FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engine production, particularly to oil system of high-maneuverability aircraft gas turbine engine. Oil system comprises at least one oil chamber furnished with two oil intakes arranged in upper and lower opposite parts of aforesaid chamber and connected to two oil pumps. Note that said oil intakes are made integral with the other oil pumps. Inlet of oil pump connected to oil intake arranged in oil chamber upper part is additionally furnished with bellows gate bleeding orifice plug fitted in pressure line of delivery oil pump.
EFFECT: higher reliability.
1 dwg
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