| 摘要 |
The need for engine bleed air in a cabin pressurizing/ventilation ECS system for aircraft is avoided in a construction including a pressurizable aircraft cabin (10) having a cabin air inlet (20) and a cabin air outlet (22). The system includes a ram air inlet (34) and an aircraft exhaust air outlet (42) along with a motor operated vapor compression cabin air cooling system (24) having an inlet (28) and an outlet (26). A turbomachine (40) includes a compressor (32) connected between the ram air inlet (34) and the cooling system inlet (28) along with a combustion turbine (38) and a power recovery turbine (41), both mechanically coupled to the compressor and connected between the aircraft exhaust air outlet (42) and the cabin air outlet (22). A motor/generator (36) is coupled to the compressor (32) and the turbines (38, 41) and is operable to drive the compressor (32) when operating as a motor and to be driven by the combustion turbine (38) when operating as a generator. A combustor (46) is connected to the combustion turbine (38) for selectively providing gasses of combustion to the combustion turbine (38) to drive the same and a heat exchanger includes a first fluid flow path (52) interconnecting the compressor (32) and the cabin (10) and a second fluid flow path (54) interconnecting the cabin (10) and the power recovery turbine (41).
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