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Inter-plane sealing assembly for high-temperature zone gap of gas turbine

A technology for gas turbines and sealing components, which is applied to combustion chambers, combustion methods, combustion equipment, etc., can solve problems such as difficulty in meeting use requirements, and achieve the effect of wide application range and convenient installation.

Inactive Publication Date: 2021-03-09
中国船舶重工集团公司第七0三研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When the gap components in the high temperature area inside the gas turbine have sealing requirements, the existing technologies are difficult to meet the use requirements

Method used

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  • Inter-plane sealing assembly for high-temperature zone gap of gas turbine
  • Inter-plane sealing assembly for high-temperature zone gap of gas turbine
  • Inter-plane sealing assembly for high-temperature zone gap of gas turbine

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Embodiment Construction

[0020] The present invention is described in more detail below in conjunction with accompanying drawing example:

[0021] combine Figure 1a-Figure 4d , In Figure 1, there is a gap between the diffuser section and the support plate at the compressed air inlet of the combustion chamber. The traditional seal is generally sealed with a compressed gasket and fixed with fastening bolts. Because the current structure is limited by space, and the air flow through it is high-temperature and high-pressure air, the traditional structure is difficult to meet. In order to ensure that the compressed air from the compressor completely enters the combustion chamber, a clasp-type sealing assembly is invented between the support plate and the diffuser section, and a high-temperature alloy material is selected. Corrosion, easy installation, no fasteners, long life and other advantages.

[0022] Referring to Fig. 2, the present invention mainly includes two groove holders and a sealing snap ri...

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Abstract

The invention aims to provide an inter-plane sealing assembly for a high-temperature zone gap of a gas turbine. The inter-plane sealing assembly comprises an upper groove clamping seat, a lower grooveclamping seat and a sealing clamping ring, the upper groove clamping seat and the lower groove clamping seat are fixed to the upper end face and the lower end face of a gap between a diffusion section at a compressed air inlet of a combustion chamber and a supporting plate correspondingly, and the two ends of the sealing clamping ring are installed in the upper groove clamping seat and the lowergroove clamping seat correspondingly; and the two ends of the sealing clamping ring are open circular rings, the diameter of the circular rings is larger than the inner size of the groove clamping seat, when the sealing clamping ring is installed in the upper groove clamping seat and the lower groove clamping seat, the circular rings contract and deform inwards, and inter-plane sealing is achievedthrough deformation and springback of a steel structure of the sealing clamping ring. The sealing assembly can be installed in a whole ring mode, fasteners do not need to be adopted for fastening, installation convenience is guaranteed, and meanwhile the risk that due to long-term operation of the gas turbine, the fasteners are broken and damage equipment is avoided; and the sealing assembly is not limited by the plane position, the groove clamping seat can be staggered, an included angle can be formed between the two planes, and the application range is extremely wide.

Description

technical field [0001] The invention relates to a sealing structure, in particular to a sealing structure of a gas turbine. Background technique [0002] The sealing structure refers to a device that is kept in contact with at least one pair of sections perpendicular to the axis under the action of fluid pressure and the elastic force (or magnetic force) of the compensation mechanism, as well as the cooperation of auxiliary seals, to prevent fluid leakage. As a key component, it is widely used in various fields, and the conditions of use are also diverse. [0003] In the gas turbine design process, there are a large number of sealing components, mainly including metal wound gaskets, graphite gaskets, spherical seals, ferrule steel expansion seals, etc. Metal wound gaskets generally use compression seals and require the use of fasteners; graphite gaskets are easily damaged; spherical seals and ferrule steel expansion seals are generally used for pipeline installation. When ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/04
CPCF23R3/04F23R2900/00012
Inventor 孙鹏冉军辉林枫齐秀龙王威张晨曦任艳平张国强
Owner 中国船舶重工集团公司第七0三研究所
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