Patent ID: 6210111
Filing Date: 2001-04-03
Classification: F01D,F05D,Y02T

Abstract:
A blade for use in a gas turbine engine, said blade comprising:a blade root;an airfoil having a first end, a second end opposite said first end and in spaced relation thereto, a leading edge, and a trailing edge in spaced relation to said leading edge, said leading and trailing edges extending from said first end to said second end;a blade platform having a first surface, a second surface, a first side and a second side opposite and in spaced relation to said first side, a platform cooling supply channel, a plurality of cooling holes in the second surface, and a plurality of cooling passages, said second surface opposite said first surface and in spaced relation thereto, said sides extending from said first surface to said second surface, said blade root connected to said first surface, said first end of said airfoil connected to said second surface, said platform cooling supply channel extending from said first side to said second side through said blade platform, and each of said cooling holes communicates with said platform cooling supply channel through one of said cooling passages;wherein said platform cooling supply channel is substantially parallel to said second surface.