CPC F02C 7/264 (2013.01) [B64D 27/10 (2013.01); F23R 3/28 (2013.01)] | 7 Claims |
1. A method of operating a gas turbine engine, the gas turbine engine comprising:
a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject a liquid fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein 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, wherein 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 comprising:
providing a fuel to the plurality of fuel spray nozzles having a calorific value of between 43.5 MJ/kg and 44 MJ/kg, wherein
the fuel provided to the plurality of fuel spray nozzles comprises a fuel blend having a blend ratio in the range of 50-100% SAF, and
the SAF comprises renewable hydrocarbons and has at least one of a density of between 90% and 98% that of kerosene and a calorific value of between 101% and 105% that of kerosene.
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