Safran Helicopter Engines

Damien Laberny

Baptiste Hallouin

Jean-Luc Breining

A stator vane of a turbine of a gas turbine engine, including an outer platform and an inner platform between which there extends an outer wall forming an outer skin, wherein it includes an inner wall, forming an inner skin, facing the outer wall so as to define an inter-skin cavity between the outer wall and the inner wall, the inner wall including a plurality of cooling orifices for impingement cooling of the outer wall, the outer wall and inner wall being produced by additive manufacturing.

Turbine stator vane comprising an inner cooling wall produced by additive manufacturing

The present disclosure relates to a blade of a guide vane assembly of a turbomachine fitted with a cooling system, generally including an insert arranged inside an internal cavity of said blade, connected to a cooling air inlet of the blade and designed to cool the surface of the internal cavity of the blade, and a bleed device configured to bleed some of the cooling air inside the insert and designed to send this bled cooling air to a central hub of the turbomachine. The bleed device of the blade may further include a bleed head arranged in the internal cavity of the blade and passing through an opening of the insert, and configured to bleed some of the cooling air inside the insert.

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Moissy-Cramayel, France

Damien Laberny