Vibration detection device for gas turbine blades

Abstract

The present invention relates to the technical field of vibration detection, and more particularly to a vibration detection device for gas turbine blades, comprising: a detection mechanism including a detection stand and a sealing housing provided on the detection stand, wherein blade tip timing sensors are provided on the inner wall of the detection stand and on the inner wall of the sealing housing, with blade tip timing sensors distributed circumferentially; a gas turbine rotor provided on the detection stand and positioned between the detection stand and the sealing housing; a locking mechanism including a support seat fixedly provided on the outer wall of the detection stand and a support shaft fixedly provided at the top end of the support seat, wherein a locking block is rotatably connected to the outer wall of the support shaft, and further includes a counterweight fixedly provided on the outer wall of the locking block, and a support pad is provided on the support seat; and a lifting mechanism, wherein the sealing housing in the present invention can automatically form an engagement with the detection stand after lifting is complete, and is easy to remove, making it easy to remove the gas turbine rotor.

Description

Technical Field

[0001] The present invention relates to the technical field of vibration detection, and particularly to a vibration detection device for a gas turbine blade.

Background Art

[0002] A gas turbine, also called a steam turbine engine, is a rotary machine that uses steam as power and converts the thermal energy of steam into mechanical work. It has advantages such as a large single-unit power, high efficiency, and a long service life, and is the prime mover most widely applied in modern thermal power plants. It is also used in the metallurgical industry, chemical industry, and ship power plants. During operation, the vibration of the gas turbine blade needs to be within a safe range. If it exceeds this range, the gas turbine blade may fatigue and break due to excessive stress, which may cause serious consequences. Even if it does not break, the abnormal vibration of the blade will accelerate the wear of the components and generate excessive noise. Therefore, it is necessary to constantly detect the vibration of the gas turbine blade.

[0003] To determine the service life and performance of a gas turbine blade, generally, before practical use, the gas turbine rotor is tested by a vibration detection device. The gas turbine rotor is set on a test bench and driven by a driving device to rotate at high speed to simulate the operating environment, detect the vibration state of the blade, and determine the service life and performance of the gas turbine blade.

[0004] During detection, after setting the gas turbine rotor on the test bench, it is necessary to further seal the test space between the rotor and the bench using a sealing structure. After suspending the gas turbine rotor onto the test bench, the sealing structure is suspended from the test bench and connected and fixed to it. After the experiment is completed, the gas turbine rotor is removed, and the blades or gas turbine rotor are replaced to perform detection again. However, the connection and fixing of the sealing structure to the test bench is usually done with bolts, and the removal of the gas turbine rotor, removal of the sealing structure, and lifting take a lot of time, resulting in an excessively long experimental cycle. Therefore, we propose a vibration detection device for gas turbine blades. [Overview of the project]

[0005] In view of the above-mentioned or prior art problems, such as the time required to remove the gas turbine rotor, detach the sealing structure, and lift it, the present invention is proposed.

[0006] Therefore, the present invention aims to provide a vibration detection device for gas turbine blades.

[0007] To solve the above technical problems, the present invention provides the following technical solutions. A vibration detection device for a gas turbine blade, comprising a detection mechanism including a detection stand and a sealing housing provided on the detection stand, wherein blade tip timing sensors are provided on the inner wall of the detection stand and on the inner wall of the sealing housing, with blade tip timing sensors distributed circumferentially; a gas turbine rotor provided on the detection stand and positioned between the detection stand and the sealing housing; a locking mechanism including a support seat fixedly provided on the outer wall of the detection stand and a support shaft fixedly provided at the top end of the support seat, wherein a locking block is rotatably connected to the outer wall of the support shaft, and the locking block is The locking mechanism further includes a counterweight fixedly mounted on the wall, with a support pad provided on the support seat, and a lifting mechanism including a pressing member fixedly mounted on the outer wall of the sealing housing, and a lifting assembly fixedly mounted on the outer wall of the pressing member, wherein in the process of the sealing housing being lowered and attached to the detection stage, the pressing member can push the locking block in such a way that it displaces it, and when the sealing housing is attached to the detection stage, the counterweight pushes down the locking block in such a way that it displaces it, and the locking block locks the pressing member in a position.

[0008] In one preferred embodiment of the vibration detection device for gas turbine blades according to the present invention, a plurality of uniformly distributed guide posts are fixedly provided on the top edge of the detection platform, a plurality of uniformly distributed docking holes are provided on the bottom edge of the sealing housing, and the outer walls of the guide posts and the inner walls of the docking holes are slidably connected.

[0009] In one preferred embodiment of the vibration detection device for gas turbine blades according to the present invention, an arc-shaped surface is provided on the side of the locking block away from the counterweight, and an adhesive surface is provided on the side of the locking block near the support pad, and the pressing member includes a pressing block fixedly provided on the outer wall of the sealing housing, and a contact arc-shaped surface provided on the side of the pressing block away from the sealing housing.

[0010] In one preferred embodiment of the vibration detection device for gas turbine blades according to the present invention, the lifting assembly includes a lifting frame fixedly provided on the outer wall of the pressing block, and a position limiting bush fixedly provided on the top of the lifting frame, wherein a cushioning material is slidably connected to the inner wall of the position limiting bush, and a lifting head is fixedly attached to the top end of the cushioning material.

[0011] In one preferred embodiment of the vibration detection device for gas turbine blades according to the present invention, the cushioning material includes a slide rod slidably provided on the inner wall of the position limiting bush, and a contact sleeve fixedly provided on the bottom end of the slide rod, a push plate fixedly attached to the bottom end of the contact sleeve, a first spring fitted to the outer wall of the contact sleeve and the slide rod, and the cushioning material further includes an insertion rod fixedly provided on the bottom end of the push plate.

[0012] In one preferred embodiment of the vibration detection device for gas turbine blades according to the present invention, the pressing member further includes a through hole provided in the pressing block, and an insertion groove is provided on the locking block.

[0013] In one preferred embodiment of the vibration detection device for gas turbine blades according to the present invention, a positioning hole is provided at the top of the support seat.

[0014] In one preferred embodiment of the vibration detection device for gas turbine blades according to the present invention, the lifting mechanism further includes a moving assembly fixedly provided on the outer wall of the push plate, the moving assembly includes a connecting rod fixedly provided on the outer wall of the push plate, and an engaging member fixedly provided on the end of the connecting rod.

[0015] In one preferred embodiment of the vibration detection device for gas turbine blades according to the present invention, the engaging member includes a housing sleeve fixedly provided at the bottom end of the connecting rod, and a second spring fixedly provided within the housing sleeve, a slide plate fixedly attached to the end of the second spring, a contact block fixedly attached to the end of the slide plate, and a groove provided in the outer wall of the locking block.

[0016] In one preferred embodiment of the vibration detection device for gas turbine blades according to the present invention, a guide surface is provided on the inner wall of the groove, and a slope is provided on the end of the contact block.

[0017] The beneficial effects of the vibration detection device for gas turbine blades according to the present invention are as follows. In this invention, the gas turbine rotor is set on a detection stand, the gas turbine rotor is connected to a drive unit via a shaft coupling, and the lifting assembly is connected to a lifting rope. The lifting and lowering of the sealing housing can be controlled by rewinding and unwinding the lifting rope by a crane or winch. During the lowering of the sealing housing, the pressing member comes into contact with the locking block. When the locking block is displaced by a certain angle, contact with the pressing member ceases, and under the gravitational action of the counterweight, the locking block displaces and returns, forming a fixed lock between the sealing housing and the detection stand. When the drive unit is driven to rotate the gas turbine rotor at high speed, the blade tip timing sensor detects vibrations in the blades of the gas turbine rotor. When replacing the gas turbine rotor or the blades thereon, rotating the locking block and pulling up the lifting rope raises the sealing housing, completing the separation of the sealing housing and the detection stand. This allows the gas turbine rotor to be easily removed, and the removal and lifting of the sealing housing are facilitated. [Brief explanation of the drawing]

[0018] To more clearly explain the technical solution in the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly described below. Of course, the drawings described below are only a part of the embodiments of the present invention, and those skilled in the art can conceive of other drawings based on these drawings without creative effort.

[0019] [Figure 1] It is an overall schematic diagram of a vibration detection device for a gas turbine blade. [Figure 2] It is a schematic diagram of the connection structure between the inspection table and the guide post in a vibration detection device for a gas turbine blade. [Figure 3] It is a schematic diagram of the connection structure between the sealing housing and the docking hole in a vibration detection device for a gas turbine blade. [Figure 4] It is a schematic diagram of the distribution state structure of the blade tip timing sensor in a vibration detection device for a gas turbine blade. [Figure 5] It is a schematic cross-sectional structure diagram of the locking mechanism and the lifting mechanism in a vibration detection device for a gas turbine blade. [Figure 6] It is a schematic diagram of the structure of the lifting mechanism in a vibration detection device for a gas turbine blade. [Figure 7] It is a schematic diagram of the connection structure between the support seat and the positioning hole in a vibration detection device for a gas turbine blade. [Figure 8] It is a schematic diagram of the structure of the locking block in a vibration detection device for a gas turbine blade. [Figure 9] It is a schematic diagram of the structure of the engaging member in a vibration detection device for a gas turbine blade.

Embodiments for Carrying out the Invention

[0020] To make the above objects, features, and advantages of the present invention clearer, the specific embodiments of the present invention will be described in detail below with reference to the drawings in the specification.

[0021] In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. However, the present invention may be implemented in other forms different from those described herein, and those skilled in the art can make similar generalizations without violating the scope of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0022] Next, as used herein, "one embodiment" or "an embodiment" refers to a particular feature, structure, or characteristic that may be included in at least one implementation form of the present invention. The descriptions of "in one embodiment" appearing at different locations in this specification do not necessarily refer to the same embodiment, nor are they mutually exclusive embodiments that are separate or selected from other embodiments.

[0023] Embodiment 1 refers to FIGS. 1 to 4 and is the first embodiment of the present invention. This embodiment provides a vibration detection device for a gas turbine blade, comprising a detection mechanism 100, a gas turbine rotor 200, a locking mechanism 300, and a lifting mechanism 400. The detection mechanism 100 includes a detection platform 101 and a sealing housing 102 provided on the detection platform 101. Blade tip timing sensors 103 are provided in a circumferential distribution on both the inner wall of the detection platform 101 and the inner wall of the sealing housing 102. In this embodiment, the blade tip timing sensors 103 can acquire the arrival time of the blade, and further calculate the vibration displacement of the blade by combining the rotational speed and the rotor diameter, thereby easily detecting the vibration condition of the gas turbine blade.

[0024] The gas turbine rotor 200 is mounted on the detection stand 101 and positioned between the detection stand 101 and the sealing housing 102. In this embodiment, the gas turbine rotor 200 is set on the detection stand 101 by lifting, and after the lifting is complete, the sealing housing 102 is attached to the detection stand 101. The detection stand 101 and the sealing housing 102 then form a sealing space, restricting the position of the gas turbine rotor 200. The gas turbine rotor 200 can be connected to an external drive unit via a shaft coupling. The drive unit drives the gas turbine rotor 200 to rotate at high speed, simulating the operating state of the gas turbine rotor 200.

[0025] The locking mechanism 300 includes a support seat 301 fixedly provided on the outer wall of the detection stage 101, and a support shaft 302 fixedly provided on the top end of the support seat 301, with a locking block 303 rotatably connected to the outer wall of the support shaft 302. The locking mechanism 300 further includes a counterweight 304 fixedly provided on the outer wall of the locking block 303, and a support pad 305 is provided on the support seat 301. In this embodiment, four locking mechanisms 300 are provided, and are provided at the four corners of the outer wall of the detection stage 101. The locking block 303 can rotate on the outer wall of the support shaft 302, and under the gravitational force of the counterweight 304, the bottom of the locking block 303 can be attached to the top of the support pad 305.

[0026] The lifting mechanism 400 includes a pressing member 401 fixedly mounted on the outer wall of the sealing housing 102, and a lifting assembly 402 fixedly mounted on the outer wall of the pressing member 401. In this embodiment, four lifting mechanisms 400 are provided, each paired with a locking mechanism 300. The pressing member 401 is used to press the end of the locking block 303 closest to the detection base 101. The lifting assembly 402 is connected to a lifting rope, and the lifting and lowering of the sealing housing 102 can be controlled by rewinding or unwinding the lifting rope using a crane or winch.

[0027] It should be explained that, during the process in which the sealing housing 102 descends and adheres to the detection stage 101, the pressing member 401 can push the locking block 303 in such a way that it displaces it, and when the sealing housing 102 adheres to the detection stage 101, the counterweight 304 pushes down the locking block 303 in such a way that it displaces it, and the locking block 303 locks the pressing member 401 into position.

[0028] Specifically, multiple uniformly distributed guide posts 101a are fixedly provided on the top edge of the detection stage 101, and multiple uniformly distributed docking holes 102a are provided on the bottom edge of the sealing housing 102. In this embodiment, the outer walls of the guide posts 101a and the inner walls of the docking holes 102a are slidably connected, and by fitting the multiple guide posts 101a and the multiple docking holes 102a together, the sealing housing 102 can be easily and accurately positioned and lowered onto the detection stage 101. The top ends of the guide posts 101a are beveled or rounded, making it easy to accurately position and insert the guide posts 101a into the docking holes 102a.

[0029] Furthermore, an arc-shaped surface 303a is provided on the side of the locking block 303 away from the counterweight 304, and an adhesive surface 303b is provided on the side of the locking block 303 closer to the support pad 305. In this embodiment, the axis of the arc-shaped surface 303a coincides with the axis of the support shaft 302, so that the locking block 303 can maintain close contact with other structures both when it rotates and when it returns to its original position, thereby increasing the strength of the structure. The adhesive surface 303b is for attaching the top of the support pad 305.

[0030] Preferably, the pressing member 401 includes a pressing block 401a fixedly provided on the outer wall of the sealing housing 102, and a contact arcuate surface 401c provided on the side of the pressing block 401a away from the sealing housing 102. In this embodiment, the provision of the contact arcuate surface 401c facilitates the smooth displacement of the locking block 303 when the locking block 303 is pressed by the pressing block 401a.

[0031] When in use, first the gas turbine rotor 200 is set on the detection stand 101, the gas turbine rotor 200 is connected to the drive unit via a shaft coupling, the lifting assembly 402 is connected to the lifting rope, and the lifting and lowering of the sealing housing 102 is controlled by rewinding and unwinding the lifting rope with a crane or winch, allowing the sealing housing 102 to be lifted onto the detection stand 101, during the lowering of the sealing housing 102 the pressing block 401a comes into contact with the locking block 303, the locking block 303 is displaced outside the support shaft 302, and when the locking block 303 is displaced by a certain angle the contact with the pressing block 401a is lost, at which point the sealing housing 102 and the detection stand 101 are in a state of being just stuck together, and the counterweight Under the gravitational force of thread 304, the locking block 303 displaces and returns, attaching its adhesive surface 303b to the top of the support pad 305. At this time, the arc-shaped surface 303a and the contact arc-shaped surface 401c are in contact, and the arc-shaped surface 303a restricts the movement of the pressing block 401a. Combined with the positional restriction of the sealing housing 102 by the guide post 101a and the docking hole 102a, the connection between the sealing housing 102 and the detection stand 101 is completed. As soon as the lifting is completed, a locking and fixing is formed between the sealing housing 102 and the detection stand 101. When the drive unit drives the gas turbine rotor 200 to rotate at high speed, the blade tip timing sensor 103 detects vibrations in the blades of the gas turbine rotor 200.

[0032] When replacing the gas turbine rotor 200 or the blades thereon, it is necessary to open the sealing housing 102. When opening it, the locking block 303 is manually moved to remove any obstructions above the pressing block 401a, and the suspension rope is pulled up, which allows the sealing housing 102 to be raised and the separation of the sealing housing 102 from the detection stand 101 to be completed.

[0033] Example 2, with reference to Figures 1 to 8, is a second embodiment of the present invention. It differs from the previous embodiment in the following respects. The lifting assembly 402 includes a lifting frame 402a fixedly mounted on the outer wall of the pressing block 401a, and a position limiting bush 402b fixedly mounted on the top of the lifting frame 402a, a cushioning material 402c slidably connected to the inner wall of the position limiting bush 402b, and a lifting head 402d fixedly attached to the top end of the cushioning material 402c, and in this embodiment, the lifting head 402d is used to connect to a lifting rope.

[0034] Specifically, the cushioning material 402c includes a slide rod 402c-1 slidably provided on the inner wall of the position limiting bush 402b, and a contact sleeve 402c-2 fixedly provided on the bottom end of the slide rod 402c-1, with a push plate 402c-3 fixedly attached to the bottom end of the contact sleeve 402c-2, and a first spring 402c-4 fitted onto the outer walls of the contact sleeve 402c-2 and the slide rod 402c-1. The cushioning material 402c further includes an insertion rod 402c-5 fixedly provided on the bottom end of the push plate 402c-3.

[0035] Furthermore, the pressing member 401 further includes a through hole 401b provided in the pressing block 401a, an insertion groove 303c is provided in the locking block 303, and a positioning hole 301a is provided at the top of the support seat 301. In this embodiment, the axes of the through hole 401b, the insertion groove 303c, and the positioning hole 301a overlap with each other.

[0036] All other structural features are the same as in Example 1.

[0037] When controlling the sealing housing 102 to be lowered and attached to the detection stand 101, under the gravitational force of the sealing housing 102 itself, the first spring 402c-4 is in a compressed state, the contact sleeve 402c-2 and the position limiting bush 402b are in contact, and the insertion rod 402c-5 protrudes from inside the through hole 401b. When the sealing housing 102 is just in contact with the surface of the detection stand 101, the first spring 402c-4 is still in a compressed state, the locking block 303 and the pressing block 401a are locked, and then the suspension rope is suspended. As it continues to lower, the push plate 402c-3 is pushed under the elastic force of the first spring 402c-4, inserting the insertion rod 402c-5 into the insertion groove 303c and the through hole 401b, and also into the positioning hole 301a. The insertion of the insertion rod 402c-5 locks the locking block 303, improving the stability after connection between the sealing housing 102 and the detection stand 101, preventing loosening and detachment. Since the inner wall of the insertion groove 303c abuts against the outer wall of the insertion rod 402c-5, the locking block 303 cannot swing or deviate.

[0038] When replacing the gas turbine rotor 200 or the blades thereon, it is necessary to open the sealing housing 102. When opening, the lifting head 402d is pulled up via the lifting rope. Once pulled up, the first spring 402c-4 is compressed first, causing the insertion rod 402c-5 to protrude from the positioning hole 301a, through hole 401b, and insertion groove 303c. As the contact sleeve 402c-2 protrudes until it contacts the position limiting bush 402b, the locking block 303 is manually moved to remove any obstructions above the pressing block 401a. By continuing to pull up the lifting rope, the sealing housing 102 can be raised, completing the separation of the sealing housing 102 from the detection stand 101.

[0039] Example 3, with reference to Figures 1 to 9, is a third embodiment of the present invention. It differs from the previous embodiments in the following respects. The lifting mechanism 400 further includes a movable assembly 403 fixedly provided on the outer wall of the push plate 402c-3, and in this embodiment, each outer wall of the push plate 402c-3 is provided with two symmetrically installed movable assemblies 403.

[0040] Furthermore, the moving assembly 403 includes a connecting rod 403a fixedly mounted on the outer wall of the push plate 402c-3, and an engaging member 403b fixedly mounted on the end of the connecting rod 403a. In this embodiment, the connecting rod 403a has an L-shaped structure.

[0041] Specifically, the engaging member 403b includes a housing sleeve 403b-1 fixedly provided at the bottom end of the connecting rod 403a, and a second spring 403b-2 fixedly provided within the housing sleeve 403b-1. A slide plate 403b-3 is fixedly attached to the end of the second spring 403b-2, and a contact block 403b-4 is fixedly attached to the end of the slide plate 403b-3. In this embodiment, the slide plate 403b-3 can slide on the inner wall of the housing sleeve 403b-1, and one end of the contact block 403b-4 penetrates the housing sleeve 403b-1.

[0042] It should be explained that a groove 303d is provided in the outer wall of the locking block 303, and the design of the groove 303d facilitates the protrusion and engagement of the abutment block 403b-4.

[0043] Furthermore, a guide surface 303e is provided on the inner wall of the groove 303d. In this embodiment, the installation of the guide surface 303e allows the contact block 403b-4 to be pushed in such a way that it displaces the locking block 303 when the contact block 403b-4 rises after it has engaged with the groove 303d.

[0044] Preferably, a slope 403b-5 is provided at the end of the contact block 403b-4. In this embodiment, the installation of the slope 403b-5 allows the contact block 403b-4 to slide and be housed in the housing sleeve 403b-1 as it descends and approaches the locking block 303.

[0045] All other structural features are the same as in Example 2.

[0046] After the sealing housing 102 is attached to the detection stand 101, when the locking block 303 is locked to the pressing block 401a, the suspension rope is controlled to be suspended, and under the elastic force of the first spring 402c-4, the push plate 402c-3 descends, the contact block 403b-4 first contacts the surface of the locking block 303, and the second spring 403b-2 is compressed by the guidance of the inclined surface 403b-5, and the contact block 403b-4 is further slid and housed in the housing sleeve 403b-1, and when the contact block 403b-4 enters the area where the groove 303d is located, the elastic force of the second spring 403b-2 pushes out the contact block 403b-4 until the insertion rod 402c-5 is inserted into the positioning hole 301a.

[0047] When the lifting rope lifts the lifting head 402d, the first spring 402c-4 is compressed, and the insertion rod 402c-5 protrudes from inside the insertion groove 303c. At this time, the contact block 403b-4 rises and comes into contact with the guide surface 303e. As it continues to rise, it pushes the guide surface 303e, displacing the locking block 303. The contact block 403b-4 remains in contact with the guide surface 303e even as the contact sleeve 402c-2 is displaced until it comes into contact with the position limiting bush 402b. In contact with the contact block 403b-4, as the suspension rope rises, the pressing block 401a rises, and when the pressing block 401a rises to a certain height, the contact blocks 403b-4 disengage from the groove 303d, allowing the sealing housing 102 to continue rising. Under the gravitational force of the counterweight 304, the locking block 303 displaces and returns to its original position, completing the removal of the sealing housing 102 from the detection stand 101. In other words, the sealing housing 102 and the detection stand 101 can be separated by lifting.

[0048] It should be noted that the above embodiments are for illustrative purposes only and do not limit the technical solutions of the present invention. While the present invention has been described in detail with reference to preferred embodiments, as those skilled in the art will understand, the technical solutions of the present invention can be modified or replaced with equivalent alternatives without departing from its spirit and scope, and such modifications are included within the scope of the claims. [Explanation of symbols]

[0049] 100 detection mechanism 101 detection platform 102 Encapsulation Housing 103 Blade tip timing sensor 101a Guidepost 102a Dorking Hall 200 Gas Turbine Rotor 300 Locking Mechanism 301 Support seat 302 Support shaft 303 Locking block 304 Counterweight 305 Support Pad 301a Positioning hole 303a Arc-shaped surface 303b Adhesive side 303c insertion groove 303d groove 303e Guide surface 400 Lifting Mechanism 401 Pressing member 402 Lifting Assembly 403 Moving Assembly 401a Pressing block 401b Through hole 401c Contact arc surface 402a Lifting Frame 402b Position limiting bush 402c cushioning material 402d Lifting Head 402c-1 Slide Rod 402c-2 Contact Sleeve 402c-3 Push Plate 402c-4 First spring 402c-5 Insertion Rod 403a Connecting rod 403b Engaging member 403b-1 Storage Sleeve 403b-2 Second spring 403b-3 Slide Plate 403b-4 Contact Block 403b-5 Slope

Claims

1. A detection mechanism (100) includes a detection platform (101) and a sealing housing (102) provided on the detection platform (101), wherein blade tip timing sensors (103) are provided on the inner wall of the detection platform (101) and the inner wall of the sealing housing (102), with blade tip timing sensors (103) distributed circumferentially. A gas turbine rotor (200) is provided on the detection stand (101) and positioned between the detection stand (101) and the sealing housing (102), A locking mechanism (300) includes a support seat (301) fixedly provided on the outer wall of the detection stand (101), and a support shaft (302) fixedly provided on the top end of the support seat (301), wherein a locking block (303) is rotatably connected to the outer wall of the support shaft (302), and further includes a counterweight (304) fixedly provided on the outer wall of the locking block (303), wherein a support pad (305) is provided on the support seat (301), The device comprises a pressing member (401) fixedly provided on the outer wall of the sealing housing (102), and a lifting mechanism (400) including a lifting assembly (402) fixedly provided on the outer wall of the pressing member (401), During the process in which the sealing housing (102) descends and adheres to the detection stage (101), the pressing member (401) can push the locking block (303) in such a displaced manner, and when the sealing housing (102) adheres to the detection stage (101), the counterweight (304) pushes down the locking block (303) in such a displaced manner, and the locking block (303) locks and positions the pressing member (401). A vibration detection device for gas turbine blades, characterized by the above.

2. Multiple uniformly distributed guide posts (101a) are fixedly provided on the top edge of the detection stage (101), and multiple uniformly distributed docking holes (102a) are provided on the bottom edge of the sealing housing (102). The vibration detection device for a gas turbine blade according to claim 1, characterized in that the outer wall of the guide post (101a) and the inner wall of the docking hole (102a) are slidably connected.

3. An arc-shaped surface (303a) is provided on the side of the locking block (303) away from the counterweight (304), and an adhesive surface (303b) is provided on the side of the locking block (303) closer to the support pad (305). The vibration detection device for a gas turbine blade according to claim 1 or 2, characterized in that the pressing member (401) includes a pressing block (401a) fixedly provided on the outer wall of the sealing housing (102), and a contact arc surface (401c) provided on the side of the pressing block (401a) away from the sealing housing (102).

4. The gas turbine blade vibration detection device according to claim 3, wherein the lifting assembly (402) includes a lifting frame (402a) fixedly provided on the outer wall of the pressing block (401a), and a position limiting bush (402b) fixedly provided on the top of the lifting frame (402a), a cushioning material (402c) slidably connected to the inner wall of the position limiting bush (402b), and a lifting head (402d) fixedly attached to the top end of the cushioning material (402c).

5. The vibration detection device for a gas turbine blade according to claim 4, wherein the cushioning material (402c) includes a slide rod (402c-1) slidably provided on the inner wall of the position limiting bush (402b), and a contact sleeve (402c-2) fixedly provided on the bottom end of the slide rod (402c-1), a push plate (402c-3) fixedly attached to the bottom end of the contact sleeve (402c-2), a first spring (402c-4) fitted to the outer wall of the contact sleeve (402c-2) and the slide rod (402c-1), and the cushioning material (402c) further includes an insertion rod (402c-5) fixedly provided on the bottom end of the push plate (402c-3).

6. The pressing member (401) further includes a through hole (401b) provided in the pressing block (401a), The vibration detection device for a gas turbine blade according to claim 5, characterized in that the locking block (303) is provided with an insertion groove (303c).

7. The vibration detection device for a gas turbine blade according to claim 6, characterized in that a positioning hole (301a) is provided at the top of the support seat (301).

8. The lifting mechanism (400) further includes a moving assembly (403) fixedly provided on the outer wall of the push plate (402c-3), The vibration detection device for a gas turbine blade according to claim 7, characterized in that the moving assembly (403) includes a connecting rod (403a) fixedly provided on the outer wall of the push plate (402c-3), and an engaging member (403b) fixedly provided on the end of the connecting rod (403a).

9. The engaging member (403b) includes a housing sleeve (403b-1) fixedly provided at the bottom end of the connecting rod (403a), and a second spring (403b-2) fixedly provided within the housing sleeve (403b-1), with a slide plate (403b-3) fixedly attached to the end of the second spring (403b-2), and a contact block (403b-4) fixedly attached to the end of the slide plate (403b-3). The vibration detection device for a gas turbine blade according to claim 8, characterized in that a groove (303d) is provided on the outer wall of the locking block (303).

10. A guide surface (303e) is provided on the inner wall of the groove (303d), The vibration detection device for a gas turbine blade according to claim 9, characterized in that a slope (403b-5) is provided at the end of the contact block (403b-4).

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