Gas turbine system and method for modifying gas turbine system

Abstract

A gas turbine system (100) comprises: a gas turbine (3) including a combustor (32); a first line (L1) for supplying a first fuel (X1) to the combustor (32); a second line (L2) for supplying a second fuel (X2) having a lower flame temperature than the first fuel (X1) to the combustor (32); a first adjuster (A1) for adjusting a first flow rate of the first fuel (X1) flowing into the combustor (32); a second adjuster (A2) for adjusting a second flow rate of the second fuel (X2) flowing into the combustor (32); and a control device (90) communicatively connected to the first adjuster (A1) and the second adjuster (A2). The control device (90) is configured to execute: calculating a flow rate ratio indicating the ratio between the first flow rate and the second flow rate; and controlling the first adjuster (A1) and the second adjuster (A2) on the basis of the flow rate ratio.

Description

Gas turbine system and method for retrofitting a gas turbine system - Patents.com

[0001] This disclosure relates to a gas turbine system and a method for modifying a gas turbine system. This application claims the benefit of priority from Japanese Patent Application No. 2023-198470, filed November 22, 2023, the contents of which are incorporated herein by reference.

[0002] The maximum output of a gas turbine is sometimes set so that the gas temperature at the turbine inlet does not exceed the turbine inlet's heat resistance temperature. However, the gas temperature at the turbine inlet can be very high and difficult to detect. Therefore, for example, Non-Patent Document 1 discloses a method for indirectly determining the gas temperature at the turbine inlet based on the gas temperature at the turbine outlet.

[0003] Masatoshi Kato and two others, "Operation and Control of Gas Turbines," Hitachi Hyoron, March 1969, pp. 62-69

[0004] To promote the use of carbon-neutral fuels, substitution with carbon-free fuels such as ammonia is being considered. The flame temperature of carbon-free fuels may be lower than that of hydrocarbon fuels. Therefore, for example, when such carbon-free fuels are mixed with hydrocarbon fuels in a gas turbine, the temperature of the combustion gases is lower than when only hydrocarbon fuels are burned to achieve the same output. Consequently, the gas temperature at the turbine inlet is also lower. In this case, even if the output of the gas turbine is increased, the gas temperature at the turbine inlet does not exceed the turbine inlet's heat resistance temperature. Therefore, in this case, the maximum output of the gas turbine can be increased compared to when only hydrocarbon fuels are burned. However, in many cases, the same maximum output as when only hydrocarbon fuels are burned is used.

[0005] The present disclosure aims to provide a gas turbine system and a method for retrofitting a gas turbine system that can increase maximum power output.

[0006] A gas turbine system according to one aspect of the present disclosure includes a gas turbine including a combustor; a first line in fluid communication with the combustor for supplying a first fuel to the combustor; a second line in fluid communication with the combustor for supplying a second fuel having a lower flame temperature than the first fuel to the combustor; a first adjuster provided in the first line for adjusting a first flow rate of the first fuel flowing into the combustor; a second adjuster provided in the second line for adjusting a second flow rate of the second fuel flowing into the combustor; and a control device communicatively connected to the first adjuster and the second adjuster, the control device being configured to calculate a flow rate ratio indicating a ratio between the first flow rate and the second flow rate, and control the first adjuster and the second adjuster based on the flow rate ratio.

[0007] Controlling the first adjuster and the second adjuster may include determining a maximum output of the gas turbine based on the flow ratio, obtaining an output of the gas turbine, and controlling the first adjuster and the second adjuster to adjust the first flow rate and the second flow rate so that the obtained output of the gas turbine does not exceed the maximum output.

[0008] The gas turbine system may include a temperature sensor that measures the temperature of the intake air to a compressor of the gas turbine, and the control device may be communicatively connected to the temperature sensor, and determining the maximum output of the gas turbine may include adjusting the maximum output of the gas turbine based on measurement data from the temperature sensor.

[0009] The gas turbine system may include a first analyzer that measures the composition of the first fuel, and the control device may be communicatively connected to the first analyzer, and determining the maximum output of the gas turbine may include adjusting the maximum output of the gas turbine based on measurement data from the first analyzer.

[0010] The gas turbine system may include a second analyzer that measures the composition of the second fuel, and the control device may be communicatively connected to the second analyzer, and determining the maximum output of the gas turbine may include adjusting the maximum output of the gas turbine based on measurement data from the second analyzer.

[0011] According to another aspect of the present disclosure, a method for modifying a gas turbine system includes preparing a program for controlling the gas turbine system, the gas turbine system including: a gas turbine including a combustor; a first line in fluid communication with the combustor for supplying a first fuel to the combustor; a second line in fluid communication with the combustor for supplying a second fuel to the combustor, the second line having a lower flame temperature than the first fuel; a first adjuster provided in the first line for adjusting a first flow rate of the first fuel flowing into the combustor; a second adjuster provided in the second line for adjusting a second flow rate of the second fuel flowing into the combustor; and a controller communicatively connected to the first adjuster and the second adjuster, the program including: preparing a program to cause a computer to execute the program; and installing the program on the controller.

[0012] According to the present disclosure, the maximum output of the gas turbine can be increased.

[0013] Fig. 1 is a schematic diagram showing a gas turbine system according to a first embodiment. Fig. 2 is a flowchart showing an example of processing by a control device. Fig. 3 is a graph showing the relationship between the output of the gas turbine and the gas temperature at the turbine inlet. Fig. 4 is a graph showing an example of processing by the control device. Fig. 5 is a graph showing another example of processing by the control device. Fig. 6 is a graph showing yet another example of processing by the control device. Fig. 7 is a schematic diagram showing a gas turbine system according to a second embodiment.

[0014] Hereinafter, embodiments of the present disclosure will be described in detail with reference to the accompanying drawings. Specific dimensions, materials, numerical values, etc. shown in the embodiments are merely examples for ease of understanding and do not limit the present disclosure unless otherwise specified. In this specification and drawings, elements having substantially the same functions and configurations are designated by the same reference numerals to avoid redundant explanation, and elements not directly related to the present disclosure are not shown.

[0015] FIG. 1 is a schematic diagram showing a gas turbine system 100 according to a first embodiment. In this disclosure, the gas turbine system may also be simply referred to as a "system." For example, the system 100 includes a first tank (first fuel supply source) 1, a second tank (second fuel supply source) 2, a first adjuster A1, a second adjuster A2, a gas turbine 3, a temperature sensor S1, and a control device 90. The system 100 may further include other components. The gas turbine 3 includes a compressor 31, a combustor 32, and a turbine 33. The gas turbine 3 may further include other components.

[0016] The first tank 1 stores the first fuel X1. For example, the first fuel X1 may be a hydrocarbon fuel such as natural gas. The first tank 1 is connected to a first line L1. For example, the first line L1 includes one or more pipes. The first line L1 is connected to the combustor 32. The first tank 1 supplies the first fuel X1 to the combustor 32 via the first line L1. For example, the first line L1 may include a compressor or a pump (not shown) for sending the first fuel X1. For example, in another embodiment, instead of the first tank 1, a device that produces the first fuel may be used as the first fuel supply source.

[0017] The second tank 2 stores the second fuel X2. The second fuel X2 has a lower flame temperature than the first fuel. In the present disclosure, the "flame temperature" may be defined as an "adiabatic flame temperature." For example, the second fuel X2 may be ammonia. For example, the second tank 2 may store liquid ammonia or gaseous ammonia. The second tank 2 is connected to the second line L2. For example, the second line L2 includes one or more pipes. The second line L2 is connected to the combustor 32. The second tank 2 supplies the second fuel X2 to the combustor 32 via the second line L2. For example, the second line L2 may include a compressor or a pump (not shown) for sending the second fuel X2. Furthermore, for example, if the second tank 2 stores liquid ammonia, the second line L2 may be provided with a vaporizer (not shown). For example, in another embodiment, instead of the second tank 2, a device for producing the second fuel may be used as the second fuel supply source.

[0018] The first adjuster A1 is provided in the first line L1 between the first tank 1 and the combustor 32. The first adjuster A1 adjusts the flow rate of the first fuel X1 flowing through the first line L1, i.e., the first flow rate F1 of the first fuel X1 flowing into the combustor 32. For example, the first adjuster A1 may include a flow controller capable of measuring and adjusting the first flow rate F1. Alternatively or additionally, for example, the first adjuster A1 may include a flow meter and at least one valve. The first adjuster A1 is communicatively connected to the control device 90 and transmits measurement data to the control device 90. The control device 90 is configured to adjust the first flow rate F1 by controlling the first adjuster A1.

[0019] The second adjuster A2 is provided in the second line L2 between the second tank 2 and the combustor 32. The second adjuster A2 adjusts the flow rate of the second fuel X2 flowing through the second line L2, i.e., the second flow rate F2 of the second fuel X2 flowing into the combustor 32. For example, the second adjuster A2 may include a flow controller capable of measuring and adjusting the second flow rate F2. Alternatively or additionally, for example, the second adjuster A2 may include a flow meter and at least one valve. The second adjuster A2 is communicatively connected to the control device 90 and transmits measurement data to the control device 90. The control device 90 is configured to adjust the second flow rate F2 by controlling the second adjuster A2.

[0020] The compressor 31 compresses the drawn air (intake air) X3. For example, the air X3 may be ambient air around the compressor 31. The compressed air X3 is supplied to the combustor 32. The combustor 32 combusts a mixed gas containing the first fuel X1 from the first tank 1, the second fuel X2 from the second tank 2, and the air X3 from the compressor 31. Combustion gas X4 from the combustor 32 is supplied to the turbine 33. The compressor 31 and the turbine 33 are connected to each other by a shaft 34.

[0021] As the combustion gas X4 passes through the impeller in the turbine 33, it rotates the impeller together with the shaft 34. For example, the shaft 34 may be connected to a generator (not shown), and the rotational force of the shaft 34 may be used to generate electricity. In other embodiments, the rotational force of the shaft 34 may be used in other devices. Furthermore, the rotational force of the shaft 34 may be used to compress the air X3 in the compressor 31. The combustion gas X4 that has passed through the turbine 33 may be used in various facilities, such as a boiler.

[0022] The temperature sensor S1 measures a temperature T1 of the air X3 drawn into the compressor 31. For example, the temperature sensor S1 may be provided in a pipe connected to the compressor 31. The temperature sensor S1 is communicably connected to the control device 90 and transmits the temperature T1 to the control device 90.

[0023] The control device 90 controls all or part of the system 100. For example, the control device 90 may be configured with one or more PCs. The control device 90 includes components such as a processor 90a, a storage device 90b, and a connector 90c, which are connected to each other via a bus. For example, the processor 90a includes a central processing unit (CPU). For example, the storage device 90b includes a hard disk, a ROM for storing programs, and a RAM as a work area. The control device 90 is connected to each component of the system 100 via the connector 90c so as to be able to communicate with them via wired or wireless communication. For example, the control device 90 may further include other components, such as a display device such as a liquid crystal display or a touch panel, and an input device such as a keyboard, buttons, or a touch panel. For example, the following operations of the control device 90 may be realized by the processor 90a executing a program stored in the storage device 90b.

[0024] Next, the operation of the system 100 will be described.

[0025] 2 is a flowchart showing an example of the processing of the control device 90. For example, the processing shown in FIG.

[0026] The processor 90a calculates the flow rate ratio R (step S100). In the present disclosure, the "flow rate ratio" refers to the ratio between the first flow rate F1 of the first fuel X1 and the second flow rate F2 of the second fuel X2. For example, in the present embodiment, the flow rate ratio R refers to the ratio of the second flow rate F2 to the total flow rate of the first flow rate F1 and the second flow rate F2 (R = F2 / (F1 + F2) × 100(%)). In other embodiments, for example, the flow rate ratio R may refer to the ratio of the first flow rate F1 to the total flow rate of the first flow rate F1 and the second flow rate F2 (R = F1 / (F1 + F2) × 100(%)). The processor 90a can receive the first flow rate F1 and the second flow rate F2 from the first adjuster A1 and the second adjuster A2, respectively.

[0027] The processor 90a controls the first adjuster A1 and the second adjuster A2 based on the flow rate ratio R (step S102), and the operation shown in Fig. 2 is terminated. Specifically, the processor 90a controls the first adjuster A1 and the second adjuster A2 as follows.

[0028] 3 is a graph showing the relationship between the output P of the gas turbine 3 and the gas temperature T2 at the inlet of the turbine 33. In Fig. 3, the horizontal axis represents the output P of the gas turbine 3, and the vertical axis represents the gas temperature T2 at the inlet of the turbine 33, i.e., the temperature of the combustion gas X4 from the combustor 32.

[0029] T0 indicates the heat resistance temperature at the inlet of the turbine 33. For example, the heat resistance temperature T0 may be determined by factors such as the material used at the inlet of the turbine 33. In the turbine 33, the temperature T2 of the combustion gas X4 is highest before passing through the impeller, i.e., at the inlet. Therefore, the heat resistance temperature T0 at the inlet of the turbine 33 is taken into consideration.

[0030] In FIG. 3 , line Y1 indicates the temperature T2 when only the first fuel X1 is burned, i.e., when the flow ratio R is 0 (%). Line Y2 indicates the temperature T2 when the first fuel X1 and the second fuel X2 are mixed and combusted. As described above, the second fuel X2 has a lower adiabatic flame temperature than the first fuel X1. Therefore, when comparing under the same output conditions, the temperature T2 of the combustion gas X4 when the first fuel X1 and the second fuel X2 are mixed and combusted (line Y2) is lower than when only the first fuel X1 is burned (line Y1). In other words, line Y2 is lower than line Y1. In this embodiment, line Y2 decreases (slides downward) as the flow ratio R increases.

[0031] As shown by lines Y1 and Y2, the temperature T2 increases as the power output P increases. The gas turbine 3 must be operated so that the temperature T2 of the combustion gas X4 does not exceed the heat-resistant temperature T0. Therefore, the maximum power output PM1 when only the first fuel X1 is burned can be determined as the point where the line Y1 intersects with the heat-resistant temperature T0. Similarly, the maximum power output PM2 when the first fuel X1 and the second fuel X2 are co-fired can be determined as the point where the line Y2 intersects with the heat-resistant temperature T0.

[0032] As shown in Fig. 3, the maximum output PM2 when the first fuel X1 and the second fuel X2 are mixed and burned can be set higher than the maximum output PM1 when only the first fuel X1 is burned. Therefore, when the second fuel X2, such as ammonia, is used, the maximum output PM2 can be increased compared to when only the first fuel X1, such as natural gas, is burned. The maximum output PM2 varies depending on the flow ratio. Specifically, in this embodiment, the maximum output PM2 increases as the flow ratio R increases.

[0033] For example, the control device 90 may store in the storage device 90b a map indicating the relationship between the flow ratio R and the maximum output PM of the gas turbine 3. For example, the processor 90a may read out the maximum output PM corresponding to the flow ratio R calculated in step S100 from the map. Alternatively or additionally, the control device 90 may store in the storage device 90b an equation indicating the relationship between the flow ratio R and the maximum output PM of the gas turbine 3. For example, the processor 90a may calculate the maximum output PM by substituting the flow ratio R calculated in step S100 into the equation.

[0034] Additionally, the control device 90 may adjust the maximum output PM based on the temperature T1 from the temperature sensor S1. Generally, as the temperature T1 of the air X3 drawn into the compressor 31 increases, the output of the gas turbine 3 decreases, and as the temperature T1 decreases, the output increases. Therefore, for example, the processor 90a may adjust the maximum output PM so that as the temperature T1 increases, the maximum output PM decreases, and as the temperature T1 decreases, the maximum output PM increases.

[0035] For example, the control device 90 may store in the storage device 90b a map indicating the relationship between the flow ratio R, the temperature T1, and the maximum output PM of the gas turbine 3. For example, the processor 90a may read out from the map the maximum output PM corresponding to the flow ratio R calculated in step S100 and the temperature T1 received from the temperature sensor S1. Alternatively or additionally, the control device 90 may store in the storage device 90b an equation indicating the relationship between the flow ratio R, the temperature T1, and the maximum output PM of the gas turbine 3. For example, the processor 90a may calculate the maximum output PM by substituting the flow ratio R calculated in step S100 and the temperature T1 received from the temperature sensor S1 into the equation.

[0036] The processor 90a obtains the current output P of the gas turbine 3. For example, the control device 90 may be communicatively connected to the gas turbine 3, and may calculate the output P of the gas turbine 3 based on various measurement data transmitted from the gas turbine 3. Note that the method of obtaining the output P of the gas turbine 3 is not limited to this.

[0037] The processor 90a controls the first adjuster A1 and the second adjuster A2 to adjust the first flow rate F1 and the second flow rate F2 so that the obtained output P of the gas turbine 3 does not exceed the determined maximum output PM.

[0038] Fig. 4 is a graph showing an example of processing by the control device 90. In Fig. 4 and the following Figs. 5 and 6, the horizontal axis indicates the flow ratio R, the vertical axis indicates the output P of the gas turbine 3, a line Y3 indicates the maximum output PM of the gas turbine 3 determined as described above, and a dashed line Y4 indicates the output P of the gas turbine 3.

[0039] For example, the gas turbine system 100 may be required to operate at a constant flow ratio R1 for various reasons. During this state, the maximum output power PM is also fixed at a constant value. In this case, the processor 90a controls the first adjuster A1 and the second adjuster A2 to adjust the first flow rate F1 and the second flow rate F2 so that the output power P of the gas turbine 3 does not exceed the fixed maximum output power PM and so that the flow ratio R is maintained at the constant value R1.

[0040] FIG. 5 is a graph showing another example of the processing of the control device 90. In FIG.

[0041] For example, the gas turbine system 100 may be required to operate with the first flow rate F1 of the first fuel X1 fixed for various reasons. In this case, only the second flow rate F2 of the second fuel X2 is adjusted. During this state, as shown by dashed line Y4, in this embodiment, the gas turbine output P increases as the flow ratio R increases. In this case, the processor 90a controls only the second adjuster A2 to adjust only the second flow rate F2 so that the flow ratio R does not exceed the value R1 corresponding to the intersection between line Y3 and dashed line Y4.

[0042] FIG. 6 is a graph showing yet another example of the processing of the control device 90. In FIG.

[0043] For example, the gas turbine system 100 may be required to operate with the second flow rate F2 of the second fuel X2 fixed for various reasons. In this case, only the first flow rate F1 of the first fuel X1 is adjusted. During this state, as shown by dashed line Y4, in this embodiment, the gas turbine output P increases as the flow ratio R decreases. In this case, the processor 90a controls only the first adjuster A1 to adjust only the first flow rate F1 so that the flow ratio R does not fall below a value R1 corresponding to the intersection between line Y3 and dashed line Y4.

[0044] The control device 90 may store a compressor map that indicates the relationship between the flow rate of the air X3 and the pressure in the compressor 31 and indicates the boundary line at which surging occurs and the boundary line at which choking occurs. The control device 90 may also store a turbine map that indicates the relationship between the flow rate of the combustion gas X4 and the pressure in the turbine 33 and indicates the boundary line at which choking occurs. The control device 90 may control the system 100 based on these maps so as to prevent surging and choking from occurring.

[0045] The system 100 as described above includes a gas turbine 3 including a combustor 32, a first line L1 fluidly connected to the combustor 32 and configured to supply a first fuel X1 to the combustor 32, a second line L2 fluidly connected to the combustor 32 and configured to supply a second fuel X2 having a lower flame temperature than the first fuel X1 to the combustor 32, a first adjuster A1 provided in the first line L1 and configured to adjust a first flow rate F1 of the first fuel X1 flowing into the combustor 32, a second adjuster A2 provided in the second line L2 and configured to adjust a second flow rate F2 of the second fuel X2 flowing into the combustor 32, and a control device 90 communicatively connected to the first adjuster A1 and the second adjuster A2. The control device 90 is configured to calculate a flow rate ratio R indicating a ratio between the first flow rate F1 and the second flow rate F2, and to control the first adjuster A1 and the second adjuster A2 based on the flow rate ratio R. As described above, the temperature T2 of the combustion gas X4 when the first fuel X1 and the second fuel X2 are mixed and burned is lower than when only the first fuel X1 is burned. Therefore, the maximum output PM2 of the gas turbine 3 when the first fuel X1 and the second fuel X2 are mixed and burned can be set higher than the maximum output PM1 when only the first fuel X1 is burned. Furthermore, the maximum output PM2 varies depending on the flow ratio R. Therefore, by controlling the first adjuster A1 and the second adjuster A2 depending on the flow ratio R, the maximum output PM of the gas turbine 3 can be increased.

[0046] Furthermore, in the system 100, controlling the first adjuster A1 and the second adjuster A2 includes determining the maximum output power PM of the gas turbine 3 based on the flow ratio R, obtaining the output power P of the gas turbine 3, and controlling the first adjuster A1 and the second adjuster A2 to adjust the first flow rate F1 and the second flow rate F2 so that the obtained output power P of the gas turbine 3 does not exceed the maximum output power PM. With this configuration, it is possible to more reliably prevent the current output power P of the gas turbine 3 from exceeding the maximum output power PM.

[0047] The system 100 also includes a temperature sensor S1 that measures the temperature T1 of the intake air X3 to the compressor 31 of the gas turbine 3, and the control device 90 is communicatively connected to the temperature sensor S1, and determining the maximum output PM of the gas turbine 3 includes adjusting the maximum output PM of the gas turbine 3 based on the measurement data from the temperature sensor S1. With this configuration, the maximum output PM can be determined more accurately.

[0048] The system 100 as described above can be realized by the following method for retrofitting an existing gas turbine system. The method for retrofitting a gas turbine system includes preparing a program for controlling the gas turbine system. The gas turbine system to which this method is applied includes: a gas turbine 3 including a combustor 32; a first line L1 fluidly connected to the combustor 32 and supplying a first fuel X1 to the combustor 32; a second line L2 fluidly connected to the combustor 32 and supplying a second fuel X2 having a lower flame temperature than the first fuel X1 to the combustor 32; a first adjuster A1 provided in the first line L1 and adjusting a first flow rate F1 of the first fuel X1 flowing into the combustor 32; a second adjuster A2 provided in the second line L2 and adjusting a second flow rate F2 of the second fuel X2 flowing into the combustor 32; and a control device 90 communicatively connected to the first adjuster A1 and the second adjuster A2. The prepared program is configured to cause the computer to calculate a flow ratio R indicating the ratio between the first flow rate F1 and the second flow rate F2, and to control the first adjuster A1 and the second adjuster A2 based on the flow ratio R. The method includes installing the prepared program in the control device 90. With this configuration, it is possible to increase the maximum output PM of the gas turbine 3 in an existing gas turbine system.

[0049] Next, other embodiments will be described.

[0050] 7 is a schematic diagram showing a gas turbine system 200 according to the second embodiment. The system 200 differs from the system 100 according to the first embodiment in that the system 200 includes a first analyzer S2 and a second analyzer S3. In other respects, the system 200 may be the same as the system 100.

[0051] The first analyzer S2 measures the composition of the first fuel X1. For example, the first analyzer S2 may be provided in the first line L1. In this embodiment, the first analyzer S2 is provided in the first line L1 between the first tank 1 and the first adjuster A1. In other embodiments, the first analyzer S2 may be provided in the first tank 1, or may be provided in the first line L1 between the first adjuster A1 and the combustor 32. For example, the first analyzer S2 may be a calorimeter. The first analyzer S2 is communicatively connected to the control device 90 and transmits measurement data to the control device 90. For example, the control device 90 may calculate a lower heating value (LHV) of the first fuel X1 based on the measurement data of the first fuel X1 from the first analyzer S2, and may calculate a flame temperature of the first fuel X1 from the lower heating value.

[0052] The second analyzer S3 measures the composition of the second fuel X2. For example, the second analyzer S3 may be provided in the second line L2. In this embodiment, the second analyzer S3 is provided in the second line L2 between the second tank 2 and the second adjuster A2. In other embodiments, the second analyzer S3 may be provided in the second tank 2, or may be provided in the second line L2 between the second adjuster A2 and the combustor 32. For example, the second analyzer S3 may be a calorimeter. The second analyzer S3 is communicatively connected to the control device 90 and transmits measurement data to the control device 90. For example, the control device 90 may calculate the lower heating value of the second fuel X2 based on the measurement data of the second fuel X2 from the second analyzer S3, and may calculate the flame temperature of the second fuel X2 from the lower heating value.

[0053] Generally, the flame temperature of a fuel may vary depending on its composition. For example, the composition of the fuel may vary depending on various factors. The flame temperatures of the first fuel X1 and the second fuel X2 affect the temperature T2 of the combustion gas X4. Therefore, the control device 90 may adjust the allowable maximum power PM of the gas turbine 3 in more detail by taking into account the composition of the first fuel X1 and the composition of the second fuel X2.

[0054] For example, the control device 90 may store the reference flame temperatures of the first fuel X1 and the second fuel X2 in the memory device 90b in advance, and may adjust (correct) the maximum output PM based on the ratio between the calculated flame temperatures of the first fuel X1 and the second fuel X2 and the reference flame temperatures of the first fuel X1 and the second fuel X2.

[0055] Furthermore, for example, the control device 90 may store the reference lower heating values ​​of the first fuel X1 and the second fuel X2 in the storage device 90b in advance, and may adjust (correct) the maximum power PM based on the ratio between the calculated lower heating values ​​of the first fuel X1 and the second fuel X2 and the reference lower heating values ​​of the first fuel X1 and the second fuel X2.

[0056] The method of adjusting the maximum output PM based on the measurement data from the first analyzer S2 and the second analyzer S3 is not limited to these.

[0057] The system 200 as described above provides the same effects as the system 100.

[0058] In particular, the system 200 includes a first analyzer S2 that measures the composition of the first fuel X1, the control device 90 is communicatively connected to the first analyzer S2, and determining the maximum output PM of the gas turbine 3 includes adjusting the maximum output PM of the gas turbine 3 based on the measurement data from the first analyzer S2. The system 200 also includes a second analyzer S3 that measures the composition of the second fuel X2, the control device 90 is communicatively connected to the second analyzer S3, and determining the maximum output PM of the gas turbine 3 includes adjusting the maximum output PM of the gas turbine 3 based on the measurement data from the second analyzer S3. These configurations enable the maximum output PM to be determined more accurately.

[0059] Although the embodiments have been described above with reference to the accompanying drawings, the present disclosure is not limited to the above-described embodiments. It is clear that a person skilled in the art can conceive of various modifications or alterations within the scope of the claims, and it is understood that such modifications also fall within the technical scope of the present disclosure.

[0060] For example, in the above embodiment, the control device 90 determines the maximum output PM of the gas turbine 3 based on the flow ratio. In other embodiments, the control device 90 does not need to determine the maximum output PM. In this case, for example, the control device 90 may store in advance in the storage device 90b a map or an equation indicating the relationship between the flow ratio R and the first flow rate F1 and the second flow rate F2 for obtaining the maximum output PM corresponding to the flow ratio R. In this case, the control device 90 does not need to determine the maximum output PM.

[0061] Also, for example, the system 200 includes both the first analyzer S2 and the second analyzer S3. In other embodiments, the system 200 may include only one of the first analyzer S2 and the second analyzer S3.

[0062] The present disclosure provides ２ It can promote the use of ammonia, which leads to reduced emissions, thereby contributing, for example, to Sustainable Development Goal (SDG) 7: "Ensure access to affordable, reliable, sustainable and modern energy."

[0063] 3 Gas turbine 31 Compressor 32 Combustor 90 Control device 100 Gas turbine system 200 Gas turbine system A1 First adjuster A2 Second adjuster F1 First flow rate F2 Second flow rate L1 First line L2 Second line P Gas turbine output PM Maximum output of gas turbine R Flow ratio S1 Temperature sensor S2 First analyzer S3 Second analyzer T1 Intake air temperature X1 First fuel X2 Second fuel X3 Air (intake air)

Claims

1. A gas turbine system comprising: a gas turbine including a combustor; a first line in fluid communication with the combustor, supplying a first fuel to the combustor; a second line in fluid communication with the combustor, supplying a second fuel having a lower flame temperature than the first fuel to the combustor; a first adjuster provided on the first line, adjusting a first flow rate of the first fuel flowing into the combustor; a second adjuster provided on the second line, adjusting a second flow rate of the second fuel flowing into the combustor; and a control device communicatively connected to the first adjuster and the second adjuster, the control device being configured to: calculate a flow ratio indicating a ratio between the first flow rate and the second flow rate; and control the first adjuster and the second adjuster based on the flow ratio.

2. The gas turbine system of claim 1, wherein controlling the first adjuster and the second adjuster comprises: determining a maximum power output of the gas turbine based on the flow ratio; obtaining a power output of the gas turbine; and controlling the first adjuster and the second adjuster to adjust the first flow rate and the second flow rate such that the obtained power output of the gas turbine does not exceed the maximum power output.

3. The gas turbine system according to claim 2, wherein the gas turbine system includes a temperature sensor that measures a temperature of intake air to a compressor of the gas turbine, the control device is communicatively connected to the temperature sensor, and determining a maximum output of the gas turbine includes adjusting a maximum output of the gas turbine based on measurement data from the temperature sensor.

4. The gas turbine system according to claim 2 or 3, wherein the gas turbine system includes a first analyzer that measures a composition of the first fuel, the control device is communicatively connected to the first analyzer, and determining a maximum output of the gas turbine includes adjusting the maximum output of the gas turbine based on measurement data from the first analyzer.

5. The gas turbine system according to claim 2 or 3, wherein the gas turbine system includes a second analyzer that measures a composition of the second fuel, the control device is communicatively connected to the second analyzer, and determining a maximum output of the gas turbine includes adjusting the maximum output of the gas turbine based on measurement data from the second analyzer.

6. The gas turbine system according to claim 4, wherein the gas turbine system includes a second analyzer that measures a composition of the second fuel, the control device is communicatively connected to the second analyzer, and determining a maximum output of the gas turbine includes adjusting a maximum output of the gas turbine based on measurement data from the second analyzer.

7. A method for retrofitting a gas turbine system, comprising: preparing a program for controlling a gas turbine system comprising: a gas turbine including a combustor; a first line in fluid communication with the combustor, supplying a first fuel to the combustor; a second line in fluid communication with the combustor, supplying a second fuel to the combustor, the second fuel having a lower flame temperature than the first fuel; a first adjuster provided in the first line, adjusting a first flow rate of the first fuel flowing into the combustor; a second adjuster provided in the second line, adjusting a second flow rate of the second fuel flowing into the combustor; and a controller communicatively connected to the first adjuster and the second adjuster, the program comprising: preparing a program for controlling a gas turbine system comprising: a gas turbine including a combustor;

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