An aircraft has an electric motor to generate thrust and a power electronic module to provide power to the electric motor. The power electronic (PE) module has an output power to fluidly couple the electric motor and the PE module. The aircraft has an alternating current (AC) lead to electrically couple the PE module and the electric motor by way of the output port. The AC lead is submerged within the output port by a liquid coolant. The aircraft also has a cooling system including a heat extractor. The cooling system passes the liquid coolant through the PE module including the output port, then through the electric motor, and then through the heat extractor.


    Access

    Download


    Export, share and cite



    Title :

    AIRCRAFT PROPULSION LIQUID COOLING


    Contributors:

    Publication date :

    2024-05-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    AIRCRAFT PROPULSION LIQUID COOLING

    TSCHIDA COLIN / KUROWSKI PIOTR / FAIRALL EARL et al. | European Patent Office | 2024

    Free access

    AIRCRAFT PROPULSION SYSTEM WITH INTEGRATED FUEL CELL COOLING

    BRELJE BENJAMIN / LYNN ROBERT GULLIVER / LOTTERMAN JEFFREY ALLEN et al. | European Patent Office | 2024

    Free access

    AIRCRAFT PROPULSION SYSTEM WITH PROPELLER AND COOLING FAN

    DIONNE LUC | European Patent Office | 2024

    Free access

    Aircraft propulsion system with propeller and cooling fan

    DIONNE LUC | European Patent Office | 2023

    Free access

    Aircraft propulsion system with propellers and cooling fans

    DIONNE LAURENT | European Patent Office | 2022

    Free access