| 摘要 |
<P>PROBLEM TO BE SOLVED: To improve the mixing characteristics of fuel and compressed air in a gas turbine combustor. Ž<P>SOLUTION: A gas turbine system includes a fuel nozzle 12. The fuel nozzle 12 includes a plurality of fuel passages 56, 58 and a plurality of air passages 48 offset in a downstream direction from the fuel passages 56, 58. An air flow from the air passages 48 is configured to intersect with a fuel flow from the fuel passages 56, 58 at a constant angle to induce swirl and mixing of the air flow and the fuel flow downstream of the fuel nozzle 12. Ž<P>COPYRIGHT: (C)2010,JPO&INPIT Ž
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