Gas turbine and gas turbine device

Abstract

A gas turbine is provided with a combustor capable of switching between an ammonia fuel and a hydrocarbon fuel to be combusted. The burner is provided with: a cylindrical body through which a combustion gas flows; a fuel nozzle for spraying the ammonia fuel, the hydrocarbon fuel, and compressed air into the cylinder; an intermediate supply unit for supplying a part of the compressed air to the cylinder; and a flow rate adjustment unit capable of adjusting the flow rate of the compressed air supplied to the cylinder. The flow rate adjusting part increases the flow rate of the compressed air supplied to the cylinder when the ammonia fuel is combusted, and reduces the flow rate of the compressed air supplied to the cylinder when the hydrocarbon fuel is combusted.

Description

Technical Field

[0001] The present invention relates to a gas turbine and a gas turbine equipment.

[0002] This application claims priority based on patent application No. 2022-133982 filed in Japan on August 25, 2022, and the contents are incorporated herein by reference. Background Art

[0003] The gas turbine includes a compressor for compressing air, a burner for burning fuel in the air compressed by the compressor to generate combustion gas, and a turbine driven by the combustion gas. As the fuel supplied to the burner, fossil fuels such as natural gas or petroleum, i.e. hydrocarbon fuels, are generally used, but ammonia is sometimes used.

[0004] For example, Patent Document 1 describes a gas turbine that increases the proportion of fossil fuel in fuel supplied to the gas turbine in a deteriorated combustibility operation region in which ammonia is supplied as a main fuel and the combustibility of ammonia deteriorates compared to normal operation.

[0005] Previous technical literature

[0006] Patent Literature

[0007] Patent Document 1: Japanese Patent Application Publication No. 2010-19195 Summary of the invention

[0008] Technical issues to be solved by the invention

[0009] Ammonia fuel has a low calorific value and a low combustion rate. In other words, ammonia fuel has poorer combustibility than hydrocarbon fuels. Therefore, in a gas turbine that can simultaneously supply ammonia fuel and hydrocarbon fuel, it is difficult to continuously maintain stable combustion when either ammonia fuel or hydrocarbon fuel is supplied.

[0010] Moreover, when ammonia is used as a fuel for a gas turbine, NOx is generated due to a part of the nitrogen formed in ammonia during combustion. Therefore, the more the amount of ammonia fuel supplied to the burner is less than the amount of compressed air supplied and the combustion is not carried out effectively, the more NOx is generated. On the other hand, if hydrocarbon fuel is burned, NOx derived from nitrogen in the compressed air is generated. Therefore, if the amount of hydrocarbon fuel supplied to the burner is close to the same level as the amount of compressed air supplied, the closer the amount of fuel or air supplied to the stoichiometric amount is, the higher the combustion temperature is, and the more NOx is generated. That is, in the case of supplying ammonia fuel and the case of supplying hydrocarbon fuel, if the amount of compressed air is set to the same condition, it is difficult to suppress the amount of NOx generated.

[0011] The present invention provides a gas turbine and a gas turbine equipment capable of maintaining stable combustion and suppressing the amount of NOx generated in a gas turbine to which ammonia fuel and hydrocarbon fuel are supplied together.

[0012] Means for solving technical problems

[0013] A gas turbine according to one embodiment of the present invention comprises: a compressor capable of compressing air to generate compressed air; a burner capable of switching the fuel to be burned between ammonia fuel and hydrocarbon fuel, and capable of burning at least one of the ammonia fuel and the hydrocarbon fuel in the compressed air supplied from the compressor to generate combustion gas; and a turbine capable of being driven by the combustion gas supplied from the burner, the burner comprising: a cylindrical body through which the combustion gas generated by the combustion of the ammonia fuel or the hydrocarbon fuel flows; and a fuel nozzle for ejecting the ammonia fuel or the hydrocarbon fuel into the interior of the cylindrical body. material and the compressed air; an intermediate supply portion that supplies a portion of the compressed air supplied to the fuel nozzle to the cylinder at the downstream side in the flow direction of the combustion gas relative to the fuel nozzle; and a flow adjustment portion that can adjust the flow rate of the compressed air supplied from the intermediate supply portion to the cylinder relative to the supply amount of the compressed air supplied to the fuel nozzle, the flow adjustment portion increases the flow rate of the compressed air supplied from the intermediate supply portion to the cylinder when burning the ammonia fuel, and reduces the flow rate of the compressed air supplied to the cylinder when burning the hydrocarbon fuel.

[0014] A gas turbine facility according to one aspect of the present invention includes: the gas turbine; an ammonia fuel supply facility capable of supplying the ammonia fuel to the gas turbine; and a hydrocarbon fuel supply facility capable of supplying the hydrocarbon fuel to the gas turbine.

[0015] Effects of the Invention

[0016] According to the gas turbine and the gas turbine equipment of the present invention, it is possible to continue stable combustion and suppress the amount of NOx generated in the gas turbine to which the ammonia fuel and the hydrocarbon fuel are supplied. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic configuration diagram of a gas turbine plant in a first embodiment according to an embodiment of the present invention.

[0018] Figure 2 It is a schematic cross-sectional view of a burner in the first embodiment according to the present invention.

[0019] Figure 3 It is a schematic cross-sectional view of a burner in a second embodiment according to the present invention.

[0020] Figure 4 yes Figure 3 AA section view.

[0021] Figure 5 yes Figure 3 An enlarged view of the main parts of the burner.

[0022] Figure 6 is with Figure 5 This is an enlarged view of a main part of a burner according to a modification example of the corresponding second embodiment.

[0023] Figure 7 is with Figure 5 This is an enlarged view of the main parts of the burner according to the corresponding third embodiment.

[0024] Figure 8 is with Figure 5 This is an enlarged view of the main parts of the burner according to the corresponding fourth embodiment.

[0025] Fig. 9 It is a schematic cross-sectional view of a burner in a fifth embodiment according to the present invention.

[0026] Fig.10 yes Figure 8 BB section view.

[0027] Fig.11 yes Figure 8 An enlarged view of the first major part of the burner.

[0028] Fig.12 yes Figure 8 An enlarged view of the second main part of the burner.

[0029] Fig.13 It is a schematic cross-sectional view of a burner in a sixth embodiment according to the present invention.

[0030] Fig.14 This is a graph showing the ratio of the supply amounts of ammonia fuel, hydrocarbon fuel, and compressed air in the sixth embodiment of the present invention.

[0031] Fig.15 It is a schematic cross-sectional view of a burner in a seventh embodiment according to the present invention. DETAILED DESCRIPTION

[0032] Hereinafter, embodiments for implementing the gas turbine 10 and the gas turbine equipment 1 according to the present invention will be described with reference to the drawings. However, the present invention is not limited to these embodiments.

[0033] <First Embodiment>

[0034] (Structure of gas turbine equipment)

[0035] like Figure 1 As shown, the gas turbine facility 1 of the present embodiment includes a gas turbine 10 , an ammonia fuel supply facility 20 , and a hydrocarbon fuel supply facility 30 .

[0036] (Structure of gas turbine)

[0037] The gas turbine 10 can switch the fuel to be burned between ammonia fuel and hydrocarbon fuel. The gas turbine 10 can be driven by combustion gas generated by burning at least one of ammonia fuel and hydrocarbon 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.

[0038] The compressor 14 can compress air to generate compressed air. The compressor 14 has a compressor rotor 14r that rotates around the rotor axis Ar, a compressor housing 14c that covers the compressor rotor 14r, and an IGV (inlet guide vane) 14v provided at the suction port of the compressor housing 14c. The IGV 14v adjusts the flow rate of air sucked into the compressor housing 14c, that is, the intake volume. The intake duct 12 is connected to the suction port of the compressor housing 14c.

[0039] The turbine 16 can be driven by the high-temperature and high-pressure combustion gas supplied from the combustor 15. The turbine 16 includes a turbine rotor 16r that rotates around 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 rotatably connected to each other around the same rotor axis Ar to form a gas turbine rotor 11. For example, a rotor of a generator is connected to the gas turbine rotor 11.

[0040] The intermediate housing 13 is disposed between the compressor housing 14 c and the turbine housing 16 c in the direction in which the rotor axis Ar extends, and connects the compressor housing 14 c and the turbine housing 16 c. Compressed air discharged from the compressor 14 flows into the intermediate housing 13 .

[0041] The burner 15 is capable of burning at least one of ammonia fuel and hydrocarbon fuel in the compressed air supplied from the compressor 14 to generate combustion gas. Hydrocarbon fuel is a fuel containing hydrocarbons, for example, fossil fuels such as natural gas or oil. Ammonia fuel and hydrocarbon fuel can be supplied to the burner 15. The burner 15 adjusts the supply amount of ammonia fuel and hydrocarbon fuel as fuel according to the operating conditions, thereby being able to operate under operating conditions of burning only ammonia fuel, burning only hydrocarbon fuel, and burning both ammonia fuel and hydrocarbon fuel. In addition, under the operating conditions of burning both ammonia fuel and hydrocarbon fuel, the supply amount of ammonia fuel and the supply amount of hydrocarbon fuel may be the same or different. The burner 15 is fixed to the intermediate casing 13. As Figure 2 As shown, the combustor 15 of the present embodiment includes a cylinder 5 , a fuel nozzle 6 , an intermediate supply portion 7 , and a flow rate adjustment portion 8 .

[0042] The cylinder 5 is formed with a combustion chamber 50 inside. The combustion chamber 50 is a space inside the cylinder 5. That is, the combustion gas generated by the combustion of at least one of the ammonia fuel and the hydrocarbon fuel circulates inside the cylinder 5. The cylinder 5 is arranged in the intermediate casing 13 into which the compressed air compressed by the compressor 14 flows. In the combustion chamber 50, at least one of the ammonia fuel and the hydrocarbon fuel is supplied and burned together with the compressed air. The combustion gas generated by the combustion of at least one of the ammonia fuel and the hydrocarbon fuel flows through the combustion chamber 50 and is transported to the turbine 16. The cylinder 5 is formed into a cylindrical shape centered on the central axis of the burner 15. In addition, the cylinder 5 is not limited to a structure consisting of only one component. The cylinder 5 can be a structure in which a plurality of components are arranged in the direction extending along the central axis.

[0043] The fuel nozzle 6 sprays ammonia fuel, hydrocarbon fuel and compressed air into the combustion chamber 50. The fuel nozzle 6 is fixed to one side end (upstream end, first end) of the cylinder 5 arranged at a position away from the turbine 16. The fuel nozzle 6 sprays ammonia fuel, hydrocarbon fuel and compressed air into the combustion chamber 50 in a manner toward the turbine 16. The fuel nozzle 6 generates combustion gas by diffusion combustion under three conditions: ammonia fuel and compressed air, hydrocarbon fuel and compressed air, and ammonia fuel, hydrocarbon fuel and compressed air. One fuel nozzle 6 is arranged inside the cylinder 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 fuel, and at least one (two in this embodiment) third injection hole 63 for injecting compressed air.

[0044] The first injection hole 61, the second injection hole 62, and the third injection hole 63 are formed separately from each other in the fuel nozzle 6 in an independent manner. The first injection hole 61, the second injection hole 62, and the third injection hole 63 of the first embodiment are formed so that each fluid is mixed before being injected into the combustion chamber 50. The first injection hole 61 sprays the ammonia fuel introduced from the outside of the burner 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 sprays the hydrocarbon fuel introduced from the outside of the burner 15 into the combustion chamber 50. The third injection hole 63 sprays the compressed air introduced from the center casing 13 into the combustion chamber 50. The third injection hole 63 is arranged between the first injection hole 61 and the second injection hole 62 in the radial direction of the fuel nozzle 6.

[0045] In addition, the first injection hole 61, the second injection hole 62, and the third injection hole 63 are not limited to a structure in which one is arranged inside the fuel nozzle 6. The first injection hole 61, the second injection hole 62, and the third injection hole 63 may be a structure formed in nozzles independent of each other. That is, the fuel nozzle 6 may be composed of a plurality of nozzles. In addition, the fuel nozzle 6 may also have other structures such as a swirl nozzle.

[0046] The intermediate supply portion 7 supplies a part of the compressed air supplied to the fuel nozzle 6 to the cylinder 5 from a portion other than the fuel nozzle 6. The intermediate supply portion 7 is located in the intermediate casing 13. The intermediate supply portion 7 is arranged at a position on the downstream side Df2 in the flow direction Df of the combustion gas relative to the fuel nozzle 6. Here, the flow direction Df of the combustion gas refers to the direction from the end of one side where the fuel nozzle 6 is arranged in the cylinder 5 toward the other end (downstream end, second end) connected to the turbine 16. Therefore, the upstream side Df1 in the flow direction Df of the combustion gas refers to the side of the cylinder 5 where the fuel nozzle 6 is arranged relative to the turbine 16. And, the downstream side Df2 in the flow direction Df of the combustion gas refers to the side of the cylinder 5 where the turbine 16 is arranged relative to the fuel nozzle 6. In addition, the intermediate supply portion 7 of the present embodiment has a connecting hole 71.

[0047] The connecting hole 71 is formed to connect the inside of the cylinder 5, that is, the combustion chamber 50, and the outside of the cylinder 5 at a position away from the fuel nozzle 6. That is, the connecting hole 71 of the present embodiment connects the combustion chamber 50 and the space in the intermediate casing 13 without passing through the fuel nozzle 6. The connecting hole 71 is formed at a position on the downstream side Df2 in the flow direction Df of the combustion gas relative to the fuel nozzle 6. The connecting hole 71 is formed to supply compressed air to a position that does not directly participate in the diffusion combustion relative to the combustion chamber 50. The connecting hole 71 is formed near the middle of the cylinder 5 in the flow direction Df. The connecting hole 71 is formed at multiple positions (for example, four places) separated from each other along the outer peripheral surface of the cylinder 5 in the circumferential direction of the cylinder 5. The multiple connecting holes 71 are arranged to be equally spaced from each other. The connecting hole 71 is formed in the intermediate casing 13, facing the middle of the flow channel of the compressed air introduced into the third injection hole 63. More specifically, when the length obtained by connecting the front end of the fuel nozzle 6 to the position connected to the turbine 16 by a straight line is set as the total length (100%) of the cylinder 5, the connecting hole 71 is preferably arranged between 30% and 70% of the front end of the fuel nozzle 6.

[0048] In addition, the communicating holes 71 are not limited to the structure in which a plurality of communicating holes 71 are formed as in the present embodiment. There may be only one communicating hole 71. Furthermore, the plurality of communicating holes 71 are not limited to being arranged at equal intervals, and may be arranged at different intervals from each other.

[0049] The flow rate regulating unit 8 can adjust the flow rate of the compressed air supplied from the intermediate supply unit 7 to the cylinder 5 relative to the supply rate of the compressed air supplied to the fuel nozzle 6. That is, the flow rate regulating unit 8 can adjust the ratio of the supply rate of the compressed air supplied to the combustion chamber 50 indirectly together with the fuel via the third injection hole 63 and the flow rate of the compressed air directly supplied to the combustion chamber 50 from the intermediate supply unit 7. The flow rate regulating unit 8 adjusts the flow rate of the compressed air supplied from the intermediate supply unit 7 to the combustion chamber 50 according to the respective supply rates of the ammonia fuel and the hydrocarbon fuel supplied to the fuel nozzle 6. Specifically, the flow rate regulating unit 8 increases the flow rate of the compressed air supplied to the cylinder 5 when the ammonia fuel is burned. On the other hand, the flow rate regulating unit 8 reduces the flow rate of the compressed air supplied to the cylinder 5 when the hydrocarbon fuel is burned. In addition, the flow rate regulating unit 8 of the present embodiment has a valve device 81.

[0050] The valve device 81 can adjust the flow rate of compressed air flowing from the outside of the cylinder 5 into the inside of the cylinder 5, that is, the combustion chamber 50. The valve device 81 is, for example, a flow regulating valve, an on-off valve, or a solenoid valve. The valve device 81 is configured to close the communicating hole 71. The valve device 81 adjusts the flow rate of compressed air passing through the communicating hole 71. Specifically, the valve device 81 increases the opening as the amount of ammonia fuel supplied to the first injection hole 61 increases (for example, it can be in a fully open state). On the other hand, the valve device 81 decreases the opening as the amount of hydrocarbon fuel supplied to the second injection hole 62 increases (for example, it can be in a fully closed state). In addition, in the case of simultaneously supplying ammonia fuel and hydrocarbon fuel, the valve device 81 adjusts the opening according to the amount of NOx, and the opening becomes the same degree or an intermediate degree as in the case of supplying only ammonia fuel. That is, in the case of simultaneous supply, in the valve device 81, the opening is set to the same degree or smaller than in the case of supplying only ammonia fuel to the fuel nozzle 6, and the opening is set to be larger than in the case of supplying only hydrocarbon fuel to the fuel nozzle 6. A plurality of valve devices 81 of the present embodiment are arranged so that one valve device 81 is arranged for one communication hole 71. That is, one valve device 81 is arranged so as to be able to close only one communication hole 71.

[0051] (Structure of ammonia fuel supply equipment)

[0052] like Figure 1 As shown, the ammonia fuel supply facility 20 can supply the ammonia fuel to the gas turbine 10. The ammonia fuel supply facility 20 of the present embodiment includes a first tank 21 and a first supply line 22.

[0053] Ammonia fuel in a liquid state is stored in the first storage tank 21. The first supply pipe 22 connects the first storage tank 21 and the fuel nozzle 6. The first supply pipe 22 heats the ammonia fuel in a liquid state and vaporizes it, and then supplies it to the first injection hole 61. The first supply pipe 22 can adjust the amount of ammonia fuel supplied to the first injection hole 61. In addition, the first supply pipe 22 has a heat exchanger (not shown) for vaporizing liquid ammonia, a pump (not shown) for increasing pressure, a valve (not shown) for adjusting the supply amount, etc.

[0054] (Structure of hydrocarbon fuel supply equipment)

[0055] The hydrocarbon fuel supply facility 30 can supply the hydrocarbon fuel to the gas turbine 10. The hydrocarbon fuel supply facility 30 of the present embodiment includes a second tank 31 and a second supply line 32.

[0056] 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 it and supplies it to the second injection hole 62. The second supply line 32 can adjust the amount of hydrocarbon fuel supplied to the second injection hole 62. At this time, the second supply line 32 has 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, etc. In addition, when the hydrocarbon fuel is stored in the second storage tank 31 in a gaseous state, it is supplied to the second injection hole 62 in its original state or after increasing the pressure. At this time, the second supply line 32 has 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, etc.

[0057] (Effect)

[0058] In the gas turbine facility 1 having the above-described structure, there are cases where only ammonia fuel, only hydrocarbon fuel, and both ammonia fuel and hydrocarbon fuel are supplied to the gas turbine 10 .

[0059] First, when only ammonia fuel is supplied, ammonia fuel is supplied from the first tank 21 to the fuel nozzle 6 through the first supply pipe 22. The ammonia fuel supplied to the fuel nozzle 6 is injected into the combustion chamber 50 through the first injection hole 61. At this time, the compressed air supplied to the fuel nozzle 6 via the intermediate housing 13 is injected into the combustion chamber 50 from the third injection hole 63. In addition, hydrocarbon fuel is not injected from the second injection hole 62. As a result, only the ammonia fuel and the compressed air are diffusely burned in the combustion chamber 50. In addition, the combustion here is not limited to diffusion combustion, but becomes a combustion that matches the shape of the fuel nozzle 6. Therefore, it can be a combustion method close to premixed combustion, rather than diffusion combustion. At the same time, the valve device 81 becomes a state of being greatly opened. As a result, most of the compressed air in the intermediate housing 13 flows into the combustion chamber 50 from the connecting hole 71. That is, a part of the compressed air to be supplied to the third injection hole 63 flows directly into the combustion chamber 50 from the connecting 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.

[0060] Furthermore, when only hydrocarbon fuel is supplied, hydrocarbon fuel is supplied from the second tank 31 to the fuel nozzle 6 through the second supply pipe 32. The hydrocarbon fuel supplied to the fuel nozzle 6 is injected into the combustion chamber 50 through the second injection hole 62. At this time, compressed air is injected into the combustion chamber 50 from the third injection hole 63. Moreover, ammonia fuel is not injected from the first injection hole 61. As a result, only hydrocarbon fuel and compressed air are burned in the combustion chamber 50. At the same time, the valve device 81 becomes a slightly opened (or closed) state. As a result, the compressed air in the intermediate housing 13 hardly flows into the combustion chamber 50 from the connecting hole 71. That is, the compressed air to be supplied to the third injection hole 63 hardly decreases and flows into the combustion chamber 50 from the third injection hole 63. In this way, when only hydrocarbon fuel is supplied to the fuel nozzle 6, the flow rate of compressed air supplied to the third injection hole 63 can be increased.

[0061] Moreover, in the case of supplying both ammonia fuel and hydrocarbon fuel, ammonia fuel is supplied from the first tank 21 to the fuel nozzle 6 through the first supply line 22. At the same time, hydrocarbon fuel is supplied from the second 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 fuel is injected into the combustion chamber 50 through the second injection hole 62. At this time, compressed air is injected into the combustion chamber 50 from the third injection hole 63. As a result, three kinds of ammonia fuel, hydrocarbon fuel and compressed air are burned in the combustion chamber 50. At the same time, the valve device 81 becomes an intermediate degree of opening. As a result, the compressed air in the intermediate housing 13 of the same degree or less than the case of burning only ammonia fuel and a larger amount than the case of burning only hydrocarbon fuel flows from the communication hole 71. That is, the supply amount of compressed air supplied to the third injection hole 63 does not increase or decrease significantly. Therefore, when burning both ammonia fuel and hydrocarbon fuel, an appropriate amount of compressed air is supplied to the third injection hole 63.

[0062] In the burner 15 of the gas turbine 10 as 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. It is known that ammonia fuel has a lower calorific value and a lower combustion speed than hydrocarbon fuels, so its combustibility is poor. Therefore, if compressed air is supplied at the same supply amount as when burning hydrocarbon fuels, it is difficult to burn in a stable state (carry out stable combustion), and thus flame retention cannot be maintained. However, as described above, when ammonia fuel is supplied to the fuel nozzle 6, the supply amount of compressed air is reduced. As a result, when burning ammonia fuel, it is possible to suppress excessive supply of compressed air and produce unstable combustion. Thus, when burning ammonia fuel, stable combustion is continued, so that flame retention can be maintained.

[0063] In addition, the ratio of ammonia fuel to the ratio of ammonia fuel to compressed air supply increases due to the reduction in the supply of compressed air. As a result, as described above, flame retention is maintained when burning ammonia fuel, thereby significantly reducing the amount of nitrogen components remaining in the combustion gas derived from nitrogen in ammonia fuel. Therefore, the generation of NOx when burning ammonia fuel can be suppressed.

[0064] Moreover, when hydrocarbon fuel is used to generate combustion gas, the flow rate of compressed air used for diffusion combustion in the fuel nozzle 6 can be increased. In order to perform stable combustion, hydrocarbon fuel requires more compressed air 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 the case where ammonia fuel is supplied to the fuel nozzle 6. As a result, when burning hydrocarbon fuel, it is possible to ensure that the required amount of compressed air is supplied to the fuel nozzle 6. Thus, even when burning hydrocarbon fuel, stable combustion is continued, thereby maintaining flame retention without generating backfire, etc.

[0065] In addition, the ratio of hydrocarbon fuel to the ratio of the supply of hydrocarbon fuel to compressed air decreases due to the increase in the supply of compressed air. As a result, when burning hydrocarbon fuel, the flame retention is maintained, and the generation of high-temperature areas in the cylinder 5 is suppressed, thereby significantly reducing the amount of nitrogen components remaining in the combustion gas derived from nitrogen in the compressed air. Therefore, the generation of NOx when burning hydrocarbon fuel can be suppressed.

[0066] Thus, even if either ammonia fuel or hydrocarbon fuel is supplied to the gas turbine 10 to which ammonia fuel or hydrocarbon fuel is supplied, stable combustion can be continued and the amount of NOx generated can be suppressed. Therefore, combustion based on ammonia fuel and hydrocarbon fuel can be effectively taken into account.

[0067] In the flow rate adjustment unit 8, the flow rate of the compressed air flowing into the cylinder 5 is adjusted by the valve device 81. Therefore, the supply amount of the compressed air when the ammonia fuel is supplied and when the hydrocarbon fuel is supplied can be adjusted with a simple structure.

[0068] Furthermore, compressed air is supplied to the cylinder 5 via the connecting hole 71 from a position away from the fuel nozzle 6 and at a position on the downstream side Df2 in the flow direction Df of the combustion gas relative to the fuel nozzle 6. In the cylinder 5, a constant space is required near the front end of the fuel nozzle 6 so that the ammonia fuel, hydrocarbon fuel and compressed air supplied from the fuel nozzle 6 can be effectively burned by combustion. In contrast, the compressed air flows into the combustion chamber 50 from a position separated from the fuel nozzle 6 to the downstream side Df2 through the connecting hole 71. Therefore, the compressed air flowing into the combustion chamber 50 from the connecting hole 71 does not directly participate in the diffusion combustion. Therefore, a structure that ensures a space for stably burning the ammonia fuel and hydrocarbon fuel supplied from the fuel nozzle 6 and can supply compressed air to the combustion chamber 50 can be obtained with a simple structure.

[0069] In particular, in the cylinder 5, the area from the front end of the fuel nozzle 6 to 30% is often used as a space for burning the fuel supplied from the fuel nozzles 6 and 6G. That is, the communication hole 71 of the present embodiment is arranged at a position exceeding the area for burning the fuel supplied from the fuel nozzle 6. Therefore, the space for stably burning the fuel supplied from the fuel nozzle 6 can be more reliably ensured.

[0070] Furthermore, in the cylinder 5, when a large amount of fuel is supplied from the fuel nozzle 6, oxygen becomes deficient, and the remaining fuel that is not completely burned is transported to the downstream area. At this time, the remaining fuel is also burned in the dilution air portion in the downstream area of ​​the cylinder 5 in the area of ​​about 30% from the rear end of the cylinder 5. Therefore, by forming the communication hole 71 facing the area from the front end of the fuel nozzle 6 to 70%, it is possible to ensure an area in the downstream area of ​​the cylinder 5 where the remaining fuel is burned.

[0071] Furthermore, the connecting holes 71 are formed at a plurality of positions separated from each other with respect to the cylinder 5. Therefore, the compressed air supplied to the vicinity of the middle of the cylinder 5 will not be greatly biased toward the vicinity of a portion of the inner circumferential surface of the cylinder 5 and supplied to the combustion chamber 50. In particular, the connecting holes 71 are arranged at equal intervals, so that the compressed air is supplied to the combustion chamber 50 in a nearly uniform state. Therefore, even if any one of the ammonia fuel and the hydrocarbon fuel is supplied, stable combustion can be effectively continued in a wide area of ​​the combustion chamber 50, and the amount of NOx generated can be effectively suppressed.

[0072] <Second Embodiment>

[0073] Next, a second embodiment of the gas turbine equipment 1 according to the present invention will be described. In the second embodiment described below, the same reference numerals are used for the same structures as those in the first embodiment, and their descriptions are omitted. In the second embodiment, the structures of the intermediate supply unit 7B and the flow rate adjustment unit 8B are different from those in the first embodiment.

[0074] like Figures 3 to 5 As shown, the intermediate supply portion 7B of the second embodiment has an annular flow path forming portion 73 and a connecting flow path portion 74. The annular flow path forming portion 73 is arranged in the intermediate housing 13. The annular flow path forming portion 73 has an annular flow path 730 formed inside the annular flow path forming portion 73 through which compressed air can flow along the outer periphery of the cylinder 5. The annular flow path forming portion 73 covers the outer periphery of the cylinder 5 over the entire circumference. Therefore, the annular flow path forming portion 73 is arranged to cover a plurality of connecting holes 71. The annular flow path forming portion 73 is directly fixed to the outer peripheral surface of the cylinder 5 without a gap through a welding portion 75. Therefore, the connecting hole 71 of the present embodiment connects the combustion chamber 50 and the annular flow path 730. The plurality of connecting holes 71 are connected to each other through the annular flow path 730 outside the cylinder 5. The connecting flow path portion 74 connects the annular flow path forming portion 73 and the valve device 81B. The connecting flow path portion 74 of the present embodiment is a tubular component bent like a bend. The connecting 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 connecting flow path portion 74 is connected to the surface of the annular flow path forming portion 73 that is farthest from the cylinder 5. The opening area at the connection position between the connecting 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 communicating hole 71.

[0075] In the flow rate adjustment section 8B of the second embodiment, a valve device 81B is connected to the connecting flow path section 74. The valve device 81B is, for example, a flow rate adjustment valve, an on-off valve, or a solenoid valve. That is, the valve device 81B adjusts the flow rate of the compressed air supplied from the annular flow path 730 and the communication hole 71 to the combustion chamber 50 by adjusting the flow rate of the compressed air flowing into the connecting flow path section 74. Only one valve device 81B is arranged with respect to the connecting flow path section 74. That is, in the second embodiment, only one valve device 81B is arranged with respect to the plurality of communication holes 71.

[0076] (Effect)

[0077] In the above-mentioned combustor 15, a part 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 flowing into the connecting flow path portion 74 flows into the annular flow path forming portion 73. At this time, the annular flow path forming portion 73 functions as a damper, whereby the compressed air existing in the annular flow path 730 is in a nearly uniform pressure state. Then, the compressed air fills the annular flow path 730 and flows into the combustion chamber 50 from the plurality of communication holes 71. Thus, the compressed air in a nearly uniform pressure state in the annular flow path forming portion 73 can be supplied from the plurality of communication holes 71 to the combustion chamber 50. Therefore, the compressed air supplied from the plurality of communication holes 71 is supplied to the combustion chamber 50 at substantially the same pressure state at any position. Therefore, even if any one of the ammonia fuel and the hydrocarbon fuel is supplied, stable combustion can be continued more effectively in a wide area of ​​the combustion chamber 50, and the amount of NOx generated can be suppressed more effectively. In addition, the compressed air can be uniformly supplied to the combustion chamber 50 using only one valve device 81B. Therefore, by using a plurality of valve devices, it is possible to avoid variations in the supply state of compressed air caused by manufacturing tolerances of each valve device or the like.

[0078] In addition, the annular flow path forming portion 73 is not limited to a structure that covers the outer periphery of the cylinder 5 throughout the entire circumference. The annular flow path forming portion 73 may be a structure that covers only a portion of the outer periphery of the cylinder 5. Furthermore, the annular flow path 730 is not limited to having the same cross-sectional area throughout the entire circumference. The cross-sectional area of ​​the annular flow path 730 may be locally changed, such as becoming smaller in the middle, as long as a sufficiently large area relative to the communicating hole 71 can be ensured.

[0079] <Modification of Second Embodiment>

[0080] In the second embodiment, the position where the connecting flow path portion 74 is connected to the annular flow path forming portion 73 is not limited. The connecting flow path portion 74 may be connected to a surface facing the flow direction Df of the combustion gas relative to the annular flow path forming portion 73. Figure 6 As shown, the connecting 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.

[0081] <Third Embodiment>

[0082] Next, a third embodiment of the gas turbine equipment 1 according to the present invention will be described. In the third embodiment described below, the same reference numerals are given to the same structures as those in the first and second embodiments, and their descriptions are omitted. Figure 7As shown, the intermediate supply portion 7D has a supply pipe 76. The supply pipe 76 is arranged in the communicating hole 71. The supply pipe 76 is formed as a tubular member having the same shape as the communicating hole 71. The supply pipe 76 is formed to extend from the inner circumferential surface of the cylinder 5 toward the inside. That is, the supply pipe 76 is arranged in a state of protruding from the inner circumferential surface of the cylinder 5 toward the inside of the cylinder 5. Thus, 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 away from the inner circumferential surface of the cylinder 5. In addition, the supply pipe 76 can be arranged in all the communicating holes 71, or can be arranged only in a part of the communicating holes 71.

[0083] (Effect)

[0084] By configuring such a supply pipe 76, the compressed air flowing into the combustion chamber 50 from the connecting hole 71 is transported to the center of the combustion chamber 50 closer to the inner side than the inner peripheral surface of the cylinder 5 through the supply pipe 76. As a result, the compressed air can be stably supplied to the depth of the combustion chamber 50 away from the connecting hole 71. Therefore, for example, in the case where the flow rate of the combustion gas in the combustion chamber 50 is fast, even in a situation that causes the compressed air supplied from the connecting hole 71 to flow immediately to the downstream side Df2, the compressed air can be supplied to the center of the combustion chamber 50. Therefore, even if any one of the ammonia fuel and the hydrocarbon fuel is supplied, the generation of embers and the generation of local high-temperature areas can be suppressed relative to the wide area of ​​the combustion chamber 50. Therefore, in the wide area of ​​the combustion chamber 50, stable combustion can be continued more effectively, and the generation of NOx can be more effectively suppressed.

[0085] <Fourth Embodiment>

[0086] Next, a fourth embodiment of the gas turbine device 1 according to the present invention will be described. In the fourth embodiment described below, the same reference numerals are used in the drawings for the same structures as those in the first to third embodiments, and their descriptions are omitted. In the fourth embodiment, the annular flow path forming portion 73 is not limited to a structure directly connected to the outer peripheral surface of the cylinder 5 as in the second or third embodiment. For example, Figure 8 As shown, the annular flow path forming portion 73 can be arranged with respect to the outer peripheral surface of the cylinder 5 across a gap 770. Specifically, the intermediate supply portion 7E has a gap forming component 77 connecting the annular flow path forming portion 73 and the cylinder 5. The gap forming component 77 forms a gap 770 between the annular flow path forming portion 73 and the outer peripheral surface of the cylinder 5. The gap forming component 77 is a component formed in an annular shape covering the connecting hole 71 on the outside of the cylinder 5. In the present embodiment, the gap 770 becomes a space sealed between the gap forming component 77, the annular flow path forming portion 73 and the cylinder 5.

[0087] (Effect)

[0088] As described above, a gap 770 is formed between the annular flow path forming portion 73 and the outer peripheral surface of the cylinder 5. Therefore, even if thermal expansion occurs in the cylinder 5 due to the influence of the high-temperature combustion gas flowing through the combustion chamber 50, the thermal expansion can be absorbed without affecting the annular flow path forming portion 73. Thus, the fixed state of the annular flow path forming portion 73 and the cylinder 5 can be stably maintained.

[0089] <Fifth Embodiment>

[0090] Next, a fifth embodiment of the gas turbine equipment 1 according to the present invention will be described. In the fifth embodiment described below, the same reference numerals are given to the same structures as those in the first to fourth embodiments, and their descriptions are omitted. In the fifth embodiment, as in the second to fourth embodiments, the intermediate supply portion 7F is not limited to a structure having an annular flow path forming portion 73.

[0091] like Fig. 9 and Fig.10 As shown, the intermediate supply portion 7F of the fifth embodiment does not have the annular flow path forming portion 73, and the connecting flow path portion 74F is directly fixed to the outer peripheral surface of the cylinder 5. The connecting flow path portion 74F is configured to cover the connecting hole 71. Therefore, the connecting hole 71 of this embodiment connects the combustion chamber 50 and the connecting flow path portion 74F. A plurality of connecting flow path portions 74F are configured in a manner that one is configured for one connecting hole 71. That is, one connecting flow path portion 74F is configured to be able to close one connecting hole 71. In addition, each of the plurality of connecting flow path portions 74F has an independent valve device 81B.

[0092] And, if Fig.11 and Fig.12 As shown, the intermediate supply portion 7F has a plurality of seals 78. The seals 78 are disposed between the connecting flow path portion 74F and the valve device 81B and between the connecting flow path portion 74F and the cylinder 5. The seals 78 are non-contact seals that can be used in high temperature and high pressure regions, such as floating ring seals.

[0093] In addition, in the configuration as in the second embodiment, the sealing portion 78 may be disposed between the annular flow path forming portion 73 and the cylindrical body 5 , and between the annular flow path forming portion 73 and the connecting flow path portion 74F.

[0094] And, if Fig.12 As shown, the combustor 15 has an annular sleeve portion 55 arranged to surround the communication hole 71 inside the cylinder 5. The sleeve portion 55 forms a flow path through which cooling air can flow between the sleeve portion 55 and the inner peripheral surface of the cylinder 5. As a flow sleeve, a part of the compressed air ejected from the compressor 14 is supplied to the sleeve portion 55 as cooling air.

[0095] In addition, in the configuration as in the second embodiment, the collar portion 55 may be disposed with respect to the communication hole 71 covered by the annular flow path forming portion 73 .

[0096] (Effect)

[0097] As described above, an independent valve device 81B is disposed in each communicating hole 71 via the connecting flow path portion 74F. As a result, the valve device 81B can be adjusted for each communicating hole 71 individually or simultaneously. Therefore, even if any one of ammonia fuel and hydrocarbon fuel is supplied, the supply amount of compressed air can be accurately adjusted to the combustion chamber 50. Therefore, even if temperature distribution or concentration distribution is uneven in the cylinder 5 or the combustion chamber 50 according to the operating state, the supply amount can be arbitrarily adjusted, thereby making it easy to suppress the generation amount of NOx.

[0098] Furthermore, by arranging the sealing portion 78 , even if high-temperature and high-pressure compressed air flows, leakage of the compressed air from the connection points of the components can be suppressed.

[0099] Furthermore, the periphery of the communicating hole 71 can be cooled by disposing the sleeve portion 55. Therefore, it is possible to suppress the occurrence of thermal expansion around the communicating hole 71 due to the influence of the high-temperature combustion gas flowing through the combustion chamber 50.

[0100] <Sixth Embodiment>

[0101] Next, according to Fig.13 and Fig.14 , a sixth embodiment of the gas turbine equipment 1 according to the present invention will be described. In the sixth embodiment described below, the same components as those of the first to fifth embodiments are denoted by the same reference numerals in the drawings, and descriptions thereof are omitted. In the sixth embodiment, the fuel nozzle 6G and the flow rate adjustment unit 8G are different.

[0102] The fuel nozzle 6G of the sixth embodiment has a mixing section 65 that forms a mixing space 650 for mixing the fluids ejected from the first injection hole 61, the second injection hole 62, and the third injection hole 63 before supplying to the combustion chamber 50. In the fuel nozzle 6G, the mixing section 65 forms a front end portion connected to the combustion chamber 50. The mixing section 65 is connected to the first injection hole 61, the second injection hole 62, and the third injection hole 63. Only a predetermined constant amount of fluid can flow into the mixing space 650. That is, in the fuel nozzle 6G of the sixth embodiment, the supplied ammonia fuel, hydrocarbon fuel, and compressed air are mixed and injected into the combustion chamber 50 from the mixing section 65 as a constant amount of fluid. Thus, the supply amount of ammonia fuel, hydrocarbon fuel, and compressed air to the fuel nozzle 6G is limited until a constant amount is reached.

[0103] The flow regulating unit 8G is not limited to the structure having the valve devices 81 and 81B as described in the first to fifth embodiments. That is, the flow regulating unit 8G of the sixth embodiment does not have the valve devices 81 and 81B. The flow regulating unit 8G of the sixth embodiment changes the ratio of the supply amount of ammonia fuel and hydrocarbon fuel to the compressed air on the basis of setting the supply amount of ammonia fuel, hydrocarbon fuel and compressed air to the fuel nozzle 6G to be constant. The flow regulating unit 8G can adjust the supply amount of at least one of the ammonia fuel and the hydrocarbon fuel, thereby adjusting the flow rate of the compressed air supplied from the connecting hole 71 to the cylinder 5. In the sixth embodiment, as described above, the supply amount of ammonia fuel, hydrocarbon fuel and compressed air to the fuel nozzle 6 is set to be constant through the mixing unit 65. In this state, the flow regulating unit 8G can adjust the supply amount of at least one of the ammonia fuel and the hydrocarbon fuel so that the supply amount of ammonia fuel when supplying ammonia fuel to the fuel nozzle 6G is greater than the supply amount of hydrocarbon fuel when supplying hydrocarbon fuel to the fuel nozzle 6G. Specifically, as Fig.13 As shown, the flow rate adjustment unit 8G of the sixth embodiment includes a first supply amount adjustment unit 85 and a second supply amount adjustment unit 86 .

[0104] The first supply amount adjustment unit 85 adjusts the supply amount of the ammonia fuel to the fuel nozzle 6G. The first supply amount adjustment unit 85 is arranged in the first supply pipeline 22. The first supply amount adjustment unit 85 is, for example, a flow rate adjustment valve, an on-off valve, or a solenoid valve. By increasing the opening of the first supply amount adjustment unit 85, the supply amount of the ammonia fuel supplied from the first supply pipeline 22 to the first injection hole 61 increases. Conversely, by decreasing the opening of the first supply amount adjustment unit 85, the supply amount of the ammonia fuel supplied from the first supply pipeline 22 to the first injection hole 61 decreases.

[0105] The second supply amount adjustment unit 86 adjusts the supply amount of hydrocarbon fuel to the fuel nozzle 6G. The second supply amount adjustment unit 86 is arranged in the second supply pipeline 32. The second supply amount adjustment unit 86 is, for example, a flow rate adjustment valve, an on-off valve, or a solenoid valve. By increasing the opening of the second supply amount adjustment unit 86, the supply amount of hydrocarbon fuel from the second supply pipeline 32 to the second injection hole 62 increases. On the contrary, by decreasing the opening of the second supply amount adjustment unit 86, the supply amount of hydrocarbon fuel from the second supply pipeline 32 to the second injection hole 62 decreases. Moreover, even when the second supply amount adjustment unit 86 is in a fully open state, the flow rate that can flow in the second supply pipeline 32 is smaller than the flow rate when the first supply amount adjustment unit 85 is in a fully open state. That is, when both the first supply amount adjustment unit 85 and the second supply amount adjustment unit 86 are in a fully open state, the supply amount of ammonia fuel becomes more than that of hydrocarbon fuel. Specifically, based on the ratio of the calorific value of the ammonia fuel to the calorific value of the hydrocarbon fuel, the second supply amount adjustment unit 86 is preferably able to flow at a flow rate that is inversely proportional to the ratio relative to the first supply amount adjustment unit 85. More specifically, when the calorific value and WI (Wobbe index) of the hydrocarbon fuel are about 4 times the calorific value of the ammonia fuel, the second supply amount adjustment unit 86 can flow only at a flow rate that is about 1 / 4 of the first supply amount adjustment unit 85.

[0106] (Effect)

[0107] like Fig.14 As shown in FIG. 1 , the flow rate adjustment unit 8G adjusts the amount of ammonia fuel, hydrocarbon fuel, and compressed air supplied to the fuel nozzle 6G. Specifically, when ammonia fuel and hydrocarbon fuel are supplied together, as shown in FIG. Fig.14 As shown in “co-firing”, the first supply amount adjusting unit 85 and the second supply amount adjusting unit 86 are adjusted in such a manner that the ratio of the total supply amount of the ammonia fuel and the hydrocarbon fuel to the supply amount of the compressed air becomes close to a value of 1:1.

[0108] Furthermore, when only ammonia fuel is supplied, Fig.14 As shown in "NH3 only", the first supply amount adjustment unit 85 is opened and the second supply amount adjustment unit 86 is closed in such a way that the supply amount of ammonia fuel is greater than the supply amount of compressed air. As a result, compared with the case of "mixed combustion", a large amount of ammonia fuel is supplied to the mixing space 650 from the first injection hole 61, and almost no compressed air is supplied from the third injection hole 63. Moreover, a large amount of compressed air that cannot flow into the third injection hole 63 is supplied to the combustion chamber 50 from the connecting hole 71. As a result, most of the compressed air in the intermediate casing 13 flows into the combustion chamber 50 from the connecting hole 71. That is, a part of the compressed air to be supplied to the third injection hole 63 flows directly into the combustion chamber 50 from the connecting hole 71.

[0109] Furthermore, when only hydrocarbon fuel is supplied, Fig.14 As shown in "CH4 only", the first supply amount adjusting unit 85 is closed and the second supply amount adjusting unit 86 is opened in such a way that the supply amount of hydrocarbon fuel is greater than the supply amount of compressed air. Moreover, the second supply amount adjusting unit 86 is configured so that only a very small flow rate can flow through the first supply amount adjusting unit 85. Therefore, compared with the case of "NH3 only" or the case of "mixed combustion", in the case of "CH4 only", the flow rate of compressed air flowing into the mixing space 650 from the third injection hole 63 increases. As a result, the amount of compressed air that cannot flow into the third injection hole 63 is reduced. As a result, the compressed air in the intermediate casing 13 hardly flows into the combustion chamber 50 from the connecting hole 71. That is, when using hydrocarbon fuel, the flow rate of compressed air used in the fuel nozzle 6 can be increased compared with the case of using ammonia fuel.

[0110] In this way, by adjusting the supply amount of ammonia fuel and the supply amount of hydrocarbon fuel, the flow rate of compressed air used in the fuel nozzle 6 can be adjusted. Therefore, it is not necessary to configure the valve device 81, 81B, and by a simpler structure or control that only changes the supply amount of ammonia fuel and the supply amount of hydrocarbon fuel, even if either ammonia fuel or hydrocarbon fuel is supplied, stable combustion can be continued and the generation amount of NOx can be suppressed. Therefore, it is possible to effectively take into account both the combustion based on ammonia fuel and hydrocarbon fuel.

[0111] In addition, as described above, the flow rate adjustment unit 8G of the sixth embodiment can be applied to a configuration without the valve devices 81 and 81B, but can also be applied to a configuration further including the valve devices 81 and 81B.

[0112] <Seventh Embodiment>

[0113] Next, according to Fig.15 , a seventh embodiment of the gas turbine equipment 1 according to the present invention will be described. In the seventh embodiment described below, the same symbols are given to the same structures as those in the first to sixth embodiments, and their descriptions are omitted. In the seventh embodiment, the difference is that the flow rate adjustment unit 8H adjusts the flow rate according to the operating state of the combustor 15.

[0114] The gas turbine 10 of the seventh embodiment is further provided with a detection unit 9 for detecting the operating state of the combustor 15. Specifically, the detection unit 9 of the present embodiment detects the temperature in the combustor 15. In addition, the detection unit 9 can be any device as long as it can detect the operating state of the combustor 15. That is, the detection unit 9 can be any device as long as it can grasp the supply state of the ammonia fuel, the hydrocarbon fuel, and the compressed air. For example, the detection unit 9 can be a device for detecting at least any one of the supply amount or temperature of the ammonia fuel, the supply amount or temperature of the hydrocarbon fuel, and the supply amount or temperature of the compressed air relative to the fuel nozzle 6. In addition, the detection unit 9 can be a device for detecting the temperature of the combustion gas flowing into the vicinity of the turbine 16, the concentration of NOx contained in the exhaust gas, and the concentration of ammonia, which is an unburned component contained in the exhaust gas. In addition, the detection unit 9 can detect the state of the supplied fluid or the state of the combustion result in the combustor 15 of a plurality of the above-mentioned.

[0115] Furthermore, the flow rate adjustment unit 8H of the seventh embodiment includes a valve control device 88 for controlling the valve device 81 according to the detection result of the detection unit 9. The valve control device 88 changes the opening of the valve device 81 according to the detection result of the detection unit 9, thereby being able to adjust the flow rate of the compressed air supplied to the combustion chamber 50. Specifically, when the temperature of the burner 15 detected by the detection unit 9 exceeds the first threshold value, the valve control device 88 sends an instruction to reduce the opening of the valve device 81. The first threshold value is, for example, a value equivalent to the temperature when the supply of hydrocarbon fuel is switched from the state where only ammonia fuel is supplied to the fuel nozzle 6 to the mixed combustion state of ammonia fuel and hydrocarbon fuel. Furthermore, when the temperature of the burner 15 detected by the detection unit 9 exceeds a second threshold value greater than the first threshold value, the valve control device 88 sends an instruction to further reduce the opening of the valve device 81 (for example, to a fully closed state). The second threshold value is, for example, a value equivalent to the temperature when the supply of ammonia fuel is stopped from the mixed combustion state where both ammonia fuel and hydrocarbon fuel are supplied to the fuel nozzle 6 to the state where only hydrocarbon fuel is supplied.

[0116] The valve control device 88 described above is a computer. The valve control device 88 has a CPU (Central Processing Unit) that performs various calculations, a main storage device such as a memory that serves as a work area of ​​the CPU, an auxiliary storage device such as a hard disk drive, an input device such as a keyboard or a mouse, and a display device in terms of hardware. In addition, the valve control device 88 can be incorporated into a control device (not shown) of the gas turbine equipment 1 as a part of the function.

[0117] (Effect)

[0118] In this way, the valve control device 88 controls the valve device 81 based on the detection result of the detection unit 9, thereby being able to adjust the flow rate of the compressed air sent from the communication hole 71 through the valve device 81 to the combustion chamber 50 without delay according to the operating state of the burner 15. Moreover, at the time of switching the supply of ammonia fuel and hydrocarbon fuel, stable combustion can be continued and the generation of NOx can be suppressed.

[0119] Furthermore, of the ammonia fuel and the hydrocarbon fuel, the hydrocarbon fuel has a much higher calorific value than the ammonia fuel. Therefore, by detecting the temperature of the burner 15 by the detection unit 9, it is possible to easily understand the supply amounts of the ammonia fuel and the hydrocarbon fuel, respectively.

[0120] (Other embodiments)

[0121] As mentioned above, the embodiment of the present invention has been described in detail with reference to the drawings, but the specific structure is not limited to this embodiment, and design changes and the like are included within the scope that does not depart from the gist of the present invention.

[0122] The gas turbine equipment 1 is not limited to the structure described in the present embodiment. For example, the gas turbine equipment 1 may include a control device for controlling various devices, a denitration device for decomposing NOx components contained in the exhaust gas from the gas turbine 10, a chimney for discharging the exhaust gas flowing out of the denitration device to the outside, and the like as other structures.

[0123] Furthermore, the burner 15 is not limited to the structure described in the present embodiment. That is, the burner 15 may include structures other than the cylinder 5, the fuel nozzles 6, 6G, the intermediate supply units 7, 7B, 7C, 7D, 7E, 7F, and the flow rate adjustment units 8, 8B, 8G, 8H (e.g., a sound damper, etc.).

[0124] The fuel nozzles 6 and 6G are not limited to the above-mentioned structure. The fuel nozzles 6 and 6G may be any type of nozzles, such as a type that mixes fuel and air in advance (premixed combustion type), a type that quickly mixes fuel and air as in the present embodiment (diffusion combustion type), a type that independently injects fuel and air, etc.

[0125] Furthermore, the adjustment of the supply state of the ammonia fuel from the ammonia fuel supply device 20 to the fuel nozzles 6, 6G and the adjustment of the supply state of the hydrocarbon fuel from the hydrocarbon fuel supply device 30 to the fuel nozzles 6, 6G can be manually performed by an operator or automatically performed by a control device of the gas turbine equipment 1, etc.

[0126] In the present embodiment, the ammonia fuel supply equipment 20 supplies gaseous ammonia fuel to the gas turbine 10, but the present invention is not limited thereto. As long as the gas turbine 10 is capable of receiving liquid ammonia fuel, the ammonia fuel supply equipment 20 can supply liquid ammonia fuel to the gas turbine 10.

[0127] Similarly, the control of the valve devices 81 and 81B, the first supply amount adjustment unit 85 , and the second supply amount adjustment unit 86 may be performed manually by an operator or automatically by a control device of the gas turbine facility 1 or the like.

[0128] Furthermore, the intermediate supply parts 7, 7B, 7C, 7D, 7E, 7F are not limited to the structure having the communicating hole 71 as described in the present embodiment. The intermediate supply parts 7, 7B, 7C, 7D, 7E, 7F may be structures capable of supplying a part of the compressed air supplied to the fuel nozzles 6, 6G to the cylinder 5 at the downstream side Df2 in the flow direction Df of the combustion gas relative to the fuel nozzles 6, 6G. Therefore, the intermediate supply parts 7, 7B, 7C, 7D, 7E, 7F may be structures that, for example, extract the compressed air compressed by the compressor 14 through piping or the like and supply it to the cylinder 5.

[0129] <Notes>

[0130] The gas turbine 10 and the gas turbine equipment 1 described in each embodiment can be understood, for example, as follows.

[0131] (1) The gas turbine 10 involved in the first embodiment includes: a compressor 14 capable of compressing air to generate compressed air; a burner 15 capable of switching the fuel to be burned between ammonia fuel and hydrocarbon fuel, and capable of burning at least one of the ammonia fuel and the hydrocarbon fuel in the compressed air supplied from the compressor 14 to generate combustion gas; and a turbine 16 capable of being driven by the combustion gas supplied from the burner 15, the burner 15 having: a cylindrical barrel 5 for passing the combustion gas generated by burning the ammonia fuel or the hydrocarbon fuel; fuel nozzles 6, 6G for spraying the ammonia fuel, the hydrocarbon fuel and the compressed air into the interior of the barrel 5; intermediate supply parts 7, 7B, 7C, 7D, 7E, 7F, relative to The downstream side Df2 of the fuel nozzles 6, 6G in the flow direction Df of the combustion gas supplies a portion of the compressed air supplied to the fuel nozzles 6, 6G to the cylinder 5; and the flow adjustment parts 8, 8B, 8G, 8H are capable of adjusting the flow rate of the compressed air supplied from the intermediate supply parts 7, 7B, 7C, 7D, 7E, 7F to the cylinder 5 relative to the supply amount of the compressed air supplied to the fuel nozzles 6, 6G. The flow adjustment parts 8, 8B, 8G, 8H increase the flow rate of the compressed air supplied from the intermediate supply parts 7, 7B, 7C, 7D, 7E, 7F to the cylinder 5 when burning the ammonia fuel, and reduce the flow rate of the compressed air supplied to the cylinder 5 when burning the hydrocarbon fuel.

[0132] Thus, when the combustion gas is generated by using the ammonia fuel, the flow rate of the compressed air used for combustion in the fuel nozzle 6 can be reduced. As a result, when the ammonia fuel is burned, the generation of unstable combustion due to excessive supply of compressed air can be suppressed. Thus, when the ammonia fuel is burned, stable combustion is continued, and flame retention can be maintained.

[0133] Furthermore, the ratio of ammonia fuel to the ratio of ammonia fuel to compressed air supply increases due to the reduction in the supply of compressed air. As a result, the amount of nitrogen components remaining in the combustion gas derived from nitrogen in the ammonia fuel can be greatly reduced. Therefore, the amount of NOx generated when the ammonia fuel is burned can be suppressed.

[0134] Furthermore, when the combustion gas is generated by using hydrocarbon fuel, the flow rate of the compressed air used for combustion in the fuel nozzle 6 can be increased. As a result, when the hydrocarbon fuel is burned, it is possible to ensure that the required amount of compressed air is supplied to the fuel nozzles 6, 6G. Thus, when the hydrocarbon fuel is burned, stable combustion is continued, and flame retention can be maintained.

[0135] In addition, the ratio of hydrocarbon fuel to the ratio of the supply of compressed air increases due to the increase in the supply of compressed air. As a result, the amount of nitrogen components remaining in the combustion gas derived from nitrogen in the compressed air can be greatly reduced. Therefore, the amount of NOx generated when the hydrocarbon fuel is burned can be suppressed.

[0136] Thus, even if either ammonia fuel or hydrocarbon fuel is supplied to the gas turbine 10 to which ammonia fuel or hydrocarbon fuel is supplied, stable combustion can be continued and the amount of NOx generated can be suppressed. Therefore, combustion based on ammonia fuel and hydrocarbon fuel can be effectively taken into account.

[0137] (2) The gas turbine 10 according to the second aspect is the gas turbine 10 according to (1), wherein the flow rate adjustment unit 8 , 8B, 8G, 8H includes a valve device 81 , 81B capable of adjusting a flow rate of the compressed air flowing into the cylinder 5 .

[0138] Thus, the supply amount of compressed air when the ammonia fuel is supplied and when the hydrocarbon fuel is supplied can be adjusted with a simple structure.

[0139] (3) The gas turbine 10 involved in the third embodiment is the gas turbine 10 of (1) or (2), wherein the intermediate supply section 7, 7B, 7C, 7D, 7E, 7F has a connecting hole 71 connecting the inside and the outside of the cylinder 5 at a position away from the fuel nozzle 6 and at a position on the downstream side Df2 in the flow direction Df of the combustion gas relative to the fuel nozzle 6, 6G.

[0140] Thus, the compressed air flowing into the combustion chamber 50 from the communication hole 71 does not directly participate in the 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 nozzles 6 and 6G can be obtained with a simple structure.

[0141] (4) The 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 cylinder 5 at a plurality of locations separated from each other.

[0142] Thus, the compressed air supplied to the cylinder 5 is not significantly biased toward a portion of the inner circumferential surface of the cylinder 5 and is supplied to the combustion chamber 50. Therefore, even if any one of the ammonia fuel and the hydrocarbon fuel is supplied, stable combustion can be effectively continued in a wide area of ​​the combustion chamber 50, and the generation of NOx can be effectively suppressed.

[0143] (5) The gas turbine 10 involved in the fifth embodiment is the gas turbine 10 of (3) or (4), wherein the intermediate supply section 7B, 7C, 7D, 7E has an annular flow path forming portion 73 that forms an annular flow path 730 through which the compressed air can flow along the outer periphery of the cylinder 5, and the connecting hole 71 connects the annular flow path forming portion 73 with the cylinder 5.

[0144] Thus, the annular flow path forming portion 73 functions as a damper, and the compressed air in the annular flow path 730 is in a nearly uniform pressure state. Then, the compressed air fills the annular flow path 730 and flows into the combustion chamber 50 from the connecting hole 71. Thus, the compressed air in the annular flow path forming portion 73 in a nearly uniform pressure state can be supplied from the connecting hole 71 to the combustion chamber 50. Therefore, even if any one of the ammonia fuel and the hydrocarbon fuel is supplied, stable combustion can be continued more effectively in a wide area of ​​the combustion chamber 50, and the amount of NOx generated can be more effectively suppressed.

[0145] (6) The gas turbine 10 according to a sixth aspect is the gas turbine 10 according to (5), wherein the annular flow path forming portion 73 is disposed with respect to the outer peripheral surface of the cylinder 5 via a gap 770 .

[0146] Thus, even if thermal expansion occurs in the cylinder 5 due to the influence of the high-temperature combustion gas flowing through the combustion chamber 50, the thermal expansion can be absorbed without affecting the annular flow path forming portion 73. Thus, the fixed state of the annular flow path forming portion 73 and the cylinder 5 can be stably maintained.

[0147] (7) The gas turbine 10 according to the seventh embodiment is any one of the gas turbines 10 described in (3) to (6), wherein the intermediate supply portion 7D, 7E has a supply pipe 76 that is arranged in the communicating hole 71 and is formed into a tubular shape and extends inward from the inner peripheral surface of the cylinder 5.

[0148] Thus, the compressed air flowing into the combustion chamber 50 from the communication hole 71 is sent to a position further inside the inner peripheral surface of the cylinder 5 through the supply pipe 76. Thus, the compressed air can be stably supplied to the deep part of the combustion chamber 50 away from the communication hole 71.

[0149] (8) The gas turbine 10 involved in the eighth embodiment is any one of the gas turbines 10 (1) to (7), wherein the flow regulating unit 8, 8B, 8G, 8H can adjust the supply amount of at least one of the ammonia fuel and the hydrocarbon fuel on the basis of setting the supply amounts of the ammonia fuel, the hydrocarbon fuel and the compressed air to the fuel nozzles 6, 6G to be constant, so that 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 fuel when the hydrocarbon fuel is supplied to the fuel nozzles 6, 6G.

[0150] Thus, by adjusting the supply amount of the ammonia fuel and the supply amount of the hydrocarbon fuel, it is possible to adjust the flow rate of the compressed air used in the fuel nozzle 6. Therefore, it is not necessary to configure the valve devices 81 and 81B, and by a simpler structure or control that only changes the supply amount of the ammonia fuel and the supply amount of the hydrocarbon fuel, even if either the ammonia fuel or the hydrocarbon fuel is supplied, stable combustion can be continued and the generation of NOx can be suppressed.

[0151] (9) The gas turbine 10 involved in the ninth embodiment is any one of the gas turbines 10 (1) to (8), which also includes a detection unit 9 for detecting the operating status of the combustor 15, and the flow adjustment unit 8, 8B, 8G, 8H adjusts the flow rate of the compressed air supplied to the cylinder 5 according to the detection result of the detection unit 9.

[0152] Thus, the flow rate of compressed air sent to the combustion chamber 50 through the flow regulators 8, 8B, 8G, and 8H can be adjusted without lag according to the operating state of the burner 15. Moreover, at the time of switching the supply of ammonia fuel and hydrocarbon fuel, stable combustion can be continued and the generation of NOx can be suppressed.

[0153] (10) The gas turbine equipment 1 involved in the tenth embodiment includes any one of the gas turbines 10 (1) to (9), an ammonia fuel supply equipment 20 capable of supplying the ammonia fuel to the gas turbine 10, and a hydrocarbon fuel supply equipment 30 capable of supplying the hydrocarbon fuel to the gas turbine 10.

[0154] Industrial Applicability

[0155] According to the gas turbine and the gas turbine equipment of the present invention, it is possible to continue stable combustion and suppress the amount of NOx generated in the gas turbine to which the ammonia fuel and the hydrocarbon fuel are supplied.

[0156] Explanation of symbols

[0157] 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 part, 71-communication hole, 8, 8B, 8G, 8H-flow adjustment part, 81, 81B-valve device, Df-flow direction, Df1-upstream side, Df2-downstream side, 16-turbine, 16 r-turbine rotor, 16c-turbine housing, Ar-rotor axis, 20-ammonia fuel supply equipment, 21-first storage tank, 22-first supply pipeline, 30-hydrocarbon fuel supply equipment, 31-second storage tank, 32-second supply pipeline, 73, 73C-annular flow path forming part, 730-annular flow path, 75-welding part, 74, 74C, 74F-connecting flow path part, 76-supply pipe, 77-gap forming part, 770-gap, 78-sealing part, 55-sleeve part, 85-first supply amount adjustment part, 86-second supply amount adjustment part, 65-mixing part, 650-mixing space, 9-detection part, 88-valve control device.

Claims

1. A gas turbine comprising: A compressor capable of compressing air to generate compressed air; a burner capable of switching the fuel to be burned between ammonia fuel and hydrocarbon fuel, and capable of burning at least one of the ammonia fuel and the hydrocarbon fuel in the compressed air supplied from the compressor to generate combustion gas; and a turbine capable of being driven by the combustion gas supplied from the combustor, The burner has: A cylindrical body through which the combustion gas generated by the combustion of the ammonia fuel or the hydrocarbon fuel flows; A fuel nozzle, which sprays the ammonia fuel, the hydrocarbon fuel and the compressed air into the interior of the cylinder; an intermediate supply portion that supplies a portion of the compressed air supplied to the fuel nozzle to the cylinder at a downstream side in a flow direction of the combustion gas relative to the fuel nozzle; and a flow rate adjusting unit capable of adjusting a flow rate of the compressed air supplied from the intermediate supply unit to the cylinder relative to a supply amount of the compressed air supplied to the fuel nozzle, The flow rate adjustment unit increases the flow rate of the compressed air supplied from the intermediate supply unit to the cylinder when the ammonia fuel is combusted, and reduces the flow rate of the compressed air supplied to the cylinder when the hydrocarbon fuel is combusted.

2. The gas turbine according to claim 1, wherein: The flow rate adjustment unit includes a valve device capable of adjusting the flow rate of the compressed air flowing into the cylinder.

3. The gas turbine according to claim 1 or 2, wherein: The intermediate supply portion has a communication hole that communicates the inside and the outside of the cylindrical body at a position away from the fuel nozzle and at a position downstream of the fuel nozzle in a 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 locations separated from each other.

5. The gas turbine according to claim 4, wherein: The intermediate supply portion includes an annular flow path forming portion that forms an annular flow path through which the compressed air can flow along the outer circumference of the cylinder. The communication hole communicates the annular flow path forming portion and the cylindrical body.

6. The gas turbine according to claim 5, wherein: The annular flow path forming portion is arranged with a gap interposed with respect to the outer peripheral surface of the cylindrical body.

7. The gas turbine according to claim 5, wherein: The intermediate supply portion includes a supply pipe that is disposed in the communication hole and is formed in a tubular shape and extends inward from the inner peripheral surface of the cylindrical body.

8. The gas turbine according to claim 1, wherein: The flow regulating unit can adjust the supply amount of at least one of the ammonia fuel and the hydrocarbon fuel on the basis of setting the supply amounts of the ammonia fuel, the hydrocarbon fuel and the compressed air to the fuel nozzle to be constant, so that the supply amount of the ammonia fuel when the ammonia fuel is supplied to the fuel nozzle is greater than the supply amount of the hydrocarbon fuel when the hydrocarbon fuel is supplied to the fuel nozzle.

9. The gas turbine according to claim 1 or 2, further comprising: a detection unit for detecting an operating state of the combustor; The flow rate adjustment unit adjusts the flow rate of the compressed air supplied to the cylinder based on the detection result of the detection unit.

10. A gas turbine equipment comprising: The gas turbine according to claim 1 or 2; an ammonia fuel supply device capable of supplying the ammonia fuel to the gas turbine; and The hydrocarbon fuel supply equipment is capable of supplying the hydrocarbon fuel to the gas turbine.

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