Aero-engine auxiliary hoisting device and method

Abstract

The invention relates to the field of aero-engine assembly, and discloses an aero-engine auxiliary hoisting device and method.The multi-degree-of-freedom assembly platform in the device comprises a platform body, a multi-degree-of-freedom rotating mechanism and a C-shaped assembly ring; the multi-degree-of-freedom rotating mechanism is arranged on the platform body, the C-shaped assembling ring is rotationally arranged on the multi-degree-of-freedom rotating mechanism, the auxiliary hoisting fixing assembly is arranged on the C-shaped assembling ring, and the aero-engine is assembled on the auxiliary hoisting fixing assembly in a sleeving mode and fixed to the C-shaped assembling ring through the auxiliary hoisting fixing assembly; and when the aero-engine rotates to a horizontal state through the C-shaped assembling ring on the auxiliary hoisting fixing assembly, one end of the cross beam hoisting tool is connected to the auxiliary hoisting fixing assembly in a hanging manner, and the other end of the cross beam hoisting tool is connected to the aero-engine in a hanging manner. The engine support has the effect of assisting in supporting an engine; when the engine is hoisted, the auxiliary hoisting device plays a role in hoisting, the hoisting work of the engine can be efficiently completed through the auxiliary hoisting device, and the reliability is high.

Description

Technical Field

[0001] The invention relates to the field of aircraft engine assembly, and in particular to an aircraft engine auxiliary hoisting device and method. Background Art

[0002] In the assembly technology of aircraft engines, the multi-degree-of-freedom assembly platform has become a key tool for improving assembly efficiency and quality due to its high flexibility and precise positioning capabilities. However, in actual application, the platform still faces a series of challenges in auxiliary support and post-assembly lifting.

[0003] Specifically, the auxiliary fulcrums of the multi-degree-of-freedom assembly platform generally adopt a pin structure design. Although this design meets the basic support requirements of the platform to a certain extent, it cannot be directly adapted and installed on the intermediate casing of the engine due to structural characteristics. This defect directly leads to a significant increase in the difficulty of operation when adjusting the attitude of the engine without additional auxiliary support measures, and the safety risk also increases accordingly. Due to the lack of stable auxiliary support, any slight deviation in the attitude adjustment process may cause engine instability, thereby threatening the personal safety of the assemblers and the integrity of the engine.

[0004] On the other hand, when the engine assembly process is successfully completed, it needs to be hoisted to the transport rack for subsequent transportation. However, due to the uneven weight distribution of the engine head, the forces borne by the main and auxiliary installation sections during the hoisting process are difficult to achieve an ideal balance. This uneven force not only prolongs the time for hoisting and disassembly, reducing the overall work efficiency, but also easily causes tilting due to the shift of the center of gravity of the engine at the moment of removal of the main installation section. The sudden tilt of the engine not only increases the risk of bumping or bruising the precision parts inside the engine, but also may pose a potential threat to the hoisting equipment and the surrounding environment.

[0005] In summary, the problems existing in the auxiliary support and post-assembly lifting links of the multi-degree-of-freedom assembly platform have become the key factors restricting the further improvement of the efficiency and quality of aircraft engine assembly. Therefore, it is urgent to develop an innovative solution to effectively meet the above challenges and ensure the safety, efficiency and accuracy of the aircraft engine assembly process. Summary of the invention

[0006] In order to overcome the defects of the above-mentioned prior art, the purpose of the present invention is to provide an aircraft engine auxiliary lifting device and method to solve the technical problem of how to improve the stability of the auxiliary support and lifting links of the aircraft engine on a multi-degree-of-freedom assembly platform in the prior art.

[0007] The present invention is achieved through the following technical solutions: In a first aspect, the present invention provides an auxiliary hoisting device for an aeroengine, comprising a multi-degree-of-freedom assembly platform and a crossbeam hoist; The multi-degree-of-freedom assembly platform includes a platform main body, a multi-degree-of-freedom rotating mechanism, and a C-shaped assembly ring; the multi-degree-of-freedom rotating mechanism is arranged on the platform main body, the C-shaped assembly ring is rotatably arranged on the multi-degree-of-freedom rotating mechanism, an auxiliary hoisting fixing component is arranged on the C-shaped assembly ring, the aeroengine is sleeved and assembled on the auxiliary hoisting fixing component, and is fixed on the C-shaped assembly ring through the auxiliary hoisting fixing component; when the aeroengine rotates to a horizontal state on the auxiliary hoisting fixing component through the C-shaped assembly ring, one end of the crossbeam hoist is hung and connected to the auxiliary hoisting fixing component, and the other end is hung and connected to the aeroengine.

[0008] Preferably, the auxiliary hoisting fixing component includes two groups of fixing components, an auxiliary fixing component, and an intermediate casing; The intermediate casing is in a ring structure and is arranged inside the C-shaped assembly ring, and the aeroengine is sleeved inside the intermediate casing; the two groups of fixing components are respectively arranged oppositely on the C-shaped assembly ring, and the fixed ends of the two groups of fixing components are respectively fixed on the aeroengine through the intermediate casing, the auxiliary fixing component is on the C-shaped assembly ring and is located between the two groups of fixing components, and the auxiliary fixing component is fixedly connected to the aeroengine by clamping on the intermediate casing.

[0009] Further, the auxiliary fixing component includes a fixing piece and an auxiliary hoisting piece; The fixing piece is on the C-shaped assembly ring and is located between the two groups of fixing components, the fixed end of the fixing piece is fixedly connected to the auxiliary hoisting piece, and is clamped on the intermediate casing through the auxiliary hoisting piece.

[0010] Furthermore, the structure of the fixing piece is the same as that of the fixing component.

[0011] Furthermore, the auxiliary hoisting piece includes an auxiliary support main body and a lifting lug; The lifting lug is fixed on the auxiliary support main body and is used for hanging and connecting with one end of the crossbeam hoist, a clamping end is arranged on the auxiliary support main body, and the clamping end is clamped and connected to the intermediate casing; a bearing hole is arranged on the auxiliary support main body, and the fixed end of the fixing piece is connected to the auxiliary support main body through the bearing hole.

[0012] Furthermore, the structure of the auxiliary support main body is in a U-shaped structure, wherein the open end is the clamping end, and a plurality of clamping bolts are respectively arranged on both sides of the clamping end, and the auxiliary support main body is clamped on the upper and lower ends of the intermediate casing through the plurality of clamping bolts.

[0013] Furthermore, the distance between the open ends of the auxiliary support main body corresponds to the height of the intermediate casing.

[0014] Furthermore, a bearing mounting seat is sequentially arranged in the bearing hole of the auxiliary support body, and a spherical bearing is arranged on the bearing mounting seat; the fixed end of the fixing member is connected to the auxiliary support body by being inserted into the spherical bearing.

[0015] Furthermore, the lifting ear is provided with a connecting bolt, and is hung and connected to one end of the beam hanger through the connecting bolt.

[0016] In a second aspect, the present invention further provides an aircraft engine auxiliary hoisting method, based on the above-mentioned aircraft engine auxiliary hoisting device, comprising the following process: The aircraft engine is mounted on the C-shaped assembly ring and fixed by an auxiliary lifting and fixing assembly. The C-shaped assembly ring is driven to rotate on the platform body by a multi-degree-of-freedom rotation mechanism, so that the aircraft engine is rotated to a horizontal state. One end of the crossbeam hanger is hung and connected to the auxiliary lifting and fixing assembly, and the other end is hung and connected to the aircraft engine to complete the auxiliary lifting of the aircraft engine.

[0017] Compared with the prior art, the present invention has the following beneficial technical effects: The present invention provides an auxiliary lifting device for an aero-engine. By setting an auxiliary lifting fixing assembly on a C-shaped assembly ring, the auxiliary support and lifting functions of the engine are taken into account, and the problems that the multi-degree-of-freedom auxiliary fulcrum and the engine cannot be transferred and the main and auxiliary installation sections of the engine are difficult to decompose are effectively solved; the operability is strong and the manufacturing cost is low. When the engine is assembled, the auxiliary lifting device plays the role of auxiliary support for the engine; when the engine is hoisted, the auxiliary lifting device plays the role of hanging. The auxiliary lifting device can efficiently complete the lifting work of the engine with high reliability.

[0018] Furthermore, the auxiliary fixing component is on the C-shaped assembly ring and is located between the two groups of fixing components. The auxiliary fixing component is fixedly connected to the aircraft engine by clamping on the intermediate casing. The auxiliary fixing component facilitates the two groups of fixing components to provide auxiliary support for the aircraft engine.

[0019] Furthermore, the fixing part is on the C-shaped assembly ring and is located between two sets of fixing components. The fixing end of the fixing part is fixedly connected to the auxiliary lifting part and is clamped on the intermediate casing through the auxiliary lifting part, so that the aircraft engine can be stably assembled on the intermediate casing.

[0020] Furthermore, the lifting lug is fixed on the auxiliary support body and is used for hanging connection with one end of the crossbeam hanger, so that the crossbeam hanger can hang the aircraft engine through the lifting lug, which greatly improves the reliability of the hanging.

[0021] The present invention provides an auxiliary hoisting method for an aeroengine. By sleeving the aeroengine on a C-shaped assembly ring and fixing it with an auxiliary hoisting and fixing component, a relatively stable preliminary installation structure is formed. This pre-fixing method reduces the shaking and displacement of the engine during subsequent operations, making the subsequent hoisting operation smoother, reducing the installation difficulty, and improving the installation efficiency. Driving the C-shaped assembly ring to rotate on the platform main body by a multi-degree-of-freedom rotating mechanism can accurately rotate the aeroengine to a horizontal state; after the aeroengine rotates to the horizontal state, one end of a crossbeam sling is hung and connected to the auxiliary hoisting and fixing component, and the other end is hung and connected to the aeroengine, forming a double-sling structure. The connection method of the crossbeam sling with the auxiliary hoisting and fixing component and the aeroengine makes the force on the engine more uniform. The weight of the engine is dispersed through multiple lifting points, avoiding structural deformation or damage caused by excessive local stress, and improving the safety and reliability of the hoisting process. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a schematic diagram of the overall structure of the auxiliary hoisting device for an aeroengine in an embodiment of the present invention; Figure 2 is a schematic diagram of the assembly structure of the auxiliary hoisting device for an aeroengine in an embodiment of the present invention; Figure 3 is a partially enlarged schematic diagram of the auxiliary hoisting device for an aeroengine in an embodiment of the present invention; Figure 4 is a schematic diagram of the structure of the auxiliary hoisting part in an embodiment of the present invention; Figure 5 is a schematic diagram of the hoisting of an aeroengine in an embodiment of the present invention; In the figure: 1. Multi-degree-of-freedom assembly platform; 2. Auxiliary hoisting part; 3. Intermediate casing; 4. Aeroengine; 5. Crossbeam sling; 11. Platform main body; 12. Multi-degree-of-freedom rotating mechanism; 13. Assembly table; 14. Fixing component; 21. Auxiliary support main body; 22. Lifting lug; 23. Connecting bolt; 24. Clamping bolt; 25. Spherical plain bearing; 26. Bearing mounting seat. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0023] In order to enable those skilled in the art to better understand the solution of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the 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 making creative efforts shall fall within the protection scope of the present invention.

[0024] The object of the present invention is to provide an auxiliary hoisting device and method for an aeroengine, so as to solve the technical problem of how to improve the stability of the auxiliary support and hoisting links of the aeroengine on a multi-degree-of-freedom assembly platform in the prior art.

[0025] The following further describes the present invention in detail with reference to the accompanying drawings: Embodiment 1 Refer to Figure 1 and Figure 2 In an embodiment of the present invention, an auxiliary hoisting device for an aeroengine is provided, which includes a multi-degree-of-freedom assembly platform 1 and a crossbeam sling 5; the multi-degree-of-freedom assembly platform 1 includes a platform main body 11, a multi-degree-of-freedom rotating mechanism 12, and a C-shaped assembly ring 13; the multi-degree-of-freedom rotating mechanism 12 is arranged on the platform main body 11, the C-shaped assembly ring 13 is rotatably arranged on the multi-degree-of-freedom rotating mechanism 12, an auxiliary hoisting fixing component is arranged on the C-shaped assembly ring 13, the aeroengine 4 is sleeved and assembled on the auxiliary hoisting fixing component, and is fixed on the C-shaped assembly ring 13 through the auxiliary hoisting fixing component; when the aeroengine 4 rotates to a horizontal state on the auxiliary hoisting fixing component through the C-shaped assembly ring 13, one end of the crossbeam sling 5 is hung and connected to the auxiliary hoisting fixing component, and the other end is hung and connected to the aeroengine 4, as Figure 5 shown.

[0026] Specifically, as shown in Figure 3 , the auxiliary hoisting fixing component includes two groups of fixing components 14, an auxiliary fixing component, and an intermediate casing 3; the intermediate casing 3 is in a ring structure and is arranged inside the C-shaped assembly ring 13, and the aeroengine 4 is sleeved inside the intermediate casing 3; the two groups of fixing components 14 are respectively arranged oppositely on the C-shaped assembly ring 13, and the fixed ends of the two groups of fixing components 14 are respectively fixed on the aeroengine 4 through the intermediate casing 3, the auxiliary fixing component is on the C-shaped assembly ring 13 and is located between the two groups of fixing components 14, and the auxiliary fixing component is fixedly connected to the aeroengine 4 by clamping on the intermediate casing 3.

[0027] In this embodiment, the intermediate casing 3 serves as a ring-shaped support body and is embedded inside the C-shaped assembly ring 13 to provide radial positioning and axial limiting for the aeroengine 4. Through cooperation with the fixing components 14 and the auxiliary fixing component, the engine is rigidly connected to the C-shaped assembly ring 13 to ensure the stability of the engine during the hoisting process.

[0028] Among them, the auxiliary fixing component includes a fixing member and an auxiliary hoisting member 2; the fixing member is on the C-shaped assembly ring 13 and is located between the two groups of fixing components 14, the fixed end of the fixing member is fixedly connected to the auxiliary hoisting member 2, and is clamped on the intermediate casing 3 through the auxiliary hoisting member 2. In this embodiment, the structure of the fixing member is the same as that of the fixing components 14.

[0029] Specifically, according to Figure 4 As shown, the auxiliary lifting member 2 includes an auxiliary support body 21 and a lifting lug 22; the lifting lug 22 is fixed on the auxiliary support body 21 and is used for hanging connection with one end of the crossbeam lifting tool 5. A clamping end is provided on the auxiliary support body 21, and the clamping end is clamped and connected to the intermediate casing 3; a bearing hole is provided on the auxiliary support body 21, and the fixed end of the fixing member is connected to the auxiliary support body 21 through the bearing hole.

[0030] Among them, the structure of the auxiliary support body 21 is in a U-shaped structure, and the open end is the clamping end. A plurality of clamping bolts 24 are respectively provided on both sides of the clamping end, and the auxiliary support body 21 is clamped on the upper and lower ends of the intermediate casing 3 through the plurality of clamping bolts 24.

[0031] Among them, the distance between the open ends of the auxiliary support body 21 corresponds to the height of the intermediate casing 3.

[0032] Specifically, a bearing mounting seat 26 is sequentially provided in the bearing hole of the auxiliary support body 21, and a spherical plain bearing 25 is provided on the bearing mounting seat 26; the fixed end of the fixing member is connected to the auxiliary support body 21 by being inserted into the spherical plain bearing 25.

[0033] In this embodiment, the spherical plain bearing 25 is designed with spherical sliding, allowing the fixing member to move freely in the axial, radial, and deflection directions. The movement of the fixing member is transmitted to the auxiliary support body 21 through the bearing mounting seat 26 to achieve the dispersion and balance of force. The fixing member can expand and contract along the bearing axis direction to adapt to the height change during the engine lifting process.

[0034] Specifically, a connecting bolt 23 is provided on the lifting lug 22, and the lifting lug 22 is hung and connected to one end of the crossbeam lifting tool 5 through the connecting bolt 23.

[0035] In this embodiment, the lifting lug 22 and the auxiliary support body 21 are integrally designed and processed. An opening is provided below the auxiliary support body 21 for connecting with the intermediate casing 5, and a connecting bolt is used for fastening; an opening is provided on the lifting lug 22 for hanging connection with the crossbeam lifting tool 5, and a clamping bolt is used for fastening; the bearing mounting seat 26 provides an installation base for the spherical plain bearing 25 and is fixed in the installation groove above the auxiliary support body by riveting; after lubricating oil is applied in the bearing mounting seat, the spherical plain bearing is installed into the bearing mounting seat through the notch of the bearing mounting seat.

[0036] In summary, the present invention provides an auxiliary hoisting device for an aeroengine. By providing an auxiliary hoisting and fixing component on the C-shaped assembly ring, it takes into account both the auxiliary support and hoisting functions of the engine, and can effectively solve problems such as the inability to transfer the multi-degree-of-freedom auxiliary fulcrum and the engine, and the difficulty in disassembling the main and auxiliary mounting nodes of the engine hoisting; it has strong operability and low manufacturing cost. During engine assembly, the auxiliary hoisting device plays an auxiliary supporting role for the engine; during engine hoisting, the auxiliary hoisting device plays a hanging role, and the engine hoisting work can be efficiently completed through the auxiliary hoisting device, with high reliability.

[0037] Embodiment 2 This embodiment provides an auxiliary hoisting method for an aeroengine. Based on the above-mentioned auxiliary hoisting device for an aeroengine, it includes the following processes: Set 4 aeroengines on the C-shaped assembly ring 13, fix the aeroengines 4 through the auxiliary hoisting and fixing component, and drive the C-shaped assembly ring 13 to rotate on the platform main body 11 through the multi-degree-of-freedom rotating mechanism 12, so that the aeroengines 4 rotate to a horizontal state. Then, one end of the crossbeam hoist 5 is hung and connected to the auxiliary hoisting and fixing component, and the other end is hung and connected to the aeroengine 4 to complete the auxiliary hoisting of the aeroengine.

[0038] The specific process is as follows: Hoist adjustment: Adjust the span and center of gravity of the front and rear hanging points of the crossbeam hoist 5 to match the design state of the aeroengine 4.

[0039] Engine attitude adjustment: Control the multi-degree-of-freedom assembly platform 1 to adjust the aeroengine 4 to a horizontal state; control the multi-degree-of-freedom assembly platform 1 to adjust the C-shaped assembly ring 13 directly above the aeroengine 4.

[0040] Hoist installation: Hang a manual hoist on the crane, and hang an electronic hanging scale under the manual hoist; use the hook of the electronic hanging scale to hang the crossbeam hoist 5 and zero the hanging scale; connect the front hanging point of the crossbeam hoist 5 to the ear 22 of the auxiliary hoisting part 2, and connect the rear hanging point of the crossbeam hoist 5 to the rear suspension of the aeroengine 4.

[0041] Removal of the auxiliary fulcrum of the multi-degree-of-freedom assembly platform: Slowly lift the crane and observe the reading of the electronic hanging scale until the crane bears the load; unscrew the auxiliary fulcrum of the multi-degree-of-freedom assembly platform 1.

[0042] Removal of the main fulcrum of the multi-degree-of-freedom assembly platform 1: By adjusting the manual hoist, slowly lift the crane and observe that the reading of the electronic hanging scale is approximately equal to the total weight of the engine, so that the main fulcrum of the multi-degree-of-freedom assembly platform no longer bears the load; unscrew the left and right main fulcrums of the multi-degree-of-freedom assembly platform in turn.

[0043] Lifting out of the aero-engine 4: Control the multi-degree-of-freedom assembly platform 1 and adjust the C-shaped assembly ring 13 to the side of the aero-engine 4; use a crane to lift out the aero-engine 4 from the multi-degree-of-freedom assembly platform 1.

[0044] In summary, the present invention provides an auxiliary lifting method for an aero-engine. By sleeving the aero-engine on the C-shaped assembly ring and fixing it with the auxiliary lifting and fixing components, a relatively stable preliminary installation structure is formed. This pre-fixing method reduces the shaking and displacement of the engine during subsequent operations, making the subsequent lifting operation smoother, reducing the installation difficulty, and improving the installation efficiency. Driving the C-shaped assembly ring to rotate on the platform main body by the multi-degree-of-freedom rotating mechanism can accurately rotate the aero-engine to the horizontal state; after the aero-engine rotates to the horizontal state, one end of the crossbeam sling is hung and connected to the auxiliary lifting and fixing components, and the other end is hung and connected to the aero-engine, forming a double-sling structure. The connection method of the crossbeam sling with the auxiliary lifting and fixing components and the aero-engine makes the force on the engine more uniform. The weight of the engine is dispersed through multiple lifting points, avoiding structural deformation or damage caused by excessive local force, and improving the safety and reliability of the lifting process.

[0045] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit them. Although the present invention has been described in detail with reference to the above embodiments, those of ordinary skill in the art should understand that: modifications or equivalent replacements can still be made to the specific implementation manners of the present invention, and any modification or equivalent replacement that does not depart from the spirit and scope of the present invention shall be covered by the protection scope of the claims of the present invention.

Claims

1. An auxiliary hoisting device for an aeroengine, characterized in that It includes a multi-degree-of-freedom assembly platform (1) and a crossbeam sling (5); The multi-degree-of-freedom assembly platform (1) includes a platform main body (11), a multi-degree-of-freedom rotating mechanism (12), and a C-shaped assembly ring (13); the multi-degree-of-freedom rotating mechanism (12) is arranged on the platform main body (11), the C-shaped assembly ring (13) is rotatably arranged on the multi-degree-of-freedom rotating mechanism (12), an auxiliary lifting and fixing component is arranged on the C-shaped assembly ring (13), the aero-engine (4) is sleeved and assembled on the auxiliary lifting and fixing component and fixed on the C-shaped assembly ring (13) through the auxiliary lifting and fixing component; when the aero-engine (4) rotates to a horizontal state on the auxiliary lifting and fixing component through the C-shaped assembly ring (13), one end of the crossbeam sling (5) is hung and connected to the auxiliary lifting and fixing component, and the other end is hung and connected to the aero-engine (4).

2. The auxiliary hoisting device for an aeroengine according to claim 1, characterized in that, The auxiliary lifting and fixing component includes two groups of fixing components (14), an auxiliary fixing component, and an intermediate casing (3); The intermediate casing (3) has an annular structure and is arranged inside the C-shaped assembly ring (13), and the aero-engine (4) is sleeved inside the intermediate casing (3); the two groups of fixing components (14) are respectively arranged oppositely on the C-shaped assembly ring (13), and the fixed ends of the two groups of fixing components (14) are respectively fixed on the aero-engine (4) through the intermediate casing (3), the auxiliary fixing component is on the C-shaped assembly ring (13) and is located between the two groups of fixing components (14), and the auxiliary fixing component is fixedly connected to the aero-engine (4) by clamping on the intermediate casing (3).

3. The auxiliary hoisting device for an aeroengine according to claim 2, characterized in that, The auxiliary fixing component includes a fixing piece and an auxiliary lifting piece (2); The fixing piece is on the C-shaped assembly ring (13) and is located between the two groups of fixing components (14), the fixed end of the fixing piece is fixedly connected to the auxiliary lifting piece (2), and is clamped on the intermediate casing (3) through the auxiliary lifting piece (2).

4. The auxiliary hoisting device for an aeroengine according to claim 3, characterized in that, The structure of the fixing piece is the same as that of the fixing component (14).

5. The auxiliary lifting device for an aeroengine according to claim 3, characterized in that, The auxiliary lifting piece (2) includes an auxiliary support main body (21) and a lifting lug (22); The lifting lug (22) is fixed on the auxiliary support main body (21) and is used for hanging and connecting with one end of the crossbeam sling (5), a clamping end is arranged on the auxiliary support main body (21), and the clamping end is clamped and connected to the intermediate casing (3); a bearing hole is arranged on the auxiliary support main body (21), and the fixed end of the fixing piece is connected to the auxiliary support main body (21) through the bearing hole.

6. The auxiliary hoisting device for an aeroengine according to claim 5, characterized in that, The structure of the auxiliary support main body (21) is in a U-shaped structure, where the open end is the clamping end, and several clamping bolts (24) are respectively arranged on both sides of the clamping end, and the auxiliary support main body (21) is clamped on the upper and lower ends of the intermediate casing (3) through the several clamping bolts (24).

7. The auxiliary hoisting device for an aeroengine according to claim 6, characterized in that, The distance between the open ends of the auxiliary support main body (21) corresponds to the height of the intermediate casing (3).

8. An auxiliary hoisting device for an aeroengine according to claim 5, characterized in that, A bearing mounting seat (26) is sequentially arranged in the bearing hole of the auxiliary support body (21), and a spherical plain bearing (25) is arranged on the bearing mounting seat (26); the fixed end of the fixing member is connected to the auxiliary support body (21) by being inserted into the spherical plain bearing (25).

9. The auxiliary hoisting device for an aeroengine according to claim 5, characterized in that, A connecting bolt (23) is arranged on the lifting lug (22), and is hung and connected to one end of the crossbeam lifting tool (5) through the connecting bolt (23).

10. A method for auxiliary hoisting of an aeroengine, characterized in that, An aero-engine auxiliary lifting device according to any one of claims 1-9, comprising the following process: The aero-engine (4) is sleeved on the C-shaped assembly ring (13), and the aero-engine (4) is fixed by the auxiliary lifting and fixing assembly, and the C-shaped assembly ring (13) is driven by the multi-degree-of-freedom rotating mechanism (12) to rotate on the platform main body (11) so that the aero-engine (4) rotates to a horizontal state, and one end of the crossbeam lifting tool (5) is hung and connected to the auxiliary lifting and fixing assembly, and the other end is hung and connected to the aero-engine (4) to complete the auxiliary lifting of the aero-engine.

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