Snecma

Stephanie Dominique Roger

Renaud James Martet

Philippe Jean-Pierre Pabion

Patrick Joseph Marie Girard

Eric Roger Schwartz

Alexandre Nicolas Dervaux

Jean-Claude Marcel Auguste Hanny

Olivier Charles Henri Massy

Philippe Hazevis

Renaud Martet

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

A device for cooling a turbine casing in a turbomachine including a turbine is disclosed. The turbine includes several stages, at least one of the stages includes a nozzle assembly formed of an annular row of fixed vanes and an impeller mounted to rotate in a cylindrical shroud formed of ring sectors fixed to the casing, a cooling circuit including ducts carrying cooling air into cavities formed in the vanes of the nozzle assembly, and an air-carrying arrangement which carries air to casing upstream hooks for suspending the ring sectors.

Device for cooling a turbomachine turbine casing

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Mormant, France

Stephanie Dominique Roger