Safran Aircraft Engines

Jean-Philippe Mallat-Desmortiers

Eric Jacques Delcoigne

Edouard Emmanuel Garreau

Thomas Tsassis

Samuel Laurent Noël Mathieu Juge

Lucas Geoffrey Desbois

Mireya Sanchez Gomez

Peter Shamma Jeanty

Cyril Leo Benoit

Romain Noselli

Jean Cahen

Cyril Léo Benoit

A turbine nozzle for a turbine engine, including two annular walls extending about the same axis, the walls being connected to each other by blades having an aerodynamic profile, the nozzle being divided into sectors and including several nozzle sectors arranged circumferentially end-to-end about a longitudinal axis. The blades include first blades made from a first metal alloy, and second blades made from a second metal alloy different from the first alloy, each nozzle sector including first blades and second blades. The invention also relates to a turbine engine, in particular of an aircraft, including at least one such nozzle. The invention also relates to a method for manufacturing such a nozzle in which each of the sectors is produced, for example, by additive manufacturing.

Bladed turbine stator for a turbine engine

A rotor vane for an aircraft turbine engine includes a blade extending between an inner platform and an outer platform which carries at least one projecting lip. The blade has a lower surface and an upper surface, and the outer platform includes, on the side of the lower and upper surfaces, lateral edges configured to cooperate in a form-fitting manner with complementary lateral edges of adjacent vanes. Each of the lateral edges has an anti-wear coating, and one of the lateral edges forms a hollow tip (P) with a bowl configured to receive the coating and further including a first concave cylindrical surface portion, the geometric dimensions of which are optimized to limit the risk of cracks appearing when the coating is applied.

Vane for an aircraft turbine engine

Growing community of inventors

Moissy-Cramayel, France

Jean-Philippe Mallat-Desmortiers