A system is provided for an aircraft propulsion system. This system includes an inlet lip, a bulkhead and a piccolo tube for a thermal anti-icing system. The inlet lip extends circumferentially about an axial centerline. The bulkhead extends circumferentially about the axial centerline. The bulkhead is configured with the inlet lip to form a cavity axially between the inlet lip and the bulkhead. The piccolo tube extends circumferentially about the axial centerline within the cavity. The piccolo tube is configured with an elliptical cross-sectional geometry.


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    Titel :

    THERMAL ANTI-ICING SYSTEM WITH NON-CIRCULAR PICCOLO TUBE


    Beteiligte:
    LONKAR VINOD (Autor:in) / PARA VENKATARAO (Autor:in)

    Erscheinungsdatum :

    06.05.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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