A method of operating a gas turbine engine including an engine core including a turbine, compressor, combustor to combust a fuel, and core shaft connecting the turbine and compressor; a fan upstream of the engine core; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a primary oil loop system to supply oil to the gearbox; and a heat exchange system. The method includes controlling the heat exchange system to adjust fuel viscosity to be lower than or equal to 0.58 mm2/s on entry to the combustor at cruise conditions.


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    Titel :

    Fuel viscosity


    Beteiligte:
    CRAIG W BEMMENT (Autor:in) / ALASTAIR G HOBDAY (Autor:in) / BENJAMIN J KEELER (Autor:in) / CHRISTOPHER P MADDEN (Autor:in) / ANDREA MINELLI (Autor:in) / ANDREW T SMITH (Autor:in) / PETER SWANN (Autor:in) / MARTIN K YATES (Autor:in)

    Erscheinungsdatum :

    14.05.2025


    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 / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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