FIELD: engine devices and pumps.
SUBSTANCE: single torque transmission mechanism to a two-shaft, double-flow aircraft turbojet engine having coaxial shafts of high-pressure rotor and low-pressure rotor dynamically interconnected and includes connected to high-pressure rotor to transfer torque to units from high-pressure turbine of the central bevel gear and reduction drives of propulsion motor gearbox and a gearbox of aircraft units. The reduction drives of the gearbox of aircraft units are connected by torque to the central bevel gear via a multi-stage reduction gear and via a flexible shaft with end hinges and bellows. The central bevel gear comprises a main gear pair of conical driving and driven gears which have gear rims. The main gear pair of the gear wheels of the central bevel gear is made with gear ratio i1,rn=(1.12÷1.43) [b/p]. The drive wheel of the main gear pair is mounted on the shaft installed in ball and roller bearings. The driven wheel is provided with a shaft mounted in a roller bearing and in a ball bearing which is mounted in the cover of the central bevel gear casing. Teeth of conical rims of driving and driven wheels have variable height decreasing towards axial apex of conventional cone of teeth apexes. Angle αr.c.g. of slope of conventional reference cone generator of gear rim to the axis of wheel shaft is determined in the range αr.c.g.1=(0.7÷1.1) [rad] for the driving wheel and αr.c.g.2=(0.55÷0.83) [rad] for the driven wheel. Angle of spiral βW, expressed in the same projection as the angle between the tangent to the tooth line to the midpoint of the latter and the radius of the same point drawn from the axis of the wheel shaft is variably determined in the range of values βW=(0.21÷0.32) [rad].
EFFECT: increased efficiency and operation life of the engine.
23 cl, 6 dwg
