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

FIELD: mechanical engineering; gas turbine engines.

SUBSTANCE: proposed turbine of gas-turbine engine with two-stage rotor has disk of first stage of rotor fixed on radial flange of shaft by axial bolts, and disk of second stage of rotor axially fixed on shaft by nut. Radial flange of shaft is arranged between turning disks. Second stage disk is fixed additionally in circumferential direction of front flange on radial flange of shaft by means of axial pins. Ratio of diameter of location of axial bolts of first stage disk to diameter of location of axial pins of second stage disk is 1.2-1.6, and that of diameter of location of axial pins of second stage disk to diameter of turbine shaft before radial flange of shaft is 1.1-1.3.

EFFECT: improved reliability of turbine owing to reduction of loads on disk-to-shaft fasteners and reduction of their temperature.

2 dwg