Patent ID: 7303375
Filing Date: 2007-12-04
Classification: B22C,F01D,F05D,Y10T

Abstract:
1. A process for fabricating a cooling system in a leading edge portion of an airfoil portion of a turbine engine component, said process comprising the steps of: providing a die in the shape of an airfoil portion to be formed; inserting at least one ceramic core into said die to form at least one central core element; inserting a refractory metal sheet having a plurality of curved finger portions into said die; introducing molten metal into said die to form said airfoil portion; and removing said at least one ceramic core and said refractory metal sheet to form a plurality of staggered holes in said leading edge portion, a plurality of curved passageways associated with said holes, and a central core element communicating with said plurality of curved passageways.