AERONAUTIC BYPASS TURBOFAN ENGINE CONTROL METHOD

摘要

FIELD: engines and pumps.;SUBSTANCE: aeronautic bypass turbofan engine control method comprises a measuring of a low pressure rotor frequency, a power control lever position, an air entering temperature at the engine inlet, a low pressure turbine outlet temperature and a compressor delivery air-pressure. The method also comprises a low pressure rotor speed frequency control by the impact on the fuel metering into the combustion chamber, a control of an installation angle size of the low pressure compressor stater and input devices, and also of an exhaust chamber critical section. The speed frequency control is achieved by means of the fuel-flow into a combustion chamber control, a position of the low pressure compressor stater and an exhaust chamber critical section area, till the obtainment of the frequency high or low threshold criteria.;EFFECT: invention allows to achieve a maximum value of a draft under constraints on the controlled parameters values and control actions.;1 dwg