| 摘要 |
PROBLEM TO BE SOLVED: To provide a combustor for a gas turbine capable of securing positive ignition startability and stability of a firm premixed flame, operating in a wide operating range with low NOx and high combustion efficiency (low CO / low HC) and realizing this easily at a low cost. SOLUTION: The combustor 10 is provided with a swirling apparatus 36 at the outlet of a swirling air current passage 38 to apply swirling speed to supplied air. Fuel is injected toward a combustion chamber 16 from a diffusion fuel injection nozzle 28, and fuel for a premixture is injected into a premixing passage 22 from a premixed fuel injection nozzle 24. The premixture formed in the premixing passage 22 is supplied to the combustion chamber 16. At this time, the swirling air current is further blasted toward the combustion chamber 16 by the swirling apparatus 36. A diffusion flame formed at a center region in the combustion chamber 16 by the diffusion fuel injection nozzle 28, and a premixed flame formed at the outer peripheral region, can be turbulently mixed by the swirling air current. COPYRIGHT: (C)2004,JPO
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