GAS TURBINE ENGINE GAS GENERATOR Russian patent published in 2013 - IPC F02C7/36 F01D5/02 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine gas generator comprises two-stage rotary compressor, combustion chamber and, at least, one turbine axial stage coupled with compressor along the axis to make single-piece rotor running stator bearings. Compressor and turbine impellers are composed of solid discs with front and rear tubular journals at every disc. Impeller of compressor first stage has its journals running in stator bearings. Note here that splines are made inside rear journal. Compressor second stage impeller front journal runs in stator roller bearings while journal splines are engaged with compressor first stage rear journal splines. Turbine impeller front journal outer surface has cylindrical thrust collar and splines and second cylindrical thrust collar on its inner surface, both being engaged with cylindrical thrust collar on compressor second stage cylindrical thrust collar outside compressor second stage impeller rear journal. Rear journals of compressor first and second stages are splined by disengage couplings with compressor second stage front journal and turbine impeller front journal.

EFFECT: higher reliability, decreased weight and costs.

15 cl, 4 dwg