TURBOJET ENGINE WITH OFFSET FANS WITH A DIFFERENTIAL SYSTEM

摘要

The invention relates to a propulsion unit of an aircraft comprising a turbine (15), at least one fan (10) with an axis offset relative to the axis of the turbine and a power transmission mechanism between the turbine and the fan, characterized in that the power transmission mechanism comprises a speed reducing gear (20) with an input and a movement output, the input being in the extension of the axis (16) of the turbine and the output connected to the fan.

主权项

1. A propulsion unit of an aircraft comprising a turbine secured to a turbine shaft, at least two fans with offset axes relative to the axis of the turbine and a power transmission mechanism between the turbine and the fans, wherein the power transmission mechanism comprises a differential system comprising a casing, an axial input shaft connected to the turbine shaft, a planet carrier driven by the input shaft, planet gears mounted on the planet carrier, at least one idler gear supported by the casing and radial shafts each perpendicular to the axial input shaft, the radial shafts each driving one of said fans and being secured to idler gears, the planet carrier and the input shaft being coaxial, the planet carrier forming a hub on which the rotation axes of the planet gears are radially arranged.