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Double ended brush seal assembly for a compressor

A technology of brush seals and compressors, which is applied to the sealing of engines, components of pumping devices for elastic fluids, engine components, etc., and can solve problems such as complex and expensive seals

Inactive Publication Date: 2013-07-10
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Providing multiple seals for leak paths in a compressor can become expensive and complicated

Method used

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  • Double ended brush seal assembly for a compressor
  • Double ended brush seal assembly for a compressor
  • Double ended brush seal assembly for a compressor

Examples

Experimental program
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Embodiment Construction

[0020] FIG. 1 shows a schematic exemplary power generation system indicated by reference numeral 10 . Power generation system 10 is a gas turbine system having compressor 20 (shown in FIG. 1 ), combustor 22 and turbine 24 . Air enters power generation system 10 through air inlet 30 connected to compressor 20 (shown in FIG. 1 ) and is compressed by compressor 20 (shown in FIG. 1 ). The compressed air is then mixed with fuel by fuel nozzles 34 . Fuel nozzles 34 inject an air-fuel mixture at a specific ratio into combustor 22 for combustion. Combustion generates hot pressurized exhaust gases, which drive blades (not shown) located within turbine 24 .

[0021] 2-3 illustrate the axial brush seal assembly 54 positioned between the rotor 46 of the compressor 20 (shown in FIG. 1 ) and the compressor discharge housing barrel 42 . Axial brush seal assembly 54 serves to reduce or prevent gas flow leakage into central gas flow region 60 or high pressure packing (HPP) region 64 during ...

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PUM

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Abstract

The invention relates to a double ended brush seal assembly for a compressor. A system having an axial brush seal assembly is provided, having a first component, a second component, at least two plates that generally oppose one another, a plurality of seal bristles, and a base plate. The first component has a first sealing surface. The second component has a second sealing surface. The plurality of seal bristles are received between the at least two plates. The plurality of seal bristles include a first end portion and a second end portion. The first end portion is configured to selectively seal against the first sealing surface and the second end portion is configured to selectively seal against the second sealing surface. At least one of the at least two plates is connected to the base plate, and the base plate supports the brush seal assembly. The axial brush seal assembly provides sealing for two leakage paths simultaneously.

Description

technical field [0001] The subject matter disclosed herein relates to systems having axial brush seal assemblies, and more particularly to axial brush seal assemblies supported by a base plate and having a plurality of seal seals with first and second ends. bristles. Background technique [0002] A gas turbine typically includes a compressor, a combustor, one or more fuel nozzles, and a turbine. Air enters the gas turbine through the air inlet and is compressed by the compressor. The compressed air is then mixed with fuel supplied by the fuel nozzles. An air-fuel mixture is supplied to the burner for combustion at a specified ratio. Combustion generates pressurized exhaust gases, which drive the blades of the turbine. [0003] Compressors typically include at least one rotor assembly and at least one stator assembly. The stator assembly typically includes a plurality of vane segments arranged in an annular configuration about the axis of rotation of the compressor. The...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/08F04D19/00
CPCF01D11/001F01D11/005F05D2240/56F16J15/3288
Inventor K.S.沙
Owner GENERAL ELECTRIC CO