HIGH-PRESSURE VANE OF HELICOPTER TURBINE COMPRISING A UPSTREAM CONDUIT AND CENTRAL COOLING CAVITY

摘要

The invention relates to a turbine engine high pressure turbine blade, comprising: - a blade (13) extending in a span direction (EV) ending in a top (S) and comprising a lower surface ( 16) and an upper surface (17) joined by a leading edge (18) and a trailing edge (19), - an internal cooling circuit (25) comprising only an upstream duct (26) and a central cavity (27) for cooling the blade by circulation of air; the upstream duct (26) and the central cavity (27) being supplied with air in a distinct manner; the upstream duct (26) being dedicated to cooling the leading edge (18) and the extrados wall (17); - the central cavity (27) being dedicated to the cooling of the intrados wall (16) and the trailing edge (19) and being provided with bridges (51) each connecting the intrados wall (16) to the wall d extrados (17).