FIELD: engines and pumps.
SUBSTANCE: fuel flow is changed to engine combustion chamber (CC) as per "military mode" signal until rotor speed of gas generator is maximum, formation of specified location of blades of guide vanes of engine compressor is stopped as per specified rotation frequency of engine rotor, formation of the specified position of blades of guide vanes of engine compressor is started as per position of throttle control lever (TCL) according to linear relation; at that, "closed" position of blades of guide vanes corresponds to "idle" position of guide vanes, and "open" position corresponds to "maximum" TCL position, and full flow changes so that rotor speed of gas generator is maximum irrespective of guide vanes position.
EFFECT: improving operation quality of electronic hydromechanical systems and improving dynamic characteristics of gas-turbine engine and flight performance of aircraft.
1 dwg
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