Turbomachine combustion chamber comprising an airflow guide device of specific shape

Patent metadata

Field	Value
Publication number	US-10443850-B2
Application number	US-201615567633-A
Country	US
Kind code	B2
Filing date	Apr 21, 2016
Priority date	Apr 23, 2015
Publication date	Oct 15, 2019
Grant date	Oct 15, 2019

Abstract

A combustion chamber for a turbomachine that includes a chamber end wall and a plurality of air and fuel injection systems distributed circumferentially about an axis of the combustion chamber. The combustion chamber includes, associated with each injection system, a guide device for guiding an airflow including at least one wall mounted on the injection system and projecting in the upstream direction, one wall acting as an obstacle to a circumferential flow of air around the axis. The one wall of the guide device for guiding the airflow has a shape substantially defining a quarter of a spheroid the interior volume of which forms a guide scoop for guiding the airflow feeding the combustion chamber.

First claim

The invention claimed is:

1. A combustion chamber for a turbomachine, comprising a chamber end wall arranged at the upstream end of the combustion chamber and a plurality of air and fuel injection systems distributed circumferentially about an axis of the combustion chamber and mounted in the chamber end wall, the combustion chamber further comprising, associated with each injection system, a guide device for guiding an airflow comprising at least one wall mounted on the injection system and projecting in the upstream direction, said at least one wall acting as an obstacle to a circumferential flow of air around the axis of the combustion chamber,
wherein said at least one wall of the guide device for guiding the airflow has a shape defining a quarter of a spheroid the interior volume of which forms a guide scoop for guiding the airflow feeding the combustion chamber.

2. The combustion chamber according to claim 1 , wherein said at least one wall of the guide device comprises a first edge and a second edge respectively lying in a first cutting plane and a second cutting plane orthogonal to each other, the guide device being mounted on the injection system by the second edge of said at least one wall.

3. The combustion chamber according to claim 2 , wherein an axis of the injection system lies in the first cutting plane, the first edge then being intersected at a middle of the first edge by the axis of the injection system and forming the upstream edge delimiting an air inlet opening of the guide device.

4. The combustion chamber according to claim 1 , wherein said at least one wall of the guide device comprises at least one discharge orifice, situated opposite an air inlet opening of the guide device.

5. The combustion chamber according to claim 1 , wherein the guide device is mounted on an air and fuel injector of the injection system.

6. The combustion chamber according to claim 5 , wherein the guide device is brazed onto the air and fuel injector.

7. The combustion chamber according to claim 1 , wherein the guide device is metal.

8. The combustion chamber according to claim 1 , wherein the axial and/or radial space requirement of the guide device is similar to that of an air and fuel injector of the injection system.

9. A turbomachine, comprising the combustion chamber according to claim 1 .

10. The turbomachine according to claim 9 , further comprising a centrifugal compressor, the output of which is connected to a radial diffuser, the radial diffuser being connected to a flow diverter emerging in a radially external region of an enclosure wherein the combustion chamber is housed.

Assignees

• Safran Aircraft Engines

Inventors

• Bourgois Sebastien Alain Christophe
• Lunel Romain Nicolas
• Bernard Clement
• Dos Santos Frederic
• Loval Sebastien

Classifications

• F23R3/16 Primary

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic