Patent ID: 8511995
Filing Date: 2013-08-20
Classification: F01D,F05D

Abstract:
1. An industrial engine turbine rotor blade comprising: an airfoil extending from a platform; the platform having a pressure side surface and a suction side surface; a plurality of V-shaped cooling channels formed within the platform on the pressure side of the platform; each V-shaped cooling channel includes an inlet hole located on a forward side of the platform and opening on a bottom side of the platform; a straight common cooling channel located on the suction side of the platform and extending along a side edge from a forward side of the platform to an aft side of the platform; a plurality of straight cooling channels on a forward side of the suction side of the platform each connected to an inlet hole opening on the bottom side of the platform and connected to the straight common cooling channel; and, a plurality of straight cooling channels on an aft side of the suction side of the platform each connected to the straight common cooling channel.