Assembly and disassembly tool for combined rotor and complete machine of turbojet engine

Abstract

The utility model discloses a turbojet engine combined rotor and complete machine assembly and disassembly tool in the technical field of aero-engine assembly, which comprises a bottom plate, a supporting unit and a positioning structure unit are arranged on the bottom plate, the supporting unit is used for supporting and fixing a turbojet engine combined rotor turbine shaft, and the positioning structure unit is used for positioning the turbojet engine combined rotor. The positioning structure unit is used for supporting the combined rotor when the whole turbojet engine is disassembled and assembled; the supporting unit comprises a support for providing a supporting point position for the combined rotor turbine shaft; the positioning structure comprises a positioning ring, the positioning ring is fixed on the bottom plate, a concave positioning hole is formed in the positioning ring, and the positioning hole can be used for fixing and supporting a combined rotor. The combined rotor of the small turbojet engine can be completely fixed to all the assemblies, and it can be conveniently guaranteed that all locking nuts of the combined rotor are easily disassembled in the assembling and disassembling process of the combined rotor and all the assemblies.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engine assembly, in particular to a turbojet engine combined rotor and complete machine assembly and disassembly tool. Background Art

[0002] At present, the combined rotor of a small turbojet engine is an important component of a turbojet engine. When assembling the combined rotor in an existing turbojet engine, the turbine and the centrifugal impeller are often first interference-fitted onto the turbine shaft, and then a wrench is used to tighten the turbine fastening nut and the front nut onto the turbine shaft. However, when using a wrench to tighten the nut, due to the excessive tightening force, the turbine and the centrifugal impeller need to be pressed hard, but it is easy to crush the turbine blades and the centrifugal impeller blades. And before the combined rotor is qualified, it needs to go through repeated disassembly and assembly processes such as trial assembly and dynamic balancing. This process not only reduces the assembly efficiency of the combined rotor, but also damages the combined rotor blades, affecting the final service life and work efficiency of the product.

[0003] During the assembly and disassembly process of the whole machine, when assembling and disassembling the combined rotor assembly, the air intake casing assembly, the diffuser assembly, and the combustion chamber assembly, the turbine shaft is usually disassembled and assembled by manpower. The turbine shaft and the components will make rotational motion, and it cannot be guaranteed that the turbine shaft and the components are completely fixed.

[0004] Based on this, designing a turbojet engine combined rotor and whole machine assembly and disassembly tooling that is easy to assemble is the primary problem we urgently need to solve. Utility Model Content

[0005] The purpose of the utility model is to provide a tool for assembling and disassembling a combined rotor of a turbojet engine and a complete machine, which utilizes a support unit to fix and disassemble the combined rotor of the turbojet engine, and utilizes a positioning structure unit to disassemble the complete turbojet engine, thereby achieving complete fixation of the combined rotor of a small turbojet engine and various components, and facilitating easy removal of various locking nuts of the combined rotor during assembly and disassembly of the combined rotor and various components.

[0006] The purpose of the utility model is mainly achieved through the following technical solutions:

[0007] A turbojet engine combined rotor and complete machine assembly and disassembly tool, comprising a base plate, the base plate being provided with a support unit and a positioning structure unit, the support unit being used for supporting and fixing a turbine shaft of the turbojet engine combined rotor, the positioning structure unit being used for supporting the combined rotor when the turbojet engine is assembled and disassembled;

[0008] A combined rotor generally refers to a rotor assembly in a turbojet engine that partially or completely integrates the compressor and turbine. It can improve the overall efficiency and reliability of the engine by reducing the number of components and simplifying the structure. However, the combined rotor assembly and disassembly process is not easy to operate. The present application sets a base plate to provide installation space for many components and ensure the stability and balance of the device. A support unit is set on the base plate, and the support unit is used to disassemble and assemble the combined rotor of the turbojet engine.

[0009] Due to the differences in structure, weight, and disassembly and assembly methods between the combined rotor and the complete engine, and the possibility of rotational motion between the turbine shaft and the components during assembly and disassembly of the complete engine, the use of a support unit alone cannot guarantee the complete fixation of the turbine shaft and the components, and it is difficult to support the disassembly and assembly of the complete turbojet engine. Therefore, a positioning structure unit is set on the bottom plate, and the positioning structure unit is used to disassemble and assemble the complete turbojet engine. A disassembly and assembly tool completes the entire process of disassembly and assembly of the turbojet engine, simplifies the disassembly and assembly tools, and saves disassembly and assembly time.

[0010] The support unit and the positioning structure unit are separated from each other so as not to affect the normal disassembly and assembly process of the parts. In addition, the above structure can disassemble and assemble the whole machine and the combined rotor at the same time, thus speeding up the disassembly and assembly of multiple machines.

[0011] The support unit includes a support that provides a support point for the combined rotor turbine shaft;

[0012] The support unit provides support for the turbine shaft of the combined rotor by arranging a support.

[0013] The positioning structure comprises a positioning ring, the positioning ring is fixed on the bottom plate, and a concave positioning hole is provided on the positioning ring, and the positioning hole can fix and support the combined rotor.

[0014] Specifically, a positioning ring is provided on the positioning structure. The positioning ring provides a support point for the disassembly and assembly of the combined rotor during the assembly of the turbojet engine through the concave positioning hole. The turbine shaft of the combined rotor is clamped into the positioning hole to achieve rapid and accurate positioning of the combined rotor.

[0015] Furthermore, the positioning ring is covered with an auxiliary ring on the outside, and a cavity is formed between the auxiliary ring and the positioning ring. When the turbine shaft of the combined rotor is fixed in the positioning hole, the engine limiter matched with the turbine shaft is located in the cavity.

[0016] The positioning structure unit is also provided with an auxiliary ring, the auxiliary ring is covered on the outside of the positioning ring, and the accommodating cavity formed between the auxiliary ring and the positioning ring is used for high-strength support of the engine.

[0017] Furthermore, the support includes a support 1 and a support 2 for supporting different ends of the turbine shaft respectively, and the distance between the support 1 and the support 2 is adjustable;

[0018] The support unit is used to disassemble and assemble the combined rotor, and two supports are provided to support different ends of the turbine shaft, and to disassemble and assemble the components of the combined rotor on the turbine shaft. Compared with one support, the structure supported at both ends is more stable, and multiple support points will complicate the structure and operation.

[0019] The distance between the two supports is adjustable, and the distance between the supports can be flexibly adjusted according to the length of the turbine shaft.

[0020] Furthermore, the bottom of the support 1 is provided with a plurality of connection holes, and the plurality of connection holes are arranged along the direction of the connecting line of the support 1 and the support 2;

[0021] The bottom of the support 2 is provided with a plurality of mounting holes, and the plurality of mounting holes are arranged along the direction of the connecting line between the support 1 and the support 2.

[0022] Specifically, a plurality of connection holes are provided at the bottom of the support, and the position of the support is adjusted by connecting different connection holes, thereby adjusting the spacing between the supports.

[0023] Furthermore, a concave arc structure is provided on the top of the support 2.

[0024] The support comprises a base fixed to the bottom plate and a vertical support seat fixed on the base for supporting the turbine shaft. An inwardly concave arc structure is arranged on the top of the support seat for quickly positioning the combined rotor.

[0025] Furthermore, the top of the support one is provided with an inwardly concave arc structure, and an arched piece is provided above the support one, and the contact surfaces of the support one and the arched piece can be fitted with each other.

[0026] The top of the support is concave, and cooperates with the arched part above to form a clamp. The contact surfaces of the upper and lower parts of the clamp can be interlocked to facilitate close contact between the two, thereby achieving a tight constraint on the combined rotor turbine shaft and thus positioning the turbine shaft.

[0027] Furthermore, the two sides of the support 1 contacting the arch member are contact side A and contact side B, and the contact side A is provided with a split pin;

[0028] One side of the clamp is connected by a split pin, which can be quickly installed and automatically locked.

[0029] The contact B side is clamped with a quick clamp, and the quick clamp is fixed on the support one.

[0030] Use the quick clamp to clamp and release to fix or release the other side of the clamp, so as to quickly adjust the use status of the clamp.

[0031] The structure of the clamp can realize the rapid clamping of the turbine shaft.

[0032] Furthermore, the combination of the support 1 and the arched member is used as a clamp, and the inner diameter of the clamp is matched with the outer diameter of the turbine shaft.

[0033] The inner diameter of the clamp is matched to the outer diameter of the turbine shaft for fast clamping of the combined rotor.

[0034] Furthermore, felt is provided on the inner side of the clamp.

[0035] Felt is arranged on the inner section of the support and the clamp, and the elasticity and friction of the felt are utilized to prevent the turbine shaft from being damaged or slipping when the clamp clamps the turbine shaft.

[0036] In summary, compared with the prior art, the present invention has the following beneficial effects:

[0037] (1) The bottom plate is provided with the support unit for disassembling and assembling the turbojet engine combined rotor and the positioning structure unit for disassembling and assembling the turbojet engine as a whole; the assembly of the combined rotor inside the turbojet engine and the external whole machine is realized, the assembly tooling is simplified and the assembly speed is accelerated;

[0038] (2) The distance between the two supports provided by the support unit is adjustable, which is highly flexible, and the tops of the two supports are provided with a concave structure to adapt to the turbine shaft, thereby realizing rapid positioning of the turbine shaft;

[0039] (3) The positioning structure unit is provided with a positioning ring, an auxiliary ring is concentrically arranged outside the positioning ring, and the accommodating cavity between the auxiliary ring and the positioning ring is used to support the engine with high strength; a positioning ring is arranged inside the positioning structure unit, and a hexagonal groove is arranged in the center of the positioning ring to facilitate rapid and accurate positioning of the combined rotor. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] The drawings described herein are used to provide a further understanding of the embodiments of the present utility model, constitute a part of this application, and do not constitute a limitation of the embodiments of the present utility model. In the drawings:

[0041] Figure 1 A schematic diagram of the three-dimensional structure of this application;

[0042] Figure 2 This is an exploded view of the support 1 of this application;

[0043] The names corresponding to the accompanying drawings are: 1. base plate; 2. positioning ring; 3. positioning hole; 4. auxiliary ring; 5. support one; 6. arch piece; 7. felt; 8. quick clamp; 9. cotter pin; 10. connecting hole; 11. support two; 12. mounting hole; 13. lifting eye screw. DETAILED DESCRIPTION

[0044] In order to make the purpose, technical solutions and advantages of the utility model more clearly understood, the utility model is further described in detail below in conjunction with embodiments and drawings. The schematic implementation manner of the utility model and its description are only used to explain the utility model and are not intended to limit the utility model.

[0045] Example:

[0046] like Figure 1-2 As shown, a turbojet engine combined rotor and complete machine assembly and disassembly tool comprises a base plate 1, on which a support unit and a positioning structure unit are arranged, wherein the support unit is used for supporting and fixing the turbojet engine combined rotor, and the positioning structure unit is used for supporting the combined rotor when the turbojet engine is assembled and disassembled;

[0047] A combined rotor generally refers to a rotor assembly in a turbojet engine that partially or completely integrates the compressor and turbine. It can improve the overall efficiency and reliability of the engine by reducing the number of components and simplifying the structure. However, the combined rotor assembly and disassembly process is not easy to operate. The present application provides a base plate 1 to provide installation space for many components and ensure the stability and balance of the device. A support unit is provided on the base plate 1, and the support unit is used to disassemble and assemble the combined rotor of the turbojet engine.

[0048] Due to the differences in structure, weight, and disassembly and assembly methods between the combined rotor and the complete engine, and the fact that the turbine shaft and various components may make rotational movements during the assembly and disassembly of the complete engine, the use of a support unit alone cannot ensure that the turbine shaft and various components are completely fixed, and it is difficult to support the disassembly and assembly process of the complete turbojet engine. Therefore, a positioning structure unit is set on the bottom plate 1, and the positioning structure unit is used to disassemble and assemble the complete turbojet engine. A disassembly and assembly tool completes the entire process of disassembly and assembly of the turbojet engine, simplifies the disassembly and assembly tools, and saves disassembly and assembly time.

[0049] The support unit and the positioning structure unit are separated from each other so as not to affect the normal disassembly and assembly process of the parts. In addition, the above structure can disassemble and assemble the whole machine and the combined rotor at the same time, thus speeding up the disassembly and assembly of multiple machines.

[0050] As an implementable embodiment of the above scheme, eye screws 13 are evenly arranged on the edge of the base plate 1 to facilitate later lifting.

[0051] The support unit includes a support that provides a support point for the combined rotor turbine shaft;

[0052] The support unit supports the turbine shaft of the combined rotor by providing a support.

[0053] The positioning structure comprises a positioning ring 2, and the positioning ring 2 is fixed on the bottom plate 1. The positioning ring 2 is provided with a concave positioning hole 3, and the positioning hole 3 can fix and support the combined rotor.

[0054] Specifically, a positioning ring 2 is provided on the positioning structure, and the positioning ring 2 realizes rapid and accurate positioning of the combined rotor through the concave positioning hole 3.

[0055] When the above solution is implemented, the shape and size of the positioning hole 3 are determined according to the shape and size of the contact point with the combined rotor.

[0056] As a feasible implementation of the above scheme, the positioning hole 3 is a regular hexagonal concave hole.

[0057] Furthermore, the outside of the positioning ring 2 is covered with an auxiliary ring 4, and a cavity is formed between the auxiliary ring 4 and the positioning ring 2. When the turbine shaft of the combined rotor is fixed in the positioning hole 3, the engine limiter matching the turbine shaft is located in the cavity.

[0058] The positioning structure unit is further provided with an auxiliary ring 4, and the auxiliary ring 4 is covered on the outside of the positioning ring 2. The accommodating cavity between the auxiliary ring 4 and the positioning ring 2 is used for high-strength support of the engine.

[0059] When the above solution is implemented, the shape and size of the opening on the auxiliary ring 4 are the same as those of the positioning hole 3 .

[0060] Furthermore, the support includes a support 1 5 and a support 2 11 for supporting different ends of the turbine shaft respectively, and the distance between the support 1 5 and the support 2 11 is adjustable;

[0061] The support unit is used to disassemble and assemble the combined rotor, and two supports are provided to support both ends of the turbine shaft, and to disassemble and assemble the combined rotor assembly on the turbine shaft. Compared with one support, the structure supported at both ends is more stable, and multiple support points will complicate the structure and operation.

[0062] The distance between the two supports is adjustable, and the distance between the supports can be flexibly adjusted according to the length of the turbine shaft.

[0063] Furthermore, the bottom of the support 1 5 is provided with a plurality of connection holes 10, and the plurality of connection holes 10 are arranged along the direction of the line connecting the support 1 5 and the support 2 11;

[0064] The bottom of the support 2 11 is provided with a plurality of mounting holes 12 , and the plurality of mounting holes 12 are arranged along the direction of the line connecting the support 1 5 and the support 2 11 .

[0065] Specifically, a plurality of connection holes 10 are provided at the bottom of the support, and the position of the support is adjusted by connecting different connection holes 10, thereby adjusting the distance between the supports.

[0066] As a specific implementation of the above, three rows of pin holes are provided on the support along the direction of the line connecting the support 1 5 and the support 2 11, with two pin holes in each row.

[0067] As an alternative to the above specific embodiment, the above pin connection can be replaced by a threaded connection, or other detachable fixed connection methods.

[0068] When the above specific implementation is used, a flat washer is arranged at the pin hole, and then a pin or a screw is installed.

[0069] Furthermore, the top of the support 2 11 is provided with a concave arc structure.

[0070] The support comprises a base fixed to the bottom plate 1 and a vertical support seat fixed on the base for supporting the turbine shaft. An inwardly concave arc structure is arranged on the top of the support seat for quickly positioning the combined rotor.

[0071] As a specific implementation of the above, the arc structure is a U-shaped groove structure, a semicircular arc structure, etc.

[0072] Furthermore, the top of the support 1 5 is provided with an inwardly concave arc structure, and an arched member 6 is provided above the support 1 5 , and the contact surfaces of the support 1 5 and the arched member 6 can be interlocked.

[0073] The top of the support 5 is concave, and cooperates with the arched part 6 above to form a clamp. The contact surfaces of the upper and lower parts of the clamp can be interlocked to facilitate close contact between the two, thereby achieving a tight constraint on the combined rotor turbine shaft and thus positioning the turbine shaft.

[0074] Furthermore, the two sides where the support 1 5 contacts the arch 6 are contact side A and contact side B, and the contact side A is provided with a split pin 9;

[0075] One side of the clamp is connected via the split pin 9, which can be quickly installed and automatically locked.

[0076] The contact B side is clamped with a quick clamp 8, and the quick clamp 8 is fixed on the support 1 5.

[0077] The clamping and loosening of the quick clamp 8 is used to fix or loosen one side of the clamp, so as to quickly adjust the use state of the clamp.

[0078] The structure of the clamp can realize the rapid clamping of the turbine shaft.

[0079] When the above solution is implemented, the fixing method of the contact A side and the contact B side can be replaced by a detachable connection and fixing method such as a threaded connection, a snap connection, etc.

[0080] Furthermore, the combination of the support 1 5 and the arched member 6 is a clamp, and the inner diameter of the clamp is matched with the outer diameter of the turbine shaft.

[0081] The inner diameter of the clamp is matched to the outer diameter of the turbine shaft for fast clamping of the combined rotor.

[0082] When the above scheme is implemented, the inner wall structure formed by the combination of the support 5 and the arch member 6 is determined according to the shape and size of the turbine shaft of the turbojet engine combined rotor to be assembled.

[0083] Furthermore, a felt 7 is provided on the inner side of the clamp.

[0084] A felt 7 is provided on the inner tangent surface of the support 5 and the clamp, and the elasticity and friction of the felt 7 are utilized to prevent the turbine shaft from being damaged or slipping when the clamp clamps the turbine shaft.

[0085] As a specific implementation of a turbojet engine combined rotor and complete machine assembly and disassembly tool, it includes:

[0086] Bottom plate 1;

[0087] A support unit is located at the left end of the base plate 1; the support unit comprises a support front end capable of supporting and locking the combined rotor turbine shaft and a support rear end capable of supporting and fixing the combined rotor turbine shaft;

[0088] The support front end includes a support 5, a plurality of connection holes 10 are provided at the bottom of the support 5, and the support 5 is fixed to the base plate 1 by means of hexagon socket cylindrical head screws; the top of the support 5 is detachably connected and locked with an arch 6 by means of a cotter pin 9, and a quick clamp 8 is connected to the opposite side of the cotter pin 9 on the support by means of a hexagon socket cylindrical head screw, and the quick clamp 8 can clamp the arch 6 and the support; the arch 6 and the opposite side of the support are both provided with a semicircular concave structure, and the arch 6 and the support are combined to form a hoop structure, and the inner diameter of the hoop is adapted to the outer diameter of the turbine shaft; the inner side of the hoop is provided with a felt 7;

[0089] The support rear end is separated from the support front end; the support rear end includes a support 2 11, the top of the support 2 11 is provided with a concave U-shaped groove, the bottom of the support 2 11 is provided with a plurality of connecting holes 10, and the plurality of connecting holes 10 are arranged along the direction of the line connecting the support 1 5 and the support 2 11; the support 2 11 is fixed to the base plate 1 by a hexagon socket head screw;

[0090] A positioning structure unit, the positioning structure unit is located at the right end of the bottom plate 1, and the positioning structure unit includes a positioning ring 2 and an auxiliary ring 4 covering the outside of the positioning ring 2;

[0091] The positioning ring 2 is fixed to the bottom plate 1 by using a hexagon socket head screw. The positioning ring 2 is a shell structure with an opening on a circular surface, the opening faces upward, and a hexagonal groove is provided at the center of the top surface of the positioning ring 2;

[0092] The auxiliary ring 4 and the positioning ring 2 form a cavity, and the cavity is used to accommodate and support the engine with high strength.

[0093] The above-mentioned disassembly and assembly tooling for the combined rotor of the turbojet engine and the complete machine is used when installing the combined rotor:

[0094] First, assemble the tooling parts on the workbench, put one end of the turbine shaft into the U-shaped groove of the support 11, clamp the other end of the turbine shaft with the clamp structure formed by the arch member 6 and the support, assemble the rear bearing (angular contact ball bearing with an external bearing adapter) on the turbine shaft, assemble the turbine to the turbine shaft, and tighten it with the turbine fastening nut.

[0095] Secondly, loosen the clamp, turn the direction of the turbine shaft, put the turbine fastening nut in the U-shaped groove of the support 11, clamp the other end of the turbine shaft with the clamp, assemble the front bearing (angular contact ball bearing) to the turbine shaft, then install the centrifugal impeller to the shaft, and finally tighten the front nut to complete the combined rotor assembly.

[0096] When the above-mentioned disassembly and assembly tooling for the turbojet engine combined rotor and the complete machine is used to disassemble the combined rotor: the disassembly is carried out in the reverse order of the assembly order of the combined rotor.

[0097] When the above-mentioned turbojet engine combined rotor and complete machine disassembly and assembly tool is used for complete machine assembly:

[0098] Place the turbine shaft with the turbine assembled vertically into the positioning hole 3 of the positioning ring 2, assemble the combustion chamber turbine guide assembly and the diffuser assembly, then install the centrifugal impeller on the shaft, tighten the front nut, and finally assemble the intake casing assembly to complete the whole machine assembly process. Disassemble according to the reverse steps of the above installation process. The above disassembly and assembly process needs to be repeated until the whole machine product is installed qualifiedly.

[0099] The turbojet engine combined rotor and complete machine assembly and disassembly tool described in the present application has the following functions:

[0100] The utility model can realize complete fixation of a combined rotor and various components of a small turbojet engine, and is convenient for ensuring easy removal of various locking nuts of the combined rotor during the disassembly and assembly process of the combined rotor and various components.

[0101] The support unit of the utility model adopts a new lightweight structural design, which has the advantages of reliable functional structure, convenient disassembly and adjustability, etc. It solves the problems of complex structure, high cost and need for fixed placement, improves assembly efficiency and reduces use cost.

[0102] The positioning structural unit of the utility model uses a special clamp for rapid clamping positioning and high-strength thin-wall support positioning, and simultaneously ensures precision and strength.

[0103] The utility model utilizes the limited platform position to meet the multi-station operation space, thereby greatly improving the utilization rate. In terms of control, the axial movable positioning installation and debugging can be used according to the actual situation, and the production efficiency can be improved by flexible use. The device with such a structure can avoid installation, debugging, maintenance, etc. in special circumstances such as designated sites, and can quickly and easily meet the multi-station installation and disassembly tasks, shorten the installation time and improve production efficiency. It also has the advantages of low cost, convenient operation, and reliable quality.

[0104] The specific implementation methods described above further illustrate the purpose, technical solutions and beneficial effects of the utility model in detail. It should be understood that the above description is only the specific implementation method of the utility model and is not used to limit the protection scope of the utility model. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the utility model should be included in the protection scope of the utility model.

Claims

1. A turbojet engine combined rotor and complete machine assembly and disassembly tool, characterized by: It comprises a base plate (1), on which a support unit and a positioning structure unit are arranged, wherein the support unit is used to support and fix the turbine shaft of the combined rotor of the turbojet engine, and the positioning structure unit is used to support the combined rotor when the turbojet engine is disassembled and assembled; The support unit includes a support that provides a support point for the combined rotor turbine shaft; The positioning structure comprises a positioning ring (2), wherein the positioning ring (2) is fixed on the base plate (1), and a concave positioning hole (3) is provided on the positioning ring (2), wherein the positioning hole (3) can fix and support the combined rotor.

2. A turbojet engine combined rotor and complete machine assembly and disassembly tool as claimed in claim 1, characterized in that: The positioning ring (2) is covered with an auxiliary ring (4) on the outside, and a cavity is formed between the auxiliary ring (4) and the positioning ring (2). When the turbine shaft of the combined rotor is fixed in the positioning hole (3), the engine limiter matching the turbine shaft is located in the cavity.

3. A turbojet engine combined rotor and complete machine assembly and disassembly tool as claimed in claim 1 or 2, characterized in that: The support comprises a support 1 (5) and a support 2 (11) for supporting different ends of the turbine shaft respectively, and the distance between the support 1 (5) and the support 2 (11) is adjustable.

4. A turbojet engine combined rotor and complete machine assembly and disassembly tool as claimed in claim 3, characterized in that: The bottom of the support 1 (5) is provided with a plurality of connection holes (10), and the plurality of connection holes (10) are arranged along the direction of the connecting line between the support 1 (5) and the support 2; The bottom of the support 2 (11) is provided with a plurality of mounting holes (12), and the plurality of mounting holes (12) are arranged along the direction of the connecting line between the support 1 (5) and the support 2.

5. A turbojet engine combined rotor and complete machine assembly and disassembly tool as claimed in claim 3, characterized in that: The top of the support 2 (11) is provided with a concave arc structure.

6. A turbojet engine combined rotor and complete machine assembly and disassembly tool as claimed in claim 3, characterized in that: The top of the support 1 (5) is provided with an inwardly concave arc structure, and an arched member (6) is provided above the support 1 (5), and the contact surfaces of the support 1 (5) and the arched member (6) can be interlocked.

7. A turbojet engine combined rotor and complete machine assembly and disassembly tool as claimed in claim 6, characterized in that: The two sides of the support (5) in contact with the arch member (6) are contact side A and contact side B, and the contact side A is provided with a split pin (9); The contact B side is clamped with a quick clamp (8), and the quick clamp (8) is fixed on the support one (5).

8. A turbojet engine combined rotor and complete machine assembly and disassembly tool as claimed in claim 7, characterized in that: The combination of the support 1 (5) and the arched member (6) forms a clamp, and the inner diameter of the clamp is matched to the outer diameter of the turbine shaft.

9. A turbojet engine combined rotor and complete machine assembly and disassembly tool as claimed in claim 8, characterized in that: A felt (7) is arranged on the inner side of the clamp.

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