The invention relates to an engine arrangement for an aircraft, having a first engine, at least one second engine and a reference axis, wherein the first engine has a first basic body with a first longitudinal axis and has a first drive body rotating about the first longitudinal axis, the second engine has a second longitudinal axis and a second drive body rotating about the second longitudinal axis, the first engine and the second engine are arranged in ballistically effective proximity to each other with the respective longitudinal axis substantially parallel to the reference axis, and, in the event of mechanical damage, the first drive body and/or the second drive body output or outputs respective drive body parts hazardously acting ballistically in relation to the respective other engine and/or in relation to the respective other drive body substantially radially with respect to the respective longitudinal axis into a respective ballistic hazard area, wherein the first drive body and the second drive body are arranged offset with respect to each other along the reference axis in such a manner that the respective ballistic hazard area is arranged spaced apart along the reference axis from the respective drive body endangered by the hazardously acting drive body parts of the respective other drive body. Furthermore, the invention relates to an aircraft having such an engine arrangement.


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    Title :

    TRIEBWERKSANORDNUNG FÜR EIN LUFTFAHRZEUG SOWIE LUFTFAHRZEUG


    Additional title:

    ENGINE ARRANGEMENT FOR AN AIRCRAFT, AND AIRCRAFT
    AGENCEMENT DE MOTEUR POUR UN AÉRONEF, ET AÉRONEF


    Contributors:

    Publication date :

    2025-04-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    German


    Classification :

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



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