Patent attributes
A turbine blade for use in a gas turbine engine, the blade being formed from two pieces bonded together along the blade chamber line to from a pressure side piece and a suction side piece. The pressure side piece includes a first serpentine flow cooling circuit with a first leg located on the suction side leading edge region and the second leg on the pressure side leading edge region with the last leg adjacent to the trailing edge region and connected to exit slots to discharge cooling air out the pressure side of the trailing edge. The suction side piece includes a second serpentine flow cooling circuit with a first leg adjacent to the trailing edge region and connected to suction side exit slots to discharge cooling air. The suction side serpentine circuit ends in a last leg adjacent to the first leg of the pressure side serpentine circuit with a row of film cooling holes to discharge cooling air from the last leg to the suction side airfoil surface for film cooling. The two serpentine flow circuits are separated from each other so that the cooling design can be flexible.
