A turbofan engine has an engine core including in flow series a compressor, a combustor and a turbine. The engine further has a fan located upstream of the engine core, has a supersonic intake for slowing down incoming air to subsonic velocities at an inlet to the fan formed by the intake, has a bypass duct surrounding the engine core, wherein the fan generates a core airflow to the engine core and a bypass airflow through the bypass duct, and has a mixer for mixing an exhaust gas flow exiting the engine core and bypass airflow exiting bypass duct. The engine further has a thrust nozzle rearwards of the mixer for discharging mixed flows, the thrust nozzle having a variable area throat. The engine further has a controller controlling the thrust produced by the engine over a range of flight operations including on-the-ground subsonic take-off and subsequent off-the-ground subsonic climb.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Supersonic aircraft turbofan


    Beteiligte:
    STIEGER RORY D (Autor:in) / HICKEY CONOR (Autor:in)

    Erscheinungsdatum :

    2022-07-05


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke



    SUPERSONIC AIRCRAFT TURBOFAN

    STIEGER RORY D / HICKEY CONOR | Europäisches Patentamt | 2020

    Freier Zugriff

    SUPERSONIC AIRCRAFT TURBOFAN ENGINE

    CORIN ROBERT J / WHURR JOHN R | Europäisches Patentamt | 2020

    Freier Zugriff

    Supersonic aircraft turbofan engine

    CORIN ROBERT J / WHURR JOHN R | Europäisches Patentamt | 2024

    Freier Zugriff

    SUPERSONIC TURBOFAN ENGINE

    MILLER BRANDON WAYNE / LARICCHIUTA MARK JOHN / DWYER DANIEL ROBERT et al. | Europäisches Patentamt | 2018

    Freier Zugriff