Gas turbine engine fan blade containment systems are disclosed. An example fan blade containment system includes a shield to be coupled to an aircraft structure and to at least partially surround a circumference of an aircraft engine. The shield is to be spaced from an outer surface the aircraft engine when the shield is coupled to the aircraft structure. A shield termination fitting is to couple a terminating end of the shield to the aircraft structure.


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    Title :

    Gas turbine engine fan blade containment systems



    Publication date :

    2020-02-04


    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 / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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