A component 100 has a first abutment 110 spaced apart from a second abutment 120 with a surface (fig.6,122) facing the first abutment and an opposing surface (fig.6,124). Between abutments lies a mount 130, and between each abutment and the mount a respective spring 140,150. A conduit (fig.6,160) is connected to the second abutment, with a through-hole (fig.6,170) extending through the first abutment, mount, and springs. When used in a mounting arrangement 300 of a gas turbine engine a fastener shaft 332 passes through the through-hole, with a head 330 contacting the first abutment, a first part 310 couples to the mount and a second part 320, coupled to the fastener 330, contacts the second abutment, so the parts are isolated from on another. The mount may have a number of through-holes 132. The conduit is preferably cylindrical, extending from the first abutment; the abutments and/or mount may be disc-shaped. Preferably, each spring connects a respective abutment to the mount, and at least partially surrounds the conduit; the mount preferably surrounds the conduit. A unit (fig.7,340) may be mounted on the first part. The component may be integrally formed as one element by an additive manufacturing process.


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    Titel :

    Component for mounting arrangement, mounting arrangement and gas turbine engine comprising mounting arrangement


    Beteiligte:
    DANIEL COUSINS (Autor:in) / ALOK GUPTA (Autor:in) / SAMUEL HOWE (Autor:in)

    Erscheinungsdatum :

    2021-07-21


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    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



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