An assembly is provided for an aircraft propulsion system (20). This assembly includes a nacelle inner structure (42) and a deflection limiter (78). The nacelle inner structure (42) includes an internal compartment (68) and a cowl (72). The internal compartment (68) is configured to house a core (49) of a gas turbine engine (22). The cowl (72) is configured to form an outer radial periphery of the internal compartment (68). The cowl (72) is also configured to form an outer radial periphery of a compartment exhaust (70) to the internal compartment (68) at an aft end (76) of the cowl (72). The deflection limiter (78) is attached to the cowl (72). The deflection limiter (78) is configured to limit radial outward movement of the cowl (72).


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    Title :

    NACELLE COWL DEFLECTION LIMITER


    Additional title:

    GONDELVERKLEIDUNGSABLENKUNGSBEGRENZER
    LIMITEUR DE DÉVIATION DE CAPOT DE NACELLE


    Contributors:
    LINDE ERIK (author)

    Publication date :

    2023-06-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    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 / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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