FIELD: engines and pumps.
SUBSTANCE: proposed method comprises measuring parameters of gas pressure downstream of compressor and turbine, determining gas expansion ratio at turbine therefrom, comparing this parameter with preset magnitude and feeding generated control signal to actuator for adjustment of jet nozzle critical section area. Preset critical section area magnitude is made up of the sum of program magnitudes of has expansion ratio at turbine and reduced low-pressure rotor rpm. Program gas expansion ratio at turbine is corrected depending on engine inlet air temperature. Program rotor reduced rpm is obtained from comparison of low-pressure rotor rpm with its program magnitude signal obtained as the sum of program rpm depending upon engine inlet air temperature and engine control lever position.
EFFECT: perfected method.
1 dwg
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