Safran Aircraft Engines

Safran

Romaine Pierre Cariou

Adrien Bernard Vincent Rollinger

Vianney Simon

Myriam Pelleterat De Borde

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.

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Moissy-Cramayel, France

Romaine Pierre Cariou