Safran Aircraft Engines

Clement Bernard

Loic Pora

Christophe Cebille

Romain Nicolas Lunel

Sebastien Christophe Chalaud

Sebastien Alain Christophe Bourgois

Sebastien Loval

Frederic Dos Santos

A slide for a fuel circuit valve of an aircraft engine extending along a longitudinal axis, and comprising a narrowed intermediate portion extending between two cylindrical end portions, a first end portion being separated from the narrowed intermediate portion by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate portion including in turn, as an extension of the shoulder, at least one cylindrical portion, the shoulder comprising at least one groove which extends radially from the cylindrical surface of the first end portion, towards the longitudinal axis, and which forms a fuel recirculation area which provides the generation of a jet of fuel on the cylindrical portion of the narrowed intermediate portion, when fuel flows along the first end portion towards the narrowed intermediate portion and the second end portion.

Aircraft engine fuel circuit valve slide

A spool for a fuel circuit valve of an aircraft engine, extending along a longitudinal axis and including a narrowed intermediate section extending between two end cylindrical sections, a first end section being separated from the narrowed intermediate section by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate section also including, extending away from the shoulder, at least one cylindrical portion, and the shoulder is provided with a step extending away from the cylindrical surface of the first end section which, when the fuel flows along the first end section towards the narrowed intermediate section and the second end portion, generates a jet of fuel on the cylindrical portion of the narrowed intermediate section, a recirculation of fuel forming in an area in front of the shoulder.

Spool for fuel circuit valve of an aircraft engine

The invention concerns a fuel system () for a turbomachine comprising: &#x2014;a control circuit (), &#x2014;a main circuit (), &#x2014;a flow rate regulator (), suitable for regulating the flow of fuel in the control circuit () and in the main circuit () depending on the speed of the turbomachine, and &#x2014;a drain tank () being designed to draw fuel from, store fuel in and drain fuel into the main circuit () on the basis of the pressure difference between the main circuit () and the tank () or the high-pressure pump () to which it is connected.

Multipoint fuel injection system for a turbomachine and associated regulation method

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.

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Moissy-Cramayel, France

Clement Bernard