METHOD FOR DETERMINATION OF GAS TURBINE ENGINE COMBUSTION CHAMBER EXTINCTION Russian patent published in 2019 - IPC F02C9/46 

FIELD: machine building.

SUBSTANCE: invention relates to control of gas turbine engines used as power units in gas and power industries. Proposed method consists in measurement of main parameters characterizing engine operation and comparing with settings. When the ignition unit is switched on, the value of high-pressure rotor rpm Nvdhp and value of temperature after high pressure turbine Tvdhp, after ignition of ignition of combustion chamber and ignition unit shutdown, high-pressure rotor rpm and temperature behind high-pressure turbine are controlled. High-pressure rotor Nvd rotation frequency is compared with high-pressure rotor Nvdhp rotation frequency value before ignition unit addition, first preset magnitude ΔNvd. Temperature downstream of high pressure turbine Tvd is compared with Tvdhp temperature before ignition unit switching on plus second pre-set value ΔTvd. At reduction of high-pressure rotor Nvd rotation frequency lower than high-pressure rotor Nvdhp rotation frequency before ignition unit switching on plus first preset magnitude ΔNvd and temperature drop downstream of high pressure turbine Tvd below temperature value after high pressure turbine Tvdhp till ignition unit switching on plus second pre-set value ΔTvd, sign of combustion chamber extinction is formed. At the same time fuel shutoff is performed.

EFFECT: disclosed method makes it possible to improve reliability of gas turbine engine operation due to reduction of probability of passing of combustion chamber extinction, including with starter operating.

1 cl, 2 dwg