An assembly (46) is provided for an aircraft propulsion system (20). This assembly (46) includes an inlet lip (52) for a nacelle inlet structure (30), a bulkhead (56) and a nozzle (58). The bulkhead (56) is configured with the inlet lip (52) to form a cavity (90) between the inlet lip (52) and the bulkhead (56). The nozzle (58) includes a distribution conduit (98) and one or more nozzle ports (100). The distribution conduit (98) projects longitudinally out from the bulkhead (56) and into the cavity (90) along a conduit centerline (102). At least a first portion (106) of the distribution conduit (98) tapers as the distribution conduit (98) extends longitudinally along the conduit centerline (102). The first portion (106) of the distribution conduit (98) has an elongated geometry in a plane perpendicular to the conduit centerline (102). The one or more nozzle ports (100) are arranged longitudinally along the conduit centerline (102) and fluidly coupled with an internal passage (120) of the distribution conduit (98).


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    Titel :

    NOZZLE FOR AN AIRCRAFT PROPULSION SYSTEM


    Weitere Titelangaben:

    DÜSE FÜR EIN FLUGZEUGANTRIEBSSYSTEM
    BUSE POUR SYSTÈME DE PROPULSION D'AVION


    Beteiligte:

    Erscheinungsdatum :

    05.04.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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