FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engine lubrication system oil tank installed on supersonic manoeuvre aircraft. Feed line with air intake in lower part of housing is made separately from main bleeding lines, installed above partition and has independent message to collector. Intake thereof is connected with feed line via knee-shaped section of main line and is connected in parallel through hole in partition, made in rear wall of body to free volume of oil tank.
EFFECT: invention enables, when aircraft is under negative overloads, to prevent ejection in atmosphere volumes of oil, which are accumulated in part of oil intakes immersed in oil, which reduces oil consumption and improves environmental characteristics of aircraft engine.
1 cl, 1 dwg
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