METHOD FOR CONTROLLING A GAS TURBINE ENGINE WITH AN AFTERBURNER Russian patent published in 2022 - IPC F02C9/28 

FIELD: aircraft engineering.

SUBSTANCE: invention relates to the field of aircraft engine building and can be used in electronic-hydromechanical automatic control systems for multi-mode gas turbine engines (GTE) with an afterburner. The technical problem, the solution of which is provided when implementing the claimed control method, is to increase the reliability of the engine. The expected result is achieved in the method for controlling a gas turbine engine with an afterburner, which consists in determining in advance the range of heights and flight speeds, during the operation of the engine at maximum reheat and non-augmented modes, the measured pressure values in two specified sections of the engine the current value of the pressure ratio in these sections is formed, the set value of the pressure ratio in these sections is formed, the speed and altitude of flight, the angles of attack and glide of the aircraft are measured, the dependence of the first correction coefficient on the angle of attack and the dependence of the second correction coefficient on the angle of slip are determined, when flying in a predetermined area, the current values of the first and second correction coefficients are formed depending on the current values of the angle of attack and slip, respectively, the maximum of the values of the two correction coefficients is selected and multiplied by the specified value of the pressure ratio in the specified sections, the current pressure ratio in the specified sections is compared with the adjusted value of the pressure ratio, and for the flight mode outside a predetermined area, with a pre-formed preset value of the pressure ratio and by the magnitude of the error obtained as a result of this comparison, the position of the flaps of the critical section of the jet nozzle of the engine is adjusted.

EFFECT: providing the possibility of changing the set value of the pressure drop in the two selected sections of the engine, depending on the conditions of the flight area of the aircraft.

1 cl, 4 dwg