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Gas turbine engine combustion chamber comprising CMC deflectors

A gas turbine and combustion chamber technology, which is applied in the combustion chamber of a turbine and in the field of gas turbines, and can solve problems such as difficulty, different expansion coefficients, etc.

Active Publication Date: 2011-05-11
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

[0009] However, fitting this type of component into metallic structures presents significant difficulties due to their significantly different coefficients of expansion

Method used

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  • Gas turbine engine combustion chamber comprising CMC deflectors
  • Gas turbine engine combustion chamber comprising CMC deflectors
  • Gas turbine engine combustion chamber comprising CMC deflectors

Examples

Experimental program
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Embodiment Construction

[0025] figure 2 Shown is a chamber end according to one embodiment of the invention. The end wall 11 of the chamber 10 is protected from radiation from the combustion zone of the deflector 12 made of CMC. The deflector is substantially identical in shape to the prior art deflector 9 and has a substantially flat portion 12a positioned parallel to the wall 11 and two portions 12b curved towards the outer and inner walls. The deflector 12 is open in its central part and comprises a cylindrical part 12c having the same axis as the carbonizing air supply system 13 .

[0026] The metal sleeve 14 is fixed in the opening of the end wall 11 of the chamber. A polished joint 14a holds the sleeve 14 against the inner edge of the opening in the wall 11 . The sleeve comprises a cylindrical portion 14b and a radial portion 14c forming a space with a retaining cup 15 welded to its periphery. Transverse teeth 14 d oriented towards the axis of the opening in the wall 11 are formed on the i...

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PUM

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Abstract

The present invention relates to a gas turbine engine combustion chamber comprising at least one deflector (12) mounted on the chamber end wall (11) provided with an opening for a carburetted air supply device (13). The chamber is characterized in that the deflector (12) comprises an opening, corresponding to the chamber end wall opening, with an annular cylindrical part (12c) for attachment to the said wall, the said cylindrical part (12c) comprising a mechanical attachment means (12c1) collaborating with a complementary attachment means (14d, 26d) on a metal sleeve (14, 26) secured to the said wall (11) and a cylindrical centring cup (16a, 26a) fixed by one end to the said sleeve (14, 26) and housed inside the cylindrical part (12c) of the deflector (12).

Description

technical field [0001] The present invention relates to the field of gas turbines and more particularly to the field of combustors of such turbines. Background technique [0002] The combustor of the gas turbine receives compressed air from an upstream high-pressure compressor and provides heated gas for combustion in a fuel-supplied combustion zone. In this way, said chamber comprises a chamber end wall located upstream and connected to the respective fuel injection system. figure 1 Chamber showing prior art. The annular chamber 1 is accommodated in the engine housing 2 downstream of the compressed air diffuser 3 . It comprises an inner wall 4 and an outer wall 5, between which a combustion zone is defined. Said chamber comprises, in its upstream part, a transverse chamber end wall 6 in which openings are formed, each opening equipped with a carbonizing air supply system 7 . Such systems are supplied with fuel from liquid fuel injectors and include concentrically stacke...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/28
CPCF23R3/283
Inventor 西拉维·杜瓦尔迪迪尔·希波吕忒·埃尔南德斯罗曼·尼古拉斯·吕内尔
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A