A method of operating a gas turbine engine; the gas turbine engine includes a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The plurality of fuel spray nozzles includes a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. The combustor is operable in a condition in which the first subset of fuel spray nozzles are supplied with more fuel than the second subset of fuel spray nozzles. A ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. The method includes: providing fuel to the one or more fuel-oil heat exchangers. Also provided is a gas turbine engine for an aircraft.


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    Titel :

    AIRCRAFT FUELLING


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

    Erscheinungsdatum :

    2024-06-27


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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    Hunter, J. / Williams, P.G. | Engineering Index Backfile | 1963


    Fuelling turbine-engined aircraft

    Engineering Index Backfile | 1958


    Electrostatic problem in aircraft fuelling

    Winter, E.F. | Engineering Index Backfile | 1962


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    Poulston, B.V. | Engineering Index Backfile | 1958


    Aircraft fuelling problems of future

    Engineering Index Backfile | 1956