Rotational propulsion system for an aircraft, comprising an engine (1) surrounded by an engine casing (6), a row of rotating blades (3) attached to the engine casing (6) at one end, and at least one vane (4) configured for non-rotation around the longitudinal axis of the engine (1) and located in a position along the longitudinal axis of the engine (1) different from the position in which the row of rotating blades (3) are located, such that said vane (4) may orientate a flow before or after the rotating blades (3) so that the resulting final flow is mostly aligned with the thrust direction of the engine (1), wherein said vane (4) is attached at one end to the engine casing (6) and at its other end comprising means for its attachment to the fuselage (2) of the aircraft such that the engine (1) may be at least partially supported by the fuselage (2) through said vane (4).


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    Titel :

    ROTATIONAL PROPULSION SYSTEM OF AN AIRCRAFT


    Weitere Titelangaben:

    ROTATIONSANTRIEBSSYSTEM EINES FLUGZEUGS
    SYSTÈME ROTATIF DE PROPULSION D'AÉRONEF



    Erscheinungsdatum :

    26.08.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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