Combustion device and gas turbine system

Abstract

A combustion device (10) is provided with: a liner (13b) having an opening (13f) provided at an end thereof and having a combustion chamber (13c) formed therein; a first ammonia flow path (24) that is inserted through an opening (13f) of the liner (13b), communicates with the combustion chamber (13c) via an injection valve (14c), and is supplied with liquid ammonia; 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).

Description

Technical Field

[0001] This disclosure relates to a combustion device and a gas turbine system. This application claims the benefit of priority based on Japanese Patent Application No. 2023-119402, filed on July 21, 2023, the contents of which are incorporated herein by reference. Background Technology

[0002] Gas turbine systems that generate power by burning fuel in a combustor are being used. As a gas turbine system, for example, as disclosed in Patent Document 1, there are systems that use ammonia as fuel. By using ammonia as fuel, carbon dioxide emissions can be suppressed.

[0003] Existing technical documents

[0004] Patent documents

[0005] Patent Document 1: Japanese Patent Application Publication No. 2016-191507 Summary of the Invention

[0006] The problem that the invention aims to solve

[0007] As a gas turbine system, there exists a system where ammonia is vaporized in a vaporizer and then supplied to the combustion chamber of the burner. The use of a vaporizer is a major cause of increased equipment costs and start-up times in gas turbine systems. Therefore, the idea of ​​supplying liquid ammonia to the combustion chamber without using a vaporizer is considered. In this case, before the ammonia is injected into the combustion chamber, the liquid ammonia in the burner's flow path is heated by the high-temperature air supplied to the combustion chamber, raising concerns about ammonia vaporization occurring within the burner's flow path. Such ammonia vaporization could become a major cause of instability in the ammonia injection rate.

[0008] The purpose of this disclosure is to provide a combustion device and a gas turbine system that can suppress the vaporization of liquid ammonia used as fuel.

[0009] Solution for solving the problem

[0010] To address the aforementioned issues, the combustion apparatus of this disclosure comprises: a bushing having an opening at its end and forming a combustion chamber therein; a first ammonia flow path inserted through the opening of the bushing, communicating with the combustion chamber via an injection valve, and supplied with liquid ammonia; a second ammonia flow path covering the outer periphery of the first ammonia flow path; and an air flow path covering the outer periphery of the second ammonia flow path.

[0011] It may also include: a tube that divides a first ammonia flow path into a second ammonia flow path; and at least one through hole disposed on the side of the tube and connecting the first ammonia flow path into the second ammonia flow path.

[0012] Alternatively, the through hole can be located axially along the pipe within the area where the airflow path exists.

[0013] Alternatively, it may have at least one group of through holes, comprising a plurality of through holes spaced apart in the circumferential direction of the tube.

[0014] Alternatively, multiple through-hole groups can be arranged at intervals along the axial direction of the pipe.

[0015] Alternatively, the positions of the through holes in the circumferential direction may differ between adjacent groups of through holes.

[0016] Alternatively, the through hole can extend in a direction that intersects the radial direction of the pipe when viewed along the axial direction of the pipe.

[0017] Alternatively, a swirling component that causes the fluid to swirl can be provided in the second ammonia flow path.

[0018] Alternatively, liquid ammonia can be supplied to the second ammonia flow path.

[0019] To address the aforementioned issues, the gas turbine system disclosed herein includes the aforementioned combustion apparatus.

[0020] Invention Effects

[0021] According to this disclosure, it is possible to suppress the vaporization of ammonia, a liquid used as fuel. Attached Figure Description

[0022] Figure 1 This is a schematic diagram showing the structure of a gas turbine system according to an embodiment of the present disclosure.

[0023] Figure 2 This is an enlarged view of the burner of the combustion device according to an embodiment of the present disclosure.

[0024] Figure 3 This is a cross-sectional view of the burner of the combustion device according to an embodiment of the present disclosure, viewed along the axial direction.

[0025] Figure 4 This is a cross-sectional view of the burner of the combustion device in the first modified example, viewed along the axial direction.

[0026] Figure 5 This is a cross-sectional view of the burner of the combustion device in the second modified example, viewed along the axial direction.

[0027] Figure 6 This is an enlarged view of the burner of the combustion device in the third modified example.

[0028] Figure 7 This is an enlarged view of the burner of the combustion device in the fourth modified example. Detailed Implementation

[0029] Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. The dimensions, materials, and other specific values ​​shown in the embodiments are merely examples to facilitate understanding and, unless specifically stated otherwise, do not limit the present disclosure. Furthermore, in this specification and the accompanying drawings, elements having substantially the same function or structure are labeled with the same symbols, thereby omitting repeated descriptions. Additionally, elements not directly related to the present disclosure are omitted from the illustrations.

[0030] Figure 1 This is a schematic diagram showing the structure of the gas turbine system 1 according to this embodiment. Figure 1 As shown, the gas turbine system 1 includes a turbocharger 11, a generator 12, a burner 13, a burner 14, an ammonia tank 15, and a flow control valve 16.

[0031] The burner 13, burner 14, ammonia tank 15 and flow control valve 16 in the gas turbine system 1 are included in the combustion device 10.

[0032] The turbocharger 11 has a compressor 11a and a turbine 11b. The impellers of the compressor 11a and the turbine 11b rotate as a single unit. The impellers of the compressor 11a and the turbine 11b are connected by a shaft.

[0033] Compressor 11a is provided in the intake passage 21 connected to burner 13. Air supplied to burner 13 flows through intake passage 21. An air intake port (not shown) for drawing in air from the outside is provided at the upstream end of intake passage 21. Air drawn in from the air intake port is delivered to burner 13 by compressor 11a. Compressed air is then discharged downstream by compressor 11a.

[0034] A turbine 11b is disposed in an exhaust flow path 22 connected to a burner 13. Exhaust gas discharged from the burner 13 flows through the exhaust flow path 22. An exhaust port (not shown) is provided at the downstream end of the exhaust flow path 22 to discharge the exhaust gas to the outside. The exhaust gas discharged from the burner 13 is conveyed to the exhaust port via the turbine 11b. The turbine 11b generates rotational power by being rotated by the exhaust gas through its impeller.

[0035] Generator 12 is connected to booster 11. Generator 12 uses the rotational power generated by booster 11 to generate electricity.

[0036] The burner 13 has a housing 13a, a bushing 13b, and a combustion chamber 13c. The housing 13a has a generally cylindrical shape. The bushing 13b is disposed inside the housing 13a. The bushing 13b has a generally cylindrical shape. The bushing 13b and the housing 13a are arranged coaxially. The combustion chamber 13c is formed inside the bushing 13b. That is, the internal space of the bushing 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.

[0037] As described later, fuel and air are supplied to combustion chamber 13c. Ammonia is primarily used as fuel for combustion within combustion chamber 13c. However, other fuels such as natural gas or hydrogen may also be used as fuel supplied to combustion chamber 13c besides ammonia. The exhaust gases generated by combustion within combustion chamber 13c are discharged into exhaust passage 22.

[0038] The bushing 13b has a main body portion 13d. The main body portion 13d has a generally cylindrical shape. A combustion chamber 13c is formed inside the main body portion 13d. A connecting portion 13e is provided at the end of the main body portion 13d. The connecting portion 13e connects the outside of the bushing 13b and the combustion chamber 13c. The connecting portion 13e has a cylindrical shape and is coaxially arranged with the main body portion 13d. The outer diameter of the connecting portion 13e is smaller than the outer diameter of the main body portion 13d. The inner diameter of the connecting portion 13e is smaller than the inner diameter of the main body portion 13d. However, the inner diameter of the connecting portion 13e may decrease or increase as it moves towards the main body portion 13d. Various components, such as swirling blades for forming a swirling airflow, may be provided inside the connecting portion 13e. An opening 13f is provided at the end of the connecting portion 13e on the side opposite to the main body portion 13d. Thus, the opening 13f is provided at the end of the bushing 13b. Furthermore, Figure 1 The bushing 13b shown can also be divided into multiple parts. In this case, the components can also be... Figure 1 Different components of the bushing 13b shown are referred to by different names. For example, the connecting part 13e may be composed of components different from those of other parts of the bushing 13b, or may be referred to by a name different from that of the other parts.

[0039] An airflow path 23 is formed between the inner surface of the housing 13a and the outer surface of the bushing 13b. An intake flow path 21 is connected to the airflow path 23. Air is supplied from the compressor 11a to the airflow path 23 via the intake flow path 21. The airflow path 23 communicates with the opening 13f of the bushing 13b. A burner 14 is inserted through the opening 13f of the bushing 13b. As indicated by arrow F1, the air supplied to the airflow path 23 is injected into the combustion chamber 13c through the opening 13f of the bushing 13b after passing through the airflow path 23. Specifically, the air supplied to the airflow path 23 is injected into the combustion chamber 13c through the space between the inner circumferential surface of the connecting portion 13e and the outer circumferential surface of the burner 14.

[0040] Burner 14 injects ammonia as fuel into combustion chamber 13c of burner 13. Burner 14 has a generally cylindrical shape. Hereinafter, the combustion chamber 13c side of burner 14 will be described ( Figure 1 The right side of the burner 14 is called the front end side, which is the side opposite to the combustion chamber 13c side. Figure 1 The left side (of the burner) is referred to as the rear end side. The front end of the burner 14 is inserted into the opening 13f of the bushing 13b. The burner 14 penetrates the housing 13a and extends to the outside of the housing 13a. The rear end of the burner 14 is located outside the housing 13a. For details about the burner 14, please refer to [reference needed]. Figure 2 and Figure 3 To be described later.

[0041] 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 control valve 16 is provided in the flow path connecting the ammonia tank 15 and the burner 14. The ammonia stored in the ammonia tank 15 is supplied to the burner 14. The flow control valve 16 controls the flow rate of ammonia supplied from the ammonia tank 15 to the burner 14. Alternatively, a [further details about the valve are needed for accurate translation]. Figure 1 Various devices shown in the illustrations (e.g., shut-off valves, check valves, various sensors, etc.) are omitted.

[0042] Figure 2 This is an enlarged view showing the burner 14 of the combustion apparatus 10 in this embodiment. Figure 2 As shown, the burner 14 has a first tube 14a, a second tube 14b, and an injection valve 14c. As will be described later, Figure 2 This example is just one instance; it can also be used to illustrate... Figure 2 Examples of applying various changes.

[0043] exist Figure 2In this example, 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 is arranged radially outward relative to the first tube 14a. The second tube 14b is radially separated 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. That is, the inner peripheral surface of the second tube 14b faces the outer peripheral surface of the first tube 14a.

[0044] exist Figure 2 In the example, 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, the axial direction, and the circumferential direction of the burner 14 will also be referred to as radial, axial, and circumferential, respectively.

[0045] The first tube 14a and the second tube 14b are inserted into the opening 13f of the bushing 13b. The axial position of the front end of the first tube 14a and the second tube 14b is, for example, aligned with the axial position of the end of the bushing 13b on the combustion chamber 13c side of the connecting portion 13e. The first tube 14a extends through the housing 13a to the outside of the housing 13a. Therefore, the rear end of the first tube 14a is located outside the housing 13a. On the other hand, the rear end of the second tube 14b abuts against the inner surface of the housing 13a. For example, the rear end of the second tube 14b is fixed to the inner surface of the housing 13a.

[0046] The internal space of the first pipe 14a corresponds to the 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 the flow path for ammonia to flow. In particular, the first ammonia flow path 24 is the flow path for ammonia injected into the combustion chamber 13c via the injection valve 14c.

[0047] The first ammonia flow path 24 has a cylindrical shape. The first ammonia flow path 24 extends along the axial direction of the burner 14. The area of ​​the cross-section of the first ammonia flow path 24 orthogonal 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 bushing 13b.

[0048] An ammonia tank 15 is connected to the downstream end of the first ammonia flow path 24 via a 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.

[0049] An injection valve 14c is provided at the front end of the first pipe 14a. The injection valve 14c has a generally cylindrical shape. The injection valve 14c is fitted into the front end side of the inner circumferential surface of the first pipe 14a. The front end of the first ammonia flow path 24 is divided by the injection valve 14c. The first ammonia flow path 24 is connected to the combustion chamber 13c via the injection valve 14c. The injection valve 14c is, for example, a pressure injection valve or a gas injection valve. A pressure injection valve is a type of valve that uses the pressure difference between the inside and outside of the pressure injection valve to atomize the liquid. A gas injection valve is a type of valve that generates a film of the liquid to be injected and uses the shear force of the film and air to atomize the liquid.

[0050] As indicated by arrow F2, liquid ammonia supplied to the first ammonia flow path 24 flows axially within the first ammonia flow path 24. Liquid ammonia passing through the first ammonia flow path 24 is injected from the injection valve 14c into the combustion chamber 13c. The injection direction of the ammonia from the injection valve 14c is approximately aligned with the axial direction of the burner 14. For example, when ammonia is injected in a conical shape while expanding radially from the injection valve 14c, the extension direction of the central axis of this cone, corresponding to the main injection direction, is approximately aligned with the axial direction of the burner 14.

[0051] The space between the first pipe 14a and the second pipe 14b corresponds to the 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 the flow path for ammonia.

[0052] The second ammonia flow path 25 has a cylindrical shape. The second ammonia flow path 25 extends along the axial direction of the burner 14. The area of ​​the cross-section of the second ammonia flow path 25 orthogonal to the axial direction is constant regardless of the axial position. The second ammonia flow path 25 is inserted into the opening 13f of the bushing 13b.

[0053] The second ammonia flow path 25 covers the outer periphery of the first ammonia flow path 24. Furthermore, the axial range of the outer periphery of the first ammonia flow path 24 covered by the second ammonia flow path 25 is not particularly limited. The second ammonia flow path 25 only needs to cover at least a portion 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. Furthermore, the axial range of the outer periphery of the second ammonia flow path 25 covered by the air flow path 23 is not particularly limited. The air flow path 23 only needs to cover at least a portion 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 housing 13a. However, the rear end of the second pipe 14b may also be located outside the housing 13a. In this case, the rear end of the second ammonia flow path 25 is closed by a component different from the housing 13a. The front end of the second ammonia flow path 25 is open and communicates with the combustion chamber 13c.

[0054] Multiple through holes 26 are provided on the side of the first pipe 14a that divides the first ammonia flow path 24 and the second ammonia flow path 25. However, the number of through holes 26 can also be one. For details regarding the configuration of the through holes 26, please refer to [reference needed]. Figure 3 As will be described later. The through-hole 26 connects the interior and exterior of the first pipe 14a. The through-hole 26 is located on the combustion chamber 13c side relative to the housing 13a. Therefore, the through-hole 26 connects the first ammonia flow path 24 and the second ammonia flow path 25.

[0055] As indicated by arrow F3, a portion of the liquid ammonia flowing in the first ammonia flow path 24 leaks out through the through-hole 26 into the second ammonia flow path 25. Then, as indicated by arrow F4, the liquid ammonia leaking into the second ammonia flow path 25 flows axially within the second ammonia flow path 25. At this time, the liquid ammonia flowing in the second ammonia flow path 25 is heated by the high-temperature air flowing in the air flow path 23. As a result, part or all of the liquid ammonia flowing in the second ammonia flow path 25 is vaporized. The ammonia that has passed through the second ammonia flow path 25 is injected into the combustion chamber 13c from the front end of the second ammonia flow path 25. The injection direction of the ammonia from the second ammonia flow path 25 is approximately aligned with the axial direction of the burner 14.

[0056] As described above, the combustion device 10 includes: a bushing 13b having an opening 13f at its end and forming a combustion chamber 13c inside; a first ammonia flow path 24 inserted through the opening 13f of the bushing 13b, communicating with the combustion chamber 13c via an injection valve 14c, and supplied with liquid ammonia; a second ammonia flow path 25 covering the outer periphery of the first ammonia flow path 24; and an air flow path 23 covering the outer periphery of the second ammonia flow path 25.

[0057] In a scenario different from this embodiment, where a second ammonia flow path 25 is not provided between the first ammonia flow path 24 and the air flow path 23, the liquid ammonia flowing in the first ammonia flow path 24 is heated by the high-temperature air flowing in the air flow path 23. Therefore, there is a concern that ammonia vaporization may occur within the first ammonia flow path 24. If ammonia vaporizes within the first ammonia flow path 24, the injection rate of ammonia into the combustion chamber 13c becomes unstable.

[0058] On the other hand, in the combustion device 10, the second ammonia flow path 25 is located between the first ammonia flow path 24 and the air flow path 23. Therefore, the liquid ammonia flowing in the first ammonia flow path 24 can be prevented from being heated by the air flowing in the air flow path 23. Thus, the vaporization of ammonia within the first ammonia flow path 24 can be suppressed. In this way, according to the combustion device 10, the vaporization of liquid ammonia used as fuel can be suppressed.

[0059] In particular, liquid ammonia is supplied to the second ammonia flow path 25 in the combustion device 10. As a result, part or all of the liquid ammonia flowing in the second ammonia flow path 25 is vaporized by heating with the high-temperature air flowing in the air flow path 23. Therefore, the heat of vaporization of the ammonia in the second ammonia flow path 25 can cool the liquid ammonia flowing in the first ammonia flow path 24. Furthermore, a portion of the heat imparted to the liquid ammonia flowing in the second ammonia flow path 25 by the air flowing in the air flow path 23 is consumed as latent heat for vaporizing the ammonia and is not transferred to the ammonia flowing in the first ammonia flow path 24. Additionally, the gaseous ammonia flowing in the second ammonia flow path 25 is heated by the air flowing in the air flow path 23 for only a short time before being injected into the combustion chamber 13c from the front end of the second ammonia flow path 25, thus reducing the temperature rise of the ammonia. Therefore, the vaporization of ammonia in the first ammonia flow path 24 can be suppressed more effectively.

[0060] Furthermore, the ammonia gas, vaporized within the second ammonia flow path 25, is injected into the combustion chamber 13c from the front end of the second ammonia flow path 25. Gaseous ammonia is more flammable than liquid ammonia. Therefore, the combustibility in the combustion chamber 13c can be improved.

[0061] In particular, the combustion device 10 includes: a first pipe 14a, which divides a first ammonia flow path 24 and a second ammonia flow path 25; and at least one through hole 26, which is provided on the side of the first pipe 14a and connects the first ammonia flow path 24 and the second ammonia flow path 25. Thus, a portion of the liquid ammonia flowing in the first ammonia flow path 24 leaks into the second ammonia flow path 25 through the through hole 26. Therefore, liquid ammonia can be appropriately supplied to the second ammonia flow path 25.

[0062] In particular, in the combustion device 10, the through hole 26 is provided axially within the range of the air flow path 23 of the first tube 14a. As a result, the liquid ammonia supplied from the through hole 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 in the air flow path 23. Therefore, the second tube 14b can be cooled more effectively. Consequently, the temperature of the second tube 14b decreases, suppressing the heating of the first tube 14a by radiant heat from the second tube 14b. Therefore, the heating of ammonia within the first ammonia flow path 24 can be more effectively suppressed, and the vaporization of ammonia within the first ammonia flow path 24 can be more effectively suppressed.

[0063] Figure 3 This is a cross-sectional view of the burner 14 of the combustion device 10 in this embodiment, viewed along the axial direction. (See attached image.) Figure 3As shown, a plurality of through holes 26 are provided circumferentially spaced on the side of the first tube 14a. Hereinafter, the plurality of through holes 26 provided circumferentially spaced will be referred to as a through hole group 27. In a through hole group 27, the positions of the through holes 26 along the axial direction of the first tube 14a are aligned with each other. Figure 2 In this example, the two through-hole groups 27, 27a and 27b, are spaced apart axially in the first tube 14a. Through-hole group 27b is located on the combustion chamber 13c side relative to through-hole group 27a. However, the number of through-hole groups 27 can be one or more.

[0064] In the combustion device 10, the number of through holes 26 and their circumferential positions are consistent between through hole groups 27a and 27b. Figure 3 In the example, in each through-hole group 27, four through holes 26 are provided at equal intervals along the circumference. However, the number of through holes 26 in each through-hole group 27 may be more than four. In each through-hole group 27, multiple through holes 26 may also be provided at unequal intervals along the circumference.

[0065] The through-hole 26 extends radially along the first pipe 14a. Therefore, as indicated by arrow F3, the liquid ammonia delivered from the first ammonia flow path 24 to the through-hole 26 flows radially from the through-hole 26 to the second ammonia flow path 25 along the first pipe 14a.

[0066] As described above, the combustion device 10 includes at least one group 27 of through holes 26 arranged circumferentially spaced apart in the first tube 14a. Therefore, compared to the case where the number of through holes 26 at the same axial position is one, the supply amount of ammonia to the liquid in the second ammonia flow path 25 is increased, and the ability to cool the liquid flowing in the first ammonia flow path 24 is improved. Furthermore, in the second ammonia flow path 25, deviations in the circumferential supply of ammonia are suppressed.

[0067] In particular, in the combustion device 10, a plurality of through-hole groups 27 are arranged at intervals along the axial direction of the first pipe 14a. As a result, compared with the case where the number of through-hole groups 27 is one, the supply of ammonia to the liquid in the second ammonia flow path 25 is further increased, and the ability of ammonia to cool the liquid flowing in the first ammonia flow path 24 is further improved.

[0068] In the above, refer to Figures 1 to 3 The combustion device 10 has been described. However, various modifications can be made to the example described above.

[0069] For example, the example described above, where the first tube 14a and the second tube 14b have a cylindrical shape, is illustrated. However, the shape of the cross-section perpendicular to the axial direction of the first tube 14a and the second tube 14b can also be a shape other than a circle, for example, it can also be a polygon.

[0070] For example, the example described above shows that the central axis of the second tube 14b and the central axis of the first tube 14a are aligned. However, the central axis of the second tube 14b and the central axis of the first tube 14a may not be aligned.

[0071] For example, in the above description, an example was given where the area of ​​the cross-section orthogonal to the axial direction of the first ammonia flow path 24 and the second ammonia flow path 25 is constant regardless of the axial position. However, the area of ​​the cross-section orthogonal to the axial direction of at least one of the first ammonia flow path 24 and the second ammonia flow path 25 can also vary depending on the axial position. For example, the area of ​​the cross-section orthogonal to the axial direction of the second ammonia flow path 25 can be smaller the closer it is to the combustion chamber 13c. In this case, the ammonia flow rate can be increased at the front end of the second ammonia flow path 25. Therefore, the ability to cool the liquid ammonia flowing in the first ammonia flow path 24 is improved at the front end of the burner 14, which is close to the combustion chamber 13c and easily heated by the flame in the combustion chamber 13c. For example, the area of ​​the cross-section orthogonal to the axial direction of the second ammonia flow path 25 can be larger the closer it is to the combustion chamber 13c. In this case, the pressure drop caused by the increase in the volume of ammonia accompanying vaporization can be reduced at the front end of the second ammonia flow path 25.

[0072] For example, in the above description, an example was given where the axial positions of the tips of the first tube 14a and the second tube 14b are aligned. However, the axial positions of the tips of the first tube 14a and the second tube 14b may not be aligned. For example, the axial position of the tip of the second tube 14b may be further away 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 mixes with the air flowing in the air flow path 23, and the combustibility of the ammonia is improved. For example, the axial position of the tip of the first tube 14a may also be further away from the combustion chamber 13c than the axial position of the tip of the second tube 14b. In this case, on the tip side of the burner 14, the volume ratio of the second ammonia flow path 25 to the volume of the first ammonia flow path 24 becomes larger, and the ability to cool the liquid ammonia flowing in the first ammonia flow path 24 is improved.

[0073] For example, in the above description, an example was given where the injection direction of ammonia from injection valve 14c and the injection direction of ammonia from the second ammonia flow path 25 are consistent. However, the injection direction of ammonia from injection valve 14c and the injection direction of ammonia from the second ammonia flow path 25 may not be consistent. For example, the injection direction of ammonia from the second ammonia flow path 25 may be a direction that tilts radially inward toward the burner 14 as it moves toward the interior of combustion chamber 13c.

[0074] For example, the example described above illustrates the supply of liquid ammonia from the first ammonia flow path 24 to the second ammonia flow path 25 via the through-hole 26. However, ammonia may also 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 it may be supplied from a different supply source than the ammonia tank 15. In this case, either liquid ammonia or gaseous ammonia may be supplied to the second ammonia flow path 25.

[0075] The following is for reference Figures 4-7 The combustion devices 10A, 10B, 10C, and 10D of each modified example will be described. The combustion devices 10A, 10B, 10C, and 10D of each modified example described below are similar to the combustion device 10 described above and are, for example, installed in the gas turbine system 1.

[0076] Figure 4 This is a cross-sectional view of the burner 14A of the combustion device 10A in the first modified example, viewed along the axial direction. In the combustion device 10A, the arrangement of the through hole 26 is different from that of the combustion device 10 described above.

[0077] exist Figure 4 In the diagram, the through hole 26 of through hole group 27a is shown in solid line, and the through hole 26 of through hole group 27b is shown in dashed line. For example... Figure 4 As shown, 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 Figure 4 In the example, in each through-hole group 27, four through-holes 26 are provided at equal intervals in the circumferential direction. On the other hand, in the combustion device 10A, the positions of the through-holes 26 in the circumferential direction are different between through-hole groups 27a and 27b. Specifically, in Figure 4In the example, the circumferential positions of each through hole 26 in through hole group 27b are offset by 45° relative to the circumferential positions of each through hole 26 in through hole group 27a. Therefore, there is no pair of through holes 26 with the same circumferential position between through hole groups 27a and 27b. However, the angle corresponding to the offset of the circumferential position between each through hole 26 in through hole group 27b and each through hole 26 in through hole group 27a can also be an angle other than 45°.

[0078] In the combustion device 10 described above, the circumferential through-holes 26 are aligned between adjacent through-hole groups 27. Specifically, the circumferential through-holes 26 are aligned between through-hole groups 27a and 27b. Therefore, the flow of ammonia from the through-holes 26 of through-hole group 27b to the second ammonia flow path 25 is obstructed by the ammonia from the through-holes 26 of through-hole group 27a to the second ammonia flow path 25 and flowing axially within the second ammonia flow path 25. Consequently, the ability of the ammonia supplied from the through-holes 26 of through-hole group 27b to the second ammonia flow path 25 to cool the second pipe 14b is reduced.

[0079] On the other hand, in the combustion device 10A, the positions of the circumferential through holes 26 differ between adjacent through hole groups 27. Specifically, the positions of the circumferential through holes 26 differ between through hole groups 27a and 27b. This prevents the flow of ammonia from the through holes 26 of through hole group 27b to the second ammonia flow path 25 from being obstructed by ammonia from the through holes 26 of through hole group 27a flowing axially in the second ammonia flow path 25. Therefore, the reduction in the ability of the ammonia supplied from the through holes 26 of through hole group 27b to the second ammonia flow path 25 to cool the second pipe 14b is suppressed.

[0080] In the above, refer to Figure 4 The combustion device 10A has been described. However, the same modifications that can be made to the combustion device 10A as those described above for the combustion device 10 can also be applied.

[0081] Figure 5 This is a cross-sectional view of the burner 14B of the combustion device 10B in the second modified example, viewed along the axial direction. In the combustion device 10B, the extension direction of the through hole 26 is different from that of the combustion device 10 described above.

[0082] In the combustion device 10B, for example, between the through-hole group 27a and the through-hole group 27b, the number of through-holes 26 and their positions in the circumferential direction are consistent. Specifically, in Figure 5In the example, in each through-hole group 27, four through holes 26 are provided at equal intervals in the circumferential direction. However, in the combustion device 10B, similar to the combustion device 10A described above, the positions of the through holes 26 in the circumferential direction may differ between adjacent through-hole groups 27.

[0083] like Figure 5 As shown, in the combustion device 10B, when viewed axially along the first tube 14a, the through hole 26 extends in a direction intersecting the radial direction of the first tube 14a. The radial direction of the first tube 14a is the direction in which the line segment connecting the through hole 26 and the central axis of the first tube 14a extends. That is, when viewed axially along the first tube 14a, the through hole 26 extends in a direction intersecting the direction from the through hole 26 toward the central axis of the first tube 14a. In other words, the central axis of the through hole 26 does not pass through the central axis of the first tube 14a, but is eccentric relative to the central axis of the first tube 14a. Specifically, in Figure 5 In this example, the through hole 26 extends along the tangential direction of the first tube 14a. However, the extending direction of the through hole 26 may also be inclined relative to the tangential direction of the first tube 14a.

[0084] As described above, in the combustion device 10B, when viewed axially along the first pipe 14a, the through hole 26 extends in a direction intersecting the radial direction of the first pipe 14a. Therefore, as indicated by arrow F3, the liquid ammonia supplied from the first ammonia flow path 24 to the through hole 26 flows from the through hole 26 to the second ammonia flow path 25 in a direction intersecting the radial direction of the first pipe 14a. Consequently, as indicated by arrow F5, the ammonia circumferentially swirls in the second ammonia flow path 25. Therefore, in the second ammonia flow path 25, circumferential deviations in the ammonia supply can be more effectively suppressed.

[0085] Furthermore, in the second ammonia flow path 25, centrifugal force, accompanied by swirling motion, acts on the ammonia. Therefore, the ammonia injected from the front end of the second ammonia flow path 25 travels within the combustion chamber 13c while diffusing radially outward. This allows the area of ​​the flame formed within the combustion chamber 13c to expand radially. Additionally, the flow of ammonia injected from the injection valve 14c can be prevented from being obstructed by the ammonia injected from the front end of the second ammonia flow path 25.

[0086] In the above, refer to Figure 5 The combustion device 10B has been described. However, the same modifications that can be made to the combustion device 10B as those made to the combustion device 10 described above may also be applied.

[0087] Figure 6 This is an enlarged view of the burner 14C of the combustion device 10C in the third modified example. The combustion device 10C is an example of the combustion device 10 described above with the addition of a rotating component 14d.

[0088] The swirling component 14d is a component that causes the fluid to swirl. The swirling component 14d is disposed in the second ammonia flow path 25. Therefore, the swirling component 14d imparts a circumferential swirling force to the ammonia flowing in the second ammonia flow path 25, similar to that of the burner 14C. The swirling component 14d consists of, for example, multiple swirling blades referred to as a hydrocyclone. For example, in the second ammonia flow path 25, the multiple swirling blades are arranged at circumferential intervals. This imparts a swirling force to the ammonia flowing in the second ammonia flow path 25, as indicated by arrow F4.

[0089] As described above, in the combustion device 10C, a swirling member 14d is provided in the second ammonia flow path 25 to swirl the fluid. Therefore, ammonia swirls circumferentially in the second ammonia flow path 25. Consequently, circumferential deviations in the ammonia supply can be more effectively suppressed in the second ammonia flow path 25.

[0090] Furthermore, in the second ammonia flow path 25, centrifugal force, accompanied by swirling motion, acts on the ammonia. Therefore, the ammonia injected from the front end of the second ammonia flow path 25 travels radially outward within the combustion chamber 13c. Thus, the area of ​​the flame formed within the combustion chamber 13c can be expanded radially. Additionally, the flow of ammonia injected from the injection valve 14c can be prevented from being obstructed by the ammonia injected from the front end of the second ammonia flow path 25.

[0091] In the above, refer to Figure 6 Combustion device 10C has been described. However, the same modifications that can be applied to combustion device 10C as those applied to combustion device 10 described above can also be made to combustion device 10. In combustion device 10C, similar to combustion device 10A described above, the positions of the through holes 26 in the circumferential direction may differ between adjacent through hole groups 27. In combustion device 10C, similar to combustion device 10B described above, when viewed along the axial direction of the first tube 14a, the through holes 26 may extend in a direction that intersects the radial direction of the first tube 14a.

[0092] Figure 7 This is an enlarged view of the burner 14D of the combustion device 10D in the fourth modified example. As described above, ammonia can also be supplied to the second ammonia flow path 25 from a flow path other than the first ammonia flow path 24. The combustion device 10D corresponds to such an example.

[0093] like Figure 7 As shown, in burner 14D, a third tube 14e is added to the burner 14 described above. The third tube 14e is coaxial with the first tube 14a and is arranged radially inward relative to the first tube 14a. The third tube 14e is radially separated 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. That is, the inner peripheral surface of the first tube 14a faces the outer peripheral surface of the third tube 14e.

[0094] The opening at the front end of the third pipe 14e is sealed by the injection valve 14c. The internal space of the third pipe 14e is connected to 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 blocked by the injection valve 14c and is not connected to the combustion chamber 13c. The third pipe 14e penetrates the housing 13a and extends to the outside of the housing 13a. Therefore, the rear end of the third pipe 14e is located outside the housing 13a.

[0095] 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. An ammonia tank 15 is connected to the rear end of the first ammonia flow path 24 via a flow control valve 16. Therefore, liquid ammonia is supplied from the ammonia tank 15 to the first ammonia flow path 24. Then, as indicated by arrow F6, the liquid ammonia supplied to the first ammonia flow path 24 flows axially within 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.

[0096] In the combustion device 10D, the space between the third pipe 14e and the first pipe 14a, i.e., the upstream flow path 25a, and the space between the first pipe 14a and the second pipe 14b, i.e., the downstream flow path 25b, are contained within the second ammonia flow path 25. The upstream flow path 25a is defined by the outer peripheral surface of the third pipe 14e and the inner peripheral surface of the first pipe 14a. The downstream flow path 25b is defined by the outer peripheral surface of the first pipe 14a and the inner peripheral surface of the second pipe 14b. The upstream flow path 25a and the downstream flow path 25b are both cylindrical. 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.

[0097] The rear end of the downstream flow path 25b is closed by the housing 13a. The front end of the downstream flow path 25b is open and communicates with the combustion chamber 13c. The front end of the upstream flow path 25a is closed by the injection valve 14c. An ammonia tank 15 is connected to the rear end of the upstream flow path 25a via a flow control valve 17. Therefore, liquid ammonia is supplied from the ammonia tank 15 to the upstream flow path 25a. And, as indicated by arrow F7, the liquid ammonia supplied to the upstream flow path 25a flows axially in the upstream flow path 25a.

[0098] As indicated by arrow F8, liquid ammonia flowing in the upstream side flow path 25a leaks out through the through-hole 26 into the downstream side flow path 25b. Then, as indicated by arrow F9, the liquid ammonia leaking into the downstream side flow path 25b flows axially in the downstream side flow path 25b. At this time, the liquid ammonia flowing in the downstream side flow path 25b is heated by the high-temperature air flowing in the air flow path 23. As a result, part or all of the liquid ammonia flowing in the downstream side flow path 25b is vaporized. The ammonia that has passed through the downstream side flow path 25b is injected into the combustion chamber 13c from the front end of the downstream side flow path 25b.

[0099] As described above, the combustion device 10D, like the combustion device 10 described above, includes: a bushing 13b having an opening 13f at its end and forming a combustion chamber 13c inside; a first ammonia flow path 24 inserted through the opening 13f of the bushing 13b, communicating with the combustion chamber 13c via an injection valve 14c, and supplied with liquid ammonia; a second ammonia flow path 25 covering the outer periphery of the first ammonia flow path 24; and an air flow path 23 covering the outer periphery of the second ammonia flow path 25. Therefore, it achieves the same effect as the combustion device 10 described above.

[0100] In particular, in the combustion device 10D, a different flow path than the one connected to the first ammonia flow path 24 is connected to the second ammonia flow path 25, and ammonia is supplied through this flow path. This allows for the separate adjustment of the ammonia supply to the first ammonia flow path 24 and the ammonia supply to the second ammonia flow path 25. Consequently, the ability to cool the liquid flowing in the first ammonia flow path 24 is easily adjusted, thus more effectively suppressing the vaporization of ammonia within the first ammonia flow path 24.

[0101] In the above, refer to Figure 7 The combustion device 10D has been described. However, the same modifications that can be made to the combustion device 10D as those made to the combustion device 10 described above may also be applied.

[0102] The above side refers to the appendix. Figure 1 While embodiments of this disclosure have been described, it is self-evident that this disclosure is not limited to these embodiments. It is obvious that those skilled in the art will conceive of various modifications or alterations within the scope of the claims, and these should be understood to also fall within the technical scope of this disclosure.

[0103] In the above description, an example was given of using the rotational power generated by the turbocharger 11 in the gas turbine system 1 as energy to drive the generator 12. However, the rotational power generated by the turbocharger 11 in the gas turbine system 1 can also be used for other purposes. Examples of other uses include driving moving bodies such as ships.

[0104] In the above description, examples of combustion devices 10, 10A, 10B, 10C, and 10D used in gas turbine system 1 have been given. However, combustion devices 10, 10A, 10B, 10C, and 10D can also be used in devices other than gas turbine system 1. Examples of devices other than gas turbine system 1 include industrial furnaces used to change the shape or properties of materials through combustion in a burner.

[0105] In the above explanation Figure 1 In the example, the air supplied from compressor 11a to burner 13 is delivered to combustion chamber 13c after passing between the outer peripheral surface of bushing 13b and the inner peripheral surface of housing 13a. However, the path of the air supplied from compressor 11a to burner 13 is not limited to the above-described example with a turning flow pattern.

[0106] Symbol Explanation

[0107] 1—Gas turbine system; 10—Combustion device; 10A—Combustion device; 10B—Combustion device; 10C—Combustion device; 10D—Combustion device; 13b—Bushing; 13f—Opening; 14a—First pipe; 14c—Injection valve; 14d—Rotating component; 23—Air flow path; 24—First ammonia flow path; 25—Second ammonia flow path; 26—Through hole; 27—Through hole group; 27a—Through hole group; 27b—Through hole group.

Claims

1. A combustion device, characterized in that, have: The bushing has an opening at its end and forms a combustion chamber inside; A first ammonia flow path, which is inserted into the opening of the bushing, communicates with the combustion chamber via an injection valve, and is supplied with liquid ammonia; The second ammonia flow path covers the outer periphery of the first ammonia flow path; as well as An airflow path that covers the outer periphery of the second ammonia flow path.

2. The combustion device according to claim 1, characterized in that, have: The tube divides the first ammonia flow path and the second ammonia flow path; and At least one through hole is provided on the side of the tube and connects the first ammonia flow path and the second ammonia flow path.

3. The combustion device according to claim 2, characterized in that, The through hole is located axially along the pipe within the range of the airflow path.

4. The combustion device according to claim 2, characterized in that, It has at least one group of through holes, which includes a plurality of through holes spaced apart in the circumferential direction of the tube.

5. The combustion device according to claim 4, characterized in that, The plurality of through holes are arranged at intervals along the axial direction of the tube.

6. The combustion device according to claim 5, characterized in that, The positions of the through holes in the circumferential direction differ between adjacent groups of through holes.

7. The combustion device according to claim 2, characterized in that, The through hole extends in a direction that intersects the radial direction of the tube when viewed along the axial direction of the tube.

8. The combustion device according to claim 1, characterized in that, A swirling component is provided in the second ammonia flow path to circulate the fluid.

9. The combustion device according to claim 1, characterized in that, Liquid ammonia is supplied to the second ammonia flow path.

10. A gas turbine system, characterized in that, The combustion device is equipped with any one of claims 1 to 9.

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