GAS-TURBINE ENGINE COMPRESSOR ROTOR Russian patent published in 1998 - IPC

FIELD: manufacture of compressors, sectional drum-and-disk rotors of axial-flow compressors of gas-turbine engines. SUBSTANCE: in the course of operation of engine, splines of disks 2, 3, 4, 5, 6, 7 and 8 ensure centering of these disks on shaft 1 and transmitting the torque to working wheels of rotor. Splines 15 of disks 6, 7 and 8 having limited width of hubs are brought under hubs 16 of adjacent disks. Splines of all disks 2 thru 8 are located in unloaded zone and therefore they do not limit service life of these disks and rotor as a whole. Loaded zone is central portion of hubs 13, 14 and 16 which is free of stress concentrators-splines 12 and 15. Simultaneous tightening by nuts 11 over rims 9 of disks 2 thru 8 and their hubs 13, 14 and 16 is ensured due to availability of initial clearance between hubs of disks 7 and 8 which is taken up due to bending of these disks in course of initial stage of tightening. Further tightening increases considerably force of tightening rims 9 obtained during initial stage and increases force in stack of hubs 13, 14 and 16. EFFECT: enhanced reliability. 3 dwg