A propulsion unit, of an aircraft, comprises a turbine (5, fig 1), at least one fan (10) with an axis offset relative to an axis of the turbine and a power transmission mechanism between the turbine (5) and the fans (10). The power transmission mechanism comprises a differential system having an axial input shaft 6, connected to a turbine shaft, and a planet carrier 12 driven by the input shaft 6. Bevel planet gears 13 are mounted on the carrier 12 and drive first toothed annular gears 141, 151 which are part of two wheels 14, 15 that also comprise second toothed annular gears 142, 152. One of the second toothed annular gears 142 drives a bevel idler gear 181 and another of the second toothed annular gears 152 drives a bevel idler gear 191. The bevel idler gears 181, 191 drive radial shafts 18, 19 that are perpendicular to the axial input shaft 6. Radial shafts 18, 19 drive the fans (10) and each may have an axis that is offset.


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    Titel :

    Turbojet engine with offset fans with a diffrential system


    Beteiligte:

    Erscheinungsdatum :

    31.05.2017


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F16H Getriebe , GEARING / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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