MONITORING METHOD OF GAS TURBINE ENGINE CONTROL SYSTEM Russian patent published in 2012 - IPC F02C9/00 

FIELD: engines and pumps.

SUBSTANCE: in addition, at takeoff of aircraft with EC (electronic control) in operation, as per measured position of throttle lever, engine inlet air temperature and pressure, air pressure after compressor, gas temperature after turbine and speed of engine rotor as per known relationships there determined is the specified fuel consumption to combustion chamber (CC) of engine; as per measured position of fuel batcher and the first pre-set relationship formed by means of calculations and experiments there determined is current fuel consumption to the engine CC; as per measured position of throttle lever and air pressure at the engine inlet and the second specified dependence formed with calculations and experiments; minimum allowable fuel consumption to CC is determined for engine current operating mode and aircraft flight altitude; current fuel consumption is compared to minimum allowable; if current fuel consumption is more than minimum allowable one, the specified fuel consumption is compared to minimum allowable; if the specified fuel consumption becomes less than minimum allowable, the change of current fuel consumption is interlocked during the pre-set period of time determined by means of calculations and experiments; when the above period of time ends and the specified fuel consumption is not more than minimum allowable, engine control is changed over to "ГМР", Control of Engine from "ГМР" signal is shaped and supplied to the screen in the crew cabin.

EFFECT: higher control quality of GTE control system during the flight and higher GTE efficiency and safety of the aircraft.

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