Aero-engine maintenance supporting component

Abstract

The utility model relates to the technical field of aero-engine maintenance, and discloses an aero-engine maintenance supporting component which comprises two supporting frames, the top ends of the supporting frames are fixedly connected with installation rings, the interiors of the installation rings are rotationally connected with rotating sleeves, the front ends and the rear ends of the rotating sleeves are rotationally connected with threaded sleeves, and the front ends and the rear ends of the rotating sleeves are provided with hole grooves. The interior of the rotating sleeve is in threaded connection with a threaded column, the interior of the hole groove is slidably connected with limiting rods, one end of the threaded column is fixedly connected with a clamping plate, a plurality of rubber strips are arranged in the clamping plate, and one ends of the two limiting rods are fixedly connected to the upper end and the lower end of the clamping plate. After the aero-engine is fixed, the aero-engine can be conveniently rotated according to different surfaces of the engine needing to be maintained, and the situation that the engine is rotated to the surface needing to be maintained after being unfixed and then is installed and fixed again is not needed, so that the operation time is conveniently shortened, the maintenance difficulty is reduced, and the maintenance efficiency is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aero-engine maintenance, in particular to a support member for aero-engine maintenance. Background Art

[0002] An aero-engine is a highly complex and precise thermal machinery. As the heart of an aircraft, it is not only the power for the aircraft to fly but also an important driving force for the development of the aviation industry. The aero-engines in use include various types such as turbofan engines, turboprop engines, ramjet engines, and piston engines. An aero-engine is a complex system containing many precision components. Through regular maintenance and inspection, potential problems can be detected and handled in a timely manner to prevent small problems from becoming big problems, thereby reducing the possibility of sudden failures.

[0003] After retrieval, the aero-engine maintenance support member disclosed in the Chinese patent with the application number CN201821883593.0 is such that when an aero-engine generally needs to be maintained, the connection between the engine and the aircraft / helicopter needs to be separated, and then the aero-engine is removed from the power cabin by a hoisting or lifting device, and then the maintenance work is carried out. The operation is rather troublesome, costly, time-consuming and laborious. Therefore, under the dual action of the clamping member and the support member, the fixing effect on the engine is good, and at the same time, the position of the clamping member can be adjusted according to needs, which is convenient for the maintenance of the engine and is extremely convenient to use.

[0004] During the use of the above support frame, it is only convenient to support and clamp the aero-engine, but not convenient to rotate and maintain the engine. When the aero-engine is fixed on the support member and multi-directional maintenance of the engine is required, the fixed aero-engine is not convenient to rotate to adjust the position for maintenance. Therefore, when the operator inspects different surfaces, the engine needs to be unfixed, rotated to the surface to be inspected, and then reinstalled. The operation is rather troublesome, increasing the difficulty of engine maintenance and reducing the maintenance efficiency. Summary of the Utility Model

[0005] The purpose of the utility model is to provide a support member for aero-engine maintenance to solve the deficiencies existing in the prior art.

[0006] To achieve the above object, the utility model adopts the following technical solutions: an aviation engine maintenance support member, including two support frames, the top ends of the support frames are fixedly connected with mounting rings, the inside of the mounting rings are rotatably connected with rotating sleeves, the front and rear ends of the rotating sleeves are rotatably connected with threaded sleeves, the front and rear ends of the rotating sleeves are provided with hole grooves, the inside of the threaded sleeves are threadedly connected with threaded columns, the inside of the hole grooves are slidably connected with limiting rods, one end of the threaded column is fixedly connected with a clamping plate, the inside of the clamping plate is provided with a plurality of rubber strips, one ends of the two limiting rods are fixedly connected to the upper and lower ends of the clamping plate, the left end of the left support frame is fixedly connected with a fixing plate, the left end of the left rotating sleeve is fixedly connected with a connecting frame, the left end of the connecting frame is fixedly connected with a rotating handle, the right end of the rotating handle is rotatably connected to the top end of the fixing plate, the left top of the fixing plate is provided with a plurality of threaded holes, and the top end of the rotating handle penetrates through a bolt, and the plurality of threaded holes are annularly distributed.

[0007] As a further description of the above technical solution:

[0008] The bottom of the support frame is fixedly connected with a bottom plate, and the left end of the right bottom plate is fixedly connected with an outer plate.

[0009] As a further description of the above technical solution:

[0010] The right end of the left bottom plate is fixedly connected with an adjusting plate.

[0011] As a further description of the above technical solution:

[0012] The inside of the adjusting plate is provided with a threaded groove, the top right end of the outer plate is rotatably connected with a knob, and the bottom of the knob is fixedly connected with a first bevel gear.

[0013] As a further description of the above technical solution:

[0014] The middle part of the inside of the outer plate is rotatably connected with a threaded rod, the outside of the threaded rod is threadedly connected inside the threaded groove, one end of the threaded rod is fixedly connected with a second bevel gear, and the first bevel gear and the second bevel gear are meshed with each other.

[0015] As a further description of the above technical solution:

[0016] The left bottom of the right support frame is fixedly connected with two outer tubes, and the right bottom of the left support frame is fixedly connected with two inner columns.

[0017] As a further description of the above technical solution:

[0018] The outside of the inner column is slidably connected inside the outer tube, and the opposite sides of the two support frames are fixedly connected with stabilizing frames.

[0019] The utility model has the following beneficial effects:

[0020] 1. Through the mutual cooperation of the support frame, mounting ring, rotating sleeve, threaded sleeve, hole groove, threaded column, limiting rod, clamping plate, rubber strip, connecting frame and rotating handle, the utility model adds the function of facilitating the rotation of the aero-engine according to different surfaces of the engine to be repaired after the aero-engine is fixed, without the need to remove the fixing of the engine and then rotate it to the surface to be repaired and reinstall and fix it, thus facilitating the shortening of the operation time, reducing the difficulty of maintenance, and being beneficial to improving the maintenance efficiency.

[0021] 2. Through the mutual cooperation of the bottom plate, outer plate, adjusting plate, threaded groove, knob, first bevel gear, threaded rod, second bevel gear, outer tube and inner column, the utility model adds the function of facilitating the adjustment of the support length dimension of the support member according to the length dimension of the aero-engine, improves the adaptability to aero-engines of different lengths, is beneficial to improving the stability of the support, and thus facilitates the maintenance operation. Description of the Drawings

[0022] Figure 1 is the overall structural schematic diagram of the aero-engine maintenance support member proposed by the utility model;

[0023] Figure 2 is the structural schematic diagram of the bottom plate of the aero-engine maintenance support member proposed by the utility model;

[0024] Figure 3 is the structural schematic diagram of the threaded sleeve of the aero-engine maintenance support member proposed by the utility model;

[0025] Figure 4 is the structural schematic diagram of the support frame of the aero-engine maintenance support member proposed by the utility model;

[0026] Figure 5 is the structural schematic diagram of the connecting frame of the aero-engine maintenance support member proposed by the utility model;

[0027] Figure 6 is the structural schematic diagram of the adjusting plate of the aero-engine maintenance support member proposed by the utility model.

[0028] Legend Explanation:

[0029] 1. Support frame; 2. Installation ring; 3. Rotating sleeve; 4. Threaded sleeve; 5. Hole groove; 6. Threaded column; 7. Limiting rod; 8. Clamping plate; 9. Rubber strip; 10. Fixed plate; 11. Connecting frame; 12. Rotating handle; 13. Threaded hole; 14. Bolt; 15. Bottom plate; 16. Outer plate; 17. Adjusting plate; 18. Threaded groove; 19. Knob; 20. First bevel gear; 21. Threaded rod; 22. Second bevel gear; 23. Outer tube; 24. Inner column; 25. Stabilizing frame. Detailed implementation manner

[0030] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0031] As shown in the atta Figure 1-6 ched drawings, an embodiment provided by the present invention: an aviation engine maintenance support member, including two support frames 1, the top ends of the support frames 1 are fixedly connected with installation rings 2, the inside of the installation rings 2 is rotatably connected with rotating sleeves 3, the front and rear ends of the rotating sleeves 3 are rotatably connected with threaded sleeves 4, the front and rear ends of the rotating sleeves 3 are provided with hole grooves 5, the inside of the threaded sleeves 4 is threadedly connected with threaded columns 6, the inside of the hole grooves 5 is slidably connected with limiting rods 7, one end of the threaded column 6 is fixedly connected with a clamping plate 8, a plurality of rubber strips 9 are arranged inside the clamping plate 8, one end of the two limiting rods 7 is fixedly connected to the upper and lower ends of the clamping plate 8, the left end of the left support frame 1 is fixedly connected with a fixed plate 10, the left end of the left rotating sleeve 3 is fixedly connected with a connecting frame 11, the left end of the connecting frame 11 is fixedly connected with a rotating handle 12, the right end of the rotating handle 12 is rotatably connected to the top end of the fixed plate 10, a plurality of threaded holes 13 are arranged at the top of the left end of the fixed plate 10, the top end of the rotating handle 12 penetrates through a bolt 14, and the plurality of threaded holes 13 are annularly distributed. By rotating the rotating handle 12, the connecting frame 11 drives the rotating sleeve 3 to rotate. The rotating sleeve 3 rotates inside the installation ring 2, which is convenient for driving the engine clamped by the clamping plate 8 to rotate, so as to facilitate the maintenance of different angular surfaces of the engine, and the rotated rotating handle 12 is fixed by using the threaded holes 13 and the bolt 14.

[0032] As shown in the atta Figure 2 ched drawings, the bottom of the support frame 1 is fixedly connected with a bottom plate 15, the left end of the right bottom plate 15 is fixedly connected with an outer plate 16, and the right end of the left bottom plate 15 is fixedly connected with an adjusting plate 17, which is convenient for adjusting the distance between the two support frames 1.

[0033] As shown in the atta Figure 6As shown in the figure, a threaded groove 18 is provided inside the adjusting plate 17. The right end of the top of the outer plate 16 is rotatably connected to a knob 19. The bottom of the knob 19 is fixedly connected to a first bevel gear 20. The middle part of the inner side of the outer plate 16 is rotatably connected to a threaded rod 21. The outside of the threaded rod 21 is threadedly connected inside the threaded groove 18. One end of the threaded rod 21 is fixedly connected to a second bevel gear 22. The first bevel gear 20 and the second bevel gear 22 are meshed. By the movement of the threaded rod 21 inside the threaded groove 18, it is convenient to push the adjusting plate 17 to move in position.

[0034] As shown in the attached Figure 1 figure, two outer tubes 23 are fixedly connected to the bottom left end of the right end support frame 1, and two inner columns 24 are fixedly connected to the bottom right end of the left end support frame 1. The outside of the inner column 24 is slidably connected inside the outer tube 23. Stable frames 25 are fixedly connected to the opposite sides of the two support frames 1. The outer tubes 23 and the inner columns 24 are beneficial to enhancing the stability of the two support frames 1 during movement.

[0035] Working principle: When in use, first insert the aero-engine into the two rotating sleeves 3, and then rotate a plurality of threaded sleeves 4, so that the threaded sleeves 4 rotate outside the rotating sleeves 3. When the threaded sleeves 4 rotate, due to the limiting effect of the limiting rod 7 sliding in the hole groove 5, it is convenient to make the threaded column 6 push the clamping plate 8 towards the engine inside the rotating sleeve 3 and then close it tightly. Under the fitting protection of the rubber strip 9, clamping is achieved. When it is necessary to rotate and repair the engine, rotate the rotating handle 12, so that the rotating handle 12 drives the connecting frame 11 to rotate, which is convenient for the connecting frame 11 to drive the rotating sleeve 3 to rotate inside the mounting ring 2, so as to drive the clamped aero-engine to rotate. When rotating to the surface that needs to be repaired, screw the bolt 14 into the corresponding threaded hole 13, which is convenient to fix the position of the rotated rotating handle 12, so as to facilitate the repair of different surfaces and improve the repair efficiency. And when it is necessary to adjust the support member according to the length of the engine, turn the knob 19, which is convenient for the knob 19 to drive the first bevel gear 20 to rotate. Through the meshing of the first bevel gear 20 and the second bevel gear 22, it is convenient for the second bevel gear 22 to drive the threaded rod 21 to rotate, so as to facilitate the movement of the threaded rod 21 inside the threaded groove 18. Under the action of the threaded groove 18, it is convenient to push the extension of the adjusting plate 17. When the internal distance between the adjusting plate 17 and the outer plate 16 changes, it drives the inner column 24 to move inside the outer tube 23, so as to drive the two support frames 1 to approach or move away from each other, which is convenient for flexibly adjusting the length of the support member to adapt to the length dimensions of different engines.

[0036] Finally, it should be noted that the above are only the preferred embodiments of the present utility model and are not intended to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements on some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. An aircraft engine maintenance support structure, comprising two support frames (1), characterized in that: The top of the support frame (1) is fixedly connected to a mounting ring (2), the interior of the mounting ring (2) is rotatably connected to a rotating sleeve (3), the front and rear ends of the rotating sleeve (3) are rotatably connected to threaded sleeves (4), the front and rear ends of the rotating sleeve (3) are provided with hole grooves (5), the interior of the threaded sleeve (4) is threadedly connected to a threaded column (6), the interior of the hole groove (5) is slidably connected to a limiting rod (7), one end of the threaded column (6) is fixedly connected to a clamping plate (8), the interior of the clamping plate (8) is provided with a plurality of rubber strips (9), and the two limiting rods (7) are provided with a plurality of rubber strips (9). ) is fixedly connected to the upper and lower ends of the clamping plate (8), the left end of the left end of the support frame (1) is fixedly connected to the fixed plate (10), the left end of the left end of the rotating sleeve (3) is fixedly connected to the connecting frame (11), the left end of the connecting frame (11) is fixedly connected to the rotating handle (12), the right end of the rotating handle (12) is rotatably connected to the top of the fixed plate (10), the top of the left end of the fixed plate (10) is provided with a plurality of threaded holes (13), the top of the rotating handle (12) is penetrated by a bolt (14), and the plurality of threaded holes (13) are distributed in a ring shape.

2. The aircraft engine maintenance support structure according to claim 1, characterized in that: The bottom of the support frame (1) is fixedly connected to a bottom plate (15), and the left end of the bottom plate (15) is fixedly connected to an outer plate (16).

3. The aircraft engine maintenance support structure according to claim 2, characterized in that: The right end of the left bottom plate (15) is fixedly connected with an adjustment plate (17).

4. The aircraft engine maintenance support structure according to claim 3, characterized in that: The adjusting plate (17) is provided with a threaded groove (18) inside, the top right end of the outer plate (16) is rotatably connected to a knob (19), and the bottom of the knob (19) is fixedly connected to a first bevel gear (20).

5. The aircraft engine maintenance support structure according to claim 4, characterized in that: A threaded rod (21) is rotatably connected to the middle portion of the inner side of the outer plate (16); the outer thread of the threaded rod (21) is connected to the inside of the thread groove (18); one end of the threaded rod (21) is fixedly connected to a second bevel gear (22); and the first bevel gear (20) and the second bevel gear (22) are meshingly connected.

6. The aircraft engine maintenance support structure according to claim 1, characterized in that: The left bottom end of the right support frame (1) is fixedly connected to two outer tubes (23), and the right bottom end of the left support frame (1) is fixedly connected to two inner columns (24).

7. The aircraft engine maintenance support structure according to claim 6, characterized in that: The outside of the inner column (24) is slidably connected to the inside of the outer tube (23), and the opposite sides of the two support frames (1) are fixedly connected with stabilizing frames (25).

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