COUPLING ASSEMBLY BETWEEN COMPRESSOR ROTORS AND TURBINE OF A GAS TURBINE ENGINE Russian patent published in 2016 - IPC F02C7/36 F01D5/02 

FIELD: engines.

SUBSTANCE: invention relates to gas turbine engines for aircraft and ground applications, namely to design of connection assembly between rotors of compressor and turbine. Connection assembly between rotors comprises a turbine shaft, into which compressor rotor trunnion is inserted, a locking tube, and a countershaft. Turbine shaft and compressor rotor trunnion are fixed relative to each other in circumferential direction by spline coupling, and axially by clamping device configured to form clamping tube. Clamping tube contacts compressor side with compressor rotor trunnion at its face and has a threaded sleeve mounted on clamping tube at turbine side and rigidly coupled to turbine shaft. Clamping tube is fixed in circumferential direction by spline coupling relative to locking tube, and at outer surface of locking tube on compressor side a groove shoulder is formed in contact at its end with clamping tube. Intermediate shaft includes turbine shaft and fixed relative thereto in circumferential direction by spline coupling, and is axially fixed with respect to latter by means of adjusting sleeve and thrust ring. Adjusting sleeve is mounted on compressor side of turbine shaft via threading and is in contact with intermediate shaft at its end. Thrust ring member is mounted on turbine shaft from opposite side to intermediate shaft, and it contacts with latter and a radial projection formed on turbine shaft outer surface. Adjusting sleeve is fixed relative to compressor rotor trunnion in circumferential direction by spline coupling, and is in contact with end face of radial projection formed on compressor rotor trunnion.

EFFECT: invention can reduce weight of rotor connection assembly, reduce its size, improve durability, reduce wear and simplify assembly.

1 cl, 1 dwg