A nacelle (21) defining an intake (12) is provided for channelling and conditioning freestream airflow to a fan (23) of a ducted fan gas turbine engine (10). The nacelle intake comprises in flow series an intake lip (40), and a diffuser (42). The intake lip has at its forwardmost end a highlight (H) which is a closed loop defining a boundary between inner and outer surfaces of the nacelle, and the diffuser terminates at its rearwardmost end at a front face of the fan (23). The intake has a circumferentially extending shock control bump (48) or a series of circumferentially spaced shock control bumps (48) formed thereon. On longitudinal cross sections through the intake containing the bump (48) or series of bumps (48): the bump or each bump of the series of bumps has a profile which forms in flow series an up-ramp (46), a maximum (M) and a down-ramp (44), at least one of the up-ramp and the down-ramp forming an inflection point or curvature discontinuity point on the profile, and the inflection point or curvature discontinuity point being axially located between the highlight and a position which is axially rearward therefrom by a distance of no more than 0.6 L, where L is the axial distance between the highlight and the front fan face.


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    Titel :

    NACELLE INTAKE


    Weitere Titelangaben:

    GONDELEINLAUF
    ADMISSION DE NACELLE


    Beteiligte:
    QIN NING (Autor:in) / SHAHPAR SHAHROKH (Autor:in) / SMITH ANGUS (Autor:in) / JOHN ALISTAIR (Autor:in)

    Erscheinungsdatum :

    2020-04-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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