Patent ID: 7033136
Filing Date: 2006-04-25
Classification: F01D,F05D,Y02T

Abstract:
1. A gas turbine blade for a turbomachine, the blade having an aerodynamic surface which extends radially between a blade root and a blade tip, which surface presents a leading edge and a trailing edge interconnected by a pressure side face and by a suction side face, and is closed at the blade tip by a transverse wall, said aerodynamic surface extending radially beyond said transverse wall so as to form a bathtub, the blade further comprising, in its central portion, a centrally-located first cooling circuit comprising: at least one suction side cavity extending radially on the suction side of the blade; at least one pressure side cavity extending radially on the pressure side of the blade; at least one central cavity extending radially in the central portion of the blade between the suction side cavity and the pressure side cavity; a first air admission opening at a radially bottom end of the suction side cavity to feed cooling air to said suction side cavity; a second air admission opening at a radially bottom end of the pressure side cavity to feed cooling air to said pressure side cavity; at least one first passage putting a radially top end of the suction side cavity into communication with a radially top end of the central cavity; at least one second passage putting a radially top end of the pressure side cavity into communication with the radially top end of the central cavity; and outlet orifices opening out both into the central cavity and into the pressure side face of the blade.