FIELD: aeronautical engineering. SUBSTANCE: proposed axial-flow compressor is designed to provide air pressure rise in combustion chamber of aircraft gas- turbine engine. Compressor contains rotor with blades and shaft provided with axial channel communicating with atmosphere and forming, together with stator, ring oil space of bearing support. Two diametrically opposite holes with faces on shaft periphery are made in shaft. Tube with side cutout in central part for communicating oil space with shaft channel is stationarily secured in holes. EFFECT: reduced overall dimensions and weight of compressor, improved reliability in operation. 3 cl, 1 dwg
