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Turbomachine with cabin bleed air through a tube with bi-ball joint

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

Active Publication Date: 2005-03-30
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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  • Turbomachine with cabin bleed air through a tube with bi-ball joint
  • Turbomachine with cabin bleed air through a tube with bi-ball joint
  • Turbomachine with cabin bleed air through a tube with bi-ball joint

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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] Image 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 cylindrica...

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PUM

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Abstract

The invention relates to the provision of sealing for bleeding air to the cabin, the air passing through a cavity delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and a strut connected to said external casing and to an external engine casing shell, this external casing shell being fastened to the annular structure by bolting. A tube is provided between the orifice in the strut and the outlet vent, a first end of which tube is mounted in said outlet vent by means of a swivel connection which is free to rotate and prevented from translational movement, and a second end of which tube is mounted in said orifice by means of a swivel connection which is free to rotate and free to move translationally.

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 Applications(China)
IPC IPC(8): F02K1/80F01D9/06F01D25/24F02K1/00
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