A gas turbine engine includes an aerodynamic track fairing adjacent to a convergent-divergent nozzle, the aerodynamic track fairing including a localized curvature along an outside edge. The aerodynamic track fairing is configured to offset a circumferential pressure gradient otherwise introduced in part by a transition between the convergent-divergent nozzle with the aerodynamic track fairing.


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    Title :

    Aerodynamic track fairing for a gas turbine engine fan nacelle


    Contributors:
    ZSURKA MARK (author)

    Publication date :

    2019-03-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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



    AERODYNAMIC TRACK FAIRING FOR A GAS TURBINE ENGINE FAN NACELLE

    ZSURKA MARK | European Patent Office | 2020

    Free access

    Track fairing assembly for a turbine engine nacelle

    SIDELKOVSKIY DMITRIY B / ZYSMAN STEVEN H / MALECKI ROBERT E | European Patent Office | 2019

    Free access

    TRACK FAIRING ASSEMBLY FOR A TURBINE ENGINE NACELLE

    SIDELKOVSKIY DMITRIY B / ZYSMAN STEVEN H / MALECK ROBERT E | European Patent Office | 2020

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    Natural laminar flow flight experiments on a turbine engine nacelle fairing

    Obara, C. J. / Hastings, E. C. / Schoenster, J. A. et al. | NTRS | 1986


    Natural laminar flow flight experiments on a turbine engine nacelle fairing

    OBARA, C. / HASTINGS, E. / SCHOENSTER, J. et al. | AIAA | 1986