Gas Turbine Systems

Abstract

A gas turbine system 1 is provided with: an ammonia tank 14; a combustor 13 that is connected to the ammonia tank 14 and that has a combustion chamber 13a; a suction flow channel 41 that is connected to the combustor 13; a compressor 11a that is provided to the suction flow channel 41; a decomposition gas reservoir 17 that is connected to the combustor 13; and an ammonia decomposition catalyst 16 that is provided to a bleed air flow channel 43 connected to the compressor 11a, is provided between the combustor 13 and the compressor 11a in the suction flow channel 41, or is provided in a space connecting the combustion chamber 13a and the suction flow channel 41 in the combustor 13, and that is connected to the ammonia tank 14 and the decomposition gas reservoir 17.

Description

[Technical field]

[0001] This disclosure relates to a gas turbine system. This application claims the benefit of priority to Japanese Patent Application No. 2021-057441, filed on March 30, 2021, the contents of which are incorporated herein by reference. [Background technology]

[0002] Gas turbine systems that obtain power by burning fuel in a combustor are used. For example, as disclosed in Patent Document 1, there is a gas turbine system that uses ammonia as fuel. By using ammonia as fuel, carbon dioxide emissions are suppressed. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] JP 2016-191507 A Summary of the Invention [Problem to be solved by the invention]

[0004] Ammonia is less flammable than other fuels (i.e., it is flame-retardant). Therefore, in combustors using ammonia as fuel, ignition may fail. Even if ignition is successful, there is a risk that some of the fuel may be discharged without being burned.

[0005] An object of the present disclosure is to provide a gas turbine system capable of improving combustibility in a combustor in which ammonia is used as fuel. [Means for solving the problem]

[0006] In order to solve the above problems, a gas turbine system according to the present disclosure includes: 1. A gas turbine system comprising:an ammonia tank; a combustor connected to the ammonia tank and having a combustion chamber; an intake air flow path connected to the combustor; a compressor provided in the intake air flow path; a decomposition gas storage device connected to the combustor; an extraction air flow path connected to the compressor; and an ammonia decomposition catalyst disposed in a space in the intake air flow path between the compressor and the combustor, or in a space in the combustor communicating between the combustion chamber and the intake air flow path, and connected to the ammonia tank and the decomposition gas storage device; Gas Turbine System During operation, it is determined whether the temperature of the ammonia decomposition catalyst is equal to or higher than a reference temperature, and when the temperature of the ammonia decomposition catalyst is equal to or higher than the reference temperature, ammonia is supplied from the ammonia tank to the ammonia decomposition catalyst. During operation of the gas turbine system, the amount of ammonia supplied from the ammonia tank to the ammonia decomposition catalyst is controlled so that the pressure in the cracked gas storage tank becomes a reference pressure, and when the pressure in the cracked gas storage tank is lower than the reference pressure, the gas turbine system is not stopped and the supply of ammonia from the ammonia tank to the ammonia decomposition catalyst is continued, and when the pressure in the cracked gas storage tank becomes equal to or higher than the reference pressure, the gas turbine system is stopped, and when the gas turbine system is started, the supply of cracked gas from the cracked gas storage tank to the combustor is started, and thereafter, the supply of ammonia from the ammonia tank to the combustor is started. .

[0007] A cooling device may be provided in the flow path connecting the ammonia decomposition catalyst and the decomposition gas reservoir.

[0008] The cooling device may be a heat exchanger provided in a flow path connecting the ammonia decomposition catalyst and the decomposition gas reservoir, and the flow path connecting the ammonia tank and the ammonia decomposition catalyst may pass through the heat exchanger.

[0009] A first flow control valve may be provided in a flow path connecting the ammonia tank and the ammonia decomposition catalyst, and a control device may be provided that controls the first flow control valve so that ammonia is supplied from the ammonia tank to the ammonia decomposition catalyst during operation of the gas turbine system.

[0010] A second flow control valve is provided in a flow path connecting the cracked gas storage device and the combustor, and a third flow control valve is provided in a flow path connecting the ammonia tank and the combustor, and the control device may control the second flow control valve and the third flow control valve so that, at startup of the gas turbine system, the supply of ammonia from the ammonia tank to the combustor starts after the supply of cracked gas from the cracked gas storage device to the combustor starts. Effect of the Invention

[0011] According to the present disclosure, it is possible to improve combustibility in a combustor using ammonia as fuel. [Brief description of the drawings]

[0012] [Figure 1] FIG. 1 is a schematic diagram showing a configuration of a gas turbine system according to an embodiment of the present disclosure. [Diagram 2] FIG. 2 is a flowchart illustrating an example of a flow of processing performed by the control device according to the embodiment of the present disclosure. [Diagram 3] FIG. 3 is a schematic diagram showing the configuration of a gas turbine system according to a first modified example. [Figure 4] FIG. 4 is a schematic diagram showing the configuration of a gas turbine system according to a second modified example. [Diagram 5] FIG. 5 is a schematic diagram showing the configuration of a gas turbine system according to a third modified example. [Figure 6] FIG. 6 is a schematic diagram showing the configuration of a gas turbine system according to a fourth modified example. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0013] Hereinafter, an embodiment of the present disclosure will be described with reference to the accompanying drawings. The dimensions, materials, and other specific numerical values ​​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 given the same reference numerals to avoid repeated explanations, and elements not directly related to the present disclosure are not illustrated.

[0014] Fig. 1 is a schematic diagram showing the configuration of a gas turbine system 1 according to this embodiment. As shown in Fig. 1, the gas turbine system 1 includes a turbocharger 11, a generator 12, a combustor 13, an ammonia tank 14, a pump 15, an ammonia decomposition catalyst 16, a decomposition gas storage tank 17, a first flow control valve 21, a second flow control valve 22, a third flow control valve 23, a steam extraction valve 24, and a control device 31.

[0015] Of the gas turbine system 1, the combustor 13, the ammonia tank 14, the pump 15, the ammonia decomposition catalyst 16, the decomposition gas storage tank 17, the first flow control valve 21, the second flow control valve 22, the third flow control valve 23, and the control device 31 are included in the combustion device 10.

[0016] The turbocharger 11 includes a compressor 11a and a turbine 11b. The compressor 11a and the turbine 11b rotate as a unit. The compressor 11a and the turbine 11b are connected to each other by a shaft.

[0017] The compressor 11a is provided in an intake passage 41 that is connected to the combustor 13. Air to be supplied to the combustor 13 flows through the intake passage 41. An intake port (not shown) through which air is taken in from the outside is provided at the upstream end of the intake passage 41. The air taken in from the intake port passes through the compressor 11a and is sent to the combustor 13. The compressor 11a compresses the air and discharges it downstream.

[0018] The turbine 11b is provided in an exhaust flow path 42 that is connected to the combustor 13. Exhaust gas discharged from the combustor 13 flows through the exhaust flow path 42. An exhaust port (not shown) through which the exhaust gas is discharged to the outside is provided at the downstream end of the exhaust flow path 42. The exhaust gas discharged from the combustor 13 passes through the turbine 11b and is sent to the exhaust port. The turbine 11b is rotated by the exhaust gas to generate rotational power.

[0019] In this embodiment, an air bleed flow passage 43 is connected to the compressor 11a. A portion of the air compressed by the compressor 11a is extracted and circulates through the air bleed flow passage 43. A bleed valve 24 is provided in the air bleed flow passage 43. The bleed valve 24 adjusts the flow rate of air (i.e., bleed air) flowing through the air bleed flow passage 43. The opening degree of the bleed valve 24 is adjusted, thereby adjusting the flow rate of bleed air flowing through the air bleed flow passage 43. The opening degree of the bleed valve 24 is controlled based on, for example, a required load. However, the bleed valve 24 does not necessarily have to be provided in the air bleed flow passage 43.

[0020] The bleed air that has flowed through the bleed air passage 43 is discharged to the outside, for example, from an exhaust port (not shown). However, since the bleed air that has flowed through the bleed air passage 43 is cooled by heat exchange with the ammonia decomposition catalyst 16 as described later, it may be used to cool the exhaust gas that flows into the turbine 11b or the turbine 11b itself.

[0021] The generator 12 is connected to the turbocharger 11. The generator 12 generates electricity using the rotational power generated by the turbocharger 11.

[0022] Ammonia is used as fuel and combusted in the combustor 13. As described later, fuel other than ammonia (for example, decomposition gas as ignition fuel, described later) is also used at the start of the gas turbine system 1 (i.e., at the start of the combustion device 10) or the like.

[0023] The combustor 13 has a combustion chamber 13a and an ignition device 13b. Air compressed by the compressor 11a is supplied to the combustion chamber 13a from the intake passage 41. Fuel is supplied to the combustion chamber 13a. For example, liquid ammonia is supplied as fuel from an ammonia tank 14 to the combustion chamber 13a (specifically, sprayed). In the combustion chamber 13a, an air-fuel mixture containing fuel and air is generated. The ignition device 13b ignites the air-fuel mixture in the combustion chamber 13a. For example, the ignition device 13b is provided inside the combustion chamber 13a. Exhaust gas generated by combustion in the combustion chamber 13a is discharged to the exhaust passage 42.

[0024] Liquid ammonia is stored in the ammonia tank 14. The ammonia tank 14 is connected to each of the combustor 13 and the ammonia decomposition catalyst 16. This makes it possible to supply ammonia from the ammonia tank 14 to each of the combustor 13 and the ammonia decomposition catalyst 16.

[0025] A flow path 44 is connected to the ammonia tank 14. A flow path 45 and a flow path 46 are connected to the downstream end of the flow path 44. The flow path 45 is connected to the combustor 13. That is, the ammonia tank 14 is connected to the combustor 13 via the flow path 44 and the flow path 45. Liquid ammonia is supplied from the ammonia tank 14 to the combustor 13 (specifically, the combustion chamber 13a) via the flow path 44 and the flow path 45. The flow path 46 is connected to the ammonia decomposition catalyst 16. That is, the ammonia tank 14 is connected to the ammonia decomposition catalyst 16 via the flow path 44 and the flow path 46. Liquid ammonia is supplied from the ammonia tank 14 to the ammonia decomposition catalyst 16 via the flow path 44 and the flow path 46.

[0026] The flow path 44 is provided with a pump 15. The pump 15 delivers ammonia supplied from the ammonia tank 14 to the downstream side. The ammonia delivered by the pump 15 passes through the flow path 44 and is sent to the flow paths 45 and 46.

[0027] A third flow control valve 23 is provided in the flow path 45. The third flow control valve 23 controls (i.e., adjusts) the flow rate of ammonia flowing through the flow path 45. That is, the third flow control valve 23 adjusts the amount of ammonia supplied from the ammonia tank 14 to the combustor 13. By adjusting the opening degree of the third flow control valve 23, the amount of ammonia supplied from the ammonia tank 14 to the combustor 13 is adjusted.

[0028] A first flow control valve 21 is provided in the flow path 46. The first flow control valve 21 controls (i.e., adjusts) the flow rate of ammonia flowing through the flow path 46. In other words, the first flow control valve 21 adjusts the amount of ammonia supplied from the ammonia tank 14 to the ammonia decomposition catalyst 16. By adjusting the opening degree of the first flow control valve 21, the amount of ammonia supplied from the ammonia tank 14 to the ammonia decomposition catalyst 16 is adjusted.

[0029] The ammonia decomposition catalyst 16 is a catalyst that decomposes ammonia and generates decomposition gas. The ammonia decomposition catalyst 16 decomposes ammonia into hydrogen and nitrogen. That is, the decomposition gas contains hydrogen and nitrogen. Note that the decomposition gas may contain undecomposed ammonia in addition to hydrogen and nitrogen. The decomposition of ammonia by the ammonia decomposition catalyst 16 is actively carried out when the temperature of the ammonia decomposition catalyst 16 is equal to or higher than a reference temperature (e.g., about 400°C to 500°C). That is, when the temperature of the ammonia decomposition catalyst 16 is equal to or higher than the reference temperature, the ammonia decomposition catalyst 16 enters a state in which the decomposition of ammonia is actively carried out.

[0030] In this embodiment, the ammonia decomposition catalyst 16 is disposed in the bleed air passage 43. In detail, heat exchange is possible between the ammonia decomposition catalyst 16 and the bleed air in the bleed air passage 43 in a state where the internal space of the ammonia decomposition catalyst 16 and the bleed air in the bleed air passage 43 are not in communication with each other. The bleed air flowing through the bleed air passage 43 is air compressed by the compressor 11a and is therefore at a high temperature (for example, 400°C or higher). Therefore, during operation of the gas turbine system 1 (i.e., during operation of the combustion device 10), the ammonia decomposition catalyst 16 is heated by the bleed air flowing through the bleed air passage 43 to a temperature at which ammonia is actively decomposed (i.e., a temperature equal to or higher than a reference temperature).

[0031] A temperature sensor 16a is provided in the ammonia decomposition catalyst 16. The temperature sensor 16a detects the temperature of the ammonia decomposition catalyst 16.

[0032] The cracked gas reservoir 17 stores the cracked gas. The cracked gas reservoir 17 is connected to the ammonia decomposition catalyst 16 via a flow path 47. The cracked gas generated by decomposition by the ammonia decomposition catalyst 16 is sent to the cracked gas reservoir 17 via the flow path 47. Note that the flow path 47 may be provided with a check valve, a shutoff valve, or the like for preventing backflow of the cracked gas from the cracked gas reservoir 17 to the ammonia decomposition catalyst 16.

[0033] The decomposition gas reservoir 17 is provided with a pressure sensor 17a. The pressure sensor 17a detects the pressure inside the decomposition gas reservoir 17.

[0034] The cracked gas reservoir 17 is connected to the combustor 13 via a flow path 48. The cracked gas is supplied from the cracked gas reservoir 17 via the flow path 48 to the combustor 13 (specifically, the combustion chamber 13a).

[0035] The flow path 48 is provided with a second flow control valve 22. The second flow control valve 22 controls (i.e., adjusts) the flow rate of the cracked gas flowing through the flow path 48. That is, the second flow control valve 22 adjusts the amount of cracked gas supplied from the cracked gas reservoir 17 to the combustor 13. By adjusting the opening degree of the second flow control valve 22, the amount of cracked gas supplied from the cracked gas reservoir 17 to the combustor 13 is adjusted.

[0036] The control device 31 includes a central processing unit (CPU), a ROM in which programs and the like are stored, a RAM as a work area, and the like, and controls the entire gas turbine system 1. For example, the control device 31 controls the ignition device 13b, the pump 15, the first flow control valve 21, the second flow control valve 22, and the third flow control valve 23. The control device 31 also acquires detection results from the temperature sensor 16a and the pressure sensor 17a.

[0037] Fig. 2 is a flowchart showing an example of the flow of processing performed by the control device 31. The processing flow shown in Fig. 2 is executed, for example, when a user performs an input operation to start up the gas turbine system 1. The input operation by the user is accepted, for example, by the control device 31.

[0038] 2 starts, in step S101, the control device 31 determines whether or not a startup condition is satisfied. The startup condition is a condition for permitting startup of the gas turbine system 1. For example, the startup condition is that no abnormality occurs in each device of the gas turbine system 1 (for example, that there is no abnormal value in the output value output from each device, or that there is no fluid leakage in each flow path, etc.).

[0039] If it is determined that the start-up conditions are met (step S101 / YES), the process proceeds to step S102. On the other hand, if it is determined that the start-up conditions are not met (step S101 / NO), the process proceeds to step S111, where the gas turbine system 1 is shut down, as described below.

[0040] If the determination in step S101 is YES, in step S102, the control device 31 causes the ignition device 13b to perform ignition. Next, in step S103, the control device 31 causes the supply of the cracked gas from the cracked gas storage device 17 to the combustor 13 to start. Specifically, the control device 31 controls the second flow control valve 22 so that the supply of the cracked gas from the cracked gas storage device 17 to the combustor 13 starts. That is, the control device 31 opens the second flow control valve 22 that is closed.

[0041] As described later, in the gas turbine system 1, during operation of the gas turbine system 1, cracked gas is generated by the ammonia decomposition catalyst 16, and the generated cracked gas is stored in the cracked gas storage vessel 17. Therefore, at the start of the process flow shown in Fig. 2, the cracked gas is stored in advance in the cracked gas storage vessel 17. However, at the initial startup of the gas turbine system 1, the cracked gas is stored in advance in the cracked gas storage vessel 17 by another method.

[0042] As described above, in this embodiment, when the gas turbine system 1 is started up, ignition is performed in a state in which the cracked gas is supplied to the combustor 13. That is, the cracked gas is used as a fuel for ignition. Unlike ammonia, hydrogen contained in the cracked gas is easily combusted and is therefore easily ignited. Therefore, ignition failure is suppressed and the reliability of ignition is improved.

[0043] Next, in step S104, the control device 31 determines whether or not the ignition is successful. If it is determined that the ignition is successful (step S104 / YES), the process proceeds to step S105. On the other hand, if it is determined that the ignition is not successful (step S104 / NO), the process proceeds to step S111, where the gas turbine system 1 is stopped, as described below.

[0044] If the determination in step S104 is YES, in step S105, the control device 31 increases the supply amount of the cracked gas. Specifically, the control device 31 controls the second flow control valve 22 so as to increase the supply amount of the cracked gas from the cracked gas storage device 17 to the combustor 13. That is, the control device 31 increases the opening degree of the second flow control valve 22. For example, the control device 31 increases the supply amount of the cracked gas from the cracked gas storage device 17 to the combustor 13 so that it changes according to a preset trend.

[0045] Next, in step S106, the control device 31 determines whether the supply amount of the cracked gas has reached a reference supply amount. For example, the reference supply amount is set to a value at which the combustibility in the combustor 13 is maintained at a predetermined level or higher even if the supply of ammonia to the combustor 13 is started (that is, at which the occurrence of a situation where a part of the ammonia is not combusted is suppressed).

[0046] When it is determined that the supply amount of the cracked gas has reached the reference supply amount (step S106 / YES), the control device 31 determines that the combustibility in the combustor 13 will be maintained at or above a predetermined level even if the supply of ammonia to the combustor 13 is started, and proceeds to step S107. On the other hand, when it is determined that the supply amount of the cracked gas has not reached the reference supply amount (step S106 / NO), the control device 31 determines that the combustibility in the combustor 13 will fall below the predetermined level if the supply of ammonia to the combustor 13 is started, and returns to step S105.

[0047] When the determination in step S106 is YES, in step S107, the control device 31 permits the supply of ammonia from the ammonia tank 14 to the combustor 13. That is, when the required output of the gas turbine system 1 is equal to or greater than the reference output, the control device 31 starts the supply of ammonia from the ammonia tank 14 to the combustor 13. In this case, the control device 31 drives the pump 15 and controls the third flow control valve 23 so as to start the supply of ammonia from the ammonia tank 14 to the combustor 13. That is, the control device 31 opens the third flow control valve 23 that is closed. This starts combustion using ammonia as fuel. Note that when the required output of the gas turbine system 1 is smaller than the reference output, the supply of ammonia from the ammonia tank 14 to the combustor 13 is not necessary.

[0048] In the gas turbine system 1, the cracked gas is supplied to the combustor 13, and combustion using ammonia as fuel is started in a state in which the combustibility is maintained at a predetermined level or higher. That is, the cracked gas is used as a fuel for supporting combustion (i.e., a fuel for supporting combustion). This suppresses the occurrence of a situation in which a portion of the ammonia does not burn. After the supply of ammonia to the combustor 13 is started, the control device 31 may continue or stop the supply of the cracked gas to the combustor 13.

[0049] Next, in step S108, the control device 31 determines whether or not a decomposed gas generation condition is satisfied. The decomposed gas generation condition is a condition for permitting the generation of decomposed gas (i.e., decomposition of ammonia) by the ammonia decomposition catalyst 16. For example, the decomposed gas generation condition is that the temperature of the ammonia decomposition catalyst 16 is equal to or higher than a reference temperature (i.e., a temperature at which the decomposition of ammonia is actively performed in the ammonia decomposition catalyst 16).

[0050] If it is determined that the decomposed gas generation condition is satisfied (step S108 / YES), the process proceeds to step S109. On the other hand, if it is determined that the decomposed gas generation condition is not satisfied (step S108 / NO), the process proceeds to step S110 without executing step S109.

[0051] When the determination in step S108 is YES, in step S109, the control device 31 supplies ammonia from the ammonia tank 14 to the ammonia decomposition catalyst 16. Specifically, the control device 31 controls the first flow control valve 21 so that ammonia is supplied from the ammonia tank 14 to the ammonia decomposition catalyst 16. That is, the control device 31 opens the first flow control valve 21 that is closed. As a result, ammonia is decomposed in the ammonia decomposition catalyst 16 to generate decomposition gas. Then, the generated decomposition gas is sent to the decomposition gas storage tank 17, and the pressure in the decomposition gas storage tank 17 increases.

[0052] In step S109, the control device 31 controls the amount of ammonia supplied to the ammonia decomposition catalyst 16 by the first flow control valve 21 so that the pressure in the cracked gas storage tank 17 becomes the reference pressure. Such control of the amount of ammonia supplied to the ammonia decomposition catalyst 16 (specifically, control of the aperture of the first flow control valve 21) is specifically realized by feedback control. The reference pressure is an index for determining whether or not the amount of cracked gas required as the amount of cracked gas used until the supply of ammonia to the combustor 13 is started (hereinafter, also simply referred to as the required amount) is stored in the cracked gas storage tank 17. For example, when the pressure in the cracked gas storage tank 17 is lower than the reference pressure, this corresponds to a case where the required amount of cracked gas is not stored in the cracked gas storage tank 17.

[0053] Next, in step S110, the control device 31 determines whether or not a stop condition is satisfied. The stop condition is a condition for permitting the stop of the gas turbine system 1. For example, the stop condition is that there is no longer a demand for power generation and the pressure in the cracked gas storage tank 17 is equal to or higher than a reference pressure.

[0054] If it is determined that the stop condition is satisfied (step S110 / YES), the process proceeds to step S111. On the other hand, if it is determined that the stop condition is not satisfied (step S110 / NO), the process returns to step S108.

[0055] When the determination in step S110 is YES, in step S111, the control device 31 stops the gas turbine system 1, and the process flow shown in Fig. 2 ends. Specifically, the control device 31 stops the supply of ammonia to the combustor 13, the supply of decomposition gas to the combustor 13, and the supply of ammonia to the ammonia decomposition catalyst 16, thereby stopping the gas turbine system 1.

[0056] As described above, when the pressure in the cracked gas storage tank 17 is lower than the reference pressure, the control device 31 does not shut down the gas turbine system 1, but continues the supply of ammonia from the ammonia tank 14 to the ammonia decomposition catalyst 16. This allows the gas turbine system 1 to be shut down after the pressure in the cracked gas storage tank 17 has recovered to the reference pressure or higher.

[0057] As described above, in the gas turbine system 1, the ammonia decomposition catalyst 16 is disposed in the extraction air passage 43. As a result, the ammonia decomposition catalyst 16 is heated by the extraction air flowing through the extraction air passage 43 to a temperature at which ammonia decomposition is actively performed (i.e., a temperature equal to or higher than the reference temperature). In this manner, the ammonia decomposition catalyst 16 is heated by effectively utilizing the heat of the air compressed by the compressor 11a. Therefore, the ammonia decomposition catalyst 16 is heated without using a dedicated heater.

[0058] Furthermore, in the gas turbine system 1, the ammonia decomposition catalyst 16 is connected to the combustor 13 via a cracked gas storage device 17. As a result, during operation of the gas turbine system 1, the ammonia decomposition catalyst 16 decomposes ammonia to generate cracked gas, and the cracked gas can be stored in the cracked gas storage device 17. Then, at the next startup of the gas turbine system 1, ignition is performed using the cracked gas stored in the cracked gas storage device 17, thereby making it possible to suppress ignition failures and improve the reliability of ignition.

[0059] As described above, according to the gas turbine system 1, the combustibility in the combustor 13 can be improved.

[0060] In particular, the control device 31 controls the first flow control valve 21 so that ammonia is supplied from the ammonia tank 14 to the ammonia decomposition catalyst 16 during operation of the gas turbine system 1 (i.e., during operation of the combustion device 10). This appropriately realizes the ammonia decomposition catalyst 16 generating decomposition gas and storing the decomposition gas in the decomposition gas storage device 17 during operation of the gas turbine system 1.

[0061] In particular, the control device 31 controls the second flow control valve 22 and the third flow control valve 23 so that, at the start of the gas turbine system 1 (i.e., at the start of the combustion device 10), the supply of the cracked gas from the cracked gas storage device 17 to the combustor 13 starts, and then the supply of ammonia from the ammonia tank 14 to the combustor 13 starts. As a result, at the start of the gas turbine system 1, the cracked gas is used as fuel for ignition, and it is possible to appropriately suppress ignition failure in the combustor 13 and improve the reliability of ignition.

[0062] Hereinafter, gas turbine systems according to each modification will be described with reference to Fig. 3 to Fig. 6. In the gas turbine systems according to each modification described below, the processing performed by the control device 31 is similar to that of the gas turbine system 1 described above, and therefore description thereof will be omitted.

[0063] Fig. 3 is a schematic diagram showing a configuration of a gas turbine system 1A according to a first modified example. As shown in Fig. 3, the gas turbine system 1A according to the first modified example is different from the gas turbine system 1 described above in that a heat exchanger 51 is provided in the flow path 47, and the flow path 46 passes through the heat exchanger 51.

[0064] In the first modified example, of the gas turbine system 1A, the combustor 13, the ammonia tank 14, the pump 15, the ammonia decomposition catalyst 16, the decomposition gas storage tank 17, the first flow control valve 21, the second flow control valve 22, the third flow control valve 23, the control device 31, and the heat exchanger 51 are included in the combustion device 10A.

[0065] As described above, the flow path 47 connects the ammonia decomposition catalyst 16 and the decomposition gas storage tank 17. The heat exchanger 51 is provided in the flow path 47. As described above, the flow path 46 connects the ammonia tank 14 and the ammonia decomposition catalyst 16. The flow path 46 passes through the heat exchanger 51.

[0066] In the heat exchanger 51, heat is exchanged between the cracked gas flowing through the flow path 47 and the ammonia flowing through the flow path 46. The temperature of the cracked gas flowing through the flow path 47 is higher than the temperature of the ammonia flowing through the flow path 46. Therefore, in the heat exchanger 51, heat is transferred from the cracked gas flowing through the flow path 47 to the ammonia flowing through the flow path 46. Thus, the cracked gas flowing through the flow path 47 is cooled. In this manner, the heat exchanger 51 corresponds to a cooling device that cools the cracked gas flowing through the flow path 47.

[0067] The temperature of the cracked gas sent to the cracked gas storage tank 17 is high (for example, about 400°C). However, the temperature of the cracked gas in the cracked gas storage tank 17 decreases between the time when the gas turbine system 1 is stopped and the time when it is next started. The greater the amount of decrease in the temperature of the cracked gas in the cracked gas storage tank 17, the greater the decrease in the pressure in the cracked gas storage tank 17.

[0068] In the gas turbine system 1A, a cooling device (specifically, a heat exchanger 51) is provided in the flow path 47 connecting the ammonia decomposition catalyst 16 and the cracked gas storage tank 17. This makes it possible to lower the temperature of the cracked gas sent to the cracked gas storage tank 17. Therefore, the amount of decrease in the temperature of the cracked gas in the cracked gas storage tank 17 from when the gas turbine system 1 is stopped to when it is next started can be reduced, and therefore the decrease in pressure in the cracked gas storage tank 17 can be suppressed. This makes it possible to make the pressure in the cracked gas storage tank 17 higher than the pressure in the combustion chamber 13a, and therefore the cracked gas can be appropriately supplied from the cracked gas storage tank 17 to the combustor 13.

[0069] In the above, an example has been described in which the heat exchanger 51 through which the flow passage 46 passes is provided in the flow passage 47 as a cooling device. However, the cooling device provided in the flow passage 47 is not limited to the heat exchanger 51. For example, a device that cools the cracked gas flowing through the flow passage 47 with cooling water or air may be provided in the flow passage 47 as a cooling device.

[0070] Fig. 4 is a schematic diagram showing a configuration of a gas turbine system 1B according to a second modified example. As shown in Fig. 4, the gas turbine system 1B according to the second modified example is different from the gas turbine system 1 described above in that a heat exchanger 52 and a heat exchanger 53 are provided in the exhaust flow path 42, and the flow path 49 passes through the heat exchangers 52 and 53.

[0071] In the second modified example, the combustor 13, the ammonia tank 14, the pump 15, the ammonia decomposition catalyst 16, the decomposition gas storage device 17, the first flow control valve 21, the second flow control valve 22, the third flow control valve 23, and the control device 31 of the gas turbine system 1B are included in the combustion device 10B.

[0072] Water flows through the flow path 49. Although the flow path 49 is shown in a simplified manner in FIG. 4, the flow path 49 is a closed circuit. In other words, water circulates through the flow path 49. A turbine (not shown) is provided in the flow path 49, and power is obtained by the turbine using the flow of water (specifically, water vapor). The flow path 49, the heat exchanger 52, the heat exchanger 53, and the turbine (not shown) are included in a system separate from the gas turbine system 1B.

[0073] Heat exchanger 52 is provided downstream of heat exchanger 53 in exhaust flow path 42. Heat exchanger 52 is provided upstream of heat exchanger 53 in flow path 49. In heat exchanger 52, liquid water flowing through flow path 49 is heated by exhaust gas flowing through exhaust flow path 42. Then, in heat exchanger 53, the heated liquid water is heated again by exhaust gas flowing through exhaust flow path 42 and vaporized into gas (i.e., water vapor). Then, a turbine (not shown) is rotated by the water vapor, generating rotational power.

[0074] As described above, the gas turbine system 1B shares a part with another system. Note that the configuration and use of the other system that shares a part with the gas turbine system 1B are not limited to the above example. Even in such a case, the same effects as those of the gas turbine system 1 described above can be achieved.

[0075] Fig. 5 is a schematic diagram showing a configuration of a gas turbine system 1C according to a third modified example. As shown in Fig. 5, the gas turbine system 1C according to the third modified example is different from the gas turbine system 1 described above in that the extraction passage 43 is not provided and the installation position of the ammonia decomposition catalyst 16 is different.

[0076] In the third modified example, the combustor 13, the ammonia tank 14, the pump 15, the ammonia decomposition catalyst 16, the decomposition gas storage device 17, the first flow control valve 21, the second flow control valve 22, the third flow control valve 23, and the control device 31 of the gas turbine system 1C are included in a combustion device 10C.

[0077] In the gas turbine system 1C, the ammonia decomposition catalyst 16 is disposed in the intake air passage 41 between the compressor 11a and the combustor 13. In detail, in a state where the internal space of the ammonia decomposition catalyst 16 and the intake air passage 41 are not in communication with each other, heat exchange is possible between the ammonia decomposition catalyst 16 and the air in the intake air passage 41. The air flowing through the intake air passage 41 downstream of the compressor 11a is compressed by the compressor 11a and is therefore at a high temperature (for example, 400°C or higher). Therefore, during operation of the gas turbine system 1C (i.e., during operation of the combustion device 10C), the ammonia decomposition catalyst 16 is heated by the air flowing through the intake air passage 41 to a temperature at which ammonia decomposition is actively performed (i.e., a temperature equal to or higher than a reference temperature).

[0078] As described above, in the gas turbine system 1C, the ammonia decomposition catalyst 16 is disposed between the compressor 11a and the combustor 13 in the intake air flow path 41, unlike the above-described gas turbine system 1. Even in this case, the ammonia decomposition catalyst 16 is heated by effectively utilizing the heat of the air compressed by the compressor 11a, as in the above-described gas turbine system 1. Therefore, the same effects as those of the above-described gas turbine system 1 are achieved.

[0079] The air supplied from the compressor 11a to the combustor 13 is used to cool the members forming the combustion chamber 13a of the combustor 13 (specifically, the liner 13d in FIG. 6, which will be described later, and the like). In the combustion device 10C of the gas turbine system 1C, the temperature of the air supplied from the compressor 11a to the combustor 13 is lowered by heat exchange between the air and the ammonia decomposition catalyst 16. Therefore, the temperature of the air reaching the members forming the combustion chamber 13a of the combustor 13 is also lowered. Therefore, the members forming the combustion chamber 13a of the combustor 13 can be effectively cooled.

[0080] Fig. 6 is a schematic diagram showing a configuration of a gas turbine system 1D according to a fourth modified example. As shown in Fig. 6, in the gas turbine system 1D according to the fourth modified example, the installation position of the ammonia decomposition catalyst 16 is different from that of the gas turbine system 1 described above.

[0081] 6 illustrates only the combustor 13 and its peripheral components in the gas turbine system 1D. However, the components of the gas turbine system 1D are similar to those of the above-described gas turbine system 1 except that the ammonia decomposition catalyst 16 is installed at a different position.

[0082] In the fourth modified example, of the gas turbine system 1D, the combustor 13, the ammonia tank 14, the pump 15, the ammonia decomposition catalyst 16, the decomposition gas storage device 17, the first flow control valve 21, the second flow control valve 22, the third flow control valve 23, and the control device 31 are included in the combustion device 10D.

[0083] In the gas turbine system 1D, the ammonia decomposition catalyst 16 is disposed in a space S in the combustor 13, which communicates the combustion chamber 13a with the intake air flow path 41. In detail, heat exchange is possible between the ammonia decomposition catalyst 16 and the air in the space S in a state where the internal space of the ammonia decomposition catalyst 16 and the space S are not in communication. The combustor 13 has a casing 13c, a liner 13d, and a burner 13e in addition to the above-mentioned combustion chamber 13a and ignition device 13b.

[0084] The casing 13c has a substantially cylindrical shape. A liner 13d is provided inside the casing 13c. The liner 13d has a substantially cylindrical shape. The liner 13d is arranged coaxially with the casing 13c. A combustion chamber 13a is formed inside the liner 13d. That is, the internal space of the liner 13d corresponds to the combustion chamber 13a. The exhaust passage 42 is connected to the combustion chamber 13a. An ignition device 13b is provided on the inner periphery of the liner 13d. An opening is formed at the end of the liner 13d (the end on the left side in FIG. 6). A burner 13e is inserted into the opening at the end of the liner 13d. A passage 45 and a passage 48 are connected to the burner 13e. Ammonia is sent to the burner 13e via the passage 45. Decomposition gas is sent to the burner 13e via the passage 48. The burner 13e faces the combustion chamber 13a. Ammonia and decomposition gas are injected into the combustion chamber 13a from the burner 13e.

[0085] A space S is formed between the inner surface of the casing 13c and the outer surface of the liner 13d. An intake air passage 41 is connected to the space S. Air is sent from the compressor 11a to the space S through the intake air passage 41. The space S is connected to an opening at the end of the liner 13d. As shown by the dashed-dotted arrow in FIG. 6, the air sent to the space S passes through the space S and is then sent to the combustion chamber 13a through the opening at the end of the liner 13d.

[0086] The air flowing through the space S is compressed by the compressor 11a and is therefore at a high temperature (for example, 400° C. or higher). Therefore, while the gas turbine system 1D is in operation (i.e., while the combustion device 10D is in operation), the ammonia decomposition catalyst 16 is heated by the air flowing through the space S to a temperature at which ammonia decomposition is actively carried out (i.e., a temperature equal to or higher than the reference temperature).

[0087] As described above, in the gas turbine system 1D, unlike the above-described gas turbine system 1, the ammonia decomposition catalyst 16 is disposed in the space S in the combustor 13 that communicates the combustion chamber 13a with the intake air flow path 41. Even in this case, similar to the above-described gas turbine system 1, the ammonia decomposition catalyst 16 is heated by effectively utilizing the heat of the air compressed by the compressor 11a. Therefore, the same effects as those of the above-described gas turbine system 1 are achieved.

[0088] Although the embodiments of the present disclosure have been described above with reference to the accompanying drawings, it goes without saying that the present disclosure is not limited to such embodiments. It is clear that a person skilled in the art can think of various modified or altered examples within the scope of the claims, and it is understood that these also naturally belong to the technical scope of the present disclosure.

[0089] In the above, an example has been described in which the rotational power generated by the turbocharger 11 is used as energy for driving the generator 12 in the gas turbine system 1, gas turbine system 1A, gas turbine system 1B, gas turbine system 1C, and gas turbine system 1D. However, in the gas turbine system 1, gas turbine system 1A, gas turbine system 1B, gas turbine system 1C, and gas turbine system 1D, the rotational power generated by the turbocharger 11 may be used for other purposes (for example, for the purpose of driving a moving body such as a ship, etc.).

[0090] In the above, an example has been described in which liquid ammonia is supplied to the combustor 13 and the ammonia decomposition catalyst 16 in the gas turbine system 1, the gas turbine system 1A, the gas turbine system 1B, the gas turbine system 1C, and the gas turbine system 1D. However, gaseous ammonia may be supplied to the combustor 13 and the ammonia decomposition catalyst 16 in the gas turbine system 1, the gas turbine system 1A, the gas turbine system 1B, the gas turbine system 1C, and the gas turbine system 1D. For example, a vaporizer may be provided downstream of the pump 15, and ammonia may be vaporized by the vaporizer and then supplied to the combustor 13 or the ammonia decomposition catalyst 16. In this case, an accumulator may be provided downstream of the vaporizer. The vaporizer and the accumulator may be provided in the flow path 44, or in the flow path 45 and the flow path 46, respectively.

[0091] In the above, there has been described the gas turbine system 1A in which a cooling device (specifically, the heat exchanger 51) is additionally provided in the flow path 47 in comparison with the gas turbine system 1. However, in comparison with the gas turbine system 1B, the gas turbine system 1C, and the gas turbine system 1D, a cooling device (specifically, the heat exchanger 51) may additionally be provided in the flow path 47.

[0092] In the above, there has been described the gas turbine system 1B in which a system including the flow path 49, the heat exchanger 52, and the heat exchanger 53 is additionally provided to the gas turbine system 1. However, a system including the flow path 49, the heat exchanger 52, and the heat exchanger 53 may be additionally provided to the gas turbine system 1A, the gas turbine system 1C, and the gas turbine system 1D. [Explanation of symbols]

[0093] 1: Gas turbine system 1A: Gas turbine system 1B: Gas turbine system 1C: Gas turbine system 1D: Gas turbine system 11a: Compressor 13: Combustor 13a: Combustion chamber 14: Ammonia tank 16: Ammonia decomposition catalyst 17: Decomposition gas storage tank 21: First flow control valve 22: Second flow control valve 23: Third flow control valve 31: Control device 41: Intake passage 43: Extraction passage 44: Passage 45: Passage 46: Passage 47: Passage 48: Passage 49: Passage 51: Heat exchanger (cooling device) S: Space

Claims

1. A gas turbine system, comprising: An ammonia tank; a combustor connected to the ammonia tank and having a combustion chamber; an intake passage connected to the combustor; a compressor provided in the intake passage; a cracked gas storage tank connected to the combustor; an ammonia decomposition catalyst that is disposed in an extraction passage connected to the compressor, in the intake passage between the compressor and the combustor, or in a space in the combustor that communicates between the combustion chamber and the intake passage, and that is connected to the ammonia tank and the decomposition gas storage; Equipped with determining whether or not a temperature of the ammonia decomposition catalyst is equal to or higher than a reference temperature during operation of the gas turbine system, and controlling ammonia to be supplied from the ammonia tank to the ammonia decomposition catalyst when the temperature of the ammonia decomposition catalyst is equal to or higher than the reference temperature; During operation of the gas turbine system, an amount of ammonia supplied from the ammonia tank to the ammonia decomposition catalyst is controlled so that the pressure in the cracked gas storage tank becomes a reference pressure, and when the pressure in the cracked gas storage tank is lower than the reference pressure, the gas turbine system is not stopped, but the supply of ammonia from the ammonia tank to the ammonia decomposition catalyst is continued, and when the pressure in the cracked gas storage tank becomes equal to or higher than the reference pressure, the gas turbine system is stopped; control so that, at the start of the gas turbine system, the supply of the cracked gas from the cracked gas storage tank to the combustor is started, and thereafter, the supply of the ammonia from the ammonia tank to the combustor is started; Gas turbine systems.

2. A cooling device is provided in a flow path connecting the ammonia decomposition catalyst and the decomposition gas storage tank. The gas turbine system of claim 1 .

3. the cooling device is a heat exchanger provided in a flow path connecting the ammonia decomposition catalyst and the decomposition gas storage device, A flow path connecting the ammonia tank and the ammonia decomposition catalyst passes through the heat exchanger. The gas turbine system of claim 2 .

4. a first flow control valve is provided in a flow path connecting the ammonia tank and the ammonia decomposition catalyst; a control device that controls the first flow control valve so that ammonia is supplied from the ammonia tank to the ammonia decomposition catalyst during operation of the gas turbine system. The gas turbine system according to any one of claims 1 to 3.

5. a second flow control valve is provided in a flow path connecting the cracked gas storage vessel and the combustor; a third flow control valve is provided in a flow path connecting the ammonia tank and the combustor; the control device controls the second flow control valve and the third flow control valve so that, at a start of the gas turbine system, the supply of the ammonia from the ammonia tank to the combustor starts after the supply of the cracked gas from the cracked gas storage tank to the combustor starts. The gas turbine system of claim 4 .

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