Tool for disassembling and assembling locking nut of turbine disc of aero-engine

Abstract

The utility model provides a tool for dismounting and mounting a turbine disc locking nut of an aero-engine, and belongs to the technical field of dismounting and mounting of gas turbine aero-engines. Comprising a fixing sleeve, a stretching fixing assembly and a supporting sleeve, the fixing sleeve comprises a first fixing ring and a fixing column, one end of the fixing column is fixedly connected with the first fixing ring, the other end of the fixing column is provided with a threaded hole, the threaded hole is used for being in threaded connection with a turbine shaft, and the stretching fixing assembly is in an annular shape; the stretching fixing assembly and the supporting sleeve are sequentially arranged on the outer surface of the fixing column in a sleeving mode. The tool is in threaded connection with the outer side of the turbine shaft, then the fixing assembly exerts certain axial pulling force, the turbine shaft generates a certain amount of reversible elastic deformation, the local diameter is reduced, matching between the locking nut and the turbine shaft is loosened, and the turbine shaft is locked. Therefore, the tightening nut can be shifted, disassembled and assembled without extra tools such as a torque wrench and the like by using a common screwdriver, and irreversible damage to related parts is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of disassembly and assembly of gas turbine aircraft engines, in particular to a tool for disassembly and assembly of locking nuts of turbine disks of aircraft engines. Background Art

[0002] The turbine system of a turbofan aircraft engine consists of a turbine disc, turbine blades, and a turbine shaft. The turbine blades are typically mounted in a mortise and tenon groove on the disc, while the disc is connected to the shaft via a spline to transmit torque. A lock nut is mounted on the end of the shaft to secure the disc in place and prevent axial displacement or dislodging. The disc typically rotates at speeds exceeding 20,000 rpm, generating significant torque and axial forces between the rotor shaft and the disc. To prevent the disc from loosening or dislodging, a high-strength lock nut is required. High loads and torque are applied to the lock nut to secure the disc. The lock nut is installed by threading it into a designated section of the turbine shaft after the components are properly aligned on the shaft. The threading distance is proportional to the required torque. When the lock nut is threaded into the end of the thread (i.e., when assembly is complete), it is fully engaged. The friction between the lock nut and the threads increases with increasing pressure, resulting in a tighter connection. When the locking nut is rotated to tightly engage with the threaded section, the threaded portion of the locking nut generates friction with the threaded portion on the turbine shaft, thereby making the connection between the thread and the nut stronger.

[0003] Because the turbine disk locking nut fits very tightly against the turbine disk, the torque provided by using an ordinary wrench to disassemble and assemble the locking nut is limited. The locking nut often gets stuck on the rotor shaft and cannot be disassembled. Wrenches with extended lever arms are generally not usable due to the small space in the turbine system, or they may easily damage the turbine disk and turbine shaft during use. At the same time, both types of wrenches require applying extremely high torque, which can easily cause irreversible damage to related parts. Utility Model Content

[0004] The technical problem to be solved by the utility model is to provide a tool for disassembling and assembling the locking nut of the turbine disk of an aircraft engine so as to solve the problems that the existing turbine disk locking nut is difficult to disassemble using an ordinary wrench or a wrench with an extended lever arm, and is easy to damage the parts and the locking nut itself.

[0005] In order to solve the above technical problems, the present invention provides the following technical solutions:

[0006] A tool for disassembling and assembling a locking nut for an aircraft engine turbine disk, comprising a fixing sleeve, a stretching fixing assembly and a supporting sleeve, wherein the fixing sleeve comprises a first fixing ring and a fixing column, one end of the fixing column is fixedly connected to the first fixing ring, and the other end of the fixing column is provided with a threaded hole, and the threaded hole is used for threaded connection with the turbine shaft, the stretching fixing assembly is ring-shaped, and the stretching fixing assembly and the supporting sleeve are sequentially sleeved on the outer surface of the fixing column, one side of the support sleeve is used for contacting the stretching fixing assembly, and the other side of the support sleeve is used for contacting the turbine disk, the stretching fixing assembly is used for providing thrust to the fixing sleeve and the supporting sleeve, and a notch is provided on the front of the support sleeve, and the notch is used for rotating the locking nut.

[0007] Preferably, the left side of the threaded hole passes through a first fixing ring, and the diameter of the first fixing ring is larger than the diameter of the fixing column.

[0008] Preferably, the outer surface of the first fixing ring is provided with a plurality of circular holes.

[0009] Preferably, the stretching and fixing assembly includes an annular hydraulic cylinder body with a chamber, an annular piston slidably mounted inside the annular hydraulic cylinder body, and a telescopic cylinder connected to the annular piston. A liquid inlet pipe is mounted on the annular hydraulic cylinder body.

[0010] Preferably, a first through hole is formed in the middle of the annular hydraulic cylinder body, and a second through hole is formed in the middle of the support sleeve. The diameters of the first through hole and the second through hole are the same as the diameter of the fixing column.

[0011] Preferably, the second through hole includes a first cavity on the left and a second cavity on the right, and the diameter of the second cavity is larger than the diameter of the first cavity.

[0012] Preferably, the notch is a T-shaped notch, and the notch corresponds to the position of the locking nut.

[0013] Preferably, a mounting cavity is provided in the middle of the support sleeve, a hollow ratchet wrench head is rotatably connected to the interior of the mounting cavity, a handle is installed on the outer surface of the hollow ratchet wrench head, and the handle passes through the notch.

[0014] Preferably, the support sleeve includes a first support column and a second support column, the first cavity is provided on the first support column, the second cavity and the notch are both provided on the second support column, and the first support column is threadedly connected to the second support column.

[0015] Preferably, a second fixing ring is fixedly connected to the inner wall of the second cavity, a first thrust bearing is installed between the left side of the hollow ratchet wrench head and the first support column, and a second thrust bearing is installed between the right side of the hollow ratchet wrench head and the second fixing ring.

[0016] Compared with the prior art, the present invention has at least the following beneficial effects:

[0017] In the above scheme, a hollow ratchet wrench head is installed inside the support sleeve. After installation, the hollow ratchet wrench head is set on the locking nut. The hollow ratchet wrench head will not affect the connection between the threaded hole on the right side of the fixing column and the outer thread on the turbine shaft. It is only necessary to repeatedly turn the handle to drive the hollow ratchet wrench head to rotate. The locking nut can be quickly installed or removed through the ratchet structure inside the hollow ratchet wrench head.

[0018] In the above scheme, the stretching fixing assembly and the support sleeve are sequentially sleeved on the outer surface of the fixing column, and then the tool is sleeved on the turbine shaft and connected to the outer thread on the turbine shaft. Then, the stretching fixing assembly applies a certain axial tension to cause the turbine shaft to produce a certain amount of reversible elastic deformation, the local diameter is reduced, and the fit between the locking nut and the turbine shaft is loosened. Therefore, no additional tools such as torque wrenches are required, and the locking nut can be moved and disassembled using an ordinary screwdriver, ensuring that the disassembly and installation of the locking nut can be completed by manpower alone, avoiding irreversible damage to related parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings, which are incorporated herein and constitute a part of the specification, illustrate embodiments of the present disclosure and, together with the description, further serve to explain the principles of the present disclosure and to enable one skilled in the relevant art to make and use the present disclosure.

[0020] Figure 1 This is a schematic diagram of the disassembly structure of the locking nut of the turbine disk of an aircraft engine;

[0021] Figure 2 This is a schematic diagram of the installation structure of the locking nut of the turbine disk of an aircraft engine;

[0022] Figure 3 This is a schematic diagram of the structure of the tooling for disassembling and assembling the locking nut of the turbine disk of an aircraft engine before installation;

[0023] Figure 4 This is a three-dimensional view of the tooling used for disassembling and assembling the locking nut of the turbine disk of an aircraft engine after installation;

[0024] Figure 5 This is a schematic diagram of the exploded structure of the left side view of the tool used for disassembling and assembling the locking nut of the turbine disk of an aircraft engine;

[0025] Figure 6 This is a schematic diagram of the exploded structure of the right side view of the tool used for disassembling and assembling the locking nut of the turbine disk of an aircraft engine;

[0026] Figure 7 A schematic cross-sectional view of a support sleeve of a tool for disassembling and assembling a locking nut for an aircraft engine turbine disk;

[0027] Figure 8 This is a schematic diagram of the structure of a hollow ratchet wrench head installed inside a tool for disassembling and assembling a locking nut of an aircraft engine turbine disk;

[0028] Figure 9 Tooling for disassembling and assembling the locking nut of the turbine disk of an aircraft engine Figure 8 Schematic diagram of the cross-section structure.

[0029] [reference numerals]

[0030] 1. Fixing sleeve; 2. Tensile fixing assembly; 3. Support sleeve; 4. Fixing column; 5. Threaded hole; 6. Notch; 7. First fixing ring; 8. Round hole; 9. Annular hydraulic cylinder; 10. Telescopic cylinder; 11. Locking nut; 12. Turbine disk; 13. Turbine shaft; 14. Outer thread; 15. Inner thread; 16. Second through hole; 17. First cavity; 18. Second cavity; 19. Liquid inlet pipe; 20. First through hole; 301. Mounting cavity; 302. Hollow ratchet wrench head; 303. Handle; 304. First support column; 305. Second support column; 306. Second fixing ring; 307. First thrust bearing; 308. Second thrust bearing.

[0031] As shown in the figure, in order to clearly implement the structure of the embodiment of the present invention, specific structures and devices are marked in the figure, but this is only for illustrative purposes and is not intended to limit the present invention to the specific structure, device and environment. According to specific needs, ordinary technicians in this field can adjust or modify these devices and environments, and the adjustments or modifications made are still included in the scope of the appended claims. DETAILED DESCRIPTION

[0032] The following describes in detail a tool for disassembling and assembling a locking nut for an aircraft engine turbine disk, provided by the present invention, in conjunction with the accompanying drawings and specific embodiments. It is also noted that, for the sake of completeness, the following embodiments are best and preferred embodiments, and those skilled in the art may employ alternative implementations for known technologies. Furthermore, the accompanying drawings are intended only to provide a more detailed description of the embodiments and are not intended to limit the present invention.

[0033] It should be noted that references in the specification to "one embodiment," "an embodiment," "an exemplary embodiment," "some embodiments," etc. indicate that the described embodiments may include specific features, structures, or characteristics, but not every embodiment necessarily includes such specific features, structures, or characteristics. In addition, when specific features, structures, or characteristics are described in conjunction with an embodiment, it is within the knowledge of persons skilled in the relevant art to implement such features, structures, or characteristics in conjunction with other embodiments (whether or not explicitly described).

[0034] In general, terms can be understood, at least in part, from their use in context. For example, depending at least in part on the context, the term "one or more" as used herein can be used to describe any feature, structure, or characteristic in the singular sense, or can be used to describe a combination of features, structures, or characteristics in the plural sense. Additionally, the term "based on" can be understood as not necessarily intended to convey an exclusive set of factors, but can instead, depending at least in part on the context, allow for the presence of other factors that are not necessarily explicitly described.

[0035] It will be understood that the meanings of “on,” “over,” and “above” in this disclosure should be interpreted in the broadest manner, such that “on” means not only “directly on” something, but also includes being “on” something with intervening features or layers, and “on” or “over” means not only “on” or “above” something, but also includes being “on” or “above” something with no intervening features or layers.

[0036] Additionally, spatially relative terms such as "below," "beneath," "lower," "above," and "upper" may be used herein for descriptive convenience to describe the relationship of one element or feature to another element or features, as illustrated in the accompanying drawings. Spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the accompanying drawings. The device may be oriented in other ways, and the spatially relative descriptors used herein should be similarly interpreted accordingly.

[0037] Example 1

[0038] like Figure 1-7 As shown, the embodiment of the present invention provides a tool for disassembling and assembling the locking nut of the turbine disk of an aircraft engine, such as Figure 1 and Figure 2As shown, a locking nut 11 for removing the turbine disk 12 from the turbine shaft 13 is provided. An inner thread 15 is provided on the turbine shaft 13 to cooperate with the locking nut 11, and an outer thread 14 is provided on the outside. The tool comprises a fixing sleeve 1, a stretching fixing assembly 2 and a support sleeve 3. The fixing sleeve 1 comprises a first fixing ring 7 and a fixing column 4. One end of the fixing column 4 is fixedly connected to the first fixing ring 7, and the other end of the fixing column 4 is provided with a threaded hole 5. The threaded hole 5 is used to be threadedly connected to the turbine shaft 13. The stretching fixing assembly 2 is ring-shaped. The stretching fixing assembly 2 and the support sleeve 3 are sequentially sleeved on the outer surface of the fixing column 4. One side of the support sleeve 3 is used to contact the stretching fixing assembly 2, and the other side of the support sleeve 3 is used to contact the turbine disk 12. The stretching fixing assembly 2 is used to provide thrust to the fixing sleeve 1 and the support sleeve 3. A notch 6 is provided on the front of the support sleeve 3. The notch 6 is used to rotate the locking nut 11. During installation, the notch 6 can be used to facilitate the subsequent disassembly or installation of a wrench to loosen or tighten the locking nut 11.

[0039] like Figure 3 and Figure 5 As shown, in this embodiment, the left side of the threaded hole 5 passes through the first fixing ring 7 , and the diameter of the first fixing ring 7 is larger than the diameter of the fixing column 4 , so that the right side of the threaded hole 5 can be connected to the outer thread 14 on the turbine shaft 13 .

[0040] like Figure 4 and Figure 6 As shown, in this embodiment, a circular hole 8 is opened on the outer surface of the first fixing ring 7. There are multiple circular holes 8, preferably six. When in use, a tool can be inserted into the circular hole 8 to better rotate the first fixing ring 7.

[0041] like Figure 5 and Figure 6 As shown, in this embodiment, the stretching and fixing assembly 2 includes an annular hydraulic cylinder body 9 with a chamber, an annular piston slidably installed inside the annular hydraulic cylinder body 9, and a telescopic cylinder 10 connected to the annular piston. A liquid inlet pipe 19 is installed on the annular hydraulic cylinder body 9.

[0042] The outer shape of the stretching and fixing component 2 is composed of two coaxially connected cylinders of different sizes, wherein the diameter of the telescopic cylinder 10 is slightly smaller than the inner diameter of the annular hydraulic cylinder body 9, and can be inserted into the interior of the annular hydraulic cylinder body 9 and connected to the annular movable body and slide. Its moving stroke should generally be about 8-13 mm. When in use, the liquid inlet pipe 19 can be connected to the external hydraulic pump oil pipe for pressurization. Generally, the pressure value is determined according to the cross-section and material of the turbine shaft 13 to ensure that the maximum stress of the turbine shaft 13 is within the elastic limit. The hydraulic pump can be an ordinary industrial hydraulic pump commonly used in the domestic market. Usually, under a tensile force of no more than 40 tons, the metal of the turbine shaft 13 undergoes reversible elastic deformation, and the locking nut 11 can be safely disassembled or installed, and the turbine shaft 13 and the turbine disk 12 will not be damaged.

[0043] like Figure 3 、 Figure 5 and Figure 6 As shown, in this embodiment, a first through hole 20 is opened in the middle of the annular hydraulic cylinder body 9, and a second through hole 16 is opened in the middle of the support sleeve 3. The diameters of the first through hole 20 and the second through hole 16 are the same as the diameter of the fixing column 4.

[0044] After the tooling is put on the turbine shaft 13 , the side of the support sleeve 3 with the T-shaped notch 6 is pressed against the turbine disk 12 , so that the fixing sleeve 1 , the stretching fixing assembly 2 , the support sleeve 3 and the turbine shaft 13 are coaxial.

[0045] like Figure 6 and Figure 7 As shown, in this embodiment, the second through hole 16 includes a first cavity 17 on the left and a second cavity 18 on the right. The diameter of the second cavity 18 is larger than the diameter of the first cavity 17. In this way, after installation, the locking nut 11 is located in the second cavity 18 without affecting subsequent disassembly.

[0046] like Figure 5 and Figure 6 As shown, in this embodiment, the notch 6 is a T-shaped notch, and the position of the notch 6 corresponds to that of the locking nut 11 .

[0047] Example 2

[0048] The difference from the first embodiment is that although the notch 6 in the first embodiment is too large, it will facilitate the disassembly and assembly of the locking nut 11, but it will reduce the support strength of the support sleeve 3. In order to increase the disassembly and assembly speed of the locking nut 11, it is necessary to avoid making the notch 6 too large. Figure 8 and Figure 9As shown, in this embodiment, a mounting cavity 301 is provided in the middle of the support sleeve 3, and a hollow ratchet wrench head 302 is rotatably connected to the interior of the mounting cavity 301. A handle 303 is installed on the outer surface of the hollow ratchet wrench head 302, and the handle 303 passes through the notch 6. The support sleeve 3 includes a first support column 304 and a second support column 305. The first cavity 17 is provided on the first support column 304, and the second cavity 18 and the notch 6 are both provided on the second support column 305. The first support column 304 is threadedly connected to the second support column 305, and a second fixing ring 306 is fixedly connected to the inner wall of the second cavity 18. A first thrust bearing 307 is installed between the left side of the hollow ratchet wrench head 302 and the first support column 304, and a second thrust bearing 308 is installed between the right side of the hollow ratchet wrench head 302 and the second fixing ring 306;

[0049] After installation, the hollow ratchet wrench head 302 is sleeved on the locking nut 11. The hollow ratchet wrench head 302 will not affect the connection between the threaded hole 5 on the right side of the fixing column 4 and the outer thread 14 on the turbine shaft 13. When disassembling, it is only necessary to repeatedly rotate the handle 303 to drive the hollow ratchet wrench head 302 to rotate. The locking nut 11 can be quickly installed or removed through the ratchet structure inside the hollow ratchet wrench head 302, and the first thrust bearing 307 and the second thrust bearing 308 are provided for support, and the pressure on the left side of the support sleeve 3 is transmitted to the right side. The gap 6 can be opened larger, so that the handle 303 has more room for movement, the speed of installation of the locking nut 11 is increased, and excessive thrust of the stretching fixing component 2 is avoided, which causes the support sleeve 3 to be deformed, and the use effect is better.

[0050] The technical solution provided by the present invention is that the various parts on the turbine shaft 13 have been Figure 2 and Figure 4As shown, the locking nut 11 is fixed to the inner thread 15 on the turbine shaft 13 to lock the turbine disc 12. When disassembling, first put the stretch fixing assembly 2 and the support sleeve 3 on the outer surface of the fixing column 4 in sequence, and then put the tool on the turbine shaft 13. The side with the T-shaped notch 6 is close to the turbine disc 12 and the two are coaxial until the right side of the threaded hole 5 is connected to the outer thread 14 on the turbine shaft 13. The transverse notch 6 in the T-shaped notch 6 faces the locking nut 11 on the turbine shaft 13. Since the stretch fixing assembly 2 is located on the support Between the sleeve 3 and the first fixed ring 7, the liquid inlet pipe 19 can be connected to the external hydraulic pump oil pipe. At this time, the hydraulic pump is turned on to start pressurizing. After the pressurization, the annular piston inside the annular hydraulic cylinder body 9 drives the telescopic cylinder 10 to start lifting under the action of liquid pressure. Due to the obstruction of the left first fixed ring 7 and the right support sleeve 3, the telescopic cylinder 10 will generate an inward thrust on the turbine disc 12. At the same time, the annular hydraulic cylinder body 9 will push the first fixed ring 7, the fixed column 4 and the turbine shaft 13 to move outward, generating an outward pulling force, thereby causing the turbine The inner thread 15 of the shaft 13 produces reversible elastic deformation, which reduces its diameter. The thinner turbine shaft 13 makes the tightening friction between the lock nut 11 and the threads on the turbine shaft 13 basically disappear, and the fit between the inner thread 15 and the lock nut 11 and the turbine disk 12 is reduced. At this time, the lock nut 11 can be removed by using a wrench through the T-notch 6. Then the hydraulic pump pressure can be reduced to zero, the entire set of tooling can be disassembled, the lock nut 11 is removed, and then the various parts on the turbine shaft 13 can be taken out one by one to complete the disassembly of the turbine system. At the same time, through experiments, it was found that when the hydraulic pump reaches the predetermined pressure, the locking nut 11 can be removed by hand without even loosening it with a wrench. Similarly, according to the above steps, the turbine shaft 13 is first stretched, and then the locking nut 11 is tightened and easily screwed in a certain number of turns along the thread direction to make it fit with the turbine disk 12. Then, the pressure in the hydraulic pump is released, so that the turbine shaft 13 returns to its original shape by relying on its own elasticity, and the installation of the locking nut 11 can be completed, so that the locking nut 11 and the turbine disk 12 fit better and are firmly installed together.

[0051] This invention encompasses any alternatives, modifications, equivalents, and solutions that do not depart from the spirit and scope of this invention. To provide a thorough understanding of this invention, specific details are described in detail in the following preferred embodiments of this invention, but those skilled in the art will be able to fully understand this invention without these detailed descriptions. Furthermore, to avoid unnecessary confusion regarding the essence of this invention, well-known methods, processes, procedures, components, and circuits are not described in detail.

[0052] Those skilled in the art will understand that all or part of the steps in the above-mentioned embodiment method can be completed by instructing the relevant hardware through a program, and the program can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc.

[0053] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as within the scope of protection of the present invention.

Claims

1. A tool for disassembling and assembling the locking nut of an aircraft engine turbine disk, characterized in that: The invention comprises a fixing sleeve (1), a stretch fixing assembly (2) and a support sleeve (3); the fixing sleeve (1) comprises a first fixing ring (7) and a fixing column (4); one end of the fixing column (4) is fixedly connected to the first fixing ring (7); the other end of the fixing column (4) is provided with a threaded hole (5); the threaded hole (5) is used for threaded connection with a turbine shaft (13); the stretch fixing assembly (2) is ring-shaped; the stretch fixing assembly (2) and the support sleeve (3) are sequentially sleeved on the outer surface of the fixing column (4); one side of the support sleeve (3) is used for contacting the stretch fixing assembly (2); the other side of the support sleeve (3) is used for contacting the turbine disk (12); the stretch fixing assembly (2) is used for providing thrust to the fixing sleeve (1) and the support sleeve (3); the front surface of the support sleeve (3) is provided with a notch (6); the notch (6) is used for rotating a locking nut (11).

2. The tool for disassembling and assembling the locking nut of the turbine disk of an aircraft engine according to claim 1, characterized in that: The left side of the threaded hole (5) passes through a first fixing ring (7), and the diameter of the first fixing ring (7) is larger than the diameter of the fixing column (4).

3. The tool for disassembling and assembling the locking nut of the turbine disk of an aircraft engine according to claim 2, characterized in that: The outer surface of the first fixing ring (7) is provided with a circular hole (8), and the number of the circular holes (8) is multiple.

4. The tool for disassembling and assembling the locking nut of the turbine disk of an aircraft engine according to claim 3, characterized in that: The stretching and fixing assembly (2) comprises an annular hydraulic cylinder body (9) with a chamber, an annular piston slidably mounted inside the annular hydraulic cylinder body (9), and a telescopic cylinder (10) connected to the annular piston. A liquid inlet pipe (19) is mounted on the annular hydraulic cylinder body (9).

5. The tool for disassembling and assembling the locking nut of the turbine disk of an aircraft engine according to claim 4, characterized in that: A first through hole (20) is provided in the middle of the annular hydraulic cylinder body (9), and a second through hole (16) is provided in the middle of the support sleeve (3). The diameters of the first through hole (20) and the second through hole (16) are the same as the diameter of the fixing column (4).

6. The tool for disassembling and assembling the locking nut of the turbine disk of an aircraft engine according to claim 5, characterized in that: The second through hole (16) comprises a first cavity (17) on the left and a second cavity (18) on the right, wherein the diameter of the second cavity (18) is greater than the diameter of the first cavity (17).

7. The tool for disassembling and assembling the locking nut of the turbine disk of an aircraft engine according to claim 6, characterized in that: The notch (6) is a T-shaped notch, and the notch (6) corresponds to the position of the locking nut (11).

8. The tool for disassembling and assembling the locking nut of the turbine disk of an aircraft engine according to claim 6, characterized in that: The middle portion of the support sleeve (3) is provided with an installation cavity (301), the interior of the installation cavity (301) is rotatably connected to a hollow ratchet wrench head (302), the outer surface of the hollow ratchet wrench head (302) is provided with a handle (303), and the handle (303) passes through the notch (6).

9. The tool for disassembling and assembling the locking nut of the turbine disk of an aircraft engine according to claim 8, characterized in that: The support sleeve (3) comprises a first support column (304) and a second support column (305), the first cavity (17) is provided on the first support column (304), the second cavity (18) and the notch (6) are both provided on the second support column (305), and the first support column (304) is threadedly connected to the second support column (305).

10. The tool for disassembling and assembling the locking nut of the turbine disk of an aircraft engine according to claim 9, characterized in that: A second fixing ring (306) is fixedly connected to the inner wall of the second cavity (18), a first thrust bearing (307) is installed between the left side of the hollow ratchet wrench head (302) and the first support column (304), and a second thrust bearing (308) is installed between the right side of the hollow ratchet wrench head (302) and the second fixing ring (306).

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