| 摘要 |
The liquid fuel-using gas turbine combustor prevents the generation of combustion oscillation. The gas turbine combustor is provided with a pilot burner disposed on the central position of the combustion casing, main burners disposed so as to surround the pilot burner. The main burners are configured such that a main nozzle is installed in the central portion of a cylindrical premixing nozzle, with a liquid fuel being injected from fuel injection holes (provided at the periphery of the main nozzle) toward the inner surface of an elongated nozzle connected to the downstream side of the premixing nozzle, and with the injection pattern of the fuel being set so as to differ among the multiple main burners. For example, different injection patterns can be provided by setting different liquid fuel injection angles (&thetas;1, &thetas;2) for the fuel injection holes on the multiple main burners. |
