Patent ID: 8398370

Claim:
A turbine rotor blade comprising: an airfoil with a leading edge region, a trailing edge region, and a mid-chord region located between the leading edge region and the trailing edge region; a leading edge impingement cavity located in the leading edge region to provide impingement cooling for a backside surface of the leading edge wall of the airfoil; a plurality of pressure side impingement cavities located along the pressure side wall in the trailing edge region and connected by metering holes in series; a long suction side impingement cavity located along the suction side wall in the trailing edge region and connected to the plurality of pressure side impingement cavities through separate metering holes; a cooling supply channel located along the pressure side wall in the mid-chord region of the airfoil and adjacent to the leading edge impingement cavity; a plurality of pressure side impingement cavities located along the pressure side wall in the mid-chord region connected in series by metering holes and connected to the cooling supply channel; a plurality of suction side impingement cavities located along the suction side wall in the mid-chord region and connected to the cooling supply channel or the series of pressure side wall impingement cavities through a separate metering hole; the impingement cavities in the trailing edge region being connected to the last pressure side wall impingement cavity in the mid-chord region; and, the impingement cavities and cooling supply channel in the mid-chord region being connected by film cooling holes to discharge spent impingement cooling air from the cavity as film cooling air.