Safran Aircraft Engines

Safran

Filippo Pagnoni

Adrien Bernard Vincent Rollinger

Léandre Ostino

Romain Pierre Cariou

Sylvain Paquin

The invention relates to a method for manufacturing a vane () of a turbine engine comprising a pressure-face wall () and a suction-face wall () spaced apart from one another, this vane () comprising a tip (S) with:

High-pressure turbine vane including a cavity under a squealer tip

A blade of a turbomachine turbine, including a platform and a vane, including a cooling area extending along the trailing edge, with three distinct types of orifices, wherein the blade includes, at the root of the blade, a first type of orifices formed in the thickness of the trailing edge fillet, at the top of the blade, a third type of orifice formed in the thickness of at least one of the lower surface and upper surface walls, and in the middle of the blade, a second type of orifice formed in the thickness of at least one of the lower surface and upper surface walls. The lower surface wall, the upper surface wall and the trailing edge fillet define a dihedral with a radially changing radius and spacing.

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Moissy-Cramayel, France

Filippo Pagnoni