| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of improving exhausting characteristic by reducing an unburned portion in partial load and stably implementing combustion by improving a fuel staging method. SOLUTION: With respect to main nozzles respectively communicated with main burners 6, the combustion at a low load band is implemented only by, for example, five main nozzles M2-M6 indicated by diagonal lines located at a position separated from a bypass elbow 9, when codes of M1-M8 are successively applied to the main nozzles counterclockwise from a bypass elbow 9 side, and the combustion is implemented by all of main nozzles M1-M8 by adding remaining main nozzles in a partial load band. COPYRIGHT: (C)2006,JPO&NCIPI
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