Environmental control system with energy recovery and bleed air

Aeronautics and astronautics – Aircraft structure – Passenger or crew accommodation

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244 53R, 244134R, 62401, 62402, B64D 1308, F25D 900

Patent

active

059113880

ABSTRACT:
The bleed air requirements for a pressurization and environmental control system for the cabin (10) of an aircraft may be reduced by a system that includes a turbomachine (20) having a rotary compressor (22) driven by a turbine wheel (26). A ram air inlet (16) is connected to the compressor inlet (28) and the aircraft is provided with a cabin air exhaust port (18) which is connected to the outlet (34) of the turbine wheel (26). A heat exchanger (40) has a cabin inlet air flow path (42) and a cabin outlet air flow path (44) in heat exchange with one another. The cabin inlet air flow path (42) is connected to the outlet (30) of the compressor (22) and to the cabin (10) of the aircraft. The cabin outlet air flow path (44) is connected to the cabin (10) as well as to the inlet (32) of the turbine (26). A bleed air inlet port (36), (70) is adapted to be connected to the bleed air tap (14) of a turbine engine (12) and is connected to one of the flow paths (42, 44, 52, 60) between the compressor outlet (30) and the turbine wheel inlet (32).

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