A system is provided for an aircraft propulsion system (10). This system includes an inlet lip (42), a bulkhead (46) and a piccolo tube (48) for a thermal anti-icing system (38). The inlet lip (42) extends circumferentially about an axial centerline (16). The bulkhead (46) extends circumferentially about the axial centerline (16). The bulkhead (46) is configured with the inlet lip (42) to form a cavity (72) axially between the inlet lip (42) and the bulkhead (46). The piccolo tube (48) extends circumferentially about the axial centerline (16) within the cavity (72). The piccolo tube (48) is configured with an elliptical cross-sectional geometry.


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    Titel :

    THERMAL ANTI-ICING SYSTEM WITH NON-CIRCULAR PICCOLO TUBE


    Weitere Titelangaben:

    THERMISCHES VEREISUNGSSCHUTZSYSTEM MIT NICHT KREISFÖRMIGEM PIKKOLOROHR
    SYSTÈME ANTIGIVRAGE THERMIQUE COMPRENANT UN TUBE PICCOLO NON CIRCULAIRE


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

    Erscheinungsdatum :

    31.05.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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