Safran Aircraft Engines

Eric Jacques Delcoigne

Bruno Marc-Etienne Loisel

Laetitia Nicole Person

Jean-Philippe Mallat-Desmortiers

Edouard Emmanuel Garreau

Thomas Tsassis

Samuel Laurent Noël Mathieu Juge

Lucas Geoffrey Desbois

Franck Denis Daniel Limousin

Stephanie Aline Marie Deflandre

Peter Shamma Jeanty

Stéphanie Aline Marie Deflandre

Laëtitia Nicole Person

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

A rotor vane for an aircraft turbine engine, the vane having an axis of rotation once it has been rigidly connected to a rotor and a stacking axis. The vane includes a blade extending between an internal platform and an external platform bearing at least one projecting lip. The external platform is configured to cooperate in a form-fitting manner with the complementary side edges of adjacent vanes. The rotor vane has wear-resistant covering of a lower side edge which extends over one wall of a substantially rectilinear first ridge of the platform and over one wall of a second ridge of the platform. The second ridge extends at least partially inside the lip and is inclined relative to the first ridge in a direction substantially parallel to a transverse axis of the lip.

Vane for an aircraft turbomachine

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Moissy-Cramayel, France

Eric Jacques Delcoigne