CONTROL METHOD OF AIRCRAFT JET TURBINE BYPASS ENGINE Russian patent published in 2017 - IPC F02C9/28 

FIELD: engines and pumps.

SUBSTANCE: control method of the aircraft turbojet bypass engine includes measuring the low-pressure rotor speed, the positions of the engine control lever (ECL), the air temperature at the engine inlet and the gas temperatures behind the low-pressure turbine, adjusting the low-pressure rotor speed, dosing of fuel consumption into the combustion chamber and angle adjustment of the input guiding devices installation of the low-pressure compressor. For each air temperature value at the engine inlet, the lower and upper limit values of the low-pressure rotor speed rotor are set at an allowable level of stresses in the working blades, and the adjustment of the low-pressure rotor speed is performed by adjustment of the fuel consumption into the combustion chamber and the position of the low-pressure compressor. Speed control is produced before low-pressure rotor reaches its limit values.

EFFECT: invention achieves a maximum thrust with limitations on the values of the controlled parameters and/or control actions.

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