TURBO-JET ENGINE Russian patent published in 2004 - IPC

FIELD: aircraft engines.

SUBSTANCE: proposed turbo-jet engine includes adjustable air intake, axial-flow compressor and gas turbine which are mounted in engine body. Their masses are comparable and their rotors rotating in opposite direction are secured on shafts connected by means of reversing mechanism; turbo-jet engine is also provided with combustion chamber and reactive nozzle. Shafts of axial-flow compressor and gas turbine are additionally connected through thrust bearing which is formed by flange of turbine shaft located inside holder of compressor shaft end and supported by ring secured on holder compressor shaft end and rigidly linked with driven gear wheel of planetary reversing mechanism closed through rollers by race of anti-friction bearing which rests against compressor and turbine shafts. Drive gear wheel of planetary reversing mechanism is secured on turbine shaft and is thrown into engagement with driven gear wheel through satellite gear wheels mounted independently in supports.

EFFECT: increased service life of engine; compensation for axial loads; minimizing of gyro torques of compressor and turbine; possibility of pilotage of flying vehicle in case of off-center loading.

3 dwg