| 摘要 |
PROBLEM TO BE SOLVED: To provide a combustion control device of a gas turbine capable of controlling a ratio of a fuel such as a pilot ration in response to a combustion gas temperature and combustor bypass valve opening as an original idea by calculating a combustion load directive value (CLCSO) proportional to the combustion gas temperature at a gas turbine entrance. SOLUTION: In this combustion control device of a gas turbine, 700°C MW and 1,500°C MW are calculated based on an IGV opening, an intake air temperature and an atmospheric pressure ratio and a CLCSO obtained by making the combustion gas temperature at the gas turbine entrance dimensionless is calculated by linear interpolation based on them and the output of a generator (gas turbine) of a measured value. The combustion control device is so structured that fuel supply quantities to respective fuel nozzles (a pilot nozzle 25, a top hat nozzle 27 and a main nozzle 26) are controlled by controlling openings of a pilot fuel flow regulation valve 19, a top hat fuel flow regulation valve 21 and a main fuel flow regulation valve 17 based on respective ratios (a pilot ratio, a top hat ratio and a main ratio) of the fuel gas determined based on the CLCSO. COPYRIGHT: (C)2007,JPO&INPIT
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