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Sealing structure between turbine stator components

A turbine stator and component technology, applied to engine components, gas turbine devices, machines/engines, etc., can solve problems such as difficult to seal with thin-walled parts, easy to wear on the surface of the expansion ring, and inconvenient disassembly and assembly, and achieve enhanced sealing and sealing The effect, the effect of ensuring the sealing requirements and reducing the amount of wear

Active Publication Date: 2019-08-23
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The existing technology generally adopts contact floating seal structures such as spherical seals, expanding ring seals, graphite seals or w-ring seals to ensure sealing and working margins, but the structure size of spherical seals is relatively large and requires certain The contact area of ​​the spherical surface is large to ensure the sealing effect, and at the same time, a gap needs to be designed between the contact surfaces to ensure the assembly, and the sealing effect is not good; the sealing of the expansion ring is to ensure the cold state of the assembly. ;The structural size of the graphite seal is too large, which is difficult to be used for sealing thin-walled parts; the w-ring seal is difficult to be used in the case of a large floating amount due to the limited compression of the w-ring, and the cost of the w-ring is relatively high

Method used

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  • Sealing structure between turbine stator components
  • Sealing structure between turbine stator components
  • Sealing structure between turbine stator components

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Experimental program
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Effect test

Embodiment 1

[0035] Such as figure 1 As shown, the present invention provides a sealing structure between turbine stator components, including sealing components 1 and fixing bolts 6;

[0036] Such as diagram 2-1 and Figure 2-2 As shown, the sealing component 1 includes at least two layers of shrapnel layers that are sheathed sequentially from the inside to the outside. In this embodiment, the number of shrapnel layers is two layers, and it can also be as Figure 2-3 Three layers of shrapnel layers are shown, and the number of layers of shrapnel layers is determined according to the working conditions and requirements of the site; the shrapnel layers are cylindrical, and each shrapnel layer includes at least three shrapnel 3 arranged in the circumferential direction, and the shrapnel 3 of each shrapnel layer The number is the same, and in this embodiment, the number of shrapnel 3 contained in each shrapnel layer is five; adjacent shrapnel 3 in the same shrapnel layer leave a shrapnel g...

Embodiment 2

[0046] The present invention provides another sealing structure between turbine stator components, including a sealing component 1 and fixing bolts 6, and a plurality of ferrules 10. The structural schematic diagram of the sealing structure between turbine stator components in this embodiment is as follows Figure 4 As shown, this sealing structure can be used to seal the outer flow channel of the high-pressure turbine test piece. One end of the sealing part 1 fixed on the first stator part 7 is the sealing fixed end, and the other end of the sealing part 1 is connected to the second stator Part 8 is in interference contact, and the end of the sealing part 1 that is in contact with the second stator part 8 is the sealing contact end;

[0047] The part of the second stator part 8 that is in contact with the sealing part 1 is a slope surface, the sealing contact end of the sealing part 1 is stretched by the slope surface, and the passage between the sealing contact end and the se...

Embodiment 3

[0052] The present invention provides yet another sealing structure between turbine stator parts, including a sealing part 1 and fixing bolts 6, and a sealing ring 9, and one end of the sealing part 1 fixed on the first stator part 7 is sealed and fixed The other end of the sealing part 1 is in interference contact with the second stator part 8, and the end of the sealing part 1 in contact with the second stator part 8 is the sealing contact end;

[0053] The structural schematic diagram of the sealing structure between the turbine stator components in this embodiment is as follows Figure 5 As shown, the sealing structure can be used for sealing the outer flow channel of the gas turbine exhaust section. The part of the second stator part 8 that is in contact with the sealing part 1 is a plane, and the sealing ring 9 is detachably fixed on the second stator part. 8, preferably, the sealing ring 9 is fixed on the second stator part 8 by bolts, a groove is formed between the sea...

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Abstract

The invention relates to the technical field of turbine part sealing structure design, and specifically provides a turbine stator part sealing structure. The sealing structure comprises a sealing part and a fixing bolt. The sealing part comprises at least two elastic piece layers which are sequentially arranged in a sleeving mode from inside to outside. The elastic piece layers are cylindrical. Each elastic piece layer comprises at least three elastic pieces arranged peripherally. The number of elastic pieces of all the elastic piece layers are equal. An elastic piece gap is reserved between every two adjacent elastic pieces in the same elastic piece layer peripherally. The elastic piece gaps of the adjacent elastic piece layers are peripherally formed in a staggered mode. The cross section of each elastic piece is in an arch shape. Each elastic piece is attached to and makes contact with two adjacent elastic pieces of the adjacent elastic piece layers. The seal part is peripherally provided with a plurality of common lap-joint portions. The common lap-joint portions are overlapped portions of all the elastic piece layers in the radial direction. The number of the common lap-joint portions is two times that of the elastic pieces of the same elastic piece layer. The fixing bolt penetrates through the common lap-joint portions, fixes one end of the sealing part to a first stator part and enables the other end of the sealing to be in interference fit with a second stator part.

Description

technical field [0001] The invention relates to the technical field of sealing structure design of turbine components, in particular to the sealing structure between turbine stator components. Background technique [0002] The development technology of aero-engines has reached a relatively high level, and it is difficult to make major breakthroughs in aerodynamics, performance, and heat transfer. However, some improvements in certain structural designs can reduce engine leakage losses, and components and The efficiency of the engine has been greatly improved, so more and more attention has been paid to the research on sealing technology. [0003] For components whose working conditions are mostly high temperature and high load, such as engine turbine components, the deformation of adjacent stator components is often inconsistent due to differences in temperature, pressure, and materials during the working process, and contact floating seals are usually used The structure is...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D11/00F02C7/28
Inventor 刘美王广宁杨利宁张傲李东彪
Owner AECC SHENYANG ENGINE RES INST