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

FIELD: mechanical engineering. SUBSTANCE: invention relates to rotors of compressors of gas-turbine engines of ground and aircraft application. Proposed rotor of compressor consists of shaft with disks fitted on shaft by means of splines and interconnected through hubs by means of front and rear nuts. Novelty is that minimum one of disks is provided with ring axial projections made integral with disk hubs. Ring axial projections are provided with splines on outer ends, and ratio of distance between outer ends of ring axial projections of said disk to thickness of wall of ring axial projection is L/H= 30-80. EFFECT: improved reliability of gas-turbine engine owing to provision of axial interference in rotor disk hubs. 3 dwg