Snecma

Safran Aircraft Engines

Sebastien Loval

Christophe Chabaille

Romain Nicolas Lunel

Sebastien Alain Christophe Bourgois

Clement Bernard

Frederic Dos Santos

Benedicte Leleu

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.

Turbomachine combustion chamber comprising an airflow guide device of specific shape

A fuel dosing device for a fuel injector of an aircraft turbomachine, including an opening, a movable member for sealing the opening, and elastic return, with the member able to be displaced under the effect of the fuel pressure. The device includes a first outlet communicating with a primary circuit of the injector as well as a second outlet communicating with a secondary circuit. In addition, it is designed such that up to a defined level of displacement of the sealing member, the latter allows the fuel coming from the opening to reach the first outlet and, only beyond the defined level of displacement, the member allows the fuel coming from the opening to reach the second outlet.

Compact dosing device for an injector with two fuel circuits for an aircraft turbomachine

A fuel injector for a turbine engine is provided. The fuel injector includes a body including an admissions chamber for admitting fuel under pressure, a stop valve mounted in the body downstream from the admission chamber and designed to open at a first determined fuel pressure and to remain open beyond that first pressure in order to feed a primary fuel circuit, and a metering valve mounted in the body downstream from the stop valve and designed to open above a second determined fuel pressure, greater than the first pressure, and to remain open above the second pressure in order to feed a secondary fuel circuit. The stop valve and the metering valve form a common movable assembly.

Fuel injector for a turbine engine

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Bussy Saint Georges, France

Sebastien Loval