CONTROL METHOD OF AIRCRAFT TURBOJET ENGINE Russian patent published in 2020 - IPC F02C9/28 

FIELD: aviation; engine building.

SUBSTANCE: invention relates to aircraft engine building and can be used in electronic hydromechanical systems of automatic control of two-shaft turbojet engines with adjustable guides of low- and high-pressure compressor. In the known method of controlling an aircraft turbojet engine, which includes measuring the rotor speed of low pressure, the position of the engine control lever (ECL), air temperature at the engine inlet, gas temperature downstream low pressure turbine and air pressure behind the high pressure compressor, adjustment of the low pressure rotor setting parameters and rotation speed by the fuel metering into the combustion chamber, adjustment of the value of the installation angle of the input guiding devices (GD) of the low pressure compressor and the critical section of the jet nozzle and the gas pressure behind the low pressure turbine, according to the proposal, additionally measuring the high-pressure rotor rpm, value of angle of installation of guiding devices (GD) of high pressure compressor, speed of movement of engine control lever (ECL), setting base for transient process and time of stabilization of changes of parameters in transient process and recording of afterburner switching signal, after which comparative evaluation of engine operating parameters is performed during transient processes time, taking into account of parameters of maximum and minimum deviations (throws and dips) of parameters, maximum allowable values of rotation frequencies of rotors and angle of installation of guiding devices (GD) depending on given rotors for each rotor, for compliance with technically specified values at transient processes and at any parameter mismatch to set values, adjusting parameters of engine operation and forming certification protocol. Estimation of engine operation parameters at transient processes can be performed using preliminary developed thermogas-dynamic mathematical model of engine and mathematical model of control system.

EFFECT: use of the invention improves stability of engine operation, reduces probability of cases exceeding permissible deviations (casts and dips) of parameters of transient processes, reduces time of debugging of variable modes by 15–20 % and increases service life of engine by 1–2 %.

1 cl, 6 dwg