Airfoil with isolated leading edge cooling

摘要

A gas turbine engine airfoil (14) includes first and second sidewalls (22,24) joined together at opposite leading and trailing edges (26,28), and spaced apart from each other therebetween to define a leading edge channel (34) extending longitudinally from a root to a tip of the airfoil. A plurality of film cooling holes (36) extend through the leading edge and are disposed in flow communication with the leading edge channel. An isolation plenum 38 extends along the first sidewall and adjacent the leading edge channel, and is separated therefrom by a partition (40) having a plurality of inlet holes (42). A plurality of film cooling gill holes (44) extend through the first sidewall, and are disposed in flow communication with the isolation plenum. Cooling air is channeled from the leading edge channel to the isolation plenum for feeding the gill holes with reduced pressure air.