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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    Title :

    NOZZLE FOR AN AIRCRAFT PROPULSION SYSTEM


    Additional title:

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


    Contributors:

    Publication date :

    2023-04-05


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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