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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    Title :

    PARTIALLY SHROUDED AIRCRAFT PROPULSION SYSTEM


    Additional title:

    TEILWEISE UMMANTELTES FLUGZEUGANTRIEBSSYSTEM
    SYSTÈME DE PROPULSION D'AÉRONEF PARTIELLEMENT CARÉNÉ


    Contributors:

    Publication date :

    2025-08-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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