Horizontal screw jack bracket for dismounting and mounting universal joint ring of aero-engine

Abstract

The utility model discloses a horizontal type screw jack bracket for dismounting and mounting a universal joint ring of an aero-engine. The horizontal type screw jack bracket comprises a lifting bracket main body, a positioning pin hole and a connecting pin hole, the lifting support body comprises a support body and a contact groove. A contact groove is formed in the top surface of the bracket body; two positioning pin holes are formed in one side of the support body and connected with an aero-engine front support through positioning pins. Two connecting pin holes are formed in the bottom face of the support body and connected with the horizontal screw jack through connecting pins. The support body is made of high-damping rubber, and the surface of the support body is covered with a rubber protection layer. The contact groove is of an arc-shaped structure and makes contact with the outer surface of the universal joint ring of the aero-engine through the dispersing assembly, the horizontal type screw jack support for disassembling and assembling the universal joint ring of the aero-engine is simple and reasonable in structure, ingenious in design and capable of being operated by a single person, the maintenance safety is guaranteed, and the maintenance efficiency is improved. And the working efficiency and the stability are greatly improved.

Description

Technical Field

[0001] This utility model relates to the field of mechanical control device technology, specifically a horizontal spiral jack support for the assembly and disassembly of universal joint rings in aero engines. Background Technology

[0002] A universal joint ring for an aircraft engine is a mechanical device mainly used to realize the power transmission between different axes. It allows two shafts to rotate freely within a certain angle range while maintaining continuous power transmission. The core principle of the universal joint ring is to use ball joints or cross joints so that two shafts can work normally under varying angles.

[0003] During routine maintenance, when disassembling and assembling components such as the hydraulic pump belt, rotor brake device, power transmission shaft assembly, and main reducer input end seal, the engine needs to be suspended at a certain height to disassemble and assemble the universal joint ring. Currently, the disassembly and assembly tooling used in the field consists of a simple set of three steel pipes and two hooks, with adjustment achieved by adjusting the length of the screw. This tooling is used frequently and is prone to damage. The main shortcomings of this tooling are as follows:

[0004] First, the tooling requires wooden blocks to support the load points on both sides, which is not stable enough. The helicopter cannot move, which may cause the engine to fall off during suspension and cause accidental damage.

[0005] Secondly, the height on both sides is mainly adjusted by adjusting the two nuts on the upper and lower parts of the hook, which makes height adjustment difficult and the left and right height difficult to control precisely, resulting in less effort for more work.

[0006] Third, the hook is not strong enough, and frequent use can easily cause the nut to strip, affecting normal use. Utility Model Content

[0007] The purpose of this utility model is to provide a horizontal screw jack bracket for the disassembly and assembly of universal joint rings in aircraft engines, in order to solve the problems of poor stability, difficulty in height adjustment, insufficient hook strength, and easy stripping of nuts due to frequent use mentioned in the background art.

[0008] To achieve the above objectives, this utility model provides the following technical solution: a horizontal screw jack bracket for disassembling and assembling universal joint rings of aircraft engines, comprising a support bracket body, positioning pin holes, and connecting pin holes; the support bracket body includes a bracket body for supporting the universal joint ring of the aircraft engine and a contact groove; the contact groove is provided on the top surface of the bracket body; two positioning pin holes are provided on one side of the bracket body, and the positioning pin holes are connected to the front bracket of the aircraft engine through positioning pins; two connecting pin holes are provided on the bottom surface of the bracket body, and the connecting pin holes are connected to the horizontal screw jack through connecting pins.

[0009] Preferably, the support body is made of high-damping rubber, and the surface of the support body is covered with a rubber protective layer.

[0010] Preferably, the contact groove has an arc-shaped structure, and the contact groove contacts the outer surface of the front support of the aero-engine through a dispersion component.

[0011] Preferably, the dispersion component includes dispersion elements and a dispersion plate; a plurality of dispersion elements are fixedly arranged in a ring array within the contact groove; the dispersion plate is fixedly connected to the end of the plurality of dispersion elements away from the contact groove.

[0012] Preferably, the dispersion element has an X-shaped structure.

[0013] Preferably, the dispersion plate has an arc-shaped structure and is in contact with the outer surface of the front support of the aero-engine.

[0014] Preferably, the center of the dispersion plate and the center of the contact groove are on the same straight line.

[0015] Compared with the prior art, the beneficial effects of this utility model are:

[0016] 1. This utility model, by setting up a support bracket body, positioning pin holes, and connecting pin holes, allows the bottom surface of the bracket body to fit against the horizontal screw jack by inserting the connecting pins from the horizontal screw jack into the connecting pin holes. Since the bracket body is made of high-damping rubber, this material integrates vertical load-bearing capacity, horizontal restoring force, and damping (energy absorption); the support hysteresis characteristics (load-deformation curve) are full and energy consumption is significant; maintenance and management costs are low (no other damping devices are required). Because the surface of the bracket body is covered with a rubber protective layer, it protects the internal rubber from ozone and ultraviolet radiation, providing better aging resistance. Subsequently, the bracket body is installed on the engine front bracket. Then, the horizontal screw jack is raised, allowing the bracket body to fully fit and bear load with the engine front bracket. Next, the positioning pin holes are connected to the aircraft engine universal joint ring via positioning pins, and the aircraft engine universal joint ring is then disassembled and assembled. Compared to existing technologies, this utility model has a simple and reasonable structure, ingenious design, and can be operated by a single person, ensuring maintenance safety and greatly improving work efficiency and stability.

[0017] 2. By setting up a dispersion component and a dispersion plate, when the dispersion plate contacts the outer surface of the front support of the aircraft engine, the dispersion plate will be subjected to force under the drive of the horizontal screw jack, and the force on the dispersion plate can be distributed to the dispersion component. Since the dispersion component has an X-shaped structure, it can have good pressure bearing capacity and stability, so that the support body can be subjected to force evenly, extending the service life of the support body, thereby improving the practicality of this utility model. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0019] Figure 2 This is a bottom view of the overall structure of this utility model;

[0020] Figure 3 This is a schematic diagram showing the overall structure of this utility model.

[0021] Figure 4 For the present utility model Figure 1 Enlarged diagram of point A in the middle.

[0022] In the picture:

[0023] 1. Support bracket body; 2. Positioning pin hole; 3. Connecting pin hole; 4. Dispersion component; 101. Bracket body; 102. Contact groove; 401. Dispersion component; 402. Dispersion plate. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0025] Please see Figures 1 to 4 This utility model provides a technical solution: a horizontal screw jack bracket for disassembling and assembling universal joint rings of aircraft engines, comprising a support bracket body 1, positioning pin holes 2, and connecting pin holes 3; the support bracket body 1 includes a bracket body 101 for supporting the universal joint ring of the aircraft engine and a contact groove 102; the contact groove 102 is provided on the top surface of the bracket body 101; two positioning pin holes 2 are provided on one side of the bracket body 101, and the positioning pin holes 2 are connected to the front bracket of the aircraft engine through positioning pins; two connecting pin holes 3 are provided on the bottom surface of the bracket body 101, and the connecting pin holes 3 are connected to the horizontal screw jack through connecting pins; the support body 101... 1. The material is high-damping rubber, which has low temperature dependence and is widely used in different climate regions. High-damping rubber has superior creep performance, just like natural rubber, and the surface of the bracket body 101 is covered with a rubber protective layer. The contact groove 102 has an arc-shaped structure and contacts the outer surface of the front bracket of the aircraft engine through the dispersion component 4. The reason for choosing the front bracket of the engine as the support point is that the front bracket of the power shaft between the engine and the main reducer needs to be disassembled during maintenance and cannot be used as a support point. Furthermore, the front bracket of the engine as a support helps to limit the displacement of the engine caused by the disassembly of the front and rear bushings during the support process.

[0026] This utility model, by setting up a support bracket body 1, a positioning pin hole 2, and a connecting pin hole 3, allows the bottom surface of the support body 101 to fit against the horizontal screw jack by inserting the connecting pin from the horizontal screw jack into the connecting pin hole 3. Since the support body 101 is made of high-damping rubber, this material integrates vertical load-bearing capacity, horizontal restoring force, and damping (energy absorption); the support hysteresis characteristics (load-deformation curve) are full and energy dissipation is significant; maintenance and management costs are low (no other damping devices are required); and because the surface of the support body 101 is covered with a rubber protective layer, the internal rubber is protected. The adhesive is unaffected by ozone and ultraviolet rays, exhibiting better aging resistance. Subsequently, the bracket body 101 is installed onto the engine front bracket. Then, the horizontal screw jack is raised to ensure that the bracket body 101 is fully attached to the engine front bracket and bears the load. Next, the positioning pin hole 2 is connected to the aircraft engine universal joint ring through the positioning pin, and the aircraft engine universal joint ring is then disassembled and assembled. Compared with the prior art, this utility model has a simple and reasonable structure, ingenious design, and can be operated by a single person. It not only ensures the safety of maintenance but also greatly improves the efficiency and stability of operation.

[0027] As a preferred embodiment, the dispersion component 4 includes a dispersion element 401 and a dispersion plate 402; a plurality of dispersion elements 401 are fixedly arranged in a ring array within the contact groove 102; the dispersion plate 402 is fixedly connected to one end of the plurality of dispersion elements 401 away from the contact groove 102; the dispersion element 401 has an X-shaped structure; the dispersion plate 402 has an arc-shaped structure and contacts the outer surface of the front support of the aero-engine; the center of the dispersion plate 402 and the center of the contact groove 102 are on the same straight line.

[0028] This invention, by setting up a dispersing component 401 and a dispersing plate 402, allows the dispersing plate 402 to be stressed when it contacts the outer surface of the front support of the aircraft engine under the drive of a horizontal screw jack. The force on the dispersing plate 402 can be distributed to the dispersing component 401. Since the dispersing component 401 has an X-shaped structure, it can have good pressure bearing capacity and stability, allowing the support body 101 to be evenly stressed, extending the service life of the support body 101, thereby improving the practicality of this invention.

[0029] Working principle: In use, insert the connecting pin on the horizontal screw jack into the connecting pin hole 3, so that the bottom surface of the bracket body 101 is in contact with the horizontal screw jack. Then, install the bracket body 101 onto the front bracket of the engine. Then, raise the horizontal screw jack so that the dispersion plate 402 contacts the outer surface of the front bracket of the aircraft engine, so that the force on the dispersion plate 402 can be distributed to the dispersion component 401, so that the bracket body 101 can be evenly stressed, and the bracket body 101 is completely in contact with the front bracket of the engine and bears the force. Then, connect the positioning pin hole 2 to the aircraft engine universal joint ring through the positioning pin, and then disassemble and assemble the aircraft engine universal joint ring.

[0030] The above is the entire working process of the device, and all contents not described in detail in this specification are existing technologies known to those skilled in the art.

[0031] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A horizontal screw jack bracket for assembling and disassembling universal joint rings in aircraft engines, characterized in that, The system includes a support bracket body (1), positioning pin holes (2), and connecting pin holes (3); the support bracket body (1) includes a bracket body (101) for supporting the universal joint ring of the aero-engine and a contact groove (102); the contact groove (102) is provided on the top surface of the bracket body (101); two positioning pin holes (2) are provided on one side of the bracket body (101), and the positioning pin holes (2) are connected to the front bracket of the aero-engine through positioning pins; two connecting pin holes (3) are provided on the bottom surface of the bracket body (101), and the connecting pin holes (3) are connected to the horizontal screw jack through connecting pins.

2. A horizontal screw jack bracket for assembling and disassembling universal joint rings in aero engines according to claim 1, characterized in that, The support body (101) is made of high-damping rubber, and the surface of the support body (101) is covered with a rubber protective layer.

3. A horizontal screw jack bracket for assembling and disassembling universal joint rings in aero engines according to claim 1, characterized in that, The contact groove (102) has an arc-shaped structure, and the contact groove (102) contacts the outer surface of the front support of the aircraft engine through the dispersion component (4).

4. A horizontal screw jack bracket for assembling and disassembling universal joint rings in aero engines according to claim 3, characterized in that, The dispersion component (4) includes a dispersion element (401) and a dispersion plate (402); a plurality of dispersion elements (401) are fixedly arranged in a ring array in the contact groove (102); the dispersion plate (402) is fixedly connected to the end of the plurality of dispersion elements (401) away from the contact groove (102).

5. A horizontal screw jack bracket for assembling and disassembling universal joint rings in aircraft engines according to claim 4, characterized in that, The dispersion component (401) has an X-shaped structure.

6. A horizontal screw jack bracket for assembling and disassembling universal joint rings in aero engines according to claim 4, characterized in that, The dispersion plate (402) has an arc-shaped structure and is in contact with the outer surface of the front support of the aero-engine.

7. A horizontal screw jack bracket for assembling and disassembling universal joint rings in aircraft engines according to claim 6, characterized in that, The center of the dispersion plate (402) and the center of the contact groove (102) are on the same straight line.

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