ROTOR OF COMPRESSOR OF GAS-TURBINE ENGINE Russian patent published in 2004 - IPC

FIELD: gas-turbine engines of aircraft and ground application. SUBSTANCE: on splined shaft of compressor rotor of proposed gas-turbine engine disks are installed on splines axially fixed by nut secured in circumferential direction by ring lock installed between nut and disk. Novelty is that ring outer axial projection of lock is movably fitted on outer surface of nut, and side surfaces of axial inner projections directed to disk can come in contact with side surfaces of shaft splines. Said projections are partially located in recesses made between splined projections of disk hub. Number of projections is multiple of number of shaft splines, and side working surfaces of projections are parallel to side surfaces of adjoining spline projections of shaft. Ratio of inner diameter D of projections to inner diameter d of spline projections of hub of disk adjoining the lock is D/d=0.9- 1/1. EFFECT: improved reliability of compressor rotor. 3 dwg