TWO-SHAFT GAS TURBINE ENGINE Russian patent published in 2010 - IPC F02C7/36 

FIELD: engines and pumps.

SUBSTANCE: two-shaft gas turbine engine includes coaxially located high and low pressure shafts. Shafts of compressor and HP turbine are connected by means of intermediate shaft fixed with a nut on compressor shaft and a thread bushing installed on turbine shaft. Thread bushing is installed on external side of front shank of turbine shaft before a spline coupling. Front shank of thread bushing, rear shank of compressor shaft and a nut fixing the intermediate shaft with end splines have spline attachment to H-shaped (in cross section) annular bushing. The latter is installed in inner plane of intermediate shaft between compressor shaft and thread bushing with possibility of axial shift in non-operating position towards compressor shaft and release of end splines of thread bushing. Annular bushing is fixed in axial position with an elastic locking ring with axial projections located in internal annular groove of annular bushing. Inner surfaces of annular bushing are made flush with inner surface of rear shank of compressor shaft. Locking ring is located between rear shank of compressor shaft and front wall of annular bushing.

EFFECT: increasing strength and operating reliability of two-shaft gas turbine engine.

4 dwg