Auxiliary gas turbine engines

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 110 to the aircraft cabin; a high pressure (HP) compressor 120 which further compresses the remaining air from the exit of the load compressor 110; a combustor 130; a turbine 140; an electrical generator 150 driven by the turbine 140; an electric motor 160 driven by the electrical output of the generator 150, the electric motor 160 in turn driving the load compressor 110; 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 150 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 required pressure and temperature for supply to the aircraft cabin. $$ $$