Dismounting device for gas compressor blade of gas turbine

Abstract

The invention relates to the technical field of press machine blade dismounting, in particular to a gas turbine compressor blade dismounting device which comprises a main body component, a first fixing seat, a second fixing seat, a first rotating shaft and a second rotating shaft. The dismounting part comprises a dismounting assembly arranged on the first fixing base, the dismounting assembly penetrates through the second fixing base, and a positioning piece arranged at the end of the dismounting assembly; the compressor blade can be disassembled without manual operation, time and labor are saved, efficiency is improved, the overhaul period is prevented from being affected, safety is improved, and damage to the surfaces of the compressor blade and an impeller is reduced.

Description

Technical Field

[0001] The invention relates to the technical field of press blade disassembly, in particular to a combustion engine compressor blade disassembly device. Background Art

[0002] The compressor blades are key components of the gas turbine. The reliability of their operation has a direct impact on the safe and stable operation of the unit. The compressor blades are dovetail-shaped and connected to the compressor impeller blade root groove. They are usually subjected to centrifugal force, airflow excitation force, etc., and the working conditions are very complex. Based on this, in order to ensure the safe, economical and stable operation of the gas turbine, the compressor blades should be inspected and repaired regularly when the number of starts and stops and the number of operating hours of the gas turbine reach a certain number. When the blades are cracked, broken or damaged, they should be replaced in time. At present, the main way to disassemble the compressor blades is manual by the operator. The disassembly is carried out in an operation-based manner. The general steps are: one operator holds a wedge of different shapes to align with the root of the blade, and the other operator holds a hammer and hits the wedge with different forces from the exhaust side to the intake side until the blade slides off from the intake side. Since this method is greatly affected by the operator's proficiency, coordination, emotions, etc., the efficiency is low. Moreover, since there are a large number of compressor blades, a lot of manpower and time are required for disassembly, which affects the maintenance period. In addition, since the angle of the hammer's attack is random, it will cause damage to the operator's safety and the surface of the blade and impeller. Summary of the invention

[0003] In view of the above problems existing in the prior art, the present invention is proposed.

[0004] Therefore, an object of the present invention is to provide a combustion engine compressor blade disassembly device.

[0005] In order to solve the above technical problems, the present invention provides the following technical solutions: including a main body component, which includes a fixing seat one and a fixing seat two; a disassembly component, which includes a disassembly component arranged on the fixing seat one, the disassembly component passes through the fixing seat two, and a positioning piece arranged at the end of the disassembly component.

[0006] As a preferred solution of the gas engine compressor blade disassembly device of the present invention, wherein: the lower sides of the fixing seat 1 and the fixing seat 2 are fixedly connected with a magnet 1, and the lower side of the magnet is fixedly connected with a rubber gasket 1.

[0007] As a preferred solution of the gas turbine compressor blade disassembly device of the present invention, the disassembly assembly includes a jack arranged on the fixing seat 1, a rubber gasket 2 is fixedly connected to the side wall of the jack, and the jack is connected to a control box via a cable.

[0008] As a preferred solution of the gas turbine compressor blade disassembly device of the present invention, wherein: a laser lamp is fixedly installed on the side wall of the positioning member, and a rubber gasket three is fixedly connected to the side wall of the positioning member.

[0009] As a preferred solution of the gas engine compressor blade disassembly device of the present invention, it also includes a stabilizing component, which includes a connecting seat arranged on a side wall of the fixing seat, a rotating component arranged on the connecting seat, and a stabilizing component arranged on the rotating component.

[0010] As a preferred solution of the gas engine compressor blade disassembly device of the present invention, wherein: the side wall of the connecting seat is fixedly connected to a connecting block, and the side wall of the connecting block is fixedly connected to a supporting ring.

[0011] As a preferred solution of the gas engine compressor blade disassembly device of the present invention, wherein: the rotating assembly includes a rotating ring arranged in the supporting ring, the outer surface of the rotating ring is fixedly connected to a fixing ring, the inner side wall of the rotating ring is slidably connected to a spline shaft, the outer surface of the spline shaft is fixedly connected to a spline block, the inner side wall of the rotating ring is provided with a spline groove matched with the spline block, the side wall of the spline shaft is fixedly connected to a connecting piece, and the side wall of the connecting piece is fixedly connected to a turning handle.

[0012] As a preferred solution of the gas engine compressor blade disassembly device of the present invention, the stabilizing assembly includes a stabilizing plate 1 arranged on the outer surface of the fixing ring, a through sliding groove is opened on one side wall of the stabilizing plate, a sliding seat is slidably connected in the through sliding groove, a stabilizing plate 2 is fixedly connected to the side wall of the sliding seat, a magnet 2 is fixedly connected to the lower side of the stabilizing plate 2, and a rubber gasket 4 is fixedly connected to the lower side of the magnet 2.

[0013] As a preferred solution of the gas engine compressor blade disassembly device of the present invention, the stabilizing component also includes a fixing assembly 1, which includes a fixed tooth block arranged on the side wall of one of the connecting parts, one of the side walls of the supporting ring is provided with a fixed tooth groove matched with the fixed tooth block, one of the outer surface of the connecting parts is rotatably connected to a swivel seat, the side wall of the swivel seat is slidably connected to a sliding rod, and the side wall of the rotating ring is fixedly connected to a spring.

[0014] As a preferred solution of the gas engine compressor blade disassembly device of the present invention, the stabilizing component also includes a fixing component 2, which includes a sliding groove arranged on the side wall of the sliding seat, a sliding block is slidably connected in the sliding groove, a connecting plate is fixedly connected to the side wall of the sliding block, a fixing column is fixedly connected to the side wall of the connecting plate, and a fixing groove is opened on one side wall of the stabilizing plate.

[0015] The beneficial effects of the gas engine compressor blade disassembly device of the present invention are as follows: by setting the main body components and the disassembly components, the compressor blades can be disassembled without manual operation, which saves time and effort, improves efficiency, avoids affecting the maintenance period, improves safety, and reduces damage to the surfaces of the compressor blades and impellers. By setting the stabilizing components, the stability during the disassembly of the compressor blades can be improved, and the damage to the surfaces of the compressor blades and impellers can be reduced, further improving safety and solving the problems existing in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0017] Figure 1 This is an overall schematic diagram of the gas turbine compressor blade removal device.

[0018] Figure 2 This is an overall schematic diagram of the gas turbine compressor blade removal device.

[0019] Figure 3 This is an overall schematic diagram of the connecting seat of the gas turbine compressor blade removal device.

[0020] Figure 4 This is an overall schematic diagram of the stabilizing components of the gas turbine compressor blade removal device.

[0021] Figure 5 This is a schematic diagram of the structural connection of the stabilizing components of the gas turbine compressor blade removal device.

[0022] Figure 6 This is a schematic diagram of the partial structural connections of a gas turbine compressor blade disassembly device.

[0023] Figure 7 This is a schematic diagram of the partial structural connections of a gas turbine compressor blade disassembly device.

[0024] In the figure: 100, main part; 101, fixing seat 1; 102, fixing seat 2; 103, magnet 1; 104, rubber gasket 1; 200, disassembly part; 201, disassembly assembly; 201a, jack; 201b, rubber gasket 2; 201c, control box; 202, positioning piece; 202a, laser light; 202b, rubber gasket 3; 300, stabilizing part; 301, connecting seat; 301a, connecting block; 301b, supporting ring; 302, rotating assembly; 302a, rotating ring; 302b, fixing ring; 302c, spline shaft; 302d, spline block ; 302e, spline groove; 302f, connecting piece; 302g, turning handle; 303, stabilizing component; 303a, stabilizing plate one; 303b, through slide groove; 303c, sliding seat; 303d, stabilizing plate two; 303e, magnet two; 303f, rubber gasket four; 304, fixing component one; 304a, fixed tooth block; 304b, fixed tooth groove; 304c, rotating seat; 304d, sliding rod; 304e, spring; 305, fixing component two; 305a, sliding groove; 305b, sliding block; 305c, connecting plate; 305d, fixing column; 305e, fixing groove. DETAILED DESCRIPTION

[0025] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below in conjunction with the accompanying drawings.

[0026] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0027] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The term "in one embodiment" that appears in different places in this specification does not necessarily refer to the same embodiment, nor is it a separate or selective embodiment that is mutually exclusive with other embodiments.

[0028] Example 1

[0029] Reference Figure 1, is the first embodiment of the present invention, which provides a gas turbine compressor blade disassembly device, which includes a main part 100, which includes a fixing seat 101 and a fixing seat 102; a disassembly part 200, which includes a disassembly component 201 arranged on the fixing seat 101, the disassembly component 201 passes through the fixing seat 102, and a positioning member 202 arranged at the end of the disassembly component 201; the fixing seat 101 and the fixing seat 102 are both fixedly connected to the lower side with a magnet 103, and the lower side of the magnet 103 is fixedly connected to a rubber gasket 104.

[0030] Specifically, both the fixing seat 101 and the fixing seat 2 102 are fixed to the compressor impeller through the magnet 103, and can also be fixed to the compressor impeller through the fixing seat 101 and the fixing seat 2 102 by bolts, but the use of bolts requires tightening, which is cumbersome and cannot quickly fix the fixing seat 101 and the fixing seat 2 102 to the compressor impeller. The magnet 103 can rely on magnetic force to increase the fixation effect, and the rubber gasket 104 wraps the magnet 103, mainly to prevent the magnet from falling off and falling into the cylinder body and to prevent the wheel from being damaged by hard objects. The main function of the positioning member 202 is to fix the disassembly component 201 and provide a relatively stable triangular structure for the disassembly component 201, so that the disassembly component 201 will not deviate from the preset angle and cause damage to the compressor blades and the compressor impeller during the process of pushing the blades.

[0031] When in use, first, plan the trajectory of the blade from the outlet side to the inlet side, so that the disassembly component 201 is aligned with the root position of the blade, and then measure the height difference between the compressor blade root and the compressor impeller disk, fix the fixing seat 101 and the fixing seat 2 102 on the compressor impeller disk through the magnet 103, and fix the position of the fixing seat 101 and the fixing seat 2 102 with the suction force of the magnet, and then the compressor blade can be disassembled through the disassembly component 201.

[0032] Example 2

[0033] Reference Figure 1-2 , which is the second embodiment of the present invention. Different from the previous embodiment, this embodiment provides a gas turbine compressor blade disassembly device, which includes a disassembly component 201 including a jack 201a arranged on a fixing seat 101, a rubber gasket 201b is fixedly connected to the side wall of the jack 201a, and the jack 201a is connected to a control box 201c through a cable.

[0034] Specifically, three jacks 201a are provided, and the three jacks 201a form a triangular shape. The three jacks 201a are extended and retracted by inferring the trajectory and force of the compressor blades. The rubber gasket 201b prevents damage to the compressor blades. The control box 201c mainly controls the working status of the three jacks 201a. This is the existing technology and will not be elaborated here.

[0035] Furthermore, a laser lamp 202a is fixedly mounted on the side wall of the positioning member 202, and a rubber gasket 202b is fixedly connected to the side wall of the positioning member 202.

[0036] Specifically, three laser lamps 202a are provided, and the three laser lamps 202a form a triangular shape. The laser lamp 202a is used to check the trajectory to ensure that it does not shift during the pushing process. The function of the rubber gasket 202b is to prevent it from causing damage such as collision to the compressor blades during the process of pushing the compressor blades.

[0037] When in use, in conjunction with Example 1, the trajectory is first detected by the laser light 202a, and then the three jacks 201a are controlled to extend and retract through the control box 201c, so that the telescopic end of the jack 201a drives the rubber gasket three 202b to push the blade, thereby realizing the disassembly of the blade. There is no need for manual disassembly of the compressor blade, which saves time and effort, improves efficiency, avoids affecting the maintenance period, improves safety, and reduces damage to the surface of the compressor blade and the impeller.

[0038] Example 3

[0039] Reference Figure 2 to Figure 5 , which is the third embodiment of the present invention. Different from the previous embodiment, this embodiment provides a gas turbine compressor blade disassembly device, which also includes a stabilizing component 300, which includes a connecting seat 301 arranged on the side wall of the fixing seat 101, a rotating component 302 arranged on the connecting seat 301, and a stabilizing component 303 arranged on the rotating component 302; the side wall of the connecting seat 301 is fixedly connected with a connecting block 301a, and the side wall of the connecting block 301a is fixedly connected with a supporting ring 301b.

[0040] Specifically, two connection blocks 301 a are provided, and the two connection blocks 301 a are symmetrically arranged.

[0041] Furthermore, the rotating assembly 302 includes a rotating ring 302a disposed in the supporting ring 301b, the outer surface of the rotating ring 302a is fixedly connected to the fixed ring 302b, the inner side wall of the rotating ring 302a is slidably connected to the spline shaft 302c, the outer surface of the spline shaft 302c is fixedly connected to the spline block 302d, the inner side wall of the rotating ring 302a is provided with a spline groove 302e adapted to the spline block 302d, the side wall of the spline shaft 302c is fixedly connected to the connecting piece 302f, and the connecting piece The side wall of 302f is fixedly connected with a turning handle 302g; the stabilizing component 303 includes a stabilizing plate 303a arranged on the outer surface of the fixing ring 302b, the side wall of the stabilizing plate 303a is provided with a through sliding groove 303b, a sliding seat 303c is slidably connected in the through sliding groove 303b, the side wall of the sliding seat 303c is fixedly connected with a stabilizing plate 2 303d, the lower side of the stabilizing plate 2 303d is fixedly connected with a magnet 2 303e, and the lower side of the magnet 2 303e is fixedly connected with a rubber gasket 4 303f.

[0042] Among them, the rotating ring 302a is rotatably connected to the inner walls of the two supporting rings 301b, six spline blocks 302d and six spline grooves 302e are each provided, and the six spline blocks 302d and the six spline grooves 302e are distributed in a ring array, two connecting members 302f are provided, and the two connecting members 302f are symmetrically arranged, the stabilizing plate 2 303d is slidably connected to the stabilizing plate 1 303a through the sliding seat 303c and the through sliding groove 303b, the stabilizing plate 2 303d is fixed to the compressor impeller disc through the magnet 2 303e, and the rubber gasket 4 303f prevents the disc from being damaged by hard objects.

[0043] When in use, the connecting piece 302f is rotated by turning the handle 302g to drive the spline shaft 302c to rotate, so that the rotating ring 302a, under the action of the spline block 302d and the spline groove 302e, drives the fixed ring 302b and the stabilizing plate 1 303a to rotate along with the spline shaft 302c, so as to drive the stabilizing plate 2 303d to rotate, so as to adjust the angle of the stabilizing plate 2 303d, and move the stabilizing plate 2 303d up and down, so that the stabilizing plate 2 303d slides up and down to a suitable position under the action of the sliding seat 303c and the through sliding groove 303b, and then the stabilizing plate 2 303d is fixed to the compressor impeller disk through the magnet 2 303e. The stabilizing plate 1 303a and the stabilizing plate 2 303d can form a triangle shape with the fixing seat 101, which plays a more stable role, improves the stability when disassembling the compressor blades, reduces the damage to the surface of the compressor blades and the impeller, and further improves the safety.

[0044] Example 4

[0045] Reference Figure 3 to Figure 7, which is the fourth embodiment of the present invention. Different from the previous embodiment, this embodiment provides a gas turbine compressor blade disassembly device, which also includes a fixing assembly 304, which includes a fixing tooth block 304a arranged on the side wall of one of the connecting members 302f, a fixing tooth groove 304b adapted to the fixing tooth block 304a is opened on the side wall of one of the supporting rings 301b, a rotating seat 304c is rotatably connected to the outer surface of one of the connecting members 302f, a sliding rod 304d is slidably connected to the side wall of the rotating seat 304c, and a spring 304e is fixedly connected to the side wall of the rotating ring 302a;

[0046] Among them, the fixed tooth block 304a and the fixed tooth groove 304b are both arranged in a ring shape, the fixed tooth block 304a and the fixed tooth groove 304b are plug-connected, the spring 304e is fixedly connected to the inner wall of one of the connecting parts 302f, the spline shaft 302c is located in the spring 304e, and the side wall of the swivel seat 304c is provided with a sliding groove adapted to the sliding rod 304d, and the sliding rod 304d is arranged in a stem shape.

[0047] Furthermore, the stabilizing component 300 also includes a fixing component 2 305, which includes a sliding groove 305a arranged on the side wall of the sliding seat 303c, a sliding block 305b is slidably connected in the sliding groove 305a, a connecting plate 305c is fixedly connected to the side wall of the sliding block 305b, a fixing column 305d is fixedly connected to the side wall of the connecting plate 305c, and a fixing groove 305e is opened on the side wall of the stabilizing plate 1 303a.

[0048] Among them, there are two fixed columns 305d, and the two fixed columns 305d are symmetrically arranged. There are multiple fixed grooves 305e, and the multiple fixed grooves 305e are equidistantly distributed. The fixed column 305d is plug-connected with the fixed groove 305e, the connecting plate 305c is rotatably connected with the sliding rod 304d, and the side wall of the sliding seat 303c is provided with a fixed slot matched with the fixed column 305d, and the fixed slot is plug-connected with the fixed column 305d.

[0049] When in use, in conjunction with Example 3, before rotating the rotating ring 302a, it is necessary to turn the handle 302g forward so that the spline shaft 302c drives the spline block 302d to move forward in the rotating ring 302a under the action of the spline groove 302e, so that the connecting member 302f moves forward, and the spring 304e is squeezed and compressed by one of the connecting members 302f to deform and generate a reaction force, so that the connecting member 302f drives the fixed tooth block 304a to disengage from the fixed tooth groove 304b. At this time, the rotating ring 302a can be adjusted in angle by the handle 302g. At the same time, when the connecting member 302f moves forward, it will drive the rotating seat 304c to move forward, and the sliding rod 304d will move forward with the rotating seat 304c driving the connecting plate 305c under the action of the sliding block 305b and the sliding groove 305a. , so that the fixed column 305d is disengaged from the corresponding fixed groove 305e. When the angle adjustment and stabilizing plate 2 303d slide up and down to the appropriate position, the turning handle 302g is released. Under the action of the spring 304e, the connecting member 302f will drive the spline shaft 302c and the fixed tooth block 304a to move backward, so that the fixed tooth block 304a is inserted into the fixed tooth groove 304b, thereby fixing the angle of the connecting member 302f and the spline shaft 302c to fix the angle of the rotating ring 302a. At the same time, the rotating seat 304c will move backward with the connecting member 302f driving the sliding rod 304d and the connecting plate 305c, so that the fixed column 305d is inserted into the corresponding fixed groove 305e, thereby fixing the position of the sliding seat 303c to fix the position of the stabilizing plate 2 303d, thereby playing a more stable role.

[0050] Importantly, it should be noted that the construction and arrangement of the present application shown in a plurality of different exemplary embodiments are only exemplary. Although only a few embodiments are described in detail in this disclosure, it should be readily understood by those who refer to this disclosure that many modifications are possible (e.g., the size, scale, structure, shape and proportion of various elements, as well as parameter values ​​(e.g., temperature, pressure, etc.), mounting arrangements, use of materials, color, directional changes, etc.) without substantially departing from the novel teachings and advantages of the subject matter described in the application. For example, the element shown as integrally formed can be composed of multiple parts or elements, the position of the element can be inverted or otherwise changed, and the nature or number or position of the discrete element can be changed or changed. Therefore, all such modifications are intended to be included in the scope of the present invention. The order or sequence of any process or method steps can be changed or reordered according to alternative embodiments. In the claims, any "device plus function" clause is intended to cover the structure described herein that performs the function, and is not only structurally equivalent but also equivalent structure. Without departing from the scope of the present invention, other replacements, modifications, changes and omissions can be made in the design, operating conditions and arrangement of the exemplary embodiments. Therefore, the invention is not limited to a specific embodiment, but extends to numerous modifications still falling within the scope of the appended claims.

[0051] Additionally, in order to provide a concise description of exemplary embodiments, all features of an actual embodiment (ie, those features that are not relevant to the best mode presently contemplated for carrying out the invention or those that are not relevant to implementing the invention) may not be described.

[0052] It will be appreciated that in the development of any actual implementation, as in any engineering or design project, numerous implementation-specific decisions may be made. Such a development effort may be complex and time-consuming, but will be a routine task of design, fabrication, and production for those of ordinary skill having the benefit of this disclosure without undue experimentation.

[0053] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, which should all be included in the scope of the claims of the present invention.

Claims

1. A gas turbine compressor blade disassembly device, characterized in that: include, A main body component (100), comprising a fixing seat 1 (101) and a fixing seat 2 (102); The disassembly component (200) comprises a disassembly assembly (201) arranged on the first fixing seat (101), the disassembly assembly (201) passing through the second fixing seat (102), and a positioning piece (202) arranged at the end of the disassembly assembly (201).

2. The gas engine compressor blade disassembly device according to claim 1, characterized in that: The lower sides of the fixing seat 1 (101) and the fixing seat 2 (102) are both fixedly connected with a magnet 1 (103), and the lower side of the magnet 1 (103) is fixedly connected with a rubber gasket 1 (104).

3. The gas engine compressor blade disassembly device according to claim 2, characterized in that: The disassembly assembly (201) comprises a jack (201a) arranged on the first fixing seat (101), a second rubber gasket (201b) being fixedly connected to the side wall of the jack (201a), and the jack (201a) is connected to a control box (201c) via a cable.

4. The gas engine compressor blade disassembly device according to claim 3, characterized in that: A laser lamp (202a) is fixedly mounted on the side wall of the positioning member (202), and a rubber gasket three (202b) is fixedly connected to the side wall of the positioning member (202).

5. The gas engine compressor blade disassembly device according to claim 4, characterized in that: It also includes a stabilizing component (300), which includes a connecting seat (301) arranged on a side wall of the fixing seat (101), a rotating component (302) arranged on the connecting seat (301), and a stabilizing component (303) arranged on the rotating component (302).

6. The gas engine compressor blade disassembly device according to claim 5, characterized in that: A connecting block (301a) is fixedly connected to the side wall of the connecting seat (301), and a supporting ring (301b) is fixedly connected to the side wall of the connecting block (301a).

7. The gas engine compressor blade disassembly device according to claim 6, characterized in that: The rotating assembly (302) comprises a rotating ring (302a) arranged in the supporting ring (301b), the outer surface of the rotating ring (302a) is fixedly connected to a fixing ring (302b), the inner side wall of the rotating ring (302a) is slidably connected to a spline shaft (302c), the outer surface of the spline shaft (302c) is fixedly connected to a spline block (302d), the inner side wall of the rotating ring (302a) is provided with a spline groove (302e) adapted to the spline block (302d), the side wall of the spline shaft (302c) is fixedly connected to a connecting piece (302f), and the side wall of the connecting piece (302f) is fixedly connected to a turning handle (302g).

8. The gas engine compressor blade disassembly device according to claim 7, characterized in that: The stabilizing component (300) comprises a stabilizing plate 1 (303a) arranged on the outer surface of a fixing ring (302b), a through-slide groove (303b) being provided on the side wall of the stabilizing plate 1 (303a), a sliding seat (303c) being slidably connected in the through-slide groove (303b), a stabilizing plate 2 (303d) being fixedly connected to the side wall of the sliding seat (303c), a magnet 2 (303e) being fixedly connected to the lower side of the stabilizing plate 2 (303d), and a rubber gasket 4 (303f) being fixedly connected to the lower side of the magnet 2 (303e).

9. The gas engine compressor blade disassembly device according to claim 8, characterized in that: The stabilizing component (300) further comprises a fixing assembly 1 (304), which comprises a fixing tooth block (304a) arranged on the side wall of one of the connecting members (302f), a fixing tooth groove (304b) matching the fixing tooth block (304a) is opened on the side wall of one of the supporting rings (301b), a rotating seat (304c) is rotatably connected to the outer surface of one of the connecting members (302f), a sliding rod (304d) is slidably connected to the side wall of the rotating seat (304c), and a spring (304e) is fixedly connected to the side wall of the rotating ring (302a).

10. The gas engine compressor blade disassembly device according to claim 9, characterized in that: The stabilizing component (300) further comprises a second fixing component (305), which comprises a sliding groove (305a) arranged on the side wall of the sliding seat (303c), a sliding block (305b) being slidably connected in the sliding groove (305a), a connecting plate (305c) being fixedly connected to the side wall of the sliding block (305b), a fixing column (305d) being fixedly connected to the side wall of the connecting plate (305c), and a fixing groove (305e) being formed on the side wall of the stabilizing plate 1 (303a).

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