A fan nacelle includes a metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements. A gas turbine engine includes a metallic fan containment case. A core engine has a static engine structure housing a compressor section, a combustor section and a turbine section. The core engine is configured to receive core airflow. A fan is arranged within the metallic fan containment case. The fan is coupled to the core engine and is arranged in a bypass flowpath provided between the core engine and the metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements.


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    Title :

    Integrated nacelle inlet and metallic fan containment case


    Contributors:

    Publication date :

    2017-01-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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