A composite material rotor blade blisk structure and method of manufacture

Abstract

The application relates to a composite rotor blade integral blade disc structure and a manufacturing method, which comprises a wheel disc, a blade body and a frame body, the blade body is connected with the wheel disc through the frame body, the frame body comprises a side rib and a bottom rib, the bottom of the side rib is connected with one end of the bottom rib, one side of the side rib and the bottom rib is provided with a V-shaped groove for accommodating and connecting the edge of the blade body, the edge of the blade body is embedded in the V-shaped groove and connected with the frame body through an adhesive, and the bottom rib is connected with the wheel disc. Through the lightweight blade body design and the connection of the blade body and the wheel disc through the frame body, the blade body and the frame body are bonded, the structure of the frame body is designed for improving the bonding force, then the frame body is connected with the wheel disc, the needs of structural strength are met, the mass of the blade body is reduced, and the other side of the side rib has a certain wall thickness, so that the performance requirement of resisting external impact can be met.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine, in particular to a composite rotor blade blisk structure and manufacturing method. BACKGROUND

[0002] The traditional fan / compressor blisk must be made of metal material, and in the production process, the blade and the disc are manufactured respectively, and then the two structures are connected into one whole by welding process. In recent years, the blisk can also be obtained by using forging and mechanical processing.

[0003] However, the traditional fan / compressor blisk has the following three deficiencies: first, the fan / compressor blade must be made of metal material, and the overall structure has no spare parts, so it is difficult to further reduce the weight; second, since the disc must be made of metal material, if the fan / compressor blade is made of composite material, there is no welding process that can reliably connect the two together, and if the bonding method is used, since the bonding can only be done at the blade root, the current bonding performance between metal and non-metal cannot meet the load requirements of the connection interface under the centrifugal load when the fan blade rotates at high speed, thereby limiting the further weight reduction of the fan / compressor blisk; third, the traditional fan / compressor blisk structure has poor damping characteristics, and it is difficult to improve the structural damping by adding other structures, so the blade is easy to vibrate when subjected to external excitation, and high-cycle fatigue failure is easy to occur, which affects the structural life and the reliability of the whole machine. SUMMARY

[0004] (1) Technical problem to be solved

[0005] The embodiment of the present application provides a composite rotor blade blisk structure and manufacturing method, which solves the technical problem of further reducing the weight of the blisk.

[0006] (2) Technical scheme

[0007] In a first aspect, the embodiment of the present application provides a composite rotor blade blisk structure, which comprises a disc and a blade, the blade is composed of a composite material blade body and a metal frame, the frame comprises a side rib and a bottom rib, the blade body is connected with the disc through the bottom rib of the frame, the bottom of the side rib is connected with one end or both ends of the bottom rib, the side rib and the bottom rib are provided with V-shaped grooves for accommodating and connecting the edges of the blade body, the edges of the blade body are embedded in the V-shaped grooves, and the blade body and the frame are connected into a whole by bonding, then the bottom rib is connected with the disc to form a whole structure, finally, the excess material is removed by mechanical processing to process the blade body and the inlet and outlet edges that meet the aerodynamic performance requirements.

[0008] Further, the blade body is made of composite material.

[0009] Further, the blade body is a hollow structure, or a solid structure.

[0010] Further, a damping structure can be arranged in the hollow area of the blade body.

[0011] Further, a connecting block can be further embedded at the bottom of the blade body, and the connecting block is connected with the frame body by one of riveting, pinning and tenoning, so that the connecting strength of the blade body and the frame body is further improved.

[0012] Further, the bottom rib and the side rib have a V-shaped groove, the internal shape of the V-shaped groove is in contact with the blade body, the geometric characteristics of the two are matched and processed to meet the assembly requirements, and an adhesive is arranged on the inner surface of the V-shaped groove and the contact surface of the blade body.

[0013] Further, the height of the bottom rib is less than 40 mm, and the wall thickness of the V-shaped groove is less than 3 mm.

[0014] Further, the minimum contact area of the frame body and the blade body is A c , and the calculation formula is:

[0015]

[0016] Wherein, A c is a critical area, m is the mass of the blade body, r is the radius of gyration of the mass center of the blade body, ω is the maximum design speed of the blade body, k is a safety factor, which is greater than 1.1, and n is the adhesive force of the adhesive.

[0017] Further, the frame body is connected with the disc by welding.

[0018] In the second aspect, a manufacturing method of a composite rotor blade integral blade disc structure is provided, which comprises the following steps: manufacturing a disc, a blade body and a frame body; coating glue on the connection between the blade body and the frame body, and performing adhesion; reinforcing the blade body and the frame body by any one of riveting, pinning and tenoning; connecting the frame body and the disc by welding; and removing excess material and strengthening the surface.

[0019] (3) Beneficial effects

[0020] In summary, the blade body is designed to be lightweight, and the frame body is used to connect the non-metal blade body and the metal disc, that is, the non-metal blade body is first adhesively connected with the frame body, the structure of the frame body is designed to improve the adhesive force, then the frame body is connected with the disc, the structural strength is met, the mass of the blade body is reduced, and the other side of the side rib has a certain wall thickness, so that the performance requirement of resisting external impact is met. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments of the present application will be briefly introduced as follows. Obviously, the drawings described below only constitute some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without any creative effort on the basis of these drawings.

[0022] Figure 1 is a general structure diagram of a composite material rotor blade blisk structure;

[0023] Figure 2 is Figure 1 is a structure diagram of a blade body and a frame body;

[0024] Figure 3 is Figure 2 is an A-A cross-sectional diagram of

[0025] Figure 4 is Figure 2 is a B-B cross-sectional diagram of

[0026] In the drawings: 1, disc; 2, blade body; 3, frame body; 30, side rib; 31, bottom rib; 32, V-shaped groove; 20, connecting block; 33, side plate. DETAILED DESCRIPTION

[0027] The embodiments of the present application will be further described in detail below with reference to the drawings and embodiments. The detailed description of the following embodiments and the drawings are used to exemplarily illustrate the principles of the present application, but cannot be used to limit the scope of the present application, that is, the present application is not limited to the described embodiments, and covers any modification, replacement and improvement of parts, components and connection modes without departing from the spirit of the present application.

[0028] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and embodiments.

[0029] Please refer to Figures 1-4 It is shown that in the first aspect, the embodiments of the present application propose a composite material rotor blade blisk structure, which comprises a disc 1, a blade body 2 and a frame body 3, the blade body 2 is connected with the disc 1 through the frame body 3, the frame body 3 comprises a side rib 30 and a bottom rib 31, the bottom of the side rib 30 is connected with one end of the bottom rib 31, the side rib 30 and the bottom rib 31 are provided with a V-shaped groove 32 accommodating and connecting the edge of the blade body 2 on one side, the edge of the blade body 2 is embedded in the V-shaped groove 32 and connected with the frame body 3 through an adhesive, and the bottom rib 31 is connected with the disc 1.

[0030] The blade body 2 can reduce weight by using non-metallic material with high structural strength, but since the non-metallic material cannot be directly connected with the wheel disc 1 made of metal material, the blade body 2 needs to be connected with the wheel disc 1 through the frame body 3, that is, the frame body 3 is made of metal material. In the connection mode of the blade body 2 and the frame body 3, adhesion is used. Since the maximum load borne by the adhesion connection mode is limited, the frame body 3 is divided into a side rib 30 and a bottom rib 31, and a V-shaped groove 32 structure is arranged to expand the contact surface with the blade body 2, thereby improving the connection strength of the adhesion mode, meeting the need of structural strength, and reducing the weight of the blade body 2. Compared with the traditional metal blade body 2, the weight of a single blade body 2 can be reduced by 30%-50%, and the other side of the side rib 30 has a certain wall thickness, which can meet the performance requirement of resisting external impact.

[0031] In some embodiments, the material density of the blade body 2 should be less than 3×10 3 kg / m 3 , to meet the lightweight design. Carbon fiber composite material can be used, which has high structural strength and light weight. The blade body 2 can use solid or hollow structure. The hollow area can be provided with damping material to reduce the amplitude of the blade body 2 under alternating external load and improve the fatigue resistance of the structure.

[0032] In some embodiments, a connecting block 20 is embedded at the bottom of the blade body 2. The connecting block 20 is connected with the frame body 3 through one of riveting, pinning and mortising, which can further improve the connection strength of the blade body 2 and the frame body 3.

[0033] In some embodiments, the bottom rib 31 is connected with a side plate 33 at the other end. The side plate 33 is provided with an adhesive on the contact surface with the blade body 2. By increasing the side plate 33, the adhesion area of the frame body 3 and the blade body 2 can be further increased, and the stability of the connection can be improved. The side plate 33 can include two groups, which are respectively in contact with the upper surface and the lower surface of the blade body 2. It should be noted that the side plate 33 can also include a top plate connected with the side plate 33 and the side rib 30, which has the same function and principle as the side plate 33. Similar structures are not listed one by one here, and should be regarded as the protection scope of the present application.

[0034] In some embodiments, the height of the bottom rib 31 is less than 40 mm, so as to avoid occupying more blade body 2 span length in the overall fan / compressor disc structure and reduce weight. The wall thickness of the V-shaped groove 32 is less than 3 mm, which can ensure the structural strength while reducing the structural weight.

[0035] In some embodiments, the minimum contact area of the frame body 3 and the blade body 2 is A c , and the calculation formula is as follows:

[0036]

[0037] wherein A c is the minimum contact area, m is the mass of the blade 2, r is the radius of gyration of the mass center of the blade 2, ω is the maximum design rotational speed of the blade 2, k is a safety factor, which is greater than 1.1, and n is the adhesive force of the adhesive;

[0038] The adhesive force n of a general adhesive is 20, and the critical area A c The critical area A can provide data basis for determining the structure of the contact part of the frame 3 and the blade 2.

[0039] In some embodiments, the frame 3 and the wheel disc 1 are connected by welding, which is firm and stable in structure. The welding method includes but is not limited to linear friction welding.

[0040] In a second aspect, a manufacturing method of a composite rotor blade integral bladed disc structure is provided, which includes the following steps:

[0041] Manufacturing the wheel disc 1, the blade 2 and the frame 3;

[0042] Gluing and bonding the connection part of the blade 2 and the frame 3;

[0043] Reinforcing the blade 2 and the frame 3 by one of riveting, pinning and mortising;

[0044] Connecting the frame 3 and the wheel disc 1 by welding;

[0045] Removing excess material and strengthening the surface.

[0046] It should be noted that each of the embodiments in the specification is described in a progressive manner, and the same or similar parts of each of the embodiments can be mutually referred to. Each embodiment focuses on the difference from other embodiments. The present application is not limited to the specific steps and structures described above and shown in the drawings. Moreover, for the sake of brevity, detailed descriptions of known methods and techniques are omitted.

[0047] The above only describes the embodiments of the present application and does not limit the present application. The present application can have various modifications and changes for those skilled in the art without departing from the scope of the present application. Any modification, equivalent replacement, improvement, etc. within the spirit and principles of the present application shall be included in the scope of the claims of the present application.

Claims

1. A composite material rotor blade blisk structure, characterized by: The blade, the frame and the disc are connected by the frame, the frame includes side ribs and a bottom rib, the bottom of the side rib is connected with one end of the bottom rib, the side rib and the bottom rib are provided with V-shaped grooves on one side for accommodating and connecting the edges of the blade, the edges of the blade are embedded in the V-shaped grooves and connected with the frame by an adhesive, and the bottom rib is connected with the disc. The minimum contact area between the frame and the blade body is A c k is a safety factor greater than 1.1, and the calculation formula is: ； where A c is the critical area, m is the mass of the blade, r is the radius of gyration of the mass center of the blade, ω is the maximum design rotational speed of the blade, k is a safety factor, and n is the adhesive strength of the adhesive.

2. A composite material rotor blade blisk structure according to claim 1, characterised in that: The blade region of the blade is a composite material.

3. A composite material rotor blade blisk structure according to claim 1, characterized in that: The blade is a hollow structure or a solid structure.

4. A composite material rotor blade blisk structure according to claim 3, characterised in that: A damping structure is arranged in the hollow region of the blade.

5. A composite material rotor blade blisk structure as defined in claim 1, wherein: A connecting block is embedded in the bottom of the blade, the connecting block is connected with the frame by one of riveting, pinning, mortising and bonding, and the connecting block can also be connected in a combined manner.

6. A composite material rotor blade blisk structure as defined in claim 1, wherein: The other end of the bottom rib is connected with a side plate, and the contact surface of the side plate and the blade is provided with an adhesive.

7. A composite material rotor blade blisk structure as defined in claim 1, wherein: The height of the bottom rib is less than 40 mm, and the thickness of the groove wall of the V-shaped groove is less than 3 mm.

8. A composite material rotor blade blisk structure as defined in claim 1, wherein: The frame is connected with the disc by welding.

9. A method of manufacturing a composite rotor blade blisk structure according to any one of claims 1-8, characterized in that, The steps include: manufacturing the disc, the blade and the frame; applying glue to the connection between the blade and the frame and connecting them by bonding; reinforcing the blade and the frame by one of riveting, pinning and mortising; connecting the frame and the disc by welding; removing excess material and strengthening the surface.

Images