A method (11000) 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 modulating valve (1902) arranged to allow or block cooling air flow into a subset of the passageways; and a fuel management system (1500) arranged to provide the fuel to the combustor (16), wherein the fuel management system (1500) comprises: two fuel-oil heat exchangers (1004, 1006) through which oil and the fuel flow, the fuel-oil heat exchangers arranged to transfer heat between the oil and the fuel and comprising a primary fuel-oil heat exchanger (1004) and a secondary fuel-oil heat exchanger (1006). The method (11000) comprises using (11100) the modulating valve (1902) to adjust the cooling air flow based on turbine inlet temperature; and transferring (11200) 200 – 600 kJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger (1004) at cruise conditions.


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    Titel :

    Operating a gas turbine engine


    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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