| 摘要 |
<p>This invention relates to a gas turbine combustor of a premixing combustion system in which a fuel and the air are mixed and burnt, consisting of a cylindrical main nozzle provided on an upstream end wall of a cylindrical combustion chamber, an auxiliary nozzle formed around the main nozzle, a main premixed gas supply means for supplying a premixed gas to the main nozzle, and an auxiliary premixed gas supply means for supplying a premixed gas, the excess air ratio of which is smaller than that of the main premixed gas, to the auxiliary nozzle. Owing to this arrangement, a lean premixed gas having an excess air ratio larger than 1 can be burnt stably under low to high loads of a gas turbine.</p> |
