TURBOJET ENGINE Russian patent published in 2003 - IPC

FIELD: mechanical engineering. SUBSTANCE: proposed turbojet engine contains compressor into operation by speed reduction gear which, in its turn, is set into rotation by turbine shaft. Speed reduction gear contains planetary gear rigidly secured on turbine shaft, crown gear rigidly secured on compressor and planet pinions coming into meshing with planetary gear and with crown gear and installed on planet pinion frame made integral with engine crankcase. Planet pinions have helical teeth engaging with helical teeth of crown gear so that reduction gear applies crown gear axial loads partially compensating axial loads created by compressor. Middle positions of crown gear and planetary gear are axially displaced relative to planet pinions. EFFECT: reduced axial loads acting onto support bearings. 2 cl, 3 dwg