GAS TURBINE ENGINE ROTOR Russian patent published in 2009 - IPC F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: gas turbine rotor comprises disks of the fist and second stages, one of them being splined onto turbine rotor shaft, and front and rear intermediate disks fitted in interdisk chamber. First stage disk has L-like flange coupled with that of the second stage disk with the help of studs and nuts. First stage disk flange has flexible element, tapered inner surface and circular rib to lock axially rear intermediate disk hub along outer surface. Second stage disk flange comprises multiple radial openings located opposite against each flange joint and having cross section with antiparallelogram rounded-angle shape, larger base being located on the nut side.

EFFECT: higher reliability, ease of manufacture and assembly.

6 dwg