Combustion equipment and gas turbine systems

Abstract

This combustion device 10 comprises a burner plate 14a that faces a combustion chamber, a plurality of injection hole groups 30 that are each formed as a ring in the burner plate 14a, and a ring-shaped slit 50 that is formed between the plurality of injection hole groups 30.

Description

[Technical Field]

[0001] This disclosure relates to a combustion device and a gas turbine system. This application claims the benefit of priority from Japanese Patent Application No. 2022-13189, filed on January 31, 2022, the contents of which are incorporated herein by reference. [Background technology]

[0002] Gas turbine systems are used that obtain power by burning fuel in a combustor. For example, some gas turbine systems use hydrogen as fuel, as disclosed in Patent Document 1. Using hydrogen as fuel reduces carbon dioxide emissions. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Laid-Open No. 2015-014400 Summary of the Invention [Problem to be solved by the invention]

[0004] In recent years, in gas turbine systems, plates facing the combustion chamber where hydrogen is burned are sometimes manufactured using metal lamination technology. In such cases, the amount of metal lamination on the combustion chamber side of the plate is greater than the amount of metal lamination on the opposite side of the combustion chamber. As the temperature of the metal laminations decreases during plate manufacturing, the metal contracts. At this time, the contraction force on the side with the larger amount of metal lamination can cause the plate to deform toward the combustion chamber.

[0005] An object of the present disclosure is to provide a combustion device and a gas turbine system that can suppress deformation of plates. [Means for solving the problem]

[0006] In order to solve the above problems, the combustion device of the present disclosure includes a plate facing a combustion chamber, a plurality of injection hole groups formed in an annular shape on the plate, and an annular slit formed between the plurality of injection hole groups, the plurality of injection hole groups including: a first injection hole group facing the combustion chamber and including a plurality of fuel injection holes spaced apart in the circumferential direction of the combustion chamber; an annular first air injection hole facing the combustion chamber and extending circumferentially radially outward from the plurality of fuel injection holes, and an annular second air injection hole facing the combustion chamber and extending circumferentially radially inward from the plurality of fuel injection holes; and a second injection hole group facing the combustion chamber and including a fuel injection hole, the first air injection hole, and the second air injection hole, and positioned radially inward from the first injection hole group. In order to solve the above problems, the combustion device of the present disclosure has a additively manufactured The nozzle includes a plate, a plurality of injection hole groups formed in an annular shape in the plate, and an annular slit formed between the plurality of injection hole groups. In order to solve the above problems, the combustion device of the present disclosure comprises a plate facing a combustion chamber, a plurality of injection hole groups formed in an annular shape on the plate, and an annular slit formed between the plurality of injection hole groups, the plurality of injection hole groups including air injection holes, and the opening area of ​​the surface of the air injection hole facing the combustion chamber is smaller than the opening area of ​​the surface opposite the combustion chamber.

[0007] In order to solve the above problems, the combustion device of the present disclosure includes a plate facing a combustion chamber, a plurality of groups of injection holes formed in an annular shape on the plate, and annular slits formed between the plurality of groups of injection holes, wherein the plate has a flat surface facing the combustion chamber, and the groups of injection holes and the slits are provided on the flat surface.

[0008] The plate may have an annular cavity formed between the plurality of injection hole groups and communicating with the slit.

[0009] The plate may have a through hole formed on the side opposite to the combustion chamber and communicating with the annular cavity.

[0010] The through-hole may be radially offset relative to the slit. The combustion device may further include a casing, a liner provided inside the casing, within which a combustion chamber is formed, and a space enclosed by the liner, the plate, and the casing, and the slits may be formed in the plate between the plurality of groups of injection holes, and the slits may face the combustion chamber but not the space. The plurality of injection hole groups may include a first injection hole group and a second injection hole group, and each of the first injection hole group and the second injection hole group may include a plurality of fuel injection holes facing the interior of the combustion chamber and spaced apart circumferentially about the combustion chamber, and at least one annular air injection hole facing the interior of the combustion chamber and extending circumferentially at least one of radially outward and radially inward relative to the plurality of fuel injection holes, and the at least one annular air injection hole may be inclined radially toward the plurality of fuel injection holes with respect to the axial direction of the combustion chamber.

[0011] In order to solve the above problems, a gas turbine system according to the present disclosure includes the above combustion device. [Effects of the Invention]

[0012] According to the present disclosure, deformation of the plate can be suppressed. [Brief explanation of the drawings]

[0013] [Figure 1] FIG. 1 is a schematic diagram showing the configuration of a gas turbine system according to an embodiment of the present disclosure. [Figure 2] FIG. 2 is a view of a burner plate according to an embodiment of the present disclosure as viewed from the combustion chamber side. [Figure 3] FIG. 3 is a cross-sectional view taken along the line A2-A2 in FIG. [Figure 4] FIG. 4 is a cross-sectional view taken along the line A3-A3 in FIG. [Figure 5] FIG. 5 is a cross-sectional view taken along the line A4-A4 in FIG. [Figure 6] FIG. 6 is a schematic diagram showing the flow of gas occurring within a combustion chamber according to an embodiment of the present disclosure. [Figure 7] FIG. 7 is a schematic cross-sectional view showing the configuration of a burner plate according to a first modified example. [Figure 8] FIG. 8 is a schematic cross-sectional view showing the configuration of a burner plate according to a second modified example. [Figure 9] FIG. 9 is a schematic cross-sectional view showing a first example of a shape of another cavity according to the second modified example. [Figure 10] FIG. 10 is a schematic cross-sectional view showing a second example of the shape of another cavity according to the second modification. [Figure 11] FIG. 11 is a schematic cross-sectional view showing the configuration of a burner plate according to a third modified example. DETAILED DESCRIPTION OF THE INVENTION

[0014] Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. Dimensions, materials, and other specific numerical values ​​shown in the embodiments are merely examples for ease of understanding and, unless otherwise specified, do not limit the present disclosure. In this specification and drawings, elements having substantially the same functions and configurations are designated by the same reference numerals to avoid redundant explanation, and elements not directly related to the present disclosure are not shown.

[0015] Fig. 1 is a schematic diagram showing the configuration of a gas turbine system 1 according to this embodiment. As shown in Fig. 1, the gas turbine system 1 includes a turbocharger 11, a generator 12, a combustor 13, a burner 14, a hydrogen tank 15, and a flow control valve 16.

[0016] Of the gas turbine system 1, the combustor 13, the burner 14, the hydrogen tank 15, and the flow control valve 16 are included in the combustion device 10.

[0017] The turbocharger 11 has a compressor 11a and a turbine 11b. The compressor 11a and the turbine 11b rotate as a unit. The compressor 11a and the turbine 11b are connected by a shaft.

[0018] The compressor 11a is provided in an intake air flow path 21 connected to the combustor 13. Air to be supplied to the combustor 13 flows through the intake air flow path 21. An intake port (not shown) through which air is taken in from the outside is provided at the upstream end of the intake air flow path 21. The air taken in through the intake port passes through the compressor 11a and is sent to the combustor 13. The compressor 11a compresses the air and discharges it downstream.

[0019] The turbine 11b is provided in an exhaust flow path 22 connected to the combustor 13. Exhaust gas discharged from the combustor 13 flows through the exhaust flow path 22. An exhaust port (not shown) through which the exhaust gas is discharged to the outside is provided at the downstream end of the exhaust flow path 22. The exhaust gas discharged from the combustor 13 passes through the turbine 11b and is sent to the exhaust port. The turbine 11b is rotated by the exhaust gas to generate rotational power.

[0020] The generator 12 is connected to the turbocharger 11. The generator 12 generates electricity using the rotational power generated by the turbocharger 11.

[0021] The combustor 13 has a casing 13a, a liner 13b, and a combustion chamber 13c. The casing 13a has a generally cylindrical shape. The liner 13b is provided inside the casing 13a. The liner 13b also has a generally cylindrical shape. The liner 13b is arranged coaxially with the casing 13a. The combustion chamber 13c is formed inside the liner 13b. In other words, the internal space of the liner 13b corresponds to the combustion chamber 13c. The combustion chamber 13c is a generally cylindrical space. An exhaust flow path 22 is connected to the combustion chamber 13c.

[0022] As will be described later, hydrogen and air are supplied to the combustion chamber 13c. Combustion takes place in the combustion chamber 13c using hydrogen as fuel. Exhaust gas generated by combustion in the combustion chamber 13c is discharged to the exhaust passage 22. A space S is formed between the inner surface of the casing 13a and the outer surface of the liner 13b. An intake passage 21 is connected to the space S. Air is sent to the space S from the compressor 11a via the intake passage 21. An opening is formed at the end of the liner 13b (the end on the left side in FIG. 1). A burner 14 is inserted into the opening at the end of the liner 13b.

[0023] The burner 14 has a burner plate (plate) 14a and multiple fuel supply pipes 14b. The burner plate 14a faces the combustion chamber 13c. The burner plate 14a closes the opening at the end of the liner 13b. In other words, the burner plate 14a closes the end of the combustion chamber 13c. The burner plate 14a has a circular plate shape. However, the shape is not limited thereto, and the burner plate 14a may have a shape other than a circular plate. For example, the burner plate 14a may be polygonal. The burner plate 14a may also be composed of multiple segments obtained by dividing a circular or polygonal plate into multiple pieces. The burner plate 14a is formed by metal additive manufacturing. The fuel supply pipe 14b is connected to the surface of the burner plate 14a opposite to the combustion chamber 13c side. In other words, the fuel supply pipe 14b is connected to the surface of the burner plate 14a facing the space S. The fuel supply pipes 14b pass through the casing 13a and extend to the outside of the casing 13a. Three fuel supply pipes 14b are shown in Fig. 1. However, the number of fuel supply pipes 14b is not limited.

[0024] As will be described later with reference to FIGS. 2 to 5, fuel injection holes (specifically, fuel injection hole 31, which will be described later) and air injection holes (specifically, first air injection holes 32 and second air injection holes 33, which will be described later) are formed in burner plate 14a. The fuel injection holes formed in burner plate 14a communicate with fuel supply pipe 14b. As will be described later, hydrogen is supplied as fuel to fuel supply pipe 14b. The hydrogen supplied from fuel supply pipe 14b to burner plate 14a passes through the fuel injection holes of burner plate 14a and is injected into combustion chamber 13c. As shown by the dashed-dotted arrow in FIG. 1, air supplied to space S passes through space S and then reaches the surface of burner plate 14a opposite to the combustion chamber 13c. The air supplied to burner plate 14a passes through the air injection holes of burner plate 14a and is injected into combustion chamber 13c.

[0025] Hydrogen is stored in the hydrogen tank 15. Note that the hydrogen in the hydrogen tank 15 may be either liquid or gas. The hydrogen tank 15 is connected to a flow control valve 16 via a flow path 23. The flow control valve 16 is connected to each fuel supply pipe 14b of the burner 14 via a 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. The amount of hydrogen supplied from the hydrogen tank 15 to the fuel supply pipe 14b is adjusted by adjusting the opening of the flow control valve 16.

[0026] Hereinafter, the circumferential direction of the combustion chamber 13c will also be simply referred to as the circumferential direction, the radial direction of the combustion chamber 13c will also be simply referred to as the radial direction, and the axial direction of the combustion chamber 13c will also be simply referred to as the axial direction.

[0027] Fig. 2 is a view of the burner plate 14a as seen from the combustion chamber 13c (specifically, as seen from the direction of arrow A1 in Fig. 1). Fig. 3 is a cross-sectional view taken along the line A2-A2 in Fig. 2. Fig. 4 is a cross-sectional view taken along the line A3-A3 in Fig. 2. Fig. 5 is a cross-sectional view taken along the line A4-A4 in Fig. 2.

[0028] As shown in FIG. 2, the burner plate 14a has a plurality of injection hole groups 30 (specifically, a first injection hole group 30-1 and a second injection hole group 30-2). Each injection hole group 30 has a plurality of fuel injection holes 31, first air injection holes 32, and second air injection holes 33. Each injection hole group 30 extends in the circumferential direction and has an annular shape. The first injection hole group 30-1 is disposed radially outward relative to the second injection hole group 30-2. In other words, the second injection hole group 30-2 is disposed radially inward relative to the first injection hole group 30-1. In this way, the first injection hole group 30-1 and the second injection hole group 30-2 are disposed with a radial interval between them. However, the number of injection hole groups 30 formed in the burner plate 14a is not limited to this example. For example, the number of injection hole groups 30 formed in the burner plate 14a may be one or three or more. Since the configuration of the first injection hole group 30-1 and the configuration of the second injection hole group 30-2 are similar, the configuration of the first injection hole group 30-1 will be described in detail below, and a detailed description of the configuration of the second injection hole group 30-2 will be omitted.

[0029] The fuel injection holes 31 face the combustion chamber 13c. The fuel injection holes 31 open on the surface of the burner plate 14a facing the combustion chamber 13c. The fuel injection holes 31 are hydrogen injection holes that inject hydrogen as fuel into the combustion chamber 13c. In each injection hole group 30, the multiple fuel injection holes 31 are provided at intervals in the circumferential direction. In each injection hole group 30, the multiple fuel injection holes 31 are provided at equal intervals. However, in each injection hole group 30, the multiple fuel injection holes 31 may be provided at unequal intervals.

[0030] In the burner plate 14a, communication holes 40 communicating with the plurality of fuel injection holes 31 are formed for each injection hole group 30. The communication holes 40 extend in the circumferential direction. The communication holes 40 are formed, for example, in an annular shape. As shown in FIGS. 2 and 3, the communication holes 40 are arranged in parallel with the plurality of fuel injection holes 31 of each injection hole group 30 in the axial direction. The communication holes 40 are arranged on the opposite side of the combustion chamber 13c from the plurality of fuel injection holes 31 of each injection hole group 30. In the example of FIG. 3, the cross-sectional shape of the communication holes 40 (specifically, the shape of a cross section perpendicular to the extension direction of the communication holes 40) is circular. However, the cross-sectional shape of the communication holes 40 may be a shape other than circular (for example, a polygonal shape, etc.).

[0031] The communication holes 40 are connected to a fuel supply pipe 14b of the burner 14. Hydrogen is supplied from the fuel supply pipe 14b to each communication hole 40. The hydrogen supplied to the communication holes 40 is injected into the combustion chamber 13c from each fuel injection hole 31, as shown by arrow C1 in FIG. 3. The hydrogen supplied to the communication hole 40 of the first injection hole group 30-1 is injected into the combustion chamber 13c from the multiple fuel injection holes 31 of the first injection hole group 30-1. The hydrogen supplied to the communication hole 40 of the second injection hole group 30-2 is injected into the combustion chamber 13c from the multiple fuel injection holes 31 of the second injection hole group 30-2.

[0032] The first air injection holes 32 face the combustion chamber 13c. The first air injection holes 32 penetrate the burner plate 14a from the surface facing the combustion chamber 13c to the surface on the opposite side. In each injection hole group 30, the first air injection holes 32 are provided radially outward of the multiple fuel injection holes 31. The first air injection holes 32 extend in the circumferential direction and are formed in an annular shape. The outer and inner diameters of the first air injection holes 32 decrease from the opposite side of the combustion chamber 13c toward the combustion chamber 13c. The change in the inner diameter of the first air injection holes 32 is smaller than the change in the outer diameter of the first air injection holes 32. Therefore, the opening area of ​​the surface of the first air injection holes 32 facing the combustion chamber 13c is smaller than the opening area of ​​the surface on the opposite side of the combustion chamber 13c. Furthermore, the central axis direction of the first air injection holes 32 is inclined toward the fuel injection holes 31, i.e., radially inward, with respect to the axial direction. A portion of the air sent to the burner plate 14a through the space S in the combustor 13 is injected into the combustion chamber 13c from the first air injection holes 32 as shown by arrows C2 in FIGS.

[0033] The first air injection holes 32 are provided with first swirler vanes 32a inclined circumferentially with respect to the combustion chamber-side axial direction Dc. In the present disclosure, the combustion chamber-side axial direction Dc may also be simply referred to as the direction Dc. The direction Dc is a direction facing the combustion chamber 13c along the axial direction of the combustion chamber 13c. Inclining circumferentially with respect to the direction Dc means extending in the direction of a vector obtained by combining a vector in the direction Dc with a circumferential vector, or inclining so as to progress circumferentially as the air injection holes 32 approach the combustion chamber 13c. The first swirler vanes 32a have, for example, a substantially flat plate shape. The first swirler vanes 32a divide the first air injection holes 32 circumferentially. The first swirler vanes 32a extend on a plane intersecting the circumferential direction. In each first air injection hole 32, multiple first swirler vanes 32a are provided at intervals in the circumferential direction. In each first air injection hole 32, the multiple first swirler vanes 32a are provided at equal intervals. However, in each first air injection hole 32, the multiple first swirler vanes 32a may be provided at unequal intervals.

[0034] For example, as shown in FIG. 4, in the first air injection holes 32 of the first injection hole group 30-1, the first swirler vanes 32a are inclined to one side in the circumferential direction (clockwise direction in FIG. 2) with respect to the direction Dc. Here, the direction of air injected from the first air injection holes 32 is a direction along the first swirler vanes 32a. Therefore, as shown by arrow C2 in FIG. 4, the direction of air injected from the first air injection holes 32 of the first injection hole group 30-1 is inclined to one side in the circumferential direction with respect to the direction Dc. Therefore, as shown by arrow B1 in FIG. 2, the air injected from the first air injection holes 32 of the first injection hole group 30-1 swirls to one side in the circumferential direction within the combustion chamber 13c.

[0035] The second air injection holes 33 face the combustion chamber 13c. The second air injection holes 33 penetrate the burner plate 14a from the surface facing the combustion chamber 13c to the surface on the opposite side. In each injection hole group 30, the second air injection holes 33 are provided radially inward relative to the multiple fuel injection holes 31. The second air injection holes 33 extend in the circumferential direction and are formed in an annular shape. The outer and inner diameters of the second air injection holes 33 increase in diameter from the opposite side of the combustion chamber 13c toward the combustion chamber 13c. The change in the outer diameter of the second air injection holes 33 is smaller than the change in the inner diameter of the second air injection holes 33. Therefore, the opening area of ​​the surface of the second air injection holes 33 facing the combustion chamber 13c is smaller than the opening area of ​​the surface on the opposite side of the combustion chamber 13c. Furthermore, the central axis direction of the second air injection holes 33 is inclined toward the fuel injection holes 31, i.e., radially outward, with respect to the axial direction. A portion of the air sent to the burner plate 14a through the space S in the combustor 13 is injected into the combustion chamber 13c from the second air injection holes 33, as shown by arrows C3 in FIGS.

[0036] The second air injection holes 33 are provided with second swirler vanes 33a that are inclined with respect to the direction Dc toward the same side in the circumferential direction as the first swirler vanes 32a (specifically, the first swirler vanes 32a that belong to the same injection hole group 30). The second swirler vanes 33a have, for example, a substantially flat plate shape. The second swirler vanes 33a divide the second air injection holes 33 in the circumferential direction. The second swirler vanes 33a extend on a plane that intersects with the circumferential direction. In each second air injection hole 33, multiple second swirler vanes 33a are provided at intervals in the circumferential direction. In each second air injection hole 33, the multiple second swirler vanes 33a are provided at equal intervals. However, in each second air injection hole 33, the multiple second swirler vanes 33a may be provided at unequal intervals.

[0037] For example, as shown in FIG. 5, in the second air injection holes 33 of the first injection hole group 30-1, the second swirler vanes 33a are inclined to one circumferential side with respect to the direction Dc (clockwise in FIG. 2). Here, the direction of air injected from the second air injection holes 33 is along the second swirler vanes 33a. Therefore, as shown by arrow C3 in FIG. 5, the direction of air injected from the second air injection holes 33 of the first injection hole group 30-1 is inclined to one circumferential side with respect to the direction Dc. Therefore, as shown by arrow B2 in FIG. 2, the air injected from the second air injection holes 33 of the first injection hole group 30-1 swirls to one circumferential side within the combustion chamber 13c.

[0038] The direction in which the first swirler vanes 32a and the second swirler vanes 33a in the first injection hole group 30-1 are inclined relative to the direction Dc and the direction in which the first swirler vanes 32a and the second swirler vanes 33a in the second injection hole group 30-2 are inclined relative to the direction Dc are on different sides in the circumferential direction. That is, in the first air injection holes 32 in the second injection hole group 30-2, the first swirler vanes 32a are inclined toward the other circumferential side (counterclockwise in FIG. 2) relative to the direction Dc. Therefore, as shown by arrow B3 in FIG. 2, air injected from the first air injection holes 32 in the second injection hole group 30-2 swirls toward the other circumferential side within the combustion chamber 13c. In the second air injection holes 33 in the second injection hole group 30-2, the second swirler vanes 33a are inclined toward the other circumferential side relative to the direction Dc. Therefore, as shown by arrow B4 in FIG. 2, the air injected from the second air injection holes 33 of the second injection hole group 30-2 swirls to the other side in the circumferential direction within the combustion chamber 13c.

[0039] The direction in which the first swirler vanes 32a and the second swirler vanes 33a in the first injection hole group 30-1 are inclined relative to the direction Dc and the direction in which the first swirler vanes 32a and the second swirler vanes 33a in the second injection hole group 30-2 are inclined relative to the direction Dc may be on the same side in the circumferential direction. Hereinafter, a case in which the first swirler vanes 32a and the second swirler vanes 33a in the first injection hole group 30-1 and the first swirler vanes 32a and the second swirler vanes 33a in the second injection hole group 30-2 are inclined relative to the direction Dc on the same side in the circumferential direction will be referred to as inclination pattern 1. For example, the first swirler vanes 32a and the second swirler vanes 33a in the first injection hole group 30-1 are inclined to one side in the circumferential direction (clockwise in FIG. 2) relative to the direction Dc. At this time, the first swirler vanes 32a and the second swirler vanes 33a in the second injection hole group 30-2 are inclined to one circumferential side (clockwise direction in FIG. 2) with respect to the direction Dc. Note that the first swirler vanes 32a and the second swirler vanes 33a in the first injection hole group 30-1 may be inclined to the other circumferential side (counterclockwise direction in FIG. 2) with respect to the direction Dc. At this time, the first swirler vanes 32a and the second swirler vanes 33a in the second injection hole group 30-2 may be inclined to the other circumferential side (counterclockwise direction in FIG. 2) with respect to the direction Dc. This allows a strong swirling flow of air to be formed throughout the entire combustion chamber 13c, improving flame stability.

[0040] In this embodiment, the direction in which the first swirler vanes 32a and second swirler vanes 33a in the first injection hole group 30-1 are inclined with respect to the direction Dc is opposite in the circumferential direction to the direction in which the first swirler vanes 32a and second swirler vanes 33a in the second injection hole group 30-2 are inclined with respect to the direction Dc. In this manner, a case in which the first swirler vanes 32a and second swirler vanes 33a in the first injection hole group 30-1 and the first swirler vanes 32a and second swirler vanes 33a in the second injection hole group 30-2 are inclined in opposite directions to each other is referred to as inclination pattern 2. For example, the first swirler vanes 32a and second swirler vanes 33a in the first injection hole group 30-1 are inclined to one side in the circumferential direction (clockwise in FIG. 2) with respect to the direction Dc. At this time, the first swirler vane 32a and the second swirler vane 33a in the second injection hole group 30-2 are inclined to the other circumferential side (counterclockwise in FIG. 2) with respect to the direction Dc. As a result, the swirling air flow is weakened by counter-swirling between the injection hole groups 30, and therefore the swirling air flow in the entire combustion chamber 13c is weakened, making it possible to suppress melting damage to the burner 14.

[0041] As described above, in each injection hole group 30, the first air injection holes 32, which are provided radially outward from the plurality of fuel injection holes 31, are provided with first swirler vanes 32a that are inclined circumferentially with respect to the direction Dc. The second air injection holes 33, which are provided radially inward from the plurality of fuel injection holes 31, are provided with second swirler vanes 33a that are inclined circumferentially to the same side as the first swirler vanes 32a with respect to the direction Dc. As a result, the air injected from the first air injection holes 32 and the second air injection holes 33 swirls on the same side in the circumferential direction within the combustion chamber 13c. Hydrogen is injected from the fuel injection holes 31 toward the swirling flow of air thus generated. Therefore, the hydrogen injected from the fuel injection holes 31 is mixed with the air while swirling due to the swirling flow of air.

[0042] As described above, according to the combustion device 10 of the gas turbine system 1, in each injection hole group 30, the hydrogen injected from the fuel injection holes 31 is rapidly mixed with the air by the swirling air flow generated by the air injected from the first air injection holes 32 and the second air injection holes 33. Therefore, the ignition position is closer to the inside of the combustion chamber 13c than when hydrogen and air are supplied to the combustion chamber 13c in a pre-mixed state. This suppresses flashback. Furthermore, this suppresses melting of the burner 14. This makes it possible to protect the burner 14 from flames. Furthermore, by appropriately adjusting the amount of air supplied and lowering the flame temperature, a reduction in NOx emissions is also achieved.

[0043] In each injection hole group 30, the inclination angles of the first swirler vanes 32a and the second swirler vanes 33a (that is, the inclination angles with respect to the direction Dc) may be the same as or different from each other.

[0044] Fig. 6 is a schematic diagram showing the flow of gas generated in the combustion chamber 13c. In Fig. 6, the arrow D1 indicates a swirling flow of air generated by the air injected from the first air injection holes 32 and the second air injection holes 33. When a swirling flow of air is generated, a circulating flow is generated, which is a gas flow that passes near the central axis of the swirling flow (i.e., near the central axis of the combustion chamber 13c) and heads toward the burner plate 14a, as indicated by the arrow D2.

[0045] As described above, in the combustion device 10, the direction in which the first swirler vanes 32a and the second swirler vanes 33a in the first injection hole group 30-1 are tilted relative to the direction Dc and the direction in which the first swirler vanes 32a and the second swirler vanes 33a in the second injection hole group 30-2 are tilted relative to the direction Dc are on different sides of the circumferential direction. As a result, the direction of the swirling flow generated by the air injected from the first injection hole group 30-1 (specifically, the clockwise direction in FIG. 2) is opposite to the direction of the swirling flow generated by the air injected from the second injection hole group 30-2 (specifically, the counterclockwise direction in FIG. 2). Therefore, the swirling flow generated by the air injected from the first injection hole group 30-1 and the swirling flow generated by the air injected from the second injection hole group 30-2 weaken each other. Therefore, the circulating flow passing near the central axis of the swirling flow toward the burner plate 14a (i.e., the flow indicated by arrow D2 in FIG. 6) is weakened, thereby suppressing the flame from approaching the burner plate 14a, and thus suppressing the melting damage of the burner 14.

[0046] In the axial direction, at a position where the swirling air flow generated by the first injection hole group 30-1 and the swirling air flow generated by the second injection hole group 30-2 interfere with each other, a local vortex is generated, and the gas injected from the first injection hole group 30-1 and the gas injected from the second injection hole group 30-2 tend to mix, thereby further reducing NOx emissions.

[0047] In the example of inclination pattern 2 described above, the first swirler vanes 32a and second swirler vanes 33a of the first injection hole group 30-1 are inclined to one circumferential side with respect to direction Dc (clockwise in FIG. 2). However, the first swirler vanes 32a and second swirler vanes 33a of the first injection hole group 30-1 may be inclined to the other circumferential side with respect to direction Dc (counterclockwise in FIG. 2). In this case, the first swirler vanes 32a and second swirler vanes 33a of the second injection hole group 30-2 are inclined to one circumferential side with respect to direction Dc.

[0048] The direction in which the first swirler vanes 32a in the first injection hole group 30-1 are inclined with respect to the direction Dc may be on the same side in the circumferential direction as the direction in which the first swirler vanes 32a in the second injection hole group 30-2 are inclined with respect to the direction Dc. In this case, the direction in which the second swirler vanes 33a in the first injection hole group 30-1 are inclined with respect to the direction Dc may be on the same side in the circumferential direction as the direction in which the second swirler vanes 33a in the second injection hole group 30-2 are inclined with respect to the direction Dc. The direction in which the first swirler vanes 32a in the first injection hole group 30-1 and the second injection hole group 30-2 are inclined with respect to the direction Dc may be opposite to the direction in which the second swirler vanes 33a in the first injection hole group 30-1 and the second injection hole group 30-2 are inclined with respect to the direction Dc. In this way, a case in which the first swirl vanes 32a in the first injection hole group 30-1 and the second injection hole group 30-2 and the second swirl vanes 33a in the first injection hole group 30-1 and the second injection hole group 30-2 are inclined in directions opposite to each other is referred to as inclination pattern 3. For example, the first swirl vanes 32a of the first injection hole group 30-1 may be inclined to one circumferential side with respect to direction Dc (clockwise in FIG. 2), and the second swirl vanes 33a of the first injection hole group 30-1 may be inclined to the other circumferential side with respect to direction Dc (counterclockwise in FIG. 2). In this case, the first swirl vanes 32a of the second injection hole group 30-2 may be inclined to one circumferential side with respect to direction Dc (clockwise in FIG. 2), and the second swirl vanes 33a of the second injection hole group 30-2 may be inclined to the other circumferential side with respect to direction Dc (counterclockwise in FIG. 2). This weakens the swirling air flow due to the reverse swirling inside and outside each injection hole group 30 and between injection hole groups 30, thereby weakening the swirling air flow throughout the entire combustion chamber 13c more than with inclination pattern 2 and suppressing melting damage to the burner 14. In addition, the reverse swirling inside and outside each injection hole group 30 allows the hydrogen and air injected from the fuel injection holes 31 to be rapidly mixed.

[0049] Furthermore, the direction in which the first swirler vanes 32a in the first injection hole group 30-1 are inclined with respect to the direction Dc may be opposite in the circumferential direction to the direction in which the first swirler vanes 32a in the second injection hole group 30-2 are inclined with respect to the direction Dc. In this case, the direction in which the second swirler vanes 33a in the first injection hole group 30-1 are inclined with respect to the direction Dc may be opposite in the circumferential direction to the direction in which the second swirler vanes 33a in the second injection hole group 30-2 are inclined with respect to the direction Dc. Furthermore, the direction in which the first swirler vanes 32a in the first injection hole group 30-1 and the second swirler vanes 33a in the second injection hole group 30-2 are inclined with respect to the direction Dc may be opposite to the direction in which the second swirler vanes 33a in the first injection hole group 30-1 and the first swirler vanes 32a in the second injection hole group 30-2 are inclined with respect to the direction Dc. In this way, a case in which the first swirl vane 32a in the first injection hole group 30-1 and the second swirl vane 33a in the second injection hole group 30-2, and the second swirl vane 33a in the first injection hole group 30-1 and the first swirl vane 32a in the second injection hole group 30-2 are inclined in directions opposite to each other is called inclination pattern 4. For example, the first swirl vane 32a of the first injection hole group 30-1 may be inclined to one circumferential side (clockwise in FIG. 2) with respect to direction Dc, and the second swirl vane 33a of the first injection hole group 30-1 may be inclined to the other circumferential side (counterclockwise in FIG. 2) with respect to direction Dc. In this case, the first swirler vane 32a of the second injection hole group 30-2 may be inclined toward the other circumferential side (counterclockwise in FIG. 2) with respect to the direction Dc, and the second swirler vane 33a of the second injection hole group 30-2 may be inclined toward one circumferential side (clockwise in FIG. 2) with respect to the direction Dc. This strengthens the swirling air flow between the injection hole groups 30 due to forward swirling, and weakens the swirling air flow inside and outside each injection hole group 30 due to reverse swirling. As a result, the swirling air flow can be weakened more than in the inclination pattern 1, further suppressing the melting of the burner 14, and the swirling air flow can be strengthened more than in the inclination pattern 3, further improving flame stability. Furthermore, the reverse swirling inside and outside each injection hole group 30 allows the hydrogen and air injected from the fuel injection holes 31 to be rapidly mixed. When there are three or more injection hole groups 30, the above-described inclination patterns 1-4 may be used in combination in the three or more injection hole groups 30.

[0050] In the combustion device 10, the injection hole group 30 is formed in the burner plate 14a that closes the end of the combustion chamber 13c. Therefore, the injection hole group 30 can be easily formed by integrally molding the burner plate 14a using metal lamination technology or the like. By integrally molding the burner plate 14a in this way, the structure of the burner 14 is simplified, the burner 14 is made smaller, and the manufacturing cost of the burner 14 is reduced, compared to when the member that forms the injection hole group 30 is separate from the burner plate 14a. In addition, hydrogen leakage from the joints of the members is suppressed. Furthermore, the occurrence of cracks at the joints due to thermal stress is suppressed.

[0051] In the combustion device 10, the burner plate 14a is formed with communication holes 40 that communicate with the multiple fuel injection holes 31. Therefore, the communication holes 40 can be easily formed by integrally molding the burner plate 14a using metal lamination technology or the like. By integrally molding the burner plate 14a in this way, the structure of the burner 14 is simplified, the burner 14 is made smaller, and the manufacturing cost of the burner 14 is reduced, compared to when the member that forms the communication holes 40 is separate from the burner plate 14a. In addition, hydrogen leakage from the joints of the members is suppressed. Furthermore, the occurrence of cracks at the joints due to thermal stress is suppressed.

[0052] Incidentally, when the burner plate 14a is manufactured using metal lamination technology, the amount of metal lamination on the surface of the burner plate 14a facing the combustion chamber 13c is greater than the amount of metal lamination on the surface opposite the combustion chamber 13c. This is because the opening area of ​​the first air injection holes 32 and the second air injection holes 33 on the surface facing the combustion chamber 13c is smaller than the opening area on the surface opposite the combustion chamber 13c. As the temperature of the metal laminated during the manufacture of the burner plate 14a decreases, the metal contracts. At this time, the contraction force on the side with the greater amount of metal lamination may cause the burner plate 14a to deform toward the combustion chamber side where the greater amount of metal lamination is present.

[0053] Therefore, in this embodiment, when the burner plate 14a is manufactured by metal lamination technology, annular slits 50 (see FIGS. 2 and 3) are formed between the plurality of injection hole groups 30 of the burner plate 14a. The slits 50 are formed on the surface of the burner plate 14a facing the combustion chamber 13c. The slits 50 communicate with the combustion chamber 13c. In other words, the slits 50 open to the combustion chamber 13c. The slits 50 extend in the axial direction of the combustion chamber 13c. However, the slits 50 may extend at an angle to the axial direction of the combustion chamber 13c.

[0054] The depth of the slits 50 is set so as to maintain a minimum thickness necessary to maintain the strength of the burner plate 14a when the burner plate 14a is attached to the liner 13b. The depth of the slits 50 is, for example, half or more of the thickness of the burner plate 14a. The depth of the slits 50 is, for example, 4 / 5 or more of the thickness of the burner plate 14a.

[0055] The radial position of the slit 50 is determined, for example, so that the mass of the burner plate 14a radially outward from the slit 50 is balanced with the mass of the burner plate 14a radially inward from the slit 50. Therefore, the radial position of the slit 50 is set at a position where the diameter is greater than half the radius of the burner plate 14a. However, the radial position of the slit 50 may be set at a position where the diameter is half the radius of the burner plate 14a, or may be set at a position where the diameter is less than half the radius of the burner plate 14a.

[0056] According to this embodiment, the burner plate 14a has the slits 50, and therefore the first injection hole group 30-1 and the second injection hole group 30-2 are separated by the slits 50 on the surface of the burner plate 14a facing the combustion chamber 13c. Therefore, the contraction force of the metal, which occurs as the temperature of the metal laminated during the manufacture of the burner plate 14a decreases, is separated on the radially inner side and the radially outer side of the slits 50. As a result, deformation of the burner plate 14a can be suppressed compared to when the slits 50 are not formed.

[0057] Fig. 7 is a schematic cross-sectional view showing the configuration of a burner plate 114a according to a first modified example. Components that are substantially the same as those of the burner plate 14a of the above embodiment are given the same reference numerals and their description will be omitted. As shown in Fig. 7, the burner plate 114a according to the first modified example differs from the above embodiment in that a plurality of slits 150 are formed.

[0058] In the first modification, a plurality of annular slits 150 are formed between the plurality of injection hole groups 30 of the burner plate 114a. The slits 150 are formed on the surface of the burner plate 114a facing the combustion chamber 13c. The slits 150 extend in the axial direction.

[0059] The plurality of slits 150 includes a first slit 150a and a second slit 150b. However, without being limited thereto, the plurality of slits 150 may include three or more slits. The first slit 150a and the second slit 150b are formed to be spaced apart from each other in the radial direction. The first slit 150a is located radially outward from the second slit 150b. In other words, the second slit 150b is located radially inward from the first slit 150a.

[0060] The depths of the first slit 150a and the second slit 150b are the same as those in the above embodiment. However, without being limited to this, the depths of the first slit 150a and the second slit 150b may be different from those in the above embodiment. Furthermore, the depths of the first slit 150a and the second slit 150b may be different from each other.

[0061] The radial positions of the first slit 150a and the second slit 150b are determined, for example, so that the mass of the burner plate 114a radially outside the first slit 150a is balanced with the mass of the burner plate 114a radially inside the second slit 150b. Therefore, the radial position of the first slit 150a is set to a position where the radius is greater than half the radius of the burner plate 114a. Also, the radial position of the second slit 150b is set to a position where the radius is less than half the radius of the burner plate 114a.

[0062] According to the first modification, by providing a plurality of slits 150, it is possible to further suppress deformation of the burner plate 114a compared to the above embodiment.

[0063] Fig. 8 is a schematic cross-sectional view showing the configuration of a burner plate 214a according to a second modified example. Components that are substantially the same as those of the burner plate 14a according to the above embodiment are given the same reference numerals and will not be described. As shown in Fig. 8, the burner plate 214a according to the second modified example differs from the above embodiment in that an annular cavity 250A is formed.

[0064] As shown in Fig. 8, annular cavities 250A are formed between the multiple injection hole groups 30 of the burner plate 214a. The cavities 250A are radially separated from the injection hole groups 30. The cavities 250A are formed approximately at the center in the thickness direction of the burner plate 214a. The cavities 250A communicate with the slits 50. The cross-sectional shape of the cavity 250A (the shape in a cross section including the central axis of the burner plate 214a) is circular.

[0065] Fig. 9 is a schematic cross-sectional view showing a first shape example of cavity 250B, which is another cavity of cavity 250A according to the second modified example. Fig. 10 is a schematic cross-sectional view showing a second shape example of cavity 250C, which is another cavity of cavity 250A according to the second modified example. As shown in Fig. 9, cavity 250B has a triangular cross-sectional shape. As shown in Fig. 10, cavity 250C has a waterdrop-shaped cross-sectional shape. Note that the cross-sectional shapes of cavities 250A, 250B, and 250C are not limited to the shapes shown in Figs. 8 to 10 and may be, for example, semicircular, elliptical, or oval.

[0066] Each of the cavities 250A, 250B, and 250C has a curved surface or a surface inclined from a surface perpendicular to the axial direction on the side closer to the combustion chamber 13c. In other words, each of the cavities 250A, 250B, and 250C does not have a surface perpendicular to the axial direction on the side closer to the combustion chamber 13c. If each of the cavities 250A, 250B, and 250C had a surface perpendicular to the axial direction on the side closer to the combustion chamber 13c, the burner plate 214a would not be formed because the portions corresponding to the cavities 250A, 250B, and 250C would collapse during lamination using metal lamination techniques. Therefore, in the second modification, each of the cavities 250A, 250B, and 250C does not have a surface perpendicular to the axial direction on the side closer to the combustion chamber 13c.

[0067] According to the second modification, by forming the cavities 250A, 250B, and 250C, it is possible to reduce the mass inside the burner plate 214a. In other words, it is possible to reduce the amount of metal deposited on the burner plate 214a, thereby making it lighter. Therefore, it is possible to reduce the amount of shrinkage that occurs when the metal cools during the manufacture of the burner plate 214a. Also, because the amount of deposition is reduced, it is possible to shorten the manufacturing time of the burner plate 214a. Furthermore, it is possible to reduce the cost of the burner plate 214a. Furthermore, because the weight of the burner plate 214a is reduced, it becomes easier to attach the burner plate 214a to the liner 13b.

[0068] Fig. 11 is a schematic cross-sectional view showing the configuration of a burner plate 314a according to the third modified example. Components that are substantially the same as those of the burner plate 214a according to the second modified example are given the same reference numerals and their explanations are omitted. As shown in Fig. 11, the burner plate 314a according to the third modified example differs from the second modified example in that a through hole 350 is formed.

[0069] In the third modified example, through holes 350 are formed between the multiple injection hole groups 30 of the burner plate 314a. The through holes 350 are formed on the opposite side of the cavity 250A from the combustion chamber 13c. The through holes 350 are radially separated from the injection hole groups 30. The through holes 350 extend in the axial direction. In other words, the through holes 350 extend parallel to the slits 50. However, the present invention is not limited to this, and the through holes 350 may extend in a direction inclined with respect to the axial direction.

[0070] As shown in Fig. 11, a plurality of through holes 350 are formed in the radial direction. However, this is not limited thereto, and only one through hole 350 may be formed in the radial direction. Furthermore, a plurality of through holes 350 are formed at equal intervals in the circumferential direction of the burner plate 314a. However, this is not limited thereto, and the plurality of through holes 350 may be formed at unequal intervals in the circumferential direction. The plurality of through holes 350 communicate with the space S and the cavity 250A. The plurality of through holes 350 are offset in the radial direction with respect to the slit 50. In other words, the plurality of through holes 350 are formed at positions offset in the radial direction with respect to the slit 50.

[0071] According to the third modification, the plurality of through holes 350 can supply air from the space S to the cavity 250A. This makes it possible to cool the inside of the cavity 250, and therefore the burner plate 314a.

[0072] Furthermore, since the multiple through holes 350 are radially offset from the slits 50, it is possible to make it difficult for the air that has passed through the through holes 350 to be directly introduced into the slits 50. Therefore, the air that has passed through the through holes 350 can be made to collide with the inner wall surface of the burner plate 314a that forms the cavity 250A. As a result, it is possible to promote cooling of the burner plate 314a and suppress melting damage of the burner plate 314a.

[0073] Furthermore, the air supplied to cavity 250A is supplied to combustion chamber 13c through slit 50. Therefore, it is possible to prevent the hydrogen flame formed in the combustion chamber 13c near burner plate 314a from approaching burner plate 314a, and it is possible to prevent melting damage to burner plate 314a.

[0074] Although the embodiments of the present disclosure have been described above with reference to the accompanying drawings, it goes without saying that the present disclosure is not limited to such embodiments. It is clear that a person skilled in the art can conceive of various modifications and alterations within the scope of the claims, and it is understood that such modifications and alterations also fall within the technical scope of the present disclosure.

[0075] In the above, an example has been described in which the rotational power generated by the turbocharger 11 in the gas turbine system 1 is used as energy to drive the generator 12. However, the present invention is not limited to this, and for example, the combustion device 10 in the gas turbine system 1 may be applied to a combustion device such as a jet engine or an industrial furnace. Furthermore, in the gas turbine system 1, the rotational power generated by the turbocharger 11 may be used for other purposes (for example, to drive a moving body such as a ship).

[0076] In the above, an example has been described in which the combustion chamber 13c has a substantially cylindrical shape. However, the shape of the combustion chamber 13c is not limited to this example. For example, the combustion chamber 13c may be a space having a substantially truncated cone shape. The shape of the burner plates 14a, 114a, 214a, and 314a can be changed as appropriate depending on the shape of the combustion chamber 13c.

[0077] 1 described above, the air sent from the compressor 11a to the combustor 13 passes between the outer peripheral surface of the liner 13b and the inner peripheral surface of the casing 13a and is then sent to the combustion chamber 13c. However, the path of the air sent from the compressor 11a to the combustor 13 is not limited to this example (i.e., the turn-flow type).

[0078] In the above, an example has been described in which the burner plates (plates) 14a, 114a, 214a, 314a are used in the gas turbine system 1. However, the burner plates 14a, 114a, 214a, 314a may be used in systems other than the gas turbine system 1. For example, the burner plates 14a, 114a, 214a, 314a may be used as heat transfer plates in which flow paths through which water flows are formed.

[0079] In the above, an example has been described in which the burner plates 14a, 114a, 214a, and 314a supply hydrogen to the combustion chamber 13c. However, the fuel supplied to the combustion chamber 13c by the burner plates 14a, 114a, 214a, and 314a is not limited to hydrogen and may be, for example, natural gas. [Explanation of symbols]

[0080] 1 Gas turbine system 10 Combustion equipment 13c Combustion chamber 14a Burner plate 114a Burner plate 214a Burner plate 314a Burner Plate 30 injection hole group 30-1 1st injection hole group 30-2 2nd injection hole group 31 Fuel injection hole 32 First air injection hole 32a First swirl wing 33 Second air injection hole 33a Second swirl wing 40 Communication hole 50 slits 250A cavity 250B Cavity 250C cavity 350 through hole

Claims

1. A plate facing the combustion chamber, a group of a plurality of injection holes formed in an annular shape in the plate; an annular slit formed between the plurality of injection hole groups; Equipped with the plurality of injection hole groups include a first injection hole group and a second injection hole group, Each of the first injection hole group and the second injection hole group includes: a plurality of fuel injection holes facing the combustion chamber and spaced apart in the circumferential direction of the combustion chamber; a first annular air injection hole facing the combustion chamber and extending in the circumferential direction radially outward of the plurality of fuel injection holes; a second annular air injection hole facing the combustion chamber and extending in the circumferential direction radially inward of the plurality of fuel injection holes; Including, the second injection hole group is located radially inward of the first injection hole group, Combustion device.

2. An additively manufactured plate facing the combustion chamber, a group of a plurality of injection holes formed in an annular shape in the plate; an annular slit formed between the plurality of injection hole groups; A combustion device comprising:

3. A plate facing the combustion chamber, a group of a plurality of injection holes formed in an annular shape in the plate; an annular slit formed between the plurality of injection hole groups; Equipped with the plurality of injection hole groups include air injection holes, an opening area of ​​the surface of the air injection hole facing the combustion chamber is smaller than an opening area of ​​the surface of the air injection hole facing away from the combustion chamber; Combustion device.

4. A plate facing the combustion chamber, a group of a plurality of injection holes formed in an annular shape in the plate; an annular slit formed between the plurality of injection hole groups; Equipped with the plate has a flat surface facing the combustion chamber, the injection hole group and the slit are provided on the plane; Combustion device.

5. an annular cavity formed between the plurality of injection hole groups in the plate and communicating with the slit; A combustion device according to any one of claims 1 to 4.

6. a through hole formed on the plate on the opposite side to the combustion chamber and communicating with the annular cavity; The combustion device according to claim 5.

7. The through hole is radially offset from the slit. The combustion device according to claim 6.

8. The combustion device is A casing; a liner provided inside the casing, the combustion chamber being formed inside the liner; a space enclosed by the liner, the plate, and the casing; Furthermore, the slits are formed in the plate between the plurality of injection hole groups, The slit faces the combustion chamber but does not face the space. A combustion device according to any one of claims 1 to 4.

9. the plurality of injection hole groups include a first injection hole group and a second injection hole group, Each of the first injection hole group and the second injection hole group includes: a plurality of fuel injection holes facing the combustion chamber and spaced apart in the circumferential direction of the combustion chamber; at least one annular air injection hole facing into the combustion chamber and extending in the circumferential direction at least one of a radially outer side and a radially inner side with respect to the plurality of fuel injection holes; Including, the at least one annular air injection hole is inclined radially toward the plurality of fuel injection holes with respect to an axial direction of the combustion chamber; A combustion device according to any one of claims 1 to 4.

10. A combustion device according to any one of claims 1 to 4, Gas turbine systems.

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