Snecma

Safran Aircraft Engines

Josserand Bassery

Raphael Dupeyre

Ba-Phuc Tang

Sebastien Digard Brou De Cuissart

David Mathieu

Guillaume Klein

Sebastien Congratel

Vincent François Boulay

Sébastien Congratel

Stephanie Deflandre

Vincent Francois Boulay

Raphaël Dupeyre

A casting method for obtaining a part that includes a tapering portion, and a turbine engine blade obtained by casting and including a tapering trailing edge, are provided. The method includes: providing an insert element having a tapering section; making a shell around the insert element; and casting a molten material into the shell including the insert element.

Casting method for obtaining a part including a tapering portion

A moving blade of a low pressure turbine includes a foot and a vane having an upper surface and a lower surface, the foot having a stilt linking the vane to the foot, wherein the stilt is formed such that the transverse section of the stilt has: a first straight portion, a second curved portion and a third straight portion, the curved portion having an outer face matching the profile of the upper surface of the vane and an inner face matching the profile of the lower surface of the vane.

Moving turbine blade

A method for producing a rotor vane () for a turbomachine, including producing a rough casting, the heel of which has a downstream lip () with a transverse increased thickness () such that the lip has an upstream surface () substantially parallel to an axis The method further includes machining said increased thickness so that the downstream lip has an upstream surface () inclined in relation to the axis.

Method for producing a rotor vane for a turbomachine

Growing community of inventors

Courbevoie, France

Josserand Bassery