CN108930664A - Mixed structure aeroengine fan blades - Google Patents
Mixed structure aeroengine fan blades Download PDFInfo
- Publication number
- CN108930664A CN108930664A CN201710372747.3A CN201710372747A CN108930664A CN 108930664 A CN108930664 A CN 108930664A CN 201710372747 A CN201710372747 A CN 201710372747A CN 108930664 A CN108930664 A CN 108930664A
- Authority
- CN
- China
- Prior art keywords
- leading edge
- blade
- mixed structure
- fan blades
- edge panel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
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- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
Abstract
The present invention provides a kind of mixed structure aeroengine fan blades comprising metal leading edge panel and composite portions, the metal leading edge panel and the composite portions are combined into one in such a way that interface couples.Mixed structure aeroengine fan blades of the present invention can effectively take into account strength character and weight loss effect, and reduce the difficulty of the processing technology of conventional composite materials fan blade, be the very promising developing direction of the big bypass ratio fan blade of lightweight.
Description
Technical field
The present invention relates to aeroengine fan blades, in particular to a kind of mixed structure aeroengine fan blades.
Background technique
In aero-engine field, large scale, lightweight fan blade are the key parts of big Bypass Ratio Turbofan Engine
One of.Currently, there are mainly two types of schemes for the big bypass ratio fan blade of the lightweight for being successfully applied to aero-engine in the world：It is a kind of
It is the pure titanium alloy hollow fan blade of R&R company, the composite material blade one is GE company with metal reinforcement side and bound edge.
In this regard, if measuring lightweight wind with equivalent hollow rate (the solid titanium alloy blade weight of practical leaf weight/identical size)
The weight loss effect of fan leaf, the full titanium alloy hollow blade of R&R company have reached 40% loss of weight (i.e. practical hollow rate), and GE
The composite material of company-titanium alloy bound edge blade then has been achieved with the loss of weight of 60% or more equivalent hollow rate.Due to having preferably
The mixed structure of weight loss effect, composite material and metal, it has also become major big bypass ratio fan blade hair of Engine Company's lightweight
The mainstream of exhibition.
Metal part in mixed structure blade is mainly used for enhancing the impact strength of blade.External existing composite wood
Expect that blade enhances blade shock resistance using titanium alloy binding structure, titanium alloy bound edge is fixed on composite material leaf by being glued
Body.
However, since the design that composite material fan metal used at present reinforces side is limited to traditional processing technology,
Therefore the supplier of only a few has the ability that processing metal reinforces side in the world, technical threshold and cost are in always
Under not.
In addition, blade shape construction is complicated, the difficulty of processing that this also has led to woven composite is very big, becomes development bottle
Neck, it is difficult to break through in a short time.
In consideration of it, those skilled in the art urgently develop the blade of more lightweight, and there is stronger shock resistance.
Summary of the invention
The technical problem to be solved by the present invention is in order to overcome blade shape construction complexity in the prior art, difficulty of processing is big to be lacked
It falls into, a kind of mixed structure aerial engine fan is provided.
The present invention is to solve above-mentioned technical problem by following technical proposals：
A kind of mixed structure aeroengine fan blades, it is characterized in that, the mixed structure aerial engine fan
Blade includes metal leading edge panel and composite portions, and the metal leading edge panel and the composite portions are joined with interface
The mode connect is combined into one.
Preferably, the composite portions include blade face and tenon.
Preferably, the metal leading edge panel of the mixed structure aeroengine fan blades along blade exhibition to from blade tip
Extend to the tenon bottom.
Preferably, the faceplate part in the metal leading edge panel extends to the fan along the tangential of the fan blade
The middle front part of blade；
Or the faceplate part in the metal leading edge panel extends to the trailing edge of the fan blade；
Or the faceplate part in the metal leading edge panel wraps up the composite portions.
Preferably, the width of the leading edge portion in the metal leading edge panel is the 10%- of corresponding position leaf chord length
30%.
Preferably, the width of the faceplate part in the metal leading edge panel is the 5%- of corresponding position vane thickness
40%.
Preferably, fluted or boss is arranged in the leading edge portion and faceplate part of the metal leading edge panel, correspondingly
The composite portions setting boss or groove；
The groove type of the composite portions setting of boss and connection interface corresponding position in the leading edge portion
At mechanical attachment；
The boss shape of the composite portions setting of groove and connection interface corresponding position on the faceplate part
At mechanical attachment.
Preferably, the leading edge portion and the faceplate part are continuous integral type, using rounded corner transition；
The faceplate part and the leading edge portion use rounded corner transition at suction surface, the faceplate part and described
Coupling structure between composite portions uses smooth surface.
Preferably, the blade face and the tenon are made of titanium alloy, woven composite and glue-line, the metal leading edge
Panel and the composite portions couple to form entire fan blade by the glue-line.
Preferably, the 60%- with a thickness of the blade overall thickness of the composite portions at the faceplate part
95%.
The positive effect of the present invention is that：
Mixed structure aeroengine fan blades of the present invention are made of metallic composite, and metal part can pass through increasing
Material fabrication technique keeps the design for the metal shock resistance structure for being limited to conventional machining process originally more flexible, such as can
To use network, cored structure, cavity structure, and the geometry after topological optimization, blade anti-impact can be enhanced
Performance is hit, lighter blade is obtained.In addition, the composite material that mixed structure blade uses is opened up along blade to thickness and external form shape
The reduction of shape variable gradient, to reduce the difficulty of composite material process planning.
Therefore, mixed structure aeroengine fan blades of the present invention can effectively take into account strength character and loss of weight effect
Fruit, and the difficulty of the processing technology of conventional composite materials fan blade is reduced, it is that the big bypass ratio fan blade of lightweight has very much
The developing direction of prospect.
Detailed description of the invention
The above and other feature of the present invention, property and advantage will pass through description with reference to the accompanying drawings and examples
And become apparent, identical appended drawing reference always shows identical feature in the accompanying drawings, wherein：
Fig. 1 is the structural schematic diagram of mixed structure aeroengine fan blades of the present invention.
Fig. 2 is the cross-sectional view splitted in Fig. 1 along line A-A.
Fig. 3 is the cross-sectional view splitted in Fig. 1 along line B-B.
Fig. 4 is the longitudinal sectional drawing of mixed structure aeroengine fan blades of the present invention.
Fig. 5 is that mixed structure aeroengine fan blades of the present invention couple schematic diagram.
Fig. 6 is that the suture of mixed structure aeroengine fan blades of the present invention couples schematic diagram.
Fig. 7 is the structural schematic diagram one of metal leading edge panel in mixed structure aeroengine fan blades of the present invention.
Fig. 8 is the structural schematic diagram two of metal leading edge panel in mixed structure aeroengine fan blades of the present invention.
Fig. 9 is the structural schematic diagram three of metal leading edge panel in mixed structure aeroengine fan blades of the present invention.
Specific embodiment
For the above objects, features and advantages of the present invention can be clearer and more comprehensible, below in conjunction with attached drawing to tool of the invention
Body embodiment elaborates.
The embodiment of the present invention is described with detailed reference to attached drawing now, its example is shown in the drawings.Any possible
In the case of, in all the appended drawings the same or similar part will be indicated using identical label.In addition, although institute in the present invention
The term used is to select from public term, but some terms mentioned in description of the invention may be
Applicant carrys out selection by his or her judgement, and detailed meanings illustrate in the relevant portion of description herein.Furthermore, it is desirable that
Not only by used actual terms, and the meaning contained by each term is also to understand the present invention.
Fig. 1 is the structural schematic diagram of mixed structure aeroengine fan blades of the present invention.Fig. 2 is to cut open in Fig. 1 along line A-A
The cross-sectional view opened.Fig. 3 is the cross-sectional view splitted in Fig. 1 along line B-B.Fig. 4 is mixed structure aerial engine fan leaf of the present invention
The longitudinal sectional drawing of piece.Fig. 5 is that mixed structure aeroengine fan blades of the present invention couple schematic diagram.Fig. 6 is that the present invention is mixed
The suture for closing structural aeronautical engine blower blade couples schematic diagram.Fig. 7 is mixed structure aerial engine fan leaf of the present invention
The structural schematic diagram one of metal leading edge panel in piece.Before Fig. 8 is metal in mixed structure aeroengine fan blades of the present invention
The structural schematic diagram two of edge panel.Fig. 9 is the knot of metal leading edge panel in mixed structure aeroengine fan blades of the present invention
Structure schematic diagram three.
As shown in Figure 1 to Figure 3, the invention discloses a kind of mixed structure aeroengine fan blades 10 comprising gold
Belong to leading edge panel 20 and composite portions, metal leading edge panel 20 and the composite portions group in such a way that interface couples
It is integrated.Preferably, the composite portions include blade face 30 and tenon 40.Here metal leading edge panel 20 can be adopted
It is made of metal materials such as titanium alloy, aluminium alloys, in the present embodiment by taking titanium alloy as an example.
Blade face 30 and tenon 40 are made of titanium alloy, woven composite 50 and glue-line 60 in the present embodiment, the metal
Leading edge panel 20 and the composite portions couple to form entire fan blade by the glue-line.
Particularly, the woven composite refers to logical by resin matrix and fibrous material therein (metal or nonmetallic)
Heat curing process is crossed to be molded with.Fibrous material includes but is not limited to aramid fibre, carbon fiber, glass fibre and its group
Close room.Matrix resin includes but is not limited to polyamide, policapram and combinations thereof etc..Component, the machine direction of composite material
By design, to improve its mechanical property, while cost is reduced.Composite density is less than the density of metallic core material, and
The impact that fan blade may be subjected to can be born by having comparable mechanical property, as bird is hit.
Metal leading edge panel 20 along blade exhibition to the bottom for extending to tenon 40 from blade tip.In metal leading edge panel 20
The width of leading edge portion 21 is the 10%-30% of corresponding position leaf chord length.The width of leading edge portion 21 along blade exhibition to
Variation, and the width for being located at the faceplate part 25 of the metal leading edge panel 20 of blade pressure surface 31 can be extended to along blade is tangential
The different location of width of blade, width are opened up along blade to that can change, and do not have metal leading edge panel 20 at suction surface 32.
The width of faceplate part 25 in metal leading edge panel 20 is the 5%-40% of corresponding position vane thickness, along leaf
The thickness of the tangential faceplate part 25 of piece can change.The all metals of metal leading edge panel 20, intensity is high, and main function is outside
When object impacts (such as bird is hit), impact force suffered by blade and composite portions is reduced and reduced, it is ensured that the integrality of blade, simultaneously
Also the strength and stiffness of blade are improved.
Fluted 27 or boss 26 are set in the leading edge portion 21 and faceplate part 25 of metal leading edge panel 20, correspondingly institute
Composite portions setting boss or groove are stated, so that the boss 26 and connection interface corresponding position in leading edge portion 21 is described
The groove of composite portions setting forms mechanical attachment, the institute of groove 27 and connection interface corresponding position on faceplate part 25
The boss for stating composite portions setting forms mechanical attachment.When fan blade deformation.Boss 26 and groove 27 interact,
Enhance the intensity at the connection interface of metal leading edge panel 20 and the composite material.Boss 26 on faceplate part 25 can be every
Disconnected glue-line 60 can block glue-line to destroy when glue-line 60 destroys, and reduce the whole of glue-line 60 and destroy, retain metal covering
The linking intensity at the interface of plate and composite material cannot make metal decking and composite material completely separable, keep fan blade
Globality.
Leading edge portion 21 and faceplate part 25 are continuous integral type, rounded corner transition can be used, to avoid answering on panel
Power concentrates (as shown in Figure 1).Faceplate part 25 and leading edge portion 21 use rounded corner transition 22 at suction surface 31.In panel part
Points 25 and the coupling structure of the composite material are smooth surface 23, and the tail portion of faceplate part 25 is 24 transition of circular arc, to keep away
The stress exempted from composite structure is concentrated.
Particularly, leading edge portion 21 can use solid construction, can also use hollow structure, or use other fillers
It is full of.Hollow structure herein can be hollow structure, lightweight structure etc., filler can select lightweight composite material,
Rubber or fluid etc..
As shown in figure 4, in the present invention preferably, blade face 30 and tenon 40 are made of three kinds of materials：Titanium alloy, braiding
Composite material 50, and the glue-line 60 that the two is linked up.Metal leading edge panel 20 and woven composite 50 pass through glue-line
60 are connected into entire fan blade.The woven composite 50 of 25 side of faceplate part extends to tenon 40 by blade tip lower edge
Bottom, at faceplate part 25 formed have three-decker：Faceplate part 25 on suction surface 32, it is compound on pressure face 31
Material 50, and the glue-line 60 that composite material 50 and faceplate part 25 are linked up.Composite material 50 at faceplate part 25
Overall thickness be blade locality thickness 60%~95%, remaining be glue-line 60.
As shown in Figure 5 and Figure 6, metal leading edge panel 20 and multiple in mixed structure aeroengine fan blades 10 of the present invention
Condensation material 50 is connected as one by overlap joint, and overlap described herein can be formed mechanical by rivet or bolt 70
It connects, tangential with number that is opening up riveting or bolt-connection that can according to need design to position different.Metal leading edge panel
It can also be coupled by suture 80 between 20 and composite material 50, need to design different sewing densities according to intensity.
Suture 80 is made of carbon fiber or other high-intensitive and soft material.
As shown in Figure 7 to 9, further, metal leading edge panel 20 can be along the tangential difference for extending to fan blade
Position can reduce the weight of fan blade if faceplate part 25 extends to fan blade middle front part along tangential in this way；Or
Person, faceplate part 25 extend to blade trailing edge, increase the intensity and rigid body of blade, improve the bird impact resistance of blade；Again alternatively,
Faceplate part 25 extends to trailing edge, and is transitioned into metal trailing edge, and leading edge portion, faceplate part and trailing edge wrap up composite material, from
And increasing the strength and stiffness of blade, the width of metal trailing edge is 5% to the 20% of width of blade.
According to above structure, the effect of metal leading edge panel 20 is mainly to provide the intensity of blade in the present invention.Its with it is preceding
Edge, trailing edge and blade tip be it is continuous, so as to significantly improve the impact strength of blade, mitigate composite portions by
Impact.The main function of glue-line 60 is connection composite material and Titanium panel, makes have certain linking intensity between the two,
Both kept under defined external load function relative position is constant, not degumming separation, and deformation is continuous coordinates.Composite wood
Material uses D braided composites, and main component is carbon fiber and resin, and effect is to provide the corresponding rigidity of blade and strong
Degree, while mitigating leaf quality.
In addition, the metal leading edge panel 20 of blade can such as forge and press, or increase material system according to its structure type by traditional handicraft
Equal unconventional process (such as selective laser cladding) is made to be process.
After the structure of blade is improved, metal leading edge panel 20 and composite portions are under centrifugal force and impact operating condition
Stress and deformation are preferably improved.If the following table 1 compared at same rotational speed (3790rpm), two chip architecture mixed structures
Blade and multiple material blade equivalent stress and deformation.Table 2 compared under the conditions of identical bird hits, two panels mixed structure blade and multiple
Material blade equivalent stress and deformation.By Tables 1 and 2 as it can be seen that when stress is greatly reduced, the deformation of composite portions
Have reduces to a certain degree.
Table 1：Under same rotational speed (3790rpm), two chip architecture mixed structure blades and again material blade equivalent stress and deformation
Situation.
Table 2：Under the conditions of identical bird is hit, two panels mixed structure blade and again material blade equivalent stress and deformation.
By above structure it is found that mixed structure aeroengine fan blades of the present invention reduce mixed structure fan blade
The difficulty of processing of metal part avoids the processing that metal reinforces side cladding bound edge.
Specifically, mixed structure fan blade is two panels bridging type structure, only piece of metal leading edge panel and a piece of
Composite material, the tangential part of blade are metal, and middle section is the mixing portion of metal and composite material, and rear portion is divided into composite wood
Material.
For this structure compared with traditional fan, the entire blade ratio as shared by metal leading edge panel is smaller, only before
Edge is divided into metal, and the tangential latter half of blade is all composite material, has used the lesser composite material of more density ratio, drop
The low quality of fan blade, and can use hollow structure in metal leading edge allows mixed structure fan blade and compound
The leaf quality of material is suitable.
The connection of the metal and composite material of mixed structure aeroengine fan blades of the present invention by it is cementing, suture,
The mode of riveting etc. couples, and couples interface boss or groove, increases interface linking intensity.
Mixed structure aeroengine fan blades of the present invention are using metal as leading edge and panel, the intensity of metal material
It is all higher with toughness, in the case of foreign object impact, metal by plastic deformation can most of impact force and energy, reduce compound
The deformation and stress of material, reduce the damage of composite material.
In conclusion mixed structure aeroengine fan blades of the present invention are made of metallic composite, metal portion
Dividing can be processed by increases material manufacturing technology, keep the design for the metal shock resistance structure for being limited to conventional machining process originally cleverer
It is living, such as network, cored structure, cavity structure, and the geometry after topological optimization can be used, it can be enhanced
Blade shock resistance obtains lighter blade.In addition, the composite material that mixed structure blade uses is opened up along blade to thickness
With the reduction of external form change in shape gradient, to reduce the difficulty of composite material process planning.
Therefore, mixed structure aeroengine fan blades of the present invention can effectively take into account strength character and loss of weight effect
Fruit, and the difficulty of the processing technology of conventional composite materials fan blade is reduced, it is that the big bypass ratio fan blade of lightweight has very much
The developing direction of prospect.
Although specific embodiments of the present invention have been described above, it will be appreciated by those of skill in the art that these
It is merely illustrative of, protection scope of the present invention is defined by the appended claims.Those skilled in the art is not carrying on the back
Under the premise of from the principle and substance of the present invention, various changes or modifications can be made to these embodiments, but these are changed
Protection scope of the present invention is each fallen with modification.
Claims (10)
1. a kind of mixed structure aeroengine fan blades, which is characterized in that the mixed structure aerial engine fan leaf
Piece includes metal leading edge panel and composite portions, and the metal leading edge panel and the composite portions are coupled with interface
Mode be combined into one.
2. mixed structure aeroengine fan blades as described in claim 1, which is characterized in that the composite portions
Including blade face and tenon.
3. mixed structure aeroengine fan blades as claimed in claim 2, which is characterized in that the mixed structure aviation
The metal leading edge panel of engine blower blade extends to the tenon bottom to from blade tip along the exhibition of blade.
4. mixed structure aeroengine fan blades as claimed in claim 3, which is characterized in that the metal leading edge panel
In faceplate part along the fan blade the tangential middle front part for extending to the fan blade；
Or the faceplate part in the metal leading edge panel extends to the trailing edge of the fan blade；
Or the faceplate part in the metal leading edge panel wraps up the composite portions.
5. mixed structure aeroengine fan blades as claimed in claim 3, which is characterized in that the metal leading edge panel
In leading edge portion width be corresponding position leaf chord length 10%-30%.
6. mixed structure aeroengine fan blades as claimed in claim 3, which is characterized in that the metal leading edge panel
In faceplate part width be corresponding position vane thickness 5%-40%.
7. mixed structure aeroengine fan blades as claimed in claim 3, which is characterized in that the metal leading edge panel
Leading edge portion and faceplate part on fluted or boss is set, correspondingly composite portions setting boss or groove；
The groove of the composite portions setting of boss and connection interface corresponding position in the leading edge portion forms machine
Tool connection；
The boss of the composite portions setting of groove and connection interface corresponding position on the faceplate part forms machine
Tool connection.
8. mixed structure aeroengine fan blades as claimed in claim 7, which is characterized in that the leading edge portion and institute
Stating faceplate part is continuous integral type, using rounded corner transition；
The faceplate part and the leading edge portion use rounded corner transition at suction surface, the faceplate part and described compound
Coupling structure between material part uses smooth surface.
9. mixed structure aeroengine fan blades as claimed in claim 2, which is characterized in that the blade face and the tenon
Head is made of titanium alloy, woven composite and glue-line, and the metal leading edge panel and the composite portions are described in
Glue-line couples to form entire fan blade.
10. mixed structure aeroengine fan blades as claimed in claim 9, which is characterized in that at the faceplate part
The composite portions the 60%-95% with a thickness of the blade overall thickness.
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| CN201710372747.3A CN108930664A (en) | 2017-05-24 | 2017-05-24 | Mixed structure aeroengine fan blades |
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| CN201710372747.3A CN108930664A (en) | 2017-05-24 | 2017-05-24 | Mixed structure aeroengine fan blades |
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Family
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112065772A (en) * | 2020-08-28 | 2020-12-11 | 南京航空航天大学 | Fan blade with folding core plate |
| CN113494483A (en) * | 2020-03-20 | 2021-10-12 | 中国航发商用航空发动机有限责任公司 | Fan blade |
| CN113547772A (en) * | 2021-06-08 | 2021-10-26 | 南京玻璃纤维研究设计院有限公司 | Preparation method of fan blade with mixed structure |
| CN114439613A (en) * | 2020-10-30 | 2022-05-06 | 中国航发商用航空发动机有限责任公司 | Aircraft engine fan blade and aircraft engine |
| CN114798363A (en) * | 2021-01-29 | 2022-07-29 | 中国航发商用航空发动机有限责任公司 | Aeroengine fan blade metal reinforcing edge glue joint curing device |
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| CN113494483B (en) * | 2020-03-20 | 2023-01-10 | 中国航发商用航空发动机有限责任公司 | Fan blade |
| CN112065772A (en) * | 2020-08-28 | 2020-12-11 | 南京航空航天大学 | Fan blade with folding core plate |
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