Patent ID: 7845906

Claim:
A cooling system for an airfoil portion of a turbine engine component including: a first cavity dedicated to cooling a trailing edge portion of said airfoil portion; a second cavity dedicated to cooling an aft portion of a pressure side wall of said airfoil portion; said first and second cavities being supplied with cooling fluid from a common supply cavity; said first cavity having a plurality of first exit slots for allowing cooling fluid to flow over said trailing edge and said second cavity having a plurality of second exit slots for allowing cooling fluid to flow over said pressure side lip portion; said common supply cavity having at least one cooling hole for allowing cooling fluid to flow over the pressure side wall of said airfoil portion; said first exit slots being offset from said second exit slots to improve cooling effectiveness; and said first exit slots being arranged in a fanned configuration to conform to fluid streamlines over the pressure side surface of the airfoil portion and said second exit slots being arranged in a fanned configuration to conform to fluid streamlines over the pressure side surface of the airfoil portion.