Gas Turbine Systems

Abstract

To suppress generation of NOx while stably burning ammonia.SOLUTION: A fuel supply facility includes: a main ammonia line in which liquid ammonia flows; a vaporizer connected to an end of the main ammonia line and heating and vaporizing the liquid ammonia by exchanging heat between a heating medium and the liquid ammonia; a gas ammonia line connected to the vaporizer and guiding gas ammonia that is ammonia vaporized by the vaporizer to a combustor of a gas turbine as fuel; a liquid ammonia line for guiding the liquid ammonia that has not undergone heat exchange with the heating medium in the vaporizer to the combustor as fuel; and a switching device capable of switching an ammonia supply state between a first state of guiding the gas ammonia from the gas ammonia line to the combustor and a second state of guiding the liquid ammonia from the liquid ammonia line to the combustor.SELECTED DRAWING: Figure 1

Description

[Technical field]

[0001] The present disclosure relates to Gas Turbine Systems Regarding. [Background technology]

[0002] A gas turbine includes a compressor that compresses air, a combustor that burns fuel in the air compressed by the compressor to generate combustion gas, and a turbine that is driven by the combustion gas. The following Patent Document 1 discloses an example in which ammonia is used as the fuel supplied to the combustor. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] International Publication No. 2018 / 181002 Summary of the Invention [Problem to be solved by the invention]

[0004] When ammonia is used as a fuel for a gas turbine, part of the nitrogen that forms the ammonia becomes NOx. Therefore, when ammonia is used as a fuel for a gas turbine, it is desirable to reduce the amount of NOx produced. Even when ammonia is used as a fuel for a gas turbine, it is desirable to burn ammonia as stably as possible, just as when natural gas or the like is used as a fuel for a gas turbine.

[0005] Therefore, an object of the present disclosure is to provide a technology that can stably supply ammonia and stably combust ammonia while suppressing the generation of NOx from the start-up of a gas turbine to rated load operation when ammonia is used as fuel for the gas turbine. [Means for solving the problem]

[0006] A gas turbine system according to one aspect of the present disclosure includes a combustor, a turbine connected to the combustor, a heating unit that heats liquid ammonia as fuel, and a fuel supply unit that supplies the fuel heated by the heating unit to the combustor, the fuel supply unit includes a first flow rate adjusting means for adjusting a flow rate of the fuel supplied to the heating unit, The heating unit includes a heat exchanger that exchanges heat between the fuel and at least a portion of steam generated by a heat recovery boiler that recovers heat contained in the combustion gas exhausted from the turbine. and a second flow rate adjusting means for adjusting the flow rate of the water vapor supplied to the heat exchanger. The fuel heated by the heating section is supplied to the combustor without thermally decomposing the ammonia molecules. Effect of the Invention

[0011] According to one embodiment of the present disclosure, it is possible to suppress the generation of NOx while stably burning ammonia. [Brief description of the drawings]

[0012] [Figure 1] FIG. 1 is a system diagram of a gas turbine plant in a first embodiment according to the present disclosure. [Diagram 2] FIG. 2 is a cross-sectional view of an embodiment of a fuel nozzle according to the present disclosure. [Diagram 3] 4 is a flowchart showing a procedure for executing a fuel supply method according to an embodiment of the present disclosure. [Figure 4] 4 is a graph illustrating fuel flow percentage over time in one embodiment according to the present disclosure. [Diagram 5] 4 is a graph showing a relationship between a fuel-air ratio and a NOx concentration in one embodiment according to the present disclosure. [Figure 6] FIG. 4 is a system diagram of a gas turbine plant in a second embodiment according to the present disclosure. [Figure 7] FIG. 11 is a system diagram of a gas turbine plant in a third embodiment according to the present disclosure. [Figure 8] 6 is a graph showing the change in fuel flow percentage over time for a first variation according to the present disclosure. [Figure 9]FIG. 11 is a system diagram of a gas turbine plant in a second modified example according to the present disclosure. [Figure 10] FIG. 11 is a system diagram of a gas turbine plant in a third modified example according to the present disclosure. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0013] Hereinafter, various embodiments and modifications according to the present disclosure will be described with reference to the drawings.

[0014] "First embodiment" Hereinafter, a first embodiment of a gas turbine plant according to the present disclosure will be described with reference to FIGS. 1 to 5. FIG.

[0015] 1, the gas turbine plant of this embodiment includes a gas turbine 10, a denitration device 20 that decomposes NOx contained in exhaust gas from the gas turbine 10, a heat recovery boiler 21 that generates steam by utilizing heat of the exhaust gas flowing out from the denitration device 20, a chimney 22 that exhausts the exhaust gas from the heat recovery boiler 21 to the outside, a steam turbine 23 that is driven by steam from the heat recovery boiler 21, a condenser 24 that converts the steam from the steam turbine 23 back into water, a pump 25 that sends the water in the condenser 24 to the heat recovery boiler 21, a fuel supply facility 40 that supplies fuel to the gas turbine 10, and a control device 60. The denitration device 20 may be disposed in the heat recovery boiler 21.

[0016] The gas turbine 10 includes a compressor 14 that compresses air A, a combustor 15 that burns fuel in the air compressed by the compressor 14 to generate combustion gas, and a turbine 16 that is driven by the high-temperature, high-pressure combustion gas.

[0017] The compressor 14 has a compressor rotor 14r that rotates around a rotor axis Ar, a compressor casing 14c that covers the compressor rotor 14r, and an intake air amount adjuster (hereinafter, referred to as an inlet guide vane (IGV)) 14i that is provided at the intake port of the compressor casing 14c. The IGV 14i adjusts the flow rate of air sucked into the compressor casing 14c according to instructions from the control device 60.

[0018] The turbine 16 has a turbine rotor 16r that rotates about a rotor axis Ar by the combustion gas from the combustor 15, and a turbine casing 16c that covers the turbine rotor 16r. The turbine rotor 16r and the compressor rotor 14r are connected to each other so as to be rotatable about the same rotor axis Ar, thereby forming a gas turbine rotor 11. To this gas turbine rotor 11, for example, a rotor of a generator is connected.

[0019] The gas turbine 10 further includes an intermediate casing 12. The intermediate casing 12 is disposed between the compressor casing 14c and the turbine casing 16c in the direction in which the rotor axis Ar extends, and connects the compressor casing 14c and the turbine casing 16c. Compressed air discharged from the compressor 14 flows into the intermediate casing 12.

[0020] The combustor 15 is fixed to the intermediate casing 12. The combustor 15 includes a combustion liner (or transition piece) 15c that forms a combustion chamber 15s therein, and a combustor body 15b that injects fuel and compressed air into the combustion chamber 15s. The combustion liner 15c that forms the combustion chamber 15s constitutes a combustion chamber former. In the combustion chamber 15s, fuel is burned in the compressed air. Combustion gas generated by the combustion of the fuel flows through the combustion chamber 15s and is sent to the turbine 16. The combustor body 15b has a fuel nozzle 15n that injects fuel into the combustion chamber 15s.

[0021] Ammonia is supplied to the denitration device 20. The denitration device 20 uses the ammonia to decompose NOx contained in the exhaust gas from the gas turbine 10 into nitrogen and water vapor.

[0022] The heat recovery steam generator 21 and the condenser 24 are connected by a water supply line 26. A pump 25 is provided on the water supply line 26 to send the water in the condenser 24 to the heat recovery steam generator 21. The heat recovery steam generator 21 and the steam turbine 23 are connected by a main steam line 27. The heat recovery steam generator 21 uses the heat of the exhaust gas from the gas turbine 10 to turn the water from the water supply line 26 into steam. This steam is sent to the steam turbine 23 via the main steam line 27. A rotor of a generator, for example, is connected to the rotor of the steam turbine 23. The steam exhausted from the steam turbine 23 is returned to water by the condenser 24.

[0023] The fuel supply equipment 40 includes an ammonia tank 41, a main ammonia line 42, a flow control valve 43, a main ammonia pump 44, a vaporizer 45, a gaseous ammonia line 46, a liquid ammonia line 47, a switch 48, a gaseous ammonia compressor 51, a liquid ammonia pump 52, a heating medium line 53, a heating medium valve 54, and a heating medium recovery line 55.

[0024] Liquid ammonia NH3L is stored in the ammonia tank 41. A main ammonia line 42 is connected to this ammonia tank 41. This main ammonia line 42 is provided with a main ammonia pump 44 that pressurizes the liquid ammonia NH3L from the ammonia tank 41, and a flow rate control valve 43 that adjusts the flow rate of ammonia flowing through the main ammonia line 42. An end of the main ammonia line 42 is connected to an ammonia inlet of a vaporizer 45.

[0025] The vaporizer 45 is a heat exchanger that exchanges heat between steam, which is a heating medium, and liquid ammonia NH3L to heat and vaporize the liquid ammonia NH3L. One end of a heating medium line 53 is connected to a medium inlet of the vaporizer 45. The other end of the heating medium line 53 is connected to the main steam line 27. A heating medium valve 54 that adjusts the flow rate of steam flowing through the heating medium line 53 is provided in the heating medium line 53. One end of a heating medium recovery line 55 is connected to a medium outlet of the vaporizer 45. The other end of the heating medium recovery line 55 is connected to the condenser 24. The other end of the heating medium recovery line 55 may be connected to a portion of the heat recovery boiler 21 through which water flows, instead of the condenser 24.

[0026] One end of a gaseous ammonia line 46 is connected to the ammonia outlet of the vaporizer 45. The other end of the gaseous ammonia line 46 is connected to the fuel nozzle 15n of the combustor 15. The gaseous ammonia line 46 is provided with a gaseous ammonia compressor 51 that pressurizes the gaseous ammonia NH3G flowing therethrough.

[0027] One end of the liquid ammonia line 47 is connected to a position between the main ammonia pump 44 and the vaporizer 45 in the main ammonia line 42. The other end of the liquid ammonia line 47 is connected to the fuel nozzle 15n of the combustor 15. The liquid ammonia line 47 is provided with a liquid ammonia pump 52 that pressurizes the liquid ammonia NH3L flowing therethrough.

[0028] The flow rate control valve 43 is provided in the main ammonia line 42 at a position between the connection position with the liquid ammonia line 47 and the main ammonia pump 44. This flow rate control valve 43 adjusts the flow rate of the liquid ammonia NH3L flowing through the main ammonia line 42, thereby adjusting the flow rate of the fuel supplied to the combustor 15.

[0029] The switch 48 switches the ammonia supply state between a first state in which gaseous ammonia NH3G is guided from the gaseous ammonia line 46 to the fuel nozzle 15n of the combustor 15, a second state in which liquid ammonia NH3L is guided from the liquid ammonia line 47 to the fuel nozzle 15n of the combustor 15, and a third state in which gaseous ammonia NH3G from the gaseous ammonia line 46 and liquid ammonia NH3L from the liquid ammonia line 47 are guided to the fuel nozzle 15n of the combustor 15. The switch 48 has a gaseous ammonia flow rate control valve 48g and a liquid ammonia flow rate control valve 48i. The gaseous ammonia flow rate control valve 48g is provided in the main ammonia line 42 at a position between the connection position with the liquid ammonia line 47 and the vaporizer 45. The gaseous ammonia flow rate control valve 48g adjusts the flow rate of liquid ammonia NH3L flowing from the main ammonia line 42 to the vaporizer 45, thereby adjusting the flow rate of gaseous ammonia NH3G supplied to the combustor 15 via the gaseous ammonia line 46. The liquid ammonia flow rate control valve 48i is provided in the liquid ammonia line 47. The liquid ammonia flow rate control valve 48i controls the flow rate of the liquid ammonia NH3L flowing through the liquid ammonia line 47.

[0030] The first state can be realized by closing the liquid ammonia flow rate control valve 48i and opening the gaseous ammonia flow rate control valve 48g. The second state can be realized by opening the liquid ammonia flow rate control valve 48i and closing the gaseous ammonia flow rate control valve 48g. The third state can be realized by half-opening both the liquid ammonia flow rate control valve 48i and the gaseous ammonia flow rate control valve 48g.

[0031] The switch 48 can be replaced with one three-way valve instead of the gaseous ammonia flow rate control valve 48g and the liquid ammonia flow rate control valve 48i. In this case, the three-way valve is provided at the connection position of the main ammonia line 42 and the liquid ammonia line 47. This three-way valve adjusts the ratio between the flow rate of liquid ammonia NH3L flowing into the vaporizer 45 and the flow rate of liquid ammonia NH3L flowing into the liquid ammonia line 47.

[0032] In this embodiment, the fuel combustion facility includes a fuel supply facility 40 and a combustor 15 .

[0033] The control device 60 receives a required output of the gas turbine 10 from the outside, and controls the operation of the flow rate control valve 43 and the switch 48 in accordance with this required output. This control device 60 is a computer. In terms of hardware, the control device 60 has a CPU (Central Processing Unit) that performs various calculations, a main storage device such as a memory that serves as a work area for the CPU, an auxiliary storage device such as a hard disk drive device, input devices such as a keyboard and a mouse, and a display device. This control device 60 functions, for example, when the CPU executes a control program stored in the auxiliary storage device.

[0034] As shown in FIG. 2, the fuel nozzle 15n of the combustor 15 has an inner cylinder 31 that is cylindrical around the nozzle axis An, and an outer cylinder 32 that is cylindrical around the nozzle axis An and is disposed on the outer circumferential side of the inner cylinder 31. Here, the direction in which the nozzle axis An extends is defined as the axial direction Da, and one of both sides of the axial direction Da is defined as the rear side Dab, and the other side is defined as the front side Daf. The position of the end of the front side Daf of the inner cylinder 31 and the position of the end of the front side Daf of the outer cylinder 32 are substantially the same in the axial direction Da. The inner circumferential side of the inner cylinder 31 forms a liquid fuel flow passage 33. The liquid fuel flow passage 33 has a liquid fuel inlet 33i and a liquid fuel injection port 33o. The end of the rear side Dab of the liquid fuel flow passage 33 forms the liquid fuel inlet 33i, and the end of the front side Daf of the liquid fuel flow passage 33 forms the liquid fuel injection port 33o. A liquid ammonia line 47 is connected to the liquid fuel inlet 33i. A gas fuel flow path 34 is formed between the outer periphery of the inner cylinder 31 and the inner periphery of the outer cylinder 32. The gas fuel flow path 34 has a gas fuel inlet 34i and a gas fuel injection port 34o. An opening is formed in the outer periphery of the outer cylinder 32 at the rear Dab portion of the outer cylinder 32. This opening forms the gas fuel inlet 34i of the gas fuel flow path 34, and the end of the front Daf of the gas fuel flow path 34 forms the gas fuel injection port 34o. A gas ammonia line 46 is connected to the gas fuel inlet 34i. On the outer periphery of the outer cylinder 32, from the end of the front Daf of the outer cylinder 32, compressed air Acom from the compressor 14 flows toward the front Daf as combustion air.

[0035] Next, the procedure of the fuel supply method in the gas turbine plant described above will be described with reference to the flowchart shown in FIG.

[0036] In this fuel supply method, an ammonia pressure increasing step S1, a flow rate adjusting step S2, a switching control step S3, a steam generating step S4, a vaporizing step S5, and a switching step S6 are performed.

[0037] In the ammonia pressure increasing step S1, the main ammonia pump 44 increases the pressure of the liquid ammonia NH3L that has flowed from the ammonia tank 41 into the main ammonia line 42. In the flow rate adjustment step S2, the flow rate adjustment valve 43 adjusts the flow rate of the liquid ammonia NH3L flowing through the main ammonia line 42. The flow rate of the fuel supplied to the combustor 15 is adjusted by adjusting the flow rate of the liquid ammonia NH3L. The control device 60 receives the required output of the gas turbine 10. The control device 60 determines the flow rate of the fuel supplied to the combustor 15 in accordance with the required output. The flow rate of the fuel is determined so as to have a positive correlation with the required output. In other words, the flow rate of the fuel is determined so that the flow rate of the fuel increases as the required output increases. The control device 60 instructs the flow rate adjustment valve 43 so that the flow rate of the fuel supplied to the combustor 15 becomes the determined flow rate.

[0038] In the switching control step S3, the controller 60 determines one of the first state, the second state, and the third state as the fuel supply state, and instructs the switch 48 to enter this one state.

[0039] A method for determining the fuel supply state by the control device 60 will be described with reference to Fig. 4. The amount of fuel supplied to the gas turbine 10 gradually increases over time from start-up to rated operation. As described above, the flow rate of fuel supplied to the combustor 15 when the required output is smaller than the rated output is less than the flow rate of fuel supplied to the combustor 15 when the required output is the rated output. If the fuel flow rate percentage when the required output is the rated output is 100%, the fuel flow rate percentage before start-up is 0%. Also, the fuel flow rate percentage when the required output is a predetermined output smaller than the rated output is α%.

[0040] In the case of a low fuel flow rate where the fuel flow rate percentage determined according to the required output is greater than 0% and less than α%, the control device 60 selects the second state from among the first state, the second state, and the third state. As described above, this second state is a state in which only liquid ammonia NH3L is introduced to the fuel nozzle 15n. In the case of a low fuel flow rate where the fuel flow rate percentage determined according to the required output is α%, the control device 60 selects the third state from among the first state, the second state, and the third state. As described above, this third state is a state in which liquid ammonia NH3L and gaseous ammonia NH3G are introduced to the fuel nozzle 15n. In the case of a high fuel flow rate where the fuel flow rate percentage determined according to the required output is greater than α%, the control device 60 selects the first state from among the first state, the second state, and the third state. As described above, this first state is a state in which only gaseous ammonia NH3G is introduced to the fuel nozzle 15n. The control device 60 instructs the switch 48 to enter the selected state.

[0041] In the steam generation step S4, the heat recovery boiler 21 exchanges heat between the exhaust gas from the gas turbine 10 and water to convert the water into steam.

[0042] The vaporization step S5 is executed when the first state or the third state is determined as the fuel supply state in the switching control step S3, and is not executed when the second state is determined as the fuel supply state. In the vaporization step S5, the liquid ammonia NH3L is heated by a heating medium in the vaporizer 45 and vaporized. As the steam serving as the heating medium, a part of the steam generated in the steam generation step S4 is used.

[0043] In the switching step S6, the switch 48 operates to switch to one of the first state, the second state, and the third state instructed by the control device 60.

[0044] For example, when the first state is instructed from the control device 60, of the gaseous ammonia flow rate control valve 48g and the liquid ammonia flow rate control valve 48i of the switch 48, the gaseous ammonia flow rate control valve 48g is opened, and the liquid ammonia flow rate control valve 48i is closed. As a result, the liquid ammonia NH3L is led to the vaporizer 45 via the main ammonia line 42 and the gaseous ammonia flow rate control valve 48g, where it becomes gaseous ammonia NH3G. This gaseous ammonia NH3G is led to the combustor 15 via the gaseous ammonia line 46 and the gaseous ammonia compressor 51. On the other hand, the liquid ammonia NH3L pressurized by the main ammonia pump 44 does not flow into the liquid ammonia line 47. Therefore, in the first state executed at the time of high fuel flow rate, only gaseous ammonia NH3G is supplied as fuel to the fuel nozzle 15n of the combustor 15. This gaseous ammonia NH3G flows through the gaseous fuel flow passage 34 of the fuel nozzle 15n and is injected into the combustion tube 15c from the gaseous fuel injection port 34o.

[0045] Also, when the second state is instructed from the control device 60, of the gaseous ammonia flow rate control valve 48g and the liquid ammonia flow rate control valve 48i of the switch 48, the gaseous ammonia flow rate control valve 48g is closed and the liquid ammonia flow rate control valve 48i is opened. As a result, the liquid ammonia NH3L is guided to the combustor 15 via the liquid ammonia line 47, the liquid ammonia flow rate control valve 48i and the liquid ammonia pump 52. On the other hand, the liquid ammonia NH3L pressurized by the main ammonia pump 44 is not guided to the vaporizer 45. Therefore, in the second state executed at the time of low fuel flow rate, only the liquid ammonia NH3L is supplied as fuel to the fuel nozzle 15n of the combustor 15. This liquid ammonia NH3L flows through the liquid fuel flow passage 33 of the fuel nozzle 15n and is injected into the combustion liner 15c from the liquid fuel injection port 33o.

[0046] Also, when the third state is instructed from the control device 60, both the gaseous ammonia flow rate control valve 48g and the liquid ammonia flow rate control valve 48i of the switch 48 are half-opened. As a result, the liquid ammonia NH3L is guided to the vaporizer 45 via the main ammonia line 42 and the gaseous ammonia flow rate control valve 48g, where it becomes gaseous ammonia NH3G. This gaseous ammonia NH3G is guided to the combustor 15 via the gaseous ammonia line 46 and the gaseous ammonia compressor 51. The liquid ammonia NH3L also flows into the liquid ammonia line 47, and is guided to the combustor 15 via the liquid ammonia line 47, the liquid ammonia flow rate control valve 48i, and the liquid ammonia pump 52. Therefore, in the third state executed at the time of α% fuel flow rate between the low fuel flow rate and the high fuel flow rate, both the liquid ammonia NH3L and the gaseous ammonia NH3G are supplied as fuel to the fuel nozzle 15n of the combustor 15. This gaseous ammonia NH3G flows through the gaseous fuel passage 34 of the fuel nozzle 15n and is injected into the combustion liner 15c from the gaseous fuel injection port 34o. Also, this liquid ammonia NH3L flows through the liquid fuel passage 33 of the fuel nozzle 15n and is injected into the combustion liner 15c from the liquid fuel injection port 33o.

[0047] Incidentally, as shown in FIG. 4, when the fuel flow rate shifts from a low fuel flow rate to a high fuel flow rate through an α% fuel flow rate, the α% fuel flow rate is maintained for a predetermined time or more. In the third state executed at an α% fuel flow rate, the liquid ammonia flow rate control valve 48i gradually closes over time, and the flow rate of liquid ammonia NH3L led to the combustor 15 gradually decreases over time. In the third state, the gaseous ammonia flow rate control valve 48g gradually opens over time, and the flow rate of gaseous ammonia NH3G led to the combustor 15 gradually increases over time. Also, when the fuel flow rate shifts from a high fuel flow rate to a low fuel flow rate through an α% fuel flow rate, the α% fuel flow rate is maintained for a predetermined time or more. In the third state executed at an α% fuel flow rate, the gaseous ammonia flow rate control valve 48g gradually closes over time, and the flow rate of gaseous ammonia NH3G led to the combustor 15 gradually decreases over time. In this third state, during this predetermined time, the liquid ammonia flow rate control valve 48i gradually opens with the passage of time, and the flow rate of the liquid ammonia NH3L introduced to the combustor 15 gradually increases with the passage of time.

[0048] When ammonia is used as fuel for the gas turbine 10, part of the nitrogen forming the ammonia becomes NOx. The amount of NOx produced depends on the flow rate of the ammonia used as fuel and the fuel-air ratio. If the flow rate of the ammonia used as fuel increases, the amount of NOx produced increases, and if the flow rate of the ammonia used as fuel decreases, the amount of NOx produced decreases. As shown in FIG. 5, the NOx concentration in the combustion gas is maximum when the fuel-air ratio is at a certain value r. This NOx concentration gradually decreases as the fuel-air ratio becomes smaller than a certain value r. This NOx concentration also gradually decreases as the fuel-air ratio becomes larger than a certain value r.

[0049] Therefore, in this embodiment, the fuel-air ratio is controlled so that the value of the fuel-air ratio does not become a value within a predetermined fuel-air ratio range R in which the NOx concentration becomes higher than a predetermined value c. This control of the fuel-air ratio is executed by the control device 60. As described above, the control device 60 determines the fuel flow rate according to the required output. Then, the control device 60 determines the opening degree of the IGV 14i based on the determined fuel flow rate, and instructs the IGV 14i of this opening degree. At this time, the control device 60 determines the opening degree of the IGV 14i so that the value of the fuel-air ratio, which is the ratio between the determined fuel flow rate and the flow rate of air sucked by the compressor 14, does not become a value within the above-mentioned predetermined fuel-air ratio range R.

[0050] As described above, in this embodiment, it is possible to guide gaseous ammonia NH3G to the combustor 15, and it is also possible to guide liquid ammonia NH3L to the combustor 15. When liquid ammonia NH3L is injected as fuel from the fuel nozzle 15n of the combustor 15, misfires and the like are suppressed, and the fuel can be burned stably. On the other hand, when gaseous ammonia NH3G is injected as fuel from the fuel nozzle 15n of the combustor 15, the generation of NOx can be suppressed. Incidentally, at the time of a low fuel flow rate, the possibility of fuel misfire is high, but the amount of NOx generated is small because the flow rate of ammonia itself is low. Conversely, at the time of a high fuel flow rate, the possibility of fuel misfire is low, but the flow rate of ammonia itself is high, and the amount of NOx generated is large. Therefore, in this embodiment, as described above, at the time of a low fuel flow rate, in order to reduce the possibility of fuel misfire and achieve stable combustion of the fuel, liquid ammonia NH3L is guided to the combustor 15. Also, in this embodiment, at the time of a high fuel flow rate, in order to suppress the generation of NOx, gaseous ammonia NH3G is guided to the combustor 15. Therefore, in this embodiment, by supplying liquid ammonia to the combustor at the time of startup, it is possible to supply ammonia as fuel to the combustor without supplying thermal energy from the outside. Furthermore, in this embodiment, from startup to rated operation, it is possible to suppress the generation of NOx while stably burning ammonia without using any fuel other than ammonia.

[0051] Furthermore, in this embodiment, as described above, the fuel-air ratio is controlled so that the value of the fuel-air ratio does not become a value within the predetermined fuel-air ratio range R in which the NOx concentration becomes higher than the predetermined value c. Therefore, in this embodiment, the generation of NOx can be suppressed from this viewpoint as well.

[0052] Furthermore, in this embodiment, the combustion gas exhausted from the gas turbine 10 passes through the denitrification device 20 and is then discharged to the outside through the chimney 22. Therefore, in this embodiment, it is possible to suppress the amount of NOx emissions.

[0053] When the state where only gaseous ammonia NH3G is introduced to the combustor 15 is changed to the state where only liquid ammonia NH3L is introduced to the combustor 15, or when the state where only liquid ammonia NH3L is introduced to the combustor 15 is changed to the state where only gaseous ammonia NH3G is introduced to the combustor 15, the stable combustibility of the fuel is impaired if the phase of the fuel injected from the fuel nozzle 15n of the combustor 15 suddenly changes. The fuel nozzle 15n of this embodiment has a liquid fuel flow passage 33 and a gaseous fuel flow passage 34, and can simultaneously inject liquid ammonia NH3L and gaseous ammonia NH3G. In addition, in this embodiment, in the process of transition from the first state to the second state, or the process of transition from the second state to the first state, both liquid ammonia NH3L and gaseous ammonia NH3G are introduced to the fuel nozzle 15n of the combustor 15 as fuel. For this reason, in this embodiment, the stable combustibility of the fuel in the transition process as described above can be ensured.

[0054] Second Embodiment Hereinafter, a second embodiment of a gas turbine plant according to the present disclosure will be described with reference to FIG.

[0055] Like the gas turbine plant of the first embodiment, the gas turbine plant of this embodiment includes a gas turbine 10, a denitrification device 20, a heat recovery steam generator 21, a steam turbine 23, a condenser 24, a pump 25, a fuel supply system 40a, and a control device 60. However, the fuel supply system 40a of this embodiment is different from the fuel supply system 40 of the first embodiment.

[0056] The fuel supply equipment 40a of this embodiment has an ammonia tank 41, a main ammonia line 42, a main ammonia pump 44, a vaporizer 45, a gaseous ammonia line 46, a liquid ammonia line 47, a switch 48, a heating medium line 53, a heating medium valve 54, and a heating medium recovery line 55, similar to the fuel supply equipment 40 of the first embodiment. However, the fuel supply equipment 40a of this embodiment does not have the flow rate control valve 43, the gaseous ammonia compressor 51, and the liquid ammonia pump 52 in the fuel supply equipment 40 of the first embodiment. Therefore, in this embodiment, the liquid ammonia flow rate control valve 48i and the gaseous ammonia flow rate control valve 48g constituting the switch 48 also function as the flow rate control valve 43 in the first embodiment. In addition, in this embodiment, the main ammonia pump 44 also functions as the gaseous ammonia compressor 51 and the liquid ammonia pump 52.

[0057] As described above, the fuel supply equipment 40a of the present embodiment does not have the flow rate control valve 43, the gaseous ammonia compressor 51, and the liquid ammonia pump 52 in the fuel supply equipment 40 of the first embodiment. Therefore, in the present embodiment, the equipment manufacturing cost can be reduced more than in the first embodiment.

[0058] "Third embodiment" Hereinafter, a third embodiment of a gas turbine plant according to the present disclosure will be described with reference to FIG.

[0059] The gas turbine plant of this embodiment, like the gas turbine plants of the first and second embodiments, includes a gas turbine 10, a denitrification device 20, a heat recovery steam generator 21, a steam turbine 23, a condenser 24, a pump 25, a fuel supply system 40b, and a control device 60. However, the fuel supply system 40b of this embodiment is different from the fuel supply systems 40 and 40a of the first and second embodiments.

[0060] The fuel supply equipment 40b of this embodiment has an ammonia tank 41, a main ammonia line 42, a flow rate control valve 43, a main ammonia pump 44, a vaporizer 45, a gaseous ammonia line 46, a switch 48b, a heating medium line 53, a heating medium valve 54, and a heating medium recovery line 55, similar to the fuel supply equipment 40 of the first embodiment. However, in the fuel supply equipment 40b of this embodiment, the gaseous ammonia line 46 also serves as the liquid ammonia line 47 in the first embodiment. Therefore, in the fuel supply equipment 40b of this embodiment, there is no liquid ammonia line 47 independent of the gaseous ammonia line 46. Therefore, the fuel supply equipment 40b of this embodiment does not have a gaseous ammonia compressor 51 and a liquid ammonia pump 52, similar to the fuel supply equipment 40a of the second embodiment. Further, the switch 48b of the present embodiment has a heating medium valve 54, and does not have a liquid ammonia flow rate control valve 48i and a gaseous ammonia flow rate control valve 48g, unlike the switch 48 of the first and second embodiments.

[0061] In this embodiment, when the second state is realized, the heating medium valve 54 is closed. As a result, the steam, which is the heating medium, is not guided to the vaporizer 45, and even if liquid ammonia NH3L flows into the vaporizer 45 from the main ammonia line 42, it is not heated by the heating medium and flows out of the vaporizer 45 in the form of liquid ammonia NH3L. This liquid ammonia NH3L is guided to the fuel nozzle 15n of the combustor 15 via the gaseous ammonia line 46, which also serves as the liquid ammonia line 47.

[0062] In this embodiment, when the first state is realized, the heating medium valve 54 is opened. As a result, the steam, which is the heating medium, is guided to the vaporizer 45, and when the liquid ammonia NH3L from the main ammonia line 42 flows into the vaporizer 45, it is heated by the heating medium, vaporized, and then flows out of the vaporizer 45. This gaseous ammonia NH3G is guided to the fuel nozzle 15n of the combustor 15 via the gaseous ammonia line 46, which also serves as the liquid ammonia line 47.

[0063] As described above, in the fuel supply equipment 40b of the present embodiment, the gaseous ammonia line 46 also serves as the liquid ammonia line 47, and therefore the equipment manufacturing costs can be reduced more than in the first and second embodiments.

[0064] In addition, since the fuel supply equipment 40b of the present embodiment does not have a liquid ammonia line 47 independent of the gaseous ammonia line 46, the fuel nozzle 15n of the present embodiment does not have two types of fuel flow paths as in the first and second embodiments, but has only one type of fuel flow path.

[0065] In the heat recovery boiler 21, hot water is generated in the process of turning water into steam. Therefore, in each of the above embodiments, this hot water may be used as the heating medium to be subjected to heat exchange with the liquid ammonia NH3L.

[0066] "First Variation" In the first embodiment, as described with reference to Fig. 4, when there is a transition from a low fuel flow rate, via an α% fuel flow rate, to a high fuel flow rate, and when there is a transition from a high fuel flow rate, via an α% fuel flow rate, to a low fuel flow rate, the α% fuel flow rate is maintained for a predetermined period of time or more. However, during such transitions, the α% fuel flow rate does not have to be maintained for a predetermined period of time or more.

[0067] Here, as shown in Fig. 8, a fuel flow rate percentage greater than α% and less than 100% is defined as β%. Also, it is assumed that the amount of fuel supplied to the gas turbine 10 increases linearly with time from start-up to rated operation. Therefore, it is assumed that the amount of fuel supplied to the gas turbine 10 increases linearly with time from α% fuel flow rate to β% fuel flow rate in the process from start-up to rated operation.

[0068] In this modified example, the second state is executed when the fuel flow rate is low and the fuel flow rate percentage is less than α%, the first state is executed when the fuel flow rate is high and the fuel flow rate percentage is greater than β%, and the third state is executed when the fuel flow rate percentage is greater than α% and less than β%.

[0069] When transitioning from a low fuel flow rate to a high fuel flow rate, in the third state executed when the fuel flow rate percentage is α% or more and β% or less, the liquid ammonia flow rate control valve 48i gradually closes over time, and the flow rate of liquid ammonia NH3L introduced to the combustor 15 gradually decreases over time. On the other hand, the gaseous ammonia flow rate control valve 48g gradually opens over time, and the flow rate of gaseous ammonia NH3G introduced to the combustor 15 gradually increases over time. Also, when transitioning from a high fuel flow rate to a low fuel flow rate, in the third state executed when the fuel flow rate percentage is α% or more and β% or less, the gaseous ammonia flow rate control valve 48g gradually closes over time, and the flow rate of gaseous ammonia NH3G introduced to the combustor 15 gradually decreases over time. On the other hand, the liquid ammonia flow rate control valve 48i gradually opens over time, and the flow rate of liquid ammonia NH3L introduced to the combustor 15 gradually increases over time.

[0070] "Second Variation" In each of the above embodiments, steam or hot water generated in the heat recovery boiler 21 is used as the heating medium to be heat exchanged with the liquid ammonia NH3L. However, exhaust gas flowing in the heat recovery boiler 21 may be used as the heating medium to be heat exchanged with the liquid ammonia NH3L. Therefore, a modified example in which exhaust gas flowing in the heat recovery boiler 21 is used as the heating medium to be heat exchanged with the liquid ammonia NH3L will be described with reference to FIG.

[0071] The fuel supply equipment 40c of this modification is a modification of the fuel supply equipment 40 of the first embodiment. A part of the exhaust gas flowing in the heat recovery boiler 21 is guided to the vaporizer 45 in this modification. For this reason, one end of a heating medium line 53c is connected to the medium inlet of the vaporizer 45 in this modification, and the other end of the heating medium line 53c is connected to the heat recovery boiler 21. The heating medium line 53c is provided with a heating medium valve 54c that adjusts the flow rate of the exhaust gas flowing through the heating medium line 53c. One end of a heating medium recovery line 55c is connected to the medium outlet of the vaporizer 45. The other end of the heating medium recovery line 55c is connected to, for example, the chimney 22. The other end of the heating medium recovery line 55c may be connected to a position downstream of the position where the other end of the heating medium line 53c is connected in the heat recovery boiler 21, instead of the chimney 22. The downstream side here is the downstream side with respect to the flow of the exhaust gas flowing in the heat recovery boiler 21.

[0072] "Third Variation" The fuel supply equipment 40c of the second modified example described above is a fuel supply equipment configured to arrange a vaporizer 45 outside the heat recovery boiler 21 and guide the exhaust gas flowing in the heat recovery boiler 21 to the vaporizer 45. However, as shown in Fig. 10, a heat transfer tube 45d as a vaporizer may be arranged in the heat recovery boiler 21, liquid ammonia NH3L may be flowed in the heat transfer tube 45d, and the liquid ammonia NH3L may be heated by the exhaust gas flowing in the heat recovery boiler 21 and outside the heat transfer tube 45d. In the case of this fuel supply equipment 40d, an end of the main ammonia line 42 is connected to one end of the heat transfer tube 45d, and one end of the gaseous ammonia line 46 is connected to the other end of the heat transfer tube 45d.

[0073] The fuel supply equipment 40d of the third modified example and the fuel supply equipment 40c of the second modified example are modified examples of the fuel supply equipment 40 of the first embodiment. However, in the fuel supply equipment 40a of the second embodiment and the fuel supply equipment 40b of the third embodiment, similarly to the third modified example or the second modified example, the exhaust gas flowing in the heat recovery boiler 21 may be used as the heating medium to be subjected to heat exchange with the liquid ammonia NH3L.

[0074] Although the embodiment and modified examples of the present disclosure have been described in detail above, the present disclosure is not limited to the above embodiment and modified examples. Various additions, modifications, substitutions, partial deletions, etc. are possible within the scope of the conceptual idea and intent of the present invention derived from the contents defined in the claims and their equivalents.

[0075] "Additional Notes" The fuel supply system in the above embodiment can be understood, for example, as follows.

[0076] (1) In a first aspect, the fuel supply system comprises: A main ammonia line 42 connected to an ammonia tank 41 capable of storing liquid ammonia NH3L, a main ammonia pump 44 provided in the main ammonia line 42 and capable of pressurizing the liquid ammonia NH3L from the ammonia tank 41, a vaporizer 45 connected to an end of the main ammonia line 42 and capable of heating and vaporizing the liquid ammonia NH3L by heat exchange between a heating medium and the liquid ammonia NH3L pressurized by the main ammonia pump 44, and a gas turbine 10 connected to the vaporizer 45 and using gaseous ammonia NH3G, which is the ammonia vaporized by the vaporizer 45, as fuel. a gaseous ammonia line 46 capable of guiding the gaseous ammonia NH3G to the combustor 15; a liquid ammonia line 47 capable of guiding liquid ammonia NH3L pressurized by the main ammonia pump 44 and not having exchanged heat with the heating medium in the vaporizer 45 to the combustor 15 as fuel; and switches 48, 48b capable of switching an ammonia supply state between a plurality of states including a first state in which the gaseous ammonia NH3G is guided to the combustor 15 from the gaseous ammonia line 46 and a second state in which the liquid ammonia NH3L is guided to the combustor 15 from the liquid ammonia line 47.

[0077] In this embodiment, it is possible to introduce gaseous ammonia NH3G to the combustor 15, and it is also possible to introduce liquid ammonia NH3L to the combustor 15. When liquid ammonia NH3L is injected as fuel from the fuel nozzle 15n of the combustor 15, misfires and the like are suppressed, and the fuel can be burned stably. On the other hand, when gaseous ammonia NH3G is injected as fuel from the fuel nozzle 15n of the combustor 15, the generation of NOx can be suppressed. Incidentally, when the fuel flow rate is low, the possibility of fuel misfire is high, but the amount of NOx generated is small because the flow rate of ammonia itself is low. Conversely, when the fuel flow rate is high, the possibility of fuel misfire is low, but the flow rate of ammonia itself is high, and the amount of NOx generated is large. Therefore, when the fuel flow rate is low, liquid ammonia NH3L is introduced to the combustor 15 in order to reduce the possibility of fuel misfire and achieve stable combustion of the fuel. Also, when the fuel flow rate is high, gaseous ammonia NH3G is introduced to the combustor 15 in order to suppress the generation of NOx. As a result, in this embodiment, the generation of NOx can be suppressed while stably burning ammonia.

[0078] (2) The fuel supply equipment in the second aspect includes: In the fuel supply equipment in the first aspect, the switches 48, 48b can switch an ammonia supply state among a third state in which the gaseous ammonia NH3G from the gaseous ammonia line 46 and the liquid ammonia NH3L from the liquid ammonia line 47 are guided to the combustor 15, the first state, and the second state.

[0079] When transitioning from a state in which only gaseous ammonia NH3G is introduced to the combustor 15 to a state in which only liquid ammonia NH3L is introduced to the combustor 15, or conversely, transitioning from a state in which only liquid ammonia NH3L is introduced to the combustor 15 to a state in which only gaseous ammonia NH3G is introduced to the combustor 15, if the phase of the fuel injected from the fuel nozzle 15n of the combustor 15 suddenly changes, the stable combustibility of the fuel is impaired. Therefore, in this embodiment, the third state is executed in the process of transition from the first state to the second state, or in the process of transition from the second state to the first state. Therefore, in this embodiment, the stable combustibility of the fuel can be ensured in the transition process as described above.

[0080] (3) The fuel supply equipment in the third aspect is The fuel supply system in the first or second aspect further includes a flow rate adjustment valve that adjusts the flow rate of the fuel supplied to the combustor.

[0081] (4) The fuel supply system according to the fourth aspect comprises: In the fuel supply system according to any one of the first to third aspects, an end of the liquid ammonia line 47 is connected to a position in the main ammonia line 42 between the main ammonia pump 44 and the vaporizer 45.

[0082] (5) In a fifth aspect, the fuel supply system comprises: In the fuel supply equipment in the fourth aspect, the switch 48 is valves 48g, 48i that can switch an ammonia supply state between a state in which the liquid ammonia NH3L pressurized by the main ammonia pump 44 is guided to the vaporizer 45 to realize the first state, and a state in which the liquid ammonia NH3L pressurized by the main ammonia pump 44 is guided to the liquid ammonia line 47 to realize the second state.

[0083] (6) In a sixth aspect, the fuel supply system comprises: The fuel supply facility in the fourth or fifth aspect further includes a liquid ammonia pump 52 provided in the liquid ammonia line 47 and capable of pressurizing the liquid ammonia NH3L flowing through the liquid ammonia line 47, and a gaseous ammonia compressor 51 provided in the gaseous ammonia line 46 and capable of pressurizing the gaseous ammonia NH3G flowing through the gaseous ammonia line 46.

[0084] In this embodiment, the pressure of the liquid ammonia NH3L guided to the combustor 15 via the liquid ammonia line 47 can be easily adjusted to the target pressure, and the pressure of the gaseous ammonia NH3G guided to the combustor 15 via the gaseous ammonia line 46 can be easily adjusted to the target pressure.

[0085] (7) A fuel supply system according to a seventh aspect includes: In the fuel supply facility according to any one of the first to third aspects, the gaseous ammonia line 46 also serves as the liquid ammonia line 47. The switch 48b is a heating medium valve 54 that switches a supply state of the heating medium between a state in which the heating medium is guided to the vaporizer 45 to realize the first state and a state in which the heating medium is not guided to the vaporizer 45 to realize the second state.

[0086] In this embodiment, the gaseous ammonia line 46 also serves as the liquid ammonia line 47, so that the line configuration is simplified and the equipment manufacturing costs can be reduced.

[0087] (8) In an eighth aspect, the fuel supply system comprises: The fuel supply equipment in any one of the first to seventh embodiments further includes a control device 60 that receives a required output of the gas turbine from an outside, determines one of a plurality of states including the first state and the second state according to the required output, and instructs the switches 48, 48b to enter the one state.

[0088] The flow rate of fuel supplied to the combustor 15 varies depending on the required output. The control device 60 of this embodiment determines one of a plurality of states including the first state and the second state depending on the required output. Therefore, in this embodiment, the fuel supply state can be set to the first state when the fuel flow rate is high, and the fuel supply state can be set to the second state when the fuel flow rate is low.

[0089] The fuel combustion facility in the above embodiment can be understood, for example, as follows. (9) A ninth aspect of the fuel combustion equipment includes: The present invention includes a fuel supply system according to any one of the first to eighth aspects, and the combustor 15 that burns the fuel from the fuel supply system 40 in compressed air Acom to generate combustion gas.

[0090] (10) A fuel combustion facility according to a tenth aspect, In the fuel combustion equipment according to the ninth aspect, the combustor 15 includes a combustion chamber forming device 15c for forming a combustion chamber 15s in which the fuel is burned and the combustion gas generated by the combustion of the fuel can be guided to a turbine 16, and a combustor body 15b capable of injecting the fuel and compressed air Acom into the combustion chamber 15s. The combustor body 15b includes a fuel nozzle 15n capable of injecting the fuel into the combustion chamber 15s. The fuel nozzle 15n includes a gas fuel flow passage 34 connected to the gas ammonia line 46 and capable of injecting the gas ammonia NH3G flowing through the gas ammonia line 46 into the combustion chamber 15s, and a liquid fuel flow passage 33 connected to the liquid ammonia line 47 and capable of injecting the liquid ammonia NH3L flowing through the liquid ammonia line 47 into the combustion chamber 15s.

[0091] The gas turbine plant in the above embodiment can be understood as follows, for example. (11) A gas turbine plant in an eleventh aspect is as follows: The fuel supply facility according to any one of the first to eighth aspects, and the gas turbine 10. The gas turbine 10 includes a compressor 14 that compresses air to generate compressed air Acom, the combustor 15 that combusts the fuel from the fuel supply facility 40 in the compressed air Acom to generate combustion gas, and a turbine 16 that can be driven by the combustion gas.

[0092] (12) A gas turbine plant according to a twelfth aspect comprises: In the gas turbine plant according to the eleventh aspect, the combustor 15 includes a combustion chamber forming device 15c for forming a combustion chamber 15s in which the fuel is burned and in which the combustion gas generated by the combustion of the fuel can be guided to the turbine 16, and a combustor body 15b capable of injecting the fuel and the compressed air Acom into the combustion chamber 15s. The combustor body 15b includes a fuel nozzle 15n capable of injecting the fuel into the combustion chamber 15s. The fuel nozzle 15n includes a gas fuel flow passage 34 connected to the gas ammonia line 46 and capable of injecting the gas ammonia NH3G flowing through the gas ammonia line 46 into the combustion chamber 15s, and a liquid fuel flow passage 33 connected to the liquid ammonia line 47 and capable of injecting the liquid ammonia NH3L flowing through the liquid ammonia line 47 into the combustion chamber 15s.

[0093] In this embodiment, gaseous ammonia NH3G and liquid ammonia NH3L can be simultaneously injected from the fuel nozzle 15n.

[0094] (13) A gas turbine plant according to a thirteenth aspect comprises: The gas turbine plant in the eleventh or twelfth aspect further includes a heat recovery boiler 21 that generates steam by utilizing the heat of the exhaust gas, which is the combustion gas exhausted from the turbine 16, and a heating medium line 53 that leads a portion of the steam generated in the heat recovery boiler 21 or a portion of the water heated in the heat recovery boiler 21 as the heating medium to the vaporizer 45.

[0095] (14) A gas turbine plant in a fourteenth aspect comprises: In the gas turbine plant in the eleventh aspect or the twelfth aspect, the vaporizer 45 can heat and vaporize the liquid ammonia NH3L by exchanging heat between the exhaust gas, which is the combustion gas exhausted from the turbine 16 as the heating medium, and the liquid ammonia NH3L pressurized by the main ammonia pump 44.

[0096] The fuel supply method in the above embodiment can be understood, for example, as follows. (15) A fuel supply method according to a fifteenth aspect includes the steps of: The ammonia supply state is switched between a plurality of states including an ammonia pressurization step S1 in which liquid ammonia NH3L from an ammonia tank 41 storing the liquid ammonia NH3L is pressurized, a vaporization step S5 in which the liquid ammonia NH3L pressurized in the ammonia pressurization step S1 is heat-exchanged with a heating medium to heat and vaporize the liquid ammonia NH3L, and a switching step S6 in which an ammonia supply state is switched between a plurality of states including a first state in which gaseous ammonia NH3G, which is the ammonia vaporized in the vaporization step S5, is introduced as fuel to a combustor 15 of a gas turbine 10, and a second state in which liquid ammonia NH3L pressurized in the ammonia pressurization step S1 and not heat-exchanged with the heating medium in the vaporization step S5 is introduced as fuel to the combustor 15.

[0097] In this embodiment, similarly to the first embodiment described above, it is possible to suppress the generation of NOx while stably burning ammonia.

[0098] (16) A fuel supply method according to a sixteenth aspect includes the steps of: In the fuel supply method according to the fifteenth aspect, in the switching step S6, an ammonia supply state is switched among a third state in which the gaseous ammonia NH3G and the liquid ammonia NH3L are introduced into the combustor 15, the first state, and the second state.

[0099] In this aspect, similar to the second aspect described above, by executing the third state during the process of transition from the first state to the second state, or during the process of transition from the second state to the first state, it is possible to ensure stable combustion of fuel during such transition processes.

[0100] (17) A fuel supply method according to a seventeenth aspect includes the steps of: In the fuel supply method according to the fifteenth or sixteenth aspect, a flow rate adjusting step S2 of adjusting a flow rate of the fuel supplied to the combustor 15 is further executed.

[0101] (18) A fuel supply method according to an eighteenth aspect includes the steps of: In the fuel supply method according to any one of the fifteenth to seventeenth aspects, the vaporization step S5 is performed by a vaporizer 45 into which the liquid ammonia NH3L pressurized in the ammonia pressurization step S1 flows in and into which the heating medium flows in, and which exchanges heat between the liquid ammonia NH3L and the heating medium. In the switching step S6, an ammonia supply state is switched between a state in which the liquid ammonia NH3L pressurized in the ammonia pressurization step S1 is introduced to the vaporizer 45 in order to realize the first state, and a state in which the liquid ammonia NH3L pressurized in the ammonia pressurization step S1 is not introduced to the vaporizer 45 in order to realize the second state.

[0102] (19) A fuel supply method according to a nineteenth aspect includes the steps of: In the fuel supply method according to any one of the fifteenth to seventeenth aspects, the vaporization step S5 is performed by a vaporizer 45 into which the liquid ammonia NH3L pressurized in the ammonia pressurization step S1 flows in and into which the heating medium flows in, and which exchanges heat between the liquid ammonia NH3L and the heating medium. In the switching step S6, a supply state of the heating medium is switched between a state in which the heating medium is introduced to the vaporizer 45 in order to realize the first state and a state in which the heating medium is not introduced to the vaporizer 45 in order to realize the second state.

[0103] (20) In a twentieth aspect, a fuel supply method includes: In the fuel supply method according to any one of the fifteenth to nineteenth aspects, a required output of the gas turbine is received from an outside, and one of a plurality of states including the first state and the second state is determined according to the required output, and a switching control step S3 is executed to execute the one state in the switching step S6.

[0104] The flow rate of fuel supplied to the combustor 15 changes depending on the required output. In this embodiment, similar to the eighth embodiment described above, the fuel supply state can be set to the first state when the fuel flow rate is high, and the fuel supply state can be set to the second state when the fuel flow rate is low.

[0105] (21) A fuel supply method according to a twenty-first aspect includes the steps of: In the fuel supply method according to any one of the fifteenth to twentieth aspects, a steam generation process S4 is further carried out in which heat of exhaust gas exhausted from the gas turbine 10 is utilized to generate steam, and in the vaporization process S5, a portion of the steam generated in the steam generation process S4 or hot water generated during the execution of the steam generation process S4 is used as the heating medium.

[0106] (22) A fuel supply method according to a twenty-second aspect includes the steps of: In the fuel supply method according to any one of the fifteenth to twentieth aspects, in the vaporization step S5, exhaust gas discharged from the gas turbine 10 is used as the heating medium. [Industrial Applicability]

[0107] According to one embodiment of the present disclosure, it is possible to suppress the generation of NOx while stably burning ammonia. [Explanation of symbols]

[0108] 10: Gas turbine 11: Gas turbine rotor 12: Intermediate casing 14: Compressor 14r: Compressor rotor 14c: Compressor casing 14i: Intake volume regulator (or IGV) 15: Combustor 15c: Combustion tube (or transition tube, or combustion chamber former) 15s: Combustion chamber 15b: Combustor body 15n: Fuel nozzle 16: Turbine 16r: Turbine rotor 16c: Turbine casing 20:Denitration equipment 21: Waste heat recovery boiler 22: Chimney 23: Steam turbine 24: Condenser 25: Pump 26: Water supply line 27: Main steam line 31: Inner cylinder 32: Outer cylinder 33: Liquid fuel flow path 33i:Liquid fuel inlet 33o:Liquid fuel injection port 34: Gas fuel flow passage 34i: Gaseous fuel inlet 34o: Gas fuel nozzle 40,40a,40b,40c,40d:Fuel supply equipment 41: Ammonia tank 42: Main ammonia line 43: Flow control valve 44: Main ammonia pump 45: Carburetor 45d: Heat transfer tube (evaporator) 46: Gaseous ammonia line 47: Liquid ammonia line 48, 48b: Switch 48g: Gaseous ammonia flow control valve 48i: Liquid ammonia flow control valve 51: Gaseous ammonia compressor 52: Liquid ammonia pump 53: Heating medium line 54: Heating medium valve 55: Heating medium recovery line 60: Control device A: Air Acom: Compressed air NH3G: Ammonia gas NH3L: Liquid ammonia An: Nozzle axis Ar: rotor axis Da: Axial direction Dab: Rear Daf: Front

Claims

1. A combustor; a turbine connected to the combustor; A heating unit that heats liquid ammonia as fuel; a fuel supply unit that supplies the fuel heated by the heating unit to the combustor; Equipped with the fuel supply unit includes a first flow rate adjusting means for adjusting a flow rate of the fuel supplied to the heating unit, The heating unit includes: a heat exchanger that exchanges heat between the fuel and at least a portion of steam generated by a heat recovery boiler that recovers heat contained in the combustion gas exhausted from the turbine; a second flow rate adjusting means for adjusting a flow rate of the water vapor supplied to the heat exchanger; A gas turbine system that supplies the fuel heated by the heating section to the combustor without thermally decomposing ammonia molecules.

2. The heating unit vaporizes the liquid ammonia as a fuel, The gas turbine system according to claim 1 , wherein the fuel supply unit supplies the vaporized gaseous ammonia to the combustor.

3. The fuel supply unit includes: an ammonia tank in which liquid ammonia is stored; a main ammonia pump for pressurizing liquid ammonia from the ammonia tank; a first fuel supply line that supplies the vaporized gaseous ammonia to the combustor; The gas turbine system of claim 2 .

4. 4. The gas turbine system according to claim 3, further comprising a second fuel supply line that supplies the liquid ammonia from the ammonia tank in a liquid state to the combustor, separately from the first fuel supply line.

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