FIELD: mechanical engineering; gas-turbine engines of aircraft and ground application. SUBSTANCE: according to invention, in compressor of gas-turbine engine with annular space formed by plate and rim of disk of first impeller and ring radial rib installed on inner surface of disk rim from side of inlet into first impeller passage by radial holes made between slots for blades along middle lines of disk projections, number of holes being 2-10 and D/d ratio lies within 50 and 500, where D is diameter of bushing of first impeller at compressor inlet, and d is diameter of radial hole. EFFECT: improved reliability owing to provision of gradual flowing of oil into passage part of first stage impeller. 3 dwg
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