Patent ID: 7278827
Filing Date: 2007-10-09
Classification: B22C,F01D,F05D

Abstract:
1. A turbine blade of a turbomachine, comprising: an airfoil extending radially from a blade base to a blade tip and axially from a leading edge to a trailing edge; at least a bottom platform connected to the base of the blade by a bottom connection zone; and a cooling circuit consisting of at least one cavity extending radially from the blade tip to the blade base, of at least one air inlet opening at a radial end of the cavity(ies), of a plurality of evacuation slots arranged along the trailing edge of the blade, said blade having a bottom evacuation slot that is disposed near the blade base, said bottom evacuation slot including: an end wall provided with an opening that opens into the cavity(ies); a setback wall; a bottom wall disposed beside the blade base; a bottom edge formed between the setback wall and the bottom wall; and a bottom shoulder formed between the bottom wall and the bottom connection zone; wherein both the bottom edge of the bottom evacuation slot and the bottom shoulder of the bottom evacuation slot have respective right sections of substantially rounded shape, thereby avoiding any protruding angles between the opening of said slot and the bottom connection zone.