GB640799A - Auxiliary gas turbine set for aircraft with cabin supercharging - Google Patents

Abstract

640,799. Gas turbine plant for aircraft. BRITISH THOMSON-HOUSTON CO., Ltd., and FORSLING, B. E. G. Aug. 27, 1948, No. 22681. [Class 110(iii)] [Also in Group XXXIII] An auxiliary gas turbine plant for aircraft comprises a turbine 4 driving a compressor 3 and a turbine 7 driving a generator 8 and other auxiliaries. The compressor 3 supplies air for the combustion chambers 6, 24 of both turbines and for the aircraft cabin. Air for the cabin passes through a cooler 29. Valves 22, 23 regulate the flow of air to turbine 7 and the cabin. Fuel for the turbine 4 is regulated in response to the speed of turbine 7 and the pressure in the aircraft cabin. Fuel for the turbine 7 is regulated in response to the inlet or exhaust temperature of that turbine. The valves 22, 23 are automatically controlled so that a rise in air pressure causes the valve 22 to open and when that valve is fully open causes the valve 23 to shut. The turbine 4 may have oppositelyrotating rotors mounted on co-axial shafts and driving separate stages of the compressor. The air from the cabin may be evacuated to the combustion chamber 24; valves being provided to control the flow of air from the cabin to atmosphere and to the chamber 24. The air from the cabin may be led to a separate combustion chamber. In that case the latter chamber and the chamber 24 deliver working fluid to separate nozzle segments of the turbine 7 which exhaust to separate exhaust pipes. The exhausts of both turbines 4, 7 may be used in propulsion nozzles. In the plant, with a turbine 4 having oppositely-rotating rotors, the shafts are supported in a downstream bearing and the exhaust is divided into two separate pipes so as not to enclose the bearing.