AVIATION GAS TURBINE ENGINE LUBRICATION SYSTEM Russian patent published in 2023 - IPC F02C7/06 

FIELD: aircraft engineering.

SUBSTANCE: lubrication system of an aircraft gas turbine engine comprises an oil tank, oil cavities of the bearing supports of the fan rotors, compressor and turbine, an oil cavity of the drive unit box and scavenger pumps with oil intakes installed inside the oil cavities of the bearing supports. The lubrication system comprises a second box of drive units, whereas the oil cavity of one box of drive units is located under the oil cavity of the bearing support of the fan rotor and is hydraulically communicated with it through a vertical overflow pipe so that the upper end of the pipe facing inside the oil cavity of the bearing support of the fan rotor is located above the oil intake of the scavenger pump. The oil cavity of the second box of drive units is located under the oil cavity of the bearing support of the compressor rotor and is hydraulically connected to it through a vertical overflow pipe so that the upper end of the pipe facing the inside of the oil cavity of the bearing support of the compressor rotor is located above the oil intake of the scavenger pump. Both boxes of drive units are hydraulically connected to each other through a horizontal overflow pipe connected to the suction line of the scavenger pump, and the oil cavity of the bearing support of the turbine rotor is connected to the suction line of the scavenger pump located outside the oil cavity, and the oil intake of the suction line is located above the oil intake of the scavenger pump located inside the oil cavity.

EFFECT: increased reliability of engine operation by duplicating the supply and pumping of oil in the engine lubrication system.

4 cl, 1 dwg