Gas turbine engine airfoil comprising a conduction pedestal

摘要

An airfoil (32) for a gas turbine engine includes an airfoil which defines a leading edge cavity (56) and a forward cavity (34A) between a pressure side wall (40P) and a suction side wall (40S). The leading edge cavity (56) is at least partially defined by a leading edge wall (40L) which extends between the pressure side wall (40P) and the suction side wall (40S). A rib (54) between the pressure side wall (40P) and the suction side wall (40S) separates the forward cavity (34A) and the leading edge cavity (56). A pedestal (60) extends between the leading edge wall (40L) and the rib (54).