| 摘要 |
A gas turbine engine 10 has a compressor section 36, a combustor section 15, and a turbine section 25 arranged in flow series. The gas turbine 10 is operated by: providing a supply of cryogenic liquid fuel 27; vaporising the cryogenic liquid fuel to produce a gaseous fuel; expanding said gaseous fuel in at least one fuel turbine 33 external to the engine's turbine section 25; and thereafter directing said expanded gaseous fuel into the engine's combustion section 15 for combustion therein. The cryogenic liquid fuel is preferably vaporised in at least one heat exchanger, which may be an inlet cooler 35, an intercooler 30 or a heat exchanger 38 downstream of the engines turbine section 25. A plurality of fuel turbines 33 may be provided in flow series and the gaseous fuel may be heated prior to expansion in each fuel turbine 33. A further fuel, other than the cryogenic liquid fuel may be burned in the combustor section 15. |
