Aircraft gas turbine engine bleed air energy recovery apparatus

Aeronautics and astronautics – Aircraft structure – Passenger or crew accommodation

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Details

244 53R, 244 58, 98 15, 60 39142, 60 3907, B64D 1300, B64D 3300

Patent

active

051372304

ABSTRACT:
An environmental control system for supplying aircraft or cabin air to an aircraft is provided with a propulsive engine compressor bleed supply means and an ECS bleed air flow control means which includes an energy recovery means for using the unrequired or unused energy to pump boundary layer air from the surface of the aircraft, such as from the engine nacelle, and exhaust this air rearward of the engine to produce thrust, thus returning some of this unused energy to the propulsive engine.

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