Aero-engine blade assembly clamp

Abstract

The utility model provides an aero-engine blade assembly clamp, which is suitable for the technical field of aero-engines, and adopts the scheme that the aero-engine blade assembly clamp comprises a mounting shell, a blade assembly, a moving block and a semi-cylinder, the blade assembly is arranged above the mounting shell, and the moving block is arranged above the mounting shell. Moving blocks are symmetrically installed in the two rectangular grooves of the installation shell in a sliding mode, the upper surfaces of the two moving blocks are fixedly connected with semi-cylinders, and the semi-cylinders are connected with the circular holes of the blade assemblies in a penetrating mode. According to the fixture for the aero-engine blade assembly, the mounting shell, the blade assembly, the moving block, the semi-cylinder, the linkage groove and the two-way lead screw are used, clamping can be conducted from the inner wall of a circular hole of the blade assembly, the blade assembly is prevented from being suspended in the clamping process, and the practicability of the fixture for the aero-engine blade assembly is improved; the utility model is also applicable to the field of aero-engines.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engines, in particular to an aviation engine blade component clamp. Background Art

[0002] The aircraft engine is undoubtedly the heart of the aircraft, a thermal machine that combines high complexity and precision. It is not only the power source that allows the aircraft to soar into the sky, but also the core force that drives the aviation industry forward. In the long history of human aviation, every leap and change is deeply imprinted with the footprints of aircraft engine technology progress. It can be said that it is the continuous innovation and development of aircraft engines that has given wings to mankind's aviation dream, allowing us to explore a wider world.

[0003] After a period of use, the aircraft engine blade assembly must be carefully inspected and maintained to ensure its normal operation and extend its service life. However, in this process, how to firmly clamp the aircraft engine blade assembly has become a key issue. The existing fixture design often adopts a side clamping method. Although it can fix the blade assembly to a certain extent, this method has many disadvantages. First, the side clamping method can easily cause damage to the flanks of the aircraft engine blade assembly, which not only affects the performance of the blade assembly, but also may bring safety hazards. Secondly, due to the limited clamping area, this clamping method is often not strong enough and is prone to loosening during the inspection and maintenance process, thereby affecting the smooth progress of the inspection and maintenance work. Therefore, this side clamping fixture design reduces its practicality to a certain extent and is difficult to meet the needs of aircraft engine blade assembly inspection and maintenance. In order to solve this problem, we need to find a more reasonable and effective clamping method to ensure that the blade assembly can be firmly clamped and not damaged during the inspection and maintenance process.

[0004] Therefore, it is necessary to provide a new aerospace engine blade assembly fixture to solve the above-mentioned technical problems. Utility Model Content

[0005] In order to solve the above technical problems, the utility model provides an aero-engine blade assembly fixture.

[0006] The aircraft engine blade assembly fixture provided by the utility model comprises: a mounting shell, a blade assembly, a moving block and a semi-cylinder, wherein the blade assembly is arranged above the mounting shell, and the moving blocks are symmetrically and slidably mounted inside two rectangular grooves of the mounting shell, and the upper surfaces of the two moving blocks are fixedly connected with semi-cylinders, and the semi-cylinders are connected with the circular holes of the blade assembly; a linkage groove and a bidirectional screw rod, wherein the two moving blocks are provided with a linkage groove, and the inner walls of the two rectangular grooves of the mounting shell are rotatably connected with the bidirectional screw rod, and the threaded surface of the bidirectional screw rod is meshed with the inner wall of the linkage groove, and the bidirectional screw rod is rotated, and the threaded surface of the bidirectional screw rod contacts the inner wall of the linkage groove, driving the moving blocks to move away from each other, and the moving blocks drive the semi-cylinders to squeeze the inner wall of the circular hole of the blade assembly, and the blade assembly is firmly clamped, so that the inspection and maintenance of the blade assembly is convenient.

[0007] Preferably, the two sides of the bidirectional screw rod are symmetrically fixed with a driving disk, and the driving disk is rotated to drive the bidirectional screw rod to rotate on the inner walls of the two rectangular grooves of the mounting shell, providing drive for the rotation of the bidirectional screw rod. The driving disk can be rotated manually without the assistance of tools.

[0008] Preferably, guide grooves are symmetrically provided on both sides of the two moving blocks, and the guide grooves are located on both sides of the linkage groove. The inner walls of the two rectangular grooves of the mounting shell are symmetrically fixedly connected with guide rods, and the guide rods are slidably connected with the guide grooves. When the moving blocks move away from each other, the guide rods slide on the inner walls of the guide grooves to ensure that the moving blocks move stably and horizontally, and no shaking occurs during the movement of the moving blocks.

[0009] Preferably, a support plate is arranged above the two moving blocks, and a one-way screw is fixedly connected to the upper surfaces of the two moving blocks. Lifting seats are symmetrically arranged on both sides of the two one-way screws, and the bottom of the lifting seat is fixedly connected to the upper surface of the moving block. A limiting block is fixedly connected to the lower surface of the two support plates, and a rotating block is rotatably connected to the inner wall of the circular hole of the limiting block. The rotating block on the inner wall of the circular hole of the rotating block contacts the threaded surface of the one-way screw to drive the support plate to move upward, and the upper surface of the support plate contacts the lower surface of the blade assembly to prevent the blade assembly from being suspended during the clamping process.

[0010] Preferably, semicircular grooves are equidistantly provided on the surface of the rotating block to increase the friction force on the surface of the rotating block, thereby ensuring that the staff can stably grasp the rotating block for rotation and preventing the surface of the rotating block from being too smooth to be stably grasped.

[0011] Preferably, a lifting rod is slidably connected to the inner walls of the two lifting seats, and the top of the lifting rod is fixedly connected to the lower surface of the support plate. When the support plate moves up and down, the lifting rod slides along the inner wall of the rectangular groove of the lifting seat, ensuring that the support plate moves up and down in a directional manner, thereby improving the stability of the movement of the support plate.

[0012] Compared with the related art, the aero engine blade assembly fixture provided by the utility model has the following beneficial effects:

[0013] The utility model provides an aircraft engine blade assembly fixture:

[0014] 1. By using a mounting shell, a blade assembly, a moving block, a semi-cylinder, a linkage groove and a bidirectional screw, the blade assembly can be clamped from the inner wall of the circular hole of the blade assembly to prevent the blade assembly from being suspended during the clamping process, thereby improving the practicality of the aircraft engine blade assembly fixture.

[0015] 2. A lifting rod is slidably connected through the inner walls of the two lifting seats, and the top of the lifting rod is fixedly connected to the lower surface of the support plate. When the support plate moves up and down, the lifting rod slides along the inner wall of the rectangular groove of the lifting seat to ensure that the support plate moves up and down in a directional manner, thereby improving the stability of the movement of the support plate. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The overall structural diagram provided by the utility model;

[0017] Figure 2 A schematic diagram of the separation of the blade assembly provided by the utility model;

[0018] Figure 3 A schematic cross-sectional view of the installation shell provided by the utility model;

[0019] Figure 4 This is an enlarged schematic diagram of the moving block provided by the utility model.

[0020] Numbers in the figure: 1. Mounting shell; 2. Blade assembly; 3. Moving block; 4. Semi-cylinder; 5. Linking groove; 6. Bidirectional screw; 7. Driving disk; 8. Guide groove; 9. Guide rod; 10. Support plate; 11. Limit block; 12. Rotating block; 13. One-way screw; 14. Lifting seat; 15. Lifting rod. DETAILED DESCRIPTION

[0021] The utility model is further described below in conjunction with the accompanying drawings and implementation modes.

[0022] Please refer to Figure 1 , Figure 2 , Figure 3 and Figure 4The aircraft engine blade assembly fixture includes: a mounting shell 1, a blade assembly 2, a moving block 3 and a semi-cylinder 4, wherein the blade assembly 2 is arranged above the mounting shell 1, and the moving blocks 3 are symmetrically and slidably installed inside the two rectangular grooves of the mounting shell 1, and the upper surfaces of the two moving blocks 3 are fixedly connected with semi-cylinders 4, and the semi-cylinders 4 are connected with the circular holes of the blade assembly 2; a linkage groove 5 and a bidirectional screw rod 6, wherein the two moving blocks 3 are provided with a linkage groove 5, and the inner walls of the two rectangular grooves of the mounting shell 1 are rotatably connected with the bidirectional screw rod 6, and the threaded surface of the bidirectional screw rod 6 is meshed with the inner wall of the linkage groove 5, and the bidirectional screw rod 6 is rotated, and the threaded surface of the bidirectional screw rod 6 contacts the inner wall of the linkage groove 5, driving the moving blocks 3 to move away from each other, and the moving blocks 3 drive the semi-cylinders 4 to squeeze the inner wall of the circular hole of the blade assembly 2, and firmly clamp the blade assembly 2, so as to facilitate the inspection and maintenance of the blade assembly 2.

[0023] Embodiment 1:

[0024] In the specific implementation process, Figure 3 As shown, the two sides of the bidirectional screw rod 6 are symmetrically fixedly connected with a driving disk 7. Rotating the driving disk 7 drives the bidirectional screw rod 6 to rotate on the inner walls of the two rectangular grooves of the mounting shell 1, providing drive for the rotation of the bidirectional screw rod 6. The driving disk 7 can be rotated manually without the assistance of tools.

[0025] refer to Figure 3 As shown, guide grooves 8 are symmetrically provided on both sides of the two moving blocks 3, and the guide grooves 8 are located on both sides of the linkage groove 5. The inner walls of the two rectangular grooves of the mounting shell 1 are symmetrically fixedly connected with guide rods 9, and the guide rods 9 are slidably connected with the guide grooves 8. When the moving blocks 3 move away from each other, the guide rods 9 slide on the inner walls of the guide grooves 8 to ensure that the moving blocks 3 move stably and horizontally, and no shaking occurs during the movement of the moving blocks 3.

[0026] refer to Figure 1 and Figure 4 As shown, a support plate 10 is arranged above the two moving blocks 3, and a one-way screw 13 is fixedly connected to the upper surfaces of the two moving blocks 3. Lifting seats 14 are symmetrically arranged on both sides of the two one-way screws 13, and the bottom of the lifting seat 14 is fixedly connected to the upper surface of the moving block 3, and the lower surfaces of the two support plates 10 are fixedly connected to the limiting blocks 11. The inner wall of the circular hole of the limiting block 11 is rotatably connected with a rotating block 12. The rotating block 12 on the inner wall of the circular hole of the rotating block 12 contacts the threaded surface of the one-way screw 13, driving the support plate 10 to move upward, and the upper surface of the support plate 10 contacts the lower surface of the blade assembly 2 to prevent the blade assembly 2 from being suspended during the clamping process.

[0027] refer to Figure 4As shown, semicircular grooves are equidistantly provided on the surface of the rotating block 12 to increase the friction force on the surface of the rotating block 12, thereby ensuring that the staff can stably grasp the rotating block 12 for rotation and preventing the surface of the rotating block 12 from being too smooth and unable to be grasped stably.

[0028] Embodiment 2:

[0029] refer to Figure 4 As shown, the inner walls of the two lifting seats 14 are slidably connected with lifting rods 15, and the tops of the lifting rods 15 are fixedly connected to the lower surface of the support plate 10. When the support plate 10 moves up and down, the lifting rods 15 slide along the inner walls of the rectangular grooves of the lifting seats 14, ensuring that the support plate 10 moves up and down in a directional manner, thereby improving the stability of the movement of the support plate 10.

[0030] The above are only embodiments of the present invention, and are not intended to limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made using the contents of the specification and drawings of the present invention, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. An aircraft engine blade assembly fixture, characterized in that: include: A mounting shell (1), a blade assembly (2), a moving block (3) and a semi-cylinder (4), wherein the blade assembly (2) is arranged above the mounting shell (1), the moving blocks (3) are symmetrically slidably mounted inside two rectangular grooves of the mounting shell (1), the upper surfaces of the two moving blocks (3) are fixedly connected with semi-cylinders (4), and the semi-cylinders (4) are connected to the circular holes of the blade assembly (2); A linkage groove (5) and a bidirectional screw rod (6), wherein the two moving blocks (3) are provided with a linkage groove (5), the inner walls of the two rectangular grooves of the mounting shell (1) are rotatably connected with the bidirectional screw rod (6), and the threaded surface of the bidirectional screw rod (6) is meshedly connected with the inner wall of the linkage groove (5).

2. The aircraft engine blade assembly fixture according to claim 1, characterized in that: The two sides of the bidirectional screw rod (6) are symmetrically fixedly connected with a driving disk (7).

3. The aircraft engine blade assembly fixture according to claim 1, characterized in that: The two movable blocks (3) are symmetrically provided with guide grooves (8), and the guide grooves (8) are located on both sides of the linkage groove (5). The inner walls of the two rectangular grooves of the mounting shell (1) are symmetrically fixedly connected with guide rods (9), and the guide rods (9) are slidably connected with the guide grooves (8).

4. The aircraft engine blade assembly fixture according to claim 1, characterized in that: A support plate (10) is arranged above the two moving blocks (3); a one-way screw rod (13) is fixedly connected to the upper surfaces of the two moving blocks (3); a lifting seat (14) is symmetrically arranged on both sides of the two one-way screw rods (13); and the bottom of the lifting seat (14) is fixedly connected to the upper surface of the moving block (3).

5. The aircraft engine blade assembly fixture according to claim 4, characterized in that: The lower surfaces of the two support plates (10) are fixedly connected to a limiting block (11), and the inner wall of the circular hole of the limiting block (11) is rotatably connected to a rotating block (12).

6. The aircraft engine blade assembly fixture according to claim 5, characterized in that: The surface of the rotating block (12) is provided with semicircular grooves at equal intervals.

7. The aircraft engine blade assembly fixture according to claim 4, characterized in that: The inner walls of the two lifting seats (14) are slidably connected with lifting rods (15), and the tops of the lifting rods (15) are fixedly connected to the lower surface of the support plate (10).

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