A gas turbine engine has a combustor with a combustion chamber and a plurality of fuel spray nozzles including a first subset of nozzles and a second subset of nozzles. The first subset of nozzles are supplied with more fuel than the second subset of nozzles. A ratio of the number of nozzles in the first subset to the number of nozzles in the second subset is in the range of 1:2 to 1:5. A method includes providing fuel to the one or more fuel-oil heat exchangers, transferring heat from oil to the fuel, and providing the fuel from the one or more fuel-oil heat exchangers to the fuel spray nozzles. Heat is transferred from the oil to the fuel to lower a viscosity of the fuel to 0.58 mm2/s or lower on injection of the fuel into the combustion chamber at cruise conditions.


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    Titel :

    AIRCRAFT FUEL CONTROL TO SUBSETS OF FUEL SPRAY NOZZLES


    Beteiligte:
    MADDEN CHRISTOPHER P (Autor:in) / BEMMENT CRAIG W (Autor:in) / SMITH ANDREW T (Autor:in) / SWANN PETER (Autor:in)

    Erscheinungsdatum :

    02.01.2025


    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 / F23R Erzeugen von Verbrennungsprodukten hohen Druckes oder hoher Geschwindigkeit, z.B. Gasturbinenbrennkammern , GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS



    Aircraft fuel control to subsets of fuel spray nozzles

    MADDEN CHRISTOPHER P / BEMMENT CRAIG W / SMITH ANDREW T et al. | Europäisches Patentamt | 2024

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