Gas turbine compressor blade dismounting device and application method

Abstract

The invention relates to the technical field of dismounting devices, in particular to a gas turbine compressor blade dismounting device and an application method.The gas turbine compressor blade dismounting device comprises a supporting component, a bottom plate, a wheel disc arranged on the lower side of the bottom plate, a first tool arranged on the front side of the bottom plate and a second tool arranged on the rear side of the first tool; the laser lamp is arranged on the first tool, the jack is arranged on the second tool, the mounting opening is formed in the first tool, and the pressure sensor is arranged on the jack; the scraping component comprises a bearing assembly arranged on the bottom plate, a scraping assembly arranged on the bearing assembly, a transmission assembly arranged on the scraping assembly and a deflection assembly arranged on the transmission assembly; by means of the device, the gas turbine compressor blade can be conveniently and rapidly disassembled, and the stability of the ejection angle of the jack can be guaranteed during disassembling.

Description

Technical Field

[0001] The present invention relates to the technical field of disassembly devices, and in particular to a disassembly device for a gas turbine compressor blade and an application method thereof. Background Art

[0002] The compressor blade is a key component of a gas turbine, and its working reliability has a direct impact on the safe and stable operation of the unit. The moving blade of the compressor is in a dovetail shape and is connected to the root groove of the compressor impeller. It is usually affected by centrifugal force, gas flow excitation force, etc., and the working conditions are very complex. Based on this, to ensure the safe, economical, and stable operation of the gas turbine, when the number of starts and stops and the running hours of the gas turbine reach a certain amount, the compressor blades should be regularly inspected. When the blades are damaged such as cracked or broken, it is necessary to replace the blades in time, so the disassembly of the blades is required.

[0003] During the disassembly process, the disassembly is mainly carried out by manual operation of the operator. The general steps are as follows: one operator holds wedges of different shapes and aligns them with the root position of the blade, while another operator holds a hammer and applies different forces to strike the wedge from the air outlet side to the air inlet side until the blade slides off from the air inlet side. Since this method is greatly affected by the operator's operation proficiency, cooperation, mood, etc., the efficiency is low. Moreover, since there are a large number of compressor blades, a large amount of manpower and time are required for disassembly, which affects the maintenance period. And because the angle of the hammer strike is random, it will cause harm to the safety of the operator and the surfaces of the blade and the impeller. Summary of the Invention

[0004] In view of the problems in the prior art that the disassembly of the gas turbine compressor blades by manual operation of the operator has low efficiency, takes a long time, affects the construction period, and the angle of the hammer strike is random, which will cause harm to the safety of the operator and the surfaces of the blade and the impeller, the present invention is proposed.

[0005] Therefore, the object of the present invention is to provide a disassembly device for a gas turbine compressor blade.

[0006] To solve the above technical problems, the present invention provides the following technical solutions: It includes a support component, which includes a bottom plate, a wheel disc arranged on the lower side of the bottom plate, a first tooling arranged on the front side of the bottom plate, a second tooling arranged on the rear side of the first tooling, a laser lamp arranged on the first tooling, a jack arranged on the second tooling, an installation opening arranged on the first tooling, and a pressure sensor arranged on the jack; a scraping component, which includes a bearing component arranged on the bottom plate, a scraping component arranged on the bearing component, a transmission component arranged on the scraping component, and a deflection component arranged on the transmission component; a stabilizing component, which includes an air extraction component arranged on the first tooling, and a negative pressure component arranged on the air extraction component; a strengthening component, which includes an expansion component arranged on the scraping component, and an anti-slip component arranged on the expansion component.

[0007] As a preferred solution of the gas turbine compressor blade disassembly device of the present invention, wherein: the bearing component includes a receiving groove arranged on the bottom plate, an installation frame fixedly connected in the receiving groove, a slider slidably connected in the installation frame, the slider is elastically connected to the inner wall of the installation frame through a first spring, a fixed block is fixedly connected to the inner side wall of the receiving groove, an arc plate is fixedly connected to the fixed block, a connecting block is fixedly connected to the side wall of the bottom plate, a support plate is rotatably connected to the connecting block through a transmission shaft, and magnets are arranged on the arc plate, the support plate and the first tooling.

[0008] As a preferred solution of the gas turbine compressor blade disassembly device of the present invention, wherein: the scraping component includes a vertical plate fixedly connected to the slider, the arc plate is arranged on the front side of the vertical plate, a triangular block is arranged on the vertical plate, and a scraper is arranged on the triangular block.

[0009] As a preferred solution of the gas turbine compressor blade disassembly device of the present invention, wherein: the transmission component includes an installation cavity arranged in the vertical plate, a rotating shaft rotatably connected in the installation cavity, the rotating shaft penetrates through the vertical plate and is rotatably connected to the vertical plate, the rotating shaft is fixedly connected to the triangular block, two limiting plates are fixedly connected in the installation cavity, extension grooves are arranged on both of the two limiting plates, extension blocks are slidably connected in the extension grooves, the extension blocks are elastically connected to the inner walls of the extension grooves through second springs, a strip-shaped opening is arranged on the vertical plate, a cylinder matched with the strip-shaped opening is fixedly connected to the extension block, a guiding plate is fixedly connected to the installation frame, and a cutting edge matched with the cylinder is arranged on the guiding plate.

[0010] As a preferred solution of the gas turbine compressor blade disassembly device of the present invention, wherein: the deflection component includes an arc-shaped groove arranged on the rotating shaft, a spherical ball slides in the arc-shaped groove, and the spherical ball is fixedly connected to the cylinder.

[0011] As a preferred embodiment of the gas turbine compressor blade disassembly device of the present invention, the air extraction assembly includes an air extraction cylinder fixedly connected to the second tooling. A piston is hermetically and slidably connected within the air extraction cylinder. A moving column is fixedly connected to the piston. The moving column penetrates through the air extraction cylinder and is hermetically and slidably connected to the air extraction cylinder. A communication port is provided on the first tooling. A clamping block is fixedly connected to the telescopic end of the jack. A limiting ring is fixedly connected to the moving column. A clamping groove matching with the clamping block is provided on the limiting ring.

[0012] As a preferred embodiment of the gas turbine compressor blade disassembly device of the present invention, the negative pressure assembly includes an air storage cavity provided on the arc-shaped plate. A plurality of suction cups are communicated with the air storage cavity. A negative pressure port communicating with the air storage cavity is provided on the suction cup. The end of the air extraction cylinder away from the limiting ring is hermetically communicated with the air storage cavity through a first pipeline.

[0013] As a preferred embodiment of the gas turbine compressor blade disassembly device of the present invention, the expansion assembly includes an inner groove provided on the triangular block. A cross plate is fixedly connected within the inner groove. A moving plate is hermetically and slidably connected to the cross plate. A sealed space is formed among the moving plate, the cross plate and the inner groove. The outer end of the air extraction cylinder is hermetically communicated with the sealed space through a second pipeline. The moving plate is elastically connected to the inner wall of the inner groove through a third spring.

[0014] As a preferred embodiment of the gas turbine compressor blade disassembly device of the present invention, the anti-slip assembly includes a toothed plate fixedly connected to the moving plate. A bearing shaft is rotatably connected within the inner groove. An arc-shaped friction pad is fixedly connected to the bearing shaft. A gear meshing with the toothed plate is fixedly connected to the bearing shaft.

[0015] An application method includes planning the trajectory of pushing the blade from the air outlet side to the air inlet side; aligning the head positions of three jacks with the blade root position; placing the first tooling at a suitable position; using a laser lamp to check the trajectory to ensure no displacement during the pushing process; measuring the height difference between the blade root and the wheel disc, and placing the second tooling at a suitable position; measuring the width between two-stage wheel discs, and pressing the bottom plate on the wheel disc according to the adjusted position; fixing the position of the bottom plate by the suction force of a magnet and making the bottom plate stable through negative pressure; then adjusting the angular position of the support plate and the bottom plate, and fixing the position of the bottom plate by borrowing the suction force of the magnet; using a laser lamp to recheck the position and angle; after checking without error, performing the blade disassembly work through the jack control cabinet.

[0016] Advantages of the present invention: By providing a support component, the removal of the gas turbine compressor blades can be carried out by the way of jacking out, without the need for workers to hammer for removal, which is more convenient to use. And when pushing, it is also corrected by a laser lamp and a pressure sensor to avoid deviation. At the same time, when fixing the bottom plate, it is fixed by a magnet, which is convenient to use. At the same time, when the jack moves, the stability of the bottom plate can be further ensured by the negative pressure method, ensuring the stability when the jack jacks out, thus solving the problems that the removal efficiency of the gas turbine compressor blades by the manual operation of the operator is relatively low, time-consuming, affecting the construction period, and the angle of hammering is random, which will cause harm to the safety of the operator and the surfaces of the blades and the impeller, achieving the effect of convenient removal of the gas turbine compressor blades and no deviation during removal. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0018] Figure 1 It is an overall schematic diagram of the gas turbine compressor blade removal device.

[0019] Figure 2 It is Figure 1 An enlarged schematic diagram of the structure at A of

[0020] Figure 3 It is an external structural schematic diagram of the gas turbine compressor blade removal device.

[0021] Figure 4 It is a cross-sectional structural schematic diagram of the bearing assembly of the gas turbine compressor blade removal device.

[0022] Figure 5 It is a cross-sectional structural schematic diagram of the transmission assembly of the gas turbine compressor blade removal device.

[0023] Figure 6 It is a cross-sectional structural schematic diagram of the deflection assembly of the gas turbine compressor blade removal device.

[0024] Figure 7 It is a cross-sectional view of the air extraction assembly of the gas turbine compressor blade removal device.

[0025] Figure 8 It is a cross-sectional structural schematic diagram of the arc plate of the gas turbine compressor blade removal device.

[0026] Figure 9 It is an external structural schematic diagram of the triangular block of the gas turbine compressor blade removal device.

[0027] Figure 10 is Figure 9 the enlarged schematic diagram of the structure at position B.

[0028] Figure 11 is the sectional view of the reinforcement component of the gas turbine compressor blade disassembly device.

[0029] In the figure: 100, support component; 101, bottom plate; 102, wheel disc; 103, first tooling; 104, second tooling; 105, laser lamp; 106, jack; 107, installation port; 108, pressure sensor; 200, scraping component; 201, bearing assembly; 201a, receiving groove; 201b, installation frame; 201c, slider; 201d, first spring; 201e, fixed block; 201f, arc plate; 201g, connecting block; 201h, support plate; 201i, magnet; 202, scraping component; 202a, vertical plate; 202b, triangular block; 202c, scraper; 203, transmission component; 203a, installation cavity; 203b, rotating shaft; 203c, limiting plate; 203d, extension groove; 203e, extension block; 203f, second spring; 203g, strip-shaped opening; 203h, cylinder; 203i, guiding plate; 203j, trimming edge; 204, deflection component; 204a, arc groove; 204b, spherical ball; 300, stabilizing component; 301, air extraction component; 301a, air extraction cylinder; 301b, piston; 301c, moving column; 301d, communication port; 301e, clamping block; 301f, limiting ring; 301g, clamping groove; 302, negative pressure component; 302a, gas storage cavity; 302b, suction cup; 302c, negative pressure port; 302d, first pipeline; 400, reinforcement component; 401, expansion component; 401a, inner groove; 401b, cross plate; 401c, moving plate; 401d, sealed space; 401e, second pipeline; 401f, third spring; 402, protection component; 402a, toothed plate; 402b, bearing shaft; 402c, friction pad; 402d, gear. Detailed implementation manners

[0030] To make the above objects, features, and advantages of the present invention more obvious and understandable, the following will describe the detailed implementation manners of the present invention in conjunction with the accompanying drawings of the specification.

[0031] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention can also be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the connotation of the present invention. Therefore, the present invention is not limited by the specific embodiments disclosed below.

[0032] Second, the "one embodiment" or "embodiment" referred to herein means a specific feature, structure, or characteristic that may be included in at least one implementation manner of the present invention. The "in one embodiment" that appears in different places in this specification does not necessarily refer to the same embodiment, nor is it an embodiment that is separate or selectively exclusive to other embodiments.

[0033] Embodiment 1

[0034] Referring to Figures 1 to 8 , which is the first embodiment of the present invention. This embodiment provides a device for disassembling a gas turbine compressor blade, which can achieve the effect of automatically ejecting the gas turbine compressor blade. It includes a support component 100, a wheel disc 102 arranged on the lower side of a bottom plate 101, including the bottom plate 101, a first tooling 103 arranged on the front side of the bottom plate 101, a second tooling 104 arranged on the rear side of the first tooling 103, a laser lamp 105 arranged on the first tooling 103, a jack 106 arranged on the second tooling 104, an installation port 107 arranged on the first tooling 103, and a pressure sensor 108 arranged on the jack 106; a scraping component 200, including a bearing component 201 arranged on the bottom plate 101, a scraping component 202 arranged on the bearing component 201, a transmission component 203 arranged on the scraping component 202, and a deflection component 204 arranged on the transmission component 203; a stabilizing component 300, including an air extraction component 301 arranged on the first tooling 103, and a negative pressure component 302 arranged on the air extraction component 301; a strengthening component 400, including an expansion component 401 arranged on the scraping component 202, and an anti-slip component arranged on the expansion component 401.

[0035] Specifically, a control box is arranged on the outer side of the jack 106 here. A cable connected to the jack 106 is arranged on the control box. The setting of the laser lamp 105 can perform position calibration. An alarm is also arranged in the control box here. When the jack 106 touches the outer frame of the blade, the pressure sensor senses and transmits a signal to the alarm to automatically give an alarm. This is the prior art and will not be elaborated here.

[0036] Further, the bearing assembly 201 includes a receiving groove 201a provided on the bottom plate 101. An installation frame 201b is fixedly connected inside the receiving groove 201a. A slider 201c is slidably connected inside the installation frame 201b. The slider 201c is elastically connected to the inner wall of the installation frame 201b through a first spring 201d. A fixed block 201e is fixedly connected to the inner side wall of the receiving groove 201a. An arc-shaped plate 201f is fixedly connected to the fixed block 201e. A connecting block 201g is fixedly connected to the side wall of the bottom plate 101. A support plate 201h is rotatably connected to the connecting block 201g through a transmission shaft. Magnets 201i are provided on the arc-shaped plate 201f, the support plate 201h and the first tooling 103; the scraping assembly 202 includes a vertical plate 202a fixedly connected to the slider 201c. The arc-shaped plate 201f is arranged on the front side of the vertical plate 202a. A triangular block 202b is provided on the vertical plate 202a. A scraper 202c is provided on the triangular block 202b.

[0037] Wherein, an anti-disengagement groove is further provided inside the installation frame 201b. An anti-disengagement block is provided inside the anti-disengagement groove. The anti-disengagement block is fixed to the slider 201c, so as to prevent the slider 201c from disengaging from the installation frame 201b. The arc-shaped plate 201f is located above the scraper 202c, so that when the scraper 202c abuts against the wheel disc 102, the phenomenon that the arc-shaped plate 201f abuts and affects the downward movement of the scraper 202c will not occur.

[0038] Preferably, the transmission assembly 203 includes an installation cavity 203a provided inside the vertical plate 202a. A rotating shaft 203b is rotatably connected inside the installation cavity 203a. The rotating shaft 203b penetrates through the vertical plate 202a and is rotatably connected to the vertical plate 202a. The rotating shaft 203b is fixedly connected to the triangular block 202b. Two limiting plates 203c are fixedly connected inside the installation cavity 203a. Extension grooves 203d are provided on both of the two limiting plates 203c. Extension blocks 203e are slidably connected inside the extension grooves 203d. The extension blocks 203e are elastically connected to the inner walls of the extension grooves 203d through second springs 203f. A strip-shaped opening 203g is provided on the vertical plate 202a. A cylinder 203h that cooperates with the strip-shaped opening 203g is fixedly connected to the extension block 203e. A guiding plate 203i is fixedly connected to the installation frame 201b. A cutting edge 203j that cooperates with the cylinder 203h is provided on the guiding plate 203i; the deflection assembly 204 includes an arc-shaped groove 204a provided on the rotating shaft 203b. A spherical ball 204b is slidably arranged inside the arc-shaped groove 204a. The spherical ball 204b is fixedly connected to the cylinder 203h.

[0039] It should be noted that the triangular block 202b is fixedly connected to the rotating shaft 203b, so that the inclination angle of the triangular block 202b can be changed. When the vertical plate 202a is downward, the triangular block 202b moves toward the outer end. When the triangular block 202b is needed to fit the circumference of the wheel 102, the angle of the triangular block 202b also needs to be changed, so as to ensure that the scraper 202c always fits the side wall of the wheel 102 to play a scraping role. The designer of the ball 204b here avoids the phenomenon of jamming between the cylinder 203h and the arc groove 204a.

[0040] When in use, to limit the position of the base, first place the scraper 202c at the lower end of the base on the wheel 102, and then squeeze the base. Since the side wall of the wheel 102 is an arc surface, when the scraper 202c is squeezed with the wheel 102, there is a downward and outward force, so that the scraper 202c moves outward. When the scraper 202c moves outward, the vertical plate 202a moves outward, so that the slider 201c moves outward, so that the first spring 201d obtains elasticity, and when the vertical plate 202a moves outward, it can drive the cylinder 203h to move. When the cylinder 203h moves outward, the cylinder 203h cooperates with the cutting edge 203j, so that the cylinder 203h moves in the direction away from the mounting frame 201b. When the cylinder 203h moves, the extension block 203e moves, so that the second spring 203f is compressed. At the same time, the cylinder 203h moves, driving the ball 204b to move in the arc groove 204a, so that the shaft 203b rotates counterclockwise (from the direction of the shaft 203b, the same below), thereby driving the angle of the triangular block 202b to change, so that The angle of the cutter is changed to ensure that when the triangular block 202b moves downward, the scraper 202c is always against the side wall of the wheel disc 102, ensuring the material hanging effect of the scraper 202c. When the scraper 202c moves to the horizontal, that is, when the triangular block 202b moves to the middle of the wheel disc 102, it continues to move a short distance, so that there is a gap between the triangular block 202b and the side wall of the wheel disc 102. When the triangular block 202b moves to the extreme position, the arc plate 201f is against the side wall of the wheel disc 102. Here, the wheel disc 102 is a magnetic The iron 201i can absorb the metal material. At this time, the magnet 201i on the arc plate 201f and the side wall of the wheel 102 attract each other, so as to achieve the limit of the bottom plate 101. At the same time, the support plate 201h is moved to make the support plate 201h move and resist the side wall of the rear end of the wheel 102. The magnet 201i is also used for absorption and limitation. When all the installation is completed, the bottom plate 101 is limited, and then the jack 106 is installed. The jack 106 is controlled to push the gas turbine compressor blades to disassemble the gas turbine compressor blades.

[0041] In summary, by setting the support member 100 and the scraping member 200, it is only necessary to place the bottom plate 101 well and then calibrate the position of the jack 106, and then start the jack 106 to automatically eject the compressor blades of the gas turbine, without manual hammering, which is more convenient to use. When fixing the bottom plate 101, it is quickly fixed by magnetic attraction, saving time. Moreover, when fixing by magnetic attraction, it can also automatically scrape the side wall of the wheel disc 102 to avoid foreign objects affecting the adsorption of the magnet 201i and ensure the stability of the adsorption of the magnet 201i.

[0042] Embodiment 2

[0043] Referring to Figures 2 to 8 , which is the second embodiment of the present invention. Different from the previous embodiment, this embodiment provides a stabilizing member 300 for the gas turbine compressor blade disassembly device, which solves the problem of how to further increase the stability of the base. It includes an air extraction assembly 301, which includes an air extraction cylinder 301a fixedly connected to the second tooling 104. A piston 301b is hermetically slidably connected in the air extraction cylinder 301a. A moving column 301c is fixedly connected to the piston 301b. The moving column 301c penetrates through the air extraction cylinder 301a and is hermetically slidably connected to the air extraction cylinder 301a. A communication port 301d is provided on the first tooling 103. A clamping block 301e is fixedly connected to the telescopic end of the jack 106. A limiting ring 301f is fixedly connected to the moving column 301c. A clamping groove 301g matching the clamping block 301e is provided on the limiting ring 301f; the negative pressure assembly 302 includes an air storage cavity 302a provided on the arc-shaped plate 201f. A plurality of suction cups 302b are communicated with the air storage cavity 302a. A negative pressure port 302c communicating with the air storage cavity 302a is provided on the suction cup 302b. One end of the air extraction cylinder 301a away from the limiting ring 301f is hermetically communicated with the air storage cavity 302a through a first pipeline 302d.

[0044] Furthermore, the air extraction cylinder 301a is located between the first tooling 103 and the second tooling 104. The setting of the communication port 301d enables the movement of the moving column 301c not to be blocked. The clamping block 301e and the clamping groove 301g cooperate, so that when the jack 106 moves, it can also drive the limiting ring 301f to move. The setting of the suction cup 302b can increase the contact surface and make the stabilizing effect better.

[0045] During use, when the arc-shaped plate 201f abuts against the side wall of the wheel disc 102, the suction cup 302b is attracted to the side wall of the wheel disc 102, and the magnet 201i fits against the side wall of the wheel disc 102. When the jack 106 extends to eject the compressor blade of the gas turbine, it can also drive the limit ring 301f to move, thereby driving the engagement of the card slot 301g and the card block 301e, driving the card block 301e to move away from the air extraction cylinder 301a, thereby driving the piston 301b to move away from the air extraction cylinder 301a, and pumping the gas in the air storage cavity 302a through the first pipeline 302d, causing the air storage cavity 302a to form a negative pressure. Thus, through the negative pressure port 302c, the pressure plate forms a negative pressure, so that the suction cup 302b firmly adheres to the side wall of the wheel disc 102, making the arc-shaped plate 201f more stable, and further making the bottom plate 101 more stable, avoiding the sliding of the bottom plate 101.

[0046] In summary, by setting the stabilizing component 300, after the bottom plate 101 is fixed, it can be reinforced by negative pressure, preventing the bottom plate 101 from moving, thereby avoiding the phenomenon of the jack 106 tilting when the jack 106 moves, and ensuring the stability of the disassembly of the compressor blade of the gas turbine.

[0047] Embodiment 3

[0048] Refer to Figures 9 to 11 , which is the third embodiment of the present invention. Different from the previous embodiment, this embodiment provides a reinforcing component 400 for the disassembly device of the compressor blade of the gas turbine, which solves the problem of how to further increase the stability of the bottom plate 101. It includes an expansion component 401 including an inner groove 401a provided on the triangular block 202b. A cross plate 401b is fixedly connected in the inner groove 401a. A moving plate 401c is hermetically slidably connected to the cross plate 401b. The moving plate 401c, the cross plate 401b and the inner groove 401a form a sealed space 401d. The outer end of the air extraction cylinder 301a is hermetically communicated with the sealed space 401d through a second pipeline 401e; the anti-slip component includes a toothed plate 402a fixedly connected to the moving plate 401c. A bearing shaft 402b is rotatably connected in the inner groove 401a. An arc-shaped friction pad 402c is fixedly connected to the bearing shaft 402b.

[0049] Specifically, the length of the second pipeline 401e here is sufficient, and the phenomenon of the pipeline being pulled due to the movement of the vertical plate 202a will not occur. The arc of the friction pad 402c here matches the arc of the wheel disc 102. Thus, when the friction pad 402c abuts against the side wall of the wheel disc 102, it can prevent the sliding of the triangular block 202b, and further ensure the stability of the bottom plate 101.

[0050] During use, when the piston 301b moves, it can also pump the gas in the air pump 301a into the sealed space 401d through the second pipeline 401e, causing the moving plate 401c to move, thereby driving the toothed plate 402a to move towards the gear 402d, driving the meshing gear 402d to rotate clockwise (viewed from the direction of directly facing the gear 402d, the same below), thereby driving the bearing shaft 402b to rotate clockwise, causing the friction pad 402c to rotate clockwise and abut against the side wall of the wheel disc 102, thereby increasing the friction force and further preventing the sliding of the bottom plate 101.

[0051] In summary, by setting the reinforcement component 400, while forming a negative pressure by pumping air, it can also pump air to make the friction pad 402c rotate and abut against the side wall of the wheel disc 102, further preventing the loosening of the bottom plate 101 by friction, making the fixing effect of the bottom plate 101 better, and further preventing the offset of the jack 106.

[0052] Embodiment 4

[0053] This is the fourth embodiment of the present invention. Different from the previous embodiment, this embodiment provides an application method, which includes planning the trajectory of the blade being pushed from the air outlet side to the air inlet side; aligning the head positions of the three jacks 106 with the blade root positions; placing the first tooling 103 at a suitable position; using the laser lamp 105 to check the trajectory to ensure that it does not shift during the pushing process; measuring the height difference between the blade root and the wheel disc 102, and placing the second tooling 104 at a suitable position; measuring the width between the two-stage wheel discs 102, and pressing the bottom plate 101 on the wheel disc 102 according to the adjusted position; fixing the position of the bottom plate 101 with the suction force of the magnet 201i and making the bottom plate 101 stable through negative pressure; then adjusting the angular position of the support plate 201h and the bottom plate 101, and fixing the position of the bottom plate 101 with the suction force of the magnet 201i; using the laser lamp 105 to recheck the position and angle; after checking without error, perform the disassembly work of the blade through the jack 106 control cabinet.

[0054] Importantly, it should be noted that the construction and arrangement of the present application shown in multiple different exemplary embodiments are merely illustrative. Although only a few embodiments are described in detail in this disclosure, those who refer to this disclosure should easily understand that many modifications are possible without materially departing from the novel teachings and advantages of the subject matter described in this application (e.g., changes in the dimensions, scales, structures, shapes and proportions of various elements, as well as parameter values (such as temperature, pressure, etc.), installation arrangements, use of materials, colors, orientations, etc.). For example, an element shown as integrally formed may be composed of multiple parts or elements, the positions of the elements may be inverted or otherwise changed, and the nature, number or position of discrete elements may be altered or changed. Accordingly, all such modifications are intended to be included within the scope of the present invention. The order or sequence of any process or method steps may be altered or reordered according to alternative embodiments. In the claims, any "means-plus-function" clause is intended to cover the structures that perform the recited function herein, and not only structural equivalents but also equivalent structures. Other substitutions, modifications, changes and omissions may be made in the design, operating conditions and arrangement of the exemplary embodiments without departing from the scope of the present invention. Accordingly, the present invention is not limited to the specific embodiments, but extends to various modifications that still fall within the scope of the appended claims.

[0055] In addition, in order to provide a concise description of the exemplary embodiments, not all features of the actual embodiments may be described (i.e., those features that are not relevant to the currently contemplated best mode of carrying out the present invention or those features that are not relevant to the implementation of the present invention).

[0056] It should be understood that in the development of any actual implementation, as in any engineering or design project, numerous specific implementation decisions may be made. Such development efforts may be complex and time-consuming, but for those of ordinary skill in the art who benefit from this disclosure, the development efforts will be a routine task of design, manufacturing and production without undue experimentation.

[0057] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them. Although the present invention has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that the technical solutions of the present invention may be modified or equivalently replaced without departing from the spirit and scope of the technical solutions of the present invention, and they should all be covered within the scope of the claims of the present invention.

Claims

1. A gas turbine compressor blade disassembly device, characterized in that: include, A supporting component (100), comprising a base plate (101), a wheel disc (102) arranged on the lower side of the base plate (101), a first tooling (103) arranged on the front side of the base plate (101), a second tooling (104) arranged on the rear side of the first tooling (103), a laser light (105) arranged on the first tooling (103), three jacks (106) arranged on the second tooling (104), a mounting port (107) arranged on the first tooling (103), and a pressure sensor (108) arranged on the jack (106); A scraping component (200) comprises a bearing assembly (201) arranged on the bottom plate (101), a scraping assembly (202) arranged on the bearing assembly (201), a transmission assembly (203) arranged on the scraping assembly (202), and a deflection assembly (204) arranged on the transmission assembly (203); A stabilizing component (300), comprising an air extraction component (301) arranged on the first tooling (103), and a negative pressure component (302) arranged on the air extraction component (301); The reinforcing component (400) comprises an expansion component (401) arranged on the scraping component (202), and an anti-slip component arranged on the expansion component (401).

2. The gas engine compressor blade disassembly device according to claim 1, characterized in that: The bearing assembly (201) comprises a receiving groove (201a) arranged on the bottom plate (101), a mounting frame (201b) is fixedly connected in the receiving groove (201a), a slider (201c) is slidably connected in the mounting frame (201b), the slider (201c) is elastically connected to the inner wall of the mounting frame (201b) via a first spring (201d), a fixing block (201e) is fixedly connected to the inner wall of the receiving groove (201a), an arc-shaped plate (201f) is fixedly connected to the fixing block (201e), a connecting block (201g) is fixedly connected to the side wall of the bottom plate (101), a supporting plate (201h) is rotatably connected to the connecting block (201g) via a transmission shaft, and magnets (201i) are provided on the arc-shaped plate (201f), the supporting plate (201h) and the first tooling (103).

3. The gas engine compressor blade disassembly device according to claim 2, characterized in that: The scraping assembly (202) comprises a vertical plate (202a) fixedly connected to a sliding block (201c); the arc-shaped plate (201f) is arranged on the front side of the vertical plate (202a); a triangular block (202b) is arranged on the vertical plate (202a); and a scraper (202c) is arranged on the triangular block (202b).

4. The gas engine compressor blade disassembly device according to claim 3, characterized in that: The transmission assembly (203) comprises an installation cavity (203a) arranged in the vertical plate (202a), a rotating shaft (203b) is rotatably connected in the installation cavity (203a), the rotating shaft (203b) passes through the vertical plate (202a) and is rotatably connected to the vertical plate (202a), the rotating shaft (203b) is fixedly connected to the triangular block (202b), two limiting plates (203c) are fixedly connected in the installation cavity (203a), and the two limiting plates (203c) are both provided with an extension groove (203d), and the extension groove (203d) An extension block (203e) is slidably connected to the inner wall of the extension groove (203d), and the extension block (203e) is elastically connected to the inner wall of the extension groove (203d) through a second spring (203f); a strip-shaped opening (203g) is provided on the vertical plate (202a); a cylinder (203h) matched with the strip-shaped opening (203g) is fixedly connected to the extension block (203e); a guide plate (203i) is fixedly connected to the installation frame (201b); and a cutting edge (203j) matched with the cylinder (203h) is provided on the guide plate (203i).

5. The gas engine compressor blade disassembly device according to claim 4, characterized in that: The deflection assembly (204) comprises an arc-shaped groove (204a) arranged on the rotating shaft (203b), a round ball (204b) sliding in the arc-shaped groove (204a), and the round ball (204b) is fixedly connected to the cylinder (203h).

6. The gas engine compressor blade disassembly device according to claim 5, characterized in that: The vacuum assembly (301) comprises a vacuum cylinder (301a) fixedly connected to the second tooling (104), a piston (301b) being sealingly and slidably connected inside the vacuum cylinder (301a), a movable column (301c) being fixedly connected to the piston (301b), the movable column (301c) passing through the vacuum cylinder (301a) and being sealingly and slidably connected to the vacuum cylinder (301a), a connecting port (301d) being provided on the first tooling (103), a clamping block (301e) being fixedly connected to the telescopic end of the jack (106), a limiting ring (301f) being fixedly connected to the movable column (301c), and a clamping groove (301g) matching the clamping block (301e) being provided on the limiting ring (301f).

7. The gas engine compressor blade disassembly device according to claim 6, characterized in that: The negative pressure component (302) comprises an air storage chamber (302a) arranged on the arc-shaped plate (201f), the air storage chamber (302a) is connected to a plurality of suction cups (302b), the suction cups (302b) are provided with a negative pressure port (302c) connected to the air storage chamber (302a), and one end of the air pump (301a) away from the limiting ring (301f) is sealed and connected to the air storage chamber (302a) via a first pipe (302d).

8. The gas engine compressor blade disassembly device according to claim 7, characterized in that: The expansion assembly (401) comprises an inner groove (401a) arranged on the triangular block (202b), a transverse plate (401b) being fixedly connected inside the inner groove (401a), a movable plate (401c) being sealingly and slidably connected to the transverse plate (401b), a sealed space (401d) being formed between the movable plate (401c), the transverse plate (401b) and the inner groove (401a), an outer end of the vacuum cylinder (301a) being sealedly connected to the sealed space (401d) via a second pipe (401e), and the movable plate (401c) being elastically connected to the inner wall of the inner groove (401a) via a third spring (401f).

9. The gas engine compressor blade disassembly device according to claim 8, characterized in that: The anti-skid assembly comprises a toothed plate (402a) fixedly connected to a movable plate (401c), a bearing shaft (402b) rotatably connected in the inner groove (401a), an arc-shaped friction pad (402c) fixedly connected to the bearing shaft (402b), and a gear (402d) meshing with the toothed plate (402a) fixedly connected to the bearing shaft (402b).

10. An application method, according to the gas engine compressor blade disassembly device according to any one of claims 1 to 9, characterized in that: include, Plan the trajectory of the blade from the outlet side to the inlet side; Align the heads of the three jacks (106) with the root positions of the blades; Placing a first tool (103) at a suitable position; Using a laser light (105) to check the trajectory to ensure that it does not shift during the pushing process; Measuring the height difference between the blade root and the wheel disc (102), and placing the second tool (104) at a suitable position; Measuring the width between the two-stage wheel discs (102), and pressing the bottom plate (101) onto the wheel discs (102) according to the adjusted position; The position of the bottom plate (101) is fixed by the suction force of the magnet (201i) and the bottom plate (101) is stabilized by negative pressure; Then, the angles of the support plate (201h) and the bottom plate (101) are adjusted, and the bottom plate (101) is fixed by the suction force of the magnet (201i); Using a laser light (105) to check the position angle; After checking that everything is correct, the blades are disassembled through the jack (106) control cabinet.

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