A method (10000) of operating a gas turbine engine (10) is disclosed, the gas turbine engine (10) comprising an engine core (11) comprising a combustor (16) arranged to burn a fuel; a turbine (19), the turbine comprising a plurality of turbine blades (19’); a compressor (14) arranged to be used as a source of cooling air for the turbine blades (19’); and an inducer (1901) arranged to accelerate and direct the cooling air onto the turbine blades (19’) and comprising a plurality of airflow passageways (1903) and a 10 modulating valve (1902) arranged to control cooling air flow into a subset of the passageways; and a fuel management system (1500) arranged to provide the fuel to the combustor (16), the fuel having a sulphur content of less than 30 ppm. The fuel management system (1500) comprises two fuel-oil heat exchangers (1004, 1006) through which oil and the fuel flow. The method (10000) comprises using the modulating valve (1902) to adjust the cooling air flow based on turbine inlet temperature.


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    Titel :

    Fuel management system


    Beteiligte:
    CRAIG W BEMMENT (Autor:in) / BENJAMIN J KEELER (Autor:in) / CHRISTOPHER P MADDEN (Autor:in) / ANDREA MINELLI (Autor:in) / PETER SWANN (Autor:in) / MARTIN K YATES (Autor:in)

    Erscheinungsdatum :

    2024-08-07


    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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