The turbofan engine can have a core engine, a bypass duct surrounding the core engine, an annular bypass flow path between the bypass duct and the core engine, and a plurality of core links extending across the bypass path and supporting the core engine relative to the bypass duct, and a fluid passage having a heat exchange portion in a given one of the core links, the heat exchange portion being configured for heat exchange with the bypass flow path, an inlet leading into the given core link and to the heat exchange portion, and an outlet extending from the heat exchange portion and out of the given core link.


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    Titel :

    Turbofan engine and core link therefore


    Beteiligte:

    Erscheinungsdatum :

    07.09.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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    OLVER BRYAN WILLIAM | Europäisches Patentamt | 2020

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    TURBOFAN ENGINE AND CORE LINK THEREFORE

    OLVER BRYAN WILLIAM | Europäisches Patentamt | 2020

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    Separated Core Turbofan Engine

    Y. Saito / M. Endoh / Y. Matsuda et al. | NTIS | 1996


    Seperated core turbofan engine

    Saito, Yoshio | TIBKAT | 1996


    Core cowl for a turbofan engine

    CERRA DAVID F / TRETOW PAUL ROBERT / WILLIE ROBERT H et al. | Europäisches Patentamt | 2018

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