Method for operating gas turbine equipment, control device and control program for executing said operating method

A non-transitory computer-readable storage medium storing a control program for gas turbine equipment including a gas turbine including a compressor configured to compress air to generate compressed air, a combustor configured to generate combustion gas by combusting a fuel in the compressed air, and a turbine configured to be driven by the combustion gas, and a plurality of types of fuel valves configured to regulate a flow rate of the fuel to be supplied to the combustor, the combustor including a plurality of types of nozzles configured to inject the fuel, and each of the plurality of types of fuel valves being provided for each of the plurality of types of nozzles, the control program causing a computer to execute a process comprising:

• a combustion load command generation step of obtaining a combustion load command value which is a parameter having a positive correlation with an inlet temperature which is a temperature of the combustion gas at an inlet of the turbine;
• a flow rate ratio calculation step of obtaining a flow rate ratio of the fuel to be supplied to each of the plurality of types of nozzles in accordance with the combustion load command value;
• a valve opening degree calculation step of obtaining a valve opening degree of each of the fuel valves for each of the plurality of types of nozzles, based on the flow rate ratio of the fuel to be supplied to each of the plurality of types of nozzles;
• and
• a control signal output step of outputting a control signal indicating the valve opening degree to each of the fuel valves of each of the plurality of types of nozzles,
• wherein the combustion load command generation step includes
• a first load command calculation step of selectively obtaining the combustion load command value when a fuel type command from an outside indicates that a fuel type of the fuel to be supplied to the combustor is a first fuel, and
• a second load command calculation step of selectively obtaining the combustion load command value when the fuel type command from the outside indicates that the fuel type of the fuel to be supplied to the combustor is a second fuel,
• wherein each of the first load command calculation step and the second load command calculation step includes
• a maximum temperature output calculation step of obtaining a maximum temperature output which is a scheduled output corresponding to the fuel type of the fuel to be supplied to the combustor, with respect to an inlet maximum temperature which is a maximum temperature at which the inlet temperature is determined in advance,
• a minimum temperature output calculation step of obtaining a minimum temperature output which is a scheduled output corresponding to the fuel type of the fuel to be supplied to the combustor, with respect to an inlet minimum temperature which is a minimum temperature at which the inlet temperature is determined in advance,
• a degradation coefficient calculation step of obtaining a degradation coefficient for correcting the maximum temperature output,
• a degradation correction step of correcting the maximum temperature output using the degradation coefficient, and
• a combustion load command value calculation step of obtaining the combustion load command value using the minimum temperature output, a corrected maximum temperature output which is the maximum temperature output corrected in the degradation correction step, and an actual output of the gas turbine as detected by an output meter,
• wherein the degradation coefficient calculation step includes
• a deviation calculation step of obtaining a deviation between the corrected maximum temperature output and the actual output, and
• a coefficient calculation step of obtaining the degradation coefficient in accordance with the deviation when temperature control is performed such that the inlet temperature is the inlet maximum temperature,
• wherein the coefficient calculation step includes a degradation parameter storage step of storing, in a degradation parameter storage unit, a degradation parameter which is a value obtained by executing proportional integration processing on a ratio of the deviation when the deviation is equal to or greater than a predetermined threshold value during the temperature control, the degradation parameter storage unit being a portion of a storage area of the computer, and
• wherein, in the coefficient calculation step, the degradation coefficient is output, based on the degradation parameter stored in the degradation parameter storage unit.

A method for operating gas turbine equipment including a gas turbine including a compressor configured to compress air to generate compressed air, a combustor configured to generate combustion gas by combusting a fuel in the compressed air, and a turbine configured to be driven by the combustion gas, and a plurality of types of fuel valves configured to regulate a flow rate of the fuel to be supplied to the combustor, the combustor including a plurality of types of nozzles configured to inject the fuel, and each of the plurality of types of fuel valves being provided for each of the plurality of types of nozzles, the method comprising:

• a combustion load command generation step of obtaining a combustion load command value which is a parameter having a positive correlation with an inlet temperature which is a temperature of the combustion gas at an inlet of the turbine;
• a flow rate ratio calculation step of obtaining a flow rate ratio of the fuel to be supplied to each of a plurality of types of nozzles in accordance with the combustion load command value;
• a valve opening degree calculation step of obtaining a valve opening degree of each of the fuel valves for each of the plurality of types of nozzles, based on the flow rate ratio of the fuel to be supplied to each of the plurality of types of nozzles;
• and
• a control signal output step of outputting a control signal indicating the valve opening degree to each of the fuel valves of each of the plurality of types of nozzles,
• wherein the combustion load command generation step includes
• a first load command calculation step of selectively obtaining the combustion load command value when a fuel type command from an outside indicates that a fuel type of the fuel to be supplied to the combustor is a first fuel, and
• a second load command calculation step of selectively obtaining the combustion load command value when the fuel type command from the outside indicates that the fuel type of the fuel to be supplied to the combustor is a second fuel,
• wherein each of the first load command calculation step and the second load command calculation step includes
• a maximum temperature output calculation step of obtaining a maximum temperature output which is a scheduled output corresponding to the fuel type of the fuel to be supplied to the combustor, with respect to an inlet maximum temperature which is a maximum temperature at which the inlet temperature is determined in advance,
• a minimum temperature output calculation step of obtaining a minimum temperature output which is a scheduled output corresponding to the fuel type of the fuel to be supplied to the combustor, with respect to an inlet minimum temperature which is a minimum temperature at which the inlet temperature is determined in advance,
• a degradation coefficient calculation step of obtaining a degradation coefficient for correcting the maximum temperature output,
• a degradation correction step of correcting the maximum temperature output using the degradation coefficient, and
• a combustion load command value calculation step of obtaining the combustion load command value using the minimum temperature output, a corrected maximum temperature output which is the maximum temperature output corrected in the degradation correction step, and an actual output of the gas turbine as detected by an output meter,
• wherein the degradation coefficient calculation step includes
• a deviation calculation step of obtaining a deviation between the corrected maximum temperature output and the actual output, and
• a coefficient calculation step of obtaining the degradation coefficient in accordance with the deviation when temperature control is performed such that the inlet temperature is the inlet maximum temperature,
• wherein the coefficient calculation step includes a degradation parameter storage step of storing, in a degradation parameter storage unit, a degradation parameter which is a value obtained by executing proportional integration processing on a ratio of the deviation when the deviation is equal to or greater than a predetermined threshold value during the temperature control, and
• wherein, in the coefficient calculation step, the degradation coefficient is output, based on the degradation parameter stored in the degradation parameter storage unit.

A control device for gas turbine equipment including a gas turbine including a compressor configured to compress air to generate compressed air, a combustor configured to generate combustion gas by combusting a fuel in the compressed air, and a turbine configured to be driven by the combustion gas, and a plurality of types of fuel valves configured to regulate a flow rate of the fuel to be supplied to the combustor, the combustor including a plurality of types of nozzles configured to inject the fuel, and each of the plurality of types of fuel valves being provided for each of the plurality of types of nozzles, the control device comprising:

• a combustion load command generator configured to obtain a combustion load command value which is a parameter having a positive correlation with an inlet temperature which is a temperature of the combustion gas at an inlet of the turbine;
• a flow rate ratio calculator configured to obtain a flow rate ratio of the fuel to be supplied to each of the plurality of types of nozzles in accordance with the combustion load command value;
• a valve opening degree calculator configured to obtain a valve opening degree of each of the fuel valves for each of the plurality of types of nozzles, based on the flow rate ratio of the fuel to be supplied to each of the plurality of types of nozzles;
• and
• a control signal output unit configured to output a control signal indicating the valve opening degree to each of the fuel valves of each of the plurality of types of nozzles,
• wherein the combustion load command generator includes
• a first load command calculation unit configured to selectively obtain the combustion load command value when a fuel type command from an outside indicates that a fuel type of the fuel to be supplied to the combustor is a first fuel,
• a second load command calculation unit configured to selectively obtain the combustion load command value when the fuel type command from the outside indicates that the fuel type of the fuel to be supplied to the combustor is a second fuel, and
• a degradation coefficient calculation unit configured to obtain a degradation coefficient, the degradation coefficient calculation unit being common to the first load command calculation unit and the second load command calculation unit,
• wherein each of the first load command calculation unit and the second load command calculation unit includes
• a maximum temperature output calculation unit configured to obtain a maximum temperature output which is a scheduled output corresponding to the fuel type of the fuel to be supplied to the combustor, with respect to an inlet maximum temperature which is a maximum temperature at which the inlet temperature is determined in advance,
• a minimum temperature output calculation unit configured to obtain a minimum temperature output which is a scheduled output corresponding to the fuel type of the fuel to be supplied to the combustor, with respect to an inlet minimum temperature which is a minimum temperature at which the inlet temperature is determined in advance,
• a degradation correction unit configured to correct the maximum temperature output using the degradation coefficient, and
• a combustion load command value calculation unit configured to obtain the combustion load command value using the minimum temperature output, a corrected maximum temperature output which is the maximum temperature output corrected by the degradation correction unit, and an actual output of the gas turbine as detected by an output meter,
• wherein the degradation coefficient calculation unit includes
• a differentiator configured to obtain a deviation between the corrected maximum temperature output and the actual output, and
• a coefficient calculation unit configured to obtain the degradation coefficient in accordance with the deviation when temperature control is performed such that the inlet temperature is the inlet maximum temperature,
• wherein the coefficient calculation unit includes a degradation parameter storage unit configured to store a degradation parameter which is a value obtained by executing proportional integration processing on a ratio of the deviation when the deviation is equal to or greater than a predetermined threshold value during the temperature control, and
• wherein the coefficient calculation unit is configured to output the degradation coefficient, based on the degradation parameter stored in the degradation parameter storage unit.