Turbine vane including a cooling-air intake portion including a helical element for swirling the cooling air
AssigneeSafran Aircraft Engines
InventorsErwan Daniel BOTREL, Sébastien Serge Francis CONGRATEL, Simon PARINET
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Abstract
A turbine vane of a turbine engine such as a turboprop or a turbojet, the vane comprising a root supporting a blade, the vane including at least one air-circulation duct for cooling the air during operation, the duct including, at the vane root, an inlet portion for collecting the cooling air, the inlet portion extending away from a lower surface of the vane root opposite the blade. At least one inlet portion is provided with a helical element for rotating the cooling air in order to improve the cooling efficiency thereof.
Claims11
1-10. (canceled)
Turbine vane (11) for a turbine engine such as a turboprop or a turbojet engine, said vane (11) comprising a root (12) supporting a blade (13), said vane (11) including at least one air-circulation duct for cooling it during operation, said duct including, at the vane root (12), an intake portion (26a-26e) for collecting the cooling air, said intake portion (26a-26e) extending away from a lower surface (21) of the vane root (12) opposite to the blade (13), characterised in that at least one intake portion (26a-26e) is provided with a helical element (33), having a base (34) located at the lower surface (21) of the vane root (12), for swirling the cooling air in order to improve the cooling efficiency thereof.
Dependencies are inferred from the claim text.