METHOD OF CONTROL OVER GAS TURBINE ENGINE Russian patent published in 2015 - IPC F02C9/26 

FIELD: aircraft engineering.

SUBSTANCE: engine inlet air temperature is measured. Signal of said temperature and the first preset program magnitude of controlled parameter are used to generate first program control signal. The latter is compared with actual magnitude of controlled parameter signal. Difference between said magnitudes is used to adjust fuel feed into engine. Additionally, second program magnitude of controlled parameter is set as well as limiting flight altitude and speed. Signal of said temperature and the second preset program magnitude of controlled parameter are used to generate second program control signal. Flight altitude and speed are measured. Measured magnitudes are compared with preset values. Unless flight altitude and speed exceed preset limiting values, first program control signal is compared with actual signal of controlled parameter. In case limiting values of altitude and speed are exceeded, second program control signal is compared with actual signal of controlled parameter.

EFFECT: higher efficiency of control with due allowance for flight conditions.

2 cl, 1 dwg