BLADE FOR A ROTATING BLADED DISK FOR AN AIRCRFT TURBINE ENGINE COMPRISING A SEALING LIP HAVING AN OPTIMIZED NON-CONSTANT CROSS SECTION

摘要

In order to increase the inertia of a blade sealing lip for an aircraft turbine engine, and thus to improve the lifespan of such a sealing lip, the sealing lip (48) is shaped so as to have a hollow (98) in its outer surface (S2) and a corresponding bulge on its inner surface (S1), the hollow and the bulge being defined from a connection cross section (60) between the sealing lip and a blade body (40), and being formed at a distance from a free axial end (62) of the sealing lip.