A fan casing for an aircraft bypass turbojet engine includes one single wall configured to form at least one portion of an outer skin of a nacelle. The wall includes at least one reinforcement for stiffening the fan casing. The reinforcement is formed by a portion of the wall forming at least one annular area projecting towards an inside of the nacelle and/or having an overthickness. The reinforcement is further configured for fastening the fan casing to arms crossing a secondary stream flow path of the turbojet engine.


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    Title :

    TURBOJET ENGINE FAN CASING



    Publication date :

    2022-04-07


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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