Gas turbine and gas turbine plant

Abstract

A gas turbine includes a combustor capable of switching a fuel to be combusted between an ammonia fuel and a hydrocarbon fuel. The combustor includes a cylindrical cylinder through which combustion gas flows, a fuel nozzle that injects the ammonia fuel, the hydrocarbon fuel, and compressed air into the inside of the cylinder, an intermediate supply portion that supplies a portion of the compressed air to the cylinder, and a flow rate adjustment portion that is capable of adjusting the flow rate of the compressed air supplied to the cylinder. The flow rate adjustment portion increases the flow rate of the compressed air supplied to the cylinder when the ammonia fuel is combusted, and decreases the flow rate of the compressed air supplied to the cylinder when the hydrocarbon fuel is combusted.

Description

Technical Field

[0001] This invention relates to a gas turbine and a gas turbine device.

[0002] This application claims priority based on Japanese Patent Application No. 2022-133982, filed on August 25, 2022, the contents of which are incorporated herein by reference. Background Technology

[0003] A gas turbine consists of a compressor that compresses air, a combustor that burns fuel in the compressed air to produce combustion gases, and a turbine driven by the combustion gases. The fuel supplied to the combustor is typically a fossil fuel, such as natural gas or petroleum, i.e., a hydrocarbon fuel, but ammonia is sometimes used as well.

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

[0005] Previous technical documents

[0006] Patent documents

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

[0008] The technical problem to be solved by the invention

[0009] Ammonia fuel has a low calorific value and a slow combustion rate. In other words, ammonia fuel has poor combustibility compared to hydrocarbon fuels. Therefore, in gas turbines capable of simultaneously supplying both ammonia and hydrocarbon fuels, it is difficult to maintain stable combustion when either fuel is supplied.

[0010] Furthermore, when ammonia is used as fuel in a gas turbine, NOx is generated during combustion as a component of the nitrogen that forms ammonia. Therefore, the more inefficient the combustion process, the more NOx production increases when the amount of ammonia fuel supplied to the burner is less than the amount of compressed air supplied. On the other hand, if hydrocarbon fuels are burned, NOx originates from nitrogen in the compressed air. Therefore, when the amount of hydrocarbon fuel supplied to the burner is close to the same as the amount of compressed air supplied, the closer the fuel or air supply is to stoichiometry, the higher the combustion temperature and the greater the NOx production. In other words, if the amount of compressed air supplied is the same regardless of whether ammonia or hydrocarbon fuel is supplied, it is difficult to suppress NOx production.

[0011] The present invention provides a gas turbine and gas turbine equipment that can maintain stable combustion and suppress NOx production in a gas turbine that simultaneously supplies ammonia fuel and hydrocarbon fuel.

[0012] means for solving technical problems

[0013] One aspect of the present invention relates to a gas turbine comprising: a compressor capable of compressing air to generate compressed air; a combustor capable of switching between burning 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 combustor having: a cylindrical body for the combustion gas generated by burning the ammonia fuel or the hydrocarbon fuel to flow through; and a fuel nozzle for injecting the ammonia fuel and the hydrocarbon fuel into the interior of the cylindrical body. The fuel and the compressed air; an intermediate supply unit that supplies a portion of the compressed air supplied to the fuel nozzle to the cylinder on the downstream side relative to the flow direction of the combustion gas relative to the fuel nozzle; and a flow rate adjustment unit that can adjust the flow rate of the compressed air supplied from the intermediate supply unit to the cylinder relative to the amount of compressed air supplied to the fuel nozzle, the flow rate adjustment unit increasing the flow rate of the compressed air supplied from the intermediate supply unit to the cylinder when burning the ammonia fuel, and decreasing the flow rate of the compressed air supplied to the cylinder when burning the hydrocarbon fuel.

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

[0015] Invention Effects

[0016] According to the present invention, the gas turbine and gas turbine device can ensure stable and continuous combustion and suppress NOx production in gas turbines supplied with ammonia fuel and hydrocarbon fuel. Attached Figure Description

[0017] Figure 1 This is a schematic structural diagram of a gas turbine device in the first embodiment of the present invention.

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

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

[0020] Figure 4 yes Figure 3 AA-direction sectional view.

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

[0022] Figure 6 Is with Figure 5 Enlarged view of the main part of the burner in the modified example of the corresponding second embodiment.

[0023] Figure 7 Is with Figure 5 Enlarged view of the main part of the burner in the corresponding third embodiment.

[0024] Figure 8 Is with Figure 5 Enlarged view of the main part of the burner in the corresponding fourth embodiment.

[0025] Figure 9 This is a schematic cross-sectional view of the burner in the fifth embodiment of the present invention.

[0026] Figure 10 yes Figure 8 BB-direction sectional view.

[0027] Figure 11 yes Figure 8 Enlarged view of the first major part of the burner.

[0028] Figure 12 yes Figure 8 Enlarged view of the second main part of the burner.

[0029] Figure 13 This is a schematic cross-sectional view of the burner in the sixth embodiment of the present invention.

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

[0031] Figure 15 This is a schematic cross-sectional view of the burner in the seventh embodiment of the present invention. Detailed Implementation

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

[0033] <First Implementation Method>

[0034] (Structure of a gas turbine equipment)

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

[0036] (Structure of a gas turbine)

[0037] The gas turbine 10 can switch between burning ammonia fuel and hydrocarbon fuel. The gas turbine 10 can be driven by combustion gases generated from burning at least one of ammonia fuel and hydrocarbon fuel. The gas turbine 10 of this embodiment includes a compressor 14, a burner 15, a turbine 16, an intake pipe 12, and an intermediate housing 13.

[0038] Compressor 14 is capable of compressing air to generate compressed air. Compressor 14 has a compressor rotor 14r rotating around a rotor axis Ar, a compressor housing 14c covering the compressor rotor 14r, and an IGV (inlet guide vane) 14v disposed at the suction port of the compressor housing 14c. The IGV 14v regulates the flow rate, i.e., the intake air volume, of the air drawn into the compressor housing 14c. Intake pipe 12 is connected to the suction port of the compressor housing 14c.

[0039] The turbine 16 is driven by high-temperature and high-pressure combustion gas supplied from the combustor 15. The turbine 16 has a turbine rotor 16r that rotates about a rotor axis Ar around the combustion gas from the combustor 15, and a turbine housing 16c covering the turbine rotor 16r. The turbine rotor 16r and the compressor rotor 14r are rotatably connected to each other about the same rotor axis Ar to form a gas turbine rotor 11. For example, a generator rotor is connected to this gas turbine rotor 11.

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

[0041] The burner 15 is capable of generating combustion gas by burning at least one of ammonia fuel and hydrocarbon fuel in compressed air supplied from the compressor 14. Hydrocarbon fuel is a fuel containing hydrocarbons, such as fossil fuels like natural gas or petroleum. Both ammonia fuel and hydrocarbon fuel can be supplied to the burner 15. The burner 15 adjusts the supply of ammonia fuel and hydrocarbon fuel according to operating conditions, thereby enabling operation under conditions of burning only ammonia fuel, burning only hydrocarbon fuel, and burning both ammonia fuel and hydrocarbon fuel. Furthermore, under the condition of burning both ammonia fuel and hydrocarbon fuel, the supply of ammonia fuel and the supply of hydrocarbon fuel can be the same or different. The burner 15 is fixed to the intermediate housing 13. Figure 2 As shown, the burner 15 of this embodiment has a cylinder 5, a fuel nozzle 6, an intermediate supply section 7, and a flow adjustment section 8.

[0042] The cylinder 5 has a combustion chamber 50 formed inside. The combustion chamber 50 is the internal space of the cylinder 5. That is, the combustion gas generated by the combustion of at least one of ammonia fuel and hydrocarbon fuel flows inside the cylinder 5. The cylinder 5 is disposed within an intermediate housing 13 into which compressed air compressed by the compressor 14 flows. In the combustion chamber 50, at least one of ammonia fuel and hydrocarbon fuel is supplied together with compressed air and combusted. The combustion gas generated by the combustion of at least one of ammonia fuel and hydrocarbon fuel flows through the combustion chamber 50 and is delivered 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 may be a structure in which multiple components are arranged in a direction extending along the central axis.

[0043] Fuel nozzle 6 injects ammonia fuel, hydrocarbon fuel, and compressed air into combustion chamber 50. Fuel nozzle 6 is fixed to one end (upstream end, first end) of the cylinder 5, located away from turbine 16. Fuel nozzle 6 injects ammonia fuel, hydrocarbon fuel, and compressed air into combustion chamber 50 towards turbine 16. Fuel nozzle 6 generates combustion gases through 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 disposed inside cylinder 5. 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 independently of each other within the fuel nozzle 6. In the first embodiment, the first injection hole 61, the second injection hole 62, and the third injection hole 63 are formed such that the fluids are mixed together before being injected into the combustion chamber 50. The first injection hole 61 injects ammonia fuel introduced from outside the burner 15 into the combustion chamber 50. The first injection hole 61 is located at the center of the fuel nozzle 6 in the radial direction. The second injection hole 62 injects hydrocarbon fuel introduced from outside the burner 15 into the combustion chamber 50. The third injection hole 63 injects compressed air introduced from inside the intermediate housing 13 into the combustion chamber 50. The third injection hole 63 is arranged radially between the first injection hole 61 and the second injection hole 62 in the fuel nozzle 6.

[0045] Furthermore, the first injection hole 61, the second injection hole 62, and the third injection hole 63 are not limited to a single structure disposed inside the fuel nozzle 6. The first injection hole 61, the second injection hole 62, and the third injection hole 63 can be formed in independent nozzles. That is, the fuel nozzle 6 can be composed of multiple nozzles. Moreover, the fuel nozzle 6 can also have other structures such as a swirling nozzle.

[0046] The intermediate supply section 7 supplies a portion of the compressed air supplied to the fuel nozzle 6 to the cylinder 5 from a location other than the fuel nozzle 6. The intermediate supply section 7 is located within the intermediate housing 13. The intermediate supply section 7 is positioned downstream of the fuel nozzle 6 in the combustion gas flow direction Df, at position Df2. Here, the combustion gas flow direction Df refers to the direction within the cylinder 5 from the end where the fuel nozzle 6 is located towards the other end (downstream end, second end) connected to the turbine 16. Therefore, the upstream side Df1 in the combustion gas flow direction Df refers to the side of the cylinder 5 where the fuel nozzle 6 is located relative to the turbine 16. Furthermore, the downstream side Df2 in the combustion gas flow direction Df refers to the side of the cylinder 5 where the turbine 16 is located relative to the fuel nozzle 6. In this embodiment, the intermediate supply section 7 has a communication hole 71.

[0047] The connecting hole 71 is formed to connect the interior of the cylinder 5, i.e., the combustion chamber 50, to the exterior of the cylinder 5 at a position away from the fuel nozzle 6. That is, in this embodiment, the connecting hole 71 connects the combustion chamber 50 to the space inside the intermediate housing 13 without passing through the fuel nozzle 6. The connecting hole 71 is formed at a position downstream of the combustion gas flow direction Df relative to the fuel nozzle 6, on the Df side. The connecting hole 71 is formed to supply compressed air to a position relative to the combustion chamber 50 that will not directly participate in diffusion combustion. The connecting hole 71 is formed near the middle of the cylinder 5 in the flow direction Df. The connecting holes 71 are formed in the circumferential direction of the cylinder 5 at multiple positions (e.g., four locations) separated from each other along the outer circumferential surface 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 housing 13, facing the middle of the flow channel of the compressed air introduced into the third injection hole 63. More specifically, when the length from the front end of the fuel nozzle 6 to the location where the turbine 16 is connected is defined as the total length of the cylinder 5 (100%), the connecting hole 71 is preferably positioned between 30% and 70% of the distance from the front end of the fuel nozzle 6.

[0048] Furthermore, the connecting hole 71 is not limited to having multiple holes as in this embodiment. There may be only one connecting hole 71. Moreover, the multiple connecting holes 71 are not limited to being arranged at equal intervals, but may be arranged at different intervals.

[0049] The flow rate adjustment unit 8 can adjust the flow rate of compressed air supplied from the intermediate supply unit 7 to the cylinder 5 relative to the amount of compressed air supplied to the fuel nozzle 6. That is, the flow rate adjustment unit 8 can adjust the ratio of the amount of compressed air supplied indirectly to the combustion chamber 50 via the third injection hole 63 along with the fuel to 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 according to the respective supply amounts of ammonia fuel and hydrocarbon fuel supplied to the fuel nozzle 6. Specifically, the flow rate adjustment unit 8 increases the flow rate of compressed air supplied to the cylinder 5 when burning ammonia fuel. On the other hand, the flow rate adjustment unit 8 decreases the flow rate of compressed air supplied to the cylinder 5 when burning hydrocarbon fuel. Furthermore, the flow rate adjustment unit 8 of this embodiment includes a valve device 81.

[0050] The valve device 81 is capable of adjusting the flow rate of compressed air flowing from the outside of the cylinder 5 into the interior of the cylinder 5, i.e., 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 communication orifice 71. The valve device 81 adjusts the flow rate of compressed air through the communication orifice 71. Specifically, the valve device 81 opens more as the amount of ammonia fuel supplied to the first injection orifice 61 increases (e.g., it can be fully open). On the other hand, the valve device 81 closes less as the amount of hydrocarbon fuel supplied to the second injection orifice 62 increases (e.g., it can be fully closed). Furthermore, when both ammonia fuel and hydrocarbon fuel are supplied simultaneously, the valve device 81 adjusts its opening according to the NOx amount, making the opening the same as or intermediate to the level of the case where only ammonia fuel is supplied. That is, when both are supplied simultaneously, the valve device 81 is set to the same level or smaller than the case where only ammonia fuel is supplied to the fuel nozzle 6, and the opening is set larger than the case where only hydrocarbon fuel is supplied to the fuel nozzle 6. Multiple valve devices 81 of this embodiment are arranged such that one is configured relative to one communication hole 71. That is, one valve device 81 is configured to close only one communication hole 71.

[0051] (Structure of the ammonia fuel supply equipment)

[0052] like Figure 1 As shown, the ammonia fuel supply device 20 is capable of supplying ammonia fuel to the gas turbine 10. The ammonia fuel supply device 20 of this embodiment has a first storage tank 21 and a first supply pipeline 22.

[0053] Liquid ammonia fuel is stored in the first storage tank 21. A first supply line 22 connects the first storage tank 21 to the fuel nozzle 6. The first supply line 22 heats and vaporizes the liquid ammonia fuel before supplying it to the first injection port 61. The first supply line 22 can adjust the amount of ammonia fuel supplied to the first injection port 61. In addition, the first supply line 22 includes a heat exchanger (not shown) for vaporizing the liquid ammonia, a pump (not shown) for pressurizing, and a valve (not shown) for adjusting the supply amount.

[0054] (Structure of hydrocarbon fuel supply equipment)

[0055] The hydrocarbon fuel supply device 30 is capable of supplying hydrocarbon fuel to the gas turbine 10. The hydrocarbon fuel supply device 30 of this embodiment has a second storage tank 31 and a second supply pipeline 32.

[0056] Hydrocarbon fuel is stored in the second storage tank 31. A second supply line 32 connects the second storage tank 31 to the fuel nozzle 6. When the hydrocarbon fuel is in a liquid state, the second supply line 32 heats and vaporizes it before supplying it to the second injection port 62. The second supply line 32 can adjust the amount of hydrocarbon fuel supplied to the second injection port 62. In this case, the second supply line 32 includes a heat exchanger (not shown) for vaporizing the liquid hydrocarbon fuel, a pump (not shown) for pressurizing it, and a valve (not shown) for adjusting the supply amount. Alternatively, when the hydrocarbon fuel is stored in the second storage tank 31 in a gaseous state, it is supplied to the second injection port 62 either in its original state or after pressurization. In this case, the second supply line 32 includes a pump (not shown) for pressurizing the gaseous hydrocarbon fuel and a valve (not shown) for adjusting the supply amount.

[0057] (Effects)

[0058] In the gas turbine equipment 1 with the above structure, there are cases where only ammonia fuel is supplied to the gas turbine 10, cases where only hydrocarbon fuel is supplied, and cases where both ammonia fuel and hydrocarbon fuel are supplied simultaneously.

[0059] First, when only ammonia fuel is supplied, ammonia fuel is supplied from the first storage tank 21 to the fuel nozzle 6 via 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 this time, compressed air supplied to the fuel nozzle 6 via the intermediate housing 13 is injected into the combustion chamber 50 through the third injection hole 63. Furthermore, no hydrocarbon fuel is injected from the second injection hole 62. As a result, only ammonia fuel and compressed air undergo diffusion combustion in the combustion chamber 50. In addition, the combustion here is not limited to diffusion combustion, but becomes combustion that matches the shape of the fuel nozzle 6. Therefore, it can be a combustion mode close to premixed combustion, rather than diffusion combustion. At the same time, the valve device 81 is in a state of being fully open. As a result, most of the compressed air in the intermediate housing 13 flows into the combustion chamber 50 through the connecting hole 71. That is, a portion of the compressed air that should be supplied to the third injection hole 63 flows directly into the combustion chamber 50 through the connecting hole 71. Therefore, when only ammonia fuel is supplied to the fuel nozzle 6, the flow rate of compressed air supplied to the third injection hole 63 can be reduced.

[0060] 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 this time, compressed air is injected into the combustion chamber 50 from the third injection hole 63. Ammonia fuel is not injected from the first injection hole 61. As a result, only hydrocarbon fuel and compressed air burn in the combustion chamber 50. Simultaneously, the valve device 81 is in a slightly open (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 that should be supplied to the third injection hole 63 hardly decreases and flows into the combustion chamber 50 from the third injection hole 63. Thus, 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] Furthermore, when both ammonia fuel and hydrocarbon fuel are supplied, ammonia fuel is supplied from the first storage tank 21 to the fuel nozzle 6 via the first supply line 22. Simultaneously, hydrocarbon fuel is supplied from the second storage tank 31 to the fuel nozzle 6 via 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 through the third injection hole 63. As a result, ammonia fuel, hydrocarbon fuel, and compressed air are burned in the combustion chamber 50. Simultaneously, the valve device 81 is opened to an intermediate degree. As a result, compressed air from the intermediate housing 13 flows in through the connecting hole 71 in the same or less amount as when only ammonia fuel is burned, and in a greater amount than when only hydrocarbon fuel is burned. That is, the amount of compressed air supplied to the third injection hole 63 does not increase or decrease significantly. Therefore, when both ammonia fuel and hydrocarbon fuel are burned, an appropriate amount of compressed air is supplied to the third injection hole 63.

[0062] In the combustor 15 of the gas turbine 10 as described above, when ammonia fuel is used to generate combustion gases, 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 rate compared to hydrocarbon fuels, resulting in poor combustibility. Therefore, if compressed air is supplied at the same rate as when burning hydrocarbon fuels, it is difficult to achieve stable combustion, thus failing to maintain flame retention. However, as described above, the supply of compressed air is reduced when ammonia fuel is supplied to the fuel nozzle 6. As a result, when burning ammonia fuel, the occurrence of unstable combustion due to excessive compressed air supply can be suppressed. Therefore, stable combustion continues when burning ammonia fuel, thereby maintaining flame retention.

[0063] Furthermore, due to the reduced supply of compressed air, the proportion of ammonia fuel in the ratio of ammonia fuel to compressed air supply increases. As a result, as described above, flame retention is maintained during the combustion of ammonia fuel, thereby significantly reducing the amount of nitrogen remaining in the combustion gases derived from nitrogen in the ammonia fuel. Therefore, the amount of NOx generated during the combustion of ammonia fuel can be suppressed.

[0064] Furthermore, when using hydrocarbon fuels to generate combustion gases, the flow rate of compressed air used for diffusion combustion in the fuel nozzle 6 can be increased. For stable combustion, hydrocarbon fuels require more compressed air than ammonia fuels. Therefore, when hydrocarbon fuels are 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 fuels, the required amount of compressed air can be ensured to be supplied to the fuel nozzle 6. Thus, even when burning hydrocarbon fuels, stable combustion is maintained, thereby maintaining flame retention and preventing backfire.

[0065] Furthermore, due to the increased supply of compressed air, the proportion of hydrocarbon fuel in the ratio of hydrocarbon fuel to compressed air supply decreases. As a result, when burning hydrocarbon fuels, flame retention is maintained, and the generation of high-temperature regions within the cylinder 5 is suppressed, thereby significantly reducing the amount of nitrogen remaining in the combustion gases originating from nitrogen in the compressed air. Therefore, the amount of NOx generated during the combustion of hydrocarbon fuels can be suppressed.

[0066] Thus, even if the gas turbine 10, which is supplied with either ammonia or hydrocarbon fuel, is supplied with either ammonia or hydrocarbon fuel, stable combustion can be maintained and NOx production can be suppressed. Therefore, combustion based on both ammonia and hydrocarbon fuels can be effectively balanced.

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

[0068] Furthermore, compressed air is supplied to the cylinder 5 from a position remote from the fuel nozzle 6 and downstream of the combustion gas flow direction Df relative to the fuel nozzle 6 via the connecting hole 71 at a position Df2. Within the cylinder 5, a constant space is required near the front end of the fuel nozzle 6 to ensure efficient combustion of the ammonia fuel, hydrocarbon fuel, and compressed air supplied from the fuel nozzle 6. In contrast, compressed air flows into the combustion chamber 50 from the position separating from the fuel nozzle 6 downstream of Df2 via the connecting hole 71. Therefore, the compressed air flowing into the combustion chamber 50 from the connecting hole 71 does not directly participate in diffusion combustion. Thus, a simple structure can be obtained that ensures stable combustion of the ammonia fuel and hydrocarbon fuel supplied from the fuel nozzle 6 and allows for the supply of compressed air to the combustion chamber 50.

[0069] In particular, in the cylinder 5, the area from the tip of the fuel nozzle 6 to 30% is often used as space for the complete combustion of fuel supplied from the fuel nozzles 6 and 6G. That is, the connecting hole 71 in this embodiment is located beyond the area for the complete combustion of fuel supplied from the fuel nozzle 6. Therefore, it is possible to more reliably ensure the space for stable combustion of fuel supplied from the fuel nozzle 6.

[0070] Furthermore, within the cylinder 5, when a large amount of fuel is supplied from the fuel nozzle 6, oxygen becomes deficient, causing unburned residual fuel to be transported to the downstream region. At this time, the residual fuel in the downstream region within the cylinder 5 will also burn in the dilution air section within approximately 30% of the area from the rear end of the cylinder 5. Therefore, by forming a connecting hole 71 facing the area from the front end of the fuel nozzle 6 to 70%, the area within the downstream region of the cylinder 5 can be ensured to burn the residual fuel.

[0071] Furthermore, the connecting holes 71 are formed at multiple locations separated from each other relative to the cylinder 5. Therefore, the compressed air supplied to the vicinity of the center of the cylinder 5 is not significantly biased towards a portion of the inner circumferential surface of the cylinder 5 when supplied to the combustion chamber 50. In particular, the connecting holes 71 are arranged at equal intervals, thereby supplying compressed air to the combustion chamber 50 in a nearly uniform manner. Therefore, even if either ammonia fuel or hydrocarbon fuel is supplied, stable combustion can be effectively maintained in a wide area of ​​the combustion chamber 50, and NOx production can be effectively suppressed.

[0072] <Second Implementation Method>

[0073] Next, a second embodiment of the gas turbine device 1 according to the present invention will be described. Furthermore, in the second embodiment described below, structures identical to those in the first embodiment are labeled with the same symbols in the figures, and their descriptions are omitted. In the second embodiment, the structures of the intermediate supply unit 7B and the flow adjustment unit 8B differ from those in the first embodiment.

[0074] like Figures 3 to 5 As shown, the intermediate supply section 7B of the second embodiment has an annular flow path forming section 73 and a connecting flow path section 74. The annular flow path forming section 73 is disposed within the intermediate housing 13. The annular flow path forming section 73 forms an annular flow path 730 inside, through which compressed air can flow along the outer periphery of the cylinder 5. The annular flow path forming section 73 covers the entire circumference of the outer periphery of the cylinder 5. Therefore, the annular flow path forming section 73 is configured to cover a plurality of connecting holes 71. The annular flow path forming section 73 is directly fixed to the outer peripheral surface of the cylinder 5 without gaps via a welding section 75. Therefore, in this embodiment, the connecting holes 71 connect the combustion chamber 50 and the annular flow path 730. The plurality of connecting holes 71 are connected to each other outside the cylinder 5 via the annular flow path 730. The connecting flow path section 74 connects the annular flow path forming section 73 and the valve device 81B. In this embodiment, the connecting flow path section 74 is a tubular component that is bent like a bend in a pipe. The connecting flow path 74 is formed such that its flow path cross-section is smaller than that of the annular flow path 730. The connecting flow path 74 is connected to the surface of the annular flow path forming part 73 that is furthest from the cylinder 5. The opening area at the connection position between the connecting flow path 74 and the annular flow path forming part 73 may be the same as or different from the opening area of ​​the connecting hole 71.

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

[0076] (Effects)

[0077] In the aforementioned burner 15, a portion of the compressed air supplied to the intermediate housing 13 flows into the connecting flow path 74 via valve device 81B. The compressed air flowing into the connecting flow path 74 flows into the annular flow path forming section 73. At this time, the annular flow path forming section 73 acts as a damper, thereby ensuring that the compressed air present 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 multiple connecting holes 71. Thus, compressed air in the annular flow path forming section 73, which is in a nearly uniform pressure state, can be supplied to the combustion chamber 50 from the multiple connecting holes 71. Therefore, the compressed air supplied from the multiple connecting holes 71 is supplied to the combustion chamber 50 at substantially the same pressure state at any location. Therefore, even if either ammonia fuel or hydrocarbon fuel is supplied, stable combustion can be maintained more effectively in a wide area of ​​the combustion chamber 50, and NOx production can be suppressed more effectively. Furthermore, compressed air can be uniformly supplied to the combustion chamber 50 using only one valve device 81B. Therefore, by utilizing multiple valve devices, deviations in the supply state of compressed air caused by manufacturing tolerances of each valve device can be avoided.

[0078] Furthermore, the annular flow path forming portion 73 is not limited to a structure that covers the entire circumference of the cylinder 5. The annular flow path forming portion 73 may only cover a portion of the outer circumference of the cylinder 5. Also, the annular flow path 730 is not limited to having the same cross-sectional area throughout its entire circumference. The cross-sectional area of ​​the annular flow path 730 can vary locally, such as decreasing in size midway, as long as it ensures a sufficiently large area relative to the connecting hole 71.

[0079] <Modifications of the Second Embodiment>

[0080] Furthermore, in the second embodiment described above, the position where the connecting flow path portion 74 is connected to the annular flow path forming portion 73 is not limited in any way. The connecting flow path portion 74 can be connected to the surface facing the flow direction Df of the combustion gas relative to the annular flow path forming portion 73. For example, in this case... Figure 6 As shown, the connecting flow path 74C can be connected to the downstream side Df2 of the annular flow path forming part 73 in the flow direction Df toward the combustion gas.

[0081] <Third Implementation Method>

[0082] Next, a third embodiment of the gas turbine device 1 according to the present invention will be described. Furthermore, in the third embodiment described below, structures identical to those in the first and second embodiments described above are labeled with the same symbols in the figures, and their descriptions are omitted. In the third embodiment, as... Figure 7As shown, the intermediate supply section 7D has a supply pipe 76. The supply pipe 76 is disposed in the connecting hole 71. The supply pipe 76 is formed as a tubular component with the same shape as the connecting hole 71. The supply pipe 76 is formed to extend inward from the inner circumferential surface of the cylinder 5. That is, the supply pipe 76 is disposed in a state that protrudes from the inner circumferential surface of the cylinder 5 toward the interior 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 may be disposed in all the connecting holes 71, or it may be disposed in only a portion of the connecting holes 71.

[0083] (Effects)

[0084] With the supply pipe 76 configured therein, compressed air flowing into the combustion chamber 50 from the connecting hole 71 is delivered through the supply pipe 76 to the vicinity of the center of the combustion chamber 50, which is located further inward than the inner circumferential surface of the cylinder 5. This allows for a stable supply of compressed air to a depth in the combustion chamber 50, away from the connecting hole 71. Therefore, even if the flow rate of the combustion gases in the combustion chamber 50 is high, compressed air can still be supplied to the vicinity of the center of the combustion chamber 50, even in situations where the compressed air supplied from the connecting hole 71 would immediately flow downstream to Df2. Therefore, even if either ammonia fuel or hydrocarbon fuel is supplied, the generation of embers and localized high-temperature zones can be suppressed relative to the wide area of ​​the combustion chamber 50. Thus, stable combustion can be sustained more effectively in the wide area of ​​the combustion chamber 50, and NOx production can be suppressed more effectively.

[0085] <Fourth Implementation Method>

[0086] Next, a fourth embodiment of the gas turbine device 1 according to the present invention will be described. Furthermore, in the fourth embodiment described below, structures identical to those in the first to third embodiments described above are marked with the same symbols in the figures, 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 embodiments. For example, as in... Figure 8 As shown, the annular flow path forming portion 73 can be disposed relative to the outer peripheral surface of the cylinder 5 with a gap 770. Specifically, the intermediate supply portion 7E has a gap forming member 77 connecting the annular flow path forming portion 73 and the cylinder 5. The gap forming member 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 member 77 is formed as an annular member covering the connecting hole 71 on the outside of the cylinder 5. In this embodiment, the gap 770 becomes a space sealed between the gap forming member 77, the annular flow path forming portion 73, and the cylinder 5.

[0087] (Effects)

[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 high-temperature combustion gases flowing in 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 of the annular flow path forming portion 73 and the cylinder 5 can be stably maintained.

[0089] <Fifth Implementation Method>

[0090] Next, a fifth embodiment of the gas turbine device 1 according to the present invention will be described. Furthermore, in the fifth embodiment described below, structures identical to those in the first to fourth embodiments described above are marked with the same symbols in the figures, and their descriptions are omitted. In the fifth embodiment, as in the second to fourth embodiments, the intermediate supply section 7F is not limited to a structure having an annular flow path forming section 73.

[0091] like Figure 9 and Figure 10 As shown, in the fifth embodiment, the intermediate supply section 7F does not have an annular flow path forming section 73, while the connecting flow path section 74F is directly fixed to the outer peripheral surface of the cylinder 5. The connecting flow path section 74F is configured to cover the connecting hole 71. Therefore, in this embodiment, the connecting hole 71 connects the combustion chamber 50 and the connecting flow path section 74F. Multiple connecting flow path sections 74F are arranged such that one is provided for each connecting hole 71. That is, one connecting flow path section 74F is configured to close one connecting hole 71. Furthermore, each of the multiple connecting flow path sections 74F has an independent valve device 81B.

[0092] And, as Figure 11 and Figure 12 As shown, the intermediate supply section 7F has multiple sealing sections 78. The sealing sections 78 are respectively disposed between the connecting flow path section 74F and the valve device 81B, and between the connecting flow path section 74F and the cylinder 5. Like a floating ring seal, the sealing section 78 is a non-contact seal capable of use in high-temperature and high-pressure areas.

[0093] In addition, in a structure such as the second embodiment, the sealing part 78 may be disposed between the annular flow path forming part 73 and the cylinder 5, and between the annular flow path forming part 73 and the connecting flow path part 74F.

[0094] And, as Figure 12 As shown, the burner 15 has an annular sleeve portion 55 configured to surround the communicating hole 71 inside the cylinder 5. The sleeve portion 55 forms a flow path between itself and the inner circumferential surface of the cylinder 5, allowing cooling air to flow. As shown in the sleeve, a portion of the compressed air ejected from the compressor 14 is supplied to the sleeve portion 55 as cooling air.

[0095] In addition, in a structure such as the second embodiment, the sleeve portion 55 can be configured relative to the connecting hole 71 covered by the annular flow path forming portion 73.

[0096] (Effects)

[0097] As described above, each connecting hole 71 is equipped with an independent valve device 81B via a connecting flow path 74F. As a result, the valve device 81B of each connecting hole 71 can be adjusted individually or simultaneously. Therefore, even if either ammonia fuel or hydrocarbon fuel is supplied, the compressed air supply to the combustion chamber 50 can be accurately adjusted. Thus, even if uneven temperature or concentration distribution occurs within the cylinder 5 or combustion chamber 50 depending on the operating conditions, the supply can be adjusted arbitrarily, thereby easily suppressing NOx production.

[0098] Furthermore, by configuring the sealing part 78, even when high-temperature and high-pressure compressed air flows through, leakage of compressed air from the connection points of various components can be suppressed.

[0099] Furthermore, by configuring the sleeve portion 55, the periphery of the connecting hole 71 can be cooled. Therefore, thermal expansion around the connecting hole 71 caused by the high-temperature combustion gases flowing in the combustion chamber 50 can be suppressed.

[0100] <Sixth Implementation Method>

[0101] Next, according to Figure 13 and Figure 14 The sixth embodiment of the gas turbine device 1 according to the present invention will be described below. Furthermore, in the sixth embodiment described below, structures identical to those in the first to fifth embodiments described above are marked with the same symbols in the figures, and their descriptions are omitted. In the sixth embodiment, the fuel nozzle 6G and the flow adjustment unit 8G are different.

[0102] The fuel nozzle 6G of the sixth embodiment has a mixing section 65, which forms a mixing space 650 for mixing fluids injected from the first injection hole 61, the second injection hole 62, and the third injection hole 63 before being supplied 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, a constant amount of fluid, consisting of a mixture of supplied ammonia fuel, hydrocarbon fuel, and compressed air, is injected from the mixing section 65 into the combustion chamber 50. This limits the supply of ammonia fuel, hydrocarbon fuel, and compressed air to the fuel nozzle 6G until a constant amount is reached.

[0103] The flow adjustment unit 8G is not limited to the structure having valve devices 81 and 81B as described in the first to fifth embodiments. That is, the flow adjustment unit 8G of the sixth embodiment does not have valve devices 81 and 81B. The flow adjustment unit 8G of the sixth embodiment sets the supply amount of ammonia fuel, hydrocarbon fuel, and compressed air to the fuel nozzle 6G to be constant, and changes the ratio of the supply amount of ammonia fuel and hydrocarbon fuel to the supply amount of compressed air. The flow adjustment unit 8G can adjust the supply amount of at least one of ammonia fuel and hydrocarbon fuel, thereby adjusting the flow rate of 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 by the mixing unit 65. In this state, the flow adjustment unit 8G can adjust the supply amount of at least one of ammonia fuel and 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 Figure 13 As shown, the flow rate adjustment unit 8G of the sixth embodiment has a first supply quantity adjustment unit 85 and a second supply quantity adjustment unit 86.

[0104] The first supply quantity adjustment unit 85 adjusts the supply quantity of ammonia fuel to the fuel nozzle 6G. The first supply quantity adjustment unit 85 is disposed in the first supply line 22. The first supply quantity adjustment unit 85 is, for example, a flow regulating valve, an on / off valve, or a solenoid valve. By increasing the opening degree of the first supply quantity adjustment unit 85, the supply quantity of ammonia fuel from the first supply line 22 to the first injection hole 61 increases. Conversely, by decreasing the opening degree of the first supply quantity adjustment unit 85, the supply quantity of ammonia fuel from the first supply line 22 to the first injection hole 61 decreases.

[0105] The second supply quantity adjustment unit 86 adjusts the supply quantity of hydrocarbon fuel to the fuel nozzle 6G. The second supply quantity adjustment unit 86 is disposed in the second supply line 32. The second supply quantity adjustment unit 86 is, for example, a flow regulating valve, an on / off valve, or a solenoid valve. By increasing the opening degree of the second supply quantity adjustment unit 86, the supply quantity of hydrocarbon fuel from the second supply line 32 to the second injection orifice 62 increases. Conversely, by decreasing the opening degree of the second supply quantity adjustment unit 86, the supply quantity of hydrocarbon fuel from the second supply line 32 to the second injection orifice 62 decreases. Furthermore, even when the second supply quantity adjustment unit 86 is fully open, the flow rate that can flow in the second supply line 32 is less than the flow rate when the first supply quantity adjustment unit 85 is fully open. That is, when both the first supply quantity adjustment unit 85 and the second supply quantity adjustment unit 86 are fully open, the supply quantity of ammonia fuel is greater than that of hydrocarbon fuel. Specifically, based on the ratio of the calorific value of ammonia fuel to that of hydrocarbon fuel, the second supply adjustment unit 86 is preferably able to flow at a rate corresponding to the inverse ratio of the first supply adjustment unit 85. More specifically, when the calorific value and WI (Wobbe index) of the hydrocarbon fuel are about four times that of the ammonia fuel, the second supply adjustment unit 86 can only flow at a rate of about one-quarter that of the first supply adjustment unit 85.

[0106] (Effects)

[0107] like Figure 14 As shown, the flow adjustment unit 8G adjusts the supply of ammonia fuel, hydrocarbon fuel, and compressed air to the fuel nozzle 6G. Specifically, when supplying ammonia fuel and hydrocarbon fuel simultaneously, as... Figure 14 As shown in the “mixed combustion”, the first supply adjustment unit 85 and the second supply adjustment unit 86 are adjusted in such a way that the ratio of the total supply of ammonia fuel and hydrocarbon fuel to the supply of compressed air is close to a 1:1 value.

[0108] Furthermore, when only ammonia fuel is supplied, such as Figure 14 As indicated by "NH3 only," the supply of ammonia fuel is adjusted so that the supply of compressed air exceeds the supply of ammonia fuel by opening the first supply adjustment section 85 and closing the second supply adjustment section 86. As a result, compared to the "co-firing" case, a large amount of ammonia fuel is supplied to the mixing space 650 from the first injection port 61, while almost no compressed air is supplied from the third injection port 63. Furthermore, a large amount of compressed air that cannot flow into the third injection port 63 is supplied to the combustion chamber 50 through the connecting port 71. Consequently, most of the compressed air in the intermediate housing 13 flows into the combustion chamber 50 through the connecting port 71. That is, a portion of the compressed air that should be supplied to the third injection port 63 flows directly into the combustion chamber 50 through the connecting port 71.

[0109] Furthermore, when only hydrocarbon fuels are supplied, such as Figure 14 As indicated by "CH4 only", the supply of hydrocarbon fuel is adjusted so that the supply of compressed air exceeds the supply of hydrocarbon fuel by closing the first supply adjustment section 85 and opening the second supply adjustment section 86. Furthermore, the second supply adjustment section 86 is configured to allow only a very small flow rate through the first supply adjustment section 85. Therefore, compared to the "NH3 only" or "co-firing" cases, in the "CH4 only" case, 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 decreases. Consequently, the compressed air within the intermediate housing 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 to when using ammonia fuel.

[0110] Thus, by adjusting the supply of ammonia fuel and hydrocarbon fuel, the flow rate of compressed air used in fuel nozzle 6 can be adjusted. Therefore, valve devices 81 and 81B are not necessarily required. With a simpler structure or control that only changes the supply of ammonia fuel and hydrocarbon fuel, stable combustion can be maintained and NOx production can be suppressed even when either ammonia fuel or hydrocarbon fuel is supplied. Therefore, combustion based on both ammonia fuel and hydrocarbon fuel can be effectively balanced.

[0111] Furthermore, as described above, the flow adjustment unit 8G of the sixth embodiment can be applied to a structure without valve devices 81 and 81B, but it can also be applied to a structure that also has valve devices 81 and 81B.

[0112] <Seventh Implementation Method>

[0113] Next, according to Figure 15 The seventh embodiment of the gas turbine device 1 according to the present invention will be described below. Furthermore, in the seventh embodiment described below, structures identical to those in the first to sixth embodiments described above are marked with the same symbols in the figures, and their descriptions are omitted. The difference in the seventh embodiment is that the flow adjustment unit 8H adjusts the flow rate according to the operating state of the burner 15.

[0114] The gas turbine 10 of the seventh embodiment also includes a detection unit 9 for detecting the operating status of the burner 15. Specifically, the detection unit 9 of this embodiment detects the temperature in the burner 15. Furthermore, the detection unit 9 can be any device capable of detecting the operating status of the burner 15. That is, the detection unit 9 can be any device capable of monitoring the supply status of ammonia fuel, hydrocarbon fuel, and compressed air. For example, the detection unit 9 can be a device that detects at least one of the supply amount or temperature of ammonia fuel, the supply amount or temperature of hydrocarbon fuel, and the supply amount or temperature of compressed air relative to the fuel nozzle 6. Furthermore, the detection unit 9 can be a device that detects 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 unburned components, i.e., ammonia, contained in the exhaust gas. Moreover, the detection unit 9 can detect the state of various supplied fluids or the state of combustion results in the burner 15.

[0115] Furthermore, the flow adjustment unit 8H of the seventh embodiment 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 changes the opening degree of the valve device 81 based on the detection result of the detection unit 9, thereby adjusting the flow rate of compressed air supplied to the combustion chamber 50. Specifically, if the temperature of the burner 15 detected by the detection unit 9 exceeds a first threshold, the valve control device 88 sends an instruction to reduce the opening degree of the valve device 81. The first threshold is, for example, a value equivalent to the temperature at which the supply of hydrocarbon fuel changes from a state where only ammonia fuel is supplied to the fuel nozzle 6 to a state of mixed combustion of ammonia fuel and hydrocarbon fuel. Moreover, if the temperature of the burner 15 detected by the detection unit 9 exceeds a second threshold greater than the first threshold, the valve control device 88 sends an instruction to further reduce the opening degree of the valve device 81 (e.g., to a fully closed state). The second threshold is, for example, a value equivalent to the temperature at which the supply of ammonia fuel stops changing from a state of mixed combustion of ammonia fuel and hydrocarbon fuel to a state where only hydrocarbon fuel is supplied to the fuel nozzle 6.

[0116] The valve control device 88 described above is a computer. In terms of hardware, the valve control device 88 includes a CPU (Central Processing Unit) for performing various calculations, a main storage device such as memory serving as the CPU's working area, an auxiliary storage device such as a hard disk drive, an input device such as a keyboard or mouse, and a display device. Furthermore, the valve control device 88 can be integrated as part of the control device (not shown) of the gas turbine equipment 1.

[0117] (Effects)

[0118] Thus, the valve control device 88 controls the valve device 81 based on the detection results of the detection unit 9, thereby enabling the flow rate of compressed air supplied to the combustion chamber 50 through the communication hole 71 via the valve device 81 without delay, according to the operating status of the burner 15. Furthermore, when switching between the supply of ammonia fuel and hydrocarbon fuel, stable combustion can be maintained, and NOx production can be suppressed.

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

[0120] (Other implementation methods)

[0121] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the specific structure is not limited to this embodiment and may include design changes that do not depart from the spirit of the present invention.

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

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

[0124] Furthermore, the configuration of fuel nozzles 6 and 6G is not limited to the structure described above. Fuel nozzles 6 and 6G can be any type of nozzle, such as those that premix fuel and air (premixed combustion), those that rapidly mix fuel and air as in this embodiment (diffusion combustion), or those that inject fuel and air independently.

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

[0126] Furthermore, in this embodiment, the ammonia fuel supply device 20 supplies gaseous ammonia fuel to the gas turbine 10, but this method is not limited. As long as the gas turbine 10 is a structure capable of receiving liquid ammonia fuel, the ammonia fuel supply device 20 can supply liquid ammonia fuel to the gas turbine 10.

[0127] Similarly, the control of valve devices 81, 81B, the first supply quantity adjustment unit 85 and the second supply quantity adjustment unit 86 can be implemented manually by the operator or automatically by the control device of the gas turbine equipment 1.

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

[0129] <Postscript>

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

[0131] (1) The gas turbine 10 according to the first method comprises: a compressor 14 capable of compressing air to generate compressed air; a combustor 15 capable of switching between burning 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 combustor 15, the combustor 15 having: a cylindrical body 5 for the combustion gas generated by burning the ammonia fuel or the hydrocarbon fuel; fuel nozzles 6 and 6G for injecting the ammonia fuel, the hydrocarbon fuel, and the compressed air into the interior of the cylindrical body 5; and intermediate supply sections 7, 7B, 7C, 7D, 7E, and 7F, relative to... The downstream side Df2 of the combustion gas flow direction Df of the fuel nozzles 6 and 6G supplies a portion of the compressed air supplied to the fuel nozzles 6 and 6G to the cylinder 5; and the flow adjustment units 8, 8B, 8G, and 8H are capable of adjusting the flow rate of the compressed air supplied from the intermediate supply units 7, 7B, 7C, 7D, 7E, and 7F to the cylinder 5 relative to the amount of compressed air supplied to the fuel nozzles 6 and 6G. The flow 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 cylinder 5 when burning ammonia fuel, and decrease the flow rate of the compressed air supplied to the cylinder 5 when burning hydrocarbon fuel.

[0132] Therefore, when using ammonia fuel to generate combustion gases, the flow rate of compressed air used for combustion in fuel nozzle 6 can be reduced. As a result, unstable combustion caused by excessive supply of compressed air can be suppressed when burning ammonia fuel. Thus, stable combustion is sustained when burning ammonia fuel, thereby maintaining flame retention.

[0133] Furthermore, due to the reduced supply of compressed air, the proportion of ammonia fuel in the ratio of ammonia fuel to compressed air increases. As a result, the amount of nitrogen remaining in the combustion gases originating from ammonia fuel can be significantly reduced. Therefore, the amount of NOx generated during the combustion of ammonia fuel can be suppressed.

[0134] Furthermore, when using hydrocarbon fuels to generate combustion gases, the flow rate of compressed air used for combustion in fuel nozzle 6 can be increased. As a result, when burning hydrocarbon fuels, the required amount of compressed air can be ensured to be supplied to fuel nozzles 6 and 6G. Thus, stable combustion is maintained during the combustion of hydrocarbon fuels, thereby maintaining flame retention.

[0135] Furthermore, due to the increased supply of compressed air, the proportion of hydrocarbon fuel in the ratio of hydrocarbon fuel to compressed air supply decreases. As a result, the amount of nitrogen remaining in the combustion gases originating from nitrogen in the compressed air can be significantly reduced. Therefore, the amount of NOx generated during the combustion of hydrocarbon fuels can be suppressed.

[0136] Thus, even if the gas turbine 10, which is supplied with either ammonia or hydrocarbon fuel, is supplied with either ammonia or hydrocarbon fuel, stable combustion can be maintained and NOx production can be suppressed. Therefore, combustion based on both ammonia and hydrocarbon fuels can be effectively balanced.

[0137] (2) The gas turbine 10 involved in the second method is the gas turbine 10 of (1), wherein the flow adjustment units 8, 8B, 8G, 8H have valve devices 81, 81B that are capable of adjusting the flow rate of the compressed air flowing into the cylinder 5.

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

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

[0140] Therefore, the compressed air flowing into the combustion chamber 50 from the connecting hole 71 does not directly participate in combustion. Thus, a structure that ensures stable combustion of ammonia fuel and hydrocarbon fuel supplied from fuel nozzles 6, 6G and that can supply compressed air to the combustion chamber 50 can be obtained with a simple structure.

[0141] (4) The gas turbine 10 involved in the fourth method is the gas turbine 10 of (3), wherein the connecting hole 71 is formed in the cylinder 5 at multiple locations separated from each other.

[0142] Therefore, the compressed air supplied to the cylinder 5 will not be significantly biased towards a portion of the inner circumferential surface of the cylinder 5 before being supplied to the combustion chamber 50. Thus, even if either ammonia fuel or hydrocarbon fuel is supplied, stable combustion can be effectively maintained in a wide area of ​​the combustion chamber 50, and NOx production can be effectively suppressed.

[0143] (5) The gas turbine 10 involved in the fifth method is the gas turbine 10 of (3) or (4), wherein the intermediate supply parts 7B, 7C, 7D, 7E have an annular flow path forming part 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 part 73 with the cylinder 5.

[0144] Therefore, the annular flow path forming section 73 acts as a damper, thereby ensuring that the compressed air present in the annular flow path 730 is under a near-uniform pressure. Then, as the compressed air fills the annular flow path 730, it flows into the combustion chamber 50 through the connecting hole 71. Thus, compressed air under a near-uniform pressure in the annular flow path forming section 73 can be supplied to the combustion chamber 50 through the connecting hole 71. Therefore, even if either ammonia fuel or hydrocarbon fuel is supplied, stable combustion can be maintained more effectively over a wide area of ​​the combustion chamber 50, and NOx production can be suppressed more effectively.

[0145] (6) The gas turbine 10 involved in the sixth method is the gas turbine 10 of (5), wherein the annular flow path forming part 73 is arranged with a gap 770 relative to the outer peripheral surface of the cylinder 5.

[0146] Therefore, even if thermal expansion occurs in the cylinder 5 due to the influence of high-temperature combustion gases flowing in the combustion chamber 50, the amount of thermal expansion can be absorbed without affecting the annular flow path forming section 73. As a result, the fixed state between the annular flow path forming section 73 and the cylinder 5 can be stably maintained.

[0147] (7) The gas turbine 10 involved in the seventh method is any one of (3) to (6) gas turbine 10, wherein the intermediate supply parts 7D, 7E have a tubular supply pipe 76 disposed in the communication hole 71 and formed to extend from the inner circumferential surface of the cylinder 5 toward the inward side.

[0148] Therefore, the compressed air flowing into the combustion chamber 50 from the connecting hole 71 is delivered through the supply pipe 76 to a position further inside than the inner circumferential surface of the cylinder 5. Thus, compressed air can be stably supplied to a depth in the combustion chamber 50 away from the connecting hole 71.

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

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

[0151] (9) The gas turbine 10 involved in the ninth method is any one of (1) to (8) and it also has a detection unit 9 for detecting the operating status of the burner 15. The flow adjustment units 8, 8B, 8G, and 8H adjust the flow rate of the compressed air supplied to the cylinder 5 according to the detection result of the detection unit 9.

[0152] Therefore, the flow rate of compressed air supplied to the combustion chamber 50 through the flow adjustment units 8, 8B, 8G, and 8H can be adjusted without delay according to the operating status of the burner 15. Moreover, stable combustion can be maintained and NOx production can be suppressed when switching between the supply of ammonia fuel and hydrocarbon fuel.

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

[0154] Industrial availability

[0155] According to the present invention, the gas turbine and gas turbine device can ensure stable and continuous combustion and suppress NOx production in gas turbines supplied with ammonia fuel and hydrocarbon fuel.

[0156] Symbol Explanation

[0157] 1-Gas turbine equipment, 10-Gas turbine, 11-Gas turbine rotor, 12-Intake pipe, 13-Intermediate housing, 14-Compressor, 14r-Compressor rotor, 14c-Compressor housing, 14v-IGV, 15-Burner, 5-Cylinder, 50-Combustion chamber, 6, 6G-Fuel nozzles, 61-First injection hole, 62-Second injection hole, 63-Third injection hole, 7, 7B, 7C, 7D, 7E, 7F-Intermediate supply section, 71-Connecting hole, 8, 8B, 8G, 8H-Flow regulation section, 81, 81B-Valve device, Df-Flow direction, Df1-Upstream side, Df2-Downstream side, 16-Turbine, 16 r-turbine rotor, 16c-turbine housing, Ar-rotor shaft, 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 component, 770-gap, 78-sealing part, 55-casing part, 85-first supply quantity adjustment part, 86-second supply quantity adjustment part, 65-mixing part, 650-mixing space, 9-detection part, 88-valve control device.

Claims

1. A gas turbine comprising: A compressor is a device that compresses air to produce compressed air. A burner capable of switching 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 gases; and The turbine is driven by the combustion gases supplied from the burner. The burner has: A cylindrical body for the flow of combustion gases generated by the combustion of the ammonia fuel or the hydrocarbon fuel; A fuel nozzle injects the ammonia fuel, the hydrocarbon fuel, and the compressed air into the interior of the cylinder. The intermediate supply section supplies a portion of the compressed air supplied to the fuel nozzle to the cylinder on the downstream side relative to the flow direction of the combustion gas relative to the fuel nozzle; and The flow rate adjustment unit is capable of adjusting the flow rate of the compressed air supplied from the intermediate supply unit to the cylinder relative to the amount of compressed air supplied to the fuel nozzle. The flow adjustment unit increases the flow rate of compressed air supplied from the intermediate supply unit to the cylinder when burning the ammonia fuel, and decreases the flow rate of compressed air supplied to the cylinder when burning the hydrocarbon fuel.

2. The gas turbine according to claim 1, wherein, The flow adjustment section has 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 section has a communication hole connecting the interior and exterior of the cylinder at a position away from the fuel nozzle and downstream of the combustion gas flow direction relative to the fuel nozzle.

4. The gas turbine according to claim 3, wherein, The connecting holes are formed in the cylinder at multiple locations that are separated from each other.

5. The gas turbine according to claim 4, wherein, The intermediate supply section has an annular flow path forming section that forms an annular flow path through which the compressed air can flow along the outer periphery of the cylinder. The connecting hole connects the annular flow path forming part and the cylinder.

6. The gas turbine according to claim 5, wherein, The annular flow path forming section is arranged with a gap relative to the outer peripheral surface of the cylinder.

7. The gas turbine according to claim 5, wherein, The intermediate supply section has a tubular supply pipe disposed in the connecting hole and formed to extend from the inner circumferential surface of the cylinder toward the inward side.

8. The gas turbine according to claim 1, wherein, The flow adjustment unit, while keeping the supply amounts of ammonia fuel, hydrocarbon fuel, and compressed air to the fuel nozzle constant, 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 is greater than the supply amount of hydrocarbon fuel when supplying hydrocarbon fuel to the fuel nozzle.

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

10. A gas turbine device comprising: The gas turbine as described in claim 1 or 2; An ammonia fuel supply system capable of supplying the ammonia fuel to the gas turbine; and A hydrocarbon fuel supply device capable of supplying the hydrocarbon fuel to the gas turbine.

Images