Abstract: A process for the manufacture of a part includes the steps of forming a core in a ceramic material, inserting the core into in a wax mould, placing an element on the core thereby forming a spacer between the core and an internal wall of the wax mould, forming a wax model of the part with the core by injecting wax into the mould, forming a shell mould in ceramic material from the wax model, removing the wax, and pouring casting metal into the shell mould, wherein the element is of elongated form and placed on the core in a laying position.

Abstract: A turbine blade of a turbomachine, having 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 cooling cavity, 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, the bottom evacuation slot including an end wall provided with an opening that opens into the cavity, 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, both the bottom edge of the bottom evacuation slot and the bottom shoulder of the bottom evacuation slot having respective right sections of substantially rounded shape, thereby avoiding any protruding angles between the opening of said slot and the bottom connection zone.

Abstract: A turbine blade of a turbomachine, having 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 cooling cavity, 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, the bottom evacuation slot including an end wall provided with an opening that opens into the cavity, 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, both the bottom edge of the bottom evacuation slot and the bottom shoulder of the bottom evacuation slot having respective right sections of substantially rounded shape, thereby avoiding any protruding angles between the opening of said slot and the bottom connection zone.

Abstract: A moving blade for a high pressure turbine of a turbomachine, the blade having at least one cooling circuit comprising at least one cavity extending radially between a tip and a base of the blade, at least one air admission opening at a radial end of the cavity(ies) to feed the cooling circuit(s) with cooing air, and a plurality of slots opening out into the cavity(ies) and opening out into the concave side of the blade between the base and the tip of the blade in a manner that is substantially perpendicular to a longitudinal axis of the blade, a connection zone being provided between a slot closest to the base of the blade and a top surface of a platform defining an inside wall for a stream of combustion gas flowing through the high pressure turbine, and the moving blade further comprising an additional cooling air exhaust slot opening out into said cavity and opening out into said connection zone in line with the trailing edge.