CONTROL METHOD OF GAS TURBINE ENGINE WITH AFTERBURNER COMBUSTION CHAMBER Russian patent published in 2019 - IPC F02C9/28 F02C9/00 

FIELD: aviation.

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). Method for controlling gas turbine engine with afterburner combustion chamber (ACC) includes control of fuel flow into afterburner by measured air temperature at engine inlet, air pressure behind the compressor, position of the engine control lever, control of the hydraulic cylinders drive of the jet nozzle flaps as per the measured pressure drop of the gas on the engine turbine. At that, preset value of starting fuel consumption into afterburner is formed from measured air pressure after compressor and air temperature at engine inlet, starting up-down of afterburning fuel is supplied to afterburner combustion chamber, afterburner combustion unit assembly is switched on, controlling afterburning of afterburner combustion chamber, additionally measuring turbo compressor rotor speed, until turbo compressor rotor speed is achieved in advance selected value and maintaining constant position of hydraulic cylinders of jet nozzle shutters, at which preset value of critical nozzle cross-section area is provided, and fuel supply is blocked to main headers of afterburner combustion chamber.

EFFECT: higher quality of control of GTE with ACC due to provision of the necessary conditions for launch of ACC at any modes of GTE operation, which reduces time of full engine intake capacity.

1 cl, 1 dwg