The example embodiments are directed to a heat dissipation system for an electric aircraft engine 110. In an example, the aircraft engine 110 includes an electric system 120 configured to power an engine fan 130 to provide thrust to an aircraft 100, the electric system 120 including cooling channels 308 to receive a coolant 307 to cool one or more components of the electric system 120, a power source to power the electric system, and one or more guide vanes 305/306 connected to the cooling channels of the electric system and configured to receive the coolant heated by and output from the cooling channels, wherein the one or more guide vanes 305/306 are further to cool the heated coolant and transfer the cooled coolant back to the cooling channels of the electric system. By dissipating heat from electric system via the guide vanes, the cooling system can provide sufficient cooling without adding additional drag to the aircraft.


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    Title :

    HEAT DISSIPATION SYSTEM FOR ELECTRIC AIRCRAFT ENGINE


    Additional title:

    WÄRMEABLEITUNGSSYSTEM FÜR EINEN ELEKTRISCHEN FLUGZEUGMOTOR
    SYSTÈME DE DISSIPATION DE CHALEUR POUR MOTEUR D'AVION


    Contributors:

    Publication date :

    2020-11-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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