Patent ID: 6183198
Filing Date: 2001-02-06
Classification: F01D,F05D

Abstract:
A gas turbine engine airfoil comprising:first and second sidewalls joined together at opposite leading and trailing edges, and spaced apart from each other therebetween to define a leading edge channel extending longitudinally between a root and a tip of said airfoil, and disposed behind said leading edge for channeling cooling air therealong;a plurality of film cooling leading edge holes extending through said leading edge, and disposed in flow communication with said leading edge channel for discharging a portion of said cooling air for film cooling said leading edge;an isolation plenum disposed along said first sidewall adjacent said leading edge channel, and separated therefrom by an isolation partition having a plurality of inlet holes for receiving a portion of said cooling air from said leading edge channel and effecting lower air pressure in said isolation plenum than in said leading edge channel; anda plurality of film cooling gill holes extending through said first sidewall, and disposed in flow communication with said isolation plenum for discharging said cooling air therefrom for film cooling said first sidewall.