AIRCRAFT TURBOJET ENGINE CONTROL METHOD Russian patent published in 2016 - IPC F02C9/26 

FIELD: electricity.

SUBSTANCE: invention relates to methods for regulating aircraft turbojet engines (TJE) with variable geometry of the output device. A method for controlling aircraft turbojet engine with variable geometry of the output device includes maintaining a predetermined pressure drop across the turbine according to the temperature of the inlet air to the engine and on engine operation. In the method previously for this type of engine is additionally formed with at least two control programs pressure differential across the turbine, at each management program created at the inlet into the engine and engine-out condition corresponding to different flight conditions height and speed, measured values of thrust and fuel consumption, and then build according to the fuel consumption of the thrust on them define management program that provides minimum fuel consumption in a given range of thrust and is administered for a further engine controller, and a signal from the aircraft when flying at maximum length and range in the regulator engine make switching control program differential pressure turbines for the program, which provides minimum fuel consumption.

EFFECT: implementation of the method can significantly increase the range and duration of flight of the aircraft.

1 cl, 2 dwg, 1 tbl