The nacelle (22) can have an inlet (20) fluidly connecting a main gas path of a gas turbine engine core, the inlet (20) having an inlet edge (102) connecting an external skin (106) to an internal duct wall (104), and a step (112A) formed in a surface (115) of at least one of the skin (106) and the duct wall (104), the step (112A) delimiting a first portion (116) of the surface (115) from a second portion (114) of the surface (115), the second portion (114) of the surface (115) being recessed relative to the first portion (116) of the surface (115), the second portion (114) of the surface (115) extending away from both the step (112A) and the inlet edge (102), whereas the first portion (116) of the surface (115) extends between the inlet edge (102) and the step (112A).


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    Titel :

    GAS TURBINE ENGINE, NACELLE THEREOF, AND ASSOCIATED METHOD OF OPERATING A GAS TURBINE ENGINE


    Weitere Titelangaben:

    GASTURBINENTRIEBWERK, DESSEN TRIEBWERKSGONDEL UND VERFAHREN ZUM BETRIEB EINES GASTURBINENTRIEBWERKS
    MOTEUR À TURBINE À GAZ, SA NACELLE ET PROCÉDÉ ASSOCIÉ POUR LE FONCTIONNEMENT D'UN MOTEUR DE TURBINE À GAZ


    Beteiligte:

    Erscheinungsdatum :

    2024-07-31


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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