Patent ID: 8491263
Filing Date: 2013-07-23
Classification: F01D,F05D

Abstract:
1. A turbine rotor blade comprising: a platform; an airfoil extending from the platform; the airfoil forming a hollow cavity open at a tip end of the airfoil; a cooling air supply cavity formed within a root of the blade; a multiple pass serpentine flow cooling circuit formed within a wall of the airfoil and the platform; the multiple pass serpentine flow cooling circuit having a first leg connected to the cooling air supply cavity and forming a radial flow cooling channel in a wall of the airfoil, a last leg forming a radial flow cooling channel in the wall of the airfoil, and a middle leg formed within the platform and connecting the first leg to the last leg; and, a cooling air exit slot formed on a tip of the blade and connected to the last leg of the serpentine flow cooling circuit.