Combustion device and gas turbine system

Abstract

A combustion device 10 comprises: a liner 13b that has an opening 13f provided at an end, and that has a combustion chamber 13c formed inside; a first ammonia flow passage 24 which is inserted into the opening 13f of the liner 13b and is connected to the combustion chamber 13c through an injection valve 14c, and to which liquid ammonia is supplied; a second ammonia flow passage 25 which covers the outer circumference of the first ammonia flow passage 24; and an air flow passage 23 which covers the outer circumference of the second ammonia flow passage 25.

Description

Combustion equipment and gas turbine systems

[0001] This application claims the benefit of priority from Japanese Patent Application No. 2023-119402, filed on July 21, 2023, the contents of which are incorporated herein by reference.

[0002] 2. Description of the Related Art Gas turbine systems are used that obtain power by burning fuel in a combustor. For example, as disclosed in Patent Document 1, there is a gas turbine system that uses ammonia as fuel. The use of ammonia as fuel reduces carbon dioxide emissions.

[0003] Japanese Patent Application Laid-Open No. 2016-191507

[0004] In some gas turbine systems, ammonia is vaporized by a vaporizer and then supplied to the combustion chamber of the combustor. The use of a vaporizer increases the equipment cost and startup time of the gas turbine system. Therefore, it is possible to supply liquid ammonia to the combustion chamber without using a vaporizer. In this case, before the ammonia is injected into the combustion chamber, the liquid ammonia in the burner flow passage is heated by the high-temperature air supplied to the combustion chamber, which may result in the ammonia vaporizing in the burner flow passage. Such vaporization of ammonia may result in, for example, an unstable ammonia injection amount.

[0005] An object of the present disclosure is to provide a combustion device and a gas turbine system that are capable of suppressing vaporization of liquid ammonia used as fuel.

[0006] In order to solve the above problems, the combustion device of the present disclosure includes a liner having an opening at an end and forming a combustion chamber inside, a first ammonia flow path that is inserted into the opening of the liner and communicates with the combustion chamber via an injection valve and through which liquid ammonia is supplied, a second ammonia flow path that covers the outer periphery of the first ammonia flow path, and an air flow path that covers the outer periphery of the second ammonia flow path.

[0007] The device may include a pipe that separates the first ammonia flow path from the second ammonia flow path, and at least one through-hole that is provided on a side surface of the pipe and that connects the first ammonia flow path to the second ammonia flow path.

[0008] The through-hole may be provided within the range in which the air flow path exists in the axial direction of the pipe.

[0009] At least one group of through holes may be provided, the group including a plurality of through holes spaced apart circumferentially around the tube.

[0010] A plurality of groups of through holes may be provided at intervals in the axial direction of the tube.

[0011] The positions of the through holes in the circumferential direction may be different between adjacent groups of through holes.

[0012] The through-hole may extend in a direction intersecting the radial direction of the pipe when viewed in the axial direction of the pipe.

[0013] The second ammonia flow path may be provided with a swirling member that swirls the fluid.

[0014] The second ammonia flow path may be supplied with liquid ammonia.

[0015] In order to solve the above problems, a gas turbine system according to the present disclosure includes the above combustion device.

[0016] According to the present disclosure, it is possible to suppress the evaporation of liquid ammonia used as fuel.

[0017] Fig. 1 is a schematic diagram showing the configuration of a gas turbine system according to an embodiment of the present disclosure. Fig. 2 is an enlarged view showing a burner of a combustion device according to an embodiment of the present disclosure. Fig. 3 is a cross-sectional view of the burner of a combustion device according to an embodiment of the present disclosure, viewed in the axial direction. Fig. 4 is a cross-sectional view of the burner of a combustion device according to a first modified example, viewed in the axial direction. Fig. 5 is a cross-sectional view of the burner of a combustion device according to a second modified example, viewed in the axial direction. Fig. 6 is an enlarged view of the burner of a combustion device according to a third modified example. Fig. 7 is an enlarged view of the burner of a combustion device according to a fourth modified example.

[0018] Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. Dimensions, materials, and other specific numerical values ​​shown in the embodiments are merely examples for ease of understanding and, unless otherwise specified, do not limit the present disclosure. In this specification and drawings, elements having substantially the same functions and configurations are designated by the same reference numerals to avoid redundant explanation, and elements not directly related to the present disclosure are not shown.

[0019] 1 is a schematic diagram showing the configuration of a gas turbine system 1 according to this embodiment. As shown in FIG. 1, the gas turbine system 1 includes a turbocharger 11, a generator 12, a combustor 13, a burner 14, an ammonia tank 15, and a flow control valve 16.

[0020] Of the gas turbine system 1 , the combustor 13 , the burner 14 , the ammonia tank 15 , and the flow control valve 16 are included in the combustion device 10 .

[0021] The turbocharger 11 includes a compressor 11 a and a turbine 11 b. The impeller of the compressor 11 a and the impeller of the turbine 11 b rotate as a single unit. The impeller of the compressor 11 a and the impeller of the turbine 11 b are connected by a shaft.

[0022] The compressor 11a is provided in an intake air flow path 21 connected to the combustor 13. Air to be supplied to the combustor 13 flows through the intake air flow path 21. An intake port (not shown) through which air is taken in from the outside is provided at the upstream end of the intake air flow path 21. The air taken in through the intake port passes through the compressor 11a and is sent to the combustor 13. The compressor 11a compresses the air and discharges it downstream.

[0023] The turbine 11b is provided in an exhaust flow path 22 connected to the combustor 13. Exhaust gas discharged from the combustor 13 flows through the exhaust flow path 22. An exhaust port (not shown) through which the exhaust gas is discharged to the outside is provided at the downstream end of the exhaust flow path 22. The exhaust gas discharged from the combustor 13 passes through the turbine 11b and is sent to the exhaust port. The turbine 11b generates rotational power when an impeller of the turbine 11b is rotated by the exhaust gas.

[0024] The generator 12 is connected to the turbocharger 11. The generator 12 generates electricity using the rotational power generated by the turbocharger 11.

[0025] The combustor 13 has a casing 13a, a liner 13b, and a combustion chamber 13c. The casing 13a has a generally cylindrical shape. The liner 13b is provided inside the casing 13a. The liner 13b also has a generally cylindrical shape. The liner 13b is arranged coaxially with the casing 13a. The combustion chamber 13c is formed inside the liner 13b. In other words, the internal space of the liner 13b corresponds to the combustion chamber 13c. The combustion chamber 13c is a generally cylindrical space. An exhaust flow path 22 is connected to the combustion chamber 13c.

[0026] As will be described later, fuel and air are supplied to the combustion chamber 13c. Ammonia is mainly used as the fuel and combustion takes place in the combustion chamber 13c. However, in addition to ammonia, other fuels such as natural gas or hydrogen may also be used as the fuel supplied to the combustion chamber 13c. Exhaust gas generated by the combustion in the combustion chamber 13c is discharged to the exhaust flow path 22.

[0027] The liner 13b has a main body 13d. The main body 13d has a substantially cylindrical shape. A combustion chamber 13c is formed inside the main body 13d. A communication portion 13e is provided at the end of the main body 13d. The communication portion 13e connects the outside of the liner 13b with the combustion chamber 13c. The communication portion 13e has a cylindrical shape and is arranged coaxially with the main body 13d. The outer diameter of the communication portion 13e is smaller than the outer diameter of the main body 13d. The inner diameter of the communication portion 13e is smaller than the inner diameter of the main body 13d. However, the inner diameter of the communication portion 13e may decrease or increase as it progresses toward the main body 13d. Various components, such as swirlers, for forming a swirling flow of air may be provided within the communication portion 13e. An opening 13f is provided at the end of the communication portion 13e opposite the main body 13d. In this way, the opening 13f is provided at the end of the liner 13b. Note that the liner 13b shown in Fig. 1 may be divided into multiple members. In that case, different members among the multiple members constituting the liner 13b shown in Fig. 1 may be called by different names. For example, the communication portion 13e may be made of a member different from other parts of the liner 13b, and may be called by a name different from the names referring to those other parts.

[0028] An air flow path 23 is formed between the inner surface of the casing 13a and the outer surface of the liner 13b. The intake air flow path 21 is connected to the air flow path 23. Air is sent from the compressor 11a to the air flow path 23 via the intake air flow path 21. The air flow path 23 communicates with an opening 13f of the liner 13b. The burner 14 is inserted into the opening 13f of the liner 13b. As shown by arrow F1, the air sent to the air flow path 23 passes through the air flow path 23 and then passes through the opening 13f of the liner 13b to be injected into the combustion chamber 13c. Specifically, the air sent to the air flow path 23 passes between the inner circumferential surface of the communication portion 13e and the outer circumferential surface of the burner 14 and is injected into the combustion chamber 13c.

[0029] The burner 14 injects ammonia as fuel into the combustion chamber 13c of the combustor 13. The burner 14 has a substantially cylindrical shape. Hereinafter, the combustion chamber 13c side of the burner 14 (the right side in FIG. 1 ) will be referred to as the front end side, and the opposite side of the burner 14 from the combustion chamber 13c side (the left side in FIG. 1 ) will be referred to as the rear end side. The front end of the burner 14 is inserted through an opening 13f of the liner 13b. The burner 14 penetrates the casing 13a and extends to the outside of the casing 13a. The rear end of the burner 14 is located outside the casing 13a. Details of the burner 14 will be described later with reference to FIGS. 2 and 3.

[0030] An ammonia tank 15 is connected to the rear end of the burner 14. Liquid ammonia is stored in the ammonia tank 15. A flow path connecting the ammonia tank 15 and the burner 14 is provided with a flow control valve 16. The ammonia stored in the ammonia tank 15 is supplied to the burner 14. The flow control valve 16 controls the flow rate of the ammonia supplied from the ammonia tank 15 to the burner 14. Note that the flow path connecting the ammonia tank 15 and the burner 14 may be provided with various devices (e.g., a shut-off valve, a check valve, various sensors, etc.) which are not shown in FIG. 1 .

[0031] Fig. 2 is an enlarged view showing the burner 14 of the combustion device 10 according to this embodiment. As shown in Fig. 2, the burner 14 has a first pipe 14a, a second pipe 14b, and an injection valve 14c. As will be described later, the example shown in Fig. 2 is merely an example, and various modifications may be made to the example shown in Fig. 2.

[0032] In the example of Fig. 2, the first tube 14a and the second tube 14b have a cylindrical shape. The second tube 14b is arranged coaxially with the first tube 14a and radially outward from the first tube 14a. The second tube 14b is radially spaced apart from the first tube 14a. The inner diameter of the second tube 14b is larger than the outer diameter of the first tube 14a. The second tube 14b covers the outer peripheral surface of the first tube 14a. In other words, the inner peripheral surface of the second tube 14b faces the outer peripheral surface of the first tube 14a.

[0033] 2, the axial direction of the first tube 14a and the second tube 14b corresponds to the axial direction of the burner 14. Hereinafter, the radial direction of the burner 14, the axial direction of the burner 14, and the circumferential direction of the burner 14 will also be simply referred to as the radial direction, the axial direction, and the circumferential direction, respectively.

[0034] The first pipe 14a and the second pipe 14b are inserted through the opening 13f of the liner 13b. The axial positions of the tips of the first pipe 14a and the second pipe 14b correspond, for example, to the axial position of the end of the communication portion 13e of the liner 13b on the combustion chamber 13c side. The first pipe 14a penetrates the casing 13a and extends to the outside of the casing 13a. Therefore, the rear end of the first pipe 14a is located outside the casing 13a. Meanwhile, the rear end of the second pipe 14b abuts against the inner surface of the casing 13a. For example, the rear end of the second pipe 14b is fixed to the inner surface of the casing 13a.

[0035] The internal space of the first pipe 14a corresponds to a first ammonia flow path 24. The first ammonia flow path 24 is defined by the inner circumferential surface of the first pipe 14a. The first ammonia flow path 24 is a flow path through which ammonia flows. In particular, the first ammonia flow path 24 is a flow path through which ammonia injected into the combustion chamber 13c via the injection valve 14c flows.

[0036] The first ammonia flow path 24 has a cylindrical shape. The first ammonia flow path 24 extends in the axial direction of the burner 14. The area of ​​a cross section of the first ammonia flow path 24 perpendicular to the axial direction is constant regardless of the axial position. The first ammonia flow path 24 is inserted into the opening 13f of the liner 13b.

[0037] The ammonia tank 15 is connected to the rear end of the first ammonia flow path 24 via the flow control valve 16. Therefore, ammonia is supplied from the ammonia tank 15 to the first ammonia flow path 24. Specifically, liquid ammonia is supplied to the first ammonia flow path 24.

[0038] An injection valve 14c is provided at the tip of the first pipe 14a. The injection valve 14c has a substantially cylindrical shape. The injection valve 14c is fitted to the tip side of the inner circumferential surface of the first pipe 14a. The tip of the first ammonia flow path 24 is defined by the injection valve 14c. The first ammonia flow path 24 communicates with the combustion chamber 13c via the injection valve 14c. The injection valve 14c is, for example, a pressure injection valve or an airflow injection valve. A pressure injection valve is a type of valve that atomizes liquid by utilizing the pressure difference between the inside and outside of the pressure injection valve. An airflow injection valve is a type of valve that generates a film of the liquid to be injected and atomizes the liquid by utilizing the shear force between the film and air.

[0039] As shown by arrow F2, the liquid ammonia supplied to the first ammonia flow path 24 flows in the axial direction through the first ammonia flow path 24. The liquid ammonia that has passed through the first ammonia flow path 24 is injected from the injector 14c into the combustion chamber 13c. The injection direction of the ammonia from the injector 14c substantially coincides with the axial direction of the burner 14. For example, when the ammonia is injected from the injector 14c in a conical shape while expanding radially, the extension direction of the central axis of the cone, which corresponds to the main injection direction, substantially coincides with the axial direction of the burner 14.

[0040] The space between the first pipe 14a and the second pipe 14b corresponds to a second ammonia flow path 25. The second ammonia flow path 25 is defined by the outer circumferential surface of the first pipe 14a and the inner circumferential surface of the second pipe 14b. The second ammonia flow path 25 is a flow path through which ammonia flows.

[0041] The second ammonia flow path 25 has a cylindrical shape. The second ammonia flow path 25 extends in the axial direction of the burner 14. The area of ​​a cross section of the second ammonia flow path 25 perpendicular to the axial direction is constant regardless of the axial position. The second ammonia flow path 25 is inserted through the opening 13f of the liner 13b.

[0042] The second ammonia flow path 25 covers the outer periphery of the first ammonia flow path 24. The axial range of the outer periphery of the first ammonia flow path 24 that is covered by the second ammonia flow path 25 is not particularly limited. It is sufficient that the second ammonia flow path 25 covers at least a partial range of the outer periphery of the first ammonia flow path 24. The outer periphery of the second ammonia flow path 25 is covered by the air flow path 23. The axial range of the outer periphery of the second ammonia flow path 25 that is covered by the air flow path 23 is not particularly limited. It is sufficient that the air flow path 23 covers at least a partial range of the outer periphery of the second ammonia flow path 25. The rear end of the second ammonia flow path 25 is closed by the casing 13a. However, the rear end of the second tube 14b may be located outside the casing 13a. In that case, the rear end of the second ammonia flow path 25 is closed by a member different from the casing 13a. The tip of the second ammonia flow path 25 is open and communicates with the combustion chamber 13c.

[0043] A plurality of through holes 26 are provided in the side surface of the first tube 14a that separates the first ammonia flow path 24 and the second ammonia flow path 25. However, the number of through holes 26 may be one. Details such as the arrangement of the through holes 26 will be described later with reference to FIG. 3. The through hole 26 communicates between the inside and outside of the first tube 14a. The through hole 26 is provided on the combustion chamber 13c side of the casing 13a. Therefore, the through hole 26 communicates between the first ammonia flow path 24 and the second ammonia flow path 25.

[0044] As shown by arrow F3, part of the liquid ammonia flowing through the first ammonia flow passage 24 leaks into the second ammonia flow passage 25 through the through-hole 26. Then, as shown by arrow F4, the liquid ammonia leaking into the second ammonia flow passage 25 flows in the axial direction through the second ammonia flow passage 25. At this time, the liquid ammonia flowing through the second ammonia flow passage 25 is heated by the high-temperature air flowing through the air flow passage 23. As a result, part or all of the liquid ammonia flowing through the second ammonia flow passage 25 is vaporized. The ammonia that has passed through the second ammonia flow passage 25 is injected into the combustion chamber 13c from the tip of the second ammonia flow passage 25. The injection direction of the ammonia from the second ammonia flow passage 25 substantially coincides with the axial direction of the burner 14.

[0045] As described above, the combustion device 10 includes the liner 13b having the opening 13f at an end thereof and the combustion chamber 13c formed therein, the first ammonia flow path 24 that is inserted into the opening 13f of the liner 13b and communicates with the combustion chamber 13c via the injection valve 14c and through which liquid ammonia is supplied, the second ammonia flow path 25 that covers the outer periphery of the first ammonia flow path 24, and the air flow path 23 that covers the outer periphery of the second ammonia flow path 25.

[0046] If, unlike this embodiment, the second ammonia flow path 25 were not disposed between the first ammonia flow path 24 and the air flow path 23, the liquid ammonia flowing in the first ammonia flow path 24 would be heated by the high-temperature air flowing in the air flow path 23. Therefore, there is a risk that the ammonia would vaporize in the first ammonia flow path 24. If the ammonia vaporizes in the first ammonia flow path 24, the amount of ammonia injected into the combustion chamber 13c would become unstable.

[0047] On the other hand, in the combustion device 10, the second ammonia flow path 25 is interposed between the first ammonia flow path 24 and the air flow path 23. This makes it possible to prevent the liquid ammonia flowing through the first ammonia flow path 24 from being heated by the air flowing through the air flow path 23. This makes it possible to prevent the vaporization of ammonia in the first ammonia flow path 24. In this way, the combustion device 10 makes it possible to prevent the vaporization of liquid ammonia used as fuel.

[0048] In particular, in the combustion device 10, liquid ammonia is supplied to the second ammonia flow path 25. As a result, some or all of the liquid ammonia flowing through the second ammonia flow path 25 is heated by the high-temperature air flowing through the air flow path 23 and vaporizes. Therefore, the liquid ammonia flowing through the first ammonia flow path 24 can be cooled by the heat of vaporization of the ammonia in the second ammonia flow path 25. Furthermore, a portion of the heat imparted to the liquid ammonia flowing through the second ammonia flow path 25 by the air flowing through the air flow path 23 is consumed as latent heat for vaporizing the ammonia and is not transferred to the ammonia flowing through the first ammonia flow path 24. Furthermore, the gaseous ammonia flowing through the second ammonia flow path 25 is heated by the air flowing through the air flow path 23 only for a short period of time until it is injected from the tip of the second ammonia flow path 25 into the combustion chamber 13c, thereby minimizing the temperature rise of the ammonia. Therefore, the vaporization of ammonia in the first ammonia flow path 24 can be more effectively suppressed.

[0049] Furthermore, the gaseous ammonia vaporized in the second ammonia flow path 25 is injected into the combustion chamber 13c from the tip of the second ammonia flow path 25. Gaseous ammonia is more combustible than liquid ammonia. Therefore, it is possible to improve the combustibility in the combustion chamber 13c.

[0050] In particular, the combustion device 10 includes a first pipe 14a that is a pipe that separates the first ammonia flow path 24 and the second ammonia flow path 25, and at least one through-hole 26 that is provided on a side surface of the first pipe 14a and that connects the first ammonia flow path 24 and the second ammonia flow path 25. As a result, a portion of the liquid ammonia flowing through the first ammonia flow path 24 leaks into the second ammonia flow path 25 through the through-hole 26. Therefore, it is possible to appropriately supply liquid ammonia to the second ammonia flow path 25.

[0051] In particular, in the combustion device 10, the through-holes 26 are provided within the range in the axial direction of the first tube 14a where the air flow path 23 exists. As a result, liquid ammonia sent from the through-holes 26 to the second ammonia flow path 25 collides with the inner circumferential surface of the second tube 14b, which is directly heated by the air flowing through the air flow path 23. This makes it possible to more effectively cool the second tube 14b. As a result, the temperature of the second tube 14b decreases, making it possible to suppress heating of the first tube 14a by radiant heat from the second tube 14b. This makes it possible to more effectively suppress heating of the ammonia in the first ammonia flow path 24, and more effectively suppress evaporation of the ammonia in the first ammonia flow path 24.

[0052] FIG. 3 is a cross-sectional view of the burner 14 of the combustion device 10 according to this embodiment, viewed in the axial direction. As shown in FIG. 3, a plurality of through holes 26 are provided at intervals in the circumferential direction on the side surface of the first tube 14a. Hereinafter, the plurality of through holes 26 provided at intervals in the circumferential direction will be referred to as a through hole group 27. In one through hole group 27, the positions of the through holes 26 in the axial direction of the first tube 14a coincide with each other. In the example of FIG. 2, two through hole groups 27, a through hole group 27a and a through hole group 27b, are provided at an interval in the axial direction of the first tube 14a. The through hole group 27b is located closer to the combustion chamber 13c than the through hole group 27a. However, the number of through hole groups 27 may be one or may be three or more.

[0053] In the combustion device 10, the number of through holes 26 and the positions of the through holes 26 in the circumferential direction are the same between the through hole group 27a and the through hole group 27b. In the example of Fig. 3, four through holes 26 are provided at equal intervals in the circumferential direction in each through hole group 27. However, the number of through holes 26 in each through hole group 27 may be other than four. In each through hole group 27, multiple through holes 26 may be provided at unequal intervals in the circumferential direction.

[0054] The through-holes 26 extend in the radial direction of the first pipe 14 a. Therefore, as shown by arrow F3, the liquid ammonia sent from the first ammonia flow path 24 to the through-holes 26 flows from the through-holes 26 to the second ammonia flow path 25 in the radial direction of the first pipe 14 a.

[0055] As described above, the combustion device 10 includes at least one through-hole group 27 including a plurality of through-holes 26 provided at intervals in the circumferential direction of the first tube 14a. This increases the amount of liquid ammonia supplied to the second ammonia flow path 25 compared to when there is only one through-hole 26 at the same axial position, improving the ability to cool the liquid ammonia flowing through the first ammonia flow path 24. Furthermore, in the second ammonia flow path 25, the amount of ammonia supplied is prevented from being biased in the circumferential direction.

[0056] In particular, in the combustion device 10, a plurality of through-hole groups 27 are provided at intervals in the axial direction of the first tube 14a. This increases the amount of liquid ammonia supplied to the second ammonia flow path 25 compared to when there is only one through-hole group 27, and improves the ability to cool the liquid ammonia flowing through the first ammonia flow path 24.

[0057] The combustion device 10 has been described above with reference to Figures 1 to 3. However, various modifications may be made to the example described above.

[0058] For example, although the above description is of an example in which the first tube 14 a and the second tube 14 b have a cylindrical shape, the cross-sectional shape of the first tube 14 a and the second tube 14 b perpendicular to the axial direction may be other than circular, for example, may be polygonal.

[0059] For example, in the above example, the central axis of the second tube 14b and the central axis of the first tube 14a are aligned with each other. However, the central axis of the second tube 14b and the central axis of the first tube 14a do not have to be aligned with each other.

[0060] For example, in the above description, an example has been described in which the cross-sectional areas of the first ammonia flow path 24 and the second ammonia flow path 25 taken perpendicular to the axial direction are constant regardless of the axial position. However, the cross-sectional area of ​​at least one of the first ammonia flow path 24 and the second ammonia flow path 25 taken perpendicular to the axial direction may change depending on the axial position. For example, the cross-sectional area of ​​the second ammonia flow path 25 taken perpendicular to the axial direction may become smaller as it approaches the combustion chamber 13c. In this case, the flow rate of ammonia can be increased at the tip end of the second ammonia flow path 25. Therefore, the ability to cool liquid ammonia flowing through the first ammonia flow path 24 is improved at the tip end of the burner 14, which is close to the combustion chamber 13c and is likely to be heated by the flame in the combustion chamber 13c. For example, the cross-sectional area of ​​the second ammonia flow path 25 taken perpendicular to the axial direction may become larger as it approaches the combustion chamber 13c. In this case, the pressure loss caused by the increase in the volume of ammonia due to vaporization can be reduced at the tip end of the second ammonia flow path 25.

[0061] For example, in the above example, the axial positions of the tips of the first tube 14a and the second tube 14b are aligned with each other. However, the axial positions of the tips of the first tube 14a and the second tube 14b do not have to be aligned with each other. For example, the axial position of the tip of the second tube 14b may be farther from the combustion chamber 13c than the axial position of the tip of the first tube 14a. In this case, the ammonia injected from the tip of the second tube 14b is mixed with the air flowing through the air flow path 23, improving the combustibility of the ammonia. For example, the axial position of the tip of the first tube 14a may be farther from the combustion chamber 13c than the axial position of the tip of the second tube 14b. In this case, the ratio of the volume of the second ammonia flow path 25 to the volume of the first ammonia flow path 24 becomes larger on the tip side of the burner 14, improving the ability to cool the liquid ammonia flowing through the first ammonia flow path 24.

[0062] For example, in the above description, the injection direction of ammonia from the injector 14c and the injection direction of ammonia from the second ammonia flow path 25 are aligned with each other. However, the injection direction of ammonia from the injector 14c and the injection direction of ammonia from the second ammonia flow path 25 do not have to be aligned with each other. For example, the injection direction of ammonia from the second ammonia flow path 25 may be inclined radially inward of the burner 14 as it advances toward the interior of the combustion chamber 13c.

[0063] For example, in the above description, an example has been described in which liquid ammonia is supplied from the first ammonia flow path 24 to the second ammonia flow path 25 via the through-hole 26. However, ammonia may be supplied to the second ammonia flow path 25 from a flow path other than the first ammonia flow path 24. For example, the through-hole 26 may be omitted from the burner 14. In this case, a flow path different from the flow path connected to the first ammonia flow path 24 is connected to the second ammonia flow path 25, and ammonia is supplied via this flow path. In this case, ammonia may be supplied to the second ammonia flow path 25 from the ammonia tank 15, or may be supplied from a supply source different from the ammonia tank 15. In this case, either liquid ammonia or gaseous ammonia may be supplied to the second ammonia flow path 25.

[0064] Combustion devices 10A, 10B, 10C, and 10D according to the respective modifications will be described below with reference to Figures 4 to 7. The combustion devices 10A, 10B, 10C, and 10D according to the respective modifications described below are provided in, for example, the gas turbine system 1, similar to the combustion device 10 described above.

[0065] 4 is a cross-sectional view of a burner 14A of a combustion device 10A according to a first modification, viewed in the axial direction. The combustion device 10A differs from the combustion device 10 described above in the arrangement of the through holes 26.

[0066] In FIG. 4 , the through holes 26 in the through hole group 27a are indicated by solid lines, and the through holes 26 in the through hole group 27b are indicated by dashed lines. As shown in FIG. 4 , in the combustion device 10A, the number of through holes 26 is the same between the through hole group 27a and the through hole group 27b. Specifically, in the example of FIG. 4 , four through holes 26 are provided at equal intervals in the circumferential direction in each through hole group 27. On the other hand, in the combustion device 10A, the positions of the through holes 26 in the circumferential direction are different between the through hole group 27a and the through hole group 27b. Specifically, in the example of FIG. 4 , the circumferential positions of each through hole 26 in the through hole group 27b are shifted by 45° relative to the circumferential positions of each through hole 26 in the through hole group 27a. Therefore, there are no pairs of through holes 26 whose circumferential positions are the same between the through hole group 27a and the through hole group 27b. However, the angle corresponding to the amount of circumferential positional deviation between each through hole 26 of the through hole group 27b and each through hole 26 of the through hole group 27a may be other than 45°.

[0067] In the combustion device 10 described above, the positions of the through holes 26 in the circumferential direction match between adjacent through-hole groups 27. Specifically, the positions of the through holes 26 in the circumferential direction match between through-hole group 27a and through-hole group 27b. Therefore, the flow of ammonia sent from the through holes 26 in through-hole group 27b to the second ammonia flow path 25 is obstructed by ammonia sent from the through holes 26 in through-hole group 27a to the second ammonia flow path 25 and flowing in the axial direction through the second ammonia flow path 25. Therefore, the ability of ammonia sent from the through holes 26 in through-hole group 27b to the second ammonia flow path 25 to cool the second tube 14b is reduced.

[0068] On the other hand, in the combustion device 10A, the positions of the through holes 26 in the circumferential direction differ between adjacent through-hole groups 27. Specifically, the positions of the through holes 26 in the circumferential direction differ between the through-hole group 27a and the through-hole group 27b. This prevents the flow of ammonia sent from the through holes 26 in the through-hole group 27b to the second ammonia flow path 25 from being hindered by ammonia sent from the through holes 26 in the through-hole group 27a to the second ammonia flow path 25 and flowing in the axial direction through the second ammonia flow path 25. This prevents a decrease in the ability of ammonia sent from the through holes 26 in the through-hole group 27b to cool the second tube 14b.

[0069] The combustion device 10A has been described above with reference to Fig. 4. However, the combustion device 10A may be modified in the same manner as the various modifications that may be made to the combustion device 10 described above.

[0070] 5 is a cross-sectional view of a burner 14B of a combustion device 10B according to a second modification, as viewed in the axial direction. In the combustion device 10B, the extending direction of the through-holes 26 is different from that of the combustion device 10 described above.

[0071] In the combustion device 10B, for example, the number of through holes 26 and the positions of the through holes 26 in the circumferential direction are the same between the through-hole group 27a and the through-hole group 27b. Specifically, in the example of Fig. 5, four through holes 26 are provided at equal intervals in the circumferential direction in each through-hole group 27. However, in the combustion device 10B, similar to the above-described combustion device 10A, the positions of the through holes 26 in the circumferential direction may be different between adjacent through-hole groups 27.

[0072] As shown in FIG. 5 , in the combustion device 10B, the through hole 26 extends in a direction intersecting the radial direction of the first pipe 14a when viewed in the axial direction of the first pipe 14a. The radial direction of the first pipe 14a is the extension direction of a line segment connecting the through hole 26 and the central axis of the first pipe 14a. In other words, the through hole 26 extends in a direction intersecting the direction from the through hole 26 toward the central axis of the first pipe 14a when viewed in the axial direction of the first pipe 14a. In other words, the central axis of the through hole 26 does not pass through the central axis of the first pipe 14a but is eccentric with respect to the central axis of the first pipe 14a. Specifically, in the example of FIG. 5 , the through hole 26 extends in a tangential direction of the first pipe 14a. However, the extension direction of the through hole 26 may be inclined with respect to the tangential direction of the first pipe 14a.

[0073] As described above, in the combustion device 10B, the through holes 26 extend in a direction intersecting the radial direction of the first tube 14a when viewed in the axial direction of the first tube 14a. Therefore, as shown by arrow F3, liquid ammonia sent from the first ammonia flow path 24 to the through holes 26 flows from the through holes 26 to the second ammonia flow path 25 in a direction intersecting the radial direction of the first tube 14a. As a result, as shown by arrow F5, the ammonia swirls in the circumferential direction in the second ammonia flow path 25. Therefore, in the second ammonia flow path 25, bias in the circumferential direction is more effectively suppressed.

[0074] Furthermore, centrifugal force due to the swirling acts on the ammonia in the second ammonia flow passage 25. Therefore, the ammonia injected from the tip of the second ammonia flow passage 25 advances into the combustion chamber 13c while spreading radially outward. This makes it possible to expand the area of ​​the flame formed in the combustion chamber 13c in the radial direction. In addition, the flow of ammonia injected from the injector 14c is prevented from being obstructed by the ammonia injected from the tip of the second ammonia flow passage 25.

[0075] The combustion device 10B has been described above with reference to Fig. 5. However, the combustion device 10B may be modified in the same manner as the various modifications that may be made to the combustion device 10 described above.

[0076] 6 is an enlarged view showing a burner 14C of a combustion apparatus 10C according to a third modified example. The combustion apparatus 10C corresponds to an example in which a swirl member 14d is added to the combustion apparatus 10 described above.

[0077] The swirl member 14d is a member that swirls the fluid. The swirl member 14d is provided in the second ammonia flow path 25. Therefore, the swirl member 14d imparts a swirling force in the circumferential direction of the burner 14C to the ammonia flowing through the second ammonia flow path 25. The swirl member 14d is, for example, a plurality of swirler blades. For example, in the second ammonia flow path 25, a plurality of swirler blades are provided at intervals in the circumferential direction. This imparts a swirling force to the ammonia flowing through the second ammonia flow path 25 as indicated by arrow F4.

[0078] As described above, in the combustion device 10C, the swirling member 14d that swirls the fluid is provided in the second ammonia flow path 25. This causes the ammonia to swirl in the circumferential direction in the second ammonia flow path 25. Therefore, in the second ammonia flow path 25, the supply amount of ammonia is more effectively prevented from being biased in the circumferential direction.

[0079] Furthermore, centrifugal force due to the swirling acts on the ammonia in the second ammonia flow passage 25. Therefore, the ammonia injected from the tip of the second ammonia flow passage 25 advances into the combustion chamber 13c while spreading radially outward. This makes it possible to expand the area of ​​the flame formed in the combustion chamber 13c in the radial direction. In addition, the flow of ammonia injected from the injector 14c is prevented from being obstructed by the ammonia injected from the tip of the second ammonia flow passage 25.

[0080] The combustion device 10C has been described above with reference to Fig. 6 . However, the combustion device 10C may be modified in the same manner as the various modifications that may be made to the combustion device 10 described above. In the combustion device 10C, similar to the combustion device 10A described above, the positions of the through holes 26 in the circumferential direction may be different between adjacent through-hole groups 27. In the combustion device 10C, similar to the combustion device 10B described above, the through holes 26 may extend in a direction intersecting the radial direction of the first pipe 14a when viewed in the axial direction of the first pipe 14a.

[0081] 7 is an enlarged view showing a burner 14D of a combustion device 10D according to a fourth modified example. As described above, ammonia may be supplied to the second ammonia passage 25 from a passage other than the first ammonia passage 24. The combustion device 10D corresponds to such an example.

[0082] As shown in Figure 7, the burner 14D includes a third tube 14e added to the burner 14 described above. The third tube 14e is arranged coaxially with the first tube 14a and radially inward relative to the first tube 14a. The third tube 14e is radially spaced apart from the first tube 14a. The outer diameter of the third tube 14e is smaller than the inner diameter of the first tube 14a. The first tube 14a covers the outer peripheral surface of the third tube 14e. In other words, the inner peripheral surface of the first tube 14a faces the outer peripheral surface of the third tube 14e.

[0083] The opening at the tip of the third pipe 14e is closed by the injection valve 14c. The internal space of the third pipe 14e is in communication with the combustion chamber 13c via the injection valve 14c. On the other hand, the space between the first pipe 14a and the third pipe 14e is closed by the injection valve 14c and does not communicate with the combustion chamber 13c. The third pipe 14e penetrates the casing 13a and extends to the outside of the casing 13a. Therefore, the rear end of the third pipe 14e is located outside the casing 13a.

[0084] In the combustion device 10D, the internal space of the third pipe 14e corresponds to the first ammonia flow path 24. The first ammonia flow path 24 is defined by the inner circumferential surface of the third pipe 14e. The ammonia tank 15 is connected to the rear end of the first ammonia flow path 24 via the flow control valve 16. Therefore, liquid ammonia is supplied from the ammonia tank 15 to the first ammonia flow path 24. Then, as shown by arrow F6, the liquid ammonia supplied to the first ammonia flow path 24 flows in the axial direction through the first ammonia flow path 24. The liquid ammonia that has passed through the first ammonia flow path 24 is injected into the combustion chamber 13c from the injection valve 14c.

[0085] In the combustion device 10D, the second ammonia flow path 25 includes an upstream flow path 25a, which is the space between the third pipe 14e and the first pipe 14a, and a downstream flow path 25b, which is the space between the first pipe 14a and the second pipe 14b. The upstream flow path 25a is defined by the outer circumferential surface of the third pipe 14e and the inner circumferential surface of the first pipe 14a. The downstream flow path 25b is defined by the outer circumferential surface of the first pipe 14a and the inner circumferential surface of the second pipe 14b. The upstream flow path 25a and the downstream flow path 25b each have a cylindrical shape. The second ammonia flow path 25 covers the outer periphery of the first ammonia flow path 24. The outer periphery of the second ammonia flow path 25 is covered by the air flow path 23.

[0086] The rear end of the downstream flow passage 25b is closed by the casing 13a. The front end of the downstream flow passage 25b is open and communicates with the combustion chamber 13c. The front end of the upstream flow passage 25a is closed by the injection valve 14c. The rear end of the upstream flow passage 25a is connected to the ammonia tank 15 via the flow control valve 17. Therefore, liquid ammonia is supplied from the ammonia tank 15 to the upstream flow passage 25a. Then, as shown by arrow F7, the liquid ammonia supplied to the upstream flow passage 25a flows in the axial direction through the upstream flow passage 25a.

[0087] As shown by arrow F8, the liquid ammonia flowing through the upstream flow passage 25a leaks into the downstream flow passage 25b through the through-hole 26. Then, as shown by arrow F9, the liquid ammonia that has leaked into the downstream flow passage 25b flows axially through the downstream flow passage 25b. At this time, the liquid ammonia flowing through the downstream flow passage 25b is heated by the high-temperature air flowing through the air passage 23. As a result, some or all of the liquid ammonia flowing through the downstream flow passage 25b is vaporized. The ammonia that has passed through the downstream flow passage 25b is injected into the combustion chamber 13c from the tip of the downstream flow passage 25b.

[0088] As explained above, the combustion device 10D, like the above-mentioned combustion device 10, comprises a liner 13b having an opening 13f at an end and having a combustion chamber 13c formed therein, a first ammonia flow path 24 that is inserted into the opening 13f of the liner 13b and communicates with the combustion chamber 13c via the injection valve 14c and to which liquid ammonia is supplied, a second ammonia flow path 25 that covers the outer periphery of the first ammonia flow path 24, and an air flow path 23 that covers the outer periphery of the second ammonia flow path 25. Therefore, the same effects as those of the above-mentioned combustion device 10 are achieved.

[0089] In particular, in the combustion device 10D, a flow path different from the flow path connected to the first ammonia flow path 24 is connected to the second ammonia flow path 25, and ammonia is supplied via this flow path. This makes it possible to separately adjust the amount of ammonia supplied to the first ammonia flow path 24 and the amount of ammonia supplied to the second ammonia flow path 25. This makes it easier to adjust the ability of the liquid flowing through the first ammonia flow path 24 to cool ammonia, and therefore makes it possible to more effectively suppress evaporation of ammonia in the first ammonia flow path 24.

[0090] The combustion device 10D has been described above with reference to Fig. 7. However, the combustion device 10D may be modified in the same manner as the various modifications that may be made to the combustion device 10 described above.

[0091] Although the embodiments of the present disclosure have been described above with reference to the accompanying drawings, it goes without saying that the present disclosure is not limited to such embodiments. It is clear that a person skilled in the art can conceive of various modifications and alterations within the scope of the claims, and it is understood that such modifications and alterations also fall within the technical scope of the present disclosure.

[0092] In the above, an example has been described in which the rotational power generated by the turbocharger 11 is used as energy to drive the generator 12 in the gas turbine system 1. However, in the gas turbine system 1, the rotational power generated by the turbocharger 11 may be used for other purposes. Examples of other uses include driving a moving body such as a ship.

[0093] The above describes an example in which the combustion apparatus 10, the combustion apparatus 10A, the combustion apparatus 10B, the combustion apparatus 10C, and the combustion apparatus 10D are used in the gas turbine system 1. However, the combustion apparatus 10, the combustion apparatus 10A, the combustion apparatus 10B, the combustion apparatus 10C, and the combustion apparatus 10D may be used in an apparatus other than the gas turbine system 1. An example of an apparatus other than the gas turbine system 1 is an industrial furnace or the like for changing the shape or properties of a material by combustion in a combustor.

[0094] 1 described above, the air sent from the compressor 11a to the combustor 13 passes between the outer peripheral surface of the liner 13b and the inner peripheral surface of the casing 13a and is then sent to the combustion chamber 13c. However, the path of the air sent from the compressor 11a to the combustor 13 is not limited to the turn-flow type example described above.

[0095] 1: Gas turbine system 10: Combustion device 10A: Combustion device 10B: Combustion device 10C: Combustion device 10D: Combustion device 13b: Liner 13f: Opening 14a: First pipe (pipe) 14c: Injector 14d: Swirling member 23: Air flow path 24: First ammonia flow path 25: Second ammonia flow path 26: Through hole 27: Group of through holes 27a: Group of through holes 27b: Group of through holes

Claims

1. A combustion device comprising: a liner having an opening at an end thereof and defining a combustion chamber therein; a first ammonia flow passage inserted into the opening of the liner, communicating with the combustion chamber via an injection valve and receiving liquid ammonia; a second ammonia flow passage covering an outer periphery of the first ammonia flow passage; and an air flow passage covering an outer periphery of the second ammonia flow passage.

2. The combustion device according to claim 1, comprising: a tube that separates the first ammonia flow path and the second ammonia flow path; and at least one through-hole that is provided on a side surface of the tube and communicates the first ammonia flow path with the second ammonia flow path.

3. The combustion device according to claim 2, wherein the through hole is provided within a range in which the air flow path exists in the axial direction of the tube.

4. The combustion apparatus of claim 2, further comprising at least one group of through holes including a plurality of said through holes spaced circumferentially about said tube.

5. A combustion apparatus as claimed in claim 4, wherein a plurality of said groups of through holes are provided at intervals in the axial direction of said tube.

6. The combustion device according to claim 5, wherein the positions of the through holes in the circumferential direction are different between adjacent groups of the through holes.

7. The combustion device according to claim 2, wherein the through hole extends in a direction intersecting a radial direction of the tube when viewed in an axial direction of the tube.

8. The combustion device according to claim 1, wherein the second ammonia flow passage is provided with a swirling member for swirling the fluid.

9. The combustion device according to claim 1, wherein the second ammonia flow passage is supplied with liquid ammonia.

10. A gas turbine system comprising a combustion device according to any one of claims 1 to 9.

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