A method of operating a gas turbine engine 10 is disclosed, the gas turbine engine comprising a fuel combustor 16; and a fuel management system providing fuel to the combustor. The fuel management system comprises two fuel-oil 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 located between the heat exchangers and arranged to deliver the fuel to the combustor. The method comprises controlling the fuel management system so as to raise the fuel temperature to at least 135°C on entry to the combustor at cruise conditions. There may be a fuel bypass 1005 to allow proportion of the fuel to bypass the first heat exchanger; and an oil bypass to allow a proportion of oil to bypass either of the two exchangers. A gas turbine engine is also claimed.
A fuelling system
12.02.2025
Patent
Elektronische Ressource
Englisch