GAS TURBINE ENGINE TURBINE ROTOR Russian patent published in 2012 - IPC F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: turbine rotor comprises disks of the first and second stages. Disks are jointed together by axial studs in radial circular ribs. Second stage disk L-shape flange is provided with radial circular rib extending from rotor axis. First stage disk radial rib is furnished with recesses directed toward rotor axis between stud holes. Second stage disk radial rib is furnished with recesses directed from rotor axis between stud holes. Second disk recesses are aligned with first stage disk recesses to make cooling air feed channels. The number of recesses equals that of studs. First stage disk flange includes axial annular ledge directed toward second stage disk. Second stage disk radial rib is arranged on inner surface of said ledge. Note here that relationship between diameter of circle whereon top point B of first stage disk recess is located and diameter of circle whereon point L of stud hole surface, the most remote from rotor axis is located makes 1.01…1.3. Note also that relationship between diameter of circle whereon point D, most close to rotor axis of stud hole surface and external point E of second stage disk recess surface makes 1.01…1.4.

EFFECT: higher reliability.

3 dwg