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Gas turbine brush seal arrangement for cabin air supply

A technology of jet engine and brush seal, which is applied to the sealing of engines, gas turbine devices, jet propulsion devices, etc., and can solve problems such as difficult sealing

Inactive Publication Date: 2005-03-23
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In an environment of high pressure that may reach 30 bar and high temperature that may reach 650 °C, various components will appear thermal and mechanical responses, so the relative displacement between the diffuser grid and the compressor casing in the axial and radial directions Basically, they are all on the order of 1.5mm, so it is very difficult to achieve the above-mentioned sealing

Method used

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  • Gas turbine brush seal arrangement for cabin air supply
  • Gas turbine brush seal arrangement for cabin air supply
  • Gas turbine brush seal arrangement for cabin air supply

Examples

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Embodiment Construction

[0034] Figure 1 to Figure 5 The prior art shown in has been discussed previously and therefore no further explanation is needed.

[0035] 6 to 8 show a sealing arrangement consisting of a brush seal 50 provided between the radially inner portion 7a of the annular structure 7 substantially parallel to the strut 13 and the upstream portion of the outer shroud 12 of the diffuser grid 10 between 12a. In Figures 6 to 8, those with the Figures 1 to 5 The same elements or parts are denoted by the same reference numerals.

[0036] A first embodiment of the invention is shown in FIG. 6 . The upstream portion 12a of the housing 12 has at its periphery an upstream flange 33a and a downstream flange 33b defining a groove 32 therebetween, the radially inner portion or body 51 of a brush seal being fastened by rivets 34. Retained in said groove 32 , the brush seal has outwardly extending bristles 52 . The body 51 can be configured in the form of a segment, or in the form of a spliced...

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Abstract

The engine has a crankcase whose outer shell is fixed to an annular structure (7) by a joint with brush (50) fixed to a periphery of an upstream part of an outer case (12) of a diffuser grid (10). The joint has radially extending bristles (52) supported on an inner surface (54) of a cylindrical sleeve (53). The sleeve integrated to the structure that is connected to an outer shell (6) of a compressor (1), surrounds the joint.

Description

technical field [0001] The invention relates to a jet engine comprising, from upstream to downstream (the upstream and downstream directions being defined by the direction of circulation of the main air flow) a high pressure compressor comprising a casing, a diffuser grid and a combustion chamber , which radially defines the main air flow duct and is connected to a radially outwardly extending annular structure, the diffuser grille includes an outer shroud in the axial extension direction of the compressor casing, and the outer shroud is connected to a rearward connected by oriented conical struts defining the upstream end of the combustion chamber, said struts themselves being connected to an outer casing extending in the upstream direction and secured to said annular structure by means of fastening means, The struts, outer casing and annular structure define a cavity around the diffuser grille, the struts are provided with vent holes to communicate the end of the combustion ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K1/80F01D11/00F01D25/24F02C7/28F02K1/00
CPCF05B2240/12F01D11/005F05D2240/12F02C7/28F05B2240/11F01D25/246F05D2240/11F05B2240/571F05D2240/56F02K1/80F02K1/00
Inventor 吉勒·勒普雷特劳伦特·马尔纳斯
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A