| 摘要 |
A fuel and gas mixer for a gas turbine combustor includes a body member. The body member has a truncated conical annulus, with its smaller end which communicates with a smaller end of a downstream truncated conical chamber. Gaseous fuel is injected into the annulus through hollow spokes arranged radially in the annulus and mixes with air flow introduced from air upstream passages. The velocity of the primary mixture of the fuel and air in the annulus increases when the flow is directed towards the downstream chamber because the truncated conical shape of the annulus reduces the cross-section of the flow passageway downstream-wise. With increased velocity, the primary mixture is diffused when entering the truncated conical chamber and is further mixed with air introduced from downstream air passages. The body member of the mixer further includes a central air passage with liquid fuel injection holes which are connected to a liquid fuel source such that the air flow entering the central passage delivers the liquid fuel into the chamber and the liquid fuel is mixed with air. The independent liquid fuel injection provides an option for the mixer of the gas turbine combustor when the liquid injection is required as, for example, in a back-up situation. The mixer according to the present invention provides an apparatus to improve a combustion process, especially under a very lean condition.
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