| 摘要 |
A dual fuel burner for a gas turbine engine comprises a gas fuel manifold and ducts opening into a central air passage, a liquid fuel manifold and tangentially arranged apertures opening into an annular liquid fuel passage terminating in an annular nozzle. The central air passage has an upstream swirler, and is arranged to receive a flow of compressed air at its upstream end and to discharge a flow of compressed air and either gaseous or liquid fuel from its downstream end. The burner also has a water manifold so that water can be injected into the fuel and air flow via ducts and an annular air passage, to control NOx emission. In an alternative arrangement, the liquid fuel can be injected into the annular air passage. The burner is intended to operate on a range of high calorific fuels, both liquid and gaseous, and is designed to minimize the surface area on which carbon may accumulate during operation.
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