Patent ID: 8833053

Claim:
A cooling system for an aero gas turbine engine, the system comprising: a duct which diverts a portion of a main bypass air stream of the engine to form a diverted bypass air stream, the duct having an inlet and an outlet, the diverted bypass air stream being fluidly separate from the main bypass air stream downstream of the inlet with respect to a flow of the diverted bypass air stream; a heat exchanger located in the duct downstream of the inlet and upstream of the outlet, the heat exchanger receiving cooling air for cooling components of the engine, the cooling air being cooled in the heat exchanger by the diverted bypass air stream; a turbine section of the engine disposed downstream of the outlet of the duct and being fluidly separate from the main bypass air stream; a tail cone located at the exit of the engine; and a nozzle located in the tail cone; wherein, after cooling the cooling air, the spent diverted air stream exits the outlet of the duct, passes through the turbine section to the tail cone, and is ejected through the nozzle.