OIL SYSTEM OF AIRCRAFT GAS TURBINE ENGINE Russian patent published in 2012 - IPC F02C7/06 

FIELD: engines and pumps.

SUBSTANCE: oil system includes oil cavities of thrust bearing of rotor and case of propulsion units the lower parts of which are equipped with oil intakes connected to oil extraction pumps, and breather the inlet of which is interconnected with the case cavity. Case of propulsion units is located above cavity of thrust bearing, hydraulically connected to it and equipped with backup oil intake located at breather inlet, and independent oil extraction pump at the breather outlet. Pump outlet is interconnected with the oil tank. Pump extracting the oil from oil cavity of thrust bearing of rotor is arranged inside the cavity and kinematically connected to the engine rotor.

EFFECT: invention allows improving reliability of aircraft gas turbine engine due to refilling of oil volume in oil tank at acrobatic flight without using any additional extraction pump.

2 cl, 1 dwg