Patent ID: 8734108

Claim:
A turbine rotor blade comprising: an airfoil with a leading edge region and a trailing edge region and a pressure side wall and a suction side wall; a platform and a root; a forward impingement cavity and an aft impingement cavity both extending in a radial direction of the airfoil from the platform to underneath a blade tip; a leading edge impingement cavity and a trailing edge impingement cavity; the four impingement cavities each having an arrangement of impingement cooling air holes to provide impingement cooling for an inner wall of the airfoil; the platform having a forward serpentine flow cooling circuit and an aft serpentine flow cooling circuit that provides convection cooling for a hot surface of the platform; the forward impingement cavity and the leading edge impingement cavity and the forward serpentine flow cooling circuit being connected in series and form a first series of cooling air channels; and, the aft impingement cavity and the trailing edge impingement cavity and the aft serpentine flow cooling circuit being connected in series and form a second series of cooling air channels.