Gas turbine control device, gas turbine control method and non-volatile storage medium

Abstract

A gas turbine control device (20) comprising: a fuel flow calculation unit (201) configured to calculate a flow per unit time of fuel supplied to a gas turbine (10) based on a measured value of the gas turbine (10); an air flow calculation unit (202) configured to calculate a flow rate per unit time of air supplied to the gas turbine (10) based on a measured value of the gas turbine (10); a turbine inlet temperature calculation unit (203) configured to calculate a turbine inlet temperature by inputting into a physical model formula expressing a ratio of heat energy balance with respect to a combustion chamber (12) of the gas turbine (10), the flow rate per unit time of the fuel, the flow rate per unit time of the air, a fuel temperature, and an air temperature at a casing (132) of the gas turbine (10); and a fuel distribution ratio calculation unit (205) configured to calculate a fuel distribution ratio for each of a plurality of fuel supply systems (50a, 50b, 50c) connected to the combustor (12) based on the turbine inlet temperature, wherein the turbine inlet temperature calculation unit (203) calculates the turbine inlet temperature by using a specific enthalpy that is changed in accordance with humidity.

Description

Technical area

[0001] The present invention relates to a gas turbine control device, a gas turbine control method and a non-volatile storage medium. State of the art

[0002] In consideration of combustion efficiency and combustion stability, a gas turbine is required to supply fuel to a combustor, which separates the gas turbine into multiple systems. In a related method for controlling the turbine, a turbine inlet temperature is evaluated from the heat balance data acquired at the time of design, and a ratio of fuel distribution to each of the fuel supply systems (fuel distribution ratio) is determined based on the turbine inlet temperature. Furthermore, there may be a risk of causing combustion vibration depending on a relationship between the fuel distribution ratio and the turbine inlet temperature. Combustion vibration damages the combustion chamber, etc., and thus, it is necessary to suppress the vibration.

[0003] Patent Document 1 discloses a method for calculating a turbine inlet temperature based on a generator output and a fuel command value. However, such a turbine inlet temperature calculation method risks failing to accurately calculate an output value of the gas turbine based on a generator output, particularly at the time of transient response when the output fluctuates. As a result, accuracy deteriorates. Further, in the technique in PTL 1, a gas turbine output value calculated based on a fuel control signal command value is corrected, and a turbine inlet temperature is calculated using the corrected value. However, the thus corrected value needs to be appropriately adjusted to correspond to a gas turbine that is a calculation target.

[0004] Patent Document 2 discloses a system for controlling a gas turbine engine having a combustion chamber that generates combustion, so that the resulting combustion gas rotates a turbine connected to the compressor and a load such as a generator to drive the compressor and generator. In the system, the oxygen concentration of the resulting combustion gas is detected, and the adiabatic flame temperature is calculated based on at least the detected oxygen concentration, so that the combustion mode is switched between premixed combustion and diffusion combustion by the calculated temperature.In this way, the system can control the fuel supply through a multi-venturi mixer using gas fuel with a non-constant composition, while avoiding flameout and achieving stable operation in response to load demand and excellent emissions performance. Furthermore, the system can control the fuel supply without the need to detect the multi-venturi mixer's throat pressure, even if it is affected by the mixer's outlet pressure and similar factors. List of citationsPatent document Patent document 1: JP 2015 - 161 176 A Patent document 2: US 2004 / 0 011 050 A1 Brief description of the inventionTechnical problem

[0005] In view of the above, the object of the present invention is to provide a gas turbine control apparatus, a gas turbine control method and a non-volatile storage medium that can solve the problems described above. Solution to the problem

[0006] The present invention provides a gas turbine control apparatus according to independent claims 1 and 2, and a gas turbine control method according to independent claims 9 and 10. Advantageous modifications can be found in dependent claims 3 to 8. Advantageous effect of the invention

[0007] According to the present invention, the gas turbine control device is capable of calculating the turbine inlet temperature with higher accuracy even at the time of transient operation, when the gas turbine output suddenly fluctuates. Thus, the gas turbine control device is capable of calculating a fuel distribution ratio for each of the fuel supply systems in accordance with the turbine inlet temperature and is capable of achieving stable combustion, suppressing the generation of combustion oscillation of the gas turbine even at the time of transient operation. Brief description of the drawings Fig. 1 is a system diagram of a gas turbine power plant. Fig. 2 is a functional block diagram of a gas turbine control apparatus according to a first embodiment. Fig. 3 is a flowchart of the gas turbine control device. Fig. 4 is a functional block diagram of a gas turbine control apparatus according to a second embodiment. Description of embodimentsFirst embodiment

[0008] Hereinafter, a gas turbine control apparatus according to a first embodiment of the present invention and a gas turbine power plant having the apparatus will be described with reference to the drawings.

[0009] Fig. 1 is a system diagram of the gas turbine power plant according to the present embodiment.

[0010] As in Fig. As illustrated in FIG. 1, the gas turbine power plant 100 in the present embodiment includes a gas turbine 10, a generator 16 that generates electricity by being driven by the gas turbine 10, a gas turbine control device 20 that controls the gas turbine 10, and a supply device 40 that supplies fuel. The gas turbine 10 and the generator 16 are connected by a rotor. Note that the gas turbine power plant 100 may be a gas turbine combined cycle (GTCC) power plant obtained by further including a steam turbine and the rotor connected to the steam turbine.

[0011] The gas turbine 10 comprises a compressor 11, a fuel supply system 50, a combustion chamber 12 and a turbine 13.

[0012] The compressor 11 generates highly compressed air by compressing outside air. Specifically, the compressor 11 includes a compressor rotor 111 rotating around a major axis and a compressor casing 112 covering the compressor rotor 111 from an outer peripheral side. The turbine 13 includes a turbine rotor 131 rotating around the major axis and a turbine casing 132 covering the turbine rotor 131 from an outer peripheral side.

[0013] The compressor rotor 111 and the turbine rotor 131 are integrally connected to each other along the main axis. The combustion chamber 12 generates high-temperature and high-pressure combustion gas by burning fuel from the fuel supply system 50 in the compressed air generated by the compressor 11. The combustion chamber 12 includes a combustion chamber inner cylinder 121 and a combustion chamber casing 17 covering the combustion chamber inner cylinder 121. Furthermore, the compressor casing 112, the combustion chamber casing 17, and the turbine casing 132 are connected to each other.

[0014] The generator 16 is connected to one end of the compressor rotor 111. The generator 16 is driven by rotation of the compressor rotor 111 and thus generates electricity.

[0015] The fuel supply system 50 regulates a pressure and flow of fuel supplied from the supply device 40. The fuel supply system 50 includes a control valve 18, a nozzle 123, and a manifold 124. The control valve 18 is a pressure control valve, a fuel flow control valve, or the like.

[0016] It should be noted that Fig. 1 illustrates a mode in which the gas turbine 10 comprises fuel supply systems 50a, 50b, 50c, .... Further, Fig. 1 shows a mode in which a first control valve 18a, a second control valve 18b, and a third control valve 18c, which control a fuel flow and a pressure for the fuel supply systems, are provided as the control valve 18, respectively. Fig. 1 illustrates only three systems, including fuel supply systems 50a, 50b, and 50c. However, the number of fuel supply systems is not limited to three. For example, the gas turbine 10 may include a top-hat fuel supply system that supplies fuel to an upper top-hat portion of the combustor 12, a pilot fuel supply system that supplies fuel to a central portion of the combustor inner cylinder 121, and a main fuel supply system that supplies fuel to a portion surrounding the pilot fuel supply system in the combustor inner cylinder 121. Further, Fig. 1 only one combustion chamber 12. However, a plurality of, for example, sixteen combustion chambers 12 are provided, and fuel is supplied to the combustion chambers 12 from the corresponding fuel supply systems 50a, 50b, 50c, .... For example, in the gas turbine power plant 100, sixteen fuel supply systems 50 are each connected to the corresponding combustion chambers 12.

[0017] The gas turbine 10 is provided with several measuring instruments that measure state variables of the gas turbine 10. For example, the gas turbine 10 is provided with a fuel flow sensor 20a that measures a fuel flow to the fuel supply system 50, a nozzle flow sensor 20b that measures a through flow (nozzle through flow) at the nozzle 123, an exhaust flow sensor 20c that measures an exhaust flow, a manifold pressure sensor 20d that measures the pressure P inin the manifold 124, a temperature sensor 20e which measures compressor inlet temperature, an index pressure difference measuring device 20f which measures a compressor index pressure difference P index measures, and the like. It should be noted that the compressor index pressure difference P index is a pressure difference between a pressure at the compressor suction port housing portion of the compressor 11 and a pressure near a blade within the compressor, and is a value that is a flow index of air supplied through the compressor. The fuel flow rate, the nozzle flow rate or the fuel valve flow rate, the exhaust flow rate, and the manifold pressure are state variables of the gas turbine 10. Furthermore, the gas turbine 10 is also provided with other measuring instruments. For example, the gas turbine 10 is provided with measuring instruments that measure a pressure P out on the combustion chamber housing 17, a fuel temperature T f, a housing air temperature T cs , and an exhaust gas temperature T 2T These are state variables of gas turbine 10.

[0018] Note that a turbine inlet temperature described below indicates a temperature at an inlet of the turbine 13 of combustion gas having a high temperature and discharged from the combustion chamber 12. The compressor 11 is provided with an intake guide vane (IGV) 14. The IGV 14 regulates an amount of air flowing into the compressor 11.

[0019] Fig. 2 is a functional block diagram of the gas turbine control apparatus according to a first embodiment. The gas turbine control device 20 is a computer, and may have a hardware configuration including a storage unit such as a read-only memory (ROM), a random access memory (RAM), and a hard disk drive (HDD), a central processing unit (CPU), a communication interface, and the like.

[0020] Based on a user operation, the CPU of the gas turbine control device 20 executes a stored control program. Thus, the gas turbine control device 20 includes a fuel flow calculation unit 201, an air flow calculation unit 202, a turbine inlet temperature calculation unit 203, a correction unit 204, a fuel distribution ratio calculation unit 205, and a valve opening calculation unit 206. Note that the fuel distribution ratio calculation unit 205 includes a first fuel distribution calculation unit 205a, a second fuel distribution calculation unit 205b, a third fuel distribution calculation unit 205c, etc., which calculate a fuel distribution ratio for the respective fuel supply systems.Further, the valve opening calculation unit 206 includes a first valve opening calculation unit 206a, a second valve opening calculation unit 206b, a third valve opening calculation unit 206c, etc., which calculate an opening amount for the respective fuel supply systems.

[0021] The fuel flow calculation unit 201 calculates, based on a measured value of the gas turbine 10, a flow per unit time of fuel supplied to the gas turbine 10.

[0022] The air flow calculation unit 202 calculates, based on a measured value of the gas turbine 10, a flow rate per unit time of air supplied to the gas turbine 10.

[0023] The turbine inlet temperature calculation unit 203 calculates a turbine inlet temperature by using a physical model formula that expresses a ratio of inlet and outlet heat energy with respect to the combustor 12 of the gas turbine 10. The physical model formula uses a fuel flow rate per unit time, an air flow rate per unit time, a fuel temperature, and an air temperature at the casing of the gas turbine 10.

[0024] The correction unit 204 calculates a correction factor for correcting the turbine inlet temperature based on a ratio of the turbine inlet temperature and the detected exhaust gas temperature at the gas turbine 10, and corrects the turbine inlet temperature with the correction factor.

[0025] Based on the corrected turbine inlet temperature, the fuel distribution ratio calculation unit 205 (205a, 205b, 205c, ...) calculates a fuel distribution ratio for each of the fuel supply systems connected to a plurality of combustors 12, respectively.

[0026] Based on the fuel distribution ratio for each of the fuel supply systems, the valve opening calculation unit 206 (206a, 206b, 206c, ...) calculates an opening amount for each of the fuel supply systems.

[0027] In reality, the gas turbine control device 20 has functions in addition to the functional units shown in Fig. 2. However, to simplify the explanation, only the functional units are described that are shown in Fig. 2 are illustrated.

[0028] Fig. 3 is a flowchart of the gas turbine control apparatus according to the present embodiment.

[0029] First, the fuel flow calculation unit 201 detects the pressure P in at the manifold 124, the pressure P out on the combustion chamber housing 17 and the fuel temperature T f . The pressure P in at the manifold 124 is measured by the manifold pressure sensor 20d. Similarly, an outlet pressure P out and a fuel temperature T f measured at the fuel nozzle by sensors. The fuel flow calculation unit 201 replaces the pressure P in at the manifold 124, the pressure P out on the combustion chamber housing 17 and the fuel temperature T f in a fuel flow calculation formula (1), and calculates a total flow G f per unit time of the fuel supplied to the combustion chambers 12 of the gas turbine 10 (step S101). [Mathematical Formula 1] Gf=f(Pin,Pout,Tf)

[0030] Furthermore, the air flow calculation unit 202 detects the compressor index pressure difference P index from the index pressure difference measuring device 20f, and detects a compressor inlet temperature T 1c from the temperature sensor 20e. By measuring the index pressure difference P index , a flow rate flowing through the compressor 11 can be calculated. The air flow calculation unit 202 replaces the index pressure difference P index and the compressor inlet temperature T 1c in an air flow calculation formula (2), and calculates a flow rate Ga per unit time of the air flowing in the compressor 11 (step S102). [Mathematical Formula 2] Ga=f(Pindex,T1C)

[0031] The turbine inlet temperature calculation unit 203 detects the fuel flow G f, which is calculated by the fuel flow calculation unit 201. The turbine inlet temperature calculation unit 203 detects the air flow G a , which is calculated by the air flow calculation unit 202. The turbine inlet temperature calculation unit 203 further detects the fuel temperature T f . The turbine inlet temperature calculation unit 203 further detects the casing air temperature T cs on the combustion chamber housing 17. The air temperature T cs at the combustion chamber housing is measured by a sensor. The turbine inlet temperature calculation unit 203 replaces the fuel flow G f , the air flow G a , the fuel temperature T f , and the housing air temperature T cs on the combustion chamber casing 17, which are recorded in a physical deviation model formula in the periphery of the combustion chamber (3), and calculates a turbine inlet temperature T 1T(Step S103). The turbine inlet temperature calculation unit 203 outputs the calculated turbine inlet temperature T 1T to the correction unit 204. It should be noted that the physical deviation model formula with formula (3) is obtained by transforming a model formula that indicates that the heat energy flowing into the combustion chamber 12 is equal to the heat energy flowing out of the combustion chamber 12, so that the turbine inlet temperature T 1Tincluded in the model formula is placed on the left side, and other elements are placed on the right side. The heat energy flowing into the combustion chamber 12 in the physical deviation model formula is represented by a sum of heat energy of fuel, heat energy of air, and heat generation energy of combustion gas. Further, the heat energy flowing out of the combustion chamber 12 is represented by the heat energy at the inlet of the turbine 13. Here, the heat energy of air varies in accordance with a specific enthalpy, taking into account an influence of the humidity of the steam contained in the air flowing through the combustor casing 17.Therefore, the turbine inlet temperature calculation unit 203 can detect the humidity of the air flowing in the combustor casing 17 with a sensor, calculate a specific enthalpy based on the humidity, and calculate the heat energy of the air by using the specific enthalpy. [Mathematical Formula 3] T1T=f(Gf,Ga,Tf,TCS)

[0032] Here, in reality, the air flowing in the compressor 11 is extracted at a stage before flowing in the combustion chamber 12. Thus, the air flow calculation unit 202 can calculate the air flow G a per unit time obtained by subtracting a flow rate per unit time of the exhaust air, and the turbine inlet temperature calculation unit 203 can calculate the turbine inlet temperature T 1T with the formula (3) described above using the air flow G a, which is obtained by subtracting the exhaust air flow. The exhaust air flow is uniformly increased in accordance with the increase in the output value of the gas turbine 10 and the value of the turbine inlet temperature T 1T The air flow calculation unit 202 can calculate the exhaust air flow by using the interpolation calculation with a data table indicating exhaust air flow rates, the output values ​​of the gas turbine 10 and values ​​of the turbine inlet temperature T 1T and a predetermined calculation formula. It should be noted that if the exhaust air flow is calculated based on the value of the turbine inlet temperature T 1T is calculated, the air flow calculation unit 202 calculates the value of the turbine inlet temperature T 1T that was previously calculated.

[0033] Here, immediately after the gas turbine 10 is activated, the above-described exhaust air flow also varies based on a change in the shape of the compressor 11, the pipe, and the like due to thermal expansion and the like. Therefore, the air flow calculation unit 202 can calculate a highly accurate exhaust air flow after activation by using a correction formula for an exhaust air flow per unit time in accordance with an elapsed time after the activation of the gas turbine 10. Further, the turbine inlet temperature calculation unit 203 can calculate the turbine inlet temperature T 1T by using the air flow G a which was obtained by subtracting the very precise exhaust air flow and thus corrected.

[0034] The correction unit 24 can further determine the turbine inlet temperature T 1T based on the exhaust gas temperature T 2TMore specifically, the gas turbine control device 20 stores in advance information indicating a ratio of the nominal exhaust gas temperature T4 at the time of nominal operation of the gas turbine 10 and a nominal turbine inlet temperature T5 at that time. The correction unit 24 acquires the information on the ratio of the nominal exhaust gas temperature T4 and the nominal turbine inlet temperature T5. The correction unit 24 calculates a correction value for the turbine inlet temperature T 1T based on the relationship between the nominal exhaust gas temperature T4 and the nominal turbine inlet temperature T5. For example, the correction unit 24 calculates a correction value for the turbine inlet temperature T 1T . The correction value satisfies the condition that a value Tx obtained by subtracting the exhaust gas temperature T 2Tobtained from the nominal exhaust gas temperature T4, corresponds to a value Ty obtained by subtracting the turbine inlet temperature T 1T from the nominal turbine inlet temperature T5 or is equal to a predetermined constant multiplication a. It should be noted that the ratio of a nominal exhaust gas temperature T4 and a nominal turbine inlet temperature T5 at this time may vary due to a pressure of the combustor housing 17. In this case, the correction unit 24 detects a pressure at the combustor housing 17 with a sensor using the ratio of the nominal exhaust gas temperature T4 and the nominal turbine inlet temperature T5 at this time, which have been corrected based on the pressure value. In this way, the correction value for the turbine inlet temperature T 1T be calculated as described above.

[0035] Here the exhaust gas temperature T 2Ta measured value with slow reactivity with respect to a change in the output of the gas turbine 10. Although the exhaust gas temperature T 2T slow reactivity, it is a very accurate value. The exhaust gas temperature and the turbine inlet temperature have a strong correlation. Therefore, the correction unit 24 corrects the turbine inlet temperature T 1T , which has the fast reactivity obtained in step S103 by using the very accurate exhaust gas temperature T 2T . More specifically, the correction unit 24 calculates an estimated value of the exhaust gas temperature T 4T based on the turbine inlet temperature T 1T . The estimated value of the exhaust gas temperature T 4T is an estimated value of the exhaust gas temperature in a case of assuming a temperature at the inlet of the turbine 13 as the turbine inlet temperature T 1T .

[0036] The collector unit 24 detects the turbine inlet temperature T 1Tand gives the turbine inlet temperature T 1T into a predetermined calculation formula that has been set in advance and calculates an assumed estimated value of the exhaust gas temperature T 3T . This calculation formula is a formula for converting the turbine inlet temperature T 1T into an exhaust gas temperature.

[0037] The correction unit 24 subjects the assumed estimated value of the exhaust gas temperature T 3T a process of delaying a change of a value for each time and calculates the estimated value of the exhaust gas temperature T 4T .

[0038] The correction unit 24 calculates a correction factor X4 which determines the turbine inlet temperature T 1T corrected based on a ratio of the exhaust gas temperature T 2T and the estimated value of the exhaust gas temperature T 4T , which is derived from the turbine inlet temperature T 1Twas calculated. In the present embodiment, for example, the correction factor X4 is a value obtained by summing a setting ratio X2 and a previous setting ratio X3. The setting ratio X2 is calculated by multiplying a setting coefficient a by a ratio X2 obtained by dividing the exhaust gas temperature T 2T by the estimated value of the exhaust gas temperature T 4T was obtained. The previous adjustment ratio X3 is calculated by multiplying 1-a by a previous correction factor X4', which is the correction factor X4 calculated previously. Further, the correction unit 24 calculates a turbine inlet temperature after correction T 1T ' by multiplying the turbine inlet temperature T 1T with the correction factor X4 (step S104). The correction factor X4 is a ratio of the exhaust gas temperature T 2T to the estimated value of the exhaust gas temperature T 4T, and thus the turbine inlet temperature after correction T 1T ' a value that provides high calculation accuracy in addition to the fast reactivity by multiplying the turbine inlet temperature T 1T with the correction factor X4. The gas turbine control device 20 determines a temperature of the combustion gas based on the turbine inlet temperature after correction T 1T ', which has fast reactivity and high calculation accuracy. Therefore, the gas turbine control device 20 is able to adjust the turbine inlet temperature after correction T 1T ' which has fast reactivity and high calculation accuracy. The correction unit 204 outputs the turbine inlet temperature after correction T 1T ' to the fuel distribution ratio calculation unit 205.

[0039] The fuel distribution ratio calculation unit 205 calculates a fuel distribution ratio for each of the fuel supply systems 50a, 50b, and 50c corresponding to the first fuel distribution ratio calculation unit 205a, the second fuel distribution ratio calculation unit 205b, and the third fuel distribution ratio calculation unit 205c, respectively (step S105). The sum of each fuel distribution ratio is 100%. A fuel distribution ratio for each of the fuel supply systems 50a, 50b, and 50c corresponding to the first fuel distribution ratio calculation unit 205a, the second fuel distribution ratio calculation unit 205b, and the third fuel distribution ratio calculation unit 205c, respectively, is calculated using a ratio formula of the turbine inlet temperature after correction T 1T' and a fuel distribution ratio. It should be noted that the fuel supply systems 50a, 50b and 50c each have a different corresponding ratio of the turbine inlet temperature after correction T 1T' and a fuel distribution ratio. The first fuel distribution ratio calculation unit 205a, the second fuel distribution ratio calculation unit 205b, and the third fuel distribution ratio calculation unit 205c output calculated opening amounts to the valve opening calculation unit 206. That is, the first fuel distribution ratio calculation unit 205a outputs a calculated fuel distribution ratio Da to the first valve opening calculation unit 206a. The second fuel distribution ratio calculation unit 205b outputs a calculated fuel distribution ratio Db to the second valve opening calculation unit 206b. The third fuel distribution ratio calculation unit 205c outputs a calculated fuel distribution ratio Dc to the third valve opening calculation unit 206c.

[0040] The first valve opening calculation unit 206a, the second valve opening calculation unit 206b, and the third valve opening calculation unit 206c, which respectively correspond to the fuel supply systems 50a, 50b, and 50c, substitute fuel distribution ratios of the respective fuel supply systems and a fuel control command value CSO into an opening amount calculation formula, and calculate opening degrees of the first control valve 18a, the second control valve 18b, and the third control valve 18c of the respective fuel supply systems (step S106). That is, the first valve opening calculation unit 206a calculates an opening amount Oa of the first control valve 18a, the second valve opening calculation unit 206b calculates an opening amount Ob of the second control valve 18b, and the third valve opening calculation unit 206c calculates an opening amount Oc of the third pressure control valve 18c.The first valve opening calculation unit 206a outputs the calculated opening amount Oa to the first control valve 18a, the second valve opening calculation unit 206b outputs the calculated opening amount Ob to the second control valve 18b, and the third valve opening calculation unit 206c outputs the calculated opening amount Oc to the third control valve 18c. The first control valve 18a, the second control valve 18b, and the third control valve 18c are controlled to have the intake opening amounts, respectively.

[0041] With the method described above, an output value of the gas turbine 10 is not used to calculate the turbine inlet temperature. Instead, the turbine inlet temperature is calculated by replacing a measured value with a faster transient response in the physical deviation model formula in the periphery of the combustion chamber. Therefore, an appropriate relationship between the turbine inlet temperature and the fuel distribution ratio can be maintained even at the time of transient response when the output of the gas turbine 10 suddenly changes. Thus, stable combustion can be achieved without causing combustion oscillation. Second embodiment

[0042] Fig.4 is a functional block diagram of a gas turbine control device according to a second embodiment. The gas turbine control device 20 can calculate a casing air temperature Tcs' based on a measured value. In the second embodiment, the casing air temperature Tcs' is calculated by substituting the values ​​of a compressor inlet pressure P 1C and a compressor outlet pressure P 2C which is used to calculate the compressor index pressure difference P index , the compressor inlet temperature T1C, and a casing air temperature measurement T CS_MEA be used in a housing air temperature calculation formula. The housing air temperature measurement T CS_MEA is generally measured together with the time delay. Thus, the measured value T CS_MEAnot used as is, and the calculation is performed using the calculation formula described above to improve reactivity. A casing temperature calculation unit 207 replaces the compressor inlet pressure P 1C , the compressor outlet pressure P 2C , the compressor inlet temperature T 1c , and the housing air temperature measurement T CS_MEA in a formula (10), which is a physical model. This allows the enclosure air temperature Tcs' to be calculated more quickly with a fast reactivity. [Mathematical Formula 4] TCS'=f(P1C,P2C,T1C,TCS_MEA)

[0043] The gas turbine control device 20 described above internally includes a computer system. Furthermore, the steps of each process described above are stored in a computer-readable recording medium in the form of a program, and the above-described processes are implemented by the computer reading and executing this program. Here, the computer-readable recording medium refers to a magnetic disk, a magneto-optical disk, a CD-ROM, a DVD-ROM, a semiconductor memory, or the like. This computer program can be distributed to the computer via a communication line, and the computer receiving this distribution can execute the program.

[0044] Furthermore, the program as described above can implement some of the functions described above. In addition, the functions described above can be implemented in combination with a program already stored on the computer system, a so-called differential file (differential program). List of reference symbols 10 gas turbines 20 Gas turbine control device 40 Feeding device 201 Fuel flow calculation unit 202 Air flow calculation unit 203 Turbine inlet temperature calculation unit 204 Correction unit 205 Fuel distribution ratio calculation unit 206 Valve opening calculation unit

Claims

[1] A gas turbine control device (20) comprising: a fuel flow calculation unit (201) configured to calculate a flow per unit time of fuel supplied to a gas turbine (10) based on a measured value of the gas turbine (10); an air flow calculation unit (202) configured to calculate a flow rate per unit time of air supplied to the gas turbine (10) based on a measured value of the gas turbine (10); a turbine inlet temperature calculation unit (203) configured to calculate a turbine inlet temperature by inputting into a physical model formula expressing a ratio of heat energy balance with respect to a combustion chamber (12) of the gas turbine (10), the flow rate per unit time of the fuel, the flow rate per unit time of the air, a fuel temperature, and an air temperature at a casing (132) of the gas turbine (10); and a fuel distribution ratio calculation unit (205) configured to calculate a fuel distribution ratio for each of a plurality of fuel supply systems (50a, 50b, 50c) connected to the combustor (12) based on the turbine inlet temperature, wherein the turbine inlet temperature calculation unit (203) calculates the turbine inlet temperature by using a specific enthalpy that is changed in accordance with humidity. [2] A gas turbine control device (20) comprising: a fuel flow calculation unit (201) configured to calculate a flow per unit time of fuel supplied to a gas turbine (10) based on a measured value of the gas turbine (10); an air flow calculation unit (202) configured to calculate a flow rate per unit time of air supplied to the gas turbine (10) based on a measured value of the gas turbine (10); a turbine inlet temperature calculation unit (203) configured to calculate a turbine inlet temperature by inputting, into a physical model formula expressing a ratio of heat energy balance with respect to a combustion chamber (12) of the gas turbine (10), the flow rate per unit time of the fuel, the flow rate per unit time of the air, a fuel temperature, and an air temperature at a casing (132) of the gas turbine (10); a fuel distribution ratio calculation unit (205) configured to calculate a fuel distribution ratio for each of a plurality of fuel supply systems (50a, 50b, 50c) connected to the combustor (12) based on the turbine inlet temperature; and a correction unit (204) configured to correct the turbine inlet temperature based on a ratio of an exhaust gas temperature at the gas turbine (10) and an exhaust gas temperature at the gas turbine (10) calculated from the turbine inlet temperature, wherein the fuel distribution ratio calculation unit (205) calculates a fuel distribution ratio based on a turbine inlet temperature after correction by the correction unit (204). [3] The gas turbine control device (20) according to claim 2, wherein the correction unit (204) corrects the turbine inlet temperature based on a relationship between a nominal exhaust gas temperature and a nominal turbine inlet temperature. [4] The gas turbine control device (20) according to any one of claims 1 to 3, wherein the air flow calculation unit (202) calculates the flow rate per unit time of the air obtained by subtracting an exhaust gas flow rate per unit time. [5] The gas turbine control device (20) according to any one of claims 1 to 4, wherein the turbine inlet temperature calculation unit (203) inputs the humidity into the physical model formula and calculates the turbine inlet temperature. [6] The gas turbine control device (20) according to any one of claims 1 to 5, wherein the air flow rate calculation unit (202) calculates an exhaust air flow rate per unit time in accordance with an elapsed time after the activation of the gas turbine (10), and calculates the flow rate per unit time of the air obtained by subtracting the exhaust air flow rate. [7] The gas turbine control device (20) according to any one of claims 1 to 6, comprising a casing temperature calculation unit (207) configured to calculate an air temperature at the casing (10) based on a measured value of the gas turbine (10). [8] The gas turbine control device (20) according to any one of claims 1 to 7, wherein the physical model formula comprises a physical deviation model formula. [9] A gas turbine control method comprising: with a gas turbine control device (20), Calculating a flow rate per unit time of fuel into a gas turbine (10) based on a measured value of the gas turbine (10); Calculating a flow rate per unit time of air supplied to the gas turbine (10) based on a measured value of the gas turbine (10); Calculating a turbine inlet temperature by inputting into a physical model formula expressing a relationship of the heat energy balance with respect to a combustion chamber (12) of the gas turbine (10), the flow rate per unit time of the fuel, the flow rate per unit time of the air, a fuel temperature, and an air temperature at a casing (132) of the gas turbine (10); and Calculating a fuel distribution ratio for each of the fuel supply systems (50a, 50b, 50c) connected to the combustion chamber (12) based on the turbine inlet temperature, where the turbine inlet temperature is calculated by using a specific enthalpy which is changed in accordance with humidity. [10] A gas turbine control method comprising: with a gas turbine control device (20), Calculating a flow rate per unit time of fuel into a gas turbine (10) based on a measured value of the gas turbine (10); Calculating a flow rate per unit time of air supplied to the gas turbine (10) based on a measured value of the gas turbine (10); Calculating a turbine inlet temperature by inputting into a physical model formula expressing a relationship of the heat energy balance with respect to a combustion chamber (12) of the gas turbine (10), the flow rate per unit time of the fuel, the flow rate per unit time of the air, a fuel temperature and an air temperature at a casing (132) of the gas turbine (10); Calculating a fuel distribution ratio for each of the fuel supply systems (50a, 50b, 50c) connected to the combustor (12) based on the turbine inlet temperature; and Correcting the turbine inlet temperature based on a ratio of an exhaust gas temperature at the gas turbine (10) and an exhaust gas temperature at the gas turbine (10) calculated from the turbine inlet temperature, wherein the fuel distribution ratio is calculated based on a turbine inlet temperature after the correction.

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