Safran Aircraft Engines

Safran

Myriam Pelleterat De Borde

Adrien Bernard Vincent Rollinger

Romain Pierre Cariou

Vianney Simon

Thierry Laurent Capolungo

Benjamin Cyrille Jacques Oudin

Florian Carry

Romaine Pierre Cariou

The invention relates to a turbine engine vane including a blade extending along a radial axis and a first cooling circuit arranged inside the blade, the first cooling circuit including a first cavity and a second cavity disposed downstream of the first cavity in a direction of circulation of a coolant in the blade, the first and second cavities radially extending inside the blade and being at least partly separated by a first radial partition having a radially internal free end, which at least partly demarcates a first coolant passage connecting the first and second cavities. According to the invention, the radially internal free end is enlarged by having a general transverse section substantially in the form of a keyhole.

Turbine engine vane equipped with a cooling circuit and lost-wax method for manufacturing such a vane

The invention relates to a turbine rotor, of a low-pressure turbine of a turbine engine for example, including a first disk, an annular seal ring including a radial flange on which is formed a scalloping defined by a plurality of scallops offering a locally increased surface, circularly distributed, said radial flange being attached to the rotor between the first disk and the second disk and a flow circuit including at least one lunule, suitable to place into fluid communication a radially inner cavity and a radially outer cavity, the lunule being formed on the radial flange of the seal ring said lunule being provided on at least one scallop.

Turbine engine turbine rotor with ventilation by counterbore

Growing community of inventors

Moissy-Cramayel, France

Myriam Pelleterat De Borde