An electric propulsion system 102 has a nacelle 104 with an aerodynamic annular housing defining an internal annular volume 106 and an inner duct 108. At least one fan stage is located in the inner duct, generating thrust with a number of aerodynamic blades 112 mounted within a fan shroud 114. A powertrain is at east partially located within the internal annular volume, having a number of power sources 136 powering a number of electric motors 124,126 driving the fan, at least one electric motor is located in a central hub 116. The system has a hub-to-tip ratio between 0.1-0.4. The electrical power source may be an energy storage system containing at least one battery of toroidal form to fit in the nacelle; it may also be a fuel cell. A thermal management system 148 may also be located in the interior volume of the nacelle, utilising a heat absorbing medium such as a dielectric liquid carried in a pipe network common to heat generating elements of the powertrain and redistribute heat to a heat exchanger 144 to heat air in an aft part of the inner duct, or de-icing heaters 150 in a leading edge of the nacelle.


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    Titel :

    Electric propulsion systems


    Beteiligte:

    Erscheinungsdatum :

    2023-10-18


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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