GAS-TURBINE ENGINE COMPRESSOR AND TURBINE ROTOR JOINT UNIT Russian patent published in 2006 - IPC F02C7/36 

FIELD: aircraft industry; aircraft engines.

SUBSTANCE: invention relates to design of joint unit of compressor and turbine rotors of gas-turbine engine. Proposed joint unit has intermediate shaft enclosing hollow splined ends of rotors of compressor and turbine and provided with bead, and threaded coupling member installed on splined end of turbine rotor. Radial-thrust bearing is installed on intermediate shaft opposite to compressor rotor end. Splines of intermediate shaft are made on bead, thrust bead is made on outer surface of turbine rotor end, splines of compressor rotor ends are made on its inner surface and splines of turbine rotor end are engaged with splines of bead of intermediate shaft and splines of compressor rotor end. Outer surface of compressor rotor end. Outer surface of compressor rotor end is in direct contact with inner surface of intermediate shaft, and end face surface of thrust bead of turbine rotor, with end face surface of intermediate shaft.

EFFECT: improved reliability of joint.

2 dwg