| 摘要 |
To present a gas turbine combustor capable of improving the fuel distribution from the main fuel nozzle, suppressing fluctuations of internal pressure and elevation of inner tube metal temperature, and enhancing the combustion stability and durability of the combustor. A gas turbine combustor used in a gas turbine having a multi-nozzle type premixing combustor with a nozzle outer tube (7) for forming and injecting a premixed gas of main fuel and combustion air divided and disposed in plural sections around a cone (4) for forming a diffusion flame by reaction between pilot fuel and combustion air disposed in a center of a section of a combustor inner tube (1), in which nozzle holes (5a) of a main fuel nozzle (5) are formed in three positions at equal intervals on the nozzle main body wall, and one of them is disposed at the outer periphery of the combustor inner tube (1) on the diametral line linking between the center of the combustor inner tube (1) and the center of the main fuel nozzle (5), and the fuel distribution to the outer periphery is decreased.
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