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


    Additional title:

    AERODYNAMISCHE SCHIENENVERKLEIDUNG FÜR DIE LÜFTUNGSGONDEL EINES GASTURBINENMOTORS
    CARÉNAGE DE GLISSIÈRE AÉRODYNAMIQUE POUR UNE NACELLE DE VENTILATEUR DE TURBINE À GAZ


    Contributors:
    ZSURKA MARK (author)

    Publication date :

    2020-03-04


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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