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 a gas turbine engine with a afterburner combustion chamber includes controlling fuel consumption into augmenter combustion chamber based on measured air temperature at engine inlet, air pressure behind compressor, position of engine control lever, control of hydraulic cylinders of jet nozzle flaps by measured pressure drop of gas on engine turbine, generation of preset value of starting fuel consumption into afterburner by measured air pressure after compressor and air temperature at engine inlet, supply of starting-up fuel of afterburn fuel into it, switching on of afterburner combustion unit ignition and control of afterburner combustion chamber combustion. At that, before air pressure after the compressor of the preset value is maintained, the constant position of the hydraulic shutters drive of the jet nozzle is maintained, 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: improving control quality of gas turbine engine with ACC due to provision of the required conditions for launching of ACC at any modes of GTE operation, which reduces time of full engine intake capacity, as well as improvement of reliability of engine control under high-altitude conditions.

1 cl, 1 dwg