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Jet engine cabin air bleed cavity sealing device

一种喷气发动机、主气流的技术，应用在发动机的密封、喷气推进装置、燃气轮机装置等方向，能够解决密封困难等问题

Active Publication Date: 2009-05-20
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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  • Jet engine cabin air bleed cavity sealing device
  • Jet engine cabin air bleed cavity sealing device
  • Jet engine cabin air bleed cavity sealing device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0030] Figure 1 to Figure 5 The prior art shown in has been discussed previously and therefore no further explanation is needed.

[0031] Figure 6 The downstream part of a jet engine compressor is shown in , wherein the compressor block has a casing 6 defining the main gas flow duct on the outside, connected to an annular structure 7 with a V-shaped cross-section, the outer periphery of which has Flange 16 ; diffuser grid 10 has a casing 12 in the direction of extension of the casing 6 , a gap 21 is formed between the upstream portion 12 a of the casing 12 and the downstream end 6 a of the casing 6 of the compressor.

[0032] The outer casing 12 of the diffuser grid 10 is connected to an inclined strut 13 which is itself connected to an outer casing 14 extending in the upstream direction and having a flange 15 at its upstream end. The flange 15 and the flange 16 are fastened together by bolts.

[0033] The strut 13 has at least one through hole 22 delimited by a cylindric...

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PUM

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Abstract

The invention relates to the sealing of air discharged into a compartment, said air flowing through a cavity delimited on the one hand by the shell (6) of the compressor and the annular structure (7) connected to the shell and on the other hand by the expansion The outer casing (12) of the compressor grille and the struts (13) connected with said outer casing and the outer casing (14) of the engine, which are fixed on the ring structure (7) by bolts. A pipe body (60) is arranged between the through hole (22) of the pillar (13) and the vent hole (23), and the first end (61) of the pipe body is installed in the vent hole (23) through the first rotary connection , the first rotary connection part can rotate freely but its translational movement is blocked, the second end (63) of the pipe body is installed in the through hole (22) through the second rotary connection part, and the second rotary connection part The part can be freely rotated and translated freely.

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 shroud and annular structure define a cavity around the diffuser grille, the struts are provided with through-holes for air release to communicate the end...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/28F01D11/00F16J15/16F02K1/80F01D9/06F01D25/24F02K1/00
CPCF01D25/24F01D9/065F02K1/80F02K1/00
Inventor 吉勒·勒普雷特
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A