CORE FOR METAL CASTING AN AERONAUTICAL PART

摘要

The present invention relates to a core for the foundry of an aeronautical part such as a turbine blade, the core being intended to be placed in an internal housing defined by a mold, the core comprising a body (13) intended to form the inner shape of the turbine blade; an impact portion (15), disposed on at least a portion of the periphery of the body (13) so as to break a jet of fluid when filling the internal housing with the fluid, the impact portion (15) comprising a apex (17) and at least one deflection wall (19) converging towards the apex (17).