A gas turbine blade seal packing device

Abstract

The application provides a compression device for a gas turbine moving blade seal grate, and belongs to the technical field of gas turbines. The moving blade seal grate is provided with a bushing extending into the inside of a blade body of the blade. The compression device comprises a plurality of pressing plates. The butt joint portions of two adjacent pressing plates correspond to the bushing. The pressing plates are provided with limiting blocks inserted into the bushing. After the end portions of the adjacent pressing plates are butted, the two limiting blocks close to each other are inserted into the same bushing, and the two limiting blocks are in abutment with the inner wall of the bushing. Through the processing scheme, the probability of misalignment of the fitting surfaces of the adjacent moving blade seal grates is reduced, and the fitting relationship between the working surfaces of the adjacent moving blade seal grates can be ensured.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of gas turbines, in particular to a pressing device for a gas turbine blade seal. BACKGROUND

[0002] The gas turbine blade works in high temperature, high pressure and high speed for a long time. The blade tip seal can be used to seal the gas in the flow passage, and improve the vibration performance of the blade. Under the action of high speed, due to the mass and shape of the blade tip seal, the mass center distribution causes a large bending stress at the tip of the blade. This stress concentration phenomenon will greatly affect the performance and service life of the blade. At present, most of the domestic and foreign power turbine blades usually pass through the pre torsion design, so that the working surface of the blade seal has a certain tight contact under the working condition of the engine. However, under some extreme conditions, the deformation of the blade seal is large, and the tight contact cannot be guaranteed at this time. SUMMARY

[0003] Therefore, the present application provides a pressing device for a gas turbine blade seal, which solves the problems in the prior art, reduces the probability of misalignment of the adjacent blade seal mating surface, and ensures the cooperation between the adjacent blade seal working surfaces.

[0004] The pressing device for a gas turbine blade seal provided by the present application adopts the following technical scheme:

[0005] A pressing device for a gas turbine blade seal, the blade seal is provided with a insertion hole extending into the blade body of the blade, the pressing device comprises a plurality of pressing plates, the abutting portions of two adjacent pressing plates correspond to the insertion hole, the pressing plate is provided with a limiting block inserted into the insertion hole, after the abutting of the end portions of the adjacent pressing plates, the two limiting blocks close to each other are inserted into the same insertion hole, and the two limiting blocks are abutted against the inner wall of the insertion hole.

[0006] Optionally, the opposite sides of the two limiting blocks on the same pressing plate are respectively matched with the inner walls of the insertion holes of the two adjacent blades.

[0007] Optionally, after the abutting of the end portions of the adjacent pressing plates, the two limiting blocks close to each other abut against each other in the same insertion hole.

[0008] Optionally, the opposite sides of the two limiting blocks close to each other in the same insertion hole are provided with opposite grooves, and the opposite grooves of the two limiting blocks abut against each other after abutting, so as to form a through hole between the two limiting blocks.

[0009] Optionally, the outer contour of the combined two limiting blocks in the same insertion hole completely matches the inner wall of the insertion hole.

[0010] Optionally, the limiting block and the pressing plate are integrally arranged.

[0011] Optionally, the blade is a hollow rotor blade, and a cavity in the hollow rotor blade penetrates the dynamic blade sealing strip to form the insertion hole.

[0012] In summary, the present application has the following beneficial technical effects:

[0013] One pressing plate can effectively cover the left half of one dynamic blade sealing strip and the right half of the adjacent dynamic blade sealing strip, so that the matching surface between the adjacent dynamic blade sealing strips is completely covered by the pressing plate. For the matching surface between any adjacent dynamic blade sealing strips on the entire turbine ring, it is under the coverage of the pressing plate. Under the action of the pressing plate of the pressing device of the present application, the radial deformation of the edge of the dynamic blade sealing strip is inhibited, and the bending deformation of the dynamic blade sealing strip is greatly reduced, thereby greatly reducing the stress at the top of the blade. At the same time, since the bending deformation of the dynamic blade sealing strip is reduced, the probability of misalignment of the matching surface between the adjacent dynamic blade sealing strips is greatly reduced, and the matching relationship between the working surfaces of the adjacent dynamic blade sealing strips can be ensured, thereby ensuring the vibration characteristics of the blade.

[0014] Under the action of the pressing device, the bending deformation caused by the mass and the deviation of the mass center of the dynamic blade sealing strip and the tip section of the blade is greatly limited, thereby reducing a lot of design restrictions on the dynamic blade sealing strip. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed in the embodiments will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0016] Figure 1 is a structural schematic view of a blade;

[0017] Figure 2 is a structural schematic view of a cavity inside a blade;

[0018] Figure 3 is a structural schematic view of a matching surface between adjacent dynamic blade sealing strips;

[0019] Figure 4 is a structural schematic view of a pressing plate and a limiting block of the present application;

[0020] Figure 5 is a structural schematic view of the butt joint of two pressing plates of the present application;

[0021] Figure 6 is a structural schematic view of the matching of the pressing plate and the dynamic blade sealing strip of the present application;

[0022] Figure 7 Structure diagram of the connection between the pressing plate and the blade sealing grid of the present application;

[0023] Figure 8 Structure diagram of the cooperation between the limiting block and the insertion hole of the present application;

[0024] Figure 9 Structure diagram of the cooperation between the limiting block and the insertion hole of the present application;

[0025] Explanation of reference numerals: 1, blade; 2, blade sealing grid; 3, blade body; 4, tenon; 5, cavity; 51, insertion hole; 6, pressing plate; 7, limiting block; 10, cooperation surface; 11, through hole. DETAILED DESCRIPTION

[0026] The embodiments of the present application will be described in detail below with reference to the drawings.

[0027] The above embodiments are only a part of the embodiments of the present application, and not all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and each detail in the specification can be modified or changed based on different views and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0028] It should be noted that the various aspects of the embodiments described below are within the scope of the appended claims. It should be apparent that the aspects described herein can be embodied in a wide variety of forms and that any specific structure and / or function described herein is merely illustrative. Based on the teachings herein one skilled in the art should appreciate that an aspect described herein can be implemented independently of any other aspects and that an aspect described herein can be implemented both as any number of software and / or hardware configurations and that the examples described herein are not limited to any particular software and / or hardware configuration. Examples of software can include, but are not limited to, firmware, resident software, micro-code, etc. Examples of hardware can include, but are not limited to, any desired combination of special-purpose hardware and / or general-purpose hardware. Examples of such hardware also can include, but are not limited to, any combination of the following: a central processing unit (CPU), a microprocessor, a microcontroller, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), etc.

[0029] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The drawings only show the components related to this application and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0030] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0031] This application provides a clamping device for sealing the teeth of a gas turbine motor blade.

[0032] like Figures 1-8 As shown, a clamping device for a gas turbine moving blade sealing grate is provided. Multiple blades 1 of the gas turbine are circumferentially distributed, and the moving blade sealing grate 2 corresponds one-to-one with the blade 1. The moving blade sealing grate 2 is provided with an insertion hole 51 extending into the blade body 3 of the blade 1. The insertion hole 51 can be independently designed. It can be formed by opening the moving blade sealing grate 2 towards the blade body 3, or it can be formed by the cavity 5 in the blade body 3 of the hollow blade 1 penetrating the moving blade sealing grate 2. The clamping device includes multiple pressure plates 6, with moving blade sealing grates 2 arranged in a ring around the periphery of the pressure plates 6. The mating portions of two adjacent pressure plates 6 correspond to the insertion holes 51. Each pressure plate 6 is provided with a limiting block 7 for insertion into the insertion holes 51. After the ends of adjacent pressure plates 6 are mated, two adjacent limiting blocks 7 are inserted into the same insertion hole 51, and the two limiting blocks 7 abut against the inner wall of the insertion hole 51. Specifically, the two limiting blocks 7 are interference-fitted with the insertion hole 51. After all pressure plates 6 are installed, the sides of adjacent pressure plates 6 abut against each other. At the same time, the limiting blocks 7 in the same insertion hole 51 abut against the inner wall of the insertion hole 51, so that the pressure plates 6 and blades 1 form a stable connection. Two adjacent pressure plates 6 are connected to the moving blade sealing grates 2 on the same blade 1, and the moving blade sealing grates 2 of two adjacent blades 1 are connected to the same pressure plate 6.

[0033] like Figures 5-7 As shown, taking three adjacent blades 1 and two pressure plates 6 as an example, the mating part of the two pressure plates 6 corresponds to the insertion hole 51 of the middle blade 1. The two limiting blocks 7 on the two pressure plates 6 that are close to each other are inserted into the insertion hole 51 on the moving blade sealing grate 2 of the middle blade 1. The remaining two limiting blocks 7 that are far apart from each other are inserted into the insertion holes 51 of the other two moving blade sealing grate 2 respectively.

[0034] One pressure plate 6 can effectively cover the left half of one moving blade sealing fence tooth 2 and the right half of the adjacent moving blade sealing fence tooth 2, and two limiting blocks 7 on one complete pressure plate 6 limit the relative displacement between the adjacent moving blade sealing fence teeth 2, so that the matching surface 10 between the adjacent moving blade sealing fence teeth 2 is completely covered by the pressure plate 6. For the matching surface 10 between any adjacent moving blade sealing fence teeth 2 on the entire turbine ring, it is covered by the pressure plate 6. Under the action of the pressure plate 6 of the pressure device in the present application, the radial deformation of the edge of the moving blade sealing fence tooth 2 is inhibited, and the bending deformation of the moving blade sealing fence tooth 2 is greatly reduced, so that the stress at the top of the blade 1 is greatly reduced. At the same time, since the bending deformation of the moving blade sealing fence tooth 2 is reduced, the probability of misalignment of the matching surface 10 between the adjacent moving blade sealing fence teeth 2 is greatly reduced, and the matching relationship between the working surfaces of the adjacent moving blade sealing fence teeth 2 can be guaranteed, thereby ensuring the vibration characteristics of the blade 1.

[0035] At present, there are many restrictions on the design of the moving blade sealing fence tooth 2 to ensure its mass and centroid position to reduce the stress at the tip of the blade 1 and the bending deformation of the moving blade sealing fence tooth 2. Under the action of the pressure device, the bending deformation caused by the deviation of the mass and the centroid of the cross section of the moving blade sealing fence tooth 2 from the tip of the blade 1 is greatly limited, thereby reducing many design restrictions on the moving blade sealing fence tooth 2.

[0036] The opposite sides of the two limiting blocks 7 on the same pressure plate 6 respectively abut the inner walls of the corresponding insertion holes 51. By making the sides of the limiting blocks 7 corresponding to the insertion holes 51 all abut the inner walls of the insertion holes 51, the contact area of the limiting blocks 7 and the insertion holes 51 is increased, and the stability of the connection between the pressure device and the blade 1 is improved. Specifically, the opposite sides of the two limiting blocks 7 on the pressure plate 6 can be interference-fitted with the corresponding insertion holes 51, so that the sides of the limiting blocks 7 corresponding to the insertion holes 51 all abut the inner walls of the insertion holes 51.

[0037] After the end portions of the adjacent pressure plates 6 are butted, the two limiting blocks 7 close to each other are in abutment with each other in the same insertion hole 51. The force between the two limiting blocks 7 is stabilized to improve the stability of the connection between the two pressure plates 6 and reduce the deformation of the moving blade sealing fence tooth 2, thereby reducing the stress at the tip.

[0038] As shown in Figure 9 The opposite sides of the two limiting blocks 7 in the same insertion hole 51 are provided with opposite grooves, and the opposite grooves on the two limiting blocks 7 form a through hole 11 between the two limiting blocks 7 after the abutment. For the hollow blade 1 with a cooling channel inside, the gas in the cooling channel inside the blade 1 can flow out through the through hole 11.

[0039] The outer contour of the two combined limiting blocks 7 in the same said socket 51 completely matches the inner wall of the socket 51. The outer contour shape of the two combined limiting blocks 7 is completely consistent with the contour shape of the socket 51 of the blade sealing grid 2, so that the two combined limiting blocks 7 fill the socket 51, the two combined limiting blocks 7 and the socket 51 are in interference fit, the limiting blocks 7 are also tightly against each other, the relative displacement between the socket 51 and the limiting blocks 7 is reduced, and the stability of the connection between the pressing plate 6 and the blade sealing grid 2 is ensured.

[0040] The limiting blocks 7 and the pressing plate 6 are integrally arranged. The structural strength of the pressing plate 6 and the limiting blocks 7 is improved, and the cooperation between the pressing plate 6 and the blade sealing grid 2 is stable.

[0041] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any skilled person in the art can easily think of changes or replacements within the technical range disclosed in the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A gas turbine bucket shroud strip packing device, characterized by, The extension hole extends into the inside of the blade body of the blade, the pressing device comprises a plurality of pressing plates, the abutting portions of two adjacent pressing plates correspond to the extension hole, the pressing plate is provided with a limiting block inserted into the extension hole, and the end portions of two adjacent pressing plates abut against each other, the two limiting blocks close to each other are inserted into the same extension hole, and the two limiting blocks abut against the inner wall of the extension hole. The blade is a hollow rotor blade, the cavity in the hollow rotor blade forms the extension hole through the blade seal grid, the opposite sides of the two limiting blocks on the same pressing plate respectively abut against the inner walls of the extension holes of two adjacent blades, the end portions of two adjacent pressing plates abut against each other, the two limiting blocks close to each other abut against each other in the same extension hole, and the outer contours of the two limiting blocks combined in the same extension hole completely abut against the inner wall of the extension hole.

2. A gas turbine bucket shroud hold-down device according to claim 1, characterised in that, The opposite recesses are arranged on the sides of the two limiting blocks close to each other in the same extension hole, and the recesses on the two limiting blocks abut against each other to form a through hole between the two limiting blocks.

3. The gas turbine bucket shroud hold-down device according to Claim 1, wherein, The limiting block and the pressing plate are integrally arranged.

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