The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.


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    Titel :

    Turbine engine having horizontally offset axes



    Erscheinungsdatum :

    2020-05-05


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



    TURBINE ENGINE HAVING HORIZONTALLY OFFSET AXES

    EL GHANNAM NORA / ATTALI MATTHIEU ETIENNE / FERRIER ROMAIN JEAN-CLAUDE et al. | Europäisches Patentamt | 2018

    Freier Zugriff

    Offset Thrust Axes and Pitch Stability

    Solies, U.P. | Online Contents | 1994


    Offset thrust axes and pitch stability

    Solies, U. P. | AIAA | 1994


    Free vibrations of horizontally curved beams with unsymmetric axes in Cartesian coordinates

    Lee, Byoung-Koo / Lee, Tae-Eun / Ahn, Dae-Soon | Springer Verlag | 2003


    Finding the Focal Axes of Offset Antennas

    Schmidt, R. F. | NTRS | 1982