| 摘要 |
PROBLEM TO BE SOLVED: To provide an improved axial flow fuel nozzle for a gas turbine.SOLUTION: An axial flow fuel nozzle includes a plurality of annular passages 62, 66, 70 for delivering materials for combustion. The annular air passage 62 receives compressor discharge air, and a plurality of swirler vane slots 64 are positioned adjacent an axial end of the annular air passage 62. The first next annular passage 66 is disposed radially inward of the annular air passage 62, and also the first annular passage 66 includes a plurality of first openings 68 positioned adjacent an axial end of the first annular passage 66 and downstream of the plurality of swirler vane slots 64. The second next annular passage 70 is disposed radially inward of the first annular passage 66, and also the second annular passage 70 includes a plurality of second openings 72 positioned adjacent an axial end of the second annular passage 70 and downstream of the plurality of first openings 68. |
