A thrust reverser inner fixed structure 400 (e.g. core cowl, inner barrel or bottle) comprising a barrel portion 401 joined to a discrete bifurcation 402. The joint may comprise mechanical fasteners 420. Maintenance and repair of the inner fixed structure may be facilitated by removing mechanical fasters to undo the joint. The discrete bifurcation and/or the barrel portion may comprise connecting flanges 407, 417 or a groove (24, figure 2) for receiving an edge of the other of the discrete bifurcation or barrel portion. The thrust reverser may comprise two discrete bifurcations (22, 23). The discrete bifurcation may comprise an integral seal retaining feature 413 and an acoustic treatment, e.g. honeycomb material, perforations or acoustic drilling. The discrete bifurcation may be manufactured by additive manufacturing, e.g. three-dimensional printing, or by resin transfer moulding, or consist of a plastic molding. The discrete bifurcation may comprise an integral beam or track 409 for connection to an engine pylon, and integral bumpers 415 or bumper fitting pads for abutting the pylon. Integral track or bumpers may result in fewer mechanical fasteners and/or smaller joining areas, thus more of the bifurcation may be acoustically treated (e.g. closer to the edges), reducing noise in operation.


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    Titel :

    Inner fixed structure


    Beteiligte:
    MICHAEL MITCHELL (Autor:in) / SCOTT LUCAS (Autor:in) / GRAEME HILL (Autor:in) / SIMON FURMSTON (Autor:in)

    Erscheinungsdatum :

    2019-08-14


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    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



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