Lightweight composite material blade for aero-engine

Abstract

The lightweight composite material blade for the aero-engine comprises a blade body and a tenon, the blade body comprises a metal layer, a first carbon fiber composite material layer and a second carbon fiber composite material layer, embedding grooves are formed in the front face and the back face of the metal layer, and the tenon is arranged in the embedding grooves. The embedding grooves are used for mounting the first carbon fiber composite material layer and the second carbon fiber composite material layer; the blade further comprises a metal front edge matched with the blade body, and the metal front edge is fixedly connected with the metal layer. By arranging the metal layer, the first carbon fiber composite material layer and the second carbon fiber composite material layer, in the actual use process, the overall structural stability and impact resistance of the blade body can be guaranteed, the overall weight of the blade body can be reduced, the overall light weight of the blade is guaranteed, and the service life of the blade is prolonged. And the overall weight of the engine is further reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aero-engine, specifically, relate to a kind of lightweight composite material blade for aero-engine. BACKGROUND

[0002] In order to improve the ratio of the aero-engine can promote thrust, reduce noise and unit thrust oil consumption, so in recent years, the ratio of various commercial turbofan engine continues to increase. The main thrust of large-bypass-ratio turbofan engine comes from the cold air flowing through the outer duct. To meet the larger bypass ratio, a larger size fan must be used. However, the fan section mass accounts for about 30%-35% of the total engine mass. Reducing the fan section mass is a key means to reduce the overall engine mass and improve engine efficiency. Therefore, using larger and lighter fan blades has become a development trend for turbofan engines.

[0003] Although the existing metal material has strong impact resistance, the overall weight of the blade is large, and the purpose of weight reduction cannot be achieved. The impact resistance of the blade made of pure composite material blade is poor. To improve the impact resistance of the composite material blade, a metal reinforcing edge is usually bonded to the leading edge of the composite material fan blade to resist the suction of sand or birds encountered during engine operation. However, the metal reinforcing edge and the composite material blade are two different materials, which are difficult to bond together, and the processing cost is high. Therefore, the utility model provides a new solution. UTILITY MODEL CONTENT

[0004] The utility model aims at solving the problem that the existing metal material has strong impact resistance, but the overall weight of the blade is large, and the purpose of weight reduction cannot be achieved. The impact resistance of the blade made of pure composite material blade is poor. To improve the impact resistance of the composite material blade, a metal reinforcing edge is usually bonded to the leading edge of the composite material fan blade to resist the suction of sand or birds encountered during engine operation. However, the metal reinforcing edge and the composite material blade are two different materials, which are difficult to bond together, and the processing cost is high. Therefore, the utility model provides a new solution.

[0005] In order to achieve the above purpose, the utility model provides the following technical scheme:

[0006] The lightweight composite material blade for aero-engine is used to improve the above problems.

[0007] The utility model is specifically as follows:

[0008] The blade body comprises a metal layer, a first carbon fiber composite material layer and a second carbon fiber composite material layer, and the metal layer is provided with an embedding groove on the front surface and the back surface, which is used for mounting the first carbon fiber composite material layer and the second carbon fiber composite material layer.

[0009] The metal leading edge is fixedly connected with the metal layer.

[0010] The metal layer comprises a connecting portion, the bottom end of the connecting portion is fixedly connected with the tenon, and the top end of the connecting portion is fixedly connected with a frame body.

[0011] The inner side edge of the metal leading edge is fixedly connected with the frame body, and the bottom end of the metal leading edge is fixedly connected with the connecting portion.

[0012] The frame body is provided with a plurality of through holes, and the through holes are uniformly distributed on the frame body.

[0013] The frame body is provided with a plurality of attachment grooves on the front surface and the back surface, and the attachment grooves are located between adjacent two through holes.

[0014] The top end of the frame body is provided with a plurality of uniformly distributed openings.

[0015] Compared with the prior art, the utility model has the advantages of:

[0016] In the scheme of the utility model,

[0017] 1. By setting up the metal layer, the first carbon fiber composite material layer and the second carbon fiber composite material layer, the overall structural stability and impact resistance of the blade body can be ensured in actual use process, the overall weight of the blade body is reduced, the overall light weight of the blade is ensured, and the overall weight of the engine is further reduced.

[0018] 2. By setting up the metal layer and the metal leading edge, the metal layer and the metal leading edge can be integrally formed in the blade processing process, without the need for secondary bonding processing, the overall processing cost can be effectively reduced, the metal layer and the metal leading edge are made of the same metal material, the combination of the two is more stable and reliable, the embedding groove is set up, the connection of the first carbon fiber composite material layer and the second carbon fiber composite material layer with the metal layer is facilitated, and the surfaces of the first carbon fiber composite material layer and the second carbon fiber composite material layer are flush with the surface of the metal leading edge. Attached Figure Description

[0019] Figure 1 A schematic diagram of the overall structure of the lightweight composite blade for aero-engines provided by this utility model;

[0020] Figure 2 A schematic diagram of the metal layer structure of a lightweight composite blade for an aero-engine provided by this utility model;

[0021] Figure 3 A schematic diagram of the metal layer structure of a lightweight composite blade for an aero-engine provided by this utility model;

[0022] Figure 4 A schematic diagram of the frame structure for a lightweight composite blade for an aero-engine provided by this utility model;

[0023] Figure 5 The present invention provides a lightweight composite material blade for aero-engines. Figure 4 Enlarged view of structure A.

[0024] The image shows:

[0025] 1. Blade body; 2. Tenon; 3. Metal layer; 4. Fitting groove; 5. First carbon fiber composite material layer; 6. Second carbon fiber composite material layer; 7. Metal leading edge; 301. Connecting part; 302. Opening; 303. Frame; 304. Through hole; 305. Attachment groove. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model.

[0027] like Figures 1-3As shown, the embodiment proposes a lightweight composite blade for an aero-engine, comprising a blade body 1 and a tenon 2, the blade body 1 comprises a metal layer 3, a first carbon fiber composite material layer 5 and a second carbon fiber composite material layer 6, the front and back surfaces of the metal layer 3 are provided with fitting grooves 4, which are used for the installation of the first carbon fiber composite material layer 5 and the second carbon fiber composite material layer 6. By setting the metal layer 3, the first carbon fiber composite material layer 5 and the second carbon fiber composite material layer 6, the overall structural stability and impact resistance of the blade body 1 can be ensured during actual use, the overall weight of the blade body 1 can be reduced, the overall lightweight of the blade is ensured, and the overall weight of the engine is further reduced; a metal leading edge 7, the metal leading edge 7 cooperates with the metal leading edge 7 of the blade body 1, and the metal leading edge 7 is fixedly connected with the metal layer 3. By setting the metal layer 3 and the metal leading edge 7, the metal layer 3 and the metal leading edge 7 can be integrally formed during blade processing, without the need for secondary bonding processing, which can effectively reduce the overall processing cost. At the same time, the metal layer 3 and the metal leading edge 7 are made of the same metal material, and the combination of the two is more stable and reliable. By setting the fitting groove 4, the connection of the first carbon fiber composite material layer 5 and the second carbon fiber composite material layer 6 with the metal layer 3 is facilitated, and the surfaces of the first carbon fiber composite material layer 5 and the second carbon fiber composite material layer 6 are flush with the surface of the metal leading edge 7.

[0028] As Figure 4 shown, as a preferred embodiment, on the basis of the above-mentioned mode, further, the metal layer 3 comprises a connecting part 301, the bottom end of the connecting part 301 is fixedly connected with the tenon 2, and the top end of the connecting part 301 is fixedly connected with a frame 303, the frame 303 is used for connecting the first carbon fiber composite material layer 5 and the second carbon fiber composite material layer 6. It should be noted that the connecting part 301 can connect the tenon 2 and the frame 303, and the connecting part 301 can also enhance the strength of the blade root.

[0029] As Figures 2-4 shown, as a preferred embodiment, on the basis of the above-mentioned mode, further, the inner side edge of the metal leading edge 7 is fixedly connected with the frame 303, and the bottom end of the metal leading edge 7 is fixedly connected with the connecting part 301. It should be noted that the two connection positions can effectively ensure the connection strength between the metal leading edge 7 and the metal layer 3.

[0030] As Figure 2 and Figure 4As shown, as a preferred embodiment, on the basis of the above-mentioned mode, further, the frame body 303 is provided with a plurality of through holes 304, and the plurality of through holes 304 are uniformly distributed on the frame body 303. It should be noted that, through the arrangement of the through hole 304, the overall weight of the frame body 303 can be effectively reduced.

[0031] As shown in the drawings, Figure 4 As shown, as a preferred embodiment, on the basis of the above-mentioned mode, further, the frame body 303 is provided with a plurality of through holes 304, and the plurality of through holes 304 are uniformly distributed on the frame body 303. It should be noted that, through the arrangement of the through hole 304, the overall weight of the frame body 303 can be effectively reduced.

[0032] As shown in the drawings, Figure 4 As shown in the drawings, Figure 5 As shown, as a preferred embodiment, on the basis of the above-mentioned mode, further, the frame body 303 is provided with a plurality of through holes 304, and the plurality of through holes 304 are uniformly distributed on the frame body 303. It should be noted that, through the arrangement of the through hole 304, the overall weight of the frame body 303 can be effectively reduced.

[0033] The above examples are only used to illustrate the technical solutions described in the present application and are not limited to the technical solutions described in the present application. Although the present application has been described in detail with reference to the above-mentioned embodiments, the present application is not limited to the above-mentioned specific embodiments, and any modification or equivalent replacement of the present application; all technical solutions and improvements within the spirit and scope of the application are covered by the scope of the claims of the present application.

Claims

1. A lightweight composite blade for an aeroengine comprising a blade body (1) and a tenon (2), characterized in that, The blade body (1) comprises a metal layer (3), a first carbon fiber composite material layer (5) and a second carbon fiber composite material layer (6), the front and back surfaces of the metal layer (3) are provided with fitting grooves (4), and the fitting grooves (4) are used for mounting the first carbon fiber composite material layer (5) and the second carbon fiber composite material layer (6); Further comprising a metal leading edge (7) matched with the blade body (1), and the metal leading edge (7) is fixedly connected with the metal layer (3).

2. A lightweight composite blade for an aero-engine as claimed in claim 1, wherein, The metal layer (3) comprises a connecting part (301), the bottom end of the connecting part (301) is fixedly connected with the tenon (2), and the top end of the connecting part (301) is fixedly connected with a frame body (303), and the frame body (303) is used for connecting the first carbon fiber composite material layer (5) and the second carbon fiber composite material layer (6).

3. A lightweight composite blade for an aero-engine as claimed in claim 2, wherein, The inner side edge of the metal leading edge (7) is fixedly connected with the frame body (303), and the bottom end of the metal leading edge (7) is fixedly connected with the connecting part (301).

4. A lightweight composite blade for an aero-engine according to claim 3, wherein, A plurality of through holes (304) are through-opened on the frame body (303), and the plurality of through holes (304) are uniformly distributed on the frame body (303).

5. A lightweight composite blade for an aero-engine as claimed in claim 4, wherein, The front and back surfaces of the frame body (303) are provided with a plurality of attachment grooves (305), and the attachment grooves (305) are located between adjacent two rows of through holes (304).

6. A lightweight composite blade for an aeroengine according to claim 5, wherein, A plurality of uniformly distributed openings (302) are through-opened on the top end of the frame body (303).

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