An assembly (54) is provided for an aircraft propulsion system (20). This assembly (54) includes a nacelle inlet structure (34) and a nozzle (122). The nacelle inlet structure (34) extends circumferentially about an axial centerline (28). The nacelle inlet structure (34) includes an inlet lip (60), a bulkhead (64) and an internal cavity (90) formed by and axially between the inlet lip (60) and the bulkhead (64). The nozzle (122) is configured to direct gas into the internal cavity (90) axially towards the bulkhead (64).


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    Title :

    THERMAL ANTI-ICING SYSTEM FOR AN AIRCRAFT PROPULSION SYSTEM


    Additional title:

    THERMISCHES ENTEISUNGSSYSTEM FÜR EIN FLUGZEUGANTRIEBSSYSTEM
    SYSTÈME D'ANTIGIVRAGE THERMIQUE POUR SYSTÈME DE PROPULSION D'AÉRONEF


    Contributors:

    Publication date :

    2024-03-06


    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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