Patent ID: 7985049

Claim:
A turbine blade for use in a gas turbine engine, the blade comprising: an airfoil portion having a leading edge and a trailing edge, a pressure side and a suction side; a leading edge cooling supply cavity to supply cooling air to the blade from a source of pressurized cooling air external to the blade; a trailing edge cooling supply cavity to supply cooling air to the blade from the source of pressurized cooling air external to the blade; a leading edge impingement cavity located adjacent to the leading edge of the blade; a leading edge metering and impingement hole connecting the leading edge cooling supply cavity to the leading edge impingement cavity; a showerhead arrangement of film cooling holes connected to the leading edge impingement cavity; a first suction side impingement cavity and a first pressure side impingement cavity both located aft from the leading edge cooling supply cavity; a first metering and impingement hole connecting the first suction side impingement cavity to the leading edge cooling supply cavity; a second metering and impingement hole connecting the first pressure side impingement cavity to the leading edge cooling supply cavity; a second suction side impingement cavity and a second pressure side impingement cavity both located forward from the trailing edge cooling supply cavity; a third metering and impingement hole connecting the second suction side impingement cavity to the trailing edge cooling supply cavity; a fourth metering and impingement hole connecting the second pressure side impingement cavity to the trailing edge cooling supply cavity; a first trailing edge impingement cavity located aft of the trailing edge cooling supply cavity; a fifth metering and impingement hole connecting the trailing edge cooling supply cavity to the first trailing edge impingement cavity; and, a cooling air exit slot opening along the trailing edge of the airfoil and in fluid communication with the first trailing edge impingement cavity.