FIELD: aircraft engineering.
SUBSTANCE: invention can be used in aircraft turbojet engines, reheated turbojet engines, double-flow turbojet engines and reheated turbojet engines. Proposed system includes oil tank, electromagnetic valves, suction line, oil return line into oil tank, pressure gauge transmitter, scavenge oil pumps, oil-fuel cooler, ejector, oil nozzles, air separator, warning filter, main oil pump, selector valves, line to pump out oil from front drive box, line to deliver oil into electric oil pump, electric scavenge oil pump, pressure relief valve, oil pressure line, oil filter and breather.
EFFECT: increased operation time of gas-turbine engine in flight at damage members of suction and delivery lines.
2 dwg
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