GAS TURBINE AND GAS TURBINE PLANT

Abstract

A gas turbine includes a combustor in which a fuel to be burned is switchable between an ammonia fuel and a hydrocarbon-based fuel. The combustor includes a cylindrical body having a cylindrical shape through which a combustion gas flows, a fuel nozzle that ejects the ammonia fuel, the hydrocarbon-based fuel, and compressed air into the cylindrical body, an intermediate supply section that supplies a portion of the compressed air to the cylindrical body, and a flow rate control section configured to control a flow rate of the compressed air supplied to the cylindrical body.The flow rate control section increases the flow rate of the compressed air supplied to the cylindrical body when the ammonia fuel is burned and decreases the flow rate of the compressed air supplied to the cylindrical body when the hydrocarbon-based fuel is burned.

Description

Technical FieldThe present disclosure relates to a gas turbine and gas turbine equipment.This application claims priority to Japanese Patent Application No. 2022-133982 filed in Japan on Aug. 25, 2022, the contents of which are incorporated herein by reference.Prior ArtA gas turbine includes a compressor that compresses air, a combustor that burns fuel in the air compressed by the compressor to generate a combustion gas, and a turbine that is driven by the combustion gas. As the fuel supplied to the combustor, a hydrocarbon-based fuel, which is a fossil fuel such as natural gas or petroleum, is generally used, but ammonia may also be used.For example, PTL 1 discloses a gas turbine that supplies ammonia as a main fuel and increases a ratio of a fossil fuel in the fuel supplied to the gas turbine in a combustion property deterioration operating region in which the combustion property of the ammonia is deteriorated, as compared with a case of a normal operation.Citation ListPatent Literature[PTL 1] Japanese Unexamined Patent Application Publication No. 2010-19195SUMMARY OF THE INVENTIONTechnical ProblemThe ammonia fuel has a small heating value and a small combustion rate. That is, the ammonia fuel has a poorer combustion property than the hydrocarbon-based fuel. Therefore, in a gas turbine that can supply the ammonia fuel and the hydrocarbon-based fuel simultaneously, it is difficult to maintain stable combustion in a case where any one of the ammonia fuel and the hydrocarbon-based fuel is supplied.Further, in a case where ammonia is used as the fuel for the gas turbine, NOx is generated by a part of nitrogen that forms ammonia during combustion. Therefore, a generation amount of NOx increases when a supply amount of the ammonia fuel supplied to the combustion chamber becomes smaller than a supply amount of the compressed air, and the combustion is not effectively performed. On the other hand, when the hydrocarbon-based fuel is burned, NOx derived from nitrogen in the compressed air is generated. Therefore, a combustion temperature becomes higher, and the generation amount of NOx becomes larger as the supply amount of the fuel or the air becomes closer to the stoichiometric amount, such as in a case where the supply amount of the hydrocarbon-based fuel to the combustor and the supply amount of the compressed air are close to each other. That is, in a case where the compressed air supply amount is set to the same condition in a case where the ammonia fuel is supplied and a case where the hydrocarbon-based fuel is supplied, it is difficult to suppress the generation amount of NOx.The present disclosure provides a gas turbine and a gas turbine equipment that can suppress a generation amount of NOx while continuing stable combustion with respect to a gas turbine to which both an ammonia fuel and a hydrocarbon-based fuel are supplied.Solution to the ProblemAn aspect of the present disclosure provides a gas turbine including: a compressor configured to compress air to generate compressed air; a combustor in which a fuel to be burned is switchable between an ammonia fuel and a hydrocarbon-based fuel, the combustor configured to burn at least one of the ammonia fuel and the hydrocarbon-based fuel in the compressed air supplied from the compressor to generate a combustion gas; and a turbine drivable by the combustion gas supplied from the combustor, the combustor including a cylindrical body having a cylindrical shape and through which the combustion gas generated by combustion of the ammonia fuel or the hydrocarbon-based fuel flows, a fuel nozzle that generates the ammonia fuel, the hydrocarbon-based fuel and discharges the compressed air into the cylindrical body, an intermediate supply portion supplying a part of the compressed air supplied to the fuel nozzle to the cylindrical body on a downstream side of the fuel nozzle in a flow direction of the combustion gas, and a flow rate control portion configured to control a flow rate of the compressed air supplied from the intermediate supply portion to the cylindrical body with respect to a supply amount of the compressed air supplied to the fuel nozzle, and the flow rate control portion increases the flow rate of the compressed air supplied from the intermediate supply portion to the cylindrical body when the ammonia fuel is burned and decreases the flow rate of the compressed air supplied to the cylindrical body when the hydrocarbon-based fuel is burned.Another aspect of the present disclosure provides gas turbine equipment including: the above-described gas turbine; ammonia fuel supply equipment configured to supply the ammonia fuel to the gas turbine; and hydrocarbon-based fuel supply equipment configured to supply the hydrocarbon-based fuel to the gas turbine.Advantageous Effects of the InventionWith the gas turbine and the gas turbine equipment according to the present disclosure, it is possible to suppress the generation amount of NOx while continuing stable combustion in the gas turbine to which the ammonia fuel and the hydrocarbon-based fuel are supplied.Brief Description of the DrawingsFIG. 1 is a schematic configuration diagram of gas turbine equipment according to a first embodiment of embodiments of the present disclosure. FIG. 2 is a schematic sectional view of a combustor according to the first embodiment of the present disclosure. FIG. 3 is a schematic sectional view of a combustor according to a second embodiment of the present disclosure. FIG. 4 is a cross-sectional view taken along line A-A of FIG. 3. FIG. 5 is an enlarged view of a main part of the combustor of FIG. 3. FIG. 6 is an enlarged view of a main part of a combustion chamber of a modification example of the second embodiment corresponding to FIG. 5. FIG. 7 is an enlarged view of a main part of a combustion chamber according to a third embodiment corresponding to FIG. 5. FIG. 8 is an enlarged view of a main part of a combustion chamber according to a fourth embodiment corresponding to FIG. 5. FIG. 9 is a schematic sectional view of a combustor according to a fifth embodiment of the present disclosure. FIG. 10 is a cross-sectional view taken along line B-B of FIG. 8. FIG. 11 is a first enlarged view of the main part of the combustor of FIG. 8. FIG. 12 is a second enlarged view of the main part of the combustor of FIG. 8. FIG. 13 is a schematic sectional view of a combustor according to a sixth embodiment of the present disclosure. FIG. 14 is a diagram showing a relationship between supply amounts of an ammonia fuel and a hydrocarbon-based fuel and compressed air according to the sixth embodiment of the present disclosure. FIG. 15 is a schematic sectional view of a combustor according to a seventh embodiment of the present disclosure.DESCRIPTION OF EMBODIMENTSHereinafter, embodiments for implementing a gas turbine 10 and gas turbine equipment 1 according to the present disclosure will be described with reference to the accompanying drawings. However, the present disclosure is not limited to only these embodiments.< Embodiment>(Configuration of Gas Turbine Equipment)The gas turbine equipment 1 according to the present embodiment includes, as shown in FIG. 1, the gas turbine 10, an ammonia fuel supply equipment 20, and a hydrocarbon-based fuel supply equipment 30.(Configuration of Gas Turbine)In the gas turbine 10, a fuel to be burned is switchable between an ammonia fuel and a hydrocarbon-based fuel. The gas turbine 10 may be driven by a combustion gas generated by burning at least one of the ammonia fuel and the hydrocarbon-based fuel. The gas turbine 10 according to the present embodiment includes a compressor 14, a combustor 15, a turbine 16, an air intake passage 12, and an intermediate casing 13.The compressor 14 may compress air to generate compressed air. The compressor 14 includes a compressor rotor 14 rthat rotates about a rotor axis line Ar, a compressor housing 14 cthat covers the compressor rotor 14 r, and an inlet guide vane (IGV) 14 vprovided in a suction port of the compressor housing 14 c. The IGV 14 vcontrols an air intake amount that is a flow rate of air sucked into the compressor housing 14 c. The air suction passage 12 is connected to the suction port of the compressor housing 14c.The turbine 16 can be driven by high-temperature and high-pressure combustion gas supplied from the combustor 15. The turbine 16 includes a turbine rotor 16 rthat rotates around the rotor axis line Ar by using the combustion gas from the combustor 15, and a turbine housing 16 ccovering the turbine rotor 16 r. The turbine rotor 16 rand the compressor rotor 14 rare connected to each other so as to be rotatable about the same rotor axis line Ar, and constitute a gas turbine rotor 11.The intermediate housing 13 is disposed between the compressor housing 14 cand the turbine housing 16 cin a direction in which the rotor axis line Ar extends, and connects the compressor housing 14 cand the turbine housing 16 c. The compressed air discharged from the compressor 14 flows into the intermediate housing 13.The combustor 15 may combust at least one of the ammonia fuel and the hydrocarbon-based fuel in the compressed air supplied from the compressor 14 to generate the combustion gas. The hydrocarbon-based fuel is a fuel containing a hydrocarbon, and is, for example, a fossil fuel such as natural gas or petroleum. The ammonia fuel and the hydrocarbon-based fuel may be supplied to the combustor 15. The combustor 15 is operable by controlling the supply amounts of the ammonia fuel and the hydrocarbon-based fuel, which are the fuels, depending on an operation situation under an operation condition in which only the ammonia fuel is burned, an operation condition in which only the hydrocarbon-based fuel is burned, and an operation condition in which both the ammonia fuel and the hydrocarbon-based fuel are burned. In the operating condition where both the ammonia fuel and the hydrocarbon-based fuel are burned, the supply amount of the ammonia fuel and the supply amount of the hydrocarbon-based fuel may be equal to or different from each other. The combustion chamber 15 is fixed to the intermediate casing 13. As shown in FIG. 2, the combustor 15 according to the present embodiment includes a cylindrical body 5, a fuel nozzle 6, an intermediate supply portion 7, and a flow rate control portion 8.The cylindrical body 5 forms therein a combustion chamber 50. the combustion chamber 50 is a space inside the cylindrical body 5. that is, the combustion gas generated by the combustion of at least one of the ammonia fuel and the hydrocarbon-based fuel flows inside the cylindrical body 5. the cylindrical body 5 is disposed in the intermediate housing 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-based 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-based fuel flows through the combustion chamber 50 and is supplied to the turbine 16. The cylindrical body 5 is formed in a cylindrical shape around a central axis line of the combustion chamber 15. A structure of the cylindrical body 5 is not limited to a structure formed of only one member. The cylindrical body 5 may have a structure in which a plurality of members are arranged in a direction in which the central axis line extends.The fuel nozzle 6 discharges the ammonia fuel, the hydrocarbon-based fuel, and the compressed air into the combustion chamber 50. The fuel nozzle 6 is fixed to an end portion (upstream end, first end portion) of the cylindrical body 5 disposed at a position separated from the turbine 16. The fuel nozzle 6 discharges the ammonia fuel, the hydrocarbon-based fuel, and the compressed air into the combustion chamber 50 toward the turbine 16. The fuel nozzle 6 generates the combustion gas by performing diffusion combustion under three conditions of the ammonia fuel and the compressed air, the hydrocarbon-based fuel and the compressed air, and the ammonia fuel, the hydrocarbon-based fuel, and the compressed air. A fuel nozzle 6 is disposed inside the cylindrical body 5. The fuel nozzle 6 includes at least one (two in the present embodiment) first ejection hole 61 for ejecting the ammonia fuel, at least one (one in the present embodiment) second ejection hole 62 for ejecting the hydrocarbon-based fuel, and at least one (two in the present embodiment) third ejection hole 63 for ejecting the compressed air.The first ejection hole 61, the second ejection hole 62, and the third ejection hole 63 are formed on the fuel nozzle 6 so as to be independent from each other and separated from each other. The first ejection hole 61, the second ejection hole 62, and the third ejection hole 63 according to the first embodiment are formed so that the respective liquids are mixed until ejected into the combustion chamber 50. The first discharge hole 61 discharges the ammonia fuel introduced from the outside of the combustion chamber 15 into the combustion chamber 50. The first ejection hole 61 is located at the center in a radial direction of the fuel nozzle 6. The second discharge hole 62 discharges the hydrocarbon-based fuel introduced from the outside of the combustion chamber 15 into the combustion chamber 50. The third ejection hole 63 ejects the compressed air introduced from inside into the intermediate housings 13 into the combustion chamber 50. The third ejection hole 63 is disposed between the first ejection hole 61 and the second ejection hole 62 in the radial direction of the fuel nozzle 6.The first ejection hole 61, the second ejection hole 62, and the third ejection hole 63 are not limited to the structure in which the first ejection hole 61, the second ejection hole 62, and the third ejection hole 63 are disposed inside a fuel nozzle 6. The first ejection hole 61, the second ejection hole 62, and the third ejection hole 63 may have a structure in which the first ejection hole 61, the second ejection hole 62, and the third ejection hole 63 are formed in independent nozzles, respectively. That is, the fuel nozzle 6 may be configured of a plurality of nozzles. The fuel nozzle 6 may further have other structures, such as a swirl damper.A part of the compressed air supplied to the fuel nozzle 6 is supplied from a location other than the fuel nozzle 6 to the cylindrical body 5 through the intermediate supply portion 7. The intermediate supply portion 7 is located in the intermediate housing 13. Here, the flow direction Df of the combustion gas is a direction from one end portion of the cylindrical body 5 at which the fuel nozzle 6 is disposed to the other end portion (downstream end, second end portion) connected to the turbine 16. Therefore, an upstream side Df 1 in the flow direction Df of the combustion gas is a side in the cylindrical body 5 on which the fuel nozzle 6 is disposed with respect to the turbine 16. Moreover, the downstream side Df 2 in the flow direction Df of the combustion gas is a side in the cylindrical body 5 on which the turbine 16 is disposed with respect to the fuel nozzle 6. The intermediate supply portion 7 according to the present embodiment includes a communication hole 71.The communication hole 71 is formed such that the combustion chamber 50 located inside the cylindrical body 5 and the outside of the cylindrical body 5 communicate with each other at a position separated from the fuel nozzle 6. That is, the communication hole 71 according to the present embodiment connects the combustion chamber 50 and a space at the intermediate housing 13 without passing through the fuel nozzle 6. The communication hole 71 is formed at a position on the downstream side Df 2 of the fuel nozzle 6 in the flow direction Df of the combustion gas. The communication hole 71 is formed at a position that does not directly contribute to the diffusion combustion with respect to the combustion chamber 50 to supply the compressed air. The communication hole 71 is formed in the vicinity of the center of the cylindrical body 5 in the flow direction Df. The communication holes 71 are formed at a plurality of positions (for example, four positions) separated from each other along an outer circumferential surface of the cylindrical body 5 in a circumferential direction of the cylindrical body 5. A plurality of communication holes 71 are arranged at equal intervals from each other. The communication hole 71 is formed in the center of the flow passage of the introduced compressed air introduced into the third ejection hole 63 in the intermediate housing 13. More specifically, in a case where a length of a straight line connecting a distal end of the fuel nozzle 6 to a position connected to the turbine 16 is set as an overall length (100%) of the cylindrical body 5, it is preferable that the communication hole 71 is disposed between a position of 30% and a position of 70% from the distal end of the fuel nozzle 6.Moreover, the communication holes 71 are not limited to the structure in which the plurality of communication holes 71 are formed as in the present embodiment. Only one communication hole 71 may be provided. Further, the plurality of communication holes 71 are not necessarily configured to be arranged at equal intervals, and may be arranged at different intervals from each other.The flow rate control section 8 can control the flow rate of the compressed air supplied from the intermediate supply section 7 to the cylindrical body 5 with respect to the supply amount of the compressed air supplied to the fuel nozzle 6. That is, the flow rate control section 8 may control a ratio between the supply amount of the compressed air indirectly supplied to the combustion chamber 50 together with the fuel via the third ejection hole 63 and the flow rate of the compressed air directly supplied from the intermediate supply section 7 to the combustion chamber 50. The flow rate control section 8 controls the flow rate of the compressed air supplied from the intermediate supply section 7 to the combustion chamber 50 in accordance with the supply amounts of the ammonia fuel and the hydrocarbon-based fuel supplied to the fuel nozzle 6. Specifically, the flow rate control section 8 increases the flow rate of the compressed air supplied to the cylindrical body 5 when the ammonia fuel is burned. On the other hand, the flow rate control section 8 decreases the flow rate of the compressed air supplied to the cylindrical body 5 when the hydrocarbon-based fuel is burned. Further, the flow rate control section 8 according to the present embodiment includes a valve device 81.The valve device 81 can regulate the flow rate of the compressed air flowing from the outside of the cylindrical body 5 to the combustion chamber 50 located inside the cylindrical body 5. The valve device 81 is, for example, a flow rate control valve, an on-off valve, or an electromagnetic valve. The valve device 81 is disposed to block the communication hole 71. The valve device 81 controls the flow rate of the compressed air flowing through the communication hole 71. Specifically, an opening degree of the valve device 81 is increased with an increase in the supply amount of the ammonia fuel to the first discharge hole 61 (for example, may be in a fully open state). On the other hand, as the supply amount of the hydrocarbon-based fuel to the second discharge hole 62 increases, the opening degree of the valve device 81 is decreased (for example, it may be in a fully closed state). Moreover, in a case where the ammonia fuel and the hydrocarbon-based fuel are supplied simultaneously, the valve device 81 controls the opening degree in accordance with the amount of NOx, and the opening degree is equal to or an intermediate value of the opening degree in a case where only the ammonia fuel is supplied. That is, in a case of simultaneous supply, the valve device 81 has an opening degree that is equal to or less than the opening degree in a case where only the ammonia fuel is supplied to the fuel nozzle 6, and has an opening degree that is greater than the opening degree in a case where only the hydrocarbon-based fuel is supplied to the fuel nozzle 6. A plurality of valve devices 81 according to the present embodiment are arranged such that one valve device 81 is arranged with respect to a communication hole 71. That is, a valve device 81 is disposed so as to be able to block only one communication hole 71.(Configuration of Ammonia Fuel Supply Equipment)As shown in FIG. 1, the ammonia fuel supply equipment 20 may supply the ammonia fuel to the gas turbine 10. The ammonia fuel supply equipment 20 according to the present embodiment includes a first storage tank 21 and a first supply line 22.The first storage tank 21 stores the ammonia fuel in a liquid state. The first supply pipe 22 connects the first storage tank 21 and the fuel nozzle 6, and the first supply pipe 22 heats and vaporizes the ammonia fuel in a liquid state to supply the vaporized ammonia fuel to the first discharge hole 61. The first supply line 22 can control the amount of the ammonia fuel supplied to the first discharge hole 61. The first supply line 22 includes a heat exchanger (not shown) for vaporizing ammonia in a liquid state, a pump (not shown) for increasing the pressure, a valve (not shown) for controlling the supply amount, and the like.(Configuration of Hydrocarbon-Based Fuel Supply Equipment)The hydrocarbon-based fuel supply equipment 30 may supply the hydrocarbon-based fuel to the gas turbine 10. The hydrocarbon-based fuel supply equipment 30 according to the present embodiment includes a second storage tank 31 and a second supply line 32.The hydrocarbon-based fuel is stored in the second storage tank 31. The second supply line 32 connects the second storage tank 31 and the fuel nozzle 6. the second supply line 32 heats and vaporizes the hydrocarbon-based fuel to supply the vaporized hydrocarbon-based fuel to the second discharge hole 62 in a case where the hydrocarbon-based fuel is in a liquid state. The amount of the hydrocarbon-based fuel supplied to the second discharge hole 62 can be controlled in the second supply line 32. In this case, the second supply line 32 includes a heat exchanger (not shown) for vaporizing the hydrocarbon-based fuel in a liquid state, a pump (not shown) for increasing the pressure, a valve (not shown) for regulating the supply amount, and the like. In a case where the hydrocarbon-based fuel is stored in the second storage tank 31 in a gaseous state, the hydrocarbon-based fuel is supplied to the second discharge hole 62 as it is or is increased in pressure. In this case, the second supply line 32 includes a pump (not shown) for increasing the pressure of the hydrocarbon-based gaseous fuel, a valve (not shown) for regulating the supply amount, and the like.(Operations and Effects)As described above, in the gas turbine equipment 1 having the configuration described above, there may be a case where only the ammonia fuel is supplied to the gas turbine 10, a case where only the hydrocarbon-based fuel is supplied, and a case where the ammonia fuel and the hydrocarbon fuel are simultaneously supplied.First, in a case where only the ammonia fuel is supplied, the ammonia fuel is supplied from the first storage tank 21 to the fuel nozzle 6 through the first supply line 22. The ammonia fuel supplied to the fuel nozzle 6 is discharged into the combustion chamber 50 through the first discharge hole 61. In this case, the compressed air supplied to the fuel nozzle 6 via the intermediate housing 13 is discharged from the third discharge hole 63 into the combustion chamber 50. The hydrocarbon-based fuel is not discharged from the second discharge hole 62. As a result, diffusion combustion of only the ammonia fuel and the compressed air is performed in the combustion chamber 50. Here, the combustion is not limited to the diffusion combustion, and may be combustion suitable for a shape of the fuel nozzle 6. Therefore, the combustion form may be a combustion form close to the premixed combustion instead of the diffusion combustion. At the same time, the valve device 81 is in a state of being widely opened. As a result, most of the compressed air in the intermediate housing 13 flows from the communication hole 71 into the combustion chamber 50. that is, part of the compressed air to be supplied to the third ejection hole 63 directly flows from the communication hole 71 into the combustion chamber 50. therefore, in a case where only the ammonia fuel is supplied to the fuel nozzle 6, the flow rate of the compressed air supplied to the third ejection hole 63 can be reduced.Moreover, in a case where only the hydrocarbon-based fuel is supplied, the hydrocarbon-based fuel is supplied from the second storage tank 31 to the fuel nozzle 6 through the second supply line 32. The hydrocarbon-based fuel supplied to the fuel nozzle 6 is discharged into the combustion chamber 50 through the second discharge hole 62. In this case, the compressed air is discharged from the third discharge hole 63 into the combustion chamber 50. Further, the ammonia fuel is not discharged from the first discharge hole 61. As a result, in the combustion chamber 50, only the hydrocarbon-based fuel and the compressed air are burned. At the same time, the valve device 81 is in a state of being slightly opened (or closed). As a result, the compressed air in the intermediate housing 13 hardly flows into the combustion chamber 50 from the communication hole 71. that is, the compressed air to be supplied to the third discharge hole 63 flows into the combustion chamber 50 from the third discharge hole 63 without being substantially reduced. In this way, in a case where only the hydrocarbon-based fuel is supplied to the fuel nozzle 6, the flow rate of the compressed air supplied to the third ejection hole 63 can be increased.Further, in a case where both the ammonia fuel and the hydrocarbon-based fuel are supplied, the ammonia fuel is supplied from the first storage tank 21 to the fuel nozzle 6 through the first supply line 22. At the same time, the hydrocarbon-based fuel is supplied from the second storage tank 31 to the fuel nozzle 6 through the second supply line 32. Therefore, the ammonia fuel is discharged into the combustion chamber 50 through the first discharge hole 61, and the hydrocarbon-based fuel is discharged into the combustion chamber 50 through the second discharge hole 62. In this case, the compressed air is discharged from the third discharge hole 63 into the combustion chamber 50. As a result, the three types of the ammonia fuel, the hydrocarbon-based fuel, and the compressed air are burned in the combustion chamber 50. At the same time, the valve device 81 has an average opening degree. As a result, the amount of the compressed air in the intermediate housing 13 flowing in from the communication holes 71 is equal to or less than the amount thereof in a case where only the ammonia fuel is burned, and is greater than the amount thereof in a case where only the hydrocarbon-based fuel is burned. That is, the supply amount of the compressed air supplied to the third ejection hole 63 is not significantly increased or significantly decreased. Therefore, an appropriate amount of the compressed air is supplied to the third discharge hole 63 in a case where both the ammonia fuel and the hydrocarbon-based fuel are burned.In the combustor 15 of the gas turbine 10 described above, in a case where the combustion gas is generated by using the ammonia fuel, the flow rate of the compressed air used for diffusion combustion in the fuel nozzle 6 can be reduced. It is known that the ammonia fuel has poor combustion property because the ammonia fuel has a lower heating value and a lower combustion rate than the hydrocarbon-based fuel. Therefore, in a case where the compressed air is supplied in the supply amount equal to or larger than the supply amount, when the hydrocarbon-based fuel is burned, it is difficult to burn (stably burn) the hydrocarbon-based fuel in a stable state, and the flame holding property cannot be maintained. However, as described above, the supply amount of the compressed air is reduced when the ammonia fuel is supplied to the fuel nozzle 6. As a result, in a case where the ammonia fuel is burned, it is possible to suppress the occurrence of unstable combustion due to excessive supply of the compressed air. Accordingly, in a case where the ammonia fuel is burned, stable combustion can be continued, and the flame holding property can be maintained.In a case where the supply amount of the compressed air is reduced, the ratio of the ammonia fuel is increased in the ratio between the supply amounts of the ammonia fuel and the compressed air. As a result, as described above, the flame holding property is maintained when the ammonia fuel is burned, and the amount of the nitrogen component remaining in the combustion gas derived from the nitrogen in the ammonia fuel can be significantly reduced. Therefore, the generation amount of NOx when the ammonia fuel is burned can be suppressed.Further, when the hydrocarbon-based fuel is used to generate the combustion gas, the flow rate of the compressed air used for diffusion combustion through the fuel nozzle 6 can be increased. A larger amount of the compressed air is required for the hydrocarbon-based fuel than for the ammonia fuel in order to stably combust the hydrocarbon-based fuel. On the other hand, when the hydrocarbon-based fuel is supplied to the fuel nozzle 6, the supply amount of the compressed air to the fuel nozzle 6 is increased compared to when the ammonia fuel is supplied to the fuel nozzle 6. As a result, it is possible to secure a required amount of the compressed air to be supplied to the fuel nozzle 6 when the hydrocarbon-based fuel is burned. Accordingly, even when the hydrocarbon-based fuel is burned, the stable combustion is continued, and thus the flame holding property can be maintained without causing a restriking or the like.In a case where the supply amount of the compressed air is increased, the proportion of the hydrocarbon-based fuel is decreased in the ratio between the supply amounts of the hydrocarbon-based fuel and the compressed air. As a result, when the hydrocarbon-based fuel is burned, the flame holding property is maintained, the generation of a high temperature region in the cylindrical body 5 is suppressed, and the amount of the nitrogen component remaining in the combustion gas derived from nitrogen in the compressed air can be significantly reduced. Therefore, the generation amount of NOx when the hydrocarbon-based fuel is burned can be suppressed.In this way, in the gas turbine 10 to which the ammonia fuel and the hydrocarbon-based fuel are supplied, the generation amount of NOx can be suppressed while stable combustion is continued regardless of whether the ammonia fuel or the hydrocarbon-based fuel is supplied. Therefore, it is possible to effectively achieve both the combustion with the ammonia fuel and the combustion with the hydrocarbon-based fuel.Further, in the flow rate control section 8, the flow rate of the compressed air flowing into the cylindrical body 5 is controlled by the valve device 81. Therefore, the supply amount of the compressed air can be controlled by a simple configuration in a case where the ammonia fuel is supplied and in a case where the hydrocarbon-based fuel is supplied.Moreover, the compressed air is supplied to the cylindrical body 5 through the communication hole 71 from a position separated from the fuel nozzle 6 and located on the downstream side Df 2 of the fuel nozzle 6 in the flow direction Df of the combustion gas. In the cylindrical body 5, a certain amount of space is required in the vicinity of the distal end of the fuel nozzle 6 to efficiently combust the ammonia fuel, the hydrocarbon-based fuel, and the compressed air supplied from the fuel nozzle 6. However, the compressed air flows from a position separated from the fuel nozzle 6 to the downstream side Df 2 through the communication hole 71 into the combustion chamber 50. therefore, the compressed air that has flowed from the communication hole 71 into the combustion chamber 50 does not directly participate in the diffusion combustion. Therefore, a structure in which the compressed air can be supplied to the combustion chamber 50 while securing a space for stably burning the ammonia fuel and the hydrocarbon-based fuel supplied from the fuel nozzle 6 can be obtained by a simple configuration.In particular, in the cylindrical body 5, a portion from the distal end of the fuel nozzle 6 to 30% is often a space required for burning the fuel supplied from the fuel nozzle 6 or 6G. That is, the communication hole 71 according to the present embodiment is disposed at a position beyond the range where the fuel supplied from the fuel nozzle 6 is completely burned. Therefore, a space for stably burning the fuel supplied from the fuel nozzle 6 can be more reliably secured.Further, in the cylindrical body 5, in a case where a large amount of fuel is supplied from the fuel nozzle 6, oxygen deficiency occurs, and surplus fuel that cannot be completely burned is supplied to a downstream region. In this case, the surplus fuel is burned in a diluted air portion in a range of about 30% from a rear end of the cylindrical body 5 in the downstream region in the cylindrical body 5. As a result, by forming the communication hole 71 to face 70% from the distal end of the fuel nozzle 6, a region where the surplus fuel is burned can be secured to the cylindrical body 5 in the downstream region.Moreover, the communication holes 71 are formed at a plurality of positions separated from each other with respect to the cylindrical body 5. Therefore, the compressed air supplied to the portion of the center of the cylindrical body 5 is supplied to the combustion chamber 50 without being largely biased toward the portion of an inner circumferential surface of a part of the cylindrical body 5. Specifically, since the communication holes 71 are arranged at equal intervals, the compressed air is supplied to the combustion chamber 50 in a nearly uniform pressure state. Therefore, the generation amount of NOx can be suppressed effectively while continuing stable combustion with high efficiency in a wide range of the combustion chamber 50 regardless of whether the ammonia fuel or the hydrocarbon-based fuel is supplied.< Embodiment>Next, a second embodiment of the gas turbine equipment 1 according to the present disclosure will be described. In the following second embodiment, the configurations common to the configurations of the first embodiment are denoted by the same reference numerals in the drawings, and description thereof is omitted. In the second embodiment, the configurations of an intermediate supply portion 7B and a flow rate control portion 8B are different from the configurations in the first embodiment.As shown in FIGS. 3 to 5, the intermediate supply portion 7B according to the second embodiment includes an annular flow passage forming portion 73 and a communication flow passage portion 74. The annular flow passage forming portion 73 forms an annular flow passage 730 through which the compressed air can flow along an outer periphery of the cylindrical body 5. The annular flow passage forming portion 73 covers the outer periphery of the cylindrical body 5 over the entire periphery. Therefore, the annular flow passage forming portion 73 is disposed to cover the plurality of communication holes 71. The annular flow passage forming portion 73 is directly fixed to the outer circumferential surface of the cylindrical body 5 without a gap by a welding portion 75. Therefore, the communication hole 71 according to the present embodiment connects the combustion chamber 50 and the annular flow passage 730. The plurality of communication holes 71 are communicated with each other outside the cylindrical body 5 through the annular flow passage 730. The communication flow passage portion 74 connects the annular flow passage forming portion 73 and a valve device 81B. The communication flow passage portion 74 according to the present embodiment is a curved tubular member such as an angle. The communication flow passage portion 74 is formed such that a flow passage cross section thereof is smaller than a flow passage cross section of the annular flow passage 730. The communication flow passage portion 74 is connected to a surface of the annular flow passage forming portion 73 that is the farthest from the cylindrical body 5. For example, an opening area at a connection position between the connection flow passage portion 74 and the annular flow passage forming portion 73 may be equal to or different from an opening area of the communication hole 71.In the flow rate control portion 8B according to the second embodiment, the valve device 81B is connected to the communication flow passage portion 74. The valve device 81B is, for example, a flow rate control valve, an on / off valve, or an electromagnetic valve. That is, the valve device 81B controls the flow rate of the compressed air supplied to the combustion chamber 50 from the annular flow passage 730 and the communication hole 71 by controlling the flow rate of the compressed air flowing into the communication flow passage portion 74. Only one valve device 81B is disposed with respect to the communication flow passage portion 74. That is, in the second embodiment, only one valve device 81B is disposed with respect to the plurality of communication holes 71.(Operations and Effects)In the above-described combustor 15, a part of the compressed air supplied to the intermediate housing 13 flows into the communication flow passage portion 74 through the valve device 81B. The compressed air that has flowed into the communication flow passage portion 74 flows into the annular flow passage forming portion 73. in this case, the annular flow passage forming portion 73 plays a role of a damper, and thus the compressed air present in the annular flow passage 730 is in a nearly uniform pressure state. Thereafter, the compressed air flows from the plurality of communication holes 71 into the combustion chamber 50 while filling the annular flow passage 730. Accordingly, the compressed air set to have a nearly uniform pressure state in the annular flow passage 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 in substantially the same pressure state at an arbitrary position of the combustion chamber 50. Therefore, the generation amount of NOx can be further effectively suppressed while stable combustion is more efficiently continued in a wide range of the combustion chamber 50 regardless of whether the ammonia fuel or the hydrocarbon-based fuel is supplied. The compressed air can be uniformly supplied to the combustion chamber 50 by using only one valve device 81B. Therefore, in a case where a plurality of valve devices are used, it is possible to avoid occurrence of variations in the compressed air supply state due to manufacturing tolerances or the like for each valve device.The annular flow passage forming portion 73 is not limited to the structure in which the outer periphery is covered by the cylindrical body 5 over the entire periphery. The annular flow passage forming portion 73 may have a structure that covers only a part of the outer periphery of the cylindrical body 5. Moreover, a cross-sectional area of the annular flow channel 730 is not necessarily the same over the entire circumference. The cross-sectional area of the annular flow channel 730 may partially change, such as a decrease in the center, as long as a sufficiently large area can be secured with respect to the communication hole 71.< Example of Second Embodiment>In the second embodiment, the position at which the communication flow passage portion 74 is connected to the annular flow passage forming portion 73 is not limited. The communication flow passage portion 74 may be connected to a surface of the annular flow passage forming portion 73 facing the flow direction Df of the combustion gas. In this case, for example, as shown in FIG. 6, a communication flow passage portion 74C may be connected to a surface of the annular flow passage forming portion 73 facing the downstream side Df 2 in the flow direction Df of the combustion gas.< Embodiment>Next, a third embodiment of the gas turbine equipment 1 according to the present disclosure will be described. In the following third embodiment, the configurations common to the configurations of the first and second embodiments are denoted by the same reference numerals in the drawings, and description thereof is omitted. In the third embodiment, as shown in FIG. 7, an intermediate supply portion 7D includes a supply pipe 76. the supply pipe 76 is disposed in the communication hole 71. The supply pipe 76 is formed as a tubular member having the same shape as the communication hole 71. The supply pipe 76 is formed to extend inward from the inner circumferential surface of the cylindrical body 5. That is, the supply pipe 76 is disposed in a state of protruding from the inner circumferential surface of the cylindrical body 5 toward the inside of the cylindrical body 5. Accordingly, the supply pipe 76 supplies the compressed fluid present in the annular flow passage 730 to the vicinity of the center of the combustion chamber 50 separated from the inner circumferential surface of the cylindrical body 5. The supply pipe 76 may be disposed in all of the communication holes 71 or in only some of the communication holes 71.(Operations and Effects)Since the supply pipe 76 is arranged in this manner, the compressed air flowing from the communication hole 71 into the combustion chamber 50 is supplied through the supply pipe 76 to the vicinity of the center of the combustion chamber 50 lower than the inner circumferential surface of the cylindrical body 5. Accordingly, the compressed air can be stably supplied to a deep portion of the combustion chamber 50 separated from the communication hole 71. Therefore, for example, even in a situation where the compressed air supplied from the communication hole 71 immediately flows toward the downstream side Df 2, such as a case where the flow velocity of the combustion gas in the combustion chamber 50 is high, the compressed air can be supplied to the region of the center of the combustion chamber 50. Therefore, even in a case where one of the ammonia fuel and the hydrocarbon-based fuel is supplied, occurrence of unburned substances or occurrence of a local high-temperature region can be suppressed in a wide range of the combustion chamber 50. Therefore, it is possible to further effectively suppress the generation amount of NOx while continuing stable combustion more efficiently in a wide range of the combustion chamber 50.< Embodiment>Next, a fourth embodiment of the gas turbine equipment 1 according to the present disclosure will be described. In the following fourth embodiment, the configurations common to the configurations of the first to third embodiments are denoted by the same reference numerals in the drawings, and description thereof is omitted. In the fourth embodiment, the annular flow passage forming portion 73 is not limited to the structure directly connected to the outer circumferential surface of the cylindrical body 5 as in the second embodiment or the third embodiment. For example, as shown in FIG. 8, the annular flow passage forming portion 73 may be disposed to have a gap 770 with the outer circumferential surface of the cylindrical body 5. Specifically, an intermediate supply portion 7E includes a gap forming member 77 that connects the annular flow passage forming portion 73 and the cylindrical body 5. The gap forming member 77 forms the gap 770 between the annular flow passage forming portion 73 and the outer circumferential surface of the cylindrical body 5. In the present embodiment, the gap 770 is a space sealed between the gap forming member 77, the annular flow passage forming portion 73, and the cylindrical body 5.(Operations and Effects)As described above, the gap 770 is formed between the annular flow passage forming portion 73 and the outer circumferential surface of the cylindrical body 5. Therefore, even in a case where thermal expansion of the cylindrical body 5 occurs due to the influence of the high-temperature combustion gas flowing through the combustion chamber 50, the thermal expansion amount can be absorbed without affecting the annular flow passage forming portion 73. Accordingly, the fixed state of the annular flow passage forming portion 73 and the cylindrical body 5 can be stably maintained.< Embodiment>Next, a fifth embodiment of the gas turbine equipment 1 according to the present disclosure will be described. In the following fifth embodiment, the configurations common to the configurations of the first to fourth embodiments are denoted by the same reference numerals in the drawings, and description thereof is omitted. In the fifth embodiment, a structure of an intermediate supply portion 7F is not limited to the structure including the annular flow passage forming portion 73 as in the second to fourth embodiments.As shown in FIGS. 9 and 10, the intermediate supply portion 7F according to the fifth embodiment does not include the annular flow passage forming portion 73, and a communication flow passage portion 74F is directly fixed to the outer circumferential surface of the cylindrical body 5. The communication flow passage portion 74F is disposed so as to cover the communication hole 71. Therefore, the communication hole 71 according to the present embodiment connects the combustion chamber 50 and the connection flow passage portion 74F. A plurality of communication flow passage portions 74F are arranged such that one communication flow passage portion 74F is arranged with respect to a communication hole 71. That is, a communication flow passage portion 74F is disposed so as to be able to block a communication hole 71. Moreover, each of the plurality of communication flow passage portions 74F includes an independent valve device 81B.Moreover, as shown in FIGS. 11 and 12, the intermediate supply portion 7F includes a plurality of sealing portions 78. the sealing portions 78 are disposed between the communication flow passage portion 74F and the valve device 81B and between the communication flow passage portion 74F and the cylindrical body 5. The seal portion 78 is a non-contact type seal that can be used in a high-temperature and high-pressure region such as a float ring seal.In the structure as in the second embodiment, the seal portion 78 may be disposed between the annular flow passage forming portion 73 and the cylindrical body 5, or between the annular flow passage forming portion 73 and the communication flow passage portion 74F.Moreover, as shown in FIG. 12, the combustion chamber 15 includes an annular sleeve portion 55 disposed inside the cylindrical body 5 so as to surround the communication hole 71. The sleeve portion 55 forms a flow passage through which cooling air can flow between the inner circumferential surface of the cylindrical body 5. In the sleeve portion 55, similarly to a flow sleeve, a part of the compressed air discharged from the compressor 14 is supplied as the cooling air.In the structure as in the second embodiment, the sleeve portion 55 may be disposed with respect to the communication hole 71 covered with the annular flow passage forming portion 73.(Operations and Effects)As described above, the valve device 81B that is independent of the other valve devices is disposed in each communication hole 71 via the communication flow passage portion 74F. As a result, the valve device 81B can be controlled separately or simultaneously for each communication hole 71. Therefore, even in a case where the ammonia fuel or the hydrocarbon-based fuel is supplied, the supply amount of the compressed air to the combustion chamber 50 can be appropriately controlled. Therefore, even in a case where temperature distribution or concentration distribution unevenness occurs in the cylindrical body 5 or the combustion chamber 50 depending on the operation state, the supply amount can be controlled to an arbitrary value, and the generation amount of NOx can be easily suppressed.Since the seal portion 78 is disposed, even in a case where the high-temperature and high-pressure operating air flows, the leakage of the compressed air from the connection portion between the respective members can be suppressed.Further, since the sleeve portion 55 is disposed, the vicinity of the communication hole 71 can be cooled. Therefore, it is possible to suppress the thermal expansion in the vicinity of the communication hole 71 due to the influence of the high-temperature combustion gas flowing through the combustion chamber 50.< Embodiment>Next, a sixth embodiment of the gas turbine equipment 1 according to the present disclosure will be described with reference to FIGS. 13 and 14. In the following sixth embodiment, the configurations common to the configurations of the first to fifth embodiments are denoted by the same reference numerals in the drawings, and description thereof is omitted. In the sixth embodiment, the fuel nozzle 6G and a flow rate control section 8G are different.The fuel nozzle 6G according to the sixth embodiment includes a mixing portion 65 that forms a mixing space 650 in which the liquids ejected from the first ejection hole 61, the second ejection hole 62, and the third ejection hole 63 are mixed with each other before being supplied to the combustion chamber 50. The mixing portion 65 forms a distal end portion, which is connected to the combustion chamber 50, at the fuel nozzle 6G. The mixing portion 65 is connected to the first ejection hole 61, the second ejection hole 62, and the third ejection hole 63. Only a predetermined amount of the fluid is allowed to flow into the mixing space 650. That is, in the fuel nozzle 6G according to the sixth embodiment, the ammonia fuel, the hydrocarbon-based fuel, and the compressed air supplied are mixed with each other and discharged as a certain amount of the fluid from the mixing portion 65 to the combustion chamber 50. Accordingly, the supply amounts of the ammonia fuel, the hydrocarbon-based fuel, and the compressed air to the fuel nozzle 6G are limited to a certain amount.The flow rate control section 8G is not limited to the structure including the valve device 81 or 81B as described in the first to fifth embodiments. That is, the flow rate control section 8G according to the sixth embodiment does not include the valve device 81 or 81B. The flow rate control section 8G according to the sixth embodiment sets the supply amounts of the ammonia fuel, the hydrocarbon-based fuel, and the compressed air to the fuel nozzle 6G to be constant, and then changes a ratio of the supply amounts of the ammonia fuel and the hydrocarbon-based fuel to the compressed air. As for the flow rate control portion 8G, the supply amount of at least one of the ammonia fuel and the hydrocarbon-based fuel can be controlled, and thus the flow rate of the compressed air supplied from the communication hole 71 to the cylindrical body 5 can be controlled. In the sixth embodiment, as described above, the supply amounts of the ammonia fuel, the hydrocarbon-based fuel, and the compressed air to the fuel nozzle 6 are constantly adjusted by the mixing section 65. In such a state, the flow rate control section 8G can regulate the supply amount of at least one of the ammonia fuel and the hydrocarbon-based fuel such that the supply amount of the ammonia fuel when the ammonia fuel is supplied to the fuel nozzle 6G is larger than the supply amount of the hydrocarbon-based fuel when the hydrocarbon-based fuel is supplied to the fuel nozzle 6G. Specifically, the flow rate control section 8G according to the sixth embodiment includes a first supply amount control section 85 and a second supply amount control section 86 as shown in FIG. 13.The first supply amount control section 85 controls the supply amount of the ammonia fuel to the fuel nozzle 6G. The first supply amount control section 85 is disposed in the first supply line 22. The first supply amount control section 85 is, for example, a flow rate control valve, an on-off valve, or an electromagnetic valve. In a case where an opening degree of the first supply amount control portion 85 is increased, the supply amount of the ammonia fuel from the first supply pipe 22 to the first discharge hole 61 is increased. Conversely, in a case where the opening degree of the first supply amount control portion 85 is decreased, the supply amount of the ammonia fuel from the first supply pipe 22 to the first discharge hole 61 is reduced.The second supply amount control section 86 controls the supply amount of the hydrocarbon-based fuel to the fuel nozzle 6G. The second supply amount control section 86 is disposed in the second supply line 32. The second supply amount control section 86 is, for example, a flow rate control valve, an on / off valve, or a solenoid valve. In a case where an opening degree of the second supply amount control portion 86 is increased, the supply amount of the hydrocarbon-based fuel from the second supply pipe 32 to the second discharge hole 62 is increased. On the contrary, in a case where the opening degree of the second supply amount control portion 86 is decreased, the supply amount of the hydrocarbon-based fuel from the second supply pipe 32 to the second discharge hole 62 is reduced. Moreover, even in the fully open state, the second supply amount control portion 86 has a lower flow rate at which the flow in the second supply line 32 can be performed than the flow rate in the fully open state of the first supply amount control portion 85. That is, in a case where both the first supply amount control portion 85 and the second supply amount control portion 86 are in the fully open state, the supply amount of the ammonia fuel is larger than the supply amount of the hydrocarbon-based fuel. In particular, it is preferable that the second supply amount control section 86 can pass the current under the flow rate of a reverse ratio of the ratio with respect to the first supply amount control section 85 based on a ratio of the heating value of the ammonia fuel to the heating value of the hydrocarbon-based fuel. More specifically, in a case where the heating value of the hydrocarbon-based fuel and a Wobbe index (WI) are about four times as large as the heating value of the ammonia fuel, the second supply amount control section 86 may allow the flow with respect to the first supply amount control section 85 only up to about 1 / 4 of the flow rate.(Operations and Effects)As shown in FIG. 14, the flow rate control section 8G controls the supply amounts of the ammonia fuel and the hydrocarbon-based fuel and the compressed air to the fuel nozzle 6G. Specifically, in a case where both the ammonia fuel and the hydrocarbon-based fuel are supplied, as shown in "mixed combustion" of FIG. 14, the first supply amount control section 85 and the second supply amount control section 86 are controlled so that a ratio between a total value of the supply amounts of the ammonia fuel and the hydrocarbon-based fuel and the supply amount of the compressed air is near 1:1.Moreover, when only the ammonia fuel is supplied, as shown in "only NH3" of FIG. 14, the control is performed in which the first supply amount control section 85 is opened and the second supply amount control section 86 is closed so that the supply amount of the ammonia fuel is larger than the supply amount of the compressed air. As a result, in the mixing space 650, more ammonia fuel is supplied from the first discharge hole 61 and less compressed air is supplied from the third discharge hole 63 compared to a case of "mixed combustion". Then, a large amount of the compressed air that cannot flow into the third ejection hole 63 is supplied from the communication hole 71 to the combustion chamber 50. As a result, a majority of the compressed air in the intermediate housing 13 flows from the communication hole 71 into the combustion chamber 50.Moreover, when only the hydrocarbon-based fuel is supplied, as shown in "CH 4 only" of FIG. 14, the control is performed in which the first supply amount control section 85 is closed and the second supply amount control section 86 is opened so that the supply amount of the hydrocarbon-based fuel is larger than the supply amount of the compressed air. Further, the second supply amount control section 86 is configured to reduce the flow with respect to the first supply amount control section 85 to only a very small flow rate. Therefore, the flow rate of the compressed air flowing from the third discharge hole 63 into the mixing space 650 in a case of "CH 4 only" is larger than in a case of "NH 3 only" or a case of "mixed combustion". As a result, the amount of compressed air that cannot flow into the third ejection hole 63 is reduced. As a result, the compressed air in the intermediate housing 13 does not flow from the communication holes 71 into the combustion chamber 50.In this way, the flow rate of the compressed air used in the fuel nozzle 6 can be controlled by controlling the supply amount of the ammonia fuel and the supply amount of the hydrocarbon-based fuel. Therefore, it is not necessary to always arrange the valve device 81 or 81B, and it is possible to suppress the generation amount of NOx while continuing stable combustion with a simpler configuration or control of only changing the supply amount of the ammonia fuel and the supply amount of the hydrocarbon-based fuel regardless of whether the ammonia fuel or the hydrocarbon-based fuel is supplied. Therefore, it is possible to effectively achieve both the combustion with the ammonia fuel and the combustion with the hydrocarbon-based fuel.As described above, the flow rate control section 8G according to the sixth embodiment may be applied to a structure in which the valve device 81 or 81B is not provided, but may be applied to a structure in which the valve device 81 or 81B is further provided.< Embodiment>Next, a seventh embodiment of the gas turbine equipment 1 according to the present disclosure will be described with reference to FIG. 15. In the following seventh embodiment, the configurations common to the configurations of the first to sixth embodiments are denoted by the same reference numerals in the drawings, and description thereof is omitted. The seventh embodiment is different from the sixth embodiment in that a flow rate control section 8H controls the flow rate based on the operating state of the combustion chamber 15.The gas turbine 10 according to the seventh embodiment further includes a detection section 9 that detects the operating state of the combustor 15. Specifically, the detection section 9 according to the present embodiment detects the temperature in the combustion chamber 15. That is, the detection section 9 only needs to be a device capable of detecting the supply states of the ammonia fuel, the hydrocarbon-based fuel, and the compressed air. For example, the detection section 9 may be a device that detects at least one of the supply amount or temperature of the ammonia fuel, the supply amount or temperature of the hydrocarbon-based fuel, and the supply amount or temperature of the compressed air with respect to the fuel nozzle 6. Moreover, the detection section 9 may be a device that detects the temperature of the combustion gas in the vicinity of inflow to 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. Further, the detection section 9 may detect a plurality of states of a state of the fluid to be supplied and a state of the combustion result in the combustion chamber 15.Moreover, the flow rate control section 8H according to the seventh embodiment includes a valve control device 88 that controls the valve device 81 based on the detection result of the detection section 9. The valve control device 88 can control the flow rate of the compressed air supplied to the combustion chamber 50 by changing the opening degree of the valve device 81 in accordance with the detection result of the detection section 9. Specifically, in a case where the temperature of the combustion chamber 15 detected by the detection section 9 exceeds a first threshold, the valve control device 88 outputs an instruction to decrease the opening degree of the valve device 81. The first threshold value is, for example, a value of a temperature corresponding to a case where the supply of the hydrocarbon-based fuel is started from a state where only the ammonia fuel is supplied to the fuel nozzle 6 and is switched to a mixed combustion state of the ammonia fuel and the hydrocarbon-based fuel. Further, in a case where the temperature of the combustion chamber 15 detected by the detection portion 9 exceeds a second threshold value larger than the first threshold value, the valve control device 88 outputs an instruction to further reduce the opening degree of the valve device 81 (for example, in the fully closed state). The second threshold value is, for example, a value of a temperature corresponding to a case where a state is switched from the mixed combustion state in which both the ammonia fuel and the hydrocarbon-based fuel are supplied to a state in which the supply of the ammonia fuel is stopped and only the hydrocarbon-based fuel is supplied to the fuel nozzle 6.The above-described valve control device 88 is a computer. The hardware of the valve control device 88 includes a central processing unit (CPU) that performs various operations, a main storage device such as a memory that is a work area of the CPU, an auxiliary storage device such as a hard disk drive device, an input device such as a keyboard or a mouse, and a display device. The valve control device 88 may be incorporated into a control device (not shown) of the gas turbine equipment 1 as a part of the functions.(Operations and Effects)As described above, by controlling the valve device 81 via the valve control device 88 on the basis of the detection result of the detection portion 9, the flow rate of the compressed air supplied from the valve device 81 to the communication hole 71 of the combustion chamber 50 can be promptly controlled depending on the operation state of the combustion chamber 15. Further, it is possible to suppress the generation amount of NOx while maintaining stable combustion even at the time of switching the supply of the ammonia fuel and the hydrocarbon-based fuel.Moreover, in the ammonia fuel and the hydrocarbon-based fuel, the heating value of the hydrocarbon-based fuel is much higher than the heating value of the ammonia fuel. Therefore, in a case where the temperature of the combustion chamber 15 is detected by the detection section 9, it is possible to easily determine the supply amounts of the ammonia fuel and the hydrocarbon-based fuel that are supplied.(Other Embodiments)Although the embodiments of the present disclosure have been described in detail with reference to the drawings, the specific configuration is not limited to these embodiments and includes, for example, a design change without departing from the gist of the present disclosure.The above-described gas turbine equipment 1 is not limited to the structure described in the present embodiment. For example, as other configurations, the gas turbine equipment 1 may include a control device that controls various devices, a denitration device that decomposes NOx contained in the exhaust gas from the gas turbine 10, and a chimney that discharges the exhaust gas flowing out of the denitration device to the outside.Moreover, the above-described combustor 15 is not limited to the structure described in the present embodiment. That is, the combustion chamber 15 may have a configuration (for example, a muffler or the like) different from the cylindrical body 5, the fuel nozzle 6 or 6G, the intermediate supply portion 7, 7B, 7C, 7D, 7E or 7F, and the flow rate control portion 8, 8B, 8G or 8H.Moreover, the embodiment of the fuel nozzle 6 or 6G is not limited to the above-described structure. The fuel nozzle 6 or 6G may be a nozzle type of any shape, such as a type (premixed combustion type) for premixing fuel and air, a type for rapidly mixing fuel and air as in the present embodiment (diffusion combustion type), or a type for independently ejecting fuel and air.Moreover, the control of the supply state of the ammonia fuel to the fuel nozzle 6 or 6G from the ammonia fuel supply equipment 20 and the control of the supply state of the hydrocarbon-based fuel to the fuel nozzle 6 or 6G from the hydrocarbon-based fuel supply equipment 30 may be manually performed by a worker, or may be automatically performed by a control device or the like of the gas turbine equipment 1.Moreover, in the present embodiment, the ammonia fuel supply equipment 20 is configured to supply the gaseous ammonia fuel to the gas turbine 10, but the present disclosure is not limited to such a configuration. As long as the gas turbine 10 has a structure capable of receiving the liquid-state ammonia fuel, the ammonia fuel supply equipment 20 can supply the liquid-state ammonia fuel to the gas turbine 10.Similarly, the valve device 81 or 81B, the first supply amount control section 85, and the second supply amount control section 86 may be manually controlled by a worker, or may be automatically controlled by a control device or the like of the gas turbine equipment 1.Moreover, the intermediate supply portion 7, 7B, 7C, 7D, 7E, or 7F is not limited to the structure including the communication holes 71 described in the present embodiment. The intermediate supply portion 7, 7B, 7C, 7D, 7E, or 7F only needs to have a structure in which a part of the compressed air supplied to the fuel nozzle 6 or 6G can be supplied to the cylindrical body 5 on the downstream side Df 2 of the fuel nozzle 6 or 6G in the flow direction Df of the combustion gas. Therefore, the intermediate supply portion 7, 7B, 7C, 7D, 7E, or 7F may have a structure in which the compressed air compressed by the compressor 14 is taken out through a pipe or the like, for example, and supplied to the cylindrical body 5.< Annotations>The gas turbine 10 and the gas turbine equipment 1 according to each of the embodiments can be understood as follows, for example.(1) A first aspect provides a gas turbine 10 including: a compressor 14 configured to compress air to generate compressed air; a combustor 15 in which a fuel to be burned is switchable between an ammonia fuel and a hydrocarbon-based fuel, the combustor 15 configured to combust at least one of the ammonia fuel and the hydrocarbon-based fuel in the compressed air supplied from the compressor 14 to generate a combustion gas; and a turbine 16 drivable by the combustion gas supplied from the combustor 15, the combustor 15 including a cylindrical body 5 having a cylindrical shape and through which the combustion gas generated by combustion of the ammonia fuel or the hydrocarbon-based fuel flows, a fuel nozzle 6 or 6G that generates the ammonia fuel, the hydrocarbon-based fuel and discharges the compressed air into the cylindrical body 5, an intermediate supply portion 7, 7B, 7C, 7D, 7E, or 7F that supplies a part of the compressed air supplied to the fuel nozzle 6 or 6G to the cylindrical body 5, on a downstream side Df 2 of the fuel nozzle 6 or 6G in a flow direction Df of the combustion gas, and a flow rate control portion 8, 8B, 8G, or 8H that controls a flow rate of the compressed air supplied from the intermediate supply portion 7, 7B, 7C, 7D, 7E, or 7F to the cylindrical body 5 with respect to a supply amount of the compressed air supplied to the fuel nozzle 6 or 6G, and the flow rate control section 8, 8B, 8G, or 8H increases the flow rate of the compressed air supplied from the intermediate supply section 7, 7B, 7C, 7D, 7E, or 7F to the cylindrical body 5 when the ammonia fuel is burned, and decreases the flow rate of the compressed air supplied to the cylindrical body 5 when the hydrocarbon-based fuel is burned.Accordingly, when the combustion gas is generated by using the ammonia fuel, the flow rate of the compressed air used for the combustion through the fuel nozzle 6 can be reduced. As a result, in a case where the ammonia fuel is burned, it is possible to suppress the occurrence of unstable combustion due to excessive supply of the compressed air. Accordingly, in a case where the ammonia fuel is burned, stable combustion can be continued, and the flame holding property can be maintained.In a case where the supply amount of the compressed air is reduced, the ratio of the ammonia fuel is increased in the ratio between the supply amounts of the ammonia fuel and the compressed air. As a result, the amount of the nitrogen component remaining in the combustion gas derived from nitrogen in the ammonia fuel can be significantly reduced. Therefore, the generation amount of NOx when the ammonia fuel is burned can be suppressed.Further, when the hydrocarbon-based fuel is used to generate the combustion gas, the flow rate of the compressed air used for the combustion through the fuel nozzle 6 can be increased. As a result, it is possible to secure a required amount of the compressed air to be supplied to the fuel nozzle 6 or 6G when the hydrocarbon-based fuel is burned. Accordingly, even in a case where the hydrocarbon-based fuel is burned, stable combustion can be continued, and the flame holding property can be maintained.In a case where the supply amount of the compressed air is increased, the proportion of the hydrocarbon-based fuel is decreased in the ratio between the supply amounts of the hydrocarbon-based fuel and the compressed air. As a result, the amount of the nitrogen component remaining in the combustion gas derived from nitrogen in the compressed air can be significantly reduced. Therefore, the generation amount of NOx when the hydrocarbon-based fuel is burned can be suppressed.In this way, in the gas turbine 10 to which the ammonia fuel and the hydrocarbon-based fuel are supplied, the generation amount of NOx can be suppressed while stable combustion is continued regardless of whether the ammonia fuel or the hydrocarbon-based fuel is supplied. Therefore, it is possible to effectively achieve both the combustion with the ammonia fuel and the combustion with the hydrocarbon-based fuel.(2) A second aspect provides the gas turbine 10 according to (1), wherein the flow rate control section 8, 8B, 8G, or 8H includes a valve device 81 or 81B configured to control a flow rate of the compressed air flowing into the cylindrical body 5.Accordingly, the supply amount of the compressed air can be controlled by a simple configuration in a case where the ammonia fuel is supplied and in a case where the hydrocarbon-based fuel is supplied.(3) A third aspect provides the gas turbine 10 according to (1) or (2), wherein the intermediate supply portion 7, 7B, 7C, 7D, 7E, or 7F includes a communication hole 71 that allows an inside and an outside of the cylindrical body 5 to communicate with each other at a position that is separated from the fuel nozzle 6 and that is located on the downstream side Df 2 of the fuel nozzle 6 or 6G in the flow direction Df of the combustion gas.Accordingly, the compressed air that has flowed from the communication hole 71 into the combustion chamber 50 does not directly participate in the combustion. Therefore, a structure in which the compressed air can be supplied to the combustion chamber 50 while securing a space for stably burning the ammonia fuel and the hydrocarbon-based fuel supplied from the fuel nozzle 6 or 6G can be obtained by a simple configuration.(4) A fourth aspect provides the gas turbine 10 according to (3), wherein the communication holes 71 are formed in the cylindrical body 5 at a plurality of positions separated from each other.Accordingly, the compressed air supplied to the cylindrical body 5 is supplied to the combustion chamber 50 without being largely biased to the vicinity of the inner circumferential surface of a part of the cylindrical body 5. Therefore, the generation amount of NOx can be suppressed effectively while continuing stable combustion with high efficiency in a wide range of the combustion chamber 50 regardless of whether the ammonia fuel or the hydrocarbon-based fuel is supplied.(5) A fifth aspect provides the gas turbine 10 according to (3) or (4), wherein the intermediate supply portion 7B, 7C, 7D, or 7E includes an annular flow passage forming portion 73 that forms an annular flow passage 730 through which the compressed air can flow along an outer periphery of the cylindrical body 5, and the communication hole 71 allows the annular flow passage forming portion 73 and the cylindrical body 5 to communicate with each other.Accordingly, the annular flow passage forming portion 73 plays a role of a damper, and thus the compressed air present in the annular flow passage 730 is in a nearly uniform pressure state. Thereafter, the compressed air flows from the communication hole 71 into the combustion chamber 50 while filling the annular flow passage 730. Accordingly, the compressed air can be supplied in a nearly uniform pressure state from the communication hole 71 to the combustion chamber 50 through the annular flow passage forming portion 73. Therefore, the generation amount of NOx can be further effectively suppressed while stable combustion is more efficiently continued in a wide range of the combustion chamber 50 regardless of whether the ammonia fuel or the hydrocarbon-based fuel is supplied.(6) A sixth aspect provides the gas turbine 10 according to (5), wherein the annular flow passage forming portion 73 is disposed to have a gap 770 with an outer circumferential surface of the cylindrical body 5.Accordingly, even in a case where the thermal expansion of the cylindrical body 5 occurs due to the influence of the high-temperature combustion gas flowing through the combustion chamber 50, the thermal expansion amount can be absorbed without affecting the annular flow passage forming portion 73. Accordingly, the fixed state of the annular flow passage forming portion 73 and the cylindrical body 5 can be stably maintained.(7) A seventh aspect provides the gas turbine 10 according to any one of (3) to (6), wherein the intermediate supply portion 7D or 7E includes a supply pipe 76 that is disposed in the communication hole 71 and that is formed in a tubular shape extending inward from an inner circumferential surface of the cylindrical body 5.Accordingly, the compressed air flowing from the communication hole 71 into the combustion chamber 50 is supplied to a portion lower than the inner circumferential surface of the cylindrical body 5 through the supply pipe 76. Accordingly, the compressed air can be stably supplied to a deep portion of the combustion chamber 50 separated from the communication hole 71.(8) An eighth aspect provides the gas turbine 10 according to any one of (1) to (7), wherein the flow rate control section 8, 8B, 8G, or 8H is configured to adjust supply amounts of the ammonia fuel, the hydrocarbon-based fuel, and the compressed air to the fuel nozzle 6 or 6G, and then control the supply amount of at least one of the ammonia fuel and the hydrocarbon-based fuel such that the supply amount of the ammonia fuel when the ammonia fuel is supplied to the fuel nozzle 6 or 6G is larger than the supply amount of the hydrocarbon-based fuel when the hydrocarbon-based fuel is supplied to the fuel nozzle 6 or 6G.Accordingly, the flow rate of the compressed air used in the fuel nozzle 6 can be controlled by controlling the supply amount of the ammonia fuel and the supply amount of the hydrocarbon-based fuel. Therefore, it is not necessary to always arrange the valve device 81 or 81B, and it is possible to suppress the generation amount of NOx while continuing stable combustion with a simpler configuration or control of only changing the supply amount of the ammonia fuel and the supply amount of the hydrocarbon-based fuel regardless of whether the ammonia fuel or the hydrocarbon-based fuel is supplied.(9) A ninth aspect provides the gas turbine 10 according to any one of (1) to (8), further comprising: a detection section 9 that detects an operation state of the combustor 15, wherein the flow rate control section 8, 8B, 8G, or 8H controls the flow rate of the compressed air supplied to the cylindrical body 5 in accordance with a detection result of the detection section 9.Accordingly, the flow rate of the compressed air to be supplied from the flow rate control section 8, 8B, 8G, or 8H to the combustion chamber 50 can be promptly controlled depending on the operating state of the combustion chamber 15. Further, it is possible to suppress the generation amount of NOx while maintaining stable combustion even at the time of switching the supply of the ammonia fuel and the hydrocarbon-based fuel.(10) A tenth aspect provides a gas turbine equipment 1 including: the gas turbine 10 according to any one of (1) to (9); an ammonia fuel supply equipment 20 configured to supply the ammonia fuel to the gas turbine 10; and a hydrocarbon-based fuel supply equipment 30 configured to supply the hydrocarbon-based fuel to the gas turbine 10.Industrial applicabilityWith the gas turbine and the gas turbine equipment according to the present disclosure, it is possible to suppress the generation amount of NOx while continuing stable combustion in the gas turbine to which the ammonia fuel and the hydrocarbon-based fuel are supplied.List of reference characters1 Gas turbine equipment 10 Gas turbine 11 Gas turbine rotor 12 Air intake passage 13 Intermediate casing 14 Compressor 14 r Compressor rotor 14 c Compressor casing 14 v IGV 15 Combustor 5 Cylindrical body 50 Combustion chamber 6, 6G Fuel nozzle 61 First discharge hole 62 Second discharge hole 63 Third discharge hole 7, 7B, 7C, 7D, 7E, 7F Intermediate supply portion 71 Communication hole 8, 8B, 8G, 8H Flow rate control portion 81, 81B Valve device Df Flow direction Df 1 Upstream side Df 2 Downstream side 16 Turbine 16 rTurbine 16 c Turbine casing Ar Rotor axis line 20 Ammonia fuel supply equipment 21 First storage tank 22 First supply line 30 Hydrocarbon-based fuel supply equipment 31 Second storage tank 32 Second supply line 73, 73C Annular flow passage forming portion 730 Annular flow passage 75 Welding portion 74, 74C, 74F Communication flow passage portion 76 Supply pipe 77 Gap forming member 770 Gap 78 Sealing portion 55 Sleeve portion 85 First supply amount control portion 86 Second supply amount control portion 65 Mixing portion 650 Mixing space 9 Detection portion 88 Valve control deviceReferences included in the specificationThis list of documents cited by the applicant has been produced in an automated manner and is only included for the better information of the reader. The list is not part of the German patent application or utility model application. The DPMA does not take any adhesion for any faults or omissions.Patent Literature citedJP 2022-133982

[0002] JP 2010-19195

[0005]

Claims

A gas turbine comprising: a compressor configured to compress air to generate compressed air; a combustor in which a fuel to be burned is switchable between an ammonia fuel and a hydrocarbon-based fuel, the combustor being configured to burn at least one of the ammonia fuel and the hydrocarbon-based fuel in the compressed air supplied from the compressor to generate a combustion gas; and a turbine drivable by the combustion gas supplied from the combustor, the combustor including: a cylindrical body having a cylindrical shape and through which the combustion gas generated by combustion of the ammonia fuel or the hydrocarbon-based fuel flows, a fuel nozzle that generates the ammonia fuel, the hydrocarbon-based fuel and discharges the compressed air into the cylindrical body, an intermediate supply portion supplying a part of the compressed air supplied to the fuel nozzle to the cylindrical body on a downstream side of the fuel nozzle in a flow direction of the combustion gas, and a flow rate control portion configured to control a flow rate of the compressed air supplied from the intermediate supply portion to the cylindrical body with respect to a supply amount of the compressed air supplied to the fuel nozzle, and the flow rate control portion increases the flow rate of the compressed air supplied from the intermediate supply portion to the cylindrical body when the ammonia fuel is burned and decreases the flow rate of the compressed air supplied to the cylindrical body when the hydrocarbon-based fuel is burned.The gas turbine according to claim 1, wherein the flow rate control section includes a valve device configured to control a flow rate of the compressed air flowing into the cylindrical body.The gas turbine according to claim 1 or 2, wherein the intermediate supply portion includes a communication hole that allows an inside and an outside of the cylindrical body to communicate with each other at a position that is separated from the fuel nozzle and that is on the downstream side of the fuel nozzle in the flow direction of the combustion gas.The gas turbine according to claim 3, wherein the communication holes are formed in the cylindrical body at a plurality of positions separated from each other.The gas turbine according to claim 4, wherein the intermediate supply portion includes an annular flow passage forming portion that forms an annular flow passage through which the compressed air can flow along an outer periphery of the cylindrical body, and the communication hole allows the annular flow passage forming portion and the cylindrical body to communicate with each other.The gas turbine according to claim 5, wherein the annular flow passage forming portion is disposed to have a gap with an outer circumferential surface of the cylindrical body.The gas turbine according to claim 5, wherein the intermediate supply portion includes a supply pipe that is disposed in the communication hole and that is formed in a tubular shape extending inward from an inner circumferential surface of the cylindrical body.The gas turbine according to claim 1, wherein the flow rate control section is configured to adjust supply amounts of the ammonia fuel, the hydrocarbon-based fuel, and the compressed air to the fuel nozzle, and then control the supply amount of at least one of the ammonia fuel and the hydrocarbon-based fuel such that the supply amount of the ammonia fuel when the ammonia fuel is supplied to the fuel nozzle is larger than the supply amount of the hydrocarbon-based fuel when the hydrocarbon-based fuel is supplied to the fuel nozzle.The gas turbine according to claim 1 or 2, further comprising: a detection section that detects an operation state of the combustor, wherein the flow rate control section controls the flow rate of the compressed air supplied to the cylindrical body in accordance with a detection result of the detection section.A gas turbine equipment, comprising: the gas turbine according to claim 1 or 2; an ammonia fuel supply equipment configured to supply the ammonia fuel to the gas turbine; and a hydrocarbon-based fuel supply equipment configured to supply the hydrocarbon-based fuel to the gas turbine.

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