Testing tool for aircraft generator rotor

Abstract

The utility model relates to the technical field of aero-engine testing devices, and particularly discloses a testing tool for an aircraft generator rotor, which comprises a tool main body arranged on a vibration testing platform; the object placing part is arranged on the tool main body and is used for placing the main rotor; the clamping component is detachably arranged on the storage component and can press and contact the main rotor along the radial direction of the main rotor; the V-shaped groove is formed in the object placing part and / or the clamping part, and the main rotor penetrates through the V-shaped groove to position the main rotor; the pressing contact assembly is arranged on the tool main body, is clamped with the main rotor and can press and contact the main rotor in the axial direction of the main rotor; according to the utility model, the main rotors with different diameters can be effectively fixed, sufficient pressing force is ensured, the main rotors are prevented from moving in the vibration test operation, and the accuracy of the vibration test result is improved.

Description

Technical Field

[0001] This utility model relates to the technical field of testing devices for aero engines, and more particularly to a testing fixture for an aircraft generator rotor. Background Technology

[0002] The integrated drive generator (IDG) is an important component of an aircraft engine, providing power to the aircraft. Inevitably, after long-term use, the main rotor inside the integrated drive generator will be damaged and needs to be repaired.

[0003] During the repair of the main rotor, a vibration test is required to verify the reliability of the repaired main rotor.

[0004] In existing testing operations, in order to fix the main rotor to the vibration test platform, Ω-shaped clamps are usually used to directly lock the main rotor. However, some main rotors are equipped with carbon fiber sleeves. Although carbon fiber has extremely high tensile strength, it is not impact-resistant and is easily damaged by bumps and knocks.

[0005] On the one hand, using an Ω-shaped clamp to directly lock the main rotor can easily damage the sleeve; on the other hand, if there is a slight deviation between the inner diameter of the Ω-shaped clamp and the outer diameter of the sleeve, the clamping force will be insufficient, the main rotor will not be effectively fixed, which will affect the reliability of the vibration test results and may even lead to incorrect experimental results. Utility Model Content

[0006] In view of the above problems, this utility model provides a test fixture for aircraft generator rotors, the purpose of which is to improve the applicability of the fixture and protect the carbon fiber sleeve.

[0007] To achieve the above-mentioned objectives, the technical solution adopted by this utility model is as follows:

[0008] A test fixture for an aircraft generator rotor is provided, comprising: a fixture body disposed on a vibration test platform; a placement component disposed on the fixture body for placing the main rotor; a clamping component detachably disposed on the placement component and capable of pressing against the main rotor in the radial direction; a V-groove formed on the placement component and / or the clamping component for the main rotor to pass through and position the main rotor; and a pressing assembly disposed on the fixture body and engaging with the main rotor, capable of pressing against the main rotor in the axial direction.

[0009] Furthermore, the test fixture also includes: a number of first threaded holes, which are formed on the fixture body along the axial direction of the main rotor; and a number of first screws, which can lock the placement component into the first threaded holes.

[0010] Furthermore, at least two first screws are provided on a storage component.

[0011] Furthermore, the pressure contact assembly includes: a snap-fit ​​component for snapping the main rotor; a mounting base disposed on the tooling body; and a force-applying rod, one end of which is rotatably connected to the snap-fit ​​component, and the other end of which extends a fixed length through the mounting base, wherein the force-applying rod and the mounting base are installed by a threaded connection.

[0012] Furthermore, the test fixture also includes two limit nuts located on both sides of the mounting base, and both limit nuts are threadedly connected to the force-applying rod.

[0013] Furthermore, the test fixture also includes: a mounting shaft, mounted on the snap-fit ​​component; a thrust block, mounted on one end of the force-applying rod; and a thrust bearing, wherein the tight ring of the thrust bearing and the mounting shaft are installed by an interference fit, and the loose ring of the thrust bearing is used for the thrust block to abut against.

[0014] The beneficial effects of this utility model are as follows: In this utility model, a storage component is provided to avoid contact between the storage component and the sleeve, thereby preventing the carbon fiber sleeve from being damaged and protecting the sleeve.

[0015] It is also equipped with a V-groove to position the main rotor, which can meet the positioning requirements of main rotors of different diameters; it is also equipped with a clamping component that can press against the main rotor in the radial direction to complete the radial positioning operation of the main rotor.

[0016] It is also equipped with a pressure contact assembly, which can prevent the main rotor from rotating by engaging with the main rotor and complete the circumferential positioning operation of the main rotor; the pressure contact assembly can also press against the main rotor in the axial direction to complete the axial positioning operation of the main rotor. Attached Figure Description

[0017] Figure 1 This is an exploded view of the overall structure of the test fixture provided in the embodiments of this application.

[0018] Figure 2 This is a side view of the test fixture holding the main rotor, provided in an embodiment of this application.

[0019] The components include: 1. Tooling body; 11. First threaded hole; 12. First screw; 2. Storage component; 3. Clamping component; 4. V-groove; 5. Pressing assembly; 51. Snap-fit ​​component; 52. Mounting base; 53. Force rod; 54. Limit nut; 55. Mounting shaft; 56. Thrust block; 57. Thrust bearing; 7. Main rotor; 71. Sleeve. Detailed Implementation

[0020] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.

[0021] Reference Figure 1 and Figure 2 As shown in the figure, this application discloses a test fixture for an aircraft generator rotor, comprising: a fixture body 1, disposed on a vibration test platform; a placement component 2, disposed on the fixture body 1 for placing a main rotor 7; a clamping component 3, detachably disposed on the placement component 2, capable of pressing against the main rotor 7 in the radial direction; a V-groove 4, formed on the placement component 2 and / or the clamping component 3, for the main rotor 7 to pass through, thereby positioning the main rotor 7; and a pressing component 5, disposed on the fixture body 1, engaging with the main rotor 7, capable of pressing against the main rotor 7 in the axial direction.

[0022] In this utility model, a storage component 2 is provided. Of course, the storage component 2 should be placed on the tooling body 1 to avoid contact between the storage component 2 and the sleeve 71, so as to prevent the carbon fiber sleeve 71 from being damaged and to protect the sleeve 71.

[0023] In this utility model, a V-groove 4 is also provided, which is used to position the main rotor 7, and can meet the positioning requirements of main rotors 7 with different diameters; and the inner wall surface of the V-groove 4 and the outer wall surface of the main rotor 7 are in line-to-line contact, which can reduce the contact area between the two; a clamping component 3 is also provided, which can press the main rotor 7 in the radial direction to complete the positioning operation of the main rotor 7 in the radial direction.

[0024] In this utility model, a pressure contact assembly 5 is also provided. By engaging the pressure contact assembly 5 with the main rotor 7, the rotation of the main rotor 7 can be prevented, and the positioning operation of the main rotor 7 in the circumferential direction can be completed. The pressure contact assembly 5 can also press the main rotor 7 in the axial direction to complete the positioning operation of the main rotor 7 in the axial direction.

[0025] By using this invention, main rotors 7 of different diameters can be effectively fixed, ensuring sufficient clamping force, preventing the main rotors 7 from moving during vibration testing, and improving the accuracy of vibration test results.

[0026] It is known that, according to design requirements, vibration testing of the main rotor 7 is conducted using an aero-engine rotor system vibration simulation test bench. This is a well-known technique to those skilled in the art, and will not be elaborated upon here.

[0027] In some embodiments, a V-groove 4 is formed on the placement component 2, the main rotor 7 is placed in the V-groove 4, and then the clamping component 3 presses and clamps the main rotor 7 in the V-groove 4.

[0028] In some embodiments, the V-groove 4 is formed on the clamping member 3, the main rotor 7 is placed on the placement member 2, and then the clamping member 3 clamps the main rotor 7 in the V-groove 4.

[0029] In some embodiments, V-shaped grooves 4 are symmetrically formed on the placement component 2 and the clamping component 3, and the main rotor 7 is clamped by the symmetrically arranged V-shaped grooves 4, which can improve the stability of clamping the main rotor 7.

[0030] Specifically, the test fixture also includes: several first threaded holes 11, which are opened on the fixture body 1 along the axial direction of the main rotor 7; several first screws 12, which can lock the placement component 2 into the first threaded holes 11; in actual use, the placement component 2 is provided with a through hole for the first screws 12 to pass through, and the first screws 12 and the first threaded holes 11 are threadedly connected. By turning the first screws 12, the placement component 2 can be pressed onto the mounting body through the nut of the first screws 12.

[0031] It is worth mentioning that the clamping component 3 can also be locked to the placement component 2 with screws, and the tooling body 1 can also be locked to the vibration test platform with screws.

[0032] In this utility model, a plurality of first threaded holes 11 are formed on the tooling body 1 along the axial direction of the main rotor 7; the placement component 2 can be flexibly disassembled and assembled on the tooling body 1, can provide clearance for the sleeve 71, and can also meet the clamping requirements of main rotors 7 of different lengths.

[0033] Specifically, at least two first screws 12 are provided on a storage component 2.

[0034] In this utility model, the pressure contact assembly 5 includes: a snap-fit ​​component 51 for snapping the main rotor 7; a mounting base 52 disposed on the tooling body 1; and a force-applying rod 53, one end of which is rotatably connected to the snap-fit ​​component 51, and the other end extends through the mounting base 52 for a fixed length, and the force-applying rod 53 and the mounting base 52 are installed by threaded connection.

[0035] In practical use, by turning the force-applying rod 53, the operator can move the force-applying rod 53 to bring the locking component 51 closer to the main rotor 7 in the axial direction, which can apply a certain pressure to the main rotor 7 in the axial direction until the locking component 51 is pressed tightly onto the main rotor 7. This not only restricts the movement of the main rotor 7 in the axial direction and completes the axial positioning of the main rotor 7, but also restricts the rotation of the main rotor 7 in the circumferential direction and completes the circumferential positioning of the main rotor 7.

[0036] It is worth mentioning that the mounting bracket 52 component can also be locked to the mounting body with screws.

[0037] It is worth mentioning that the snap-fit ​​component 51 can snap into the process notch at the end of the main rotor 7, or it can be a keyway / radial through hole.

[0038] In this embodiment, the test fixture also includes two limiting nuts 54 located on both sides of the mounting base 52, and both limiting nuts 54 are threadedly connected to the force-applying rod 53. After the force-applying rod 53 is turned to the required stroke, the force-applying rod 53 is kept stationary, and then the limiting nuts 54 are turned to bring the two limiting nuts 54 closer to the mounting base 52 until the two limiting nuts 54 respectively abut against both sides of the mounting base 52, thereby limiting the force-applying rod 53.

[0039] Specifically, the test fixture also includes: a mounting shaft 55, which is mounted on the snap-fit ​​component 51; a thrust block 56, which is mounted on one end of the force-applying rod 53; and a thrust bearing 57, wherein the tight ring of the thrust bearing 57 and the mounting shaft 55 are installed by an interference fit, and the loose ring of the thrust bearing 57 is used for the thrust block 56 to abut against.

[0040] In this embodiment, the locking component 51 and the thrust block 56 are rotatably connected by a thrust bearing 57. During the rotation of the thrust rod, the locking component 51 can remain stationary relative to the thrust rod, thus preventing excessive friction between the force rod 53 and the locking component 51 from causing the main rotor 7 to rotate.

[0041] Those skilled in the art will understand that although preferred embodiments of the present invention have been described, those skilled in the art, once they learn the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of the present invention. Clearly, those skilled in the art can make various alterations and modifications to the present invention without departing from its spirit and scope. Thus, if these modifications and modifications of the present invention fall within the scope of the machine equivalents of the claims of the present invention, the present invention also intends to include these modifications and modifications.

Claims

1. A testing fixture for an aircraft generator rotor, characterized in that, include: The main body of the tooling (1) is set on the vibration test platform; The storage component (2) is set on the tooling body (1) for the main rotor (7) to be placed; The clamping component (3) is detachably mounted on the storage component (2) and can press against the main rotor (7) in the radial direction of the main rotor (7); V-grooves (4) are formed on the storage component (2) and / or the clamping component (3) for the main rotor (7) to pass through and to position the main rotor (7); The pressure contact assembly (5) is mounted on the tooling body (1) and snaps into the main rotor (7), and can press against the main rotor (7) along the axial direction of the main rotor (7).

2. The testing fixture for the aircraft generator rotor according to claim 1, characterized in that, Also includes: Several first threaded holes (11) are opened on the tooling body (1) along the axial direction of the main rotor (7); Several first screws (12) are used to lock the storage component (2) into the first threaded hole (11).

3. The testing fixture for the aircraft generator rotor according to claim 2, characterized in that, At least two first screws (12) are provided on a storage component (2).

4. The testing fixture for the aircraft generator rotor according to claim 1, characterized in that, The pressure contact assembly (5) includes: A snap-fit ​​component (51) is used to snap-fit ​​the main rotor (7); Mounting base (52) is provided on tooling body (1); The force-applying rod (53) has one end rotatably connected to the snap-fit ​​component (51), and the other end extends through the mounting base (52) to a fixed length. The force-applying rod (53) and the mounting base (52) are installed by threaded connection.

5. The test fixture for the aircraft generator rotor according to claim 4, characterized in that, It also includes two limit nuts (54) located on both sides of the mounting base (52), and both limit nuts (54) are installed on the force-applying rod (53) by threaded connection.

6. The test fixture for the aircraft generator rotor according to claim 1, characterized in that, Also includes: The mounting shaft (55) is mounted on the snap-fit ​​component (51); A thrust block (56) is located at one end of the force-applying rod (53); The thrust bearing (57) is installed with the tight ring of the thrust bearing (57) and the mounting shaft (55) by an interference fit, and the loose ring of the thrust bearing (57) is abutted by the thrust block (56).

Images