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


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

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


    Beteiligte:

    Erscheinungsdatum :

    2021-06-03


    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



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

    TETRAULT PHILIPPE-ANDRE | Europäisches Patentamt | 2024

    Freier Zugriff

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

    TETRAULT PHILIPPE-ANDRE | Europäisches Patentamt | 2021

    Freier Zugriff

    Gas turbine engine nacelle

    SMITH ANGUS ROY / ARZOGLOU DIMITRIS | Europäisches Patentamt | 2018

    Freier Zugriff

    Gas turbine engine nacelle

    SMITH ANGUS ROY / ARZOGLOU DIMITRIS | Europäisches Patentamt | 2019

    Freier Zugriff

    NACELLE FOR GAS TURBINE ENGINE

    CHRISTIE ROBERT E / MACMANUS DAVID G / SHEAF CHRISTOPHER T J | Europäisches Patentamt | 2021

    Freier Zugriff