Patent ID: 6705836
Filing Date: 2004-03-16
Classification: F01D,F05D,Y02T

Abstract:
A gas turbine blade for an airplane engine, the blade having at least a first cooling circuit comprising at least a concave side cavity extending radially beside the concave face of the blade, at least a second cooling circuit independent of the first cooling circuit comprising at least one convex side cavity extending radially beside the convex face of the blade, and at least one third cooling circuit independent of the first and second cooling circuits and comprising at least one central cavity situated in the central portion of the blade between the concave side cavity and the convex side cavity, at least one leading edge cavity situated in the vicinity of the leading edge of the blade, communication orifices opening out into the central cavity and into the leading edge cavity, and outlet orifices opening out into the leading edge cavity and through the leading edge of the blade.