A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle (501) defining a duct (502), and a fan (503) located within the duct. The fan comprises a hub arranged to rotate around a rotational axis (A-A) and a plurality of blades attached to the hub. Each blade has a span (r) from a root at the hub defining a 0 percent span position (r = 0) to a tip defining a 100 percent span position (r = 1) and a plurality of span positions therebetween (r ∈ [0, 1]), and a leading edge and a trailing edge defining, for each span position, a chord therebetween having a chord length (c). For each one of said plurality of blades, the ratio of chord length at the 0 percent span position (chub) to chord length at the 100 percent span position (ctip) is 1 or greater.


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    Titel :

    BOUNDARY LAYER INGESTION FAN SYSTEM


    Weitere Titelangaben:

    GRENZSCHICHTAUFNAHMEGEBLÄSESYSTEM
    SYSTÈME DE VENTILATEUR D'INGESTION DE COUCHE LIMITE


    Beteiligte:

    Erscheinungsdatum :

    20.04.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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