FIELD: motors and pumps.
SUBSTANCE: invention relates to the field of aircraft engine building, in particular to the oil system of an aircraft gas turbine engine. Mains of the oil supply to the oil cavities of the compressor rotor bearings and the drive box of the units are communicated with the ascending branch of the siphon seal, and the main oil supply to the oil cavity of the turbine bearing is communicated with the descending branch of the siphon seal. And the jet of air bleeding is communicated with the highway of pumping oil.
EFFECT: invention makes it possible to increase the reliability of the oil system operation due to the provision of fire safety.
1 cl, 1 dwg
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