Combustion system

Abstract

A combustion system (10) is provided with a combustion chamber (13c), a cylindrical air chamber (31) having an injection hole (31) a facing the inside of the combustion chamber (13c), a fuel supply flow path (41) connected to the air chamber (31), and an air supply flow path (32) connected to a side surface of the air chamber (31).

Description

Technical Field

[0001] The present disclosure relates to a combustion system. This application claims priority based on Japanese Patent Application No. 2022-119760 filed on July 27, 2022, and incorporates the contents thereof into this application. Background Art

[0002] A gas turbine system is used that generates power by burning fuel in a combustor. As a combustion system of a gas turbine system, there is a combustion system that uses hydrogen as fuel, as disclosed in Patent Document 1, for example. By using hydrogen as fuel, carbon dioxide emissions are suppressed.

[0003] Prior art literature

[0004] Patent Literature

[0005] Patent Document 1: Japanese Patent Application Publication No. 2015-014400 Summary of the invention

[0006] Problems to be solved by the invention

[0007] In the combustion system, it is required to protect the burner from the flame. For example, the combustion speed of hydrogen is very fast compared to the combustion speed of other fuels such as natural gas. Therefore, when hydrogen is used as a fuel, flashback (i.e., the phenomenon of flame backflow into the burner) is likely to occur due to uneven mixing of hydrogen and air. In addition, the temperature of the flame formed by the combustion of hydrogen is higher than the temperature of the flame formed by the combustion of other fuels. Therefore, the burner is easily damaged by the flame. Therefore, when hydrogen is used as a fuel, it is very necessary to protect the burner from the flame.

[0008] An object of the present disclosure is to provide a combustion system capable of protecting a burner from flames.

[0009] Solutions to Solve Problems

[0010] To solve the above problems, the combustion system disclosed in the present invention includes: a combustion chamber; a cylindrical air chamber having an injection hole facing the combustion chamber; a fuel supply flow path connected to the air chamber; and an air supply flow path connected to a side surface of the air chamber.

[0011] The air supply flow path may be connected to the air chamber eccentrically with respect to a central axis of the air chamber.

[0012] The air chamber may have a cylindrical shape.

[0013] The air supply flow path may include a plurality of flow paths connected to one air chamber.

[0014] The air chamber, the fuel supply flow path, and the air supply flow path may be formed in a burner plate that blocks an end portion of the combustion chamber.

[0015] A fuel manifold may be formed on the burner plate.

[0016] Effects of the Invention

[0017] According to the present disclosure, the burner can be protected from flames. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 : is a schematic diagram showing the configuration of a gas turbine system according to an embodiment of the present disclosure.

[0019] Figure 2 This is a diagram of the burner plate according to the embodiment of the present disclosure as viewed from the combustion chamber side.

[0020] Figure 3 yes Figure 2 Cross-sectional view of section A2-A2 in FIG.

[0021] Figure 4 yes Figure 3 Cross-sectional view of section A3-A3 in FIG.

[0022] Figure 5 This is a diagram of a burner plate according to a first modified example as viewed from the combustion chamber side.

[0023] Figure 6 yes Figure 5 A sectional view of the A4-A4 section in FIG.

[0024] Figure 7 yes Figure 6 Cross-sectional view of section A5-A5 in FIG.

[0025] Figure 8 This is a diagram of a burner plate according to a second modified example as viewed from the combustion chamber side.

[0026] Fig. 9 yes Figure 8 Cross-sectional view of section A6-A6 in FIG.

[0027] Fig.10 yes Fig. 9 Cross-sectional view of section A7-A7 in FIG.

[0028] Fig.11 This is a diagram showing an example of a connection relationship between an air chamber and an air supply flow path according to an embodiment of the present disclosure.

[0029] Fig.12 This is a diagram showing an example of a connection relationship between an air chamber and an air supply flow path according to an embodiment of the present disclosure.

[0030] Fig.13 This is a diagram showing an example of a connection relationship between an air chamber and an air supply flow path according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0031] The embodiments of the present disclosure are described below with reference to the accompanying drawings. The dimensions, materials, and other specific values ​​shown in the embodiments are only examples for ease of understanding and do not limit the present disclosure unless otherwise specified. In this specification and the accompanying drawings, elements with substantially the same function and structure will be represented by the same reference numerals to omit repeated descriptions, and illustrations of elements that are not directly related to the present disclosure will be omitted.

[0032] Figure 1 Schematic diagram showing the structure of the gas turbine system 1 of this embodiment. Figure 1 As shown, the gas turbine system 1 includes a supercharger 11 , a generator 12 , a combustor 13 , a burner 14 , a hydrogen tank 15 , and a flow control valve 16 .

[0033] In the gas turbine system 1 , a combustor 13 , a burner 14 , a hydrogen tank 15 , and a flow control valve 16 are included in a combustion system 10 .

[0034] The supercharger 11 includes a compressor 11a and a turbine 11b. The compressor 11a and the turbine 11b rotate as a whole. The compressor 11a and the turbine 11b are connected by a rotating shaft.

[0035] The compressor 11a is provided in the intake air passage 21 connected to the burner 13. The air supplied to the burner 13 flows in the intake air passage 21. An air intake port (not shown) for sucking air from the outside is provided at the upstream end of the intake air passage 21. The air sucked from the air intake port is delivered to the burner 13 by the compressor 11a. The compressor 11a compresses the air and discharges it to the downstream side.

[0036] The turbine 11b is provided in the exhaust flow path 22 connected to the burner 13. The exhaust gas discharged from the burner 13 flows through the exhaust flow path 22. An exhaust port (not shown) for discharging the exhaust gas to the outside is provided at the downstream end of the exhaust flow path 22. The exhaust gas discharged from the burner 13 passes through the turbine 11b and is delivered to the exhaust port. The turbine 11b generates rotational power by utilizing the rotation of the exhaust gas.

[0037] The generator 12 is connected to the supercharger 11. The generator 12 uses the rotational power generated by the supercharger 11 to generate electric power.

[0038] The burner 13 has an outer shell 13a, an inner shell 13b, and a combustion chamber 13c. The outer shell 13a has a substantially cylindrical shape. The inner shell 13b is provided inside the outer shell 13a. The inner shell 13b has a substantially cylindrical shape. The inner shell 13b is coaxially arranged with the outer shell 13a. A combustion chamber 13c is formed inside the inner shell 13b. That is, the internal space of the inner shell 13b is equivalent to the combustion chamber 13c. The combustion chamber 13c is a substantially cylindrical space. The exhaust flow path 22 is connected to the combustion chamber 13c.

[0039] As described later, hydrogen and air are supplied to the combustion chamber 13c. In the combustion chamber 13c, hydrogen is used as a fuel and is burned. However, other fuels besides hydrogen may be used as fuel. Exhaust gas generated by combustion in the combustion chamber 13c is discharged to the exhaust flow path 22. A space S is formed between the inner surface of the outer shell 13a and the outer surface of the inner liner 13b. The intake flow path 21 is connected to the space S. Air is supplied from the compressor 11a to the space S via the intake flow path 21. At the end of the inner liner 13b ( Figure 1 The left end portion of the inner container 13b has an opening. The burner 14 is inserted through the opening at the end portion of the inner container 13b.

[0040] The burner 14 has a burner plate 14a and a plurality of fuel supply pipes 14b. The burner plate 14a blocks the opening at the end of the inner shell 13b. That is, the burner plate 14a blocks the end of the combustion chamber 13c. The burner plate 14a has a circular plate shape. The fuel supply pipe 14b is connected to the surface of the burner plate 14a that is opposite to the combustion chamber 13c. The fuel supply pipe 14b penetrates the outer shell 13a and extends to the outside of the outer shell 13a. Figure 1 In FIG. 1 , three fuel supply pipes 14b are shown. However, the number of fuel supply pipes 14b is not limited.

[0041] As described later, hydrogen is delivered to the fuel supply pipe 14b. Then, hydrogen is delivered to the burner plate 14a via the fuel supply pipe 14b. Figure 1 As shown by the dot-dash arrow in , the air delivered to the space S is delivered to the inside of the burner plate 14a from the surface of the burner plate 14a on the opposite side to the combustion chamber 13c after passing through the space S. However, a through hole may be provided on the side of the inner liner 13b, and air may be delivered from the space S to the inside of the burner plate 14a through the through hole. As described later, the hydrogen delivered to the burner plate 14a is sprayed into the combustion chamber 13c while being mixed with air.

[0042] Hydrogen is stored in the hydrogen tank 15. In addition, in the hydrogen tank 15, hydrogen can be liquid or gas. The hydrogen tank 15 is connected to the flow control valve 16 via the flow path 23. The flow control valve 16 is connected to each fuel supply pipe 14b of the burner 14 via the flow path 24. The hydrogen stored in the hydrogen tank 15 is supplied to the fuel supply pipe 14b via the flow path 23, the flow control valve 16 and the flow path 24. The flow control valve 16 controls (i.e., adjusts) the flow rate of hydrogen supplied from the hydrogen tank 15 to the fuel supply pipe 14b. By adjusting the opening of the flow control valve 16, the supply amount of hydrogen from the hydrogen tank 15 to the fuel supply pipe 14b is adjusted.

[0043] Hereinafter, the circumferential direction of the combustion chamber 13c and the burner plate 14a is also referred to as the circumferential direction, the radial direction of the combustion chamber 13c and the burner plate 14a is also referred to as the radial direction, and the axial direction of the combustion chamber 13c and the burner plate 14a is also referred to as the axial direction.

[0044] Figure 2 This is a diagram showing the burner plate 14a as viewed from the combustion chamber 13c side (specifically, from Figure 1 (viewed from the direction of arrow A1). Figure 3 yes Figure 2 A sectional view of the A2-A2 section in FIG. That is, Figure 3 This is a cross-sectional view of the burner plate 14a as viewed from the radial direction. Figure 4 yes Figure 3 A sectional view of the A3-A3 section in FIG. That is, Figure 4 This is a cross-sectional view of the burner plate 14a as viewed from the axial direction.

[0045] like Figures 2 to 4 As shown, an air chamber 31 , an air supply flow path 32 , an air manifold 33 , a fuel supply flow path 41 , and a fuel manifold 42 are formed in the burner plate 14 a .

[0046] A plurality of air chambers 31 are provided at intervals in the circumferential direction on the outer peripheral side of the burner plate 14a. Figures 2 to 4 In the example, a plurality of air chambers 31 are arranged at equal intervals along the circumferential direction. However, a plurality of air chambers 31 may be arranged at non-equal intervals along the circumferential direction. In addition, the number of air chambers 31 is not limited to Figures 2 to 4 .

[0047] The air chamber 31 is cylindrical. Figures 2 to 4 In the example of FIG. 3 , the air chamber 31 has a cylindrical shape. However, the air chamber 31 may have a shape other than a cylindrical shape (for example, an elliptical cylindrical shape, etc.) as long as it is cylindrical. Figures 2 to 4In the example, the air chamber 31 extends along the axial direction of the combustion chamber 13c. That is, the central axis of the air chamber 31 is an axis along the axial direction of the combustion chamber 13c. However, the central axis of the air chamber 31 may be inclined relative to the axial direction of the combustion chamber 13c. The air chamber 31 opens to the surface of the burner plate 14a that is opposite to the combustion chamber 13c. This opening is equivalent to the injection hole 31a facing the combustion chamber 13c. As described later, the hydrogen and air supplied to the air chamber 31 are mixed with each other and injected into the combustion chamber 13c from the injection hole 31a.

[0048] The air supply passage 32 is connected to the air chamber 31. Figures 2 to 4 In the example of FIG. 1 , one air supply passage 32 is connected to one air chamber 31. However, as described later, a plurality of air supply passages 32 may be connected to one air chamber 31. Each air supply passage 32 is connected to an air manifold 33. Air is supplied from the air manifold 33 to each air supply passage 32. Then, air is supplied to the air chamber 31 via the air supply passage 32.

[0049] Specifically, the air supply passage 32 is connected to the side of the air chamber 31. Thus, the air supplied from the air supply passage 32 to the air chamber 31 circulates in the air chamber 31 along the circumferential direction of the air chamber 31. In particular, Figure 4 As shown, the air supply passage 32 is connected to the air chamber 31 eccentrically with respect to the central axis of the air chamber 31. That is, the extension line of the air supply passage 32 does not pass through the central axis of the air chamber 31. As a result, the air supplied from the air supply passage 32 to the air chamber 31 is more likely to swirl in the air chamber 31 along the circumferential direction of the air chamber 31.

[0050] exist Figure 4 In the example, the air supply flow path 32 is connected to the air chamber 31 in the tangential direction of the air chamber 31. However, in a case where the air supply flow path 32 is connected to the air chamber 31 eccentrically with respect to the central axis of the air chamber 31, the connection direction of the air supply flow path 32 and the air chamber 31 may not be the tangential direction of the air chamber 31. In addition, the air supply flow path 32 may not be eccentric with respect to the central axis of the air chamber 31. Even in that case, the air can still be made to swirl in the air chamber 31 by appropriately setting the flow direction of the air flowing from the air supply flow path 32 into the air chamber 31 or the shape of the air chamber 31. Figure 3 From the viewpoint of Figure 3 From the viewpoint of FIG. 1 , the air supply flow path 32 may be inclined with respect to a direction perpendicular to the axial direction of the burner plate 14 a .

[0051] The air manifold 33 and the space S in the burner 13 (see Figure 1 ) is connected. Figures 2 to 4In the example of FIG. 1 , the air manifold 33 has a circular ring shape extending in the circumferential direction of the burner plate 14a. However, the shape of the air manifold 33 is not limited to Figures 2 to 4 The air manifold 33 opens on the surface of the burner plate 14a opposite to the combustion chamber 13c. Air is supplied to the air manifold 33 from the space S in the burner 13. Each air supply flow path 32 is connected to the air manifold 33. Figures 2 to 4 In the example of FIG. 3 , the air manifold 33 is disposed radially outward relative to the air chamber 31, and each air supply flow path 32 extends radially inward from the air manifold 33. However, the air manifold 33 may be disposed radially inward relative to the air chamber 31. In that case, each air supply flow path 32 extends radially outward from the air manifold 33.

[0052] As described above, each air chamber 31 is connected to the air manifold 33 via each air supply flow path 32. Therefore, air is supplied from the air manifold 33 to each air chamber 31 via each air supply flow path 32. Then, in the air chamber 31, a swirling flow of air swirling in the circumferential direction of the air chamber 31 is generated.

[0053] The fuel supply flow path 41 is connected to the air chamber 31. Figures 2 to 4 In the example, one fuel supply flow path 41 is connected to one air chamber 31. However, a plurality of fuel supply flow paths 41 may be connected to one air chamber 31. Each fuel supply flow path 41 is connected to a fuel manifold 42. Hydrogen is supplied from the fuel manifold 42 to each fuel supply flow path 41. Then, hydrogen is supplied to the air chamber 31 via the fuel supply flow path 41. Specifically, the fuel supply flow path 41 is connected to the bottom surface of the air chamber 31 (i.e., the surface opposite to the injection hole 31a). However, the fuel supply flow path 41 may also be connected to a portion of the air chamber 31 other than the bottom surface.

[0054] The fuel manifold 42 and the fuel supply pipe 14b (see Figure 1 ) is connected. Figures 2 to 4 In the example of FIG. 1 , the fuel manifold 42 has a circular ring shape extending in the circumferential direction of the burner plate 14a. However, the shape of the fuel manifold 42 is not limited to Figures 2 to 4 The fuel manifold 42 is connected to the fuel supply pipe 14b via a flow path (not shown) opened on the surface opposite to the combustion chamber 13c side of the burner plate 14a. Hydrogen is supplied from the fuel supply pipe 14b to the fuel manifold 42. Each fuel supply flow path 41 is connected to the fuel manifold 42. Figures 2 to 4 In the example of FIG. 4 , the fuel manifold 42 is arranged in the axial direction relative to the air chamber 31, and each fuel supply flow path 41 extends axially from the fuel manifold 42. However, the positional relationship between the fuel manifold 42 and the air chamber 31 is not limited to Figures 2 to 4 .

[0055] As described above, each air chamber 31 is connected to the fuel manifold 42 via each fuel supply flow path 41. Therefore, hydrogen is supplied from the fuel manifold 42 to each air chamber 31 via each fuel supply flow path 41. Then, the hydrogen delivered to the air chamber 31 is quickly mixed with the air by the swirling flow of the air generated in the air chamber 31, and is injected into the combustion chamber 13c from the injection hole 31a together with the air.

[0056] As described above, the combustion system 10 includes a combustion chamber 13c, a cylindrical air chamber 31 having an injection hole 31a facing the combustion chamber 13c, a fuel supply flow path 41 connected to the air chamber 31, and an air supply flow path 32 connected to the side of the air chamber 31. Thus, the fuel (in the above example, hydrogen) delivered to the air chamber 31 is quickly mixed with the air by the swirling flow of the air generated in the air chamber 31, and is injected into the combustion chamber 13c from the injection hole 31a together with the air. Therefore, it is possible to supply the fuel to the combustion chamber 13c in a state of being effectively mixed with the air without providing a space for premixing the fuel and the air, thereby suppressing the burner 14 from being exposed to the high-temperature combustion gas. As a result, the burner 14 can be protected from the flame.

[0057] Furthermore, since the fuel is supplied to the combustion chamber 13c in a state of being effectively mixed with the air, the generation of NOx can be suppressed by appropriately adjusting the amount of air supplied and lowering the temperature of the flame. Furthermore, in each air chamber 31, the mixing of the fuel and the air is performed independently, thereby increasing the degree of freedom in configuring the injection hole 31a. Furthermore, since the generation of a swirling flow of the combustion gas swirling in the circumferential direction in the combustion chamber 13c can be suppressed, the generation of a circulating flow as the flow of the combustion gas toward the burner plate 14a through the vicinity of the central axis of the swirling flow (i.e., the vicinity of the central axis of the combustion chamber 13c) can be suppressed.

[0058] In particular, in the combustion system 10, the air supply passage 32 is connected to the air chamber 31 eccentrically with respect to the central axis of the air chamber 31. Thus, the air sent from the air supply passage 32 to the air chamber 31 is more likely to swirl in the air chamber 31 along the circumferential direction of the air chamber 31. Therefore, in the air chamber 31, the fuel and the air can be mixed more efficiently.

[0059] In particular, in the combustion system 10, the air chamber 31 has a cylindrical shape. Therefore, the air sent from the air supply flow path 32 to the air chamber 31 is more likely to swirl in the air chamber 31 along the circumferential direction of the air chamber 31. Therefore, in the air chamber 31, fuel and air can be mixed more efficiently.

[0060] In particular, in the combustion system 10, the air chamber 31, the fuel supply flow path 41, and the air supply flow path 32 are formed in the burner plate 14a that blocks the end of the combustion chamber 13c. Therefore, by integrally forming the burner plate 14a using a metal lamination technique or the like, the air chamber 31, the fuel supply flow path 41, and the air supply flow path 32 can be easily formed. By integrally forming the burner plate 14a in this way, the structure of the burner 14 is simplified, the burner 14 is miniaturized, and the manufacturing cost of the burner 14 is reduced, compared with a case where the components forming the air chamber 31, the fuel supply flow path 41, and the air supply flow path 32 are separate from the burner plate 14a. In addition, hydrogen leakage from the joint portion of the components is suppressed. In addition, cracks generated in the joint portion due to thermal stress are suppressed.

[0061] In particular, in the combustion system 10, the fuel manifold 42 is formed in the burner plate 14a. Therefore, by integrally forming the burner plate 14a using a metal lamination technique or the like, the fuel manifold 42 can be easily formed. By integrally forming the burner plate 14a in this way, the structure of the burner 14 is simplified, the burner 14 is miniaturized, and the manufacturing cost of the burner 14 is reduced, compared with the case where the component forming the fuel manifold 42 is separated from the burner plate 14a. In addition, hydrogen leakage from the joint portion of the components is suppressed. In addition, cracks generated in the joint portion due to thermal stress are suppressed. In addition, the number of fuel supply pipes 14b can be reduced.

[0062] Furthermore, each of the parts obtained by dividing the burner plate 14a (for example, each of the parts divided at a predetermined angle in the circumferential direction) may be integrally formed and the obtained parts may be assembled by metal lamination technology, etc. In that case, it is also possible to reduce the manufacturing cost of the burner 14, suppress hydrogen leakage from the joint part of the parts, and suppress cracks in the joint part due to thermal stress.

[0063] Refer to the following Figures 5 to 10 Gas turbine systems according to the respective modifications will be described. In the gas turbine systems according to the respective modifications described below, the structures other than the burner plate are the same as those of the gas turbine system 1 described above, and thus the description thereof will be omitted.

[0064] Figure 5 This is a diagram of a burner plate 14aA according to a first modified example as viewed from the combustion chamber 13c side. Figure 6 yes Figure 5 A sectional view of the A4-A4 section in FIG. That is, Figure 6 This is a cross-sectional view of the burner plate 14aA as viewed from the radial direction. Figure 7 yes Figure 6 A sectional view of the A5-A5 section in FIG. That is, Figure 7 This is a cross-sectional view of the burner plate 14aA as viewed from the axial direction.

[0065] like Figures 5 to 7As shown, a combustion system 10A of a gas turbine system 1a according to a first modification includes a burner plate 14aA. The burner plate 14aA is different from the burner plate 14a described above in the number and arrangement of air chambers 31 .

[0066] like Figures 5 to 7 As shown, as in the burner plate 14 a , the air chamber 31 , the air supply flow path 32 , the air manifold 33 , the fuel supply flow path 41 , and the fuel manifold 42 are formed in the burner plate 14 aA.

[0067] The burner plate 14aA includes a plurality of air chambers 31-1 and a plurality of air chambers 31-2 as the air chambers 31. The plurality of air chambers 31-1 are air chambers 31 formed at radially outermost positions among the plurality of air chambers 31 of the burner plate 14aA and arranged at intervals in the circumferential direction. The plurality of air chambers 31-2 are air chambers 31 formed at radially inner positions than the plurality of air chambers 31-1 among the plurality of air chambers 31 of the burner plate 14aA and arranged at intervals in the circumferential direction.

[0068] The burner plate 14aA includes an air manifold 33-1 and an air manifold 33-2 as the air manifold 33. The air manifold 33-1 and the air manifold 33-2 each have an annular shape extending in the circumferential direction of the burner plate 14aA. The air manifold 33-1 is located at the radially outermost side of the plurality of air manifolds 33 formed on the burner plate 14aA. The air manifold 33-2 is located radially inward of the air manifold 33-1.

[0069] Each air chamber 31-1 is connected to the air manifold 33-1 via the air supply flow path 32-1. Therefore, air is supplied from the air manifold 33-1 to each air chamber 31-1 via each air supply flow path 32-1. Each air chamber 31-2 is connected to the air manifold 33-2 via the air supply flow path 32-2. Therefore, air is supplied from the air manifold 33-2 to each air chamber 31-2 via each air supply flow path 32-2.

[0070] The burner plate 14aA includes a fuel manifold 42-1 and a fuel manifold 42-2 as the fuel manifolds 42. The fuel manifold 42-1 and the fuel manifold 42-2 each have an annular shape extending in the circumferential direction of the burner plate 14aA. The fuel manifold 42-1 is located radially outermost among the plurality of fuel manifolds 42 formed on the burner plate 14aA. The fuel manifold 42-2 is located radially inward of the fuel manifold 42-1.

[0071] Each air chamber 31-1 is connected to a fuel manifold 42-1 via a fuel supply flow path 41. Therefore, hydrogen is supplied from the fuel manifold 42-1 to each air chamber 31-1. Each air chamber 31-2 is connected to a fuel manifold 42-2 via a fuel supply flow path 41. Therefore, hydrogen is supplied from the fuel manifold 42-2 to each air chamber 31-2.

[0072] As described above, like the combustion system 10, the combustion system 10A includes the combustion chamber 13c, the cylindrical air chamber 31 having the injection hole 31a facing the combustion chamber 13c, the fuel supply flow path 41 connected to the air chamber 31, and the air supply flow path 32 connected to the side of the air chamber 31. Thus, the same effect as the combustion system 10 can be obtained.

[0073] In particular, in the combustion system 10A, a plurality of groups of air chambers 31 arranged at intervals in the circumferential direction are arranged at intervals in the radial direction. As a result, the number of air chambers 31 can be increased, so that the fuel supplied to the burner plate 14aA can be dispersed to more air chambers 31. Therefore, in each air chamber 31, the fuel and the air can be mixed more effectively. Thus, the burner 14 can be more effectively suppressed from being exposed to the high-temperature combustion gas. Thus, the burner 14 can be more effectively protected from the flame. Furthermore, the generation of NOx can be more easily suppressed.

[0074] References Figures 5 to 7 The air chamber 31-1 and the air chamber 31-2 have been described. However, the number and arrangement of the air chamber 31-1 and the air chamber 31-2 are not limited to Figures 5 to 7 For example, the plurality of air chambers 31 - 1 and the plurality of air chambers 31 - 2 may be arranged at equal intervals along the circumferential direction, or may be arranged at unequal intervals along the circumferential direction.

[0075] Figure 8 This is a diagram of a burner plate 14aB according to a second modification example as viewed from the combustion chamber 13c side. Fig. 9 yes Figure 8 A sectional view of the A6-A6 section in FIG. That is, Fig. 9 This is a cross-sectional view of the burner plate 14aB as viewed from the radial direction. Fig.10 yes Fig. 9 A sectional view of the A7-A7 section in FIG. That is, Fig.10 This is a cross-sectional view of the burner plate 14aB as viewed from the axial direction.

[0076] like Figures 8 to 10 As shown, a combustion system 10B of a gas turbine system 1B according to a second modification includes a burner plate 14aB. The burner plate 14aB is different from the burner plate 14a and the burner plate 14aA described above in the number and arrangement of the air chambers 31 .

[0077] like Figures 8 to 10As shown, like the burner plate 14a described above, an air chamber 31, an air supply flow path 32, an air manifold 33, a fuel supply flow path 41, and a fuel manifold 42 are formed in the burner plate 14aB.

[0078] In the burner plate 14aB, a plurality of air chambers 31-3, a plurality of air chambers 31-4, a plurality of air chambers 31-5, and one air chamber 31-6 are formed as air chambers 31. The plurality of air chambers 31-3 are air chambers 31 formed at radially outermost positions among the plurality of air chambers 31 of the burner plate 14aB and arranged at intervals in the circumferential direction. The plurality of air chambers 31-4 are air chambers 31 formed at radially inner positions than the plurality of air chambers 31-3 among the plurality of air chambers 31 of the burner plate 14aB and arranged at intervals in the circumferential direction. The plurality of air chambers 31-5 are air chambers 31 formed at radially inner positions than the plurality of air chambers 31-4 among the plurality of air chambers 31 of the burner plate 14aB and arranged at intervals in the circumferential direction. The air chamber 31-6 is an air chamber 31 arranged radially inner than the plurality of air chambers 31-5. The air chamber 31 - 6 is provided on the central axis of the burner plate 14aB.

[0079] The burner plate 14aB includes an air manifold 33-3, an air manifold 33-4, and an air manifold 33-5 as the air manifold 33. The air manifold 33-3, the air manifold 33-4, and the air manifold 33-5 each have an annular shape extending in the circumferential direction of the burner plate 14aB. The air manifold 33-3 is located at the radially outermost side of the plurality of air manifolds 33 formed on the burner plate 14aB. The air manifold 33-4 is located radially inward of the air manifold 33-3. The air manifold 33-5 is located radially inward of the air manifold 33-4.

[0080] Each air chamber 31-3 is connected to the air manifold 33-3 via the air supply flow path 32-3. Therefore, air is supplied to each air chamber 31-3 from the air manifold 33-3 via each air supply flow path 32-3. Each air chamber 31-4 is connected to the air manifold 33-4 via the air supply flow path 32-4. Therefore, air is supplied to each air chamber 31-4 from the air manifold 33-4 via each air supply flow path 32-4. Each air chamber 31-5 is connected to the air manifold 33-5 via the air supply flow path 32-5. Therefore, air is supplied to each air chamber 31-5 from the air manifold 33-5 via each air supply flow path 32-5. The air chamber 31-6 is connected to the air manifold 33-5 via the air supply flow path 32-6. Therefore, air is supplied to the air chamber 31-6 from the air manifold 33-5 via the air supply flow path 32-6.

[0081] In the burner plate 14aB, a fuel manifold 42-3, a fuel manifold 42-4, a fuel manifold 42-5, and a fuel manifold 42-6 are formed as fuel manifolds 42. The fuel manifold 42-3, the fuel manifold 42-4, and the fuel manifold 42-5 each have an annular shape extending in the circumferential direction of the burner plate 14aB. The fuel manifold 42-3 is located at the radially outermost side of the plurality of fuel manifolds 42 formed on the burner plate 14aB. The fuel manifold 42-4 is located radially inwardly compared to the fuel manifold 42-3. The fuel manifold 42-5 is located radially inwardly compared to the fuel manifold 42-4. The fuel manifold 42-6 is located radially inwardly compared to the fuel manifold 42-5. The fuel manifold 42-6 is provided on the central axis of the burner plate 14aB and has, for example, a spherical shape.

[0082] Each air chamber 31-3 is connected to the fuel manifold 42-3 via the fuel supply flow path 41. Therefore, hydrogen is supplied from the fuel manifold 42-3 to each air chamber 31-3. Each air chamber 31-4 is connected to the fuel manifold 42-4 via the fuel supply flow path 41. Therefore, hydrogen is supplied from the fuel manifold 42-4 to each air chamber 31-4. Each air chamber 31-5 is connected to the fuel manifold 42-5 via the fuel supply flow path 41. Therefore, hydrogen is supplied from the fuel manifold 42-5 to each air chamber 31-5. The air chamber 31-6 is connected to the fuel manifold 42-6 via the fuel supply flow path 41. Therefore, hydrogen is supplied from the fuel manifold 42-6 to the air chamber 31-6.

[0083] As described above, like the combustion system 10, the combustion system 10B includes the combustion chamber 13c, the cylindrical air chamber 31 having the injection hole 31a facing the combustion chamber 13c, the fuel supply flow path 41 connected to the air chamber 31, and the air supply flow path 32 connected to the side of the air chamber 31. Thus, the same effect as the combustion system 10 can be obtained.

[0084] In particular, in the combustion system 10B, more groups of multiple air chambers 31 arranged at intervals in the circumferential direction are arranged at intervals in the radial direction compared to the above-mentioned combustion system 10A. Furthermore, in the combustion system 10B, unlike the above-mentioned combustion system 10 and the combustion system 10A, an air chamber 31 is also arranged on the center side of the burner plate 14aB. As a result, the number of air chambers 31 can be further increased, so that the fuel supplied to the burner plate 14aB can be dispersed to more air chambers 31. Therefore, in each air chamber 31, the fuel and the air can be mixed more effectively. Thus, the burner 14 can be more effectively suppressed from being exposed to high-temperature combustion gas. Thus, the burner 14 can be more effectively protected from the influence of the flame. Furthermore, it is easier to suppress the generation of NOx.

[0085] References Figures 8 to 10The air chamber 31-3, the air chamber 31-4, the air chamber 31-5, and the air chamber 31-6 have been described. However, the number and arrangement of the air chamber 31-3, the air chamber 31-4, the air chamber 31-5, and the air chamber 31-6 are not limited to Figures 8 to 10 For example, the plurality of air chambers 31-3, the plurality of air chambers 31-4, and the plurality of air chambers 31-5 may be arranged at equal intervals along the circumferential direction, or may be arranged at non-equal intervals along the circumferential direction. For example, the air chamber 31-6 may be arranged near the center of the burner plate 14aB, in which case the number of the air chambers 31-6 may be plural.

[0086] References Figures 2 to 10 The example in which one air supply flow path 32 is connected to one air chamber 31 is described. However, a plurality of air supply flow paths 32 may be connected to one air chamber 31. Figures 11 to 13 Examples of connecting a plurality of air supply flow paths 32 to one air chamber 31 are described. Figures 11 to 13 Each of the figures shows an example of the connection relationship between the air chamber 31 and the air supply flow path 32. The connection relationship between the air chamber 31 and the air supply flow path 32 described below can also be applied to any of the burner plate 14a, burner plate 14aA and burner plate 14aB.

[0087] In the following Figures 11 to 13 In each example, in the radial direction outside the air chamber 31 ( Figures 11 to 13 The upper side of the Figures 11 to 13 An air manifold 33 is respectively arranged on the lower side of the center.

[0088] exist Fig.11 In the example of FIG. 1 , the air chamber 31 is connected to the radially outer air manifold 33 via two air supply flow paths 32. Therefore, air is supplied to the air chamber 31 from the radially outer air manifold 33 via the two air supply flow paths 32. Each air supply flow path 32 is connected to the air chamber 31 eccentrically with respect to the central axis of the air chamber 31. Each air supply flow path 32 is bent.

[0089] As mentioned above, in Fig.11 In the example of FIG. 1 , the air supply flow path 32 includes a plurality of flow paths (in Fig.11 In the example of FIG. 1 , two air supply flow paths 32 are provided. Thus, in the air chamber 31, it is easy to more uniformly generate a swirling flow of air that swirls in the circumferential direction of the air chamber 31. Therefore, in the air chamber 31, fuel and air can be mixed more effectively.

[0090] In particular, Fig.11In the example of FIG. 1 , the air chamber 31 is connected to only one of the air manifold 33 radially outward relative to the air chamber 31 and the air manifold 33 radially inward relative to the air chamber 31 via the air supply flow path 32. Therefore, the radial distance between adjacent air manifolds 33 can be reduced. Thus, the number of air chambers 31 can be further increased.

[0091] Compared to Fig.11 For example, Fig.12 The example corresponds to an example in which the air chamber 31 is connected to the radially inner air manifold 33 via two air supply flow paths 32 in addition to the radially outer air manifold 33. Fig.12 In the example of FIG. 1 , the air chamber 31 is connected to both the air manifold 33 on the radially outer side of the air chamber 31 and the air manifold 33 on the radially inner side of the air chamber 31 via the air supply flow path 32. Therefore, the number of air supply flow paths 32 connected to the air chamber 31 can be further increased. As a result, in the air chamber 31, it is easy to generate a swirling flow of air that swirls in the circumferential direction of the air chamber 31 more uniformly. Fig.12 In the example of FIG. 1 , each air supply flow path 32 is linear.

[0092] Compared to Fig.12 For example, Fig.13 The example corresponds to the example of bending each air supply flow path 32. By bending each air supply flow path 32, it becomes easy to reduce the radial distance between adjacent air manifolds 33. Thus, the number of air chambers 31 can be further increased. Furthermore, by adjusting the degree of bending, etc., it is easy to generate the swirling flow of air in the air chamber 31 more uniformly.

[0093] References Figures 11 to 13 An example of the connection relationship between the air chamber 31 and the air supply flow path 32 is described. However, the connection relationship between the air chamber 31 and the air supply flow path 32 is not limited to the above example. For example, the number of air supply flow paths 32 connected to the air chamber 31 may be three, or may be five or more. For example, the number of air supply flow paths 32 connected to the radially outer air manifold 33 and the number of air supply flow paths 32 connected to the radially inner air manifold 33 may also be different from each other. For example, the air supply flow path 32 connected to the air chamber 31 may be curved. For example, a part of the plurality of air supply flow paths 32 connected to the air chamber 31 may be bent or curved.

[0094] Although the embodiments of the present disclosure are described above with reference to the accompanying drawings, it is self-evident that the present disclosure is not limited to such embodiments. Obviously, those skilled in the art can think of various changes and modifications within the scope of the claims, and it should be understood that these naturally also fall within the technical scope of the present disclosure.

[0095] References Figures 2 to 10 The burner plate 14a, the burner plate 14aA, and the burner plate 14aB have been described. However, the burner plate 14a, the burner plate 14aA, and the burner plate 14aB may be appropriately modified, added, or deleted. For example, a plurality of fine through holes may be added to the burner plate 14a, the burner plate 14aA, and the burner plate 14aB, which penetrate from the surface on the combustion chamber 13c side to the surface on the opposite side to the combustion chamber 13c side. Thus, air is ejected from the space S in the burner 13 to the combustion chamber 13c through the through holes. Therefore, it is possible to suppress the flame from approaching the burner plate 14a, the burner plate 14aA, and the burner plate 14aB.

[0096] In the above, an example is described in which the rotational power generated by the supercharger 11 in the gas turbine system 1, the gas turbine system 1a, and the gas turbine system 1B is used as energy for driving the generator 12. However, in the gas turbine system 1, the gas turbine system 1a, and the gas turbine system 1B, the rotational power generated by the supercharger 11 can be used for other purposes (for example, for the purpose of driving a mobile object such as a ship, etc.).

[0097] In the above description, an example in which the shape of the combustion chamber 13c is substantially cylindrical is described. However, the shape of the combustion chamber 13c is not limited to this example. For example, the combustion chamber 13c may be a substantially cylindrical space. The shapes of the burner plate 14a, the burner plate 14aA, and the burner plate 14aB may be appropriately changed according to the shape of the combustion chamber 13c.

[0098] Described above Figure 1 In the example of FIG. 1 , the air delivered from the compressor 11a to the burner 13 passes between the outer circumference of the liner 13b and the inner circumference of the outer shell 13a and is then delivered to the combustion chamber 13c. However, the path of the air delivered from the compressor 11a to the burner 13 is not limited to this example (i.e., the turning flow type).

[0099] The present disclosure helps protect burners from flame images and thus can, for example, contribute to achieving Goal 7 of the Sustainable Development Goals (SDGs): "Ensure access to affordable, reliable, sustainable and modern energy for all."

[0100] Reference numerals

[0101] 10: Combustion system, 10A: Combustion system, 10B: Combustion system, 13c: Combustion chamber, 14a: Burner plate, 14aA: Burner plate, 14aB: Burner plate, 31: Air chamber, 31-1: Air chamber, 31-2: Air chamber, 31-3: Air chamber, 31-4: Air chamber, 31-5: Air chamber, 31-6: Air chamber, 31a: Injection hole, 32: Air supply flow path, 32-1: Air supply flow path, 32-2: air supply flow path, 32-3: air supply flow path, 32-4: air supply flow path, 32-5: air supply flow path, 32-6: air supply flow path, 41: fuel supply flow path, 42: fuel manifold, 42-1: fuel manifold, 42-2: fuel manifold, 42-3: fuel manifold, 42-4: fuel manifold, 42-5: fuel manifold, 42-6: fuel manifold.

Claims

1. A combustion system, characterized in that: have: Combustion chamber; A cylindrical air chamber having an injection hole facing the combustion chamber; a fuel supply flow path connected to the air chamber; and The air supply flow path is connected to a side surface of the air chamber.

2. The combustion system according to claim 1, characterized in that: The air supply flow path is connected to the air chamber eccentrically with respect to a central axis of the air chamber.

3. The combustion system according to claim 1, characterized in that: The air chamber has a cylindrical shape.

4. The combustion system according to claim 1, characterized in that: The air supply flow path includes a plurality of flow paths connected to one of the air chambers.

5. The combustion system according to any one of claims 1 to 4, characterized in that: The air chamber, the fuel supply flow path, and the air supply flow path are formed in a burner plate that closes an end portion of the combustion chamber.

6. The combustion system according to claim 5, characterized in that: A fuel manifold is formed on the burner plate.

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