Safran Aircraft Engines

Laetitia Nicole Person

Matthieu Jean Luc Vollebregt

Daniel Quach

Patrick Emilien Paul Emile Huchin

Joseph Toussaint Tami Lizuzu

Coralie Cinthia Guerard

Jean-Claude Marcel Auguste Hanny

Vincent Marc Herb

Bruno Marc-Etienne Loisel

Pascal Francis Patrick Gomez

Eric Jacques Delcoigne

Franck Denis Daniel Limousin

Stephanie Aline Marie Deflandre

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

A core used in the manufacture, by lost-wax casting, of a turbomachine blade, includes a main element and at least one first secondary element, each including a functional part and a non-functional part. The non-functional part of the main element and the non-functional part of the at least one first secondary element are assembled and shaped so as to cooperate with each other by sliding in a longitudinal direction extending between the base and the top of a blade and by rotating around the longitudinal direction.

Core for manufacturing a turbomachine blade

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Moissy-Cramayel, France

Laetitia Nicole Person