A method and system 155 for determining one or more fuel characteristics of an aviation fuel for an aircraft gas turbine engine 10. The method comprises determining one or more performance parameters of the engine during a first time period of operation and determining one or more fuel characteristics based on the performance parameter(s). The characteristic(s) may be determined during a second later period of operation, and the first period may be a first flight phase and the second period may be a second flight phase, different from the first. The performance parameter(s) may include a fan rotation speed, a turbine entry temperature (TET), and/or a combustor fuel-to-air ratio. Each determined performance parameter may be compared with a reference performance parameter corresponding to operation of an engine with a fuel having a known fuel characteristic. The fuel characteristic(s) may include a hydrocarbon distribution, a percentage of sustainable aviation fuel (SAF), an aromatic hydrocarbon content and/or an indication that the fuel is a fossil fuel e.g. kerosene.


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    Titel :

    Performance parameters


    Beteiligte:
    PETER SWANN (Autor:in) / DAVID M BEAVEN (Autor:in) / CRAIG W BEMMENT (Autor:in) / ALASTAIR G HOBDAY (Autor:in) / BENJAMIN J KEELER (Autor:in) / CHRISTOPHER P MADDEN (Autor:in) / MARTIN K YATES (Autor:in)

    Erscheinungsdatum :

    2023-07-26


    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



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