Safran Aircraft Engines

Alexandre Corsaut

Pierre Jean-Baptiste Metge

Paul Ghislain Albert Levisse

Catherine Pikovsky

Fabien Stéphane Garnier

Sébastien Christophe Loval

Etienne Gérard Joseph Canelle

Ghislain Hervé Abadie

Rémi-Paul Honoré Godier

Kevin Auber

Marc Serrau

Sébastien Jahin

Driss Karim

A fuel distribution assembly for a turbomachine extends between a first interface plane and a second interface plane substantially parallel to the first interface plane, the distribution assembly including a plurality of distribution ducts, each duct having at least one inlet portion that is open to the first interface plane or to the second interface plane, at least one outlet portion that is open to the first interface plane or to the second interface plane, and a middle portion fluidly connecting each inlet portion of the duct and each outlet portion of the duct. The middle portion of each duct has an internal cross-section of substantially elliptical shape.

Fuel distribution assembly for a turbomachine

The present document relates to an annular assembly for a turbomachine turbine, in particular of an aircraft, said annular assembly extending about a longitudinal axis X and comprising: a distributor fixed to an external casing; a bladed disc mounted so as to rotate inside the external casing; said bladed disc being surrounded by a circumferentially segmented ring carried by the external casing and formed by a crown arranged radially on the outside of the bladed disc and by an annular deflector that is carried by an upstream edge of the crown and extends radially towards the inside from said upstream edge of the crown; characterized in that it comprises sealing members () between two circumferentially adjacent ring segments, these sealing members () comprising first circumferential sealing means () between two circumferentially consecutive deflector segments.

Annular assembly for a turbomachine turbine

The present invention relates to a bypass air/fluid heat exchanger () for a turbofan engine. According to the invention, this exchanger () comprises: &#x2014;an annular outer shroud () with two walls, an inner wall () and an outer wall (), &#x2014;an annular inner shroud () concentric with the outer shroud (), &#x2014;a series of OGV guide vanes () which connect said outer shroud to said inner shroud, &#x2014;and a circulation circuit () for circulating said fluid, the two shrouds delimiting a bypass air flow path, the fluid circulation circuit () is formed in the body of the outer shroud () and in the body of at least one of the OGV guide vanes (), this circulation circuit () opening at the two respective ends thereof into an inlet opening () and into an outlet opening (), formed through said outer wall () of the outer shroud, and the two shrouds (), the OGV guide vanes () and the circulation circuit () of said fluid are integral.

Bypass air/fluid heat exchanger, method for manufacturing same and turbofan engine provided with such exchanger

The invention relates to a pressurized-air supply unit for an air-jet cooling device cooling an outer casing of a turbomachine turbine. This unit is notable in that it is monobloc, in that it comprises: &#x2014;a body which has an interior wall provided with air-ejection perforations, an exterior wall and outlet ducts which are configured to be coupled to cooling lines of the cooling device, &#x2014;an elbowed air-conveying pipe coupled by its outlet opening to said exterior wall of the body, and in that said unit comprises at least one air-distribution partition, arranged in the outlet opening and connecting the internal face of the portion of the air-conveying pipe that is situated facing the body to the internal face of the opposite portion of the air-conveying pipe.

Pressurized-air supply unit for an air-jet cooling device

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Moissy-Cramayel, France

Alexandre Corsaut