An aero-engine rotor hoisting device and hoisting method

Abstract

The application discloses an aero-engine rotor hoisting device and a hoisting method, and belongs to the technical field of aero-engine assembly. The aero-engine rotor hoisting device comprises a claw, a limiting ring, a mounting plate, a cover plate, a lifting ring screw and a hoisting assembly. The claws are arranged in an annular array outside the limiting ring. The mounting plate is used for movably sleeving the limiting ring and pressing the claws to be limited outside the limiting ring. Locking pieces are used for sequentially penetrating the mounting plate and the cover plate to connect and fasten the two, and then the top of the claw is pressed and limited between the mounting plate and the cover plate. A plurality of hoisting screw holes are arranged in an annular array on the mounting plate. The hoisting assembly is used for being connected with a crane. The application can solve the hoisting difficulty of a turbine rotor assembly in a unit assembly process, can prevent the turbine rotor assembly from falling in the hoisting process, and can improve the assembly efficiency of the turbine rotor assembly in the unit assembly process.

Description

TECHNICAL FIELD

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

[0002] The information provided in this section is for the purpose of generally presenting the context of the application. The work of the presently named inventors, to the extent the descriptions are concerned therewith, and the descriptions of certain aspects set forth in this section are not necessarily prior art to the present application, expressly incorporated by reference herein.

[0003] In the technical field of aero-engine assembly, due to the structural characteristics of a certain type of aero-engine gas turbine rotor and the space structure limitation of unit body assembly, the rotor assembly cannot be grabbed by hand or hoisted by a designed hoist. The certain type of rotor assembly is composed of turbine disc, front baffle, rear baffle and rotor blade, and the structure is shown in the accompanying drawings of the specification. Figure 1 The assembly position of the gas turbine rotor assembly in the unit body is shown in the accompanying drawings of the specification. Figure 2 The gas turbine rotor is inserted into the gas turbine stator assembly through the center pull rod, and there is a certain gap (0.6-0.8mm) between the gas turbine blade and the gas turbine stator assembly. The gap between the inner hole of the turbine disc and the center pull rod is 9-11mm.

[0004] At present, the rotor is hoisted by using the gap between the blades, as shown in the accompanying drawings of the specification. The hook is hooked on the blade back by passing through the blade, and soft rubber is attached on the hook to prevent the blade from being scratched. Figure 3 In the actual operation process, it is difficult to pass the hook through the blade due to the small gap between the working blades. After hoisting the gas turbine first and second stage rotor assembly into the unit body, it is difficult to disassemble the hook from the middle of the working blade due to the limited operation space.

[0005] It should be noted that the information disclosed in the above background section is only used to strengthen the understanding of the background of the present application, and therefore can include information which does not constitute prior art known to those of ordinary skill in the art. SUMMARY

[0006] In view of at least one of the above technical problems, the present application provides an aero-engine rotor hoisting device, which can solve the problem of difficult hoisting of the turbine rotor assembly in the unit body assembly process, prevent the rotor assembly from falling during hoisting, and improve the assembly efficiency of the turbine rotor assembly in the unit body assembly process.

[0007] According to an aspect of the present application, an aero-engine rotor hoisting device is provided for hoisting a gas turbine rotor assembly to assemble with a gas turbine stator assembly to form an engine unit, the gas turbine rotor assembly comprising a turbine disc, a front baffle, a rear baffle and rotor blades, the unit further comprising a center pull rod for passing through the middle of the gas turbine rotor and connecting with the gas turbine stator assembly, the aero-engine rotor hoisting device comprising a claw, a limiting ring, a mounting plate, a cover plate, a lifting ring screw and a hanging assembly:

[0008] The claw is arranged in an annular array outside the limiting ring, and is used for clamping connection with the gas turbine rotor assembly. The mounting plate is used for movably sleeving outside the limiting ring and pressing the claw tightly. The cover plate is used for movably sleeving outside the limiting ring and limiting the top of the mounting plate. The top of the limiting ring is provided with a limiting platform for limiting the top of the cover plate. A plurality of mounting screw holes are arranged in an annular array on the mounting plate, and the mounting screw holes are used for arranging locking members and connecting and fastening the mounting plate and the cover plate through the locking members in sequence, so as to press the top of the claw tightly between the mounting plate and the cover plate.

[0009] A plurality of hoisting screw holes are arranged in an annular array on the mounting plate. The lifting ring screw comprises a lifting ring and a threaded column. The threaded column is used for threaded connection with the hoisting screw hole. The lifting ring is used for connecting with the hanging assembly. The hanging assembly is used for connecting with the crane.

[0010] In some embodiments of the present application, the aero-engine rotor hoisting device further comprises a positioning member. The top of the claw is provided with an overlapping platform for overlapping the top of the mounting plate. A first connecting through hole is arranged on the overlapping platform and corresponds to a second connecting through hole arranged on the mounting plate. The positioning member is used for positioning the mounting plate and the claw by sequentially passing through the first connecting through hole and the second connecting through hole. The bottom of the claw is provided with a clamping portion for hooking an installation edge of a rear end inner hole of the turbine disc.

[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, the bottom of the limiting ring is provided with a supporting boss for limiting the bottom of the claw to offset outwardly along the radial direction of the limiting ring.

[0013] In some embodiments of the present application, the hanging assembly comprises a mounting disc, a limiting assembly, a connecting ball, a limiting plate, a connecting column and a connecting rod, a plurality of limiting cavities are arranged in the annular array of the mounting disc, a through hole is arranged at the top and bottom of the limiting cavity, a limiting plate is movably arranged in each limiting cavity, the bottom of the limiting plate is connected with the connecting rod, the connecting rod is used for connecting with the lifting ring screw, the top of the limiting plate is provided with a limiting assembly, a connecting ball is movably arranged in the limiting assembly, the limiting assembly is used for limiting the connecting ball, a first compression spring is arranged between each connecting ball, the connecting column is arranged on the top of the mounting plate, and the connecting column is used for connecting with the crane.

[0014] In some embodiments of the present application, the hanging assembly further comprises a mounting ring and a connecting ring, the mounting ring is arranged on the mounting disc and each connecting ball is located in the mounting ring, a plurality of connecting rings are provided, the plurality of connecting rings are movably arranged on the mounting ring, each connecting ring is arranged one by 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 limiting counterbores are arranged in the annular array of the mounting disc, a plurality of limiting columns are arranged in the annular array of the bottom of the mounting ring, each limiting column is used for cooperating with each limiting counterbore, a connecting platform is arranged on the limiting column, a first connecting screw hole is arranged on the connecting platform, the connecting screw hole is used for arranging a locking screw and cooperating with a second connecting screw hole arranged on the mounting disc through the locking screw, so as to connect and fasten the connecting platform and the mounting disc.

[0016] In some embodiments of the present application, the limiting assembly comprises a first limiting piece and a second limiting piece, the second limiting piece is arranged on the limiting plate, a hemispherical recess is arranged at the top of the second limiting piece, the hemispherical recess is used for placing the connecting ball, the first limiting piece is arranged on the second limiting piece, and the first limiting piece is used for limiting the connecting ball.

[0017] In some embodiments of the present application, a first limiting hole is arranged at the top of the limiting cavity, the first limiting hole is used for limiting the second limiting piece, a second limiting hole is arranged at the bottom of the limiting cavity, and the second limiting hole is used for limiting the connecting rod.

[0018] The present application also discloses an aero-engine rotor hoisting method, which adopts the aero-engine rotor hoisting device, and comprises the following steps:

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

[0020] S200, removing the limiting ring of the aero-engine rotor hoisting device, and extending the clamping jaw into the inner hole of the turbine disc to hook the turbine disc inner hole mounting edge;

[0021] S300, the limiting ring is sequentially threaded through the cover plate and the mounting plate, the clamping jaw is limited, and it is observed that the limiting ring limiting platform should be attached to the top surface of the cover plate;

[0022] S400, after the hanging assembly hooks the lifting ring screw, the gas turbine rotor assembly is hoisted through cooperation of the hanging assembly and the crane;

[0023] S500, during the descent of the gas turbine rotor assembly, the center pull rod passes through the limiting ring, and after the gas turbine rotor assembly is lowered into place, the hanging assembly, the limiting ring, and the clamping jaw are sequentially removed.

[0024] The application has the following beneficial effects:

[0025] The aero-engine rotor hoisting device of the application limits the clamping jaw arranged in an annular array through the limiting ring, and simultaneously limits the clamping jaw through the mounting plate and the cover plate, and the mounting plate and the cover plate are both movably sleeved on the outer circle of the limiting ring, so that the mounting plate, the clamping jaw, and the cover plate can be taken out and disassembled together, facilitating assembly of the hoisting device as a whole and facilitating disassembly of the hoisting device after hoisting is completed; meanwhile, the clamping jaw can be limited through the limiting ring inserted into the mounting plate and the cover plate after the clamping jaw is adjusted to the position and is in clamping and cooperative engagement with the gas turbine rotor assembly, so as to ensure stable connection of the clamping jaw during hoisting and to ensure safety and stability of the gas turbine rotor assembly during hoisting.

[0026] The aero-engine rotor hoisting method of the application also has the beneficial effects described above. Meanwhile, the hoisting method of the application is very convenient to operate, does not need complicated teaching of workers, and can realize stable hoisting of the gas turbine rotor assembly through simple steps, that is, the clamping jaw is first hooked to the mounting edge of the turbine disc inner hole by extending into the turbine disc inner hole, then the limiting ring is sequentially threaded through the cover plate and the mounting plate to limit the clamping jaw, so as to avoid radial deviation and loosening of the clamping jaw, and the gas turbine rotor assembly can be hoisted through cooperation of the hanging assembly and the crane, effectively improving the hoisting efficiency. The method is mainly used to solve the problem of difficult hoisting of the aero-engine gas turbine rotor assembly in a unit body, and through application of the method and the device, the assembly problem of the gas turbine rotor assembly without a stress point in a unit body with a space structure limitation can be solved, and the safety and reliability of hoisting of the gas turbine rotor assembly are ensured.

[0027] Of course, implementation of any product of the application does not necessarily need to achieve all the advantages described above. In addition to the purposes, features, and advantages described above, the application has other purposes, features, and advantages. The application will be further described in detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0028] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application and are incorporated in and constitute a part of this application. The illustrations, together with the description, serve to explain the application, but do not limit the application.

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

[0030] Figure 2 is a schematic diagram of the assembly position of a prior gas turbine rotor assembly in a cell;

[0031] Figure 3 is a schematic diagram of the structure of a prior rotor hanger;

[0032] Figure 4 is a schematic diagram of the overall structure of a preferred embodiment of the application;

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

[0034] Figure 6 is a schematic diagram of the assembly of a preferred embodiment of the application with a gas turbine rotor assembly;

[0035] Figure 7 is a schematic diagram of the structure of a pawl of a preferred embodiment of the application;

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

[0037] Figure 9 is a schematic diagram of the structure of a mounting plate of a preferred embodiment of the application;

[0038] Figure 10 is a schematic diagram of the structure of a hanger assembly of a preferred embodiment of the application;

[0039] Figure 11 is a schematic diagram of the mounting of a stop plate of a preferred embodiment of the application;

[0040] Figure 12 is a schematic diagram of a stop assembly of a preferred embodiment of the application;

[0041] Figure 13 is a schematic diagram of the position of a stop plate of a preferred embodiment of the application;

[0042] Figure 14 is a schematic diagram of the mounting of a connecting ball of a preferred embodiment of the application;

[0043] Figure legend: 1, clamping jaw; 2, limiting ring; 3, mounting plate; 4, positioning piece; 5, cover plate; 6, locking piece; 7, lifting ring screw; 8, hanging assembly; 81, mounting disc; 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 with reference to the accompanying drawings, but the present application can be implemented in various different ways as defined and covered by the following.

[0045] Figure 1 is a schematic diagram of the overall structure of the existing gas turbine rotor assembly; Figure 2 is a schematic diagram of the assembly position of the existing gas turbine rotor assembly in the unit body; Figure 3 is a schematic diagram of the structure of the existing rotor hanging; Figure 4 is a schematic diagram of the half-section of the preferred embodiment of the present application; Figure 5 is a schematic diagram of the overall structure of the preferred embodiment of the present application; Figure 6 is a schematic diagram of the hoisting of the preferred embodiment of the present application in cooperation with the gas turbine rotor assembly; Figure 7 is a schematic diagram of the structure of the clamping jaw of the preferred embodiment of the present application; Figure 8 is a schematic diagram of the structure of the limiting ring of the preferred embodiment of the present application; Figure 9 is a schematic diagram of the structure of the mounting plate of the preferred embodiment of the present application; Figure 10 is a schematic diagram of the structure of the hanging assembly of the preferred embodiment of the present application; Figure 11 is a schematic diagram of the installation of the limiting plate of the preferred embodiment of the present application; Figure 12 is a schematic diagram of the limiting assembly of the preferred embodiment of the present application; Figure 13 is a schematic diagram of the position of the limiting plate of the preferred embodiment of the present application; Figure 14 is a schematic diagram of the installation of the connecting ball of the preferred embodiment of the present application.

[0046] An aero-engine rotor hoisting device 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 comprising a turbine disc, a front baffle, a rear baffle and rotor blades, the unit body further comprising a center pull rod for passing through the middle of the gas turbine rotor and connecting with the gas turbine stator assembly, the aero-engine rotor hoisting device comprising a clamping jaw 1, a limiting ring 2, a mounting plate 3, a cover plate 5, a lifting ring screw 7 and a hanging assembly 8:

[0047] The claw 1 is arranged in an annular array outside the limiting ring 2, the claw 1 is used for clamping cooperation with the gas turbine rotor assembly, the mounting plate 3 is used for movably sleeving outside the limiting ring 2 and pressing the claw 1 to be limited outside the limiting ring 2, the cover plate 5 is used for movably sleeving outside the limiting ring 2 and limiting the top of the mounting plate 3, the top of the limiting ring 2 is provided with a limiting platform, the limiting platform is used for limiting the top of the cover plate 5, a plurality of mounting screw holes are arranged in an annular array on the mounting plate 3, the mounting screw hole is used for arranging the locking piece 6 and connecting and fastening the mounting plate 3 and the cover plate 5 through the locking piece 6 in sequence, and then the top of the claw 1 is pressed and limited between the mounting plate 3 and the cover plate 5.

[0048] A plurality of hoisting screw holes are arranged in an annular array on the mounting plate 3, the lifting ring screw 7 includes a lifting ring and a threaded column, the threaded column is used for screwing with the hoisting screw hole, the lifting ring is used for connecting with the lifting assembly 8, and the lifting assembly 8 is used for connecting with the crane.

[0049] Here, the meaning of the locking piece 6 is a structure for connecting and fastening the mounting plate 3 and the cover plate 5, and in some embodiments, the locking piece 6 is a hexagonal head bolt or a screw rod.

[0050] The aero-engine rotor hoisting device can limit the claw 1 arranged in an annular array through the limiting ring 2, and can limit the claw 1 through the mounting plate 3 and the cover plate 5, and the mounting plate 3 and the cover plate 5 are movably sleeved outside the limiting ring 2, so that the mounting plate 3, the claw 1 and the cover plate 5 can be taken out and disassembled together, facilitating the assembly of the hoisting device as a whole and facilitating the disassembly of the hoisting device after hoisting is completed; meanwhile, the claw 1 can be limited through the limiting ring 2 inserted into the mounting plate 3 and the cover plate 5 after the claw 1 is adjusted to the position and clamped with the gas turbine rotor assembly, so as to ensure the connection stability of the claw 1 during hoisting and the safety and stability of the gas turbine rotor assembly during hoisting.

[0051] Preferably, please refer to Figure 4 and 6 The aero-engine rotor hoisting device further comprises a positioning piece 4, the top of the claw 1 is provided with a lap joint platform, the lap joint platform is used for lap joint on the top of the mounting plate 3, a first connecting through hole is arranged on the lap joint platform, the connecting through hole is used for corresponding arrangement with a second connecting through hole prearranged on the mounting plate 3, and the positioning piece 4 is used for sequentially penetrating the first connecting through hole and the second connecting through hole to position the mounting plate 3 and the claw 1; the bottom of the claw 1 is provided with a clamping part, and the clamping part is used for hooking the mounting edge prearranged in the rear end hole of the turbine disc.

[0052] It can be understood that the clamping jaw 1 is lapped on the top of the mounting plate 3 through the lapping platform on the top thereof, and the lapping platform is limited with the mounting plate 3 through the positioning member 4, then the lapping platform can be longitudinally limited through the cover plate 5 being pressed on the top of the mounting plate 3, the cover plate 5 is connected with the mounting plate 3 through the locking member 6, and then the lapping platform is longitudinally limited, and the lapping platform is transversely limited through the positioning member 4, so that the clamping jaw 1 is stably installed, and the clamping jaw 1 is prevented from falling off from the mounting plate 3.

[0053] The positioning member 4 can be a cylindrical pin.

[0054] Preferably, as shown in Figure 7 , the first connecting through hole is a through hole with a strip-shaped cross section, and the second connecting through hole is a round hole structure.

[0055] It can be understood that the strip-shaped through hole is arranged on the lapping platform on the top of the clamping jaw 1, so that the clamping jaw 1 can be transversely adjusted, the position of the clamping jaw 1 is adjusted to be clamped and matched with the gas turbine rotor assembly, then the clamping jaw is transversely limited through the limiting ring 2, and the clamping stability of the clamping jaw 1 is ensured.

[0056] Preferably, as shown in Figure 4 and 8 , the bottom of the limiting ring 2 is provided with a circle of supporting bosses, and the supporting bosses are used for limiting the bottom of the clamping jaw 1 to make the bottom of the clamping jaw 1 outwardly deviate along the radial direction of the limiting ring 2.

[0057] It can be understood that the supporting bosses on the bottom of the limiting ring 2 can push the clamping jaw 1 outwardly to the outside of the limiting ring 2, the clamping part on the bottom of the clamping jaw 1 is stably clamped and matched with the gas turbine rotor assembly, the stability in the hoisting process is improved, since the clamping jaw 1 is hooked from the middle of the gas turbine rotor assembly to the mounting edge of the gas turbine rotor assembly outwardly around, and the limiting ring 2 is matched with the clamping jaw 1 to limit the clamping jaw 1, so that the clamping jaw 1 cannot be inwardly retracted, the clamping and matching are very stable, and the safety of hoisting is ensured.

[0058] Preferably, as shown in Figures 10-14 , the hanging assembly 8 comprises a mounting disc 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 arranged in the inner ring of the mounting disc 81, through holes are arranged on the top and the bottom of the limiting cavity 812, the limiting plate 811 is movably arranged in each limiting cavity 812, the bottom of the limiting plate 811 is connected with the connecting rod 810, the connecting rod 810 is used for being connected with the lifting ring screw 7, the limiting assembly is arranged on the top of the limiting plate 811, the connecting ball 85 is movably arranged in the limiting assembly, the limiting assembly is used for limiting the connecting ball 85, the first compression spring 86 is arranged between each connecting ball 85, the connecting column 89 is arranged on the top of the mounting disc 81, and the connecting column 89 is used for being connected with the crane.

[0059] It can be understood that the hanging assembly 8 can cooperate with the lifting ring screw 7 to lift the lifting device and the gas turbine rotor assembly. Since the lifting ring screw 7 is spaced apart by multiple lifting ring screws, in order to reduce the instability of lifting caused by unbalanced force and shaking during movement, and to affect the speed of lifting, multiple movable limiting plates 811 are arranged inside the mounting disc 81. A movable connecting ball 85 is arranged on each limiting plate 811 through a limiting assembly. A first compression spring 86 is arranged between each connecting ball 85. The first compression spring 86 can buffer and balance each limiting plate 811 and the connecting rod 810. The first compression spring 86 can reduce the amplitude of shaking during lifting, avoid uncontrollable impact during lifting, improve the safety and stability of the gas turbine rotor assembly lifting, and effectively ensure the efficiency of lifting.

[0060] Preferably, referring to Figure 10 The hanging assembly 8 further comprises a mounting ring 82 and a connecting ring 88. The mounting ring 82 is arranged on the mounting disc 81, and each connecting ball 85 is located in the mounting ring 82. The connecting ring 88 is provided with multiple connecting rings 88. The multiple connecting rings 88 are movably arranged on the mounting ring 82. Each connecting ring 88 is arranged one-to-one with each connecting ball 85, and a second compression spring 87 is arranged between adjacent connecting rings 88 and connecting balls 85.

[0061] It can be understood that in order to strengthen the stability of each connecting ball 85, the limiting plate 811 and the connecting rod 810 as a whole, and to reduce the displacement amplitude of shaking, each connecting ball 85 is connected to each connecting ring 88 through the second compression spring 87. The connecting ring 88 is limited by the mounting ring 82. The connecting ball 85 can realize multi-directional buffering and limiting, which is beneficial to improve the anti-seismic performance of the hanging assembly 8 as a whole, and facilitate fine control of the lifting speed.

[0062] Preferably, referring to Figure 10 The mounting disc 81 is provided with a plurality of limiting counterbores arranged in a ring array. The bottom of the mounting ring 82 is provided with a plurality of limiting columns 821 arranged in a ring array. Each limiting column 821 is used to cooperate with each limiting counterbore. A connecting platform is arranged on the limiting column 821. A first connecting screw hole is arranged on the connecting platform. The connecting screw hole is used to arrange a locking screw and cooperate with a second connecting screw hole arranged on the mounting disc 81 through the locking screw to connect and fasten the connecting platform and the mounting disc 81.

[0063] It can be understood that the limiting column 821 not only plays a mounting role of the mounting ring 82. By disassembling the locking screw, the limiting column 821 can be easily removed from the mounting disc 81, that is, the disassembly of the mounting ring 82 can be completed. The limiting column 821 also plays a limiting role of the connecting ring 88, avoiding excessive sliding of the connecting ring 88 along the mounting ring 82, and ensuring the limiting role of the connecting ring 88 to the connecting ball 85.

[0064] Preferably, please refer to Figure 12 As shown, the limiting assembly includes a first limiting piece 83 and a second limiting piece 84, the second limiting piece 84 is arranged on the limiting plate 811, a hemispherical groove is arranged on the top of the second limiting piece 84, the hemispherical groove is used for placing the connecting ball 85, the first limiting piece 83 is arranged on the second limiting piece 84, and the first limiting piece 83 is used for limiting the connecting ball 85.

[0065] It can be understood that the connecting ball 85 is limited by the hemispherical groove on the top of the second limiting piece 84, and the connecting ball 85 can roll in the hemispherical groove, and at the same time, the first limiting piece 83 limits the top of the connecting ball 85, so that the connecting ball 85 can be prevented from falling off without interfering with the movement of the connecting ball 85.

[0066] Optionally, a groove is arranged on the bottom of the first limiting piece 83 for limiting the connecting ball 85, which can enhance the limitation of the connecting ball 85 and ensure smooth rolling; a plurality of limiting rods are arranged on the bottom of the first limiting piece 83, and the limiting rods are connected with the second limiting piece 84 through bolts, which can facilitate the disassembly and assembly of the first limiting piece 83.

[0067] Preferably, please refer to Figure 11 and 13 As shown, a first limiting hole 813 is arranged on the top of the limiting cavity 812, the first limiting hole 813 is used for limiting the second limiting piece 84, and a second limiting hole 814 is arranged on the bottom of the limiting cavity 812, the second limiting hole 814 is used for limiting the connecting rod 810.

[0068] It can be understood that the limiting plate 811 can slide in the limiting cavity 812, and at the same time, the first limiting hole 813 on the top of the limiting cavity 812 can limit the second limiting piece 84, and the second limiting hole 814 on the bottom of the limiting cavity 812 can limit the connecting rod 810, so that the shaking of the hanging assembly 8 caused by excessive movement of the limiting plate 811 can be avoided, and the safety and stability of the lifting process can be ensured.

[0069] The application also discloses an aero-engine rotor lifting method, which adopts the aero-engine rotor lifting device, and includes the following steps:

[0070] S100, placing the gas turbine rotor assembly on the workbench with the rear end upward;

[0071] S200, taking down the limiting ring 2 of the aero-engine rotor lifting device, and extending the clamping jaw 1 into the inner hole of the turbine disc to hook the mounting edge of the inner hole of the turbine disc;

[0072] S300, sequentially passing the limiting ring 2 through the cover plate 5 and the mounting plate 3 to limit the clamping jaw 1, and observing that the limiting platform of the limiting ring 2 should be attached to the top surface of the cover plate 5.

[0073] S400, after the hooking assembly 8 hooks the lifting ring screw 7, the gas turbine rotor assembly is hoisted by cooperation of the hooking assembly 8 and the crane;

[0074] S500, during the lowering of the gas turbine rotor assembly, the center pull rod passes through the limiting ring 2, and after the gas turbine rotor assembly is lowered into place, the hooking assembly 8, the limiting ring 2, and the clamping jaw 1 are taken out in turn.

[0075] The aero-engine rotor hoisting method of the present application also has the above beneficial effects. At the same time, the hoisting method of the present application is very convenient to operate, does not need complicated teaching to workers, and can realize stable hoisting of the gas turbine rotor assembly through simple steps. Only the clamping jaw 1 is first hooked into the inner hole of the turbine disc by extending into the inner hole of the turbine disc, the limiting ring 2 is sequentially passed through the cover plate 5 and the mounting plate 3 to limit the clamping jaw 1, the radial deviation and loosening of the clamping jaw 1 are avoided, and then the gas turbine rotor assembly can be hoisted by cooperation of the hooking assembly 8 and the crane, thereby effectively improving the hoisting efficiency. The method is mainly used to solve the problem of difficult hoisting of the aero-engine gas turbine rotor assembly in the unit body. Through the application of the method and the device, the assembly problem of the gas turbine rotor assembly without a force point in the unit body with a space structure limitation can be solved, and the safe and reliable hoisting of the gas turbine rotor assembly is ensured.

[0076] It should be noted that in this text, the terms "include", "contain" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or device.

[0077] The principles and implementation modes of the present application are described by applying specific examples in this text, and the above example descriptions are only used to help understand the method of the present application and its core idea. The above description is only the preferred implementation mode of the present application. It should be noted that due to the limited nature of the language expression, there are infinite specific structures, and for ordinary skilled persons in the technical field, some improvements, refinements or changes can be made without departing from the principles of the present application, or the technical features described above can be combined in an appropriate manner. These improvements, refinements, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, shall be regarded as the protection of the present application.

Claims

1. An aeroengine rotor hoist device for hoisting a gas turbine rotor assembly comprising a turbine disk, a front shroud, a rear shroud and rotor blades to be assembled with a gas turbine stator assembly to form an engine unit, the unit further comprising a center tie rod for passing through the middle of the gas turbine rotor and connecting with the gas turbine stator assembly, characterized in that, The aero-engine rotor hoisting device comprises a claw (1), a limiting ring (2), a mounting plate (3), a cover plate (5), a lifting ring screw (7) and a hanging assembly (8): The claw (1) is arranged in an annular array outside the limiting ring (2), the claw (1) is used for clamping cooperation with a gas turbine rotor assembly, the mounting plate (3) is used for movably sleeving outside the limiting ring (2) and pressing the claw (1) to be limited outside the limiting ring (2), the cover plate (5) is used for movably sleeving outside the limiting ring (2) and limiting the top of the mounting plate (3), the top of the limiting ring (2) is provided with a limiting platform, the limiting platform is used for limiting the top of the cover plate (5), a plurality of mounting screw holes are arranged in an annular array on the mounting plate (3), the mounting screw holes are used for arranging locking pieces (6) and connecting and fastening the mounting plate (3) and the cover plate (5) through the locking pieces (6) in sequence, and then the top of the claw (1) is pressed and limited in the middle of the mounting plate (3) and the cover plate (5); A plurality of hoisting screw holes are arranged in an annular array on the mounting plate (3), the lifting ring screw (7) comprises a lifting ring and a threaded column, the threaded column is used for screwing with the hoisting screw hole, the lifting ring is used for connecting with the hanging assembly (8), and the hanging assembly (8) is used for connecting with a crane; The hanging assembly (8) comprises a mounting disc (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 arranged in an annular array in the mounting disc (81), a through hole is arranged in the top and the bottom of each limiting cavity (812), the limiting plate (811) is movably arranged in each limiting cavity (812), the bottom of the limiting plate (811) is connected with the connecting rod (810), the connecting rod (810) is used for connecting with the lifting ring screw (7), the limiting assembly is arranged on the top of the limiting plate (811), the connecting ball (85) is movably arranged in the limiting assembly, the limiting assembly is used for limiting the connecting ball (85), a first compression spring (86) is arranged between each connecting ball (85), the connecting column (89) is arranged on the top of the mounting disc (81), and the connecting column (89) is used for connecting with the crane.

2. An aircraft engine rotor hoist as defined in claim 1, wherein, The aero-engine rotor hoisting device further comprises a positioning piece (4), the top of the claw (1) is provided with a lap joint platform, the lap joint platform is used for lap joint on the top of the mounting plate (3), a first connecting through hole is arranged on the lap joint platform, the first connecting through hole is used for corresponding arrangement with a second connecting through hole prearranged on the mounting plate (3), and the positioning piece (4) is used for sequentially penetrating through the first connecting through hole and the second connecting through hole to position the mounting plate (3) and the claw (1); the bottom of the claw (1) is provided with a clamping part, and the clamping part is used for hooking an installation edge prearranged in a rear end inner hole of a turbine disc.

3. An aircraft engine rotor hoist as defined in claim 2 wherein, The first connecting through hole is a through hole with a strip-shaped cross section, and the second connecting through hole is a round hole structure.

4. An aircraft engine rotor hoist as defined in claim 1 wherein, A supporting boss is arranged on the bottom of the limiting ring (2), the supporting boss is used for limiting the bottom of the claw (1) to make the bottom of the claw (1) outwardly deviate along the radial direction of the limiting ring (2).

5. An aircraft engine rotor hoist as defined in claim 1 wherein, The hanging assembly (8) further comprises a mounting ring (82) and a plurality of connecting rings (88), the mounting ring (82) is arranged on the mounting disc (81) and each connecting ball (85) is located in the mounting ring (82), the connecting rings (88) are provided with a plurality of connecting rings (88), the plurality of connecting rings (88) are movably sleeved on the mounting ring (82), each connecting ring (88) is arranged in 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).

6. An aircraft engine rotor hoist as defined in claim 5 wherein, A plurality of limiting holes are arranged in an annular array on the mounting disc (81), a plurality of limiting columns (821) are arranged in an annular array on the bottom of the mounting ring (82), each limiting column (821) is used for cooperation with each limiting hole, a connecting platform is arranged on the limiting column (821), a first connecting hole is arranged on the connecting platform, the first connecting hole is used for arranging a locking screw and cooperating with a second connecting hole arranged on the mounting disc (81) through the locking screw, so as to connect and fasten the connecting platform and the mounting disc (81).

7. An aircraft engine rotor hoist as defined in claim 1 wherein, The limiting assembly comprises a first limiting piece (83) and a second limiting piece (84), the second limiting piece (84) is arranged on the limiting plate (811), a hemispherical recess is arranged on the top of the second limiting piece (84), the hemispherical recess is used for placing the connecting ball (85), and the first limiting piece (83) is arranged on the second limiting piece (84) and is used for limiting the connecting ball (85).

8. An aircraft engine rotor hoist as defined in claim 7, wherein, A first limiting hole (813) is arranged on the top of the limiting cavity (812) and is used for limiting the second limiting piece (84), and a second limiting hole (814) is arranged on the bottom of the limiting cavity (812) and is used for limiting the connecting rod (810).

9. An aircraft engine rotor hoisting method using the aircraft engine rotor hoisting device according to any one of claims 1 to 8, characterized by, It comprises the following steps: S100, placing the gas turbine rotor assembly on the workbench with the rear end upward; S200, removing the limiting ring (2) of the aero-engine rotor hoisting device, and hooking the pawl (1) into the turbine disc inner hole to hook the turbine disc inner hole mounting edge; S300, then the limiting ring (2) passes through the cover plate (5) and the mounting plate (3) in turn, and the pawl (1) is limited, and it is observed that the limiting platform of the limiting ring (2) is attached to the top surface of the cover plate (5); S400, after hooking the lifting eye screw (7) with the hanging assembly (8), the gas turbine rotor assembly is hoisted by cooperating the hanging assembly (8) with the crane; S500, during the descending process of the gas turbine rotor assembly, the center pull rod passes through the limiting ring (2), and after the gas turbine rotor assembly is lowered into position, the hanging assembly (8), the limiting ring (2) and the pawl (1) are taken out in turn.

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