Gas turbines and gas turbine equipment

Abstract

This gas turbine is provided with a combustor which can switch a fuel to be combusted between an ammonia fuel and a hydrocarbon-based fuel. The combustor has: a cylindrical body which has a cylindrical shape and through which a combustion gas flows; a fuel nozzle through which the ammonia fuel, the hydrocarbon-based fuel and the compressed air are emitted into the inside of the cylindrical body; an intermediate supply section which supplies a portion of the compressed air into the cylindrical body; and a flow amount adjustment section which can adjust the flow amount of the compressed air to be supplied into the cylindrical body. The flow amount adjustment section increases the flow amount of the compressed air to be supplied into the cylindrical body when it is intended to combust the ammonia fuel, and decreases the flow amount of the compressed air to be supplied into the cylindrical body when it is intended to combust the hydrocarbon-based fuel.

Description

[Technical Field]

[0001] The present disclosure relates to gas turbines and gas turbine installations. This application claims priority to Japanese Patent Application No. 2022-133982, filed on August 25, 2022, the contents of which are incorporated herein by reference. [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 driven by the combustion gas. The fuel supplied to the combustor is generally a hydrocarbon fuel, which is a fossil fuel such as natural gas or petroleum, but ammonia may also be used.

[0003] For example, Patent Document 1 describes a gas turbine that supplies ammonia as a main fuel, and in a combustion deterioration operating region where the combustibility of ammonia deteriorates, increases the proportion of fossil fuel in the fuel supplied to the gas turbine compared to normal operation. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] Japanese Patent Application Laid-Open No. 2010-19195 Summary of the Invention [Problem to be solved by the invention]

[0005] However, ammonia fuel has a low calorific value and a low combustion rate. In other words, ammonia fuel has poor combustibility compared to hydrocarbon-based fuel. Therefore, in a gas turbine that can simultaneously supply ammonia fuel and hydrocarbon-based fuel, it is difficult to maintain stable combustion whether ammonia fuel or hydrocarbon-based fuel is supplied.

[0006] Furthermore, when ammonia is used as fuel for a gas turbine, some of the nitrogen that forms ammonia during combustion generates NOx. Therefore, the less the amount of ammonia fuel supplied to the combustor is compared to the amount of compressed air supplied, and the less effective the combustion, the greater the amount of NOx generated. On the other hand, when hydrocarbon fuel is burned, NOx originating from the nitrogen in the compressed air is generated. Therefore, the closer the fuel and air supply amounts are to near stoichiometry, such as when the amounts of hydrocarbon fuel and compressed air supplied to the combustor are approximately the same, the higher the combustion temperature and the greater the amount of NOx generated. In other words, if the amount of compressed air supplied is the same when ammonia fuel and hydrocarbon fuel are supplied, it is difficult to suppress the amount of NOx generated.

[0007] The present disclosure provides a gas turbine and gas turbine equipment that can reduce the amount of NOx generated while maintaining stable combustion in a gas turbine that is supplied with both ammonia fuel and hydrocarbon-based fuel. [Means for solving the problem]

[0008] A gas turbine according to one aspect of the present disclosure includes: a compressor capable of compressing air to generate compressed air; a combustor capable of switching between ammonia fuel and a hydrocarbon-based fuel as a fuel to be burned and capable of generating combustion gas by burning at least one of the ammonia fuel and the hydrocarbon-based fuel in the compressed air supplied from the compressor; and a turbine capable of being driven by the combustion gas supplied from the combustor, wherein the combustor includes a cylindrical body through which the combustion gas generated by combustion of the ammonia fuel or the hydrocarbon-based fuel flows; The system includes a fuel nozzle that sprays air into the interior of the cylindrical body, an intermediate supply unit that supplies a portion of the compressed air supplied to the fuel nozzle to the cylindrical body downstream of the fuel nozzle in the flow direction of the combustion gas, and a flow rate adjustment unit that can adjust the flow rate of the compressed air supplied from the intermediate supply unit to the cylindrical body relative to the supply amount of the compressed air supplied to the fuel nozzle, wherein the flow rate adjustment unit increases the flow rate of the compressed air supplied from the intermediate supply unit to the cylindrical body when combusting the ammonia fuel, and decreases the flow rate of the compressed air supplied to the cylindrical body when combusting the hydrocarbon-based fuel.

[0009] A gas turbine facility according to one aspect of the present disclosure includes the gas turbine, an ammonia fuel supply facility capable of supplying the ammonia fuel to the gas turbine, and a hydrocarbon-based fuel supply facility capable of supplying the hydrocarbon-based fuel to the gas turbine. [Effects of the Invention]

[0010] According to the gas turbine and gas turbine facility of the present disclosure, it is possible to suppress the amount of NOx generated while maintaining stable combustion in a gas turbine supplied with ammonia fuel and hydrocarbon-based fuel. [Brief explanation of the drawings]

[0011] [Figure 1] FIG. 1 is a schematic configuration diagram of a gas turbine facility in a first embodiment according to an embodiment of the present disclosure. [Figure 2]FIG. 1 is a schematic cross-sectional view of a combustor in a first embodiment according to the present disclosure. [Figure 3] FIG. 4 is a schematic cross-sectional view of a combustor in a second embodiment according to the present disclosure. [Figure 4] FIG. 4 is a cross-sectional view taken along the line AA in FIG. 3. [Figure 5] FIG. 4 is an enlarged view of a main part of the combustor in FIG. 3. [Figure 6] FIG. 6 is an enlarged view of a main part of a combustor according to a modified example of the second embodiment, corresponding to FIG. 5. [Figure 7] FIG. 6 is an enlarged view of a main part of a combustor according to a third embodiment, corresponding to FIG. 5. [Figure 8] FIG. 6 is an enlarged view of a main part of a combustor according to a fourth embodiment, corresponding to FIG. 5. [Figure 9] FIG. 10 is a schematic cross-sectional view of a combustor in a fifth embodiment according to the present disclosure. [Figure 10] FIG. 9 is a cross-sectional view taken along the arrow BB in FIG. 8. [Figure 11] FIG. 9 is an enlarged view of a first main part of the combustor of FIG. 8. [Figure 12] FIG. 9 is a second enlarged view of the main part of the combustor of FIG. 8. [Figure 13] FIG. 10 is a schematic cross-sectional view of a combustor in a sixth embodiment according to the present disclosure. [Figure 14] 13 is a graph showing the ratio of the supply amounts of ammonia fuel and hydrocarbon-based fuel to compressed air in a sixth embodiment of the present disclosure. [Figure 15] FIG. 13 is a schematic cross-sectional view of a combustor in a seventh embodiment according to the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0012] Hereinafter, embodiments for carrying out a gas turbine 10 and a gas turbine facility 1 according to the present disclosure will be described with reference to the accompanying drawings. However, the present disclosure is not limited to these embodiments.

[0013] First Embodiment (Gas turbine equipment configuration) As shown in FIG. 1, the gas turbine facility 1 of this embodiment includes a gas turbine 10, an ammonia fuel supply facility 20, and a hydrocarbon-based fuel supply facility 30.

[0014] (Gas turbine configuration) The gas turbine 10 is capable of switching the fuel to be burned between ammonia fuel and hydrocarbon-based fuel. The gas turbine 10 is capable of being driven by combustion gas generated by burning at least one of the ammonia fuel and the hydrocarbon-based fuel. The gas turbine 10 of this embodiment includes a compressor 14, a combustor 15, a turbine 16, an intake duct 12, and an intermediate casing 13.

[0015] The compressor 14 is capable of compressing air to generate compressed air. The compressor 14 has a compressor rotor 14r that rotates about a rotor axis Ar, a compressor casing 14c that covers the compressor rotor 14r, and an IGV (inlet guide vane) 14v that is provided at the suction port of the compressor casing 14c. The IGV 14v adjusts the intake air volume, which is the flow rate of air sucked into the compressor casing 14c. The intake duct 12 is connected to the suction port of the compressor casing 14c.

[0016] The turbine 16 can be driven by high-temperature, high-pressure combustion gas supplied from the combustor 15. 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.

[0017] The intermediate casing 13 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 13.

[0018] The combustor 15 is capable of generating combustion gas by combusting at least one of ammonia fuel and hydrocarbon-based fuel in compressed air supplied from the compressor 14. The hydrocarbon-based fuel is a fuel containing hydrocarbons, such as fossil fuels such as natural gas and petroleum. The combustor 15 is capable of supplying ammonia fuel and hydrocarbon-based fuel. The combustor 15 is operable under three operating conditions: ammonia fuel only, hydrocarbon-based fuel only, and both ammonia fuel and hydrocarbon-based fuel are combusted by adjusting the supply amounts of the ammonia fuel and hydrocarbon-based fuel according to the operating conditions. Under the operating conditions in which both ammonia fuel and hydrocarbon-based fuel are combusted, the supply amounts of the ammonia fuel and the hydrocarbon-based fuel may be the same or different. The combustor 15 is fixed to the intermediate casing 13. As shown in FIG. 2 , the combustor 15 of this embodiment includes a cylindrical body 5, a fuel nozzle 6, an intermediate supply unit 7, and a flow rate adjustment unit 8.

[0019] The cylindrical body 5 defines a combustion chamber 50 therein. The combustion chamber 50 is the internal space of the cylindrical body 5. In other words, combustion gas generated by the combustion of at least one of ammonia fuel and hydrocarbon-based fuel flows through the interior of the cylindrical body 5. The cylindrical body 5 is disposed inside the intermediate casing 13, into which compressed air compressed by the compressor 14 flows. In the combustion chamber 50, at least one of ammonia fuel and hydrocarbon-based fuel is supplied together with the compressed air and combusted. The combustion gas generated by the combustion of at least one of ammonia fuel and hydrocarbon-based fuel flows through the combustion chamber 50 and is sent to the turbine 16. The cylindrical body 5 is formed in a cylindrical shape centered on the central axis of the combustor 15. Note that the cylindrical body 5 is not limited to a structure composed of only one member. The cylindrical body 5 may also have a structure in which multiple members are arranged in the direction of extension of the central axis.

[0020] The fuel nozzle 6 injects ammonia fuel, hydrocarbon-based fuel, and compressed air into the combustion chamber 50. The fuel nozzle 6 is fixed to one end (upstream end, first end) of the cylindrical body 5 that is located away from the turbine 16. The fuel nozzle 6 injects the ammonia fuel, hydrocarbon-based fuel, and compressed air into the combustion chamber 50 toward the turbine 16. The fuel nozzle 6 generates combustion gas by diffusion combustion under three conditions: ammonia fuel and compressed air, hydrocarbon-based fuel and compressed air, and ammonia fuel, hydrocarbon-based fuel, and compressed air. One fuel nozzle 6 is disposed inside the cylindrical body 5. The fuel nozzle 6 has at least one (two in this embodiment) first injection hole 61 for injecting ammonia fuel, at least one (one in this embodiment) second injection hole 62 for injecting hydrocarbon-based fuel, and at least one (two in this embodiment) third injection hole 63 for injecting compressed air.

[0021] The first injection hole 61, the second injection hole 62, and the third injection hole 63 are formed separately from one another within the fuel nozzle 6 so as to be independent of one another. The first injection hole 61, the second injection hole 62, and the third injection hole 63 of the first embodiment are formed so that the respective fluids are mixed until injected into the combustion chamber 50. The first injection hole 61 injects ammonia fuel introduced from outside the combustor 15 into the combustion chamber 50. The first injection hole 61 is located at the center in the radial direction of the fuel nozzle 6. The second injection hole 62 injects hydrocarbon-based fuel introduced from outside the combustor 15 into the combustion chamber 50. The third injection hole 63 injects compressed air introduced from inside the intermediate casing 13 into the combustion chamber 50. The third injection hole 63 is located between the first injection hole 61 and the second injection hole 62 in the radial direction of the fuel nozzle 6.

[0022] The first injection hole 61, the second injection hole 62, and the third injection hole 63 are not limited to being arranged inside one fuel nozzle 6. The first injection hole 61, the second injection hole 62, and the third injection hole 63 may each be formed in an independent nozzle. In other words, the fuel nozzle 6 may be made up of a plurality of nozzles. The fuel nozzle 6 may further have another structure such as a swirler.

[0023] The intermediate supply unit 7 supplies a portion of the compressed air supplied to the fuel nozzles 6 to the cylindrical body 5 from a location other than the fuel nozzles 6. The intermediate supply unit 7 is located within the intermediate casing 13. The intermediate supply unit 7 is located at a position downstream Df2 of the combustion gas flow direction Df relative to the fuel nozzles 6. Here, the combustion gas flow direction Df is the direction from one end of the cylindrical body 5 at which the fuel nozzles 6 are located to the other end (downstream end, second end) connected to the turbine 16. Therefore, the upstream side Df1 of the combustion gas flow direction Df is the side of the cylindrical body 5 at which the fuel nozzles 6 are located relative to the turbine 16. Furthermore, the downstream side Df2 of the combustion gas flow direction Df is the side of the cylindrical body 5 at which the turbine 16 is located relative to the fuel nozzles 6. Furthermore, the intermediate supply unit 7 of this embodiment has a communication hole 71.

[0024] The communication hole 71 is formed at a position away from the fuel nozzle 6 to communicate between the combustion chamber 50, which is inside the cylindrical body 5, and the outside of the cylindrical body 5. That is, the communication hole 71 of this embodiment connects the combustion chamber 50 and the space inside the intermediate casing 13 without going through the fuel nozzle 6. The communication hole 71 is formed at a position Df2 downstream of the fuel nozzle 6 in the flow direction Df of the combustion gas. The communication hole 71 is formed to supply compressed air to a position in the combustion chamber 50 that does not directly contribute to diffusion combustion. The communication hole 71 is formed near the middle of the cylindrical body 5 in the flow direction Df. The communication holes 71 are formed at multiple positions (e.g., four positions) spaced apart from one another along the outer circumferential surface of the cylindrical body 5 in the circumferential direction of the cylindrical body 5. The multiple communication holes 71 are arranged at equal intervals. The communication hole 71 is formed in the intermediate casing 13 so as to face the middle of the flow path of the compressed air introduced into the third injection hole 63. More specifically, it is preferable that the communication hole 71 be positioned between 30% and 70% from the tip of the fuel nozzle 6, assuming that the length of a straight line from the tip of the fuel nozzle 6 to the point where it is connected to the turbine 16 is the total length (100%) of the cylindrical body 5.

[0025] The number of communication holes 71 is not limited to a structure in which multiple communication holes 71 are formed as in this embodiment. There may be only one communication hole 71. Furthermore, the multiple communication holes 71 are not limited to being arranged at equal intervals, and may be arranged at different intervals from each other.

[0026] The flow rate adjustment unit 8 is capable of adjusting the flow rate of compressed air supplied from the intermediate supply unit 7 to the cylindrical body 5 relative to the supply rate of compressed air supplied to the fuel nozzle 6. In other words, the flow rate adjustment unit 8 is capable of adjusting the ratio between the supply rate of compressed air indirectly supplied to the combustion chamber 50 together with fuel via the third injection holes 63 and the flow rate of compressed air directly supplied to the combustion chamber 50 from the intermediate supply unit 7. The flow rate adjustment unit 8 adjusts the flow rate of compressed air supplied from the intermediate supply unit 7 to the combustion chamber 50 in accordance with the respective supply rates of ammonia fuel and hydrocarbon-based fuel supplied to the fuel nozzle 6. Specifically, the flow rate adjustment unit 8 increases the flow rate of compressed air supplied to the cylindrical body 5 when combusting ammonia fuel. On the other hand, the flow rate adjustment unit 8 reduces the flow rate of compressed air supplied to the cylindrical body 5 when combusting hydrocarbon-based fuel. In addition, the flow rate adjustment unit 8 of this embodiment has a valve device 81.

[0027] The valve device 81 is capable of adjusting the flow rate of compressed air flowing from the outside of the cylindrical body 5 into the combustion chamber 50, which is inside the cylindrical body 5. The valve device 81 is, for example, a flow rate control valve, an on / off valve, or a solenoid valve. The valve device 81 is arranged to block the communication hole 71. The valve device 81 adjusts the flow rate of compressed air passing through the communication hole 71. Specifically, the valve device 81 increases in opening degree (for example, it may be in a fully open state) as the amount of ammonia fuel supplied to the first injection hole 61 increases. On the other hand, the valve device 81 decreases in opening degree (for example, it may be in a fully closed state) as the amount of hydrocarbon-based fuel supplied to the second injection hole 62 increases. Furthermore, when ammonia fuel and hydrocarbon-based fuel are supplied simultaneously, the valve device 81 adjusts its opening degree in accordance with the amount of NOx, and the opening degree becomes the same as or medium as when only ammonia fuel is supplied. That is, in the case of simultaneous supply, the valve device 81 has an opening degree that is equal to or smaller than when only ammonia fuel is supplied to the fuel nozzle 6, and has an opening degree that is larger than when only hydrocarbon fuel is supplied to the fuel nozzle 6. A plurality of valve devices 81 of this embodiment are arranged so that one is disposed for one communication hole 71. That is, one valve device 81 is arranged so that it can close only one communication hole 71.

[0028] (Configuration of ammonia fuel supply equipment) 1, the ammonia fuel supply facility 20 is capable of supplying ammonia fuel to the gas turbine 10. The ammonia fuel supply facility 20 of this embodiment includes a first storage tank 21 and a first supply line 22.

[0029] Ammonia fuel in a liquid state is stored in the first storage tank 21. The first supply line 22 connects the first storage tank 21 and the fuel nozzle 6. The first supply line 22 heats and vaporizes the ammonia fuel in a liquid state and supplies it to the first injection hole 61. The first supply line 22 is capable of adjusting the amount of ammonia fuel supplied to the first injection hole 61. The first supply line 22 includes a heat exchanger (not shown) for vaporizing the ammonia in a liquid state, a pump (not shown) for increasing the pressure, a valve (not shown) for adjusting the supply amount, and the like.

[0030] (Configuration of hydrocarbon fuel supply equipment) The hydrocarbon fuel supply facility 30 is capable of supplying hydrocarbon fuel to the gas turbine 10. The hydrocarbon fuel supply facility 30 of this embodiment has a second storage tank 31 and a second supply line 32.

[0031] The second storage tank 31 stores hydrocarbon fuel. The second supply line 32 connects the second storage tank 31 and the fuel nozzle 6. When the hydrocarbon fuel is in a liquid state, the second supply line 32 heats and vaporizes the hydrocarbon fuel and supplies it to the second injection hole 62. The second supply line 32 is capable of adjusting the amount of hydrocarbon fuel supplied to the second injection hole 62. In this case, the second supply line 32 includes a heat exchanger (not shown) for vaporizing the hydrocarbon fuel in a liquid state, a pump (not shown) for increasing the pressure, a valve (not shown) for adjusting the supply amount, and the like. Note that when the hydrocarbon fuel is stored in the second storage tank 31 in a gaseous state, the hydrocarbon fuel is supplied to the second injection hole 62 either as is or after being pressurized. In this case, the second supply line 32 includes a pump (not shown) for increasing the pressure of the hydrocarbon fuel in a gaseous state, a valve (not shown) for adjusting the supply amount, and the like.

[0032] (Action and effect) In the gas turbine facility 1 having the above configuration, there are cases where only ammonia fuel is supplied to the gas turbine 10, cases where only hydrocarbon-based fuel is supplied, and cases where ammonia fuel and hydrocarbon fuel are supplied simultaneously.

[0033] First, when only ammonia fuel is supplied, ammonia fuel is supplied from the first storage tank 21 to the fuel nozzle 6 through the first supply line 22. The ammonia fuel supplied to the fuel nozzle 6 is injected into the combustion chamber 50 through the first injection hole 61. At that time, compressed air supplied to the fuel nozzle 6 through the intermediate casing 13 is injected into the combustion chamber 50 through the third injection hole 63. No hydrocarbon fuel is injected through the second injection hole 62. As a result, only the ammonia fuel and compressed air undergo diffusion combustion in the combustion chamber 50. Note that the combustion here is not limited to diffusion combustion but may be combustion suited to the configuration of the fuel nozzle 6. Therefore, instead of diffusion combustion, a combustion form similar to premixed combustion may also be used. At the same time, the valve device 81 is opened widely. As a result, much of the compressed air in the intermediate casing 13 flows into the combustion chamber 50 through the communication hole 71. In other words, some of the compressed air that would otherwise be supplied to the third injection hole 63 flows directly into the combustion chamber 50 through the communication hole 71. Therefore, when only ammonia fuel is supplied to the fuel nozzle 6, the flow rate of the compressed air supplied to the third injection hole 63 can be reduced.

[0034] Furthermore, when only hydrocarbon fuel is supplied, the hydrocarbon fuel is supplied from the second storage tank 31 to the fuel nozzle 6 through the second supply line 32. The hydrocarbon fuel supplied to the fuel nozzle 6 is injected into the combustion chamber 50 through the second injection hole 62. At that time, compressed air is injected into the combustion chamber 50 from the third injection hole 63. Furthermore, ammonia fuel is not injected from the first injection hole 61. As a result, only the hydrocarbon fuel and compressed air are combusted in the combustion chamber 50. At the same time, the valve device 81 is slightly opened (or closed). As a result, almost no compressed air in the intermediate casing 13 flows into the combustion chamber 50 through the communication hole 71. In other words, the compressed air that should be supplied to the third injection hole 63 flows into the combustion chamber 50 from the third injection hole 63 with almost no decrease. In this way, when only hydrocarbon fuel is supplied to the fuel nozzle 6, the flow rate of the compressed air supplied to the third injection hole 63 can be increased.

[0035] Furthermore, when both ammonia fuel and hydrocarbon-based fuel are supplied, ammonia fuel is supplied from the first storage tank 21 to the fuel nozzle 6 through the first supply line 22. Simultaneously, hydrocarbon-based fuel is supplied from the second storage tank 31 to the fuel nozzle 6 through the second supply line 32. Therefore, ammonia fuel is injected into the combustion chamber 50 through the first injection hole 61, and hydrocarbon-based fuel is injected into the combustion chamber 50 through the second injection hole 62. At that time, compressed air is injected into the combustion chamber 50 through the third injection hole 63. As a result, the three fuels, i.e., ammonia fuel, hydrocarbon-based fuel, and compressed air, are combusted in the combustion chamber 50. At the same time, the valve device 81 is opened to a moderate degree. As a result, the amount of compressed air in the intermediate casing 13 that is equal to or less than when only ammonia fuel is combusted, but greater than when only hydrocarbon-based fuel is combusted, flows in through the communication hole 71. In other words, the amount of compressed air supplied to the third injection hole 63 is not significantly increased or decreased. Therefore, an appropriate amount of compressed air is supplied to the third injection holes 63 when burning both the ammonia fuel and the hydrocarbon fuel.

[0036] In the combustor 15 of the gas turbine 10 described above, when ammonia fuel is used to generate combustion gas, the flow rate of compressed air used for diffusion combustion in the fuel nozzle 6 can be reduced. Ammonia fuel is known to have poor combustibility due to its lower calorific value and slower combustion rate than hydrocarbon fuels. Therefore, if compressed air is supplied at the same rate as when hydrocarbon fuel is burned, it is difficult to burn the ammonia fuel in a stable state (stable combustion), and flame stability cannot be maintained. However, as described above, the supply rate of compressed air is reduced when ammonia fuel is supplied to the fuel nozzle 6. As a result, when ammonia fuel is burned, it is possible to prevent unstable combustion due to excessive supply of compressed air. This makes it possible to maintain stable combustion and flame stability when burning ammonia fuel.

[0037] Furthermore, by reducing the supply amount of compressed air, the proportion of ammonia fuel in the ratio of the supply amounts of ammonia fuel and compressed air increases. As a result, as described above, flame stability is maintained when the ammonia fuel is burned, and the amount of nitrogen components remaining in the combustion gas originating from nitrogen in the ammonia fuel can be significantly reduced. Therefore, the amount of NOx generated when the ammonia fuel is burned can be suppressed.

[0038] Furthermore, when generating combustion gas using a hydrocarbon fuel, the flow rate of compressed air used for diffusion combustion in the fuel nozzle 6 can be increased. Hydrocarbon fuel requires more compressed air for stable combustion than ammonia fuel. In contrast, when hydrocarbon fuel is supplied to the fuel nozzle 6, the amount of compressed air supplied to the fuel nozzle 6 is increased compared to when ammonia fuel is supplied to the fuel nozzle 6. As a result, the amount of compressed air required to be supplied to the fuel nozzle 6 when combusting the hydrocarbon fuel can be secured. This allows stable combustion to continue even when combusting the hydrocarbon fuel, and flame stability can be maintained without the occurrence of flashback or the like.

[0039] Furthermore, by increasing the amount of compressed air supplied, the proportion of hydrocarbon fuel in the ratio of the amount of hydrocarbon fuel to the amount of compressed air supplied decreases. As a result, flame stability is maintained when the hydrocarbon fuel is burned, the generation of high-temperature regions inside the cylindrical body 5 is suppressed, and the amount of nitrogen components remaining in the combustion gas originating from nitrogen in the compressed air can be significantly reduced. Therefore, the amount of NOx generated when the hydrocarbon fuel is burned can be suppressed.

[0040] In this way, regardless of whether ammonia fuel or hydrocarbon-based fuel is supplied to the gas turbine 10, which is supplied with ammonia fuel and hydrocarbon-based fuel, it is possible to suppress the amount of NOx generated while maintaining stable combustion. Therefore, it is possible to effectively achieve both combustion with ammonia fuel and combustion with hydrocarbon-based fuel.

[0041] Furthermore, in the flow rate adjusting unit 8, the flow rate of the compressed air flowing into the cylindrical body 5 is adjusted by the valve device 81. Therefore, the supply amount of compressed air when ammonia fuel is supplied and when hydrocarbon fuel is supplied can be adjusted with a simple configuration.

[0042] Further, compressed air is supplied to the cylindrical body 5 through the communication hole 71 from a position away from the fuel nozzle 6 and a position downstream Df2 with respect to the fuel nozzle 6 in the flow direction Df of the combustion gas. In the cylindrical body 5, a certain amount of space is required near the tip of the fuel nozzle 6 to efficiently combust the ammonia fuel, hydrocarbon fuel, and compressed air supplied from the fuel nozzle 6. Meanwhile, the communication hole 71 allows the compressed air to flow into the combustion chamber 50 from a position downstream Df2 away from the fuel nozzle 6. Therefore, the compressed air flowing into the combustion chamber 50 from the communication hole 71 does not directly participate in diffusion combustion. Therefore, a structure capable of supplying compressed air to the combustion chamber 50 while ensuring a space for stably burning the ammonia fuel and hydrocarbon fuel supplied from the fuel nozzle 6 can be obtained with a simple configuration.

[0043] In particular, in the cylindrical body 5, the area up to 30% from the tip of the fuel nozzle 6 often becomes the space required to burn up the fuel supplied from the fuel nozzles 6, 6G. In other words, the communication hole 71 of this embodiment is disposed in a position beyond the area where the fuel supplied from the fuel nozzle 6 has been burned up. Therefore, it is possible to more reliably ensure the space for stably burning the fuel supplied from the fuel nozzle 6.

[0044] Furthermore, when a large amount of fuel is supplied from the fuel nozzle 6 to the cylindrical body 5, oxygen becomes insufficient, and the surplus fuel that is not completely burned is sent to the downstream area. At that time, the surplus fuel is burned in a diluted air portion in a region of about 30% from the rear end of the cylindrical body 5, even within the downstream area of ​​the cylindrical body 5. Therefore, by forming the communication hole 71 facing the region up to 70% from the tip of the fuel nozzle 6, a region for burning the surplus fuel can be secured in the downstream area of ​​the cylindrical body 5.

[0045] Furthermore, the communication holes 71 are formed at a plurality of positions spaced apart from one another with respect to the cylindrical body 5. Therefore, the compressed air supplied near the middle of the cylindrical body 5 is supplied to the combustion chamber 50 without being significantly biased toward a portion near the inner circumferential surface of the cylindrical body 5. In particular, since the communication holes 71 are arranged at equal intervals, the compressed air is supplied to the combustion chamber 50 in a nearly uniform state. Therefore, whether ammonia fuel or hydrocarbon fuel is supplied, efficient and stable combustion can be maintained over a wide area of ​​the combustion chamber 50, while the amount of NOx generated can be effectively suppressed.

[0046] Second Embodiment Next, a second embodiment of the gas turbine equipment 1 according to the present disclosure will be described. In the second embodiment described below, components common to the first embodiment will be denoted by the same reference numerals in the drawings, and description thereof will be omitted. In the second embodiment, the configurations of the intermediate supply unit 7B and the flow rate adjustment unit 8B are different from those of the first embodiment.

[0047] As shown in FIGS. 3 to 5 , the intermediate supply unit 7B of the second embodiment includes an annular flow passage forming portion 73 and a connecting flow passage portion 74. The annular flow passage forming portion 73 is disposed within the intermediate casing 13. The annular flow passage forming portion 73 defines an annular flow passage 730 therein, through which compressed air can flow along the outer periphery of the cylindrical body 5. The annular flow passage forming portion 73 covers the entire outer periphery of the cylindrical body 5. Therefore, the annular flow passage forming portion 73 is disposed so as to cover the multiple communication holes 71. The annular flow passage forming portion 73 is directly fixed to the outer periphery of the cylindrical body 5 with welds 75 without any gaps. Therefore, the communication hole 71 of this embodiment connects the combustion chamber 50 and the annular flow passage 730. The multiple communication holes 71 are connected to each other outside the cylindrical body 5 by the annular flow passage 730. The connecting flow passage portion 74 connects the annular flow passage forming portion 73 and the valve device 81B. The connecting flow passage portion 74 of this embodiment is a curved tubular member such as an elbow. The connection flow path portion 74 is formed so that its flow path cross section is smaller than the flow path cross section of the annular flow path 730. The connection flow path portion 74 is connected to the surface of the annular flow path forming portion 73 that is farthest from the cylindrical body 5. The opening area at the connection position between the connection flow path portion 74 and the annular flow path forming portion 73 may be the same as or different from the opening area of ​​the communication hole 71.

[0048] In the flow rate adjustment unit 8B of the second embodiment, the valve device 81B is connected to the connection flow path portion 74. The valve device 81B is, for example, a flow rate adjustment valve, an on / off valve, or a solenoid valve. In other words, the valve device 81B adjusts the flow rate of the compressed air flowing into the connection flow path portion 74, thereby adjusting the flow rate of the compressed air supplied from the annular flow path 730 and the communication holes 71 to the combustion chamber 50. Only one valve device 81B is provided for the connection flow path portion 74. In other words, in the second embodiment, only one valve device 81B is provided for each of the plurality of communication holes 71.

[0049] (Action and effect) In the combustor 15 described above, a portion of the compressed air supplied to the intermediate casing 13 flows into the connecting flow path portion 74 via the valve device 81B. The compressed air that has flowed into the connecting flow path portion 74 then flows into the annular flow path forming portion 73. At this time, the annular flow path forming portion 73 functions as a damper, causing the compressed air present in the annular flow path 730 to be in a nearly uniform pressure state. The compressed air then fills the annular flow path 730 and flows into the combustion chamber 50 through the multiple communication holes 71. As a result, the compressed air that has been in a nearly uniform pressure state in the annular flow path forming portion 73 can be supplied to the combustion chamber 50 through the multiple communication holes 71. Therefore, the compressed air supplied from the multiple communication holes 71 is supplied to the combustion chamber 50 at substantially the same pressure state regardless of the position. Therefore, whether ammonia fuel or hydrocarbon fuel is supplied, more efficient and stable combustion can be maintained over a wide area of ​​the combustion chamber 50, while the amount of NOx generated can be more effectively reduced. Furthermore, by using only one valve device 81B, compressed air can be uniformly supplied to the combustion chamber 50. Therefore, by using multiple valve devices, it is possible to avoid variations in the supply state of compressed air due to manufacturing tolerances or the like for each valve device.

[0050] The annular flow path forming portion 73 is not limited to a structure that covers the entire outer periphery of the cylindrical body 5. The annular flow path forming portion 73 may be a structure that covers only a portion of the outer periphery of the cylindrical body 5. Furthermore, the cross-sectional area of ​​the annular flow path 730 is not limited to a structure that is constant over the entire periphery. The cross-sectional area of ​​the annular flow path 730 may vary partially, for example, becoming smaller midway, as long as a sufficiently large area is ensured relative to the communication holes 71.

[0051] <Modification of the second embodiment> In the second embodiment, the position at which the connection flow path portion 74 is connected to the annular flow path forming portion 73 is not limited in any way. The connection flow path portion 74 may be connected to a surface of the annular flow path forming portion 73 that faces the flow direction Df of the combustion gas. In this case, for example, as shown in FIG. 6, the connection flow path portion 74C may be connected to a surface of the annular flow path forming portion 73 that faces the downstream side Df2 in the flow direction Df of the combustion gas.

[0052] Third Embodiment Next, a third embodiment of the gas turbine equipment 1 according to the present disclosure will be described. Note that, in the third embodiment described below, components common to the first and second embodiments are denoted by the same reference numerals in the drawings, and descriptions thereof will be omitted. In the third embodiment, as shown in FIG. 7 , an intermediate supply unit 7D has a supply pipe 76. The supply pipe 76 is disposed in the communication hole 71. The supply pipe 76 is formed as a tubular member having the same shape as the communication hole 71. The supply pipe 76 is formed to extend inward from the inner circumferential surface of the cylindrical body 5. In other words, the supply pipe 76 is disposed in a state protruding from the inner circumferential surface of the cylindrical body 5 toward the interior of the cylindrical body 5. As a result, the supply pipe 76 supplies the compressed fluid present in the annular flow path 730 to the vicinity of the center of the combustion chamber 50, which is away from the inner circumferential surface of the cylindrical body 5. Note that the supply pipe 76 may be disposed in all of the communication holes 71, or in only some of the communication holes 71.

[0053] (Action and effect) By disposing the supply pipe 76 in this manner, the compressed air flowing into the combustion chamber 50 from the communication hole 71 is delivered by the supply pipe 76 to near the center of the combustion chamber 50, which is deeper than the inner circumferential surface of the cylindrical body 5. This allows the compressed air to be stably supplied deep into the combustion chamber 50, away from the communication hole 71. Therefore, even in a situation where the compressed air supplied from the communication hole 71 immediately flows toward the downstream side Df2, such as when the flow velocity of the combustion gas in the combustion chamber 50 is high, the compressed air can be supplied near the center of the combustion chamber 50. Therefore, regardless of whether ammonia fuel or hydrocarbon fuel is supplied, the generation of unburned fuel and the generation of localized high-temperature regions can be suppressed over a wide area of ​​the combustion chamber 50. Therefore, the amount of NOx generated can be more effectively suppressed while maintaining more efficient and stable combustion over a wide area of ​​the combustion chamber 50.

[0054] <Fourth embodiment> Next, a fourth embodiment of the gas turbine equipment 1 according to the present disclosure will be described. Note that in the fourth embodiment described below, components common to the first to third embodiments are denoted by the same reference numerals in the drawings, and descriptions thereof will be omitted. In the fourth embodiment, the annular flow-path forming portion 73 is not limited to a structure in which it is directly connected to the outer circumferential surface of the cylindrical body 5, as in the second and third embodiments. For example, as shown in FIG. 8 , the annular flow-path forming portion 73 may be disposed with a gap 770 from the outer circumferential surface of the cylindrical body 5. Specifically, the intermediate supply unit 7E includes a gap forming member 77 connecting the annular flow-path forming portion 73 and the cylindrical body 5. The gap forming member 77 forms a gap 770 between the annular flow-path forming portion 73 and the outer circumferential surface of the cylindrical body 5. The gap forming member 77 is an annular member formed on the outside of the cylindrical body 5 to cover the communication hole 71. In this embodiment, the gap 770 is a sealed space between the gap forming member 77, the annular flow-path forming portion 73, and the cylindrical body 5.

[0055] (Action and effect) As described above, a gap 770 is formed between the annular flow path forming portion 73 and the outer peripheral surface of the cylindrical body 5. Therefore, even if thermal expansion occurs in the cylindrical body 5 due to the influence of high-temperature combustion gas flowing through the combustion chamber 50, the amount of thermal expansion can be absorbed without affecting the annular flow path forming portion 73. This makes it possible to stably maintain the fixed state between the annular flow path forming portion 73 and the cylindrical body 5.

[0056] Fifth Embodiment Next, a fifth embodiment of the gas turbine equipment 1 according to the present disclosure will be described. In the fifth embodiment described below, components common to the first to fourth embodiments will be denoted by the same reference numerals in the drawings, and description thereof will be omitted. In the fifth embodiment, the intermediate supply section 7F is not limited to a structure including the annular flow path forming section 73, as in the second to fourth embodiments.

[0057] As shown in Figures 9 and 10, the intermediate supply section 7F of the fifth embodiment does not have an annular flow path forming section 73, and a connection flow path section 74F is fixed directly to the outer peripheral surface of the cylindrical body 5. The connection flow path section 74F is arranged to cover the communication hole 71. Therefore, the communication hole 71 of this embodiment connects the combustion chamber 50 and the connection flow path section 74F. A plurality of connection flow path sections 74F are arranged so that one is arranged for one communication hole 71. In other words, one connection flow path section 74F is arranged so that it can block one communication hole 71. Furthermore, each of the plurality of connection flow path sections 74F has an independent valve device 81B.

[0058] 11 and 12, the intermediate supply section 7F has a plurality of seals 78. The seals 78 are respectively arranged between the connection flow path section 74F and the valve device 81B, and between the connection flow path section 74F and the cylindrical body 5. The seals 78 are non-contact seals that can be used in high temperature and high pressure regions, such as floating ring seals.

[0059] In a structure such as that of the second embodiment, the sealing portion 78 may be disposed between the annular flow path forming portion 73 and the cylindrical body 5, or between the annular flow path forming portion 73 and the connecting flow path portion 74F.

[0060] 12, the combustor 15 has an annular sleeve portion 55 disposed inside the cylindrical body 5 so as to surround the communication hole 71. The sleeve portion 55 forms a flow path through which cooling air can circulate between the sleeve portion 55 and the inner circumferential surface of the cylindrical body 5. Like a flow sleeve, part of the compressed air discharged from the compressor 14 is supplied to the sleeve portion 55 as cooling air.

[0061] In addition, the sleeve portion 55 may be disposed with respect to the communication hole 71 covered by the annular flow path forming portion 73 in a structure such as that of the second embodiment.

[0062] (Action and effect) As described above, an independent valve device 81B is disposed in each communication hole 71 via the connecting flow path portion 74F. As a result, the valve device 81B can be adjusted separately or simultaneously for each communication hole 71. Therefore, regardless of whether ammonia fuel or hydrocarbon fuel is supplied, the amount of compressed air supplied to the combustion chamber 50 can be adjusted appropriately. Therefore, even if uneven temperature distribution or concentration distribution occurs in the cylindrical body 5 or the combustion chamber 50 depending on the operating state, the supply amount can be adjusted as desired, making it easier to suppress the amount of NOx generated.

[0063] Furthermore, by providing the seal portion 78, even if high-temperature, high-pressure compressed air flows, leakage of the compressed air from the connection points of the various components can be suppressed.

[0064] Furthermore, the provision of the sleeve portion 55 makes it possible to cool the area around the communication hole 71. Therefore, thermal expansion around the communication hole 71 due to the influence of high-temperature combustion gas flowing through the combustion chamber 50 can be suppressed.

[0065] Sixth Embodiment Next, a sixth embodiment of the gas turbine equipment 1 according to the present disclosure will be described with reference to Fig. 13 and Fig. 14. In the sixth embodiment described below, components common to the first to fifth embodiments are denoted by the same reference numerals in the drawings, and description thereof will be omitted. In the sixth embodiment, a fuel nozzle 6G and a flow rate adjusting unit 8G are different.

[0066] The fuel nozzle 6G of the sixth embodiment has a mixer 65 that forms a mixing space 650 in which fluids injected from the first injection hole 61, the second injection hole 62, and the third injection hole 63 are mixed before being supplied to the combustion chamber 50. The mixer 65 forms a tip portion of the fuel nozzle 6G that is connected to the combustion chamber 50. The mixer 65 is connected to the first injection hole 61, the second injection hole 62, and the third injection hole 63. Only a predetermined fixed amount of fluid is allowed to flow into the mixing space 650. That is, in the fuel nozzle 6G of the second embodiment, the supplied ammonia fuel, hydrocarbon-based fuel, and compressed air are mixed and injected as a fixed amount of fluid from the mixer 65 into the combustion chamber 50. As a result, the amounts of ammonia fuel, hydrocarbon-based fuel, and compressed air supplied to the fuel nozzle 6G are limited to a fixed amount.

[0067] The flow rate adjustment unit 8G is not limited to a structure including valve devices 81 and 81B as described in the first to fifth embodiments. That is, the flow rate adjustment unit 8G of the sixth embodiment does not include valve devices 81 and 81B. The flow rate adjustment unit 8G of the sixth embodiment keeps the amounts of ammonia fuel, hydrocarbon-based fuel, and compressed air supplied to the fuel nozzle 6G constant, and changes the ratio of the amount of ammonia fuel and hydrocarbon-based fuel supplied to the compressed air. The flow rate adjustment unit 8G is capable of adjusting the amount of at least one of the ammonia fuel and the hydrocarbon-based fuel supplied, thereby adjusting the flow rate of the compressed air supplied to the cylindrical body 5 from the communication hole 71. In the sixth embodiment, as described above, the mixer 65 keeps the amounts of ammonia fuel, hydrocarbon-based fuel, and compressed air supplied to the fuel nozzle 6 constant. In this state, the flow rate adjuster 8G is capable of adjusting the supply amount of at least one of the ammonia fuel and the hydrocarbon-based fuel so that the supply amount of the ammonia fuel when the ammonia fuel is supplied to the fuel nozzle 6G is greater than the supply amount of the hydrocarbon-based fuel when the hydrocarbon-based fuel is supplied to the fuel nozzle 6G. Specifically, the flow rate adjuster 8G of the second embodiment has a first supply amount adjuster 85 and a second supply amount adjuster 86, as shown in FIG.

[0068] The first supply amount adjustment unit 85 adjusts the amount of ammonia fuel supplied to the fuel nozzle 6G. The first supply amount adjustment unit 85 is disposed in the first supply line 22. The first supply amount adjustment unit 85 is, for example, a flow rate adjustment valve, an on / off valve, or a solenoid valve. As the aperture of the first supply amount adjustment unit 85 increases, the amount of ammonia fuel supplied from the first supply line 22 to the first injection hole 61 increases. Conversely, as the aperture of the first supply amount adjustment unit 85 decreases, the amount of ammonia fuel supplied from the first supply line 22 to the first injection hole 61 decreases.

[0069] The second supply amount adjustment unit 86 adjusts the amount of hydrocarbon fuel supplied to the fuel nozzle 6G. The second supply amount adjustment unit 86 is disposed in the second supply line 32. The second supply amount adjustment unit 86 is, for example, a flow rate adjustment valve, an on / off valve, or a solenoid valve. As the aperture of the second supply amount adjustment unit 86 increases, the amount of hydrocarbon fuel supplied from the second supply line 32 to the second injection holes 62 increases. Conversely, as the aperture of the second supply amount adjustment unit 86 decreases, the amount of hydrocarbon fuel supplied from the second supply line 32 to the second injection holes 62 decreases. Furthermore, even when the second supply amount adjustment unit 86 is fully open, the flow rate that can flow through the second supply line 32 is reduced compared to when the first supply amount adjustment unit 85 is fully open. In other words, when both the first supply amount adjustment unit 85 and the second supply amount adjustment unit 86 are fully open, the amount of ammonia fuel supplied is greater than the amount of hydrocarbon fuel. Specifically, it is preferable that the second supply amount adjustment unit 86 is capable of flowing the ammonia fuel to the first supply amount adjustment unit 85 at a flow rate that corresponds to the inverse ratio of the ratio, based on the ratio of the calorific value of the ammonia fuel to the calorific value of the hydrocarbon-based fuel. More specifically, when the calorific value and WI (Wobbe Index) of the hydrocarbon-based fuel are about four times the calorific value of the ammonia fuel, the second supply amount adjustment unit 86 can only flow the ammonia fuel to the first supply amount adjustment unit 85 at a flow rate that is about ¼.

[0070] (Action and effect) The flow rate adjusting unit 8G adjusts the amounts of ammonia fuel, hydrocarbon-based fuel, and compressed air supplied to the fuel nozzle 6G, as shown in Fig. 14. Specifically, when both ammonia fuel and hydrocarbon-based fuel are supplied, as shown in "mixed combustion" in Fig. 14, the first supply amount adjusting unit 85 and the second supply amount adjusting unit 86 are adjusted so that the ratio between the total amount of ammonia fuel and hydrocarbon-based fuel supplied and the amount of compressed air supplied becomes close to 1:1.

[0071] Furthermore, when only ammonia fuel is supplied, as shown in "NH3 only" in Fig. 14 , the first supply amount adjustment unit 85 is opened and the second supply amount adjustment unit 86 is closed so that the amount of ammonia fuel supplied is greater than the amount of compressed air supplied. As a result, compared to the case of "mixed combustion," more ammonia fuel is supplied to the mixing space 650 from the first injection hole 61 and less compressed air is supplied from the third injection hole 63. Then, most of the compressed air that cannot flow into the third injection hole 63 is supplied to the combustion chamber 50 from the communication hole 71. As a result, most of the compressed air in the intermediate casing 13 flows into the combustion chamber 50 from the communication hole 71. In other words, some of the compressed air that would have been supplied to the third injection hole 63 flows directly into the combustion chamber 50 from the communication hole 71.

[0072] Furthermore, when only hydrocarbon-based fuel is supplied, as shown in "CH4 only" in FIG. 14, the first supply amount adjustment unit 85 is closed and the second supply amount adjustment unit 86 is opened so that the amount of hydrocarbon-based fuel supplied is greater than the amount of compressed air supplied. Furthermore, the second supply amount adjustment unit 86 is configured to allow only a very small flow rate to flow through the first supply amount adjustment unit 85. Therefore, in the case of "CH4 only," the flow rate of compressed air flowing into the mixing space 650 from the third injection hole 63 is greater than in the case of "NH3 only" or "mixed combustion." As a result, the amount of compressed air that cannot flow into the third injection hole 63 is reduced. As a result, less compressed air in the intermediate casing 13 flows into the combustion chamber 50 through the communication hole 71. In other words, when hydrocarbon-based fuel is used, the flow rate of compressed air used in the fuel nozzle 6 can be increased compared to when ammonia fuel is used.

[0073] In this way, by adjusting the supply amount of ammonia fuel and the supply amount of hydrocarbon-based fuel, the flow rate of compressed air used in the fuel nozzle 6 can be adjusted. Therefore, it is not necessary to always provide the valve devices 81, 81B, and with a simpler configuration and control that only changes the supply amount of ammonia fuel and the supply amount of hydrocarbon-based fuel, it is possible to suppress the amount of NOx generated while maintaining stable combustion, regardless of whether ammonia fuel or hydrocarbon-based fuel is supplied. Therefore, it is possible to effectively achieve both combustion by ammonia fuel and combustion by hydrocarbon-based fuel.

[0074] As described above, the flow rate adjusting section 8G of the sixth embodiment is applicable to a structure without the valve devices 81, 81B, but may also be applicable to a structure further including the valve devices 81, 81B.

[0075] Seventh Embodiment Next, a seventh embodiment of the gas turbine equipment 1 according to the present disclosure will be described with reference to Fig. 15. In the seventh embodiment described below, components common to the first to sixth embodiments are denoted by the same reference numerals in the drawings, and descriptions thereof will be omitted. The seventh embodiment differs in that a flow rate adjusting unit 8H adjusts the flow rate based on the operating state of the combustor 15.

[0076] The gas turbine 10 of the seventh embodiment further includes a detection unit 9 that detects the operating state of the combustor 15. Specifically, the detection unit 9 of the present embodiment detects the temperature in the combustor 15. The detection unit 9 may be any device that can detect the operating state of the combustor 15. In other words, the detection unit 9 may be any device that can grasp the supply states of ammonia fuel, hydrocarbon fuel, and compressed air. For example, the detection unit 9 may be a device that detects at least one of the amount and temperature of ammonia fuel supplied to the fuel nozzle 6, the amount and temperature of hydrocarbon fuel supplied, and the amount and temperature of compressed air supplied. The detection unit 9 may also be a device that detects the temperature of the combustion gas near the point where it flows into the turbine 16, the concentration of NOx contained in the exhaust gas, or the concentration of ammonia, which is unburned fuel contained in the exhaust gas. Furthermore, the detection unit 9 may detect multiple states of the fluids supplied and the state of the combustion result in the combustor 15.

[0077] The flow rate adjustment unit 8H of the seventh embodiment also includes a valve control device 88 that controls the valve device 81 based on the detection result of the detection unit 9. The valve control device 88 is capable of adjusting the flow rate of compressed air supplied to the combustion chamber 50 by changing the aperture of the valve device 81 in accordance with the detection result of the detection unit 9. Specifically, when the temperature of the combustor 15 detected by the detection unit 9 exceeds a first threshold, the valve control device 88 sends an instruction to reduce the aperture of the valve device 81. The first threshold is, for example, a temperature value corresponding to a state in which only ammonia fuel is supplied to the fuel nozzle 6, and the supply of hydrocarbon-based fuel is started to switch to a mixed combustion state of ammonia fuel and hydrocarbon-based fuel. Furthermore, when the temperature of the combustor 15 detected by the detection unit 9 exceeds a second threshold that is higher than the first threshold, the valve control device 88 sends an instruction to further reduce the aperture of the valve device 81 (for example, to a fully closed state). The second threshold value is, for example, a temperature value corresponding to a case where a mixed combustion state in which both ammonia fuel and hydrocarbon-based fuel are supplied is switched to a state in which the supply of ammonia fuel is stopped and only hydrocarbon-based fuel is supplied to the fuel nozzle 6.

[0078] The valve control device 88 described above is a computer. In terms of hardware, the valve control device 88 has a CPU (Central Processing Unit) that performs various calculations, a main storage device such as memory that serves as a work area for the CPU, an auxiliary storage device such as a hard disk drive, input devices such as a keyboard and a mouse, and a display device. The valve control device 88 may be incorporated as part of the functions of a control device (not shown) of the gas turbine facility 1.

[0079] (Action and effect) In this way, by controlling the valve device 81 with the valve control device 88 based on the detection result of the detection unit 9, the flow rate of compressed air sent from the communication hole 71 to the combustion chamber 50 by the valve device 81 can be adjusted without delay in accordance with the operating state of the combustor 15. Furthermore, even at the timing of switching between the supply of ammonia fuel and the supply of hydrocarbon-based fuel, stable combustion can be maintained and the amount of NOx generated can be suppressed.

[0080] Furthermore, between ammonia fuel and hydrocarbon-based fuel, the hydrocarbon-based fuel has a much higher calorific value than the ammonia fuel. Therefore, by detecting the temperature of the combustor 15 with the detection unit 9, it is possible to easily grasp the amount of ammonia fuel and the amount of hydrocarbon-based fuel being supplied.

[0081] (Other embodiments) The above describes in detail the embodiments of the present disclosure with reference to the drawings, but the specific configuration is not limited to this embodiment, and design changes and the like are also included within the scope that does not deviate from the gist of the present disclosure.

[0082] The above-described gas turbine facility 1 is not limited to the structure described in this embodiment. For example, the gas turbine facility 1 may include other components such as a control device that controls various devices, a denitration device that decomposes NOx contained in the exhaust gas from the gas turbine 10, and a chimney that discharges the exhaust gas that has flowed out from the denitration device to the outside.

[0083] Furthermore, the above-described combustor 15 is not limited to the structure described in this embodiment. That is, the combustor 15 may include components (e.g., acoustic dampers) other than the cylindrical body 5, fuel nozzles 6, 6G, intermediate supply units 7, 7B, 7C, 7D, 7E, and 7F, and flow rate adjustment units 8, 8B, 8G, and 8H.

[0084] Furthermore, the configuration of the fuel nozzles 6, 6G is not limited to the above-described structure, and the fuel nozzles 6, 6G may be of any type, such as a type that mixes fuel and air in advance (premixed combustion type), a type that mixes fuel and air quickly as in this embodiment (diffusion combustion type), or a type that sprays fuel and air independently.

[0085] Furthermore, adjustment of the supply state of the ammonia fuel from the ammonia fuel supply facility 20 to the fuel nozzles 6, 6G and adjustment of the supply state of the hydrocarbon-based fuel from the hydrocarbon-based fuel supply facility 30 to the fuel nozzles 6, 6G may be performed manually by an operator or automatically by a control device of the gas turbine facility 1 or the like.

[0086] Furthermore, in the present embodiment, the ammonia fuel supply facility 20 supplies gaseous ammonia fuel to the gas turbine 10, but the present invention is not limited to this. If the gas turbine 10 has a structure capable of receiving liquid ammonia fuel, the ammonia fuel supply facility 20 may supply liquid ammonia fuel to the gas turbine 10.

[0087] Similarly, the control of the valve devices 81, 81B, the first supply amount adjustment unit 85, and the second supply amount adjustment unit 86 may be performed manually by an operator, or may be performed automatically by a control device of the gas turbine equipment 1, etc.

[0088] Furthermore, the intermediate supply units 7, 7B, 7C, 7D, 7E, and 7F are not limited to the structure having the communication holes 71 as described in this embodiment. The intermediate supply units 7, 7B, 7C, 7D, 7E, and 7F may have any structure as long as they are capable of supplying a portion of the compressed air supplied to the fuel nozzles 6, 6G to the cylindrical body 5 on the downstream side Df2 of the fuel nozzles 6, 6G in the flow direction Df of the combustion gas. Therefore, the intermediate supply units 7, 7B, 7C, 7D, 7E, and 7F may have a structure that extracts compressed air compressed by the compressor 14 via piping or the like and supplies the extracted air to the cylindrical body 5, for example.

[0089] <Additional Notes> The gas turbine 10 and the gas turbine equipment 1 described in each embodiment can be understood, for example, as follows.

[0090] (1) A gas turbine 10 according to a first aspect includes a compressor 14 capable of compressing air to generate compressed air, a combustor 15 capable of switching between ammonia fuel and a hydrocarbon-based fuel as a fuel to be burned and capable of generating a combustion gas by burning at least one of the ammonia fuel and the hydrocarbon-based fuel in the compressed air supplied from the compressor 14, and a turbine 16 capable of being driven by the combustion gas supplied from the combustor 15, wherein the combustor 15 includes a cylindrical body 5 through which the combustion gas generated by combustion of the ammonia fuel or the hydrocarbon-based fuel flows, fuel nozzles 6, 6G that inject the ammonia fuel, the hydrocarbon-based fuel, and the compressed air into the cylindrical body 5, and a turbine 16 that is connected to the fuel nozzles 6, 6G. The system includes intermediate supply units 7, 7B, 7C, 7D, 7E, and 7F that supply a portion of the compressed air to the cylindrical body 5 downstream Df2 of the fuel nozzles 6, 6G in the flow direction Df of the combustion gas, and flow rate adjustment units 8, 8B, 8G, and 8H that can adjust the flow rate of the compressed air supplied from the intermediate supply units 7, 7B, 7C, 7D, 7E, and 7F to the cylindrical body 5 relative to the supply amount of the compressed air supplied to the fuel nozzles 6, 6G, and the flow rate adjustment units 8, 8B, 8G, and 8H increase the flow rate of the compressed air supplied from the intermediate supply units 7, 7B, 7C, 7D, 7E, and 7F to the cylindrical body 5 when combusting the ammonia fuel, and reduce the flow rate of the compressed air supplied to the cylindrical body 5 when combusting the hydrocarbon-based fuel.

[0091] This makes it possible to reduce the flow rate of compressed air used for combustion in the fuel nozzle 6 when generating combustion gas using ammonia fuel. As a result, when combusting ammonia fuel, it is possible to prevent unstable combustion caused by excessive supply of compressed air. This makes it possible to continue stable combustion and maintain flame stability when combusting ammonia fuel.

[0092] Furthermore, by reducing the supply amount of compressed air, the ratio of ammonia fuel to the supply amount of compressed air increases. As a result, the amount of nitrogen components remaining in the combustion gas originating from nitrogen in the ammonia fuel can be significantly reduced. Therefore, the amount of NOx generated when the ammonia fuel is combusted can be suppressed.

[0093] Furthermore, when generating combustion gas using a hydrocarbon fuel, the flow rate of compressed air used for combustion in the fuel nozzle 6 can be increased. As a result, the amount of compressed air required to be supplied to the fuel nozzles 6, 6G when burning the hydrocarbon fuel can be secured. This makes it possible to continue stable combustion and maintain flame stability even when burning the hydrocarbon fuel.

[0094] Furthermore, by increasing the amount of compressed air supplied, the proportion of hydrocarbon fuel in the ratio of the amount of hydrocarbon fuel to the amount of compressed air supplied decreases. As a result, the amount of nitrogen components remaining in the combustion gas, which originates from the nitrogen in the compressed air, can be significantly reduced. Therefore, the amount of NOx generated when hydrocarbon fuel is burned can be suppressed.

[0095] In this way, regardless of whether ammonia fuel or hydrocarbon-based fuel is supplied to the gas turbine 10, which is supplied with ammonia fuel and hydrocarbon-based fuel, it is possible to suppress the amount of NOx generated while maintaining stable combustion. Therefore, it is possible to effectively achieve both combustion with ammonia fuel and combustion with hydrocarbon-based fuel.

[0096] (2) The gas turbine 10 according to the second aspect is the gas turbine 10 of (1), wherein the flow rate control units 8, 8B, 8G, and 8H have valve devices 81 and 81B that can adjust the flow rate of the compressed air flowing into the cylindrical body 5.

[0097] This makes it possible to adjust the supply amount of compressed air with a simple configuration when ammonia fuel is supplied and when hydrocarbon fuel is supplied.

[0098] (3) A gas turbine 10 according to a third aspect is a gas turbine 10 according to (1) or (2), wherein the intermediate supply sections 7, 7B, 7C, 7D, 7E, and 7F have a communication hole 71 that connects the inside and outside of the cylindrical body 5 at a position away from the fuel nozzle 6 and at a position Df2 downstream of the fuel nozzles 6 and 6G in the flow direction Df of the combustion gas.

[0099] As a result, the compressed air that flows into the combustion chamber 50 from the communication hole 71 does not directly participate in combustion. Therefore, a simple structure can be obtained that can supply compressed air to the combustion chamber 50 while ensuring a space for stably burning the ammonia fuel and hydrocarbon fuel supplied from the fuel nozzles 6, 6G.

[0100] (4) A gas turbine 10 according to a fourth aspect is the gas turbine 10 according to (3), wherein the communication holes 71 are formed in the cylindrical body 5 at a plurality of positions spaced apart from one another.

[0101] As a result, the compressed air supplied to the cylindrical body 5 is supplied to the combustion chamber 50 without being significantly biased toward a portion near the inner circumferential surface of the cylindrical body 5. Therefore, whether ammonia fuel or hydrocarbon fuel is supplied, efficient and stable combustion can be continued over a wide area of ​​the combustion chamber 50, while the amount of NOx generated can be effectively suppressed.

[0102] (5) A gas turbine 10 according to a fifth aspect is the gas turbine 10 of (3) or (4), wherein the intermediate supply sections 7B, 7C, 7D, and 7E have an annular flow path forming section 73 that forms an annular flow path 730 along the outer periphery of the cylindrical body 5 through which the compressed air can flow, and the communication hole 71 connects the annular flow path forming section 73 and the cylindrical body 5.

[0103] As a result, the annular flow path forming portion 73 functions as a damper, and the compressed air present in the annular flow path 730 is made to have a nearly uniform pressure state. Thereafter, the compressed air fills the annular flow path 730 and flows into the combustion chamber 50 from the communication hole 71. As a result, the compressed air made to have a nearly uniform pressure state in the annular flow path forming portion 73 can be supplied to the combustion chamber 50 from the communication hole 71. Therefore, whether ammonia fuel or hydrocarbon fuel is supplied, it is possible to continue stable combustion more efficiently over a wide area of ​​the combustion chamber 50 and more effectively suppress the amount of NOx generated.

[0104] (6) A gas turbine 10 according to a sixth aspect is the gas turbine 10 according to (5), wherein the annular flow passage forming portion 73 is disposed with a gap 770 between it and the outer peripheral surface of the cylindrical body 5 .

[0105] As a result, even if thermal expansion occurs in the cylindrical body 5 due to the influence of high-temperature combustion gas flowing through the combustion chamber 50, the amount of thermal expansion can be absorbed without affecting the annular flow path forming portion 73. As a result, the fixed state between the annular flow path forming portion 73 and the cylindrical body 5 can be stably maintained.

[0106] (7) A gas turbine 10 according to a seventh aspect is any one of the gas turbines 10 of (3) to (6), wherein the intermediate supply sections 7D, 7E are arranged in the communication holes 71 and have a tubular supply pipe 76 extending inward from the inner circumferential surface of the cylindrical body 5.

[0107] As a result, the compressed air flowing into the combustion chamber 50 from the communication hole 71 is sent by the supply pipe 76 to a position deeper than the inner circumferential surface of the cylindrical body 5. This allows the compressed air to be stably supplied deep into the combustion chamber 50, away from the communication hole 71.

[0108] (8) A gas turbine 10 according to an eighth aspect is the gas turbine 10 of any one of (1) to (7), wherein the flow rate adjustment units 8, 8B, 8G, 8H are capable of adjusting the supply amount of at least one of the ammonia fuel and the hydrocarbon-based fuel so that, while keeping the supply amounts of the ammonia fuel, the hydrocarbon-based fuel, and the compressed air to the fuel nozzles 6, 6G constant, the supply amount of the ammonia fuel when the ammonia fuel is supplied to the fuel nozzles 6, 6G is greater than the supply amount of the hydrocarbon-based fuel when the hydrocarbon-based fuel is supplied to the fuel nozzles 6, 6G.

[0109] As a result, by adjusting the supply amount of ammonia fuel and the supply amount of hydrocarbon-based fuel, it is possible to adjust the flow rate of compressed air used in the fuel nozzle 6. Therefore, it is not necessary to always provide the valve devices 81, 81B, and with a simpler configuration and control that only changes the supply amount of ammonia fuel and the supply amount of hydrocarbon-based fuel, it is possible to suppress the amount of NOx generated while maintaining stable combustion, regardless of whether ammonia fuel or hydrocarbon-based fuel is supplied.

[0110] (9) A gas turbine 10 according to a ninth aspect is any one of the gas turbines 10 of (1) to (8), further comprising a detection unit 9 that detects the operating state of the combustor 15, and the flow rate adjustment units 8, 8B, 8G, and 8H adjust the flow rate of the compressed air supplied to the cylindrical body 5 according to the detection result of the detection unit 9.

[0111] This allows the flow rate of compressed air sent to the combustion chamber 50 by the flow rate adjusting units 8, 8B, 8G, and 8H to be adjusted without delay in accordance with the operating state of the combustor 15. Furthermore, even at the timing of switching between the supply of ammonia fuel and the supply of hydrocarbon-based fuel, stable combustion can be maintained while suppressing the amount of NOx generated.

[0112] (10) A gas turbine facility 1 according to a tenth aspect includes a gas turbine 10 selected from any one of (1) to (9), an ammonia fuel supply facility 20 capable of supplying the ammonia fuel to the gas turbine 10, and a hydrocarbon-based fuel supply facility 30 capable of supplying the hydrocarbon-based fuel to the gas turbine 10. [Industrial Applicability]

[0113] According to the gas turbine and gas turbine facility of the present disclosure, it is possible to suppress the amount of NOx generated while maintaining stable combustion in a gas turbine supplied with ammonia fuel and hydrocarbon-based fuel. [Explanation of symbols]

[0114] 1. Gas turbine equipment 10...Gas turbine 11...Gas turbine rotor 12...Intake duct 13...Intermediate casing 14...Compressor 14r...Compressor rotor 14c...Compressor casing 14v...IGV 15...Combustor 5...Cylinder 50...Combustion chamber 6, 6G...Fuel nozzle 61...First injection hole 62…Second injection hole 63…Third injection hole 7, 7B, 7C, 7D, 7E, 7F…Intermediate supply section 71...Communication hole 8, 8B, 8G, 8H...Flow rate adjustment section 81, 81B...Valve gear Df…Flow direction Df1...Upstream side Df2: downstream side 16...Turbine 16r...Turbine rotor 16c...Turbine casing Ar...Rotor axis 20...Ammonia fuel supply facility 21...First storage tank 22...First supply line 30...Hydrocarbon fuel supply equipment 31...Second storage tank 32...Second supply line 73, 73C...Annular flow path forming section 730...Annular flow path 75...Welded section 74, 74C, 74F...connecting flow path section 76…Supply pipe 77...Gap forming member 770...gap 78...Seal part 55...Sleeve part 85...First supply amount adjustment section 86...Second supply amount adjustment section 65…Mixing section 650…Mixed space 9...Detection unit 88...Valve control device

Claims

1. a compressor capable of compressing air to generate compressed air; a combustor that is capable of switching the fuel to be burned between ammonia fuel and a hydrocarbon-based fuel, and that is capable of burning at least one of the ammonia fuel and the hydrocarbon-based fuel in the compressed air supplied from the compressor to generate combustion gas; a turbine that can be driven by the combustion gas supplied from the combustor, The combustor includes: a cylindrical body through which the combustion gas generated by combustion of the ammonia fuel or the hydrocarbon-based fuel flows; a fuel nozzle that ejects the ammonia fuel, the hydrocarbon-based fuel, and the compressed air into the cylindrical body; an intermediate supply unit that supplies a portion of the compressed air to be supplied to the fuel nozzle to the cylindrical body downstream of the fuel nozzle in a flow direction of the combustion gas; a flow rate adjusting unit that adjusts a flow rate of the compressed air supplied from the intermediate supply unit to the cylindrical body relative to a supply amount of the compressed air supplied to the fuel nozzle, The flow rate adjusting unit increases the flow rate of the compressed air supplied from the intermediate supply unit to the cylindrical body when the ammonia fuel is combusted, and decreases the flow rate of the compressed air supplied to the cylindrical body when the hydrocarbon-based fuel is combusted.

2. The gas turbine according to claim 1 , wherein the flow rate adjusting unit has a valve device capable of adjusting the flow rate of the compressed air flowing into the cylindrical body.

3. 3. The gas turbine according to claim 1, wherein the intermediate supply section has a communication hole that communicates the inside and outside of the cylindrical body at a position away from the fuel nozzle and downstream of the fuel nozzle in the flow direction of the combustion gas.

4. The gas turbine according to claim 3 , wherein the communication holes are formed in the cylindrical body at a plurality of positions spaced apart from one another.

5. the intermediate supply unit has an annular flow path forming unit that forms an annular flow path along an outer periphery of the cylindrical body through which the compressed air can flow, The gas turbine according to claim 4 , wherein the communication hole provides communication between the annular flow passage forming portion and the cylindrical body.

6. The gas turbine according to claim 5 , wherein the annular flow passage forming portion is disposed with a gap from an outer peripheral surface of the cylindrical body.

7. The gas turbine according to claim 5 , wherein the intermediate supply section has a supply pipe disposed in the communication hole and formed in a tubular shape extending inward from an inner circumferential surface of the cylindrical body.

8. 2. The gas turbine according to claim 1, wherein the flow rate adjusting unit is capable of adjusting a supply amount of at least one of the ammonia fuel and the hydrocarbon-based fuel such that, while supply amounts of the ammonia fuel, the hydrocarbon-based fuel, and the compressed air to the fuel nozzle are kept constant, a supply amount of the ammonia fuel when the ammonia fuel is supplied to the fuel nozzle is greater than a supply amount of the hydrocarbon-based fuel when the hydrocarbon-based fuel is supplied to the fuel nozzle.

9. a detector that detects an operating state of the combustor; The gas turbine according to claim 1 or 2, wherein the flow rate adjusting unit adjusts the flow rate of the compressed air supplied to the cylindrical body in accordance with a detection result from the detection unit.

10. The gas turbine according to claim 1 or 2; an ammonia fuel supply facility capable of supplying the ammonia fuel to the gas turbine; a hydrocarbon-based fuel supply facility capable of supplying the hydrocarbon-based fuel to the gas turbine.

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