| 摘要 |
An auxiliary gas turbine engine comprises: a load compressor (110); a cabin air supply duct (115) which supplies at least some of the air from the exit of the load compressor to the aircraft cabin; a high pressure compressor (120) which further compresses the remaining air from the exit of the load compressor; a combustor (130); a turbine (140); an electrical generator (150) driven by the turbine; an electric motor (160) driven by the electrical output of the generator, the electric motor in turn driving the load compressor; and at least one air heater/cooler (170A, 170B or 170C) comprising a heat exchanger matrix (172A,172B or 172C) located in the appropriate air duct and a reversible refrigeration plant or heat pump (174A,174B or 174C) which is electrically powered from the generator so that it can either cool or heat the air passing through the matrix. The load compressor and heat exchanger(s) together produce air at the pressure and temperature required for supply to the aircraft cabin.
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