Gas turbine combustor control device and gas turbine combustor control method

Abstract

The present application relates to a gas turbine combustor control device for controlling a gas turbine combustor including a primary nozzle group corresponding to a primary combustion region and a secondary nozzle group corresponding to a secondary combustion region located downstream of the primary combustion region. The device calculates a first distribution ratio, which is the fuel distribution ratio of secondary fuel to fuel, on the basis of a first combustion load command value corresponding to an outlet-side combustion temperature of the secondary combustion region, and calculates a second distribution ratio, which is the fuel distribution ratio of primary fuel to the fuel, on the basis of a second combustion load command value corresponding to the outlet-side combustion temperature of the primary combustion region.

Description

Gas turbine combustor control device and gas turbine combustor control method

[0001] This application claims priority to Japanese Patent Application No. 2024-060056, filed with the Japan Patent Office on April 3, 2024, the contents of which are incorporated herein by reference.

[0002] A gas turbine combustor is known that is mounted on a gas turbine and generates combustion gas for driving the turbine. The gas turbine combustor includes a fuel injection nozzle that injects fuel supplied from a fuel supply system into a combustion chamber defined by a combustion liner to generate combustion gas. The fuel injection nozzle includes multiple types of nozzles, such as a main nozzle, a pilot nozzle, and a top hat nozzle, and fuel is supplied to each type of nozzle from the fuel supply system at a predetermined distribution ratio.

[0003] In a typical gas turbine combustor, these fuel injection nozzles are arranged relatively upstream in the direction of flow of combustion gas. However, as disclosed in Patent Document 1, for example, a gas turbine combustor of a so-called multi-stage combustion type has also been proposed, in which, in addition to a primary nozzle arranged relatively upstream in the flow direction, a secondary nozzle is provided downstream of the primary nozzle in the flow direction.

[0004] JP 2013-238387 A

[0005] The fuel allocation ratio for each fuel injection nozzle included in a gas turbine combustor is calculated based on the operating state of the gas turbine, and the relationship between the operating state and the allocation ratio is defined based on operating data acquired during a test run of the gas turbine. When a multi-stage combustion gas turbine combustor such as that described in Patent Document 1 is developed based on a single-stage combustion gas turbine combustor, the relationship between the operating state and the allocation ratio is significantly changed due to the addition of a new fuel injection nozzle (secondary nozzle). Therefore, when the test run is performed again, the relationship needs to be defined anew.

[0006] At least one embodiment of the present disclosure has been made in view of the above circumstances, and an object of the present disclosure is to provide a gas turbine combustor control device and a gas turbine combustor control method that are capable of simply setting a fuel allocation ratio to each nozzle.

[0007] To achieve the above object, a gas turbine combustor control device according to at least one embodiment of the present disclosure provides a gas turbine combustor control device for controlling a gas turbine combustor including: a combustion liner defining a combustion chamber; a primary nozzle group including a plurality of primary nozzles for injecting a primary fuel which is a part of fuel supplied from a fuel supply system into a primary combustion zone of the combustion chamber; and a secondary nozzle group including at least one secondary nozzle for injecting a remaining secondary fuel of the fuel excluding the primary fuel into a secondary combustion zone which is located on a downstream side of the primary combustion zone in a flow direction of combustion gas in the combustion chamber, the gas turbine combustor control device comprising: a first combustion load command value calculation unit for calculating a first combustion load command value corresponding to an outlet side combustion temperature of the secondary combustion zone; a first allocation ratio calculation unit for calculating a first allocation ratio which is a fuel allocation ratio of the secondary fuel to the fuel, based on the first combustion load command value; a second combustion load command value calculation unit for calculating a second combustion load command value corresponding to an outlet side combustion temperature of the primary combustion zone; and a second allocation ratio calculation unit for calculating a second allocation ratio which is a fuel allocation ratio of the primary fuel to the fuel, based on the second combustion load command value. Equipped with.

[0008] To achieve the above object, a gas turbine combustor control device according to at least one embodiment of the present disclosure provides a gas turbine combustor control method for controlling a gas turbine combustor including: a combustion liner defining a combustion chamber; a primary nozzle group including a plurality of primary nozzles for injecting a primary fuel which is a part of fuel supplied from a fuel supply system into a primary combustion zone of the combustion chamber; and a secondary nozzle group including at least one secondary nozzle for injecting a remaining secondary fuel of the fuel excluding the primary fuel, into a secondary combustion zone located on a downstream side of the primary combustion zone in a flow direction of combustion gas in the combustion chamber, the gas turbine combustor control method comprising: calculating a first combustion load command value corresponding to a combustion temperature on an outlet side of the secondary combustion zone; calculating a first allocation ratio which is a fuel allocation ratio of the secondary fuel to the fuel, based on the first combustion load command value; calculating a second combustion load command value corresponding to the combustion temperature on an outlet side of the primary combustion zone; and calculating a second allocation ratio which is a fuel allocation ratio of the primary fuel to the fuel, based on the second combustion load command value.

[0009] According to at least one embodiment of the present disclosure, it is possible to provide a gas turbine combustor control device and a gas turbine combustor control method that are capable of simply setting a fuel distribution ratio for each nozzle.

[0010] FIG. 1 is a schematic configuration diagram of a gas turbine according to one embodiment. FIG. 2 is a schematic configuration diagram of the gas turbine combustor of FIG. 1. FIG. 3 is a schematic configuration diagram of a gas turbine combustor according to a first reference technology. FIG. 4 is a block configuration diagram of a gas turbine combustor control device for controlling the gas turbine combustor of FIG. 3. FIG. 5 is a block configuration diagram of a gas turbine combustor control device according to a second reference technology. FIG. 6 is a block configuration diagram of a gas turbine combustor control device according to one embodiment. FIG. 7 is an example of a function fx4 of FIG. 6. FIG. 8 is an example of a function fx2 of FIG. 6. FIG. 9 is an example of a function fx3 of FIG.

[0011] Hereinafter, several embodiments of the present disclosure will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of the configurations described as embodiments or shown in the drawings are merely illustrative examples and are not intended to limit the scope of the present disclosure.

[0012] 1 is a schematic configuration diagram of a gas turbine 1 according to one embodiment. The gas turbine 1 includes a compressor 2 for generating compressed air, a gas turbine combustor 4 for generating combustion gas using the compressed air and fuel, and a turbine 6 that can be driven by the combustion gas generated by the gas turbine combustor 4. In this embodiment, a single-shaft gas turbine is exemplified as the gas turbine 1, and the compressor 2 and the turbine 6 are connected by a rotating shaft 9. A generator 5 is further connected to this rotating shaft 9.

[0013] The intake air volume of the compressor 2 can be adjusted by opening and closing an inlet guide vane (IGV) 3 provided at the inlet of the compressor 2. The opening and closing operation of the inlet guide vane 3 can be achieved by driving an actuator 7 such as a servo motor provided on the inlet guide vane 3.

[0014] In the gas turbine combustor 4, the compressed air delivered from the compressor 2 and the fuel F supplied from a fuel supply system 10 are mixed and burned to generate combustion gas, which is a working fluid for driving the turbine 6. The turbine 6 is driven by the combustion gas flowing in from the gas turbine combustor 4, and the rotation of the rotary shaft 9 causes the generator 5 to generate electricity.

[0015] The fuel supply system 10 is configured to supply fuel F from a fuel supply source 12 to a gas turbine combustor 4. As will be described later with reference to FIG. 2 , the gas turbine combustor 4 has a primary nozzle group 22 and a secondary nozzle group 24 as fuel injection nozzles for injecting the fuel F into a combustion chamber 20. In the fuel supply system 10, the fuel F from the fuel supply source 12 is first distributed by a first distribution unit 14 into primary fuel F1 and secondary fuel F2 based on a first distribution ratio DR1. The primary fuel F1 is supplied to the primary nozzle group 22, and the secondary fuel F2 is supplied to the secondary nozzle group 24. The first distribution unit 14 is configured to include pipes, shutoff valves, and flow rate adjustment valves (not shown), and is able to distribute the fuel F to the primary fuel F1 and the secondary fuel F2 at the first distribution ratio DR1 by adjusting the open / closed states of the respective valves.

[0016] The primary fuel F1 distributed to the primary nozzle group 22 is further distributed to the multiple primary nozzles 23 included in the primary nozzle group 22 by the second distribution unit 16. As will be described later with reference to FIG. 2 , the primary nozzle group 22 includes main nozzles 23M, pilot nozzles 23PL, and top hat nozzles 23TH as the primary nozzles 23, and the primary fuel F1 is distributed to each type of primary nozzle at a second distribution ratio DR2. Specifically, the second distribution unit 16 distributes the primary fuel F1 to the main nozzles 23M as main fuel F1M, to the pilot nozzles 23PL as pilot fuel F1PL, and to the top hat nozzles 23TH as top hat fuel F1TH. The second distribution unit 16 is configured to include pipes, shut-off valves, and flow rate adjustment valves (not shown), and is able to distribute the primary fuel F1 at the second distribution ratio DR2 by adjusting the open / close states of each valve.

[0017] The fuel F supplied from the fuel supply system 10 may be hydrogen, methane, light oil, heavy oil, jet fuel, natural gas, gasified coal, or a combination of any two or more of these. In the following description, the compressed air sent from the compressor 2 to the gas turbine combustor 4 will also be referred to as "combustion air" as appropriate.

[0018] Fig. 2 is a schematic configuration diagram of the gas turbine combustor 4 shown in Fig. 1. The gas turbine combustor 4 includes an inner cylinder 21, which is a combustion cylinder that defines a combustion chamber 20, a primary nozzle group 22 including a plurality of types of fuel injection nozzles, and a secondary nozzle group 24.

[0019] The primary nozzle group 22 is provided at one end of the combustion chamber 20 (the upstream side in the flow direction of combustion gas) and includes a plurality of primary nozzles 23. The plurality of primary nozzles 23 includes a main nozzle 23M, a pilot nozzle 23PL, and a top hat nozzle 23TH. The pilot nozzle 23PL and the main nozzle 23M are provided inside the inner cylinder 21, and the top hat nozzle 23TH is provided between the inner cylinder 21 and an outer cylinder 25 that is arranged radially outward from the inner cylinder 21.

[0020] The pilot nozzle 23PL is a fuel injection nozzle for diffusion combustion intended to improve combustion stability, and one pilot nozzle 23PL is provided in the center of the inner cylinder 21. The main nozzles 23M are fuel nozzles for premixed combustion in which main fuel F1M and compressed air are mixed upstream of the combustion section and then combusted, with the aim of reducing NOx, and multiple main nozzles 23M are provided around the pilot nozzle 23PL. The top hat nozzles 23TH are fuel nozzles for premixed combustion in which top hat fuel F1TH and compressed air are mixed further upstream than the main nozzles 23M and then combusted, with the aim of further reducing NOx, and multiple top hat nozzles 23TH are provided further outward than the main nozzles 23M.

[0021] The primary fuel F1 from the fuel supply system 10 is distributed and supplied to the main nozzles 23M, the pilot nozzles 23PL, and the top hat nozzles 23TH that configure the primary nozzle group 22. Specifically, the primary fuel F1 distributed by the second distribution unit 16 is supplied to the main nozzles 23M as main fuel F1M, to the pilot nozzles 23PL as pilot fuel F1PL, and to the top hat nozzles 23TH as top hat fuel F1TH.

[0022] Combustion occurs by injecting primary fuel F1 and combustion air from each primary nozzle 23 of the primary nozzle group 22 into a primary combustion zone 30 located relatively upstream in the flow direction of the combustion gas within the combustion chamber 20. The main stream high-temperature gas, which is the combustion gas generated in the primary combustion zone 30, flows downstream in the flow direction of the combustion gas.

[0023] The secondary nozzle group 24 is disposed downstream of the primary nozzle group 22 in the combustion gas flow direction and includes at least one secondary nozzle 28. In this embodiment, the secondary nozzle group 24 includes a plurality of secondary nozzles 28 disposed at predetermined intervals along the circumferential direction of the inner cylinder 21. The secondary nozzles 28 of the secondary nozzle group 24 inject secondary fuel F2 and combustion air into a secondary combustion zone 32 located downstream of the primary combustion zone 30 in the combustion gas flow direction. In the secondary combustion zone 32, a second stage of combustion occurs in the combustion chamber 20 as a result of the secondary fuel F2 and combustion air being injected from the secondary nozzles 28.

[0024] Next, a gas turbine combustor control device 100 for controlling the gas turbine combustor 4 having the above configuration will be described. The gas turbine combustor control device 100 is a control unit for controlling the gas turbine combustor 4 and is configured to include, for example, a central processing unit (CPU), a random access memory (RAM), a read-only memory (ROM), and a computer-readable storage medium. A series of processes for realizing various functions is stored in, for example, a storage medium in the form of a program. The CPU reads the program into, for example, the RAM and executes information processing and arithmetic processing, thereby realizing various functions. The program may be installed in a ROM or other storage medium in advance, may be provided in a state where it is stored in a computer-readable storage medium, or may be distributed via wired or wireless communication means. Examples of the computer-readable storage medium include a magnetic disk, a magneto-optical disk, a CD-ROM, a DVD-ROM, and a semiconductor memory.

[0025] Here, several reference techniques will be described as prerequisite techniques for explaining the gas turbine combustor control device 100 according to this embodiment. Fig. 3 is a schematic configuration diagram of a gas turbine combustor 4' according to a first reference technique, and Fig. 4 is a block configuration diagram of a gas turbine combustor control device 200 for controlling the gas turbine combustor 4' in Fig. 3.

[0026] A gas turbine combustor 4′ shown in FIG. 3 is a gas turbine combustor of a single-stage combustion type that does not include a secondary nozzle group 24, as compared with the aforementioned gas turbine combustor 4 shown in FIG. 2 (except for this difference, the gas turbine combustor 4′ has a configuration equivalent to that of the aforementioned gas turbine combustor 4 unless otherwise specified).

[0027] As shown in FIG. 4 , the gas turbine combustor control device 200 includes a fuel flow rate command value calculating unit 202, a combustion load command value calculating unit 204, an allocation ratio calculating unit 206, a nozzle fuel flow rate command value calculating unit 208, and a fuel supply system control unit 210.

[0028] The fuel flow rate command value calculation unit 202 is configured to set a fuel flow rate command value CSO based on an output command value D from a central load dispatching center that manages the output of the generator 5. The relationship between the output command value D and the fuel flow rate command value CSO is specified in advance as a function fx1', and the fuel flow rate command value calculation unit 202 inputs the output command value D received from the central load dispatching center into this function fx1', and outputs the corresponding fuel flow rate command value CSO.

[0029] The combustion load command value calculation unit 204 is configured to calculate a combustion load command value CLCSO corresponding to an outlet-side combustion temperature T1T of the combustion chamber 20. As schematically shown in FIG. 3 , the outlet-side combustion temperature T1T of the combustion chamber 20 is the combustion temperature at the most downstream position in the combustion chamber 20 in the flow direction of the combustion gas (in other words, it is also the inlet temperature of the turbine 6 located downstream of the combustion chamber 20). This outlet-side combustion temperature T1T is high, and therefore it is difficult to stably measure it using a sensor over a long period of time. Therefore, the combustion load command value CLCSO is calculated as an index corresponding to the outlet-side combustion temperature T1T of the combustion chamber 20.

[0030] In the first reference technology, the combustion load command value CLCSO is calculated based on the intake air temperature T1C of the compressor 2, the position command value IGV of the inlet guide vane 3, and the output MW of the generator 5. The combustion load command value CLCSO calculated in this manner is a dimensionless value of the outlet-side combustion temperature T1T of the combustion chamber 20, that is, a value proportional to the outlet-side combustion temperature T1T of the combustion chamber 20.

[0031] The distribution ratio calculation unit 206 is configured to calculate a distribution ratio of the fuel F to each primary nozzle 23 included in the gas turbine combustor 4′, based on the combustion load command value CLCSO. Specifically, the distribution ratio calculation unit 206 calculates a distribution ratio DR corresponding to the combustion load command value CLCSO and the pilot nozzle 23PL. ＰＬ 1, and the combustion load command value CLCSO calculated by the combustion load command value calculation unit 204 is input to the function fx2′ to obtain the distribution ratio DR corresponding to the pilot nozzle 23PL. ＰＬ 1 is calculated. The distribution ratio calculation unit 206 calculates the distribution ratio DR corresponding to the combustion load command value CLCSO and the top hat nozzle 23TH. ＴＨ 1, and by inputting the combustion load command value CLCSO calculated by the combustion load command value calculation unit 204 to the function fx3′, the distribution ratio DR corresponding to the top hat nozzle 23TH is calculated. ＴＨ 1 is calculated.

[0032] The functions fx2' and fx3' are determined based on operational data obtained in advance by a test run of the gas turbine combustor 4'.

[0033] The nozzle fuel flow rate command value calculation unit 208 calculates the fuel flow rate command value CSO calculated by the fuel flow rate command value calculation unit 202 and the distribution ratio DR calculated by the distribution ratio calculation unit 206. ＰＬ 1 and DR ＴＨ 1, the nozzle fuel flow rate command value calculation unit 208 calculates a fuel flow rate command value corresponding to each primary nozzle 23. Specifically, the nozzle fuel flow rate command value calculation unit 208 calculates a fuel flow rate command value CSO by the distribution ratio DR ＰＬ 1 to calculate the pilot fuel flow rate command value PLCSO corresponding to the pilot nozzle 23PL, and to the fuel flow rate command value CSO by multiplying the fuel flow rate command value PLCSO by the distribution ratio DR ＴＨThe nozzle fuel flow rate command value calculation unit 208 calculates a top hat fuel flow rate command value THCSO corresponding to the top hat nozzle 23TH by multiplying the pilot fuel flow rate command value PLCSO corresponding to the pilot nozzle 23PL and the top hat fuel flow rate command value THCSO corresponding to the top hat nozzle 23TH by 1. Furthermore, the nozzle fuel flow rate command value calculation unit 208 calculates a main fuel flow rate command value MCSO corresponding to the main nozzle 23M by subtracting the pilot fuel flow rate command value PLCSO corresponding to the pilot nozzle 23PL and the top hat fuel flow rate command value THCSO corresponding to the top hat nozzle 23TH from the fuel flow rate command value CSO.

[0034] The fuel supply system control unit 210 is configured to realize the respective fuel flow rate command values ​​calculated by the nozzle fuel flow rate command value calculation unit 208 by controlling the fuel supply system 10. Specifically, based on the calculation result of the nozzle fuel flow rate command value calculation unit 208, the fuel supply system control unit 210 controls the fuel flow rate from the fuel supply system 10 to the pilot nozzle 23PL based on a pilot fuel flow rate command value PLCSO, controls the fuel flow rate from the fuel supply system 10 to the top hat nozzle 23TH based on a top hat fuel flow rate command value THCSO, and controls the fuel flow rate from the fuel supply system 10 to the main nozzle 23M based on a main fuel flow rate command value MCSO.

[0035] Next, assume a case where the gas turbine combustor 4′ according to the above-described first reference technology is improved to the gas turbine combustor 4 shown in FIG. 2 by additionally providing the secondary nozzle group 24. In this case, taking into consideration that the gas turbine combustor 4 has a configuration in which the secondary nozzle group 24 is additionally provided with respect to the gas turbine combustor 4′, it is considered to perform an extensible design change of the gas turbine combustor control device 200 according to the first reference technology to a gas turbine combustor control device 300 according to a second reference technology described below.

[0036] 5 is a block configuration diagram of a gas turbine combustor control device 300 according to the second reference technology. The gas turbine combustor control device 300 includes a fuel flow rate command value calculating unit 302, a combustion load command value calculating unit 304, an allocation ratio calculating unit 306, a nozzle fuel flow rate command value calculating unit 308, and a fuel supply system control unit 310.

[0037] In the gas turbine combustor control device 300, a fuel flow rate command value calculation unit 302 and a combustion load command value calculation unit 304 are similar to the fuel flow rate command value calculation unit 202 and the combustion load command value calculation unit 204, respectively, that are included in the gas turbine combustor control device 200 described above (a function fx1″ included in the fuel flow rate command value calculation unit 302 is the same as the function fx1′ included in the fuel flow rate command value calculation unit 202). On the other hand, in the gas turbine combustor 4, the secondary nozzle group 24 is additionally provided compared to the gas turbine combustor 4′, and accordingly, the allocation ratio calculation unit 306 calculates three allocation ratios DR ＰＬ 1. Dr. ＴＨ 2 and DR ＡＦＩ 2 is calculated.

[0038] Specifically, the distribution ratio calculation unit 306 calculates the distribution ratio DR corresponding to the combustion load command value CLCSO and the pilot nozzle 23PL. ＰＬ 2, and by inputting the combustion load command value CLCSO calculated by the combustion load command value calculation unit 304 to the function fx2'', the distribution ratio DR corresponding to the pilot nozzle 23PL is obtained. ＰＬ The distribution ratio calculation unit 306 calculates the combustion load command value CLCSO and the distribution ratio DR corresponding to the top hat nozzle 23TH. ＴＨ 2, and by inputting the combustion load command value CLCSO calculated by the combustion load command value calculation unit 304 to the function fx3'', the distribution ratio DR corresponding to the top hat nozzle 23TH is obtained. ＴＨ 2 is calculated. The distribution ratio calculation unit 306 calculates the combustion load command value CLCSO and the distribution ratio DR corresponding to the secondary nozzle group 24. ＡＦＩ 2, and by inputting the combustion load command value CLCSO calculated by the combustion load command value calculation unit 304 to the function fx4'', the distribution ratio DR corresponding to the secondary nozzle group 24 is obtained. ＡＦＩ 2 is calculated.

[0039] The nozzle fuel flow rate command value calculation unit 308 is configured to calculate a fuel flow rate command value corresponding to each primary nozzle 23 based on the fuel flow rate command value CSO calculated by the fuel flow rate command value calculation unit 302 and each distribution ratio calculated by the distribution ratio calculation unit 306. Specifically, the nozzle fuel flow rate command value calculation unit 308 calculates a fuel flow rate command value corresponding to each primary nozzle 23 based on the fuel flow rate command value CSO calculated by the fuel flow rate command value calculation unit 302 and each distribution ratio calculated by the distribution ratio calculation unit 306. ＰＬ 2 to calculate the pilot fuel flow rate command value PLCSO corresponding to the pilot nozzle 23PL, and to the fuel flow rate command value CSO by multiplying the fuel flow rate command value PLCSO by the distribution ratio DR ＴＨ 2 to calculate the top hat fuel flow rate command value THCSO corresponding to the top hat nozzle 23TH, and to the fuel flow rate command value CSO, the distribution ratio DR ＡＦＩ 2 to calculate a secondary fuel flow rate command value AFICSO corresponding to the secondary nozzle group 24. Furthermore, the nozzle fuel flow rate command value calculation unit 308 calculates a main fuel flow rate command value MCSO corresponding to the main nozzle 23M by subtracting the pilot fuel flow rate command value PLCSO corresponding to the pilot nozzle 23PL, the top hat fuel flow rate command value THCSO corresponding to the top hat nozzle 23TH, and the secondary fuel flow rate command value AFICSO corresponding to the secondary nozzle group 24 from the fuel flow rate command value CSO.

[0040] The fuel supply system control unit 310 is configured to realize the respective fuel flow rate command values ​​calculated by the nozzle fuel flow rate command value calculation unit 308 by controlling the fuel supply system 10 (the first distribution unit 14 and the second distribution unit 16). Specifically, the fuel supply system control unit 310 controls the flow rate of the pilot fuel F1PL from the fuel supply system 10 to the pilot nozzle 23PL, based on a pilot fuel flow rate command value PLCSO, controls the flow rate of the top hat fuel F1TH from the fuel supply system 10 to the top hat nozzle 23TH, based on a top hat fuel flow rate command value THCSO, controls the flow rate of the main fuel F1M from the fuel supply system 10 to the main nozzle 23M, based on a main fuel flow rate command value MCSO, and controls the flow rate of the secondary fuel F2 from the fuel supply system 10 to the secondary nozzle group 24, based on a secondary fuel flow rate command value AFICSO.

[0041] 2 and 3 , the gas turbine combustor 4 that is a control target of the gas turbine combustor control device 300 according to the second reference technology has the pilot nozzle 23PL, the top hat nozzle 23TH, and the main nozzles 23M as common components with the gas turbine combustor 4′ that is a control target of the gas turbine combustor control device 200 according to the first reference technology. On the other hand, the gas turbine combustor 4 is additionally provided with the secondary nozzle group 24 compared to the gas turbine combustor 4′, and therefore the fuel distribution balance is changed, and therefore the distribution ratios corresponding to the pilot nozzle 23PL, the top hat nozzle 23TH, and the main nozzles 23M that are common components cannot be directly applied to the gas turbine combustor 4. That is, the distribution ratio DR according to the first reference technology ＰＬ 1 and DR ＴＨ 1, the distribution ratio DR in the second reference technology ＰＬ 2 and DR ＴＨ Therefore, in the second reference technology, the configuration of the gas turbine combustor control device 200 according to the first reference technology cannot be effectively used, and the distribution ratio DR ＰＬ 2. Dr. ＴＨ In order to re-determine the value of 2, the test run must be performed again. This problem can be preferably solved by the embodiment described below.

[0042] 6 is a block configuration diagram of a gas turbine combustor control device 100 according to one embodiment. The gas turbine combustor control device 100 includes a fuel flow rate command value calculating unit 102, a first combustion load command value calculating unit 104, a first allocation ratio calculating unit 106, a secondary fuel flow rate command value calculating unit 108, a primary fuel flow rate command value calculating unit 110, a second combustion load command value calculating unit 112, a second allocation ratio calculating unit 114, a primary nozzle fuel flow rate command value calculating unit 116, and a fuel supply system control unit 118.

[0043] Similar to the fuel flow rate command value calculation units 202 and 302 in the above-described respective reference techniques, the fuel flow rate command value calculation unit 102 is configured to set a fuel flow rate command value CSO based on an output command value D from a central load dispatching center that manages the output of the generator 5. The relationship between the output command value D and the fuel flow rate command value CSO is set in advance as a function fx1, and the fuel flow rate command value calculation unit 102 inputs the output command value D received from the central load dispatching center into the function fx1, thereby outputting the corresponding fuel flow rate command value CSO.

[0044] The function fx1 of the fuel flow rate command value calculation unit 102 is the same as the function fx1′ of the fuel flow rate command value calculation unit 202 in the above-mentioned first reference technology and the function fx1″ of the fuel flow rate command value calculation unit 302 in the above-mentioned second reference technology.

[0045] The first combustion load command value calculation unit 104 is configured to calculate a first combustion load command value CLCSO corresponding to an outlet-side combustion temperature T1T of the secondary combustion zone 32. As schematically shown in FIG. 2 , the outlet-side combustion temperature T1T of the secondary combustion zone 32 is the combustion temperature at the most downstream position in the flow direction of the combustion gas within the secondary combustion zone 32 (in other words, it is also the inlet temperature of the turbine 6 located downstream of the secondary combustion zone 32). This outlet-side combustion temperature T1T is high, and therefore difficult to stably measure using a sensor over a long period of time. Therefore, the first combustion load command value CLCSO is calculated as an index corresponding to the outlet-side combustion temperature T1T of the secondary combustion zone 32.

[0046] In this embodiment, the first combustion load command value CLCSO is calculated based on the intake air temperature T1C of the compressor 2, the position command value IGV of the inlet guide vane 3, and the output MW of the generator 5. The first combustion load command value CLCSO calculated in this manner is a dimensionless value of the outlet-side combustion temperature T1T of the secondary combustion zone 32, that is, a value proportional to the outlet-side combustion temperature T1T of the secondary combustion zone 32.

[0047] Note that the first combustion load command value-calculating unit 104 calculates the first combustion load command value CLCSO based on the output MW of the generator 5, but the relationship between the output MW and the first combustion load command value CLCSO may be learned using operation data of the gas turbine 1. In this case, the relationship between the output MW and the first combustion load command value CLCSO is defined by a learning model constructed by machine learning using operation data of the gas turbine 1 as learning data, for example. When the calculation accuracy of the first combustion load command value CLCSO is reduced due to a change in performance of the gas turbine 1 (such as aging deterioration), for example, this learning model can be updated by re-learning using newly accumulated operation data as learning data, thereby improving the calculation accuracy of the first combustion load command value CLCSO.

[0048] The first distribution ratio calculation unit 106 is configured to calculate a first distribution ratio DR1 based on the first combustion load command value CLCSO. The first distribution ratio DR1 is a fuel distribution ratio of the secondary fuel F2 to the fuel F in the first distribution unit 14 of the fuel supply system 10. The relationship between the first combustion load command value CLCSO and the first distribution ratio DR1 is specified in advance as a function fx4.

[0049] Here, Fig. 7 shows an example of the function fx4 in Fig. 6. The function fx4 is defined so that the first distribution ratio DR1 increases as the first combustion load command value CLCSO increases. A first distribution ratio calculation unit 106 inputs the first combustion load command value CLCSO calculated by the first combustion load command value calculation unit 104 into the function fx4, thereby calculating the corresponding first distribution ratio DR1.

[0050] The secondary fuel flow rate command value calculation unit 108 is configured to calculate a secondary fuel flow rate command value AFICSO, which is a control command value corresponding to the flow rate of the secondary fuel F2 for the secondary nozzle group 24. The secondary fuel flow rate command value AFICSO is obtained by multiplying the fuel flow rate command value CSO calculated by the fuel flow rate command value calculation unit 102 by the first distribution ratio DR1 calculated by the first distribution ratio calculation unit 106.

[0051] The primary fuel flow rate command value calculation unit 110 is configured to calculate a primary fuel flow rate command value HECSO, which is a control command value corresponding to the flow rate of the primary fuel F1 to the primary nozzle group 22. The primary fuel flow rate command value HECSO is found by subtracting the secondary fuel flow rate command value AFICSO calculated by the secondary fuel flow rate command value calculation unit 108 from the fuel flow rate command value CSO calculated by the fuel flow rate command value calculation unit 102.

[0052] The second combustion load command value calculation unit 112 is configured to calculate a second combustion load command value HECLCSO corresponding to the outlet combustion temperature HET1T of the primary combustion zone 30. As schematically shown in FIG. 2 , the outlet combustion temperature HET1T of the primary combustion zone 30 is the combustion temperature at the most downstream position in the flow direction of the combustion gas in the primary combustion zone 30 (in other words, it is also the most upstream position in the flow direction of the combustion gas in the secondary combustion zone 32). This outlet combustion temperature HET1T is also high in temperature, making it difficult to stably measure it using a sensor over a long period of time. Therefore, the second combustion load command value HECLCSO is calculated as an index corresponding to the outlet combustion temperature HET1T of the primary combustion zone 30.

[0053] In the present embodiment, the second combustion load command value HECLCSO is calculated by the following equation using the maximum design temperature T1Tmax and the minimum design temperature T1Tmin of the outlet-side combustion temperature HET1T of the primary combustion zone 30 and the outlet-side temperature (turbine inlet temperature) T1T of the secondary combustion zone 32. Here, the outlet-side combustion temperature HET1T of the primary combustion region 30 is expressed by the following equation using the cabin air temperature T2C of the compressor 2, the first distribution ratio DR1 calculated by the first distribution ratio calculation unit 106, and the air distribution ratio AR of the combustion air to the secondary nozzle group 24. The second combustion load command value HECLCSO calculated in this manner is a dimensionless value of the exit side combustion temperature HET1T of the primary combustion region 30, that is, a value proportional to the exit side combustion temperature HET1T of the primary combustion region 30.

[0054] The second allocation ratio calculation unit 114 is configured to calculate a second allocation ratio DR2, which is a fuel allocation ratio of the primary fuel F1 to the fuel F. In the present embodiment, the multiple primary nozzles 23 belonging to the primary nozzle group 22 include at least one main nozzle 23M, a pilot nozzle 23PL, and a top hat nozzle 23TH. The second allocation ratio calculation unit 114 calculates the second allocation ratio DR2 as the pilot allocation ratio DR2 of the primary fuel F1 to the pilot nozzle 23PL. ＨＥＰＬ , and the top hat distribution ratio DR2 of the primary fuel F1 to the top hat nozzle 23TH ＨＥＴＨ are calculated respectively.

[0055] In the second distribution ratio calculation unit 114, the second combustion load command value HECLCSO and the pilot distribution ratio DR2 ＨＥＰＬ The relationship between the second combustion load command value HECLCSO and the top hat distribution ratio DR2 is defined in advance as a function fx2. ＨＥＴＨ The relationship between these functions fx2 and fx3 is defined in advance as a function fx3. These functions fx2 and fx3 are calculated as the distribution ratio DR in the distribution ratio calculation unit 206 of the first reference technique (see FIG. 4). ＰＬ 1 and DR ＴＨ 1. That is, in this embodiment, the functions fx2' and fx3' of the first reference technology can be directly adopted (reused) as the functions fx2 and fx3. Therefore, it is not necessary to redo the trial run to re-determine the functions fx2 and fx3 for calculating each distribution ratio, as in the second reference technology described above.

[0056] 8 and 9 are examples of the functions fx2 and fx3 in Fig. 6, respectively. The function fx2 increases as the first combustion load command value CLCSO increases. ＨＥＰＬ The function fx3 is defined so that the top hat distribution ratio DR decreases as the first combustion load command value CLCSO increases. ＨＥＴＨ is specified to increase.

[0057] The primary nozzle fuel flow rate command value calculation unit 116 is configured to calculate a primary nozzle fuel flow rate command value corresponding to each primary nozzle 23 included in the primary nozzle group 22, based on the primary fuel flow rate command value HECSO calculated by the primary fuel flow rate command value calculation unit 110 and the second distribution ratio DR2 calculated by the second distribution ratio calculation unit 114. Specifically, the primary nozzle fuel flow rate command value calculation unit 116 calculates a primary nozzle fuel flow rate command value corresponding to each primary nozzle 23 included in the primary nozzle group 22, based on the primary fuel flow rate command value HECSO calculated by the primary fuel flow rate command value calculation unit 110 and the second distribution ratio DR2 calculated by the second distribution ratio calculation unit 114. ＨＥＰＬ and multiplying the primary fuel flow rate command value HECSO by the top hat distribution ratio DR2 ＨＥＴＨ Furthermore, the pilot fuel flow rate command value PLCSO and the top hat fuel flow rate command value THCSO are subtracted from the primary fuel flow rate command value HECSO to calculate a main fuel flow rate command value MCSO, which is a primary nozzle fuel flow rate command value corresponding to the main nozzle 23M.

[0058] The fuel supply system control unit 118 is configured to realize the flow rate command values ​​calculated by the secondary fuel flow rate command value calculation unit 108, the primary fuel flow rate command value calculation unit 110, and the primary nozzle fuel flow rate command value calculation unit 116, by controlling the fuel supply system 10 (the first distribution unit 14 and the second distribution unit 16). Specifically, the fuel supply system control unit 118 controls the first distribution unit 14 so as to realize the secondary fuel flow rate command value AFICSO calculated by the secondary fuel flow rate command value calculation unit 108 and the primary fuel flow rate command value HECSO calculated by the primary fuel flow rate command value calculation unit 110. The fuel supply system control unit 118 also controls the second distribution unit 16 so as to realize the pilot fuel flow rate command value PLCSO, the top hat fuel flow rate command value THCSO, and the main fuel flow rate command value MCSO calculated by the primary nozzle fuel flow rate command value calculation unit 116.

[0059] As described above, according to the above embodiment, it is possible to simply set the distribution ratio of the fuel F to each nozzle in the gas turbine combustor 4 of the multi-stage combustion type.

[0060] (1) A gas turbine combustor control device according to one aspect is a gas turbine combustor control device (100) for controlling a gas turbine combustor (4) including: a combustion liner (21) that defines a combustion chamber (20); a primary nozzle group (22) including a plurality of primary nozzles (23) for injecting a primary fuel (F1) that is a part of a fuel (F) supplied from a fuel supply system (10) into a primary combustion zone (30) of the combustion chamber; and a secondary nozzle group (24) including at least one secondary nozzle (28) for injecting a remaining secondary fuel (F2) of the fuel excluding the primary fuel into a secondary combustion zone (32) that is located downstream of the primary combustion zone in a flow direction of combustion gas in the combustion chamber, the gas turbine combustor control device (100) comprising: a first combustion load command value calculation unit (104) for calculating a first combustion load command value (CLCSO) corresponding to an outlet-side combustion temperature (T1T) of the secondary combustion zone; a first distribution ratio calculation unit (106) for calculating a first distribution ratio (DR1) that is a fuel distribution ratio of the secondary fuel to the fuel based on the first combustion load command value; a second combustion load command value calculation unit (112) for calculating a second combustion load command value (HECLCSO) that corresponds to an outlet side combustion temperature (HET1T) of the primary combustion region; and a second distribution ratio (DR2 (DR2 ＨＥＰＬ , DR2 ＨＥＴＨ )), and a second allocation ratio calculation unit (114) for calculating

[0061] According to the above aspect (1), the fuel (F) supplied from the fuel supply system (10) to the gas turbine combustor (4) is distributed to the primary nozzle group (22) and the secondary nozzle group (24) based on a first distribution ratio (DR1) which is a fuel distribution ratio of the secondary fuel to the fuel. This first distribution ratio (DR1) is calculated based on a first combustion load command value (CLCSO) corresponding to an outlet-side combustion temperature of the secondary combustion zone (32). The primary fuel (F1) distributed to the primary nozzle group is calculated based on a second distribution ratio (DR2) which is a fuel distribution ratio of the primary fuel to the fuel. ＨＥＰＬ , DR2 ＨＥＴＨ)), and is further allocated to a plurality of primary nozzles (23) included in the primary nozzle group (22). The second allocation ratio (DR2) is calculated based on a second combustion load command value (HECLCSO) corresponding to an outlet-side combustion temperature of the primary combustion region (30). Although the second allocation ratio (DR2) is calculated based on the second combustion load command value (HECLCSO) in this manner, the relationship (fx2, fx3) between the second allocation ratio and the second combustion load command value can directly utilize the relationship (fx2', fx3') between the allocation ratio for each nozzle (23) in the single-stage combustion gas turbine combustor (4') having only the primary nozzle group. In other words, in the control of the multi-stage combustion gas turbine combustor (4), by utilizing the allocation ratio between nozzles in the control of the single-stage combustion gas turbine (4') as the allocation ratio for each nozzle included in the primary nozzle group, it is possible to simply set the allocation ratio for each nozzle while suppressing the complexity of the control.

[0062] (2) In another aspect, in the aspect (1), the second combustion load command value (HECLCSO) is calculated based on the first combustion load command value (CLCSO), the first distribution ratio (DR1), an distribution ratio (AR) of the combustion air supplied to the gas turbine combustor to the second nozzle group, a casing air temperature of a compressor, and a maximum design value (T1Tmax) and a minimum design value (T1Tmin) of a combustion temperature on an outlet side of the secondary combustion zone.

[0063] According to the above aspect (2), the second combustion load command value (HECLCSO) corresponding to the combustion temperature on the outlet side of the primary combustion zone is calculated based on the first combustion load command value (CLCSO), the first distribution ratio (DR1), the air distribution ratio (AR) for the second nozzle group, the casing air temperature of the compressor, and the maximum design value (T1Tmax) and the minimum design value (T1Tmin) of the combustion temperature on the outlet side of the secondary combustion zone. The combustion temperature on the outlet side of the primary combustion zone is typically high, and therefore difficult to stably obtain over a long period of time by actual measurement using a sensor. However, the combustion temperature can be favorably handled by the second combustion load command value (HECLCSO) calculated in this manner.

[0064] (3) In another aspect, in the aspect (1) or (2), the fuel supply system further includes: a secondary fuel flow rate command value calculation unit (108) for calculating a secondary fuel flow rate command value (AFICSO) for the secondary nozzle group based on the fuel flow rate command value (CSO) of the fuel and the first distribution ratio (DR1); and a primary fuel flow rate command value calculation unit (110) for calculating a primary fuel flow rate command value (HECSO) for the primary nozzle group by subtracting the secondary fuel flow rate command value (AFICSO) from the fuel flow rate command value (CSO).

[0065] According to the above aspect (3), the secondary fuel flow rate command value (AFICSO) for the secondary nozzle group can be suitably calculated by allocating the fuel flow rate command value (CSO) of the fuel supplied from the fuel supply system based on the first allocation ratio (DR1). Also, the primary fuel flow rate command value (HECSO) for the primary nozzle group can be suitably calculated by subtracting the secondary fuel flow rate command value (AFICSO) from the fuel flow rate command value (CSO). In this way, the allocation of the fuel supplied from the fuel supply system to the primary nozzle group and the secondary nozzle group can be easily controlled by a simple calculation.

[0066] (4) In another aspect, in the aspect (3), the primary fuel flow rate command value (HECSO) and the second distribution ratio (DR2 ＨＥＰＬ , DR2 ＨＥＴＨ The fuel flow rate command value calculation unit (116) calculates primary nozzle fuel flow rate command values ​​(PLCSO, THCSO, MCSO) that are fuel distribution ratios among the plurality of primary nozzles based on the fuel flow rate command values ​​(PLCSO, THCSO, MCSO).

[0067] According to the above aspect (4), by distributing the primary fuel flow rate command value assigned to the primary nozzle group based on the primary fuel flow rate command value (HECSO) and the second distribution ratio, it is possible to suitably allocate fuel to each primary nozzle included in the primary nozzle group.

[0068] (5) In another aspect, in the aspect (4), the plurality of primary nozzles include at least one main nozzle (23M), a pilot nozzle (23PL), and a top hat nozzle (23TH), and the second distribution ratio calculation unit (114) calculates a pilot distribution ratio (DR2) of the primary fuel to the pilot nozzle as the second distribution ratio. ＨＥＰＬ ), and a top hat distribution ratio (DR2 ＨＥＴＨ ) are calculated respectively.

[0069] According to the above aspect (5), the fuel distribution ratio for each of the main nozzles, the pilot nozzle, and the top hat nozzle included in the primary nozzle group can be suitably calculated using the second distribution ratio (DR2).

[0070] (6) In another aspect, in the aspect (5), the primary nozzle fuel flow rate command value calculation unit (116) calculates the primary fuel flow rate command value (HECSO) and the pilot distribution ratio (DR2 ＨＥＰＬ a pilot fuel flow command value (PLCSO) corresponding to the pilot nozzle is calculated as the primary nozzle fuel flow command value based on the primary fuel flow command value (HECSO) and the top hat distribution ratio (DR2 ＨＥＴＨ ), a top hat fuel flow command value (THCSO) corresponding to the top hat nozzle is calculated as the primary nozzle fuel flow command value, and a main fuel flow command value (MCSO) corresponding to the at least one main nozzle is calculated as the primary nozzle fuel flow command value by subtracting the pilot fuel flow command value (PLCSO) and the top hat fuel flow command value (THCSO) from the fuel flow command value (HECSO).

[0071] According to the above aspect (6), the second distribution ratio (DR2 ＨＥＰＬ , DR2 ＨＥＴＨ), it is possible to suitably calculate the fuel flow rate command values ​​(PLCSO, THCSO, MCSO) corresponding to the main nozzles, the pilot nozzles, and the top hat nozzles included in the primary nozzle group, respectively.

[0072] (7) In another aspect, in any one of the above aspects (1) to (6), the first distribution ratio calculation unit (106) calculates the first distribution ratio (DR1) so that the first distribution ratio (DR1) increases as the first combustion load command value (CLCSO) increases.

[0073] According to the above aspect (7), the first distribution ratio (DR1) is calculated so as to increase as the first combustion load command value (CLCSO) increases.

[0074] (8) In another aspect, in any one of the above aspects (1) to (7), the first combustion load command value calculation unit (104) calculates the first combustion load command value (CLCSO) based on an output of a turbine (6) driven by the combustion gas generated by the gas turbine combustor, and a relationship between the output and the first combustion load command value is learned using operation data of the gas turbine (1).

[0075] According to the aspect (8) above, the first combustion load command value (CLCSO) is calculated based on the output of the gas turbine (1). The relationship between the output of the gas turbine and the first combustion load command value is defined by, for example, a learning model constructed by machine learning using operation data of the gas turbine as learning data. When the calculation accuracy of the first combustion load command value is reduced due to, for example, a change in performance of the gas turbine (aging, etc.), this learning model can be updated by relearning, thereby improving the calculation accuracy of the first combustion load command value.

[0076] (9) A gas turbine combustor control method according to one aspect is a gas turbine combustor control method for controlling a gas turbine combustor (4) including: a combustion liner (21) that defines a combustion chamber (20); a primary nozzle group (22) including a plurality of primary nozzles (23) for injecting a primary fuel (F1) that is a part of a fuel (F) supplied from a fuel supply system (10) into a primary combustion zone (30) of the combustion chamber; and a secondary nozzle group (24) including at least one secondary nozzle (28) for injecting a remaining secondary fuel (F2) of the fuel excluding the primary fuel into a secondary combustion zone (32) that is located downstream of the primary combustion zone in a flow direction of combustion gas in the combustion chamber, the method comprising: calculating a first combustion load command value (CLCSO) corresponding to an outlet-side combustion temperature (T1T) of the secondary combustion zone; and calculating a first allocation ratio (DR1) that is a fuel allocation ratio of the secondary fuel to the fuel based on the first combustion load command value. a step of calculating a second combustion load command value (HECLCSO) corresponding to an outlet-side combustion temperature of the primary combustion zone; and a step of calculating a second distribution ratio (DR2 (DR2 ＨＥＰＬ , DR2 ＨＥＴＨ ) and

[0077] According to the above aspect (9), the fuel (F) supplied from the fuel supply system (10) to the gas turbine combustor (4) is distributed to the primary nozzle group (22) and the secondary nozzle group (24) based on a first distribution ratio (DR1) which is a fuel distribution ratio of the secondary fuel to the fuel. This first distribution ratio (DR1) is calculated based on a first combustion load command value (CLCSO) corresponding to an outlet-side combustion temperature of the secondary combustion zone (32). The primary fuel (F1) distributed to the primary nozzle group is calculated based on a second distribution ratio (DR2) which is a fuel distribution ratio of the primary fuel to the fuel. ＨＥＰＬ , DR2 ＨＥＴＨ)), and is further allocated to a plurality of primary nozzles (23) included in the primary nozzle group (22). The second allocation ratio (DR2) is calculated based on a second combustion load command value (HECLCSO) corresponding to an outlet-side combustion temperature of the primary combustion region (30). Although the second allocation ratio (DR2) is calculated based on the second combustion load command value (HECLCSO) in this manner, the relationship (fx2, fx3) between the second allocation ratio and the second combustion load command value can directly utilize the relationship (fx2', fx3') between the allocation ratio for each nozzle (23) in the single-stage combustion gas turbine combustor (4') having only the primary nozzle group. In other words, in the control of the multi-stage combustion gas turbine combustor (4), by utilizing the allocation ratio between nozzles in the control of the single-stage combustion gas turbine (4') as the allocation ratio for each nozzle included in the primary nozzle group, it is possible to simply set the allocation ratio for each nozzle while suppressing the complexity of the control.

[0078] REFERENCE SIGNS LIST 1 gas turbine 2 compressor 3 inlet guide vane 4 gas turbine combustor 5 generator 6 turbine 9 rotating shaft 10 fuel supply system 12 fuel supply source 14 first distribution unit 16 second distribution unit 20 combustion chamber 21 inner cylinder (combustion cylinder) 22 primary nozzle group 23 primary nozzle 23M main nozzle 23PL pilot nozzle 23TH top hat nozzle 24 secondary nozzle group 25 outer cylinder 28 secondary nozzle 30 primary combustion zone 32 secondary combustion zone 100 gas turbine combustor control device 102 fuel flow rate command value calculation unit 104 first combustion load command value calculation unit 106 first distribution ratio calculation unit 108 secondary fuel flow rate command value calculation unit 110 primary fuel flow rate command value calculation unit 112 second combustion load command value calculation unit 114 second distribution ratio calculation unit 116 Primary nozzle fuel flow command value calculation unit 118 Fuel supply system control unit DR1 First distribution ratio DR2 (DR2 ＨＥＰＬ , DR2 ＨＥＴＨ) Second distribution ratio HET1T Combustion temperature at the outlet of the primary combustion region T1T Combustion temperature at the outlet of the secondary combustion region CLCSO First combustion load command value HECLCSO Second combustion load command value CSO Fuel flow rate command value AFICSO Secondary fuel flow rate command value HECSO Primary fuel flow rate command value MCSO Main fuel flow rate command value PLCSO Pilot fuel flow rate command value THCSO Top hat fuel flow rate command value F Fuel F1 Primary fuel F1M Main fuel F1PL Pilot fuel F1TH Top hat fuel F2 Secondary fuel

Claims

1. A gas turbine combustor control device for controlling a gas turbine combustor comprising: a combustion liner that defines a combustion chamber; a primary nozzle group including a plurality of primary nozzles for injecting a primary fuel that is a part of the fuel supplied from a fuel supply system into a primary combustion zone of the combustion chamber; and a secondary nozzle group including at least one secondary nozzle for injecting a remaining secondary fuel of the fuel excluding the primary fuel into a secondary combustion zone that is located downstream of the primary combustion zone in a flow direction of combustion gas in the combustion chamber, the gas turbine combustor control device comprising: a first combustion load command value calculation unit for calculating a first combustion load command value corresponding to an outlet side combustion temperature of the secondary combustion zone; a first allocation ratio calculation unit for calculating a first allocation ratio that is a fuel allocation ratio of the secondary fuel to the fuel, based on the first combustion load command value; a second combustion load command value calculation unit for calculating a second combustion load command value corresponding to an outlet side combustion temperature of the primary combustion zone; and a second allocation ratio calculation unit for calculating a second allocation ratio that is a fuel allocation ratio of the primary fuel to the fuel, based on the second combustion load command value.

2. The gas turbine combustor control device according to claim 1, wherein said second combustion load command value is calculated based on said first combustion load command value, said first distribution ratio, an distribution ratio of the combustion air supplied to said gas turbine combustor to said second nozzle group, a compressor casing air temperature, and a maximum design value and a minimum design value of the combustion temperature on an outlet side of said secondary combustion zone.

3. The gas turbine combustor control device according to claim 1 or 2, further comprising: a secondary fuel flow rate command value calculation unit for calculating a secondary fuel flow rate command value for the secondary nozzle group, based on a fuel flow rate command value of the fuel and the first distribution ratio; and a primary fuel flow rate command value calculation unit for calculating a primary fuel flow rate command value for the primary nozzle group by subtracting the secondary fuel flow rate command value from the fuel flow rate command value.

4. The gas turbine combustor control device according to claim 3, further comprising a primary nozzle fuel flow rate command value calculation unit for calculating a primary nozzle fuel flow rate command value, which is a fuel distribution ratio among the plurality of primary nozzles, based on the primary fuel flow rate command value and the second distribution ratio.

5. The gas turbine combustor control device according to claim 4, wherein the plurality of primary nozzles include at least one main nozzle, a pilot nozzle, and a top hat nozzle, and the second allocation ratio calculation unit calculates, as the second allocation ratio, a pilot allocation ratio of the primary fuel to the pilot nozzle and a top hat allocation ratio of the primary fuel to the top hat nozzle, respectively.

6. The gas turbine combustor control device according to claim 5, wherein the primary nozzle fuel flow rate command value calculation unit calculates a pilot fuel flow rate command value corresponding to the pilot nozzle, as the primary nozzle fuel flow rate command value, based on the primary fuel flow rate command value and the pilot allocation ratio; calculates a top hat fuel flow rate command value corresponding to the top hat nozzle, as the primary nozzle fuel flow rate command value, based on the primary fuel flow rate command value and the top hat allocation ratio; and calculates a main fuel flow rate command value corresponding to the at least one main nozzle, as the primary nozzle fuel flow rate command value, by subtracting the pilot fuel flow rate command value and the top hat fuel flow rate command value from the fuel flow command value.

7. The gas turbine combustor control device according to claim 1 or 2, wherein the first distribution ratio calculation unit calculates the first distribution ratio so that it increases as the first combustion load command value increases.

8. The gas turbine combustor control device according to claim 1 or 2, wherein the first combustion load command value calculation unit calculates the first combustion load command value based on an output of a turbine driven by the combustion gas generated by the gas turbine combustor, and the relationship between the output and the first combustion load command value is learned using operation data of the gas turbine.

9. A gas turbine combustor control method for controlling a gas turbine combustor comprising: a combustion liner that defines a combustion chamber; a primary nozzle group including a plurality of primary nozzles for injecting primary fuel, which is a part of the fuel supplied from a fuel supply system, into a primary combustion zone in the combustion chamber; and a secondary nozzle group including at least one secondary nozzle for injecting remaining secondary fuel of the fuel excluding the primary fuel, into a secondary combustion zone located downstream of the primary combustion zone in a flow direction of combustion gas in the combustion chamber, the gas turbine combustor control method comprising: a step of calculating a first combustion load command value corresponding to an outlet-side combustion temperature of the secondary combustion zone; a step of calculating a first allocation ratio that is a fuel allocation ratio of the secondary fuel to the fuel, based on the first combustion load command value; a step of calculating a second combustion load command value corresponding to the outlet-side combustion temperature of the primary combustion zone; and a step of calculating a second allocation ratio that is a fuel allocation ratio of the primary fuel to the fuel, based on the second combustion load command value.

Images