Gas turbine engine fan cooled heat exchanger

A cooling apparatus for a heat exchanger used with an aircraft gas turbine engine having a fan duct including a fan nozzle and fan nozzle throat, said cooling apparatus comprising:

• a cooling air duct means,
• said cooling air duct means having a cooling duct inlet at a relatively high pressure region of the fan nozzle upstream of the fan nozzle throat and a cooling duct outlet at a relatively low pressure region of the fan nozzle upstream of the fan nozzle throat,
• a heat exchanger means disposed in the duct means between said cooling duct inlet and said cooling duct outlet,
• a diffuser disposed in said cooling air duct means downstream of said cooling duct inlet and upstream of said heat exchanger means,
• a cooling duct nozzle disposed in said cooling air duct means downstream of said heat exchanger means, and
• said cooling duct nozzle having an exit generally at said cooling duct outlet,
• a forward facing scoop at said cooling duct inlet for capturing cooling air in the fan duct,
• an aft facing scoop at said cooling duct outlet for directing the cooling air exhaust flow,
• a booster bypass system including a booster bypass valve disposed in a core engine flow path between booster and core engine compressor sections of the engine,
• a booster bypass cooling duct providing a flowpath for booster bypass cooling air from said booster bypass valve to said cooling air duct means.