Snecma

Snecma Moteurs

Patrice Jean-Marc Rosset

Marc R Marchi

Patrick Emilien Paul Emile Huchin

Serge Louis Antunes

Sébastien Jean Laurent Prestel

Jacques Auguste Amedee Boury

Sébastien Serge Francis Congratel

Hélène Myriam Condat

Franck Boisnault

Thierry Henri Raymond Alaux

Boris Soulalioux

Denis Aydin

Rémi Blanc

Patrick Pierre Gazeau

Jacques Auguste Amédée Boury

A turbine wheel for a turbine engine comprising a disc carrying blades. Each blade comprises an upstream radial wall and a downstream radial wall which extend inwards from the platform of the blade. Inter-blade cavities each accommodate one inter-blade sealing and vibration damping member. According to the invention, each inter-blade sealing and vibration damping member comprises at least a first transverse partition wall axially arranged at a distance from a downstream (or upstream, respectively) portion of the member and axially opposite two upstream (or downstream, respectively) so as to obstruct a flow of incoming air into the cavity between two adjacent upstream radial walls or two adjacent downstream radial walls.

Turbine wheel for a turbine engine

A nozzle sector of an aircraft turbo-machine, including a hooking member () having a projection () radially extending towards the outside of the sector, a recess () being provided through at least one part of a distal end of the projection (), the recess () being configured to accommodate a shoulder member () forming a stop for a surface of an adjacent sector ().

Anti-rotation nozzle sector and method for manufacturing such a sector

A cooled turbine vane for a turbine engine, that includes a blade mounted on a platform carried by a base, the blade including one or more cavities formed therein for cooling air circulation, the cavity extending along the trailing edge and being supplied with cooling air by a supply duct connecting an air intake located in a lower portion of the base and the cavity of the trailing edge by defining a bend within the base. The duct includes, on an axis substantially radial relative to the air intake a bell-shaped niche located under the platform, the niche being open at a top thereof via a dusting hole extending through the platform and being defined at a foot of the base by walls extending substantially radially from the platform to close the platform laterally.

Turbine vane with dusting hole at the base of the blade

A method of producing cooling fluid discharge orifices in the wall of a part manufactured by the technique of lost wax casting in which a pattern of the part is produced in a wax mold, the orifices each having a first portion emerging at the external surface of the wall is disclosed. The method includes making cavities in the wax pattern that correspond to the first portions of said orifices of the part. Thus, it is possible to produce cooling air discharge orifices without sharp edges.

Method of manufacturing a turbomachine component that includes cooling air discharge orifices

Growing community of inventors

La Chapelle Gauthier, France

Patrice Jean-Marc Rosset