A cooling system includes: a heat sink located radially outward of a motor and including a plurality of fins; a motor cooling channel located between a stator of the motor and the plurality of fins and allowing a coolant to flow therethrough; an inverter cooling channel for cooling an inverter device by allowing the coolant to flow therethrough; a first flow channel allowing the coolant to flow from the motor cooling channel to the inverter cooling channel; a second flow channel allowing the coolant to flow from the inverter cooling channel to the motor cooling channel; and a pump provided in one of the first flow channel or the second flow channel.


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    Title :

    Aircraft propulsion system comprising a cooling system


    Contributors:

    Publication date :

    2025-06-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge



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