Safran Aircraft Engines

Clément Yves Emile Bernard

Christophe Chabaille

Sébastien Christophe Loval

An injector nose for a turbomachine includes a primary fuel circuit ending in a fuel-ejection nozzle, and a secondary fuel circuit including an annular-shaped terminal fuel-ejection part arranged around the fuel-ejection nozzle. An upstream part of the primary fuel circuit includes an annular channel, which extends around the secondary fuel circuit and is defined by an external wall of the injector nose. The injector nose includes air intake channels extending through the annular channel and having inlets opening into the external wall and outlets opening into an annular air injection channel arranged radially to the inside in relation to the terminal fuel-ejection part, around the fuel-ejection nozzle, and cooperating with the terminal fuel-ejection part in order to form an aerodynamic secondary injector.

Injector nose for turbomachine comprising a primary fuel circuit arranged around a secondary fuel circuit

An injector nose for a turbomachine includes a primary fuel circuit terminated by a fuel ejection nozzle defining an injection axis (), and a secondary fuel circuit () comprising a secondary fuel swirler () formed of swirler channels () opening into a terminal fuel ejection portion () of annular shape arranged around the fuel ejection nozzle. Each swirler channel () has a passage section which decreases in a direction going from an upstream end () to a downstream end () of the swirler channel (). The reduction of the passage section of the swirler channels () makes it possible to increase the head loss between the inlet and the outlet of the secondary fuel swirler () and thus notably to accelerate the fuel within the secondary fuel swirler, while allowing lower fuel flow rates.

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Paris, France

Clément Yves Emile Bernard