A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse. The inlet duct has a surface defining the second ellipse which curves away from the first ellipse, such that the second ellipse is larger at an intermediate location. The second ellipse is even larger at a downstream end of the inlet duct leading into a fan.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Gas turbine engine inlet wall design


    Beteiligte:

    Erscheinungsdatum :

    2016-03-22


    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 INLET WALL DESIGN

    VOYTOVYCH DMYTRO MYKOLAYOVYCH / SHARMA OM P | Europäisches Patentamt | 2015

    Freier Zugriff

    GAS TURBINE ENGINE INLET WALL DESIGN

    VOYTOVYCH DMYTRO MYKOLAYOVYCH / SHARMA OM P | Europäisches Patentamt | 2021

    Freier Zugriff

    Gas turbine engine inlet wall design

    VOYTOVYCH DMYTRO MYKOLAYOVYCH / SHARMA OM P | Europäisches Patentamt | 2024

    Freier Zugriff

    Gas turbine engine inlet wall design

    VOYTOVYCH DMYTRO MYKOLAYOVYCH / SHARMA OM P | Europäisches Patentamt | 2021

    Freier Zugriff

    Gas turbine engine inlet

    QIU YUAN J / MILLER ROBERT M / LORD WESLEY K et al. | Europäisches Patentamt | 2022

    Freier Zugriff