Patent ID: 8047788

Claim:
A turbine airfoil for use in a gas turbine engine, the turbine airfoil comprising: a cooling air supply channel connected to an outside source of pressurized cooling air; a first serpentine flow cooling circuit located along a leading edge of the turbine airfoil, the first serpentine flow cooling circuit having a supply leg located on the pressure side of the airfoil and a discharge leg located on the suction side of the airfoil; a second serpentine flow cooling circuit located along the leading edge of the turbine airfoil and adjacent to the first serpentine flow cooling circuit, the second serpentine flow cooling circuit having a supply leg located on the suction side of the airfoil and a discharge leg located on the pressure side of the airfoil; the discharge leg of the first serpentine flow cooling circuit is connected to the supply leg of the second serpentine flow cooling circuit such that cooling air from the discharge leg of the first serpentine flow cooling circuit flows into the supply leg of the second serpentine flow cooling circuit; and, a metering hole to connect the cooling air supply channel to the first leg of the first serpentine flow cooling circuit.