Method for cooling a component of a gas turbine engine

摘要

A method of cooling a gas turbine engine component, such as a heat exchanger (54), using cooling gases (air) from the secondary flow path (34) of a fan duct (32) is disclosed. Various details of the method are developed which reduce the complexity and cost of the cooling system (52). In one embodiment, cooling air is flowed between locations (inlet (58), outlet (62)) located in the fan duct having an adverse static pressure gradient and heated air from the heat exchanger is returned to the flow path (34). <IMAGE>