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


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    Title :

    NOZZLE FOR AN AIRCRAFT PROPULSION SYSTEM


    Contributors:

    Publication date :

    2020-03-19


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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