An air-cooled transverse flux electric motor 60 includes a stator 61 having coils (Fig.9A, 614) for carrying current and a rotor 62 arranged to interact with the stator to generate a torque for driving rotation of the rotor. The motor is configured to supply a flow of air (Fig.19A, A1-3) to the insulated coils of the stator to remove heat therefrom. The current carrying coils are directly exposed to the flow of air whereby heat is exchanged directly from the coils to the flow of air. Each current carrying coils comprises an effective cooling surface area that is directly exposed to the flow of air. The effective cooling surface area is at least 20% of an overall surface area of the coil. The motor may be used in an electrical propulsion unit (EPU) (Fig.1, 100) in a vertical take-off and landing (VTOL) aircraft (Fig.1, 1), the EPU including a propeller or fan (Fig.1, 110). The effective cooling surface area may be in the range 35-65% of the total surface area of the coil. The stator may include a flux guiding stator iron defining stator slots housing the stator coils, each slot extending circumferentially such that current flows through the coil in a circumferential direction. The stator slots may have a cross sectional area in a plane perpendicular to the circumferential direction and a fill factor between 10% and 50%. Air may flow radially through circumferentially arranged flux guiding stator elements (Fig.18A, 612) of the stator iron.


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    Titel :

    Electrical machines for aircraft power and propulsion systems


    Beteiligte:
    ELLIS F H CHONG (Autor:in) / ANDREAS REEH (Autor:in) / JOHANNES GABRIEL BAUER (Autor:in) / ANTON RUDENKO (Autor:in)

    Erscheinungsdatum :

    2024-07-17


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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