FIELD: aircraft industry and other industries.
SUBSTANCE: invention relates to automatic control systems of gas-turbine engines, particularly, to fuel systems, and it can be used in aircraft engines. Proposed fuel system of gas-turbine engine contains pump to deliver fuel into combustion chamber, metering device series-connected to pump, pump to feed fuel to power control sets, engine governor actuator hydraulically coupled with output of pump delivering fuel into combustion chamber and restrictor connected to governor, and constant pressure differential valve also hydraulically coupled with output of pump to feed fuel to power control sets and cock with servodrive connected to said valve. Servodrive is connected to restrictor, and output of cock is hydraulic coupled with output of pump delivering fuel into combustion chamber, and constant differential valve is connected to input and output of cock.
EFFECT: reduced weight and increased reliability of fuel system of gas-turbine engine.
1 dwg
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