Aero-engine rotor hoisting device and hoisting method

Abstract

The invention discloses an aero-engine rotor hoisting device and hoisting method, and belongs to the technical field of aero-engine assembly.The aero-engine rotor hoisting device comprises clamping jaws, a limiting ring, a mounting plate, a cover plate, a lifting bolt and a hanging assembly; the mounting plate is used for movably sleeving the outer ring of the limiting ring and pressing and limiting the clamping jaw on the outer side of the limiting ring, the locking piece sequentially penetrates through the mounting plate and the cover plate to connect and fasten the mounting plate and the cover plate, and then the top of the clamping jaw is pressed and limited between the mounting plate and the cover plate; a plurality of hoisting screw holes are formed in the mounting plate in an annular array mode, and the hanging assembly is used for being connected with a crane. The problem that the turbine rotor assembly is difficult to hoist in the unit body assembling process can be solved, meanwhile, the rotor assembly can be prevented from falling in the hoisting process, and the assembling efficiency of the turbine rotor assembly in the unit body assembling process is improved.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft engine assembly, and in particular, to an aircraft engine rotor hoisting device. In addition, the present application also relates to a hoisting method using the aircraft engine rotor hoisting device. Background Art

[0002] The information provided in this section is for the purpose of generally presenting the background of the present application. To the extent described in this section, the work of the presently named inventors and aspects of the description that may not constitute prior art at the time of filing are neither explicitly nor implicitly admitted to be prior art to the present application.

[0003] In the field of aircraft engine assembly technology, a certain type of aircraft engine gas turbine rotor cannot be grasped by hand or hoisted by a hoist due to its structural characteristics and the unit assembly space structure limitation. A certain type of rotor assembly consists of turbine discs, front baffles, rear baffles, rotor blades and other components. The structure is shown in the attached manual. Figure 1 The assembly position of the gas turbine rotor assembly in the unit body is shown in the attached manual. Figure 2 As shown, the gas turbine rotor is inserted into the gas turbine stator assembly through a center tie rod, there is a certain gap (0.6-0.8 mm) between the gas turbine blades and the gas turbine stator assembly, and the gap between the inner hole of the turbine disk and the center tie rod is 9-11 mm.

[0004] At present, the gap between blades is used to design the rotor suspension, as shown in the attached manual. Figure 3 As shown in the figure, the hook passes through the blade and hooks the back of the blade. Soft rubber is bonded to the hook to prevent the blade from being scratched. In actual operation, due to the small gap between the working blades, it is difficult to pass the hook through the blade. After the first and second stage rotor assemblies of the gas turbine are hoisted into the unit body, it is difficult to disassemble the hook from the middle of the working blade due to limited operating space.

[0005] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present application, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0006] In view of at least one of the above technical problems, the present application provides an aircraft engine rotor lifting device, which can solve the problem of difficulty in lifting the turbine rotor assembly during the unit assembly process, and at the same time prevent the rotor assembly from falling during the lifting process, and improve the assembly efficiency of the turbine rotor assembly during the unit assembly process.

[0007] According to one aspect of the present application, an aircraft engine rotor hoisting device is provided, which is used to hoist a gas turbine rotor assembly to assemble it with a gas turbine stator assembly to form an engine unit body, the gas turbine rotor assembly includes a turbine disk, a front baffle, a rear baffle and rotor blades, the unit body also includes a central pull rod, the central pull rod is used to pass through the middle of the gas turbine rotor and connect to the gas turbine stator assembly, the aircraft engine rotor hoisting device includes a claw, a limit ring, a mounting plate, a cover plate, a lifting eye screw and a hanging assembly:

[0008] The claws are arranged in an annular array on the outer ring of the limit ring, the claws are used to engage with the gas turbine rotor assembly, the mounting plate is used to be movably sleeved on the outer ring of the limit ring and press the claws to limit the outer side of the limit ring, the cover plate is used to be movably sleeved on the outer ring of the limit ring and limit the top of the mounting plate, a limit platform is provided on the top of the limit ring, the limit platform is used to limit the top of the cover plate, a plurality of mounting screw holes are provided in an annular array on the mounting plate, the mounting screw holes are used to set locking pieces and pass through the mounting plate and the cover plate in sequence to connect and tighten the two, so as to press the top of the claws to limit the middle of the mounting plate and the cover plate;

[0009] A plurality of lifting screw holes are provided in a circular array on the mounting plate. The lifting eye screw comprises a lifting eye and a threaded column. The threaded column is used to cooperate with the thread of the lifting screw hole. The lifting eye is used to connect with the hanging assembly. The hanging assembly is used to connect with the crane.

[0010] In some embodiments of the present application, the aircraft engine rotor lifting device also includes a positioning member, a overlapping platform is provided on the top of the claw, the overlapping platform is used to overlap on the top of the mounting plate, a first connecting through hole is opened on the overlapping platform, the connecting through hole is used to correspond to the second connecting through hole preset on the mounting plate, the positioning member is used to pass through the first connecting through hole and the second connecting through hole in sequence to position the mounting plate and the claw; a clamping portion is provided at the bottom of the claw, the clamping portion is used to hook the preset mounting edge of the inner hole at the rear end of the turbine disk.

[0011] In some embodiments of the present application, the first connecting through hole is a through hole with a strip-shaped cross section, and the second connecting through hole is a circular hole structure.

[0012] In some embodiments of the present application, a circle of supporting bosses is provided at the bottom of the limiting ring, and the supporting bosses are used to limit the bottom of the claw so that the bottom of the claw is offset outward along the radial direction of the limiting ring.

[0013] In some embodiments of the present application, the hanging assembly includes a mounting plate, a limit assembly, a connecting ball, a limit plate, a connecting column and a connecting rod. A plurality of limit cavities are provided in a circular array in the mounting plate. Through holes are provided at the top and bottom of the limit cavities. A limit plate is movably provided in each limit cavity. The bottom of the limit plate is connected to the connecting rod. The connecting rod is used to be connected to the lifting eye screw. A limit assembly is provided at the top of the limit plate. A connecting ball is movably provided in the limit assembly. The limit assembly is used to limit the connecting ball. A first compression spring is provided between each connecting ball. The connecting column is provided at the top of the mounting plate. The connecting column is used to connect to the crane.

[0014] In some embodiments of the present application, the hanging assembly also includes a mounting ring and a connecting ring. The mounting ring is arranged on the mounting plate and each connecting ball is located in the mounting ring. There are multiple connecting rings, and the multiple connecting rings are movably mounted on the mounting ring. Each connecting ring is arranged one-to-one with each connecting ball and a second compression spring is arranged between adjacent connecting rings and connecting balls.

[0015] In some embodiments of the present application, a plurality of limit countersunk holes are provided in a circular array on the mounting plate, and a plurality of limit columns are provided in a circular array at the bottom of the mounting ring. Each limit column is used to cooperate with each limit countersunk hole, and a connecting platform is provided on the limit column. A first connecting screw hole is provided on the connecting platform. The connecting screw hole is used to set a locking screw and cooperate the connecting platform with a preset second connecting screw hole on the mounting plate through the locking screw, so as to connect and fasten the connecting platform to the mounting plate.

[0016] In some embodiments of the present application, the limiting assembly includes a first limiting member and a second limiting member, the second limiting member is arranged on the limiting plate, a hemispherical groove is opened on the top of the second limiting member, the hemispherical groove is used to place the connecting ball, the first limiting member is arranged on the second limiting member, and the first limiting member is used to limit the connecting ball.

[0017] In some embodiments of the present application, a first limiting hole is opened at the top of the limiting cavity, and the first limiting hole is used to limit the second limiting member. A second limiting hole is opened at the bottom of the limiting cavity, and the second limiting hole is used to limit the connecting rod.

[0018] The present application also discloses a method for hoisting an aircraft engine rotor, which uses the above-mentioned aircraft engine rotor hoisting device and includes the following steps:

[0019] S100, placing the gas turbine rotor assembly on a workbench with its rear end facing upward;

[0020] S200, remove the limiting ring of the aircraft engine rotor hoisting device, extend the claw into the inner hole of the gas turbine disk and hook the installation edge of the inner hole of the turbine disk;

[0021] S300, then pass the limit ring through the cover plate and the mounting plate in sequence, limit the claws, and observe whether the limit platform of the limit ring should fit with the top surface of the cover plate;

[0022] S400, after hooking the hanging assembly onto the lifting eye screw, the gas turbine rotor assembly is hoisted by cooperating the hanging assembly with the crane;

[0023] S500, during the lowering process of the gas turbine rotor assembly, the center pull rod is passed through the limit ring. After the gas turbine rotor assembly falls into place, the hanging assembly and the limit ring are taken out in sequence, and the claws are taken out.

[0024] This application has the following beneficial effects:

[0025] The aircraft engine rotor lifting device of the present application limits the claws arranged in a ring array by a limiting ring, and at the same time limits the connection of the claws by a mounting plate and a cover plate, and the mounting plate and the cover plate are both movably sleeved on the outer ring of the limiting ring, so the mounting plate, the claws and the cover plate can be taken out and disassembled together, which is convenient for the overall assembly of the lifting device and also convenient for the disassembly of the lifting device after the lifting is completed; at the same time, after the claws are adjusted to a position to engage with the gas turbine rotor assembly, the limiting ring is inserted into the mounting plate and the cover plate to limit the claws, thereby ensuring that the claws are firmly connected during lifting, and ensuring the safety and stability of the gas turbine rotor assembly lifting process.

[0026] The aircraft engine rotor hoisting method of the present application also has the above-mentioned beneficial effects. At the same time, the hoisting method of the present application is very convenient to operate, and there is no need for complicated teaching to the workers. The smooth hoisting of the gas turbine rotor assembly can be achieved through simple steps. It is only necessary to first extend the claws into the inner hole of the gas turbine disk to hook the installation edge of the inner hole of the turbine disk, and then pass the limit ring through the cover plate and the mounting plate in sequence to limit the claws to prevent the claws from radially offset and loosening. The gas turbine rotor assembly can be hoisted by cooperating with the hanging assembly and the crane, effectively improving the hoisting efficiency. The present method is mainly used to solve the problem of difficulty in hoisting the aircraft engine gas turbine rotor assembly in the unit body. Through the application of the present method and device, the assembly problem of the gas turbine rotor assembly without a stress point in the unit body with spatial structure restrictions can be solved, ensuring the safe and reliable hoisting of the gas turbine rotor assembly.

[0027] Of course, any product implementing this application does not necessarily need to achieve all the advantages described above at the same time. In addition to the purposes, features and advantages described above, this application also has other purposes, features and advantages. The following will further describe this application in detail with reference to the figures. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The illustrative embodiments and descriptions of the present application are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0029] Figure 1 is a schematic diagram of the overall structure of an existing gas turbine rotor assembly;

[0030] Figure 2 is a schematic diagram of the assembly position of a conventional gas turbine rotor assembly in a unit body;

[0031] Figure 3 It is a structural schematic diagram of an existing rotor suspension;

[0032] Figure 4 It is a half-section schematic diagram of a preferred embodiment of the present application;

[0033] Figure 5 It is a schematic diagram of the overall structure of the preferred embodiment of the present application;

[0034] Figure 6 It is a schematic diagram of the preferred embodiment of the present application being hoisted in cooperation with a gas turbine rotor assembly;

[0035] Figure 7 It is a schematic structural diagram of the claws of the preferred embodiment of the present application;

[0036] Figure 8 It is a schematic diagram of the structure of the limit ring of the preferred embodiment of the present application;

[0037] Fig. 9 It is a structural schematic diagram of a mounting plate of a preferred embodiment of the present application;

[0038] Fig.10 It is a structural schematic diagram of a hanging assembly of a preferred embodiment of the present application;

[0039] Fig.11 It is a schematic diagram of the installation of the limiting plate of the preferred embodiment of the present application;

[0040] Fig.12 is a schematic diagram of a limit assembly of a preferred embodiment of the present application;

[0041] Fig.13 It is a schematic diagram of the position of the limiting plate of the preferred embodiment of the present application;

[0042] Fig.14 It is a schematic diagram of the installation of the connecting ball of the preferred embodiment of the present application;

[0043] Legend: 1. Clamping claw; 2. Limiting ring; 3. Mounting plate; 4. Positioning piece; 5. Cover plate; 6. Locking piece; 7. Eye screw; 8. Hanging assembly; 81. Mounting plate; 82. Mounting ring; 821. Limiting column; 83. First limiting piece; 84. Second limiting piece; 85. Connecting ball; 86. First compression spring; 87. Second compression spring; 88. Connecting ring; 89. Connecting column; 810. Connecting rod; 811. Limiting plate; 812. Limiting cavity; 813. First limiting hole; 814. Second limiting hole. DETAILED DESCRIPTION

[0044] The embodiments of the present application are described in detail below in conjunction with the accompanying drawings, but the present application can be implemented in a variety of different ways defined and covered below.

[0045] Figure 1 is a schematic diagram of the overall structure of an existing gas turbine rotor assembly; Figure 2 is a schematic diagram of the assembly position of a conventional gas turbine rotor assembly in a unit body; Figure 3 It is a structural schematic diagram of an existing rotor suspension; Figure 4 It is a half-section schematic diagram of a preferred embodiment of the present application; Figure 5 It is a schematic diagram of the overall structure of the preferred embodiment of the present application; Figure 6 It is a schematic diagram of the preferred embodiment of the present application being hoisted in cooperation with a gas turbine rotor assembly; Figure 7 It is a schematic structural diagram of the claws of the preferred embodiment of the present application; Figure 8 It is a schematic diagram of the structure of the limit ring of the preferred embodiment of the present application; Fig. 9 It is a structural schematic diagram of a mounting plate of a preferred embodiment of the present application;

[0046] Fig.10 It is a structural schematic diagram of a hanging assembly of a preferred embodiment of the present application; Fig.11 It is a schematic diagram of the installation of the limiting plate of the preferred embodiment of the present application; Fig.12 is a schematic diagram of a limit assembly of a preferred embodiment of the present application; Fig.13 It is a schematic diagram of the position of the limiting plate of the preferred embodiment of the present application; Fig.14 It is a schematic diagram of the installation of the connecting ball of the preferred embodiment of the present application.

[0047] An aircraft engine rotor hoisting device is used for hoisting a gas turbine rotor assembly to assemble with a gas turbine stator assembly to form an engine unit body, the gas turbine rotor assembly includes a turbine disk, a front baffle, a rear baffle and rotor blades, the unit body also includes a central pull rod, the central pull rod is used to pass through the middle of the gas turbine rotor and connect with the gas turbine stator assembly, the aircraft engine rotor hoisting device includes a claw 1, a limit ring 2, a mounting plate 3, a cover plate 5, a lifting eye screw 7 and a hanging assembly 8:

[0048] The claws 1 are arranged in an annular array on the outer ring of the limiting ring 2. The claws 1 are used to engage with the gas turbine rotor assembly. The mounting plate 3 is used to be movably sleeved on the outer ring of the limiting ring 2 and press the claws 1 to limit the outer side of the limiting ring 2. The cover plate 5 is used to be movably sleeved on the outer ring of the limiting ring 2 and limit the top of the mounting plate 3. A limiting platform is provided on the top of the limiting ring 2. The limiting platform is used to limit the top of the cover plate 5. A plurality of mounting screw holes are provided in an annular array on the mounting plate 3. The mounting screw holes are used to set locking members 6 and pass through the mounting plate 3 and the cover plate 5 in sequence to connect and tighten the two, thereby pressing the top of the claws 1 to limit the middle of the mounting plate 3 and the cover plate 5.

[0049] A plurality of lifting screw holes are provided in a circular array on the mounting plate 3. The lifting eye screw 7 comprises a lifting eye and a threaded column. The threaded column is used to cooperate with the thread of the lifting screw hole. The lifting eye is used to connect with the hanging assembly 8. The hanging assembly 8 is used to connect with the crane.

[0050] Here, the “locking member 6” means a structure for connecting and fastening the mounting plate 3 and the cover plate 5. In some embodiments, the locking member 6 is a hexagonal bolt or a screw.

[0051] The aircraft engine rotor lifting device of the present application limits the claws 1 arranged in a ring array by a limiting ring 2, and at the same time connects and limits the claws 1 by a mounting plate 3 and a cover plate 5, and the mounting plate 3 and the cover plate 5 are both movably mounted on the outer ring of the limiting ring 2, so the mounting plate 3, the claws 1 and the cover plate 5 can be taken out and disassembled together, which is convenient for the overall assembly of the lifting device and also convenient for the disassembly of the lifting device after the lifting is completed; at the same time, after the claws 1 are adjusted to a position to engage with the gas turbine rotor assembly, the limiting ring 2 can be inserted into the mounting plate 3 and the cover plate 5 to limit the claws 1, thereby ensuring that the claws 1 are firmly connected during lifting, and ensuring the safety and stability of the gas turbine rotor assembly lifting process.

[0052] Preferably, please refer to Figure 4 and 6 As shown, the aircraft engine rotor lifting device also includes a positioning member 4, a lap platform is arranged on the top of the claw 1, the lap platform is used to overlap the top of the mounting plate 3, a first connecting through hole is opened on the lap platform, the connecting through hole is used to correspond to the second connecting through hole preset on the mounting plate 3, the positioning member 4 is used to pass through the first connecting through hole and the second connecting through hole in sequence to position the mounting plate 3 and the claw 1; a clamping portion is arranged at the bottom of the claw 1, and the clamping portion is used to hook the preset mounting edge of the inner hole at the rear end of the turbine disk.

[0053] It can be understood that the claw 1 is overlapped on the top of the mounting plate 3 through the overlap platform on its top, and the overlap platform and the mounting plate 3 are limited by the positioning piece 4. Then, the cover plate 5 can be pressed on the top of the mounting plate 3, and the cover plate 5 can be connected to the mounting plate 3 with the locking piece 6, so as to limit the overlap platform longitudinally, and cooperate with the positioning piece 4 to limit the overlap platform horizontally, so as to realize the stable installation of the claw 1 and prevent the claw 1 from falling off the mounting plate 3.

[0054] The positioning member 4 can be a cylindrical pin.

[0055] Preferably, please refer to Figure 7 As shown, the first connecting through hole is a through hole with a strip-shaped cross section, and the second connecting through hole is a circular hole structure.

[0056] It can be understood that a strip-shaped through hole is provided on the overlapping platform at the top of the claw 1, so that the claw 1 can be fine-tuned horizontally, which is convenient for adjusting the position of the claw 1 to engage with the gas turbine rotor assembly. Subsequently, the claw can be laterally limited by the limiting ring 2 to ensure the clamping stability of the claw 1.

[0057] Preferably, please refer to Figure 4 and 8 As shown, a circle of supporting bosses is provided at the bottom of the limiting ring 2 , and the supporting bosses are used to limit the bottom of the claw 1 so that the bottom of the claw 1 deviates outward along the radial direction of the limiting ring 2 .

[0058] It can be understood that the supporting boss at the bottom of the limit ring 2 can push the claw 1 to the outside of the limit ring 2, ensuring that the clamping part at the bottom of the claw 1 is firmly engaged with the gas turbine rotor assembly, thereby improving the stability during the lifting process. Since the claw 1 hooks the installation edge of the gas turbine rotor assembly from the middle of the gas turbine rotor assembly along the four sides, and at the same time cooperates with the limit ring 2 to limit the claw 1, it is ensured that the claw 1 will not retract inward, thereby achieving a very stable clamping fit and ensuring the safety of lifting.

[0059] Preferably, please refer to Figure 10-14 As shown, the hanging assembly 8 includes a mounting plate 81, a limiting assembly, a connecting ball 85, a limiting plate 811, a connecting column 89 and a connecting rod 810. A plurality of limiting cavities 812 are provided in a circular array in the mounting plate 81. Through holes are provided at the top and bottom of the limiting cavity 812. A limiting plate 811 is movably provided in each limiting cavity 812. The bottom of the limiting plate 811 is connected to the connecting rod 810. The connecting rod 810 is used to be connected to the eye screw 7. A limiting assembly is provided at the top of the limiting plate 811. A connecting ball 85 is movably provided in the limiting assembly. The limiting assembly is used to limit the connecting ball 85. A first compression spring 86 is provided between each connecting ball 85. A connecting column 89 is provided at the top of the mounting plate 81. The connecting column 89 is used to be connected to a crane.

[0060] It can be understood that the hanging assembly 8 can cooperate with the lifting eye screws 7 to lift the lifting device and the gas turbine rotor assembly. Since there are multiple lifting eye screws 7 distributed at intervals, in order to reduce the unstable lifting due to unbalanced force and shaking during movement during the lifting process, which affects the lifting speed, multiple movable limit plates 811 are arranged inside the mounting plate 81, and connecting balls 85 that can be rotated at will are installed on the limit plates 811 through the limit assembly. A first compression spring 86 is arranged between each connecting ball 85. The first compression spring 86 can buffer and pull each limit plate 811 and the connecting rod 810 to maintain balance, which can reduce the amplitude of shaking during lifting, avoid uncontrollable impact during lifting, improve the safety and stability of the lifting of the gas turbine rotor assembly, and effectively ensure the lifting efficiency.

[0061] Preferably, please refer to Fig.10 As shown, the hanging assembly 8 also includes a mounting ring 82 and a connecting ring 88. The mounting ring 82 is arranged on the mounting plate 81 and each connecting ball 85 is located in the mounting ring 82. There are multiple connecting rings 88, and the multiple connecting rings 88 are movably mounted on the mounting ring 82. Each connecting ring 88 is arranged one by one with each connecting ball 85, and a second compression spring 87 is arranged between adjacent connecting rings 88 and connecting balls 85.

[0062] It can be understood that in order to enhance the overall stability of each connecting ball 85, the limiting plate 811 and the connecting rod 810 and reduce the displacement amplitude of the shaking, each connecting ball 85 is connected to each connecting ring 88 through a second compression spring 87, and the connecting ring 88 is limited by the mounting ring 82, which can achieve multi-directional buffering and limiting of the connecting ball 85, which is beneficial to improving the overall seismic resistance of the suspension assembly 8 and facilitating the fine control of the lifting speed.

[0063] Preferably, please refer to Fig.10 As shown, a plurality of limiting countersunk holes are provided in a circular array on the mounting plate 81, and a plurality of limiting columns 821 are provided in a circular array at the bottom of the mounting ring 82. Each limiting column 821 is used to cooperate with each limiting countersunk hole, and a connecting platform is provided on the limiting column 821. A first connecting screw hole is provided on the connecting platform. The connecting screw hole is used to set a locking screw and cooperate the connecting platform with a preset second connecting screw hole on the mounting plate 81 through the locking screw, so as to connect and fasten the connecting platform to the mounting plate 81.

[0064] It can be understood that the limiting column 821 not only plays the role of installing the mounting ring 82, but also can be easily removed from the mounting plate 81 by removing the locking screw to complete the removal of the mounting ring 82; the limiting column 821 also plays a limiting role on the connecting ring 88, thereby preventing the connecting ring 88 from sliding too much along the mounting ring 82, thereby ensuring the limiting effect of the connecting ring 88 on the connecting ball 85.

[0065] Preferably, please refer to Fig.12 As shown, the limiting component includes a first limiting member 83 and a second limiting member 84. The second limiting member 84 is arranged on the limiting plate 811. A hemispherical groove is opened on the top of the second limiting member 84. The hemispherical groove is used to place the connecting ball 85. The first limiting member 83 is arranged on the second limiting member 84. The first limiting member 83 is used to limit the connecting ball 85.

[0066] It can be understood that the connecting ball 85 is limited by the hemispherical groove at the top of the second limiting member 84. The connecting ball 85 can roll in the hemispherical groove, and at the same time cooperate with the first limiting member 83 to limit the top of the connecting ball 85, which can ensure that the connecting ball 85 does not fall off without interfering with the movement of the connecting ball 85.

[0067] Optionally, a groove for limiting the connecting ball 85 is opened at the bottom of the first limiting member 83, which can strengthen the limiting of the connecting ball 85 and ensure its smooth rolling; a plurality of limiting rods are arranged at the bottom of the first limiting member 83, and the limiting rods are connected to the second limiting member 84 by bolts, which can facilitate the disassembly and assembly of the first limiting member 83.

[0068] Preferably, please refer to Fig.11 and 13 As shown, a first limiting hole 813 is formed at the top of the limiting cavity 812, and the first limiting hole 813 is used to limit the second limiting member 84. A second limiting hole 814 is formed at the bottom of the limiting cavity 812, and the second limiting hole 814 is used to limit the connecting rod 810.

[0069] It can be understood that the limit plate 811 can slide in the limit cavity 812, and at the same time, the first limit hole 813 at the top of the limit cavity 812 can limit the second limit member 84, and the second limit hole 814 at the bottom of the limit cavity 812 can limit the connecting rod 810, so as to avoid excessive movement of the limit plate 811 and cause the overall shaking of the hanging assembly 8, thereby ensuring the safety and stability of the lifting process.

[0070] The present application also discloses a method for hoisting an aircraft engine rotor, which uses the above-mentioned aircraft engine rotor hoisting device and includes the following steps:

[0071] S100, placing the gas turbine rotor assembly on a workbench with its rear end facing upward;

[0072] S200, remove the limit ring 2 of the aircraft engine rotor lifting device, and extend the claw 1 into the inner hole of the gas turbine disk to hook the installation edge of the inner hole of the turbine disk;

[0073] S300, pass the limit ring 2 through the cover plate 5 and the mounting plate 3 in sequence, limit the claw 1, and observe whether the limit platform of the limit ring 2 is in contact with the top surface of the cover plate 5;

[0074] S400, after hooking the hanging assembly 8 onto the eye screw 7, the gas turbine rotor assembly is hoisted by cooperating with the hanging assembly 8 and the crane;

[0075] S500, during the lowering process of the gas turbine rotor assembly, the center pull rod is passed through the limit ring 2. After the gas turbine rotor assembly falls into place, the hanging assembly 8 and the limit ring 2 are taken out in sequence, and the claw 1 is taken out.

[0076] The aircraft engine rotor hoisting method of the present application also has the above-mentioned beneficial effects. At the same time, the hoisting method of the present application is very convenient to operate, and there is no need to conduct complicated teaching to the workers. The gas turbine rotor assembly can be smoothly hoisted through simple steps. It is only necessary to first extend the claw 1 into the inner hole of the gas turbine disk to hook the installation edge of the inner hole of the turbine disk, and then pass the limit ring 2 through the cover plate 5 and the mounting plate 3 in sequence to limit the claw 1 to prevent the claw 1 from radially offset and loosening. The gas turbine rotor assembly can be hoisted by cooperating with the hanging assembly 8 and the crane, effectively improving the hoisting efficiency. The present method is mainly used to solve the problem of difficulty in hoisting the aircraft engine gas turbine rotor assembly in the unit body. Through the application of the present method and device, the assembly problem of the gas turbine rotor assembly without a stress point in the unit body with spatial structure restrictions can be solved, ensuring the safe and reliable hoisting of the gas turbine rotor assembly.

[0077] It should be noted that, in this article, the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or apparatus.

[0078] This article uses specific examples to illustrate the principles and implementation methods of this application. The above examples are only used to help understand the method and its core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as the protection of this application.

Claims

1. An aircraft engine rotor hoisting device, used for hoisting a gas turbine rotor assembly to assemble with a gas turbine stator assembly to form an engine unit body, the gas turbine rotor assembly includes a turbine disk, a front baffle, a rear baffle and rotor blades, the unit body also includes a center tie rod, the center tie rod is used to pass through the middle of the gas turbine rotor and connect to the gas turbine stator assembly, characterized in that: The aircraft engine rotor hoisting device comprises a clamping claw (1), a limiting ring (2), a mounting plate (3), a cover plate (5), a lifting eye screw (7) and a hanging assembly (8): The claws (1) are arranged in an annular array on the outer ring of the limiting ring (2), the claws (1) are used to engage with the gas turbine rotor assembly, the mounting plate (3) is used to be movably sleeved on the outer ring of the limiting ring (2) and to press the claws (1) to be limited outside the limiting ring (2), the cover plate (5) is used to be movably sleeved on the outer ring of the limiting ring (2) and to limit the top of the mounting plate (3), a limiting platform is provided on the top of the limiting ring (2), the limiting platform is used to limit the top of the cover plate (5), a plurality of mounting screw holes are provided in an annular array on the mounting plate (3), the mounting screw holes are used to set locking members (6) and the locking members (6) are passed through the mounting plate (3) and the cover plate (5) in sequence to connect and tighten the two, thereby pressing the top of the claws (1) to be limited between the mounting plate (3) and the cover plate (5); A plurality of lifting screw holes are provided in a circular array on the mounting plate (3); the lifting eye screw (7) comprises a lifting eye and a threaded column; the threaded column is used to cooperate with the thread of the lifting screw hole; the lifting eye is used to connect with the hanging assembly (8); and the hanging assembly (8) is used to connect with the crane.

2. The aircraft engine rotor hoisting device according to claim 1, characterized in that: The aircraft engine rotor hoisting device also includes a positioning member (4); a lap platform is provided on the top of the clamping claw (1); the lap platform is used to overlap the top of the mounting plate (3); a first connecting through hole is opened on the lap platform; the connecting through hole is used to correspond to a second connecting through hole preset on the mounting plate (3); the positioning member (4) is used to pass through the first connecting through hole and the second connecting through hole in sequence to position the mounting plate (3) and the clamping claw (1); a clamping portion is provided on the bottom of the clamping claw (1); the clamping portion is used to hook the mounting edge preset in the inner hole at the rear end of the turbine disk.

3. The aircraft engine rotor hoisting device according to claim 2, characterized in that: The first connecting through hole is a through hole with a strip-shaped cross section, and the second connecting through hole is a circular hole structure.

4. The aircraft engine rotor hoisting device according to claim 1, characterized in that: A circle of supporting bosses is arranged at the bottom of the limiting ring (2), and the supporting bosses are used to limit the bottom of the clamping claw (1) so that the bottom of the clamping claw (1) deviates outwardly along the radial direction of the limiting ring (2).

5. The aircraft engine rotor hoisting device according to claim 1, characterized in that: The hanging assembly (8) comprises a mounting plate (81), a limiting assembly, a connecting ball (85), a limiting plate (811), a connecting column (89) and a connecting rod (810); a plurality of limiting cavities (812) are provided in a circular array in the mounting plate (81); through holes are provided at the top and bottom of the limiting cavities (812); a limiting plate (811) is movably provided in each limiting cavity (812); the bottom of the limiting plate (811) is connected to the connecting rod (810); the connecting rod (810) is used to be connected to the eye screw (7); a limiting assembly is provided at the top of the limiting plate (811); a connecting ball (85) is movably provided in the limiting assembly; the limiting assembly is used to limit the connecting ball (85); a first compression spring (86) is provided between each connecting ball (85); a connecting column (89) is provided at the top of the mounting plate (81); and the connecting column (89) is used to be connected to a crane.

6. The aircraft engine rotor hoisting device according to claim 5, characterized in that: The hanging assembly (8) also includes a mounting ring (82) and a connecting ring (88), wherein the mounting ring (82) is arranged on the mounting plate (81) and each connecting ball (85) is located in the mounting ring (82), a plurality of connecting rings (88) are provided, and the plurality of connecting rings (88) are movably sleeved on the mounting ring (82), each connecting ring (88) is arranged in a one-to-one correspondence with each connecting ball (85), and a second compression spring (87) is arranged between adjacent connecting rings (88) and connecting balls (85).

7. The aircraft engine rotor hoisting device according to claim 6, characterized in that: A plurality of limiting countersunk holes are provided in an annular array on the mounting plate (81), and a plurality of limiting posts (821) are provided in an annular array at the bottom of the mounting ring (82). Each limiting post (821) is used to cooperate with each limiting countersunk hole. A connecting platform is provided on the limiting post (821), and a first connecting screw hole is provided on the connecting platform. The connecting screw hole is used to set a locking screw and cooperate the connecting platform with a second connecting screw hole preset on the mounting plate (81) through the locking screw, so as to connect and fasten the connecting platform to the mounting plate (81).

8. The aircraft engine rotor hoisting device according to claim 5, characterized in that: The limiting component comprises a first limiting member (83) and a second limiting member (84); the second limiting member (84) is arranged on the limiting plate (811); a hemispherical groove is provided on the top of the second limiting member (84); the hemispherical groove is used to place the connecting ball (85); the first limiting member (83) is arranged on the second limiting member (84); and the first limiting member (83) is used to limit the connecting ball (85).

9. The aircraft engine rotor hoisting device according to claim 8, characterized in that: A first limiting hole (813) is provided at the top of the limiting cavity (812), and the first limiting hole (813) is used to limit the second limiting member (84). A second limiting hole (814) is provided at the bottom of the limiting cavity (812), and the second limiting hole (814) is used to limit the connecting rod (810).

10. A method for hoisting an aircraft engine rotor, using the aircraft engine rotor hoisting device according to any one of claims 1 to 9, characterized in that: It includes the following steps: S100, placing the gas turbine rotor assembly on a workbench with its rear end facing upward; S200, removing the limiting ring (2) of the aircraft engine rotor hoisting device, extending the claw (1) into the inner hole of the gas turbine disk to hook the installation edge of the inner hole of the turbine disk; S300, the limiting ring (2) is then passed through the cover plate (5) and the mounting plate (3) in sequence to limit the position of the claw (1), and it is observed that the limiting platform of the limiting ring (2) should be in contact with the top surface of the cover plate (5); S400, after hooking the hanging assembly (8) onto the eye screw (7), the gas turbine rotor assembly is hoisted by cooperating with the hanging assembly (8) and the crane; S500, during the lowering process of the gas turbine rotor assembly, the center pull rod is passed through the limiting ring (2). After the gas turbine rotor assembly falls into place, the hanging assembly (8) and the limiting ring (2) are taken out in sequence, and the claw (1) is taken out.

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