GAS TURBINE ENGINE LOW PRESSURE ROTOR CONNECTION UNIT Russian patent published in 2019 - IPC F02C7/36 

FIELD: engines and pumps.

SUBSTANCE: invention relates to gas turbine engines (GTE) of aircraft application, namely to design of compressor and turbine rotor connection unit. Technical result is achieved by the fact that the known unit for connection of the low-pressure rotor shafts of the gas turbine engine contains the low pressure compressor shaft, the low pressure turbine shaft, the journals of which are inserted into the intermediate shaft, wherein said shafts are fixed relative to each other in circumferential and axial directions, bushing rigidly connected to stator, piston installed in bushing with possibility of axial displacement and fixed relative to it in circumferential direction, wherein between the sleeve and the piston a cavity is formed, which is interconnected with the pressure gas or liquid main line with the bypass valve, a ball bearing, the external ring of which is rigidly connected to the stator, according to the present invention. Unit contains an additional intermediate shaft installed between a ball bearing and an intermediate shaft and fixed relative to the last in circumferential direction by means of a splined connection, and in axial direction by means of a radial ledge and a nut accordingly made and installed by means of a threaded connection on an intermediate shaft. On the nut there is a locking ring element, on ends of which there are axial ledges in circumferential direction, installed in corresponding blind slots in the end of the additional intermediate shaft, as well as in through slots in the nut end face. On the outer surface of the locking ring element between the adjacent end surfaces of the nut and the piston, there is a radial collar, between which and the first end surfaces of the first there are gaps, wherein in the gap between the radial collar of the locking ring element and the end surface of the nut an axial spring is installed. Piston is made with possibility of contact with the nut and radial collar of the ring safety element. Working surfaces of piston, nut and radial collar of locking ring element are conic relative to longitudinal axis of gas turbine engine, large bases of which are located on the side of low pressure compressor, note here that annular locking cover is rigidly fixed on said sleeve, while radial projection is made on outer surface of nut between adjacent end surfaces of annular stop cover and piston. Gaps are formed between said radial ledge and said end surfaces.

EFFECT: higher safety of twin-engine aircraft in case of emergency situation in engine operation associated with low-pressure turbine shaft breakage, or in case of any damages requiring forced mechanical shutdown of the rotor, as well as wider field of application of this device.

1 cl, 4 dwg