed.
In another aspect, the present invention provides an aircraft engine fan blade, see fig. 3 and 4, comprising a metal skeleton 100 and a cured layer 200, wherein:
The metal framework 100, see fig. 2, comprises an arc-shaped framework 102 and an arrow part 101, wherein the arc-shaped framework is provided with a plurality of through holes 103, and the windward end of the arc-shaped framework 102 is provided with the arrow part 101;
The metal framework 100 is processed by adopting a mechanical processing or 3D printing technology, the metal framework 100 comprises an arrow part 101 and an arc framework 102, a plurality of through holes 103 are formed in the arc framework and are used for weight reduction, the cross section of the arrow part 101 is in an arrow shape, the arrow part 101 is arranged at the windward end of the arc framework 102, the arrow part 101 can be arranged at the windward end, or the arrow part 101 can not be arranged at the windward end, namely, the metal framework 100 is in a single arrow shape or a double arrow shape, and the metal wrapping edge is arranged on the arrow surface of the windward end and is integrated with the metal wrapping edge. The arcuate skeleton 102 may be provided with a plurality of protrusions 104 on its surface, preferably in the form of strips. The metal backbone 100 is the core carrier of the entire aero-engine fan blade.
The cured layer 200, see fig. 5A and 5B, includes a solder fiber cured layer 201 and a fiber resin cured layer 202, see fig. 6, wherein:
a solder fiber solidified layer 201 provided on the surface of the arc-shaped skeleton 102 and penetrating the hole 103;
the solder fiber solidified layer 201 is formed by solidifying fibers with solder, and is adhered to the surface of the metal skeleton 100 by the solder, and the fibers are entangled and inserted on the surface of the metal skeleton 100 through holes on the metal skeleton 100. The solder is liquid, paste or belt.
The fiber resin cured layer 202 is provided on the outer surface of the solder fiber cured layer 201.
The resin is impregnated and cured on the fibers to form a basin and a back of the fan blade, which are provided on the outer surface of the solder fiber cured layer 201.
While the foregoing is directed to embodiments of the present invention, other and further details of the invention may be had by the present invention, it should be understood that the foregoing description is merely illustrative of the present invention and that no limitations are intended to the scope of the invention, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the invention.
Claims (8)
1. A method of making an aero-engine fan blade, comprising:
s1, processing a metal framework, wherein the section of the metal framework is of a single arrow or double arrow head hole arc structure;
S2, setting brazing filler metal on the surface of the non-arrow-shaped part of the metal framework;
s3, winding the fibers on the surface of the metal framework through holes on the metal framework so as to enable the fibers to form a fiber braid;
S4, heating the brazing filler metal to enable the brazing filler metal to melt and infiltrate part of the fiber woven body;
S5, impregnating resin on the non-impregnated solder part of the fiber woven body and solidifying the resin to form the aero-engine fan blade,
Wherein the infiltration and curing temperature of the resin is less than or equal to the temperature of the solder;
The aero-engine fan blade formed comprises:
The metal framework (100) comprises an arc framework (102) and an arrow part (101), wherein a plurality of through holes (103) are formed in the arc framework (102), and the arrow part (101) is formed at the windward end of the arc framework (102);
The solidified layer (200) comprises a solder fiber solidified layer (201) and a fiber resin solidified layer (202), wherein the solder fiber solidified layer (201) comprises solder and fibers, is arranged on the surface of the arc-shaped framework (102) and is inserted into the through hole (103); and a fiber resin solidified layer (202) comprising fibers and resin, which is provided on the outer surface of the solder fiber solidified layer (201).
2. The manufacturing method according to claim 1, further comprising, before step S2:
And carrying out sand blasting or roughening treatment on the surface of the non-arrow-head part of the metal framework.
3. The manufacturing method according to claim 1, step S5 further comprising:
The cured resin is polished to smooth transition of the resin surface to the arrow surface.
4. The manufacturing method according to claim 1, wherein the solder is heated by a high-temperature heating furnace or a high-temperature radiation method.
5. The manufacturing method according to claim 1, wherein in step S2, the brazing filler metal is sprayed or laid on the surface of the non-arrowed portion of the metal skeleton.
6. The method of claim 1, wherein the solder is in the form of a liquid, paste, or ribbon.
7. The manufacturing method according to claim 1, wherein the metal skeleton (100) is machined using machining or 3D printing techniques.
8. The manufacturing method according to claim 1, wherein a metal cladding layer is provided on the surface of the arrow part (101) of the windward end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910426590.7A CN110067772B (en) | 2019-05-21 | 2019-05-21 | Aeroengine fan blade and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910426590.7A CN110067772B (en) | 2019-05-21 | 2019-05-21 | Aeroengine fan blade and manufacturing method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110067772A CN110067772A (en) | 2019-07-30 |
| CN110067772B true CN110067772B (en) | 2024-07-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910426590.7A Active CN110067772B (en) | 2019-05-21 | 2019-05-21 | Aeroengine fan blade and manufacturing method thereof |
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| Country | Link |
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| CN (1) | CN110067772B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110936638A (en) * | 2019-11-29 | 2020-03-31 | 中国科学院工程热物理研究所 | Three-dimensional woven material integrating additive manufacturing and composite material and preparation method thereof |
| CN113910641B (en) * | 2021-10-11 | 2023-06-02 | 成都锐美特新材料科技有限公司 | Carbon fiber composite material product, preparation method thereof and wearable seat |
| CN116160721B (en) * | 2023-02-03 | 2024-05-14 | 武汉理工大学 | Rocket nozzle preparation system |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108661945A (en) * | 2017-03-31 | 2018-10-16 | 中国航发商用航空发动机有限责任公司 | A kind of fan blade |
| CN210509714U (en) * | 2019-05-21 | 2020-05-12 | 中国科学院工程热物理研究所 | Aircraft engine fan blade |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9333578B2 (en) * | 2014-06-30 | 2016-05-10 | General Electric Company | Fiber reinforced brazed components and methods |
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2019
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108661945A (en) * | 2017-03-31 | 2018-10-16 | 中国航发商用航空发动机有限责任公司 | A kind of fan blade |
| CN210509714U (en) * | 2019-05-21 | 2020-05-12 | 中国科学院工程热物理研究所 | Aircraft engine fan blade |
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| Publication number | Publication date |
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| CN110067772A (en) | 2019-07-30 |
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