Snecma

Olivier Charles Henri Massy

Renaud James Martet

Patrick Joseph Marie Girard

Philippe Jean-Pierre Pabion

Jean-Claude Marcel Auguste Hanny

Stephanie Dominique Roger

Renaud Martet

Stéphanie Dominique Roger

The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, is disclosed. The blade includes an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element; an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ; and a connection zone between the airfoil and the airfoil end face. The connection zone forms a fattening of the airfoil. The connection zone extends about the leading edge between a point Psituated on the suction face of the airfoil upstream of the suction face neck and a point Psituated on the pressure face of the airfoil upstream of the pressure face neck.

Turbomachine blade that is cast with a local fattening of the section of the airfoil

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Paris, France

Olivier Charles Henri Massy