Patent ID: 7857589
Filing Date: 2010-12-28
Classification: F01D,F05D

Abstract:
1. A turbine airfoil having a leading edge and a trailing edge, a pressure side and a suction side, and a cooling supply cavity within the airfoil, the turbine airfoil comprising: a plurality of serpentine flow cooling modules extending along the leading edge of the airfoil, each module comprising: a first leg of the serpentine flow channel located on one of the pressure side or the suction side of the leading edge; a last leg of the serpentine flow channel located on the other of the pressure side or the suction side of the leading edge; a middle leg of the serpentine flow channel located along the stagnation line of the leading edge; a metering and impingement hole connecting the first leg of each module to the cooling supply cavity; and, each leg in the serpentine flow cooling module including a plurality of film cooling holes to discharge film cooling air onto the respective surface of the leading edge.