A cooling system for an engine of an aircraft of a having hybrid-electric propulsion system including a nacelle body including a bottom cooling air intake disposed below a propeller hub for supplying air to an oil-air cooler, wherein the bottom cooling air intake includes a splitter dividing the bottom cooling air intake into a first channel and a second channel.


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    Titel :

    COOLING SYSTEM CONFIGURATIONS FOR AN AIRCRAFT HAVING HYBRID-ELECTRIC PROPULSION SYSTEM


    Beteiligte:
    BECKER FRANK (Autor:in) / LATULIPE ERIC (Autor:in) / WANG XI (Autor:in)

    Erscheinungsdatum :

    2020-09-03


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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