An assembly for an aircraft (20) includes a first propulsor rotor (60), a powerplant (64) and a propulsion system housing (66). The powerplant (64) is configured to drive rotation of the first propulsor rotor (60) about an axis (54). The propulsion system housing (66) includes an inner structure (110) and an outer structure (116) with a bypass flowpath (136) radially between the inner structure (110) and the outer structure (116). The bypass flowpath (136) is downstream of the first propulsor rotor (60) and extends axially along the inner structure (110) and the outer structure (116) within the propulsion system housing (66). The inner structure (110) extends axially along and circumferentially around the powerplant (64). The outer structure (116) extends axially along and partially circumferentially about the first propulsor rotor (60) to cover an outer periphery of a first circumferential sector (130) of the first propulsor rotor (60). A remaining second circumferential sector (132) of the first propulsor rotor (60) is open to an environment (134) outside of the propulsion system housing (66).


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    Titel :

    PARTIALLY SHROUDED AIRCRAFT PROPULSION SYSTEM


    Weitere Titelangaben:

    TEILWEISE UMMANTELTES FLUGZEUGANTRIEBSSYSTEM
    SYSTÈME DE PROPULSION D'AÉRONEF PARTIELLEMENT CARÉNÉ


    Beteiligte:

    Erscheinungsdatum :

    13.08.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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