A gas turbine engine includes a fan duct including a fan duct inner structure that surrounds a core engine, a fan case that surrounds a fan, a core engine frame, and at least one mechanism configured to secure a portion of the fan duct inner structure to a portion of the core engine frame. The at least one mechanism includes a castellated arcuate portion mounted to one of the fan duct inner structure and the core engine frame and an inwardly projecting retaining feature mounted to the other of the fan duct inner structure and the core engine frame. The castellated arcuate portion is rotatable about an engine central longitudinal axis to position a feature of the castellated arcuate portion proximate to a portion of the inwardly projecting retaining feature to latch the fan duct inner structure.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Castellated latch mechanism for a gas turbine engine


    Beteiligte:

    Erscheinungsdatum :

    28.08.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / 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



    Gas turbine engine hydraulically operated nacelle latch

    SAWYERS-ABBOTT NIGEL DAVID | Europäisches Patentamt | 2019

    Freier Zugriff

    NUT, CASTELLATED, HEXAGON-A-286

    SAE Technical Papers | 2000



    LATCH MECHANISM

    AVRAHAM ZIV | Europäisches Patentamt | 2021

    Freier Zugriff

    LATCH MECHANISM

    NEWBOLD TYLER | Europäisches Patentamt | 2021

    Freier Zugriff