Gas turbine engine for aviation use - is controlled by digital computer supplied with engine condition and pilot command signals to vary blower blade pitch nozzle cross-section

摘要

An aircraft gas turbine engine has a high pressure turbine driving a high pressure compressor and a low pressure turbine driving a low pressure blower. The output is produced by the thrust of the discharge of the low pressure turbine and the thrust of part of the delivery of the blower which bypasses the rest of the engine. Various transducers measure the temperature and pressure at several points in the engine. The control commands from the pilot are also converted into electrical signals and both sets of signals are fed into a digital computer. The output of the computer energises positioners which vary the pitch of the blower blades, the cross section of the nozzle and the fuel delivery rate.