Gas turbine control device, gas turbine control method, and program

Abstract

This gas turbine control device comprises: a fuel flow rate calculation unit that calculates a flow rate of fuel flowing into a combustor; an air flow rate calculation unit that calculates an air flow rate of intake air of a compressor; a compressor intake air humidity estimation unit that estimates an intake air relative humidity of the compressor on the basis of an atmospheric temperature and an atmospheric relative humidity measured on an upstream side of an intake air cooling device and an intake air temperature of the compressor measured on a downstream side of the intake air cooling device; a turbine inlet temperature calculation unit that calculates a turbine inlet temperature on the basis of the fuel flow rate, the air flow rate, the intake air relative humidity, and a physical model equation relating to heat energy balance; and a fuel distribution ratio calculation unit that calculates a fuel distribution ratio for a fuel supply system on the basis of the turbine inlet temperature.

Description

Gas turbine control device, gas turbine control method, and program

[0001] This disclosure relates to a gas turbine control device, a gas turbine control method, and a program. This application claims priority to Japanese Patent Application No. 2024-179805, filed in Japan on October 15, 2024, which is incorporated herein by reference.

[0002] The fuel supply system that supplies fuel to the combustor of a gas turbine is sometimes divided into multiple fuel supply systems from the viewpoint of combustion efficiency and combustion stability. The ratio of fuel allocated to each of the multiple fuel supply systems, i.e., the fuel distribution ratio, can be calculated based on the turbine inlet temperature. However, since there is no instrument that can reliably measure the turbine inlet temperature, it is common practice to estimate the turbine inlet temperature based on measurement data obtained by sensors installed in the gas turbine, and then calculate the fuel distribution ratio using the estimated turbine inlet temperature. For example, Patent Document 1 describes a technique for calculating the gas turbine inlet temperature from the heat balance around the combustor. The thermal energy flowing into the combustor is represented by the sum of the thermal energy of the fuel, the thermal energy of the air, and the exothermic energy of the combustion gases, and the thermal energy of the air fluctuates according to the specific enthalpy, which takes into account the effect of humidity due to water vapor contained in the air flowing into the combustor casing. Patent Document 1 describes installing a sensor to measure the humidity of the air flowing into the combustor casing, calculating the specific enthalpy based on the humidity of the air measured by this sensor, and then calculating the thermal energy of the air using the calculated specific enthalpy.

[0003] Japanese Patent Publication No. 2023-166083

[0004] Gas turbines have a characteristic where the density of the intake air to the compressor decreases when the ambient temperature rises, resulting in a decrease in gas turbine output. For this reason, it has been considered to install an intake air cooling device upstream of the compressor to cool the intake air and increase its density. Patent Document 1 does not include an intake air cooling device, and therefore calculates the thermal energy of the air using ambient humidity. On the other hand, in a configuration that includes an intake air cooling device, it is possible to install a humidity sensor upstream of the intake air cooling device, but it is difficult to install a humidity sensor to measure the intake air humidity of the compressor downstream of the intake air cooling device. For this reason, in conventional technology, when the intake air cooling device is switched ON or OFF, the intake air humidity of the compressor becomes uncertain, which reduces the accuracy of the turbine inlet temperature estimation and makes it difficult to properly control the fuel distribution ratio.

[0005] The purpose of this disclosure is to provide a gas turbine control device, a gas turbine control method, and a program that enable fuel distribution ratio control based on the turbine inlet temperature calculated using the estimated intake air humidity behind a vaporization or water spray type intake air cooler, even when an intake air cooler is installed.

[0006] According to one aspect of the present disclosure, a gas turbine control device includes: a fuel flow rate calculation unit that calculates the fuel flow rate into the combustor based on measurement data relating to a fuel supply system that supplies fuel to the combustor of a gas turbine; an air flow rate calculation unit that calculates the air flow rate of the intake air of the compressor based on measurement data relating to the compressor of the gas turbine; a compressor intake air humidity estimation unit that estimates the intake air relative humidity of the compressor based on atmospheric temperature and atmospheric relative humidity measured upstream of an intake air cooling device capable of cooling the intake air of the compressor, and the intake air temperature of the compressor measured downstream of the intake air cooling device; a turbine inlet temperature calculation unit that calculates the turbine inlet temperature based on the fuel flow rate, the air flow rate, the intake air relative humidity, and a physical model equation relating to the thermal energy balance of the combustor; and a fuel distribution ratio calculation unit that calculates the fuel distribution ratio of each of the fuel supply systems connected to the combustor based on the turbine inlet temperature.

[0007] According to one aspect of the present disclosure, a gas turbine control method includes the steps of: calculating a fuel flow rate into a combustor based on measurement data relating to a fuel supply system that supplies fuel to a combustor of a gas turbine; calculating an air flow rate of intake air to a compressor based on measurement data relating to a compressor of a gas turbine; estimating the intake air relative humidity of a compressor based on atmospheric temperature and atmospheric relative humidity measured upstream of an intake air cooling device capable of cooling the intake air of the compressor, and the intake air temperature of the compressor measured downstream of the intake air cooling device; calculating a turbine inlet temperature based on the fuel flow rate, the air flow rate, the intake air relative humidity, and a physical model equation relating to the thermal energy balance of the combustor; and calculating the fuel distribution ratio of each of the fuel supply systems connected to the combustor based on the turbine inlet temperature.

[0008] According to one aspect of the present disclosure, the program causes a gas turbine control device to perform the following steps: calculate the fuel flow rate into the combustor based on measurement data relating to a fuel supply system that supplies fuel to the combustor of a gas turbine; calculate the air flow rate of the intake air of the compressor based on measurement data relating to the compressor of the gas turbine; estimate the intake air relative humidity of the compressor based on the ambient temperature and ambient relative humidity measured upstream of an intake air cooling device capable of cooling the intake air of the compressor, and the intake air temperature of the compressor measured downstream of the intake air cooling device; calculate the turbine inlet temperature based on the fuel flow rate, the air flow rate, the intake air relative humidity, and a physical model equation relating to the thermal energy balance of the combustor; and calculate the fuel distribution ratio of each of the fuel supply systems connected to the combustor based on the turbine inlet temperature.

[0009] According to the above embodiment, even when an intake air cooling device is installed, the intake air humidity downstream of the intake air cooling device is estimated, and the fuel distribution ratio is controlled by the turbine inlet temperature calculated using this estimate.

[0010] This is a schematic diagram showing the overall configuration of a plant according to one embodiment. This is a block diagram showing the functional configuration of a gas turbine control device according to one embodiment. This is a diagram showing an example of the compressor intake humidity estimation process. This is a flowchart showing an example of the processing of a gas turbine control device according to one embodiment. This is a diagram illustrating the change in turbine inlet temperature due to the ON or OFF of the intake cooling device. This is a schematic block diagram showing the configuration of a computer according to one embodiment.

[0011] The embodiments will be described in detail below with reference to the drawings.

[0012] (Overall Plant Configuration) Figure 1 is a schematic diagram showing the overall configuration of a plant according to one embodiment. As shown in Figure 1, the plant 100 comprises a gas turbine 10, a gas turbine control device 20 that controls the gas turbine 10, a fuel supply device 30 that supplies fuel, a fuel supply system 40 that guides the fuel supplied by the fuel supply device 30 to the gas turbine 10, and a generator 50 that generates electricity by driving the gas turbine 10.

[0013] The gas turbine 10 comprises a compressor 11, a combustor 12, a turbine 13, and an intake air cooling device 17.

[0014] The compressor 11 draws in air and compresses the drawn-in air to generate high-pressure compressed air. The compressed air generated by the compressor 11 is supplied to the combustor 12 and turbine 13 located downstream. The compressor 11 comprises a compressor rotor 111 that rotates around the main shaft As as its central axis, a compressor casing 112 that covers the compressor rotor 111 from the outer circumference, and an IGV (Inlet Guide Vane) 14 for adjusting the amount of air drawn in by the compressor 11. The IGV 14 is connected to the gas turbine control device 20 by a control line such as a communication line, as indicated by the dotted arrow. The amount of air drawn in by the compressor 11 is adjusted by the IGV 14 adjusting its opening degree based on command values ​​from the gas turbine control device 20.

[0015] In this embodiment, an intake cooling device 17 is provided in the intake system through which the air drawn into the compressor 11 flows. The intake cooling device 17 is connected to the gas turbine control device 20 by a control line such as a communication line. The intake cooling device 17 switches its operating state ON or OFF based on a control command from the gas turbine control device 20. When the operating state is ON, the intake cooling device 17 cools the air before it is introduced into the compressor 11 (the intake air of the compressor 11). The intake cooling device 17 is an evaporative or water spray type intake cooling device. For example, the intake cooling device 17 is an evaporative cooler that evaporates cooling water through a medium provided inside the intake system and cools the air introduced into the intake system by the latent heat of vaporization of the cooling water. Alternatively, the intake cooling device 17 may be a FOG type cooling device that cools the air by spraying mist, or a chiller, etc.

[0016] The turbine 13 comprises a turbine rotor 131 that rotates around the main shaft As as its central axis, and a turbine casing 132 that covers the turbine rotor 131 from the outer circumference. The compressor rotor 111 and the turbine rotor 131 are connected and rotate integrally around the main shaft As as its central axis.

[0017] The combustor 12 generates high-pressure, high-temperature combustion gas by injecting fuel supplied from the fuel supply system 40 into compressed air generated by the compressor 11 and burning it. The combustor 12 comprises a combustor inner cylinder 121 and a combustor casing 16 that encloses the combustor inner cylinder 121. The combustor inner cylinder 121 burns the fuel in the combustor casing 16 by injecting and igniting fuel supplied from the fuel supply system 40. The combustor casing 16 is connected to the compressor casing 112 and the turbine casing 132. The combustion gas generated in the combustor casing 16 is supplied to the turbine casing 132, causing the turbine rotor 131 to rotate, and the rotation of the turbine rotor 131 causes the compressor rotor 111 to rotate together with it, drawing in air.

[0018] The fuel supply system 40 supplies fuel supplied by the fuel supply device 30 to the combustor 12 at a predetermined pressure and flow rate through fuel piping. In Figure 1, the fuel supply system 40 includes, in addition to the fuel piping connected between the fuel supply device 30 and the gas turbine 10, which is indicated by solid or dashed arrows, a flow control valve (hereinafter referred to as a flow control valve) 41, a nozzle 42, and manifold piping 43 provided in the fuel piping.

[0019] The fuel supply system 40 includes multiple fuel supply systems 40-1, 40-2, 40-3, ... Although only three fuel supply systems 40-1, 40-2, and 40-3 are shown in the example in Figure 1, the number of fuel supply systems is not limited to three. The fuel supply device 30 branches the fuel to be supplied and supplies each of the branched fuels to fuel supply systems 40-1 to 40-3. For example, fuel supply system 40-1 is a top-hat fuel supply system for supplying fuel to the top-hat section of the combustor 12, fuel supply system 40-2 is a pilot fuel supply system for supplying fuel to the center of the combustor inner cylinder 121, and fuel supply system 40-3 is a main fuel supply system for supplying fuel to the section surrounding the center of the combustor inner cylinder 121.

[0020] Since the fuel supply system 40 includes three fuel supply systems 40-1 to 40-3, the flow control valve 41 has flow control valves 41-1, 41-2, and 41-3, each corresponding to fuel supply systems 40-1, 40-2, and 40-3, respectively. Each of the flow control valves 41-1, 41-2, and 41-3 is connected to the gas turbine control device 20 by a control line such as a communication line, as indicated by the dotted arrows. When each of the flow control valves 41-1, 41-2, and 41-3 receives a command value indicating the valve opening degree from the gas turbine control device 20 via the control line, it increases or decreases the valve opening degree according to the received command value.

[0021] Similar to the flow control valve 41, the nozzle 42 has nozzles 42-1, 42-2, and 42-3, each corresponding to one of the fuel supply systems 40-1 to 40-3. Regarding the manifold piping 43, for space reasons, only the manifold piping 43 corresponding to fuel supply system 40-1 is shown in Figure 1, but in reality, one manifold piping 43 is provided for each of the fuel supply systems 40-1 to 40-3. Hereafter, when it is necessary to explain the manifold piping 43 corresponding to each of the fuel supply systems 40-1 to 40-3 individually, the branch numbers of the reference numerals will be used to refer to them as manifold piping 43-1 to 43-3, respectively. Each of the manifold pipes 43-1 to 43-3 is connected to the combustor 12. For example, manifold pipe 43-1 supplies fuel to the top hat section of the combustor 12, manifold pipe 43-2 supplies fuel to the center of the combustor inner cylinder 121, and manifold pipe 43-3 supplies fuel to the section surrounding the center of the combustor inner cylinder 121.

[0022] The rotor 15 is connected to the compressor rotor 111 and rotates integrally with the compressor rotor 111 and the turbine rotor 131 around the main shaft As as its central axis. The generator 50 is connected to one end of the compressor rotor 111 via the rotor 15. The generator 50 is driven by the rotation of the rotor 15 to generate electricity.

[0023] Furthermore, the gas turbine 10 is equipped with various sensors 25a to 25g. Each of the sensors 25a to 25g is connected to the gas turbine control device 20 by a control line such as a communication line, as indicated by the dotted arrows, and transmits the measurement data detected by the measurement to the gas turbine control device 20 via the control line.

[0024] The flow control valve front pressure sensor 25a, the flow control valve rear pressure sensor 25b, and the fuel temperature sensor 25c detect measurement data related to the fuel supply system 40, as shown below.

[0025] The flow regulating valve upstream pressure sensor 25a includes flow regulating valve upstream pressure sensors 25a-1, 25a-2, and 25a-3 provided for each of the fuel supply systems 40-1, 40-2, and 40-3. Each of the flow regulating valve upstream pressure sensors 25a-1, 25a-2, and 25a-3 detects the flow regulating valve upstream pressure P １ＦＶ (1), P １ＦＶ (2), P １ＦＶ (3).

[0026] The flow regulating valve downstream pressure sensor 25b includes flow regulating valve downstream pressure sensors 25b-1, 25b-2, and 25b-3 provided for each of the fuel supply systems 40-1, 40-2, and 40-3. Each of the flow regulating valve downstream pressure sensors 25b-1, 25b-2, and 25b-3 detects the flow regulating valve downstream pressure P ２ＦＶ (1), P ２ＦＶ (2), P ２ＦＶ (3).

[0027] The fuel temperature sensor 25c includes fuel temperature sensors 25c-1, 25c-2, and 25c-3 provided for each of the fuel supply systems 40-1, 40-2, and 40-3. Each of the fuel temperature sensors 25c-1, 25c-2, and 25c-3 detects the fuel temperature T ｆ (1), T ｆ (2), T ｆ (3).

[0028] The wattmeter sensor 25d, index differential pressure sensor 25e, compressor inlet pressure sensor 25f, compressor outlet pressure sensor 25h, compressor outlet temperature sensor 25i, combustor compartment temperature sensor 25j, exhaust gas pressure sensor 25k, exhaust gas temperature sensor 25l, ambient temperature sensor 25p, humidity sensor 25q, and compressor inlet temperature sensor 25r detect measurement data related to the gas turbine as shown below.

[0029] The wattmeter sensor 25d measures the power generated by the generator 50 and detects the measured power as the gas turbine output G ｏｕｔ .

[0030] The index differential pressure sensor 25e controls the compressor index differential pressure P ｉｎｄｅｘ It detects the compressor index differential pressure P. ｉｎｄｅｘ This refers to the pressure difference between the pressure at the casing inlet of the compressor 11 and the pressure near the blades inside the compressor 11, and is an indicator of the airflow rate that the compressor 11 inhales.

[0031] The compressor inlet pressure sensor 25f measures the compressor inlet pressure P, which is the pressure at the suction port of the casing of the compressor 11. １Ｃ Detects.

[0032] The compressor outlet pressure sensor 25h detects the compressor outlet pressure P, which is the pressure at the outlet of the compressor 11. ２Ｃ Detects.

[0033] The compressor outlet temperature sensor 25i measures the compressor outlet temperature T, which is the temperature at the outlet of the compressor 11. ２Ｃ Detects.

[0034] The combustion chamber temperature sensor 25j measures the combustion gas temperature, i.e., the temperature of the air inside the combustion chamber 16, which is the combustion chamber temperature T. ＣＳ Detects.

[0035] The exhaust gas pressure sensor 25k detects the exhaust gas pressure P, which is the pressure at the outlet of the turbine 13. ２Ｔ The exhaust gas temperature sensor 25l detects the exhaust gas temperature T, which is the temperature at the outlet of the turbine 13. ２Ｔ Detects.

[0036] The ambient temperature sensor 25p measures the temperature of the air flowing upstream of the intake cooling device 17 in the intake system, i.e., the ambient temperature T. ０ Detects.

[0037] The humidity sensor 25q measures the relative humidity of the air flowing upstream of the intake cooling device 17 in the intake system, i.e., the atmospheric relative humidity RH. ０ Detects.

[0038] The compressor inlet temperature sensor 25r measures the compressor inlet temperature T, which is the intake air temperature of the compressor 11, and is the air flowing downstream of the intake cooling device 17 in the intake system. １Ｃ Detects.

[0039] (Functional Configuration of Gas Turbine Control Device) Figure 2 is a block diagram showing the functional configuration of a gas turbine control device according to one embodiment. As shown in Figure 2, it includes a fuel flow rate calculation unit 201, an air flow rate calculation unit 202, a compressor intake humidity estimation unit 203, a heat balance calculation unit 204, a correction processing unit 205, a turbine inlet temperature calculation unit 206, a fuel distribution ratio calculation unit 207, and a valve opening degree calculation unit 208.

[0040] The fuel flow rate calculation unit 201 substitutes the data indicating the valve openings O1, O2, and O3 given as command values ​​to the flow control valve 41, and the measurement data related to each of the fuel supply systems 40-1, 40-2, and 40-3 into a predetermined fuel flow rate calculation function f1(•) to calculate the fuel flow rate G, which indicates the amount of fuel flowing into the combustor 12 of the gas turbine 10 per unit time. ｆｔ The following is calculated. Here, the measurement data for each of the fuel supply systems 40-1, 40-2, and 40-3 is the flow control valve front pressure P detected by the flow control valve front pressure sensor 25a. １ＦＶ (1), P １ＦＶ (2), P １ＦＶ (3) The pressure P after the flow control valve detected by the flow control valve after pressure sensor 25b ２ＦＶ (1), P ２ＦＶ (2), P ２ＦＶ (3) and the fuel temperature T detected by the fuel temperature sensor 25c ｆ (1), T ｆ (2), T ｆ (3) This is the data. Based on this data, the fuel flow rate calculation unit 201 performs calculations using the fuel flow rate calculation function f1(•) for each fuel supply system 40-1, 40-2, and 40-3, and calculates the fuel flow rate G that flows into the combustor 12 per unit time through each of the fuel supply systems 40-1, 40-2, and 40-3. ｆｔ (1) and fuel flow rate G ｆｔ (2) and fuel flow rate G ｆｔ (3) Calculate the fuel flow rate G of the fuel supply system 40-1. ｆｔ (1) is calculated as shown in equation (1) below. Fuel flow rate G of fuel supply systems 40-2 and 40-3 ｆｔ (2), fuel flow rate G ｆｔ (3) is found in the same way.

[0041]

[0042] Furthermore, the fuel flow rate calculation unit 201 calculates the fuel flow rate Gft that flows into the combustor 12 through the fuel supply system 40 per unit time by summing the fuel flow rates Gft(1), Gft(2), and Gft(3) corresponding to each of the fuel supply systems 40-1, 40-2, and 40-3, as shown in the following equation (2).

[0043]

[0044] The air flow rate calculation unit 202 calculates the compressor index differential pressure P of the gas turbine 10, which is measured data related to the compressor 11 of the gas turbine 10, specifically the compressor index differential pressure P detected by the index differential pressure sensor 25e. ｉｎｄｅｘ The compressor inlet pressure P detected by the compressor inlet pressure sensor 25f １Ｃ The compressor inlet temperature T detected by the compressor inlet temperature sensor 25r １Ｃ Substituting these values ​​into the predetermined airflow rate calculation function f2(•) as shown in equation (3) below, the airflow rate G represents the amount of air drawn in by the compressor 11 of the gas turbine 10 per unit time. ａｔ Calculate.

[0045]

[0046] The compressor intake humidity estimation unit 203 uses measurement data related to the intake system of the compressor 11 of the gas turbine 10, specifically the ambient temperature T detected by the ambient temperature sensor 25p. ０ And the humidity sensor 25q detects the atmospheric relative humidity RH ０ The compressor intake air temperature T detected by the compressor inlet temperature sensor 25r １Ｃ In relation to this, the intake relative humidity RH indicates the humidity of the air introduced into the compressor 11 (the intake air of the compressor 11). ｃ This allows us to estimate the intake relative humidity RH of the compressor 11 without installing a humidity sensor downstream of the intake cooling device 17. ｃ The following can be estimated and obtained: Dry-bulb temperature, wet-bulb temperature, and relative humidity are correlated, and if any two of these values ​​are known, the remaining value can be determined. Therefore, the compressor intake humidity estimation unit 203 uses known formulas and parameter values ​​to estimate the atmospheric temperature T, which is the dry-bulb temperature detected by the sensor. ０ and atmospheric relative humidity RH ０The wet-bulb temperature of the atmosphere is calculated from the following. Note that the saturated water vapor pressure does not change before and after the intake air cooling device 17, and the relationship with the wet-bulb temperature does not change. For this reason, the compressor intake air humidity estimation unit 203 estimates that the wet-bulb temperature of the intake air of the compressor 11 is the same as the calculated wet-bulb temperature of the atmosphere. The compressor intake air humidity estimation unit 203 then calculates the wet-bulb temperature and the compressor intake air temperature T １Ｃ Therefore, the intake relative humidity RH of the compressor 11 ｃ We estimate this.

[0047] Figure 3 shows an example of the processing of the compressor intake humidity estimation unit. For example, the compressor intake humidity estimation unit 203 estimates the intake relative humidity RH of the compressor 11 based on Sprung's formula shown in equation (4) and the equation showing the relationship between relative humidity, saturated water vapor pressure, and water vapor pressure shown in equation (5). ｃ The following is estimated. In equation (4), t is the dry-bulb temperature [°C], t' is the wet-bulb temperature [°C], e is the water vapor pressure [Pa], es(t') is the saturated water vapor pressure [Pa] at wet-bulb temperature t' [°C], A is the psychrometer coefficient, and P is the atmospheric pressure [Pa]. The psychrometer coefficient A is a constant, for example, 0.000662 if the wet bulb is not frozen, and 0.000583 if it is frozen. In equation (5), RH is the relative humidity [%].

[0048]

[0049]

[0050] From equation (4), we obtain equation (6) to determine the saturated water vapor pressure es at temperature t'.

[0051]

[0052] From equation (5), the water vapor pressure e1 upstream of the intake cooling device 17 (i.e., the atmosphere) is equal to the atmospheric relative humidity RH ０ and atmospheric temperature T ０ It can be calculated using equation (7).

[0053]

[0054] The saturated water vapor pressure es(t') at temperature t' can be determined from various known approximation formulas. For example, the formula of August et al. using Tetens' parameter values ​​shown in equation (8) may be used, or other formulas may be used. That is, es(T') from equation (7) ０ ) can also be expressed as equation (8). For example, as shown in Figure 3, the atmospheric temperature T ０ The temperature is 21°C, and the atmospheric relative humidity is RH. ０ When the concentration is 63%, the atmospheric water vapor pressure e1 is calculated (estimated) to be 1570 Pa.

[0055]

[0056] Furthermore, from the atmospheric water vapor pressure e1 and equation (6), the atmospheric wet-bulb temperature t' can be solved using the following equation (9). In equation (9), es(t') can also be replaced with equation (8). As shown in the example in Figure 3, the atmospheric temperature T ０ When the temperature is 21°C and the atmospheric water vapor pressure e1 = 1570 Pa, the atmospheric wet-bulb temperature t' is calculated to be 16.5°C.

[0057]

[0058] Furthermore, in the case of an evaporative or water spray type intake air cooling system, the wet-bulb temperature is constant before and after the cooling system, so the compressor intake air humidity estimation unit 203 adds the intake air temperature T of the compressor 11 to equation (4). １Ｃ Then, the water vapor pressure e2 of the intake air of the compressor 11, which is downstream of the intake air cooling device 17, is calculated using equation (10) by substituting the determined wet-bulb temperature t'. In addition, the saturated water vapor pressure es2 of the intake air of the compressor 11 is determined using an approximate formula, for example, as exemplified in equation (8). As shown in the example in Figure 3, the wet-bulb temperature t' = 16.5°C and the intake air temperature T １Ｃ When the temperature is 17°C, the water vapor pressure e2 of the intake air from the compressor 11 is calculated to be 1830 Pa, and the saturated water vapor pressure es2 is 1940 Pa.

[0059]

[0060] Furthermore, the compressor intake humidity estimation unit 203 substitutes the saturated water vapor pressure es2 and water vapor pressure e2 of the intake air of the compressor 11 into equation (5) to estimate the intake relative humidity RH ｃThe following is calculated: As shown in Figure 3, when the water vapor pressure e2 = 1830 Pa and the saturated water vapor pressure es2 = 1940 Pa, the intake relative humidity RH ｃ It is calculated to be 95%.

[0061] The compressor intake humidity estimation unit 203 may have reference data such as a conversion table or psychrometric chart that shows the relationship between dry-bulb temperature, wet-bulb temperature, and relative humidity, instead of the formulas and parameter values ​​described above. In this case, the compressor intake humidity estimation unit 203 will use the ambient temperature T ０ And, atmospheric relative humidity RH ０ And, intake air temperature T １Ｃ Based on the reference data, the intake relative humidity RH ｃ Specifically, the compressor intake humidity estimation unit 203 estimates the dry-bulb temperature, which is the ambient temperature T, from the reference data. ０ (Dry-bulb temperature 1 in Figure 3) and atmospheric relative humidity RH ０ The wet-bulb temperature t' of the atmosphere corresponding to the combination is obtained. Similarly, the compressor intake humidity estimation unit 203 obtains the wet-bulb temperature t' of the atmosphere and the compressor intake temperature T from the reference data. １Ｃ (Intake relative humidity RH corresponding to dry bulb temperature 2 in Figure 3) ｃ Obtain it.

[0062] The heat balance calculation unit 204 applies the measured data to a calculation formula (hereinafter referred to as the gas turbine heat balance calculation formula) that shows the overall energy balance of the gas turbine 10, i.e., the balance of work and heat, and calculates the fuel flow rate G when the measured data was obtained. ｆｓ And, airflow rate G ａｓ The heat balance calculation unit 204 applies the measurement data to the gas turbine heat balance calculation formula, for example, the gas turbine output G detected by the power meter sensor 25d. ｏｕｔ The exhaust gas pressure P detected by the exhaust gas pressure sensor 25k ２Ｔ The exhaust gas temperature T detected by the exhaust gas temperature sensor 25l ２Ｔ The compressor inlet pressure P detected by the compressor inlet pressure sensor 25f １Ｃ The compressor inlet temperature T detected by the compressor inlet temperature sensor 25r １Ｃ The compressor outlet pressure P detected by the compressor outlet pressure sensor 25h２Ｃ and the compressor outlet temperature T detected by the compressor outlet temperature sensor 25i ２Ｃ .

[0063] The correction processing unit 205 corrects the fuel flow rate G calculated by the fuel flow rate calculation unit 201 ｆｔ and the air flow rate G calculated by the air flow rate calculation unit 202 ａｔ to obtain the corrected fuel flow rate G ｆｃｏｒ and the corrected air flow rate G ａｃｏｒ and outputs them. The specific processing of the correction processing unit 205 is the same as that of the prior art (for example, the technology described in Patent Document 1). That is, the correction processing unit 205 calculates the fuel correction coefficient K from the fuel flow rate G calculated by the fuel flow rate calculation unit 201 ｆｔ and the fuel flow rate Gfs calculated by the heat balance calculation unit 204, ｆ multiplies the fuel flow rate G calculated by the fuel flow rate calculation unit 201 ｆｔ by the fuel correction coefficient K ｆ to output the corrected fuel flow rate G ｆｃｏｒ . The correction processing unit 205 calculates the air correction coefficient K from the air flow rate G calculated by the air flow rate calculation unit 202 ａｔ and the air flow rate G calculated by the heat balance calculation unit 204 ａｓ , multiplies the air flow rate G calculated by the air flow rate calculation unit 202 ａ by the air correction coefficient K ａｔ to output the corrected air flow rate G ａ . ａｃｏｒ

[0064] The turbine inlet temperature calculation unit 206 calculates the turbine inlet temperature T1T using the equations for solving the predetermined heat balance around the combustor 12 shown in the following equations (9) to (11), that is, the physical model equations for the heat energy balance related to the combustor 12. The physical model equations for the heat energy balance are, for example, equations obtained by modifying the unsteady physical model. The equation representing the unsteady physical model is a model equation representing that the heat energy flowing into the combustor 12 is equal to the heat energy flowing out of the combustor 12. In Equation (9), G ａ is the air flow rate, G ｆ is the fuel flow rate, H1T is the enthalpy of the combustion gas, H ｆ is the fuel enthalpy, H ａ ​is the compressor outlet enthalpy, and LHV represents the combustion gas calorific value. Fuel flow rate G ｆ and airflow rate G ａ These are the corrected fuel flow rates G output by the correction processing unit 205. ｆｃｏｒ and corrected airflow rate G ａｃｏｒ This is the fuel enthalpy H ｆ This is the combustion gas temperature (combustor cabin temperature T ＣＳ ) is obtained from. Compressor outlet enthalpy H ａ The compressor outlet temperature T ２Ｃ Compressor inlet temperature (intake air temperature) T １Ｃ , intake relative humidity RH of compressor 11 ｃ It can be determined from the atmospheric pressure P. Also, in equations (11) to (13), x = air, N ２ , CO ２ , H ２ O, Ar, SO ２ The water flow rate G is used to convert the combustion gas enthalpy H1T to the turbine inlet temperature T1T. Ｈ２０ is the intake relative humidity RH ｃ It is calculated based on the following.

[0065]

[0066]

[0067]

[0068] Thus, in the turbine inlet temperature calculation unit 206, the intake relative humidity RH of the compressor 11 is calculated. ｃ By using this as a parameter, the turbine inlet temperature T1T can be accurately determined regardless of whether the intake cooling device 17 is ON or OFF.

[0069] The fuel distribution ratio calculation unit 207 calculates the fuel distribution ratio D for each of the fuel supply systems 40-1, 40-2, and 40-3 based on the turbine inlet temperature T1T calculated by the turbine inlet temperature calculation unit 206, using a predetermined relationship formula between the turbine inlet temperature T1T and the fuel distribution ratio. １ , D ２ , D ３ The fuel distribution ratio calculation unit 207 calculates three fuel distribution ratios D. １ , D２ , D ３ The sum of these amounts to 100%.

[0070] The valve opening degree calculation unit 208 calculates the fuel distribution ratio D calculated by the fuel distribution ratio calculation unit 207. １ , D ２ , D ３ Based on the externally supplied fuel control signal command value (CSO: Control Signal Output), the valve opening degree O for each of the flow control valves 41-1, 41-2, and 41-3 is calculated according to a predetermined valve opening degree calculation formula. １ , O ２ , O ３ The valve opening degree calculation unit 208 calculates the calculated valve opening degree O. １ , O ２ , O ３ Each of these is given as a command value for the corresponding flow control valves 41-1, 41-2, and 41-3. As a result, flow control valve 41-1 sets the valve opening to O １ The opening degree is adjusted accordingly, and the flow control valve 41-2 is set to valve opening degree O ２ The opening degree is adjusted accordingly, and the flow control valve 41-3 is set to valve opening degree O ３ The valve opening degree is adjusted accordingly. The valve opening degree calculation unit 208 calculates the valve opening degree O １ , O ２ , O ３ This is fed back to the fuel flow rate calculation unit 201.

[0071] (Example of operation of gas turbine control device) Figure 4 is a flowchart showing an example of processing of a gas turbine control device according to one embodiment. The processing flow of the gas turbine control device 20 will be explained with reference to Figure 4.

[0072] The flow control valve front pressure sensors 25a-1 to 25a-3, the flow control valve rear pressure sensors 25b-1 to 25b-3, and the fuel temperature sensors 25c-1 to 25c-3 perform measurements at each detection cycle and transmit the measurement data detected by the measurements to the gas turbine control device 20 via the control line. The fuel flow rate calculation unit 201 calculates the flow control valve front pressure P transmitted by the flow control valve front pressure sensors 25a-1 to 25a-3. １ＦＶ (1), P １ＦＶ(2), P １ＦＶ (3) The flow control valve after pressure P transmitted by the flow control valve after pressure sensors 25b-1 to 25b-3 ２ＦＶ (1), P ２ＦＶ (2), P ２ＦＶ (3) The fuel temperature T transmitted by the fuel temperature sensors 25c-1 to 25c-3 ｆ (1), T ｆ (2), T ｆ (3) The fuel flow rate calculation unit 201 receives and takes in the valve opening O calculated and output by the valve opening calculation unit 208 in the previous detection cycle. １ , O ２ , O ３ Take it in (Step S1-1).

[0073] The fuel flow rate calculation unit 201 substitutes the data acquired in step S1-1 into equation (1) as described above to calculate the fuel flow rate G ｆｔ (1), G ｆｔ (2), G ｆｔ (3) is calculated. The fuel flow rate calculation unit 201 calculates the fuel flow rate G as shown in equation (2). ｆｔ (1), G ｆｔ (2), G ｆｔ (3) The sum of these is the fuel flow rate G, which represents the amount of fuel flowing into the combustor 12 of the gas turbine 10 per unit time. ｆｔ Calculate (Step S2-1).

[0074] The power meter sensor 25d, exhaust gas pressure sensor 25k, exhaust gas temperature sensor 25l, compressor inlet pressure sensor 25f, compressor inlet temperature sensor 25r, compressor outlet pressure sensor 25h, and compressor outlet temperature sensor 25i perform measurements at each detection cycle and transmit the measurement data detected by the measurements to the gas turbine control device 20 via the control line. The heat balance calculation unit 204 calculates the gas turbine output G transmitted by the power meter sensor 25d. ｏｕｔ The exhaust gas pressure P transmitted by the exhaust gas pressure sensor 25k ２Ｔ The exhaust gas temperature T transmitted by the exhaust gas temperature sensor 25l ２Ｔ The compressor inlet pressure P transmitted by the compressor inlet pressure sensor 25f is then transmitted. １Ｃ The compressor inlet temperature (compressor intake temperature) T is transmitted by the compressor inlet temperature sensor 25r. １ＣThe compressor outlet pressure P transmitted by the compressor outlet pressure sensor 25h ２Ｃ The compressor outlet temperature T transmitted by the compressor outlet temperature sensor 25i ２Ｃ The data is received and taken in (step S1-2).

[0075] The heat balance calculation unit 204 calculates the fuel flow rate G based on the data acquired in step S1-2 and the gas turbine heat balance calculation formula. ｆｓ And, airflow rate G ａｓ Calculate (Step S2-2).

[0076] The index differential pressure sensor 25e performs measurements at each detection cycle, and the measurement data detected by the measurement is the compressor index differential pressure P ｉｎｄｅｘ The data is transmitted to the gas turbine control device 20 via the control line. The air flow rate calculation unit 202 calculates the compressor index differential pressure P transmitted by the index differential pressure sensor 25e. ｉｎｄｅｘ The compressor inlet pressure P transmitted by the compressor inlet pressure sensor 25f is then transmitted. １Ｃ The compressor inlet temperature T transmitted by the compressor inlet temperature sensor 25r １Ｃ The data is received and taken in (step S1-3).

[0077] The air flow rate calculation unit 202 substitutes the data acquired in step S1-3 into equation (3) as described above to calculate the air flow rate G, which represents the amount of air drawn in by the compressor 11 of the gas turbine 10 per unit time. ａｔ Calculate (Step S2-3).

[0078] The ambient temperature sensor 25p, humidity sensor 25q, and compressor inlet temperature sensor 25r take measurements at each detection cycle, and the measurement data detected by the measurements is the ambient temperature T ０ Atmospheric relative humidity RH ０ Compressor inlet temperature (compressor intake temperature) T １Ｃ The data is transmitted to the gas turbine control device 20 via the control line. The compressor intake humidity estimation unit 203 uses the ambient temperature T transmitted by the ambient temperature sensor 25p. ０ And the humidity sensor 25q transmits the atmospheric relative humidity RH ０ The compressor inlet temperature T transmitted by the compressor inlet temperature sensor 25r１Ｃ The data is received and taken in (step S1-4).

[0079] The compressor intake humidity estimation unit 203 estimates the intake relative humidity RH of the compressor 11 based on the data acquired in step S1-4, using the method described above. ｃ We estimate (Step S2-4).

[0080] In Figure 4, the sets of processes in steps S1-1 and S2-1, S1-2 and S2-2, S1-3 and S2-3, and S1-4 and S2-4 are performed in parallel.

[0081] The correction processing unit 205 processes the fuel flow rate G calculated by the fuel flow rate calculation unit 201. ｆｔ The heat balance calculation unit 204 calculated the fuel flow rate G. ｆｓ Fuel correction coefficient K based on the above ｆ Multiply by this to get the fuel flow rate G ｆｔ Corrected fuel flow rate G ｆｃｏｒ The correction processing unit 205 calculates the air flow rate G calculated by the air flow rate calculation unit 202. ａｔ The airflow rate G calculated by the heat balance calculation unit 204 ａｓ Air correction coefficient K based on the above ａ Multiply by this to get the airflow rate G. ａｔ Corrected airflow rate G ａｃｏｒ The value is calculated (step S3-2). The processes in step S3-1 and step S3-2 are performed in parallel.

[0082] Next, the turbine inlet temperature calculation unit 206 calculates the corrected fuel flow rate G ｆｃｏｒ And, corrected airflow rate G ａｃｏｒ The turbine inlet temperature calculation unit 206 receives the combustor chamber temperature T transmitted by the combustor chamber temperature sensor 25j. ＣＳ And the fuel temperature T transmitted by fuel temperature sensors 25c-1 to 25c-3 ｆ (1), T ｆ (2), T ｆ (3) The data is received and taken in. The combustion chamber temperature sensor 25j measures at each detection cycle and the measurement data detected by the measurement is the combustion chamber temperature TＣＳ The data is transmitted to the gas turbine control device 20 via the control line. The turbine inlet temperature calculation unit 206 receives the fuel temperature T ｆ (1), T ｆ (2), T ｆ (3) The average value of fuel temperature T ｆ The turbine inlet temperature calculation unit 206 calculates the intake relative humidity RH estimated by the compressor intake humidity estimation unit 203. ｃ The turbine inlet temperature calculation unit 206 calculates the turbine inlet temperature T1T using this data and equations (11) to (13) as described above (step S4).

[0083] The fuel distribution ratio calculation unit 207 receives the turbine inlet temperature T1T output by the turbine inlet temperature calculation unit 206. Based on the received turbine inlet temperature T1T, the fuel distribution ratio calculation unit 207 calculates the fuel distribution ratio D for each of the fuel supply systems 40-1, 40-2, and 40-3 using the relationship formula between the turbine inlet temperature T1T and the fuel distribution ratio. １ , D ２ , D ３ Calculate (Step S5).

[0084] The valve opening degree calculation unit 208 calculates the fuel distribution ratio D output by the fuel distribution ratio calculation unit 207. １ , D ２ , D ３ The valve opening calculation unit 208 takes in the fuel distribution ratio D that it has taken in. １ , D ２ , D ３ Based on the fuel control signal command value (CSO), the valve opening degree O for each of the flow control valves 41-1, 41-2, and 41-3 is calculated using the valve opening degree calculation formula. １ , O ２ , O ３ The valve opening degree calculation unit 208 calculates the valve opening degree O １ , O ２ , O ３ Each of these is output to the corresponding flow control valves 41-1, 41-2, and 41-3. The valve opening degree calculation unit 208 outputs the calculated valve opening degree O １ , O ２ , O ３The output is sent to the fuel flow rate calculation unit 201, and the process ends.

[0085] The series of processes shown in Figure 4 above are performed as the process for one detection cycle, and the series of processes shown in Figure 4 are performed for each cycle.

[0086] (Effects) As described above, the gas turbine control device 20 according to this embodiment includes a fuel flow rate calculation unit 201 that calculates the fuel flow rate into the combustor 12 based on measurement data relating to the fuel supply system 40 that supplies fuel to the combustor 12 of the gas turbine 10, an air flow rate calculation unit 202 that calculates the air flow rate of the intake air of the compressor 11 based on measurement data relating to the compressor 11 of the gas turbine 10, and the ambient temperature T measured upstream of the intake air cooling device 17 that can cool the intake air of the compressor 11. ０ and atmospheric relative humidity RH ０ And the intake air temperature T of the compressor 11 measured downstream of the intake air cooling device 17. １Ｃ Based on this, the intake relative humidity RH of the compressor 11 ｃ A compressor intake humidity estimation unit 203 estimates the fuel flow rate G ｆ And, airflow rate G ａ And, intake relative humidity RH ｃ The system includes a turbine inlet temperature calculation unit 206 that calculates the turbine inlet temperature T1T based on a physical model equation relating to the thermal energy balance of the combustor 12, and a fuel distribution ratio calculation unit 207 that calculates the fuel distribution ratio for each of the fuel supply systems 40 connected to the combustor 12 based on the turbine inlet temperature T1T.

[0087] In this way, the gas turbine control device 20 can estimate the humidity of the air downstream of the intake air cooling device 17, i.e., the intake air of the compressor 11 (intake humidity), without installing a humidity sensor downstream of the intake air cooling device 17. As a result, the turbine inlet temperature T1T can be calculated accurately using the estimated intake humidity of the compressor 11, making it possible to perform appropriate fuel distribution ratio control based on the turbine inlet temperature T1T. Furthermore, changes in intake humidity caused by switching the intake air cooling device 17 ON or OFF can be reflected in the fuel distribution ratio without delay.

[0088] Figure 5 is the first diagram illustrating the change in turbine inlet temperature due to the ON or OFF state of the intake air cooling system. Figure 5 illustrates the time series of the intake air temperature D11 of the compressor 11, the biases D21 and D22 with respect to the exhaust gas temperature control command value of the gas turbine 10, and the turbine inlet temperatures D31 and D32 associated with the ON or OFF state of the intake air cooling system 17. D21 represents the change in bias in the control example of this embodiment, and D22 represents an example of the change in bias in the control example of the prior art. For example, when the intake air cooling system is ON, control is performed such as adding the bias value to the exhaust gas temperature limit of the gas turbine 10. As the exhaust gas temperature limit increases, the fuel flow rate supplied to the combustor 12 increases, and the output of the gas turbine 10 increases. Also, D31 represents the change in turbine inlet temperature associated with the control of this embodiment, and D32 represents the change in turbine inlet temperature associated with the control of the prior art.

[0089] In the conventional technology, as described above, it was not possible to install a humidity sensor downstream of the intake air cooling device. Therefore, for example, when the intake air cooling device was switched ON (cooler on) at time t1, the intake air humidity remained uncertain until the intake air temperature reached the set value. Consequently, in the conventional technology, in order to suppress the overshoot of the turbine inlet temperature, as shown in D22 of Figure 5, the system waited for a predetermined time to elapse after switching the intake air cooling device ON before starting to add a bias corresponding to the cooling of the intake air. As a result, as shown in Figure 5, the turbine inlet temperature D32 temporarily decreased during the period from time t1 to time t2, and the efficiency of the gas turbine decreased accordingly. Furthermore, in the conventional technology, as shown in D22 of Figure 5, after switching the intake air cooling device OFF (cooler off) at time t3, because the intake air humidity was uncertain, the system controlled to reset the bias to zero before time t4, when the intake air temperature returned to the state before the intake air cooling device was activated. As a result, the fuel supplied to the combustor decreased faster than the actual changes in intake air temperature and humidity, causing D32 to temporarily decrease from time t3 to time t4, and consequently reducing the efficiency of the gas turbine.

[0090] In contrast, the gas turbine control device 20 according to this embodiment estimates the intake air humidity of the compressor 11, calculates the turbine inlet temperature according to the intake air humidity, and controls the gas turbine 10. As a result, as shown in D21 of Figure 5, after time t1 when the intake air cooling device 17 is switched ON, the change in the turbine inlet temperature can be calculated more accurately by detecting changes in intake air temperature and intake air humidity. This allows for automatic control of adding a bias based on the turbine inlet temperature to prevent the turbine inlet temperature from falling below the rated level. Furthermore, after time t3 when the intake air cooling device 17 is switched OFF, the change in the turbine inlet temperature can be calculated more accurately by detecting changes in intake air temperature and intake air humidity. This allows for automatic control of gradually decreasing the bias based on the turbine inlet temperature to prevent the turbine inlet temperature D31 from rising above the rated level. In this way, the gas turbine control device 20 can maintain a constant turbine inlet temperature D31 even when the intake air cooling device 17 is switched ON or OFF, thereby suppressing a decrease in the efficiency of the gas turbine 10.

[0091] Furthermore, the compressor intake air humidity estimation unit 203 estimates the ambient temperature T ０ and atmospheric relative humidity RH ０ Based on this, the wet-bulb temperature of the atmosphere is calculated, and the wet-bulb temperature of the atmosphere and the intake air temperature T of the compressor 11 are used. １Ｃ Based on this, the intake relative humidity RH of the compressor 11 ｃ We estimate this.

[0092] In this way, the gas turbine control device 20 utilizes the fact that the wet-bulb temperature does not change before and after the intake air cooling device 17, and uses the existing ambient temperature sensor 25p, humidity sensor 25q, and compressor inlet temperature sensor 25r to accurately determine the intake relative humidity RH of the compressor 11. ｃ It is possible to estimate this.

[0093] Furthermore, the compressor intake humidity estimation unit 203 estimates the atmospheric temperature T, which is the dry-bulb temperature, based on reference data representing the relationship between dry-bulb temperature, wet-bulb temperature, and relative humidity. ０ And, atmospheric relative humidity RH ０The wet-bulb temperature of the atmosphere corresponding to the combination is calculated, and based on the reference data, the estimated wet-bulb temperature of the atmosphere and the intake air temperature T (dry-bulb temperature) are used. １Ｃ Intake relative humidity RH corresponding to the combination ｃ We estimate this.

[0094] In this way, the gas turbine control device 20 determines the intake relative humidity RH based on pre-prepared reference data. ｃ This can be easily estimated.

[0095] Furthermore, the compressor intake humidity estimation unit 203 estimates the atmospheric temperature T based on a relational expression representing the relationship between dry-bulb temperature, wet-bulb temperature, water vapor pressure, and saturated water vapor pressure at the wet-bulb temperature, and an approximate formula for saturated water vapor pressure. ０ and atmospheric relative humidity RH ０ The corresponding wet-bulb temperature of the atmosphere is calculated, and an approximate formula is used, along with the intake air temperature T. １Ｃ Based on this, the saturated water vapor pressure es2 of the intake air of the compressor 11 is calculated, and the relationship is obtained using the wet-bulb temperature of the atmosphere, the saturated water vapor pressure es2 of the intake air of the compressor 11, and the intake air temperature T １Ｃ Based on this, the water vapor pressure e2 of the intake air of the compressor 11 is calculated, and based on the water vapor pressure e2 and saturated water vapor pressure es2 of the intake air of the compressor 11, the intake relative humidity RH ｃ We estimate this.

[0096] In this way, the gas turbine control device 20 determines the intake relative humidity RH of the compressor 11 based on the relational equation and the approximation equation. ｃ It can estimate with high accuracy. Furthermore, since it does not require reference data, the storage capacity can be reduced.

[0097] (Other Embodiments) Although one embodiment has been described in detail above with reference to the drawings, the specific configuration is not limited to that described above, and various design changes can be made. In other embodiments, the order of the above-described processes may be changed as appropriate. Also, some processes may be executed in parallel.

[0098] (Computer Configuration) Figure 6 is a schematic block diagram showing the configuration of a computer according to one embodiment. The computer 900 comprises a processor 901, a main memory 902, an auxiliary memory 903, and an interface 904. The gas turbine control device 20 described above is implemented in the computer 900. The operation of each of the above-described processing units is stored in the auxiliary memory 903 in the form of a program. The processor 901 reads the program from the auxiliary memory 903, loads it into the main memory 902, and executes the above processing according to the program. The processor 901 also allocates memory area in the main memory 902 to be used for the above processing according to the program.

[0099] The program may be for implementing a part of the functions to be performed by the computer 900. For example, the program may perform functions in combination with other programs already stored in the auxiliary storage device 903, or in combination with other programs implemented in other devices. In other embodiments, the computer may be equipped with a custom LSI (Large Scale Integrated Circuit) such as a PLD (Programmable Logic Device) in addition to or instead of the above configuration. Examples of PLDs include PAL (Programmable Array Logic), GAL (Generic Array Logic), CPLD (Complex Programmable Logic Device), FPGA (Field Programmable Gate Array), etc. In this case, some or all of the functions implemented by the processor may be implemented by the integrated circuit.

[0100] Examples of auxiliary storage devices 903 include HDDs (Hard Disk Drives), SSDs (Solid State Drives), magnetic disks, magneto-optical disks, CD-ROMs (Compact Disc Read Only Memory), DVD-ROMs (Digital Versatile Disc Read Only Memory), and semiconductor memory. The auxiliary storage device 903 may be an internal medium directly connected to the bus of the computer 900, or it may be an external medium (external storage device 910) connected to the computer 900 via an interface 904 or a communication line. Furthermore, if this program is distributed to the computer 900 via a communication line, the computer 900 that receives the distribution may expand the program into the main memory 902 and execute the above processing. In at least one embodiment, the auxiliary storage device 903 is a tangible storage medium that is not temporary.

[0101] <Note> The above-described embodiment can be understood, for example, as follows.

[0102] (1) According to the first embodiment, the gas turbine control device 20 controls the fuel flow rate G into the combustor 12 based on measurement data relating to the fuel supply system 40 that supplies fuel to the combustor 12 of the gas turbine 10. ｆ A fuel flow rate calculation unit 201 calculates the air flow rate G of the intake air of the compressor 11 of the gas turbine 10 based on measurement data related to the compressor 11 of the gas turbine 10. ａ The airflow rate calculation unit 202 calculates the airflow rate T, and the ambient temperature T measured upstream of the intake cooling device 17 capable of cooling the intake air of the compressor 11 is also calculated. ０ and atmospheric relative humidity RH ０ And the intake air temperature T of the compressor 11 measured downstream of the intake air cooling device 17. １Ｃ Based on this, the intake relative humidity RH of the compressor 11 ｃ A compressor intake humidity estimation unit 203 estimates the fuel flow rate G ｆ And, airflow rate G ａ And, intake relative humidity RH ｃThe system includes a turbine inlet temperature calculation unit 206 that calculates the turbine inlet temperature T1T based on a physical model equation relating to the thermal energy balance of the combustor 12, and a fuel distribution ratio calculation unit 207 that calculates the fuel distribution ratio for each of the fuel supply systems 40 connected to the combustor 12 based on the turbine inlet temperature T1T.

[0103] In this way, the gas turbine control device 20 can estimate the humidity of the air downstream of the intake air cooling device 17, i.e., the intake air of the compressor 11 (intake humidity), without installing a humidity sensor downstream of the intake air cooling device 17. As a result, the turbine inlet temperature T1T can be calculated accurately using the estimated intake humidity of the compressor 11, making it possible to perform appropriate fuel distribution ratio control based on the turbine inlet temperature T1T. Furthermore, since the change in intake humidity caused by switching the intake air cooling device 17 ON or OFF can be reflected in the fuel distribution ratio without delay, the decrease in the efficiency of the gas turbine 10 can be suppressed.

[0104] (2) According to the second embodiment, in the gas turbine control device 20 according to the first embodiment, the compressor intake humidity estimation unit 203 determines the ambient temperature T ０ and atmospheric relative humidity RH ０ Based on this, the wet-bulb temperature of the atmosphere is calculated, and the wet-bulb temperature of the atmosphere and the intake air temperature T of the compressor 11 are used. １Ｃ Based on this, the intake relative humidity RH of the compressor 11 ｃ We estimate this.

[0105] In this way, the gas turbine control device 20 utilizes the fact that the wet-bulb temperature does not change before and after the intake air cooling device 17, and uses the existing ambient temperature sensor 25p, humidity sensor 25q, and compressor inlet temperature sensor 25r to accurately determine the intake relative humidity RH of the compressor 11. ｃ It is possible to estimate this.

[0106] (3) According to the third embodiment, in the gas turbine control device 20 according to the second embodiment, the compressor intake humidity estimation unit 203 estimates the atmospheric temperature T, which is the dry bulb temperature, based on reference data representing the relationship between the dry bulb temperature, wet bulb temperature, and relative humidity. ０ And, atmospheric relative humidity RH ０The wet-bulb temperature of the atmosphere corresponding to the combination is calculated, and based on the reference data, the estimated wet-bulb temperature of the atmosphere and the intake air temperature T (dry-bulb temperature) are used. １Ｃ Intake relative humidity RH corresponding to the combination ｃ We estimate this.

[0107] In this way, the gas turbine control device 20 determines the intake relative humidity RH based on pre-prepared reference data. ｃ This can be easily estimated.

[0108] (4) According to the fourth embodiment, in the gas turbine control device 20 according to the second embodiment, the compressor intake humidity estimation unit 203 estimates the atmospheric temperature T based on a relational expression representing the relationship between dry bulb temperature, wet bulb temperature, water vapor pressure, and saturated water vapor pressure at the wet bulb temperature, and an approximate formula for saturated water vapor pressure. ０ and atmospheric relative humidity RH ０ The corresponding wet-bulb temperature of the atmosphere is calculated, and an approximate formula is used, along with the intake air temperature T. １Ｃ Based on this, the saturated water vapor pressure es2 of the intake air of the compressor 11 is calculated, and the relationship is obtained using the wet-bulb temperature of the atmosphere, the saturated water vapor pressure es2 of the intake air of the compressor 11, and the intake air temperature T １Ｃ Based on this, the water vapor pressure e2 of the intake air of the compressor 11 is calculated, and based on the water vapor pressure e2 and saturated water vapor pressure es2 of the intake air of the compressor 11, the intake relative humidity RH ｃ We estimate this.

[0109] In this way, the gas turbine control device 20 determines the intake relative humidity RH of the compressor 11 based on the relational equation and the approximation equation. ｃ It can estimate with high accuracy. Furthermore, since it does not require reference data, the storage capacity can be reduced.

[0110] (5) According to the fifth aspect, the gas turbine control method controls the fuel flow rate G into the combustor 12 based on measurement data relating to the fuel supply system 40 that supplies fuel to the combustor 12 of the gas turbine 10. ｆ The steps include calculating the airflow rate G of the intake air of the compressor 11 of the gas turbine 10 based on measurement data related to the compressor 11 of the gas turbine 10. ａThe steps include calculating the ambient temperature T measured upstream of the intake air cooling device 17 capable of cooling the intake air of the compressor 11. ０ and atmospheric relative humidity RH ０ And the intake air temperature T of the compressor 11 measured downstream of the intake air cooling device 17. １Ｃ Based on this, the intake relative humidity RH of the compressor 11 ｃ The steps include estimating the fuel flow rate G ｆ And, airflow rate G ａ And, intake relative humidity RH ｃ The method includes the steps of calculating the turbine inlet temperature T1T based on a physical model equation relating to the thermal energy balance of the combustor 12, and calculating the fuel distribution ratio of each of the fuel supply systems 40 connected to the combustor 12 based on the turbine inlet temperature T1T.

[0111] (6) According to the sixth aspect, the program determines the fuel flow rate G into the combustor 12 based on measurement data relating to the fuel supply system 40 that supplies fuel to the combustor 12 of the gas turbine 10. ｆ The steps include calculating the airflow rate G of the intake air of the compressor 11 of the gas turbine 10 based on measurement data related to the compressor 11 of the gas turbine 10. ａ The steps include calculating the ambient temperature T measured upstream of the intake air cooling device 17 capable of cooling the intake air of the compressor 11. ０ and atmospheric relative humidity RH ０ And the intake air temperature T of the compressor 11 measured downstream of the intake air cooling device 17. １Ｃ Based on this, the intake relative humidity RH of the compressor 11 ｃ The steps include estimating the fuel flow rate G ｆ And, airflow rate G ａ And, intake relative humidity RH ｃ The gas turbine control device is instructed to perform the following steps: calculate the turbine inlet temperature T1T based on a physical model equation relating to the thermal energy balance of the combustor 12, and calculate the fuel distribution ratio for each of the fuel supply systems 40 connected to the combustor 12 based on the turbine inlet temperature T1T.

[0112] According to the above embodiment, even when an intake air cooling device is installed, the intake air humidity downstream of the intake air cooling device is estimated, and the fuel distribution ratio is controlled by the turbine inlet temperature calculated using this estimate.

[0113] 100 Plant 10 Gas turbine 11 Compressor 12 Combustor 13 Turbine 17 Intake air cooling system 20 Gas turbine control device 201 Fuel flow rate calculation unit 202 Air flow rate calculation unit 203 Compressor intake air humidity estimation unit 204 Heat balance calculation unit 205 Correction processing unit 206 Turbine inlet temperature calculation unit 207 Fuel distribution ratio calculation unit 208 Valve opening degree calculation unit 25a Flow control valve front pressure sensor 25b Flow control valve rear pressure sensor 25c Fuel temperature sensor 25d Power meter sensor 25e Index differential pressure sensor 25f Compressor inlet pressure sensor 25h Compressor outlet pressure sensor 25i Compressor outlet temperature sensor 25j Combustor cabin temperature sensor 25k Exhaust gas pressure sensor 25l Exhaust gas temperature sensor 25p Atmospheric temperature sensor 25q Humidity sensor 25r Compressor inlet temperature sensor 30 Fuel supply device 40 Fuel supply system 41 Flow control valve 42 Nozzle 43 Manifold piping 50 Generator

Claims

1. A gas turbine control device comprising: a fuel flow rate calculation unit that calculates the fuel flow rate into a combustor based on measurement data relating to a fuel supply system that supplies fuel to a combustor of a gas turbine; an air flow rate calculation unit that calculates the air flow rate of the intake air of a compressor based on measurement data relating to the compressor of the gas turbine; a compressor intake air humidity estimation unit that estimates the intake air relative humidity of a compressor based on atmospheric temperature and atmospheric relative humidity measured upstream of an intake air cooling device capable of cooling the intake air of the compressor, and the intake air temperature of the compressor measured downstream of the intake air cooling device; a turbine inlet temperature calculation unit that calculates the turbine inlet temperature based on the fuel flow rate, the air flow rate, the intake air relative humidity, and a physical model equation relating to the thermal energy balance of the combustor; and a fuel distribution ratio calculation unit that calculates the fuel distribution ratio of each of the fuel supply systems connected to the combustor based on the turbine inlet temperature.

2. The gas turbine control device according to claim 1, wherein the compressor intake humidity estimation unit calculates the wet-bulb temperature of the atmosphere based on the atmospheric temperature and the relative humidity of the atmosphere, and estimates the intake relative humidity of the compressor based on the wet-bulb temperature of the atmosphere and the intake temperature of the compressor.

3. The compressor intake humidity estimation unit calculates the wet-bulb temperature of the atmosphere corresponding to a combination of the dry-bulb temperature of the atmosphere and the relative humidity of the atmosphere, based on reference data representing the relationship between the dry-bulb temperature, the wet-bulb temperature, and the relative humidity of the atmosphere, and estimates the intake relative humidity corresponding to a combination of the estimated wet-bulb temperature of the atmosphere and the intake temperature, which is the dry-bulb temperature, based on the reference data, the gas turbine control device according to claim 2.

4. The compressor intake humidity estimation unit calculates the wet-bulb temperature of the atmosphere corresponding to the atmospheric temperature and atmospheric relative humidity based on a relational expression representing the relationship between dry-bulb temperature, wet-bulb temperature, water vapor pressure, and saturated water vapor pressure at the wet-bulb temperature, and an approximation formula for the saturated water vapor pressure; calculates the saturated water vapor pressure of the intake air of the compressor based on the approximation formula and the intake air temperature; calculates the water vapor pressure of the intake air of the compressor based on the relational expression, the wet-bulb temperature of the atmosphere, the saturated water vapor pressure of the intake air of the compressor, and the intake air temperature; and estimates the intake relative humidity based on the water vapor pressure and saturated water vapor pressure of the intake air of the compressor, as described in claim 2.

5. A gas turbine control method comprising: a step of calculating the fuel flow rate into the combustor based on measurement data relating to a fuel supply system that supplies fuel to the combustor of a gas turbine; a step of calculating the air flow rate of the intake air of the compressor based on measurement data relating to the compressor of the gas turbine; a step of estimating the intake air relative humidity of the compressor based on the ambient temperature and ambient relative humidity measured upstream of an intake air cooling device capable of cooling the intake air of the compressor, and the intake air temperature of the compressor measured downstream of the intake air cooling device; a step of calculating the turbine inlet temperature based on the fuel flow rate, the air flow rate, the intake air relative humidity, and a physical model equation relating to the thermal energy balance of the combustor; and a step of calculating the fuel distribution ratio of each of the fuel supply systems connected to the combustor based on the turbine inlet temperature.

6. A program that causes a gas turbine control device to perform the following steps:

6. Calculate the fuel flow rate into the combustor based on measurement data relating to a fuel supply system that supplies fuel to the combustor of a gas turbine; 6. Calculate the airflow rate of the intake air of the compressor based on measurement data relating to the compressor of the gas turbine; 7. Estimate the intake air relative humidity of the compressor based on atmospheric temperature and atmospheric relative humidity measured upstream of an intake air cooling device capable of cooling the intake air of the compressor, and the intake air temperature of the compressor measured downstream of the intake air cooling device; 8. Calculate the turbine inlet temperature based on the fuel flow rate, the airflow rate, the intake air relative humidity, and a physical model equation relating to the thermal energy balance of the combustor; and 9. Calculate the fuel distribution ratio for each of the fuel supply systems connected to the combustor based on the turbine inlet temperature.

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