Patent ID: 6220817
Filing Date: 2001-04-24
Classification: F01D,F05D,Y02T

Abstract:
A gas turbine engine airfoil comprising:an airfoil outer wall having pressure and suction side joined together at chordally spaced apart leading and trailing edges of said airfoil and extending longitudinally from a root to a tip;said side being spaced apart from each other between said leading and trailing edges and joined together by a plurality of internal ribs defining at least two independent serpentine outer and inner cooling circuits arranged in part in different longitudinal tiers;said outer and inner cooling circuits include outer and inner tier serpentine portions respectively wherein said outer serpentine portion is disposed longitudinally above said inner serpentine portion for differentially longitudinally cooling said airfoil;said outer and inner serpentine portions include outer and inner exits and entrances wherein said outer and inner exists are positioned aft of said outer and inner entrances respectively so as to have a chordal flow direction aftwards from said leading edge to said trailing edge within said serpentine portions and said inner entrance is aft of said outer entrance;said outer and inner serpentine portions include outer and inner turning channels respectively; andat least two chordwise extending adjacent chord ribs of said internal ribs disposed between said outer and inner turning channels.