FIELD: engines and pumps.
SUBSTANCE: invention relates to gas turbine engine oil system to be incorporated with instructional aircraft and allows removing constraints on the "oil starvation" conditions of the most heavy duty engine components, i.e. rotor thrust bearings limiting the rotor safe operation in extreme operating conditions. On changing from aerobatic maneuver over to normal flight and vice verse, the engine oil system automatically switches over the operating conditions of two hydraulically coupled oil pressure pumps, i.e. the main and auxiliary ones, connected to two different oil intakes and arranged in opposite parts of oil tank, from the operating to idling conditions and vice verse.
EFFECT: continuous oil feed.
3 cl, 1 dwg
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