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


    Access

    Download


    Export, share and cite



    Title :

    Nozzle for a thermal anti-icing system


    Contributors:

    Publication date :

    2023-03-28


    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



    NOZZLE FOR A THERMAL ANTI-ICING SYSTEM

    CHILUKURI RADHAKRISHNA / PATIL YUVARAJ / SAYA ASHOK BABU et al. | European Patent Office | 2023

    Free access

    NOZZLE FOR A THERMAL ANTI-ICING SYSTEM

    CHILUKURI RADHAKRISHNA / PATIL YUVARAJ / SAYA ASHOK BABU et al. | European Patent Office | 2021

    Free access

    Anti-Icing Nozzle Particle Rejection

    Ask, T. / Ask, B. / Permanent International Association of Road Congresses | British Library Conference Proceedings | 2003


    Anti-Icing Nozzle Particle Rejection

    Ask, T. / Ask, B. / Permanent International Association of Road Congresses | British Library Conference Proceedings | 2003


    NOZZLE AND VANE SYSTEM FOR NACELLE ANTI-ICING

    CLARK GEORGE WIBERG / SHILADITYA MUKHERJEE | European Patent Office | 2017

    Free access