CONTROL METHOD OF GAS TURBINE ENGINE WITH AFTERBURNER COMBUSTION CHAMBER Russian patent published in 2020 - IPC F02C9/28 F02C9/00 

FIELD: engine building.

SUBSTANCE: invention relates to aircraft engine building and can be used in electronic-hydromechanical systems for automatic control of multi-mode gas turbine engines (GTE) with afterburner combustion chamber (ACC). In the known method for control of gas turbine engine with afterburner combustion chamber (ACC) additionally measuring area of critical section of jet nozzle, generating a signal F equal to the ratio of the degree of reduction of gas pressure on the turbine to the measured area of the critical cross-section of the jet nozzle, generating a signal Frat equal to the ratio of the deviation of the current value of the signal F from its average value to its average value, preliminary by results of tests determining values Fgr and Fgr2, corresponding to values of signal Frat at start-up and extinction of afterburner respectively, when the signal Frat exceeds the preset positive value Fgr, the combustion in the afterburner combustion chamber is determined and the augmenter of the afterburner combustion chamber is switched off, and at start of afterburner combustion chamber with reduction of signal Frat below lower preset negative value Fgr2, extinguishing of afterburner combustion chamber is determined and supply of fuel into augmenter is stopped.

EFFECT: higher reliability of determination of combustion in afterburner combustion chamber, reduced weight of engine due to exclusion of flame sensors in afterburner combustion chamber and electric wires to them, and also increased speed of reaction of system in part of detection of combustion of fuel in afterburner combustion chamber.

3 cl, 1 dwg