VANE FOR AN AIRCRAFT TURBINE ENGINE

The invention relates to a rotor vane (10) for an aircraft turbine engine, said vane having an axis (A) of rotation once it has been rigidly connected to a rotor and a stacking axis (X). The vane comprises a blade (16) extending between an internal platform (19) and an external platform (20) bearing...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	LOISEL BRUNO MARC-ETIENNE, DELCOIGNE ERIC JACQUES, PERSON LAETITIA NICOLE, DEFLANDRE STEPHANIE ALINE MARIE, LIMOUSIN FRANCK DENIS DANIEL
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to a rotor vane (10) for an aircraft turbine engine, said vane having an axis (A) of rotation once it has been rigidly connected to a rotor and a stacking axis (X). The vane comprises a blade (16) extending between an internal platform (19) and an external platform (20) bearing at least one projecting lip (31, 32), said blade having a lower surface (16a) and an upper surface(16b). The external platform comprises lower (22) and upper (21) side edges, located on the side of the lower (16a) and upper (16b) surfaces respectively and configured to cooperate in a form-fittingmanner with the complementary side edges (21, 22) of adjacent vanes, each of said side edges having a wear-resistant covering (36). The rotor vane of the invention is characterised in that the wear-resistant covering of the lower side edge extends over one wall (40a) of a substantially rectilinear first ridge (40) of the platform and over one wall (42a) of a second ridge (42) of the platform, saidsecond ridge extending at