Patent ID: 6290463
Filing Date: 2001-09-18
Classification: F01D,F05D,Y02T

Abstract:
A coolable gas turbine engine airfoil, said airfoil comprising:an outer airfoil wall with pressure and suction sides extending chordwise between leading and trailing edges of said airfoil,a cooling plenum formed between a span rib and said outer wall and extending along at least one of said leading and trailing edges,leading edge shower head cooling holes extending through said leading edge to said plenum,a cooling air channel within said airfoil bounded in part by said span rib,a slotted cooling air impingement means in said span rib for impinging cooling air from said channel on an interior surface of said outer airfoil wall along said one of said leading and trailing edges,said slotted cooling air impingement means comprising two or more closely spaced apart longitudinally extending slots extending along almost an entire length of said span rib wherein said slots have slot lengths that are at least about an order of magnitude larger than slot widths of said slots and said slot widths being constant along said slot lengths.