| 摘要 |
A combustion control device for a gas turbine is capable of controlling fuel ratios such as a pilot ratio and controlling an aperture of a combustor bypass valve in response to a combustion gas temperature at an inlet of the gas turbine in accordance with the original concept by computing a combustion load command value which is proportional to the combustion gas temperature. The combustion control device is configured to calculate a 700° CMW value and a 1500° CMW value based on an inlet guide vane aperture, an intake-air temperature, and an atmospheric pressure ratio, then to calculate the combustion load command value to render the combustion gas temperature at the inlet of the gas turbine dimensionless by direct interpolation based on these values and an actual measurement value of a power generator output, and to control apertures of a pilot fuel flow rate control valve, a top hat fuel flow rate control valve, and a main fuel flow rate control valve based on ratios of fuel gas to be determined based on this combustion load command value, and thereby to control fuel supplies to a pilot nozzle, a top hat nozzle, and a main nozzle.
|
