Patent ID: 6126396
Filing Date: 2000-10-03
Classification: F01D,F05D,Y02T

Abstract:
A gas turbine engine airfoil comprising:an airfoil outer wall having width wise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending longitudinally from a root to a tip;at least one internal serpentine cooling circuit having a plurality of longitudinally extending internal ribs extending width wise between said pressure and suction side walls;said one internal serpentine cooling circuit having a plurality of longitudinally extending serpentine channels between said longitudinally extending internal ribs;said serpentine cooling circuit including an entrance and a terminal end wherein said terminal end is positioned aft of said entrance so as to have a chordal flow direction afterwards from said leading edge to said trailing edge within said serpentine circuit; andat least one longitudinally extending side wall impingement chamber in downstream fluid communication with said serpentine cooling circuit, said side wall impingement chamber positioned between one of said side walls and a first inner wall bounding said serpentine cooling circuit and between two of said internal ribs.