A method 12000 of operating a gas turbine engine 10 is disclosed, the gas turbine engine comprising a combustor 16 arranged to combust a fuel; and a fuel management system arranged to provide the fuel to the combustor. The fuel management system comprises two fuel-oil heat exchangers through which oil and the fuel flow, the heat exchangers arranged to transfer heat to the fuel and comprising a primary fuel-oil heat exchanger 1004 and a secondary fuel-oil heat exchanger 1006; and a fuel pump 1003 arranged to deliver the fuel to the combustor, wherein the fuel pump is located between the two heat exchangers. The method comprises controlling 12200 the fuel management system so as to adjust the fuel viscosity to lower than 0.58 mm2 /s on entry to the combustor at cruise conditions.
Management of fuel
2024-07-03
Patent
Elektronische Ressource
Englisch
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