An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a nacelle inlet structure (58). The nacelle inlet structure (58) includes an inner inlet opening (64), an outer inlet opening (66) and a rotating structure (72). The rotating structure (72) extends circumferentially about the inner inlet opening (64). The rotating structure (72) is configured to rotate about an axis (76) between a first position and a second position. The rotating structure (72) at least partially closes the outer inlet opening (66) in the first position. The rotating structure (72) at least partially opens the outer inlet opening (66) in the second position.


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    Title :

    AIRCRAFT PROPULSION SYSTEM INLET STRUCTURE WITH VARIABLE AIRFLOW INLET AREA


    Additional title:

    EINLASSSTRUKTUR EINES FLUGZEUGANTRIEBSSYSTEMS MIT EINLASSBEREICH MIT VARIABLER LUFTSTRÖMUNG
    STRUCTURE D'ENTRÉE DE SYSTÈME DE PROPULSION D'AÉRONEF AVEC ZONE D'ADMISSION À FLUX D'AIR VARIABLE


    Contributors:

    Publication date :

    2022-06-15


    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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