A nacelle (100) for housing a fan within a gas turbine engine (10) having a longitudinal centre line (101) includes a leading edge (108) and a trailing edge (110). A nacelle length (Lnac) is defined as an axial distance between the leading edge (108) and the trailing edge (110). An azimuthal angle (θ) is defined about the longitudinal centre line (101). The nacelle length (Lnac) varies azimuthally. The nacelle length (Lnac) decreases azimuthally from an inboard end (116) of the nacelle (100) to an outboard end (118) of the nacelle (100).


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    Titel :

    NACELLE FOR GAS TURBINE ENGINE AND AIRCRAFT COMPRISING THE SAME


    Weitere Titelangaben:

    GONDEL FÜR GASTURBINENTRIEBWERK UND FLUGZEUG DAMIT
    NACELLE POUR MOTEUR À TURBINE À GAZ ET AÉRONEF LA COMPRENANT


    Beteiligte:

    Erscheinungsdatum :

    06.03.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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