Combustor Control Method and Combustor Controller
Provided are a combustor control method and a combustor controller capable of calculating the combustion air flow and the fuel flow in multi-shafts gas turbine with high precision and without the need of performing complicated calculations and thereby calculating a fuel-air ratio necessary for stable combustion control. The multi-shaft gas turbine is made up of a gas generator turbine and a power turbine. Combustors includes a diffusive combustion units and a plurality of premixed combustion units. An ignition/extinction control unit of the combustor control device calculates the combustion air flow supplied to the combustors based on the open position of compressor inlet guide vanes attached to the gas generator turbine, revolution speed of the gas generator turbine and compressor inlet temperature, calculates the flow of fuel supplied to the combustors based on revolution speed of the power turbine, and calculates the fuel-air ratio in real time as flame reference based on the calculated combustion air flow and fuel flow.
1 . A combustor control method for controlling combustion in combustors equipped with a diffusive combustion unit and a plurality of premixed combustion units, the combustor control method being used for multi-shafts gas turbine made up of:
a gas generator turbine on first shaft including a compressor which supplies compressing air, the combustors which is supplied with fuel and the compressed air discharged from the compressors, and high pressure turbine, which is supplied with combustion gas combusted in the combustors, for driving the compressor; and
a power turbine including low pressure turbine on second shaft separated from the first shaft is driven by the combustion gas discharged from the gas generator turbine,
wherein the combustor control method comprises the following steps executed using an ignition/extinction control unit of a combustor controller:
calculating combustion air flow supplied to the combustors based on an open position of compressor inlet guide vanes attached to the gas generator turbine, revolution speed of the gas generator turbine and atmospheric temperature;
calculating a flow of the fuel supplied to the combustors based on revolution speed of the power turbine; and
calculating a fuel-air ratio in real time as flame reference based on the calculated combustion air flow and fuel flow.
2 . The combustor control method according to claim 1 , wherein fuel flow demand for the diffusive combustion units and each of the premixed combustion units are calculated by a ratio of premix combustion is previously set according to flame control reference, FCR, using the functional unit of fuel flow demand, FFD, for each of combustion units of the combustion controller.
3 . The combustor control method according to claim 2 , wherein the functional unit of fuel flow demand for each of combustion units sets a local minimum value, FCRRLMN, and a local maximum value, FCRRLMX, as limiting values for restricting the flame reference, FCR, outputted by the ignition/extinction control unit while changing the local minimum value, FCRRLMN, and the local maximum value, FCRRLMX, in response to transferring combustion mode.
4 . The combustor control method according to claim 3 , wherein the functional unit of fuel flow demand for each of combustion units compares the flame reference, FCR, outputted by the ignition/extinction control unit, the local minimum value, FCRRLMN, and the local maximum value, FCRRLMX, and figures out the median of the those values as a new flame reference, FCRRL.
5 . The combustor control method according to claim 4 , wherein when the local minimum value, FCRRLMN, and the local maximum value, FCRRLMX, have been changed upon the transferring combustion mode, the functional unit of fuel flow demand for each of combustion units suppress a change rate of the flame a reference so as to make the change rate constant and outputs the change rate-limited flame a reference, FCRRL.
6 . The combustor control method according to claim 2 , wherein the functional unit of fuel flow demand for each of combustion units outputs the uniform fuel flow demand to each of premixed combustion units in response to the transferring of the combustion mode commanded by ignition/extinction control unit.
7 . A combustor controller for controlling combustion in a combustors equipped with a diffusive combustion unit and a plurality of premixed combustion units, the combustor controller being used for multi-shafts gas turbine made up of:
a gas generator turbine on first shaft including a compressor which supplies compressing air, the combustors which is supplied with fuel and the compressed air discharged from the compressor, and high pressure turbine, which is supplied with combustion gas combusted in the combustors, for driving the compressor; and
a power turbine on second shaft separated from the first shaft including low pressure turbine which is driven by the combustion gas discharged from the gas generator turbine,
wherein the combustor controller comprises an ignition/extinction control unit which calculates combustion air flow supplied to the combustors based on an open position of compressor inlet guide vanes attached to the gas generator turbine, revolution speed of the gas generator turbine and compressor inlet temperature, calculates the fuel flow supplied to the combustors based on revolution speed of the power turbine, and calculates a fuel-air ratio in real time as flame reference based on the calculated combustion air flow and fuel flow.