FIELD: aircraft industry.
SUBSTANCE: proposed superhigh by-pass ratio turbojet engine is provided with double-row opposite rotation fan whose rotors are connected with low-pressure turbine through reduction gear. Driving central gear of reduction gear is connected with external driven gear installed on first rotor of fan through idler gears and with internal driven gear installed on second rotor of fan. Idler gears are installed on combination bearing unit consisting of two sliding bearings with antifriction bearing placed in between. Inner race of antifriction bearing is installed on axle of idler gears by means of elastic member. Ratio of diameter of pitch circle of internal driven gear to diameter of pitch circle of driving central gear is 2-5.
EFFECT: improved reliability and economy, reduced mass of engine.
5 dwg
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