Combustion chamber of a turbine engine comprising a through-part with an opening

Patent metadata

Field	Value
Publication number	US-2018045413-A1
Application number	US-201615552056-A
Country	US
Kind code	A1
Filing date	Feb 23, 2016
Priority date	Feb 25, 2015
Publication date	Feb 15, 2018
Grant date	—

Abstract

A combustion chamber of a turbine engine, including at least one wall defining the combustion chamber and including an aperture for enabling a through-part to pass therethrough. The through-part includes, in the portion thereof located within the combustion chamber, at least one opening able to create an air film to cool the area downstream of the through-part.

First claim

1 . A combustion chamber of a turbine engine, comprising at least one wall defining the combustion chamber and comprising an aperture for enabling a through-part to pass therethrough, said through-part comprising, in the portion thereof located within the combustion chamber, at least one opening able to create an air film for cooling the area downstream of the through-part, wherein the inner surface of said at least one wall includes two tongues extending parallel to each other, able to generate an air film for cooling said at least one wall, the through-part being located between both tongues.

2 . The combustion chamber according to claim 1 , wherein said at least one opening of the through-part corresponds to a slot made on the surface of the through-part especially of an oblong shape.

3 . The combustion chamber according to claim 1 , wherein said at least one opening of the through-part extends longitudinally along the annular edge of the through-part, over at least one quarter of the annular edge of the through-part.

4 . The combustion chamber according to claim 1 , wherein said at least one opening of the through-part is formed at the radially inner end of the through-part.

5 . The combustion chamber according to claim 1 , wherein said at least one opening of the through-part extends parallel to the direction of the cooling air flow supplying it.

6 . The combustion chamber according to claim 1 , wherein said at least one wall comprises the radially outer annular wall of the combustion chamber.

7 . The combustion chamber according to claim 1 , wherein said at least one wall comprises the radially inner annular wall of the combustion chamber.

8 . The combustion chamber according to claim 1 , wherein said at least one wall comprises the chamber bottom annular wall of the combustion chamber.

9 . The combustion chamber according to claim 1 , wherein said at least one wall comprises a plurality of micro-perforations to enable an inlet of cooling air in the combustion chamber for cooling said at least one wall.

10 . The combustion chamber according to claim 1 , wherein said through-part is a cooling bushing for a spark plug.

11 . A turbine engine, comprising a compressor, and a combustion chamber according to claim 1 , disposed in an annular enclosure arranged at the outlet of the compressor, and wherein a portion of an air flow coming from the compressor is intended to bypass the combustion chamber along said at least one wall.

Assignees

• Safran Helicopter Engines

Inventors

• Lamaison Olivier
• Savary Nicolas

Classifications

• F23R3/045 Primary

  using pipes · CPC title

• F02C7/266

  Electric (sparking plugs H01T) · CPC title

• F23R3/52 Primary

  Toroidal combustion chambers · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2260/606

  Bypassing the fluid · CPC title