GAS TURBINE ENGINE COMPRESSOR ROTOR Russian patent published in 2010 - IPC F04D29/26 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine compressor rotor comprises impellers, shaft and shell rear ring coupled with said shaft. Note that impeller has, on its edges, an axial circular ring. Free end of the latter accommodates sealing cylindrical and radial ledges to form bayonet joint with mating surface and mating inner radial ledge of adjacent impeller that features preset radial gaps. Cylindrical ledge of said axial circular ring free end stays in contact with outer surface of rim mating surface. Note here that rotor shaft features wall thickness increasing from compressor rotor inlet to outlet with H /h=1.1…2, where: H is shaft wall minimum thickness; h is shaft wall minimum thickness under first impeller.

EFFECT: higher reliability of compressor rotor thanks to ruling out of axial clearances and equal to rotor shaft strength over rotor length.

2 dwg