An assembly (48) is provided for an aircraft propulsion system (20). The assembly (48) includes a nacelle inlet structure (32) with an internal cavity (82). The assembly (48) also includes a nozzle (88) configured to direct fluid into the internal cavity (82) through a plurality of ports (100) that include one or more first ports (100A) and at least one second port (100B). The nozzle (88) includes a trunk conduit (94), a first branch conduit (96) and a second branch conduit (98). The first branch conduit (96) and the second branch conduit (98) are fluidly coupled in parallel to the trunk conduit (94). The first branch conduit (96) includes the first port(s) (100A). The second branch conduit (98) includes the second port (100B).


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    Title :

    NOZZLE FOR A THERMAL ANTI-ICING SYSTEM


    Additional title:

    DÜSE FÜR EIN THERMISCHES ENTEISUNGSSYSTEM
    BUSE POUR UN SYSTÈME ANTIGIVRAGE THERMIQUE


    Contributors:

    Publication date :

    2023-08-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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