Patent ID: 8535006

Claim:
A turbine airfoil comprising: a pressure side wall and a suction side wall connected to each other along leading and trailing edges; a cavity disposed between the pressure and suction side walls; a continuous serpentine cooling flow path formed by first and second inner walls in the cavity, wherein the continuous serpentine cooling flow path routes a coolant flow in the following sequence as seen in a transverse section of the airfoil: a) a cooling inlet channel that extends span-wise along at least a portion of the pressure side wall; b) a forward pressure side near-wall channel along a forward portion of the pressure side wall; c) a leading edge near-wall channel; d) a forward suction side near-wall channel along a forward portion of the suction side wall; e) a loop channel routed forward then back, between the first and second inner walls; f) an intermediate suction side near-wall channel along an intermediate portion of the suction side wall; and g) an aft channel that is aft of the cooling inlet channel between the pressure and suction side walls.