| 摘要 |
PURPOSE: To provide an aircraft gas turbine engine in which the passenger/ aircraft air bleed requirement is met, the engine compressor air bleed is lessened, and efficient means is provided, a quick and reliable restarting/reigniting performance during the flight for the engine is established, the cooling air is provided, and the aircraft effect is decreased in good combusting efficiency form. CONSTITUTION: This compressed air supplying system of a gas turbine engine for aircraft is equipped with an auxiliary compressor 24 and means 40 and 50 to drive mechanically the auxiliary compressor from the rotor of the gas turbine engine. The configuration includes an air turbine 56 and a cycle changing means to operate the auxiliary compressor independently of the operating cycle of the compressor of the gas turbine engine, for example a speed change drive 36 and an air intake from an outer plate of engine nacelle 10.
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