FIELD: transport.
SUBSTANCE: invention relates to aircraft, more particular to turbo-jet engine front cone oil anti-icing system. Anti-icing system contains feeding tube connected to engine front cone which tube provides connection of low-pressure compressor shaft with engine front cone and has radius (r), shell, duplicating wall of engine front cone and providing passage for oil circulation. The system also contains multiple radial oil return tubes located between most eccentric relative to Z-Z axis portion of shell and bearing which tubes are intended to provide oil return towards the bearing. Means of oil return to bearing are located at some distance (R) from Z-Z axis which distance exceeds radius (r) of feeding tube.
EFFECT: improved oil pressure level providing in anti-icing system.
9 cl, 3 dwg
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