JP7456554B2 - Combustion equipment and gas turbine systems - Google Patents

Description

TECHNICAL FIELD This disclosure relates to combustion devices and gas turbine systems. This application claims the benefit of priority based on Japanese Patent Application No. 2021-051544 filed on March 25, 2021, the contents of which are incorporated into this application.

Gas turbine systems are used that obtain power by burning fuel in a combustor. Some gas turbine systems use hydrogen as fuel, for example, as disclosed in Patent Document 1. By using hydrogen as a fuel, carbon dioxide emissions are suppressed.

Japanese Patent Application Publication No. 2015-014400

The combustion rate of hydrogen is very fast compared to the combustion rate of other fuels such as natural gas. Therefore, if fuel and air are premixed and supplied from the burner to the combustion chamber of the combustor, as is the case when natural gas etc. This makes it easier for flames to flow back into the room. Furthermore, 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 flame. Thus, there is a high need to protect the burner from flames.

An object of the present disclosure is to provide a combustion device and a gas turbine system in which the burner can be protected from flame.

In order to solve the above problems, a combustion device of the present disclosure includes a combustion chamber, a hydrogen flow path having a hydrogen injection port facing into the combustion chamber, a first air flow path having a first air injection port facing into the combustion chamber, and , a plurality of flow path groups each having a second air injection port facing into the combustion chamber and a second air flow path extending in a direction intersecting the first air flow path; , are arranged in parallel in the circumferential direction of the combustion chamber at intervals from each other .

A plurality of hydrogen channels may be provided in at least one channel group.

In at least one flow path group, the hydrogen flow path is arranged between the first air flow path and the second air flow path in a direction crossing the extending direction of the first air flow path and the extending direction of the second air flow path. It may be placed between the road.

In at least one group of channels, the hydrogen channels are parallel to each other in a direction in which one of the first air channel and the second air channel is inclined with respect to the axial direction of the combustion chamber. may be set.

The combustion chamber may include a burner plate that closes an end of the combustion chamber, and a plurality of flow passage groups may be formed in the burner plate.

A manifold communicating with the plurality of hydrogen channels may be formed in the burner plate.

In order to solve the above problems, a gas turbine system of the present disclosure includes the above combustion device.

According to the present disclosure, the burner can be protected from flame.

FIG. 1 is a schematic diagram showing the configuration of a gas turbine system according to an embodiment of the present disclosure. FIG. 2 is a view of the burner plate according to the embodiment of the present disclosure, viewed from the combustion chamber side. FIG. 3 is a sectional view taken along the line A2-A2 in FIG. FIG. 4 is a diagram of the burner plate according to the first modification as viewed from the combustion chamber side. FIG. 5 is a sectional view taken along the line A3-A3 in FIG. FIG. 6 is a diagram of a burner plate according to a second modification as viewed from the combustion chamber side. FIG. 7 is a sectional view taken along the line A4-A4 in FIG.

Embodiments of the present disclosure will be described below with reference to the accompanying drawings. The dimensions, materials, and other specific numerical values shown in the embodiments are merely examples for easy understanding, and do not limit the present disclosure unless otherwise specified. In this specification and drawings, elements having substantially the same functions and configurations are designated by the same reference numerals to omit redundant explanation, and elements not directly related to the present disclosure are omitted from illustration. do.

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 supercharger 11, a generator 12, a combustor 13, a burner 14, a hydrogen tank 15, and a flow control valve 16.

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

The supercharger 11 has a compressor 11a and a turbine 11b. Compressor 11a and turbine 11b rotate as a unit. The compressor 11a and the turbine 11b are connected by a shaft.

The compressor 11a is provided in an intake passage 21 that is connected to the combustor 13. Air to be supplied to the combustor 13 flows through the intake passage 21. An intake port (not shown) through which air is taken in from the outside is provided at the upstream end of the intake passage 21. The air taken in from 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.

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 exhaust gas is discharged to the outside is provided at the downstream end of the exhaust flow path 22. Exhaust gas discharged from the combustor 13 passes through the turbine 11b and is sent to the exhaust port. The turbine 11b generates rotational power by being rotated by exhaust gas.

Generator 12 is connected to supercharger 11 . The generator 12 uses the rotational power generated by the supercharger 11 to generate electricity.

The combustor 13 has a casing 13a, a liner 13b, and a combustion chamber 13c. The casing 13a has a substantially cylindrical shape. A liner 13b is provided inside the casing 13a. The liner 13b has a substantially cylindrical shape. Liner 13b is arranged coaxially with casing 13a. A 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 substantially cylindrical space. An exhaust flow path 22 is connected to the combustion chamber 13c.

As will be described later, hydrogen and air are supplied to the combustion chamber 13c. In the combustion chamber 13c, hydrogen is used as fuel and combustion occurs. Exhaust gas generated by combustion within the combustion chamber 13c is discharged into the exhaust flow path 22. A space S is formed between the inner surface of the casing 13a and the outer surface of the liner 13b. An intake flow path 21 is connected to the space S. Air is sent to the space S from the compressor 11a via the intake flow path 21. An opening is formed at the end of the liner 13b (the left end in FIG. 1). The burner 14 is inserted into the opening at the end of the liner 13b.

The burner 14 has a burner plate 14a and a plurality of hydrogen supply pipes 14b. Burner plate 14a closes the opening at the end of liner 13b. That is, the burner plate 14a closes the end of the combustion chamber 13c. The burner plate 14a has a disc shape. The hydrogen supply pipe 14b is connected to a surface of the burner plate 14a on the opposite side to the combustion chamber 13c side. The hydrogen supply pipe 14b penetrates the casing 13a and extends to the outside of the casing 13a. In FIG. 1, three hydrogen supply pipes 14b are shown. However, the number of hydrogen supply pipes 14b is not limited.

As described later with reference to FIGS. 2 and 3, the burner plate 14a includes a hydrogen flow path (specifically, a hydrogen flow path 31 described later) and an air flow path (specifically, a hydrogen flow path 31 described later). 1 air flow path 32 and a second air flow path 33) are formed. A hydrogen flow path formed in the burner plate 14a communicates with the hydrogen supply pipe 14b. Hydrogen is sent to the hydrogen supply pipe 14b as described later. Hydrogen sent from the hydrogen supply pipe 14b to the burner plate 14a passes through the hydrogen flow path of the burner plate 14a and is injected into the combustion chamber 13c. As shown by the dashed-dotted line arrow in FIG. 1, the air sent to the space S passes through the space S and then reaches the surface of the burner plate 14a on the opposite side to the combustion chamber 13c side. The air sent to the burner plate 14a is injected into the combustion chamber 13c through the air passage of the burner plate 14a.

Hydrogen is stored in the hydrogen tank 15. Note that hydrogen in the hydrogen tank 15 may be in liquid form or gaseous form. The hydrogen tank 15 is connected to a flow rate control valve 16 via a flow path 23. The flow control valve 16 is connected to each hydrogen supply pipe 14b of the burner 14 via a flow path 24. Hydrogen stored in the hydrogen tank 15 is supplied to the hydrogen supply pipe 14b via the flow path 23, the flow control valve 16, and the flow path 24. The flow control valve 16 controls (that is, adjusts) the flow rate of hydrogen supplied from the hydrogen tank 15 to the hydrogen supply pipe 14b. By adjusting the opening degree of the flow rate control valve 16, the amount of hydrogen supplied from the hydrogen tank 15 to the hydrogen supply pipe 14b is adjusted.

Below, the circumferential direction of the combustion chamber 13c is also simply referred to as the circumferential direction. The radial direction of the combustion chamber 13c is also simply referred to as the radial direction. The axial direction of the combustion chamber 13c is also simply referred to as the axial direction.

FIG. 2 is a diagram of the burner plate 14a viewed from the combustion chamber 13c side (specifically, a diagram viewed from the direction of arrow A1 in FIG. 1). Specifically, FIG. 2 shows a part of the outer peripheral side of the burner plate 14a. FIG. 3 is a sectional view taken along the line A2-A2 in FIG.

As shown in FIGS. 2 and 3, a plurality of channel groups 30 including a hydrogen channel 31, a first air channel 32, and a second air channel 33 are formed in the burner plate 14a. The plurality of flow path groups 30 are arranged in parallel in the circumferential direction. However, the interval (that is, the separation distance in the circumferential direction) between adjacent channel groups 30 is not limited to the examples shown in FIGS. 2 and 3. The plurality of channel groups 30 may be arranged in parallel at equal intervals, or may be arranged in parallel at irregular intervals. However, the arrangement of the plurality of channel groups 30 is not limited to this example, as will be described later.

The hydrogen flow path 31 has a hydrogen injection port 31a facing into the combustion chamber 13c. The hydrogen injection port 31a is provided on the surface of the burner plate 14a on the combustion chamber 13c side. A manifold 40 communicating with the plurality of hydrogen channels 31 is formed in the burner plate 14a. Manifold 40 extends in the circumferential direction. The manifold 40 is, for example, formed in an annular shape. The manifold 40 communicates with the hydrogen channels 31 of each channel group 30. In the example of FIG. 2, the manifold 40 is provided radially outward from the plurality of flow path groups 30. However, the arrangement of the manifold 40 is not limited to this example. For example, the manifold 40 may be provided radially inner than the plurality of flow path groups 30.

A plurality of hydrogen supply pipes 14b of the burner 14 are connected to the manifold 40. Hydrogen is supplied from the plurality of hydrogen supply pipes 14b to the hydrogen channels 31 of each channel group 30 via the manifold 40. Hydrogen supplied to the hydrogen flow path 31 is injected into the combustion chamber 13c from the hydrogen injection port 31a.

The hydrogen flow path 31 is formed in a straight line. The hydrogen flow path 31 is inclined to one side in the circumferential direction (clockwise direction in FIG. 2) with respect to the axial direction on the combustion chamber side. The combustion chamber side axial direction is a direction facing the combustion chamber 13c in the axial direction of the combustion chamber 13c. Inclining in the circumferential direction with respect to the axial direction of the combustion chamber side means extending in the direction of a vector that is a combination of the vector in the axial direction of the combustion chamber side and the vector in the circumferential direction, or inclining in the circumferential direction as it approaches the combustion chamber 13c. It means to lean forward. That is, the extending direction of the hydrogen flow path 31 is a direction that is inclined to one side in the circumferential direction with respect to the axial direction on the combustion chamber side. Therefore, the injection direction of hydrogen injected from the hydrogen injection port 31a is a direction that is inclined to one side in the circumferential direction with respect to the axial direction on the combustion chamber side, as shown by arrow B1. However, as will be described later, the direction in which the hydrogen flow path 31 extends is not limited to this example. Note that the hydrogen flow path 31 may be bent or curved.

The cross-sectional area of the hydrogen flow path 31 is, for example, constant at each position in the extending direction of the hydrogen flow path 31. However, the cross-sectional area of the hydrogen flow path 31 may not be constant at each position in the extending direction of the hydrogen flow path 31. When the cross-sectional area of the hydrogen flow path 31 is smaller at the hydrogen injection port 31a compared to other parts, the injection speed of hydrogen injected from the hydrogen injection port 31a increases, and the mixing of hydrogen and air is reduced. promoted.

The first air flow path 32 has a first air injection port 32a facing into the combustion chamber 13c. The first air injection port 32a is provided on the surface of the burner plate 14a on the combustion chamber 13c side. The first air flow path 32 is provided on the other side of the hydrogen flow path 31 in the circumferential direction (counterclockwise direction in FIG. 2). The first air injection port 32a is provided on the other side in the circumferential direction with respect to the hydrogen injection port 31a. However, as will be described later, the positional relationship between the first air flow path 32 and the hydrogen flow path 31 is not limited to this example.

The first air flow passage 32 is formed in a straight line. The first air flow passage 32 penetrates the burner plate 14a from the combustion chamber 13c side to the opposite side of the combustion chamber 13c side. A portion of the air sent to the burner plate 14a through the space S in the combustor 13 is supplied to the first air flow passage 32. The air supplied to the first air flow passage 32 is injected from the first air injection port 32a into the combustion chamber 13c.

The first air flow path 32 is inclined toward one side in the circumferential direction (clockwise direction in FIG. 2) with respect to the axial direction on the combustion chamber side. That is, the extending direction of the first air flow path 32 is a direction that is inclined to one side in the circumferential direction with respect to the axial direction on the combustion chamber side. Therefore, the injection direction of the air injected from the first air injection port 32a is a direction inclined to one side in the circumferential direction with respect to the axial direction on the combustion chamber side, as shown by arrow B2. However, as will be described later, the extending direction of the first air flow path 32 is not limited to this example. Note that, strictly speaking, the first air flow path 32 may be curved. That is, strictly speaking, the inclination angle of the first air flow path 32 with respect to the combustion chamber side axial direction may be slightly different at each position in the extending direction of the first air flow path 32.

The cross-sectional area of the first air flow path 32 is, for example, constant at each position in the extending direction of the first air flow path 32. However, the cross-sectional area of the first air flow path 32 may not be constant at each position in the extending direction of the first air flow path 32. If the flow path cross-sectional area of the first air flow path 32 is smaller at the first air injection port 32a compared to other parts, the injection speed of the air injected from the first air injection port 32a becomes high, and hydrogen mixing with air is promoted.

The second air flow path 33 has a second air injection port 33a facing into the combustion chamber 13c. The second air injection port 33a is provided on the surface of the burner plate 14a on the combustion chamber 13c side. The second air flow path 33 is provided radially inner than the hydrogen flow path 31 and the first air flow path 32. The second air injection port 33a is provided radially inward with respect to the hydrogen injection port 31a. The circumferential position of the second air injection port 33a is on one side in the circumferential direction (clockwise direction in FIG. 2) from the circumferential position of the first air injection port 32a. The radial position of the second air injection port 33a is radially inner than the radial position of the first air injection port 32a. However, as will be described later, the positional relationship between the second air flow path 33, the hydrogen flow path 31, and the first air flow path 32 is not limited to this example.

The second air flow path 33 is formed in a straight line. The second air passage 33 passes through the burner plate 14a from the combustion chamber 13c side to the opposite side to the combustion chamber 13c side. A portion of the air sent to the burner plate 14a through the space S in the combustor 13 is supplied to the second air flow path 33. The air supplied to the second air flow path 33 is injected into the combustion chamber 13c from the second air injection port 33a.

The second air flow path 33 is inclined toward the other side in the circumferential direction (counterclockwise direction in FIG. 2) with respect to the combustion chamber side axial direction. That is, the extending direction of the second air flow path 33 is a direction inclined toward the other side in the circumferential direction with respect to the axial direction on the combustion chamber side. Therefore, the injection direction of the air injected from the second air injection port 33a is a direction inclined toward the other side in the circumferential direction with respect to the axial direction on the combustion chamber side, as shown by arrow B3. However, as will be described later, the extending direction of the second air passage 33 only needs to intersect with the extending direction of the first air passage 32, and is not limited to this example. Note that, strictly speaking, the second air flow path 33 may be curved. That is, strictly speaking, the inclination angle of the second air flow path 33 with respect to the combustion chamber side axial direction may be slightly different at each position in the extending direction of the second air flow path 33.

The cross-sectional area of the second air flow path 33 is, for example, constant at each position in the extending direction of the second air flow path 33. However, the cross-sectional area of the second air flow path 33 may not be constant at each position in the extending direction of the second air flow path 33. If the flow path cross-sectional area of the second air flow path 33 is smaller at the second air injection port 33a compared to other parts, the injection speed of the air injected from the second air injection port 33a increases, and hydrogen mixing with air is promoted.

As described above, the second air flow path 33 extends in a direction intersecting the first air flow path 32. Therefore, the direction of air ejected from the second air injection port 33a intersects the direction of air injection from the first air injection port 32a. Specifically, as the first air flow path 32 approaches the combustion chamber 13c, it approaches the second air injection port 33a in a direction perpendicular to the axial direction of the combustion chamber 13c. On the other hand, as the second air flow path 33 approaches the combustion chamber 13c, it approaches the first air injection port 32a in a direction perpendicular to the axial direction of the combustion chamber 13c.

Therefore, the air injected from the first air injection port 32a and the air injected from the second air injection port 33a interfere with each other and swirl around the central axis in the axial direction of the combustion chamber 13c, as shown by arrow C1. Hydrogen injected from the hydrogen injection port 31a is injected toward the swirling flow of air shown by arrow C1. Therefore, the hydrogen injected from the hydrogen injection port 31a is mixed with the air while swirling due to the swirling flow of air shown by arrow C1.

As described above, according to the combustion device 10 of the gas turbine system 1, hydrogen injected from the hydrogen injection port 31a is rapidly mixed with air due to the swirling flow of air generated in the combustion chamber 13c. Therefore, compared to the case where hydrogen and air are supplied to the combustion chamber 13c in a pre-mixed state, the ignition position is located inside the combustion chamber 13c. Therefore, backfire is suppressed. Moreover, melting damage of the burner 14 is suppressed. Therefore, the burner 14 can be protected from flame. Furthermore, the flame is held at the center of the swirling flow and stabilized by the swirling flow of air generated within the combustion chamber 13c. Further, by appropriately adjusting the air supply amount and lowering the flame temperature, the amount of NOx emissions can be reduced.

In the combustion device 10, a plurality of flow passage groups 30 are formed in the burner plate 14a that closes the end of the combustion chamber 13c. Therefore, by integrally molding the burner plate 14a using metal lamination technology or the like, the plurality of flow path groups 30 can be easily formed. By integrally molding the burner plate 14a in this way, the structure of the burner 14 is simplified and the burner 14 is made smaller compared to the case where the members forming the plurality of flow path groups 30 are separate from the burner plate 14a. This reduces the manufacturing cost of the burner 14. Furthermore, leakage of hydrogen from the joining portions of the members is suppressed. Furthermore, the occurrence of cracks in the bonded portion due to thermal stress is suppressed.

In the combustion device 10, a manifold 40 that communicates with the plurality of hydrogen channels 31 is formed in the burner plate 14a. Therefore, the manifold 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 miniaturized, and the burner 14 is 14 manufacturing costs are reduced. Furthermore, leakage of hydrogen from the joining portions of the members is suppressed. Furthermore, the occurrence of cracks in the bonded portion due to thermal stress is suppressed.

In addition, each divided part of the burner plate 14a (for example, each part divided at a predetermined angle in the circumferential direction) may be integrally molded using metal lamination technology or the like, and the resulting parts may be assembled. In this case, too, the manufacturing cost of the burner 14 is reduced, hydrogen leakage from the joints of the parts is suppressed, and cracks at the joints due to thermal stress are suppressed.

Hereinafter, gas turbine systems according to each modification will be described with reference to FIGS. 4 to 7. In addition, in the gas turbine system according to each modified example described below, the configuration other than the burner plate is the same as that of the gas turbine system 1 described above, so the description will be omitted.

FIG. 4 is a diagram of the burner plate 14aA according to the first modification as viewed from the combustion chamber 13c side. Specifically, FIG. 4 shows a part of the outer peripheral side of the burner plate 14aA. FIG. 5 is a sectional view taken along the line A3-A3 in FIG. As shown in FIGS. 4 and 5, a combustion device 10A of a gas turbine system 1A according to a first modification includes a burner plate 14aA.

The burner plate 14aA differs from the burner plate 14a described above in that a plurality of hydrogen channels 31 are provided in each channel group 30.

As shown in FIGS. 4 and 5, each channel group 30 formed in the burner plate 14aA has two hydrogen channels 31, a first air channel 32, and a second air channel 33. Similarly to the burner plate 14a described above, in each flow path group 30, the first air flow path 32 is located on the outside in the radial direction with respect to the second air flow path 33. The first air flow path 32 is inclined toward one side in the circumferential direction (clockwise direction in FIG. 4) with respect to the axial direction on the combustion chamber side. The second air flow path 33 is inclined toward the other side in the circumferential direction (counterclockwise direction in FIG. 4) with respect to the combustion chamber side axial direction. The circumferential position of the second air injection port 33a is on one side in the circumferential direction from the circumferential position of the first air injection port 32a. The radial position of the second air injection port 33a is radially inner than the radial position of the first air injection port 32a.

Both of the two hydrogen flow paths 31 have a hydrogen injection port 31a facing into the combustion chamber 13c. Both hydrogen channels 31 communicate with the manifold 40.

In each flow path group 30, one hydrogen flow path 31 (hydrogen flow path 31 on the upper right side in FIG. 4) is located on one side in the circumferential direction (clockwise direction in FIG. 4) with respect to the first air flow path 32. ), and is provided on the outside in the radial direction with respect to the second air flow path 33. The hydrogen injection port 31a of one hydrogen flow path 31 is provided on one side in the circumferential direction with respect to the first air injection port 32a and on the outside in the radial direction with respect to the second air injection port 33a.

One hydrogen flow path 31 is inclined toward one side in the circumferential direction (clockwise direction in FIG. 4) with respect to the axial direction on the combustion chamber side. That is, the extending direction of one hydrogen flow path 31 is a direction that is inclined toward one side in the circumferential direction with respect to the axial direction on the combustion chamber side. Therefore, the injection direction of hydrogen injected from the hydrogen injection port 31a of one hydrogen flow path 31 is a direction inclined to one side in the circumferential direction with respect to the axial direction on the combustion chamber side, as shown by arrow B1.

In each flow path group 30, the other hydrogen flow path 31 (hydrogen flow path 31 on the lower left side in FIG. 4) is located on the other side in the circumferential direction (counterclockwise in FIG. 4) with respect to the second air flow path 33. direction) and is provided radially inward with respect to the first air flow path 32. The hydrogen injection port 31a of the other hydrogen flow path 31 is provided on the other side in the circumferential direction with respect to the second air injection port 33a and on the radially inner side with respect to the first air injection port 32a.

The other hydrogen flow path 31 is inclined toward the other side in the circumferential direction (counterclockwise direction in FIG. 4) with respect to the axial direction on the combustion chamber side. That is, the extending direction of the other hydrogen flow path 31 is a direction that is inclined toward the other side in the circumferential direction with respect to the axial direction on the combustion chamber side. Therefore, the injection direction of hydrogen injected from the hydrogen injection port 31a of the other hydrogen flow path 31 is a direction inclined toward the other side in the circumferential direction with respect to the axial direction on the combustion chamber side, as shown by arrow B4.

Also in the combustion device 10A according to the first modification, similarly to the combustion device 10 described above, combustion is performed by air injected from the first air injection port 32a and air injected from the second air injection port 33a. A swirling flow of air is generated within the chamber 13c. In each flow path group 30, hydrogen injected from the two hydrogen injection ports 31a is injected toward a swirling flow of air indicated by an arrow C1. Therefore, the hydrogen injected from the two hydrogen injection ports 31a is mixed with air while swirling due to the swirling flow of air indicated by the arrow C1. Thereby, the burner 14 can be protected from flame. Furthermore, a reduction in NOx emissions is also achieved.

As described above, in the combustion device 10A according to the first modification, a plurality of (specifically, two) hydrogen flow paths 31 are provided in each flow path group 30. As a result, the amount of hydrogen supplied to the combustion chamber 13c increases compared to the combustion device 10 described above.

In the above, an example in which two hydrogen channels 31 are provided in each channel group 30 has been described. However, in the channel group 30, three or more hydrogen channels 31 may be provided. Further, a plurality of hydrogen channels 31 may be provided only in some of the channel groups 30. If a plurality of hydrogen flow paths 31 are provided in at least one flow path group 30, the same effects as in the above combustion device 10A can be achieved.

FIG. 6 is a diagram of a burner plate 14aB according to a second modification as viewed from the combustion chamber 13c side. Specifically, FIG. 6 shows a part of the outer peripheral side of burner plate 14aB. FIG. 7 is a sectional view taken along the line A4-A4 in FIG. As shown in FIGS. 6 and 7, a combustion device 10B of a gas turbine system 1B according to a second modification includes a burner plate 14aB.

In burner plate 14aB, the positional relationship between hydrogen flow path 31, first air flow path 32, and second air flow path 33 in each flow path group 30 is different from burner plate 14a described above.

As shown in FIGS. 6 and 7, each channel group 30 formed in the burner plate 14aB includes a hydrogen channel 31, a first air channel 32, and a second air channel 33. Similarly to the burner plate 14a described above, in each flow path group 30, the first air flow path 32 is located on the outside in the radial direction with respect to the second air flow path 33. The first air flow path 32 is inclined toward one side in the circumferential direction (clockwise direction in FIG. 6) with respect to the axial direction on the combustion chamber side. The second air flow path 33 is inclined toward the other side in the circumferential direction (counterclockwise direction in FIG. 6) with respect to the combustion chamber side axial direction. The circumferential position of the second air injection port 33a is on one side in the circumferential direction from the circumferential position of the first air injection port 32a. The radial position of the second air injection port 33a is radially inner than the radial position of the first air injection port 32a.

In the second modification, the hydrogen flow path 31 is arranged between the first air flow path 32 and the second air flow path 33 in the radial direction. The hydrogen flow path 31 is separated from the first air flow path 32 and the second air flow path 33 in the radial direction. The hydrogen injection port 31a is arranged between the first air injection port 32a and the second air injection port 33a in the radial direction. The hydrogen injection port 31a is spaced apart from the first air injection port 32a and the second air injection port 33a in the radial direction.

The hydrogen flow path 31 extends in the axial direction of the combustion chamber 13c. That is, the extending direction of the hydrogen flow path 31 is the axial direction of the combustion chamber 13c. Therefore, the injection direction of hydrogen injected from the hydrogen injection port 31a is in the axial direction of the combustion chamber 13c, as shown by arrow B1 in FIG. The center of the hydrogen injection port 31a is arranged near the center between the center of the first air injection port 32a and the center of the second air injection port 33a in the circumferential direction.

In the combustion device 10B according to the second modification, similarly to the combustion device 10 described above, combustion is performed by air injected from the first air injection port 32a and air injected from the second air injection port 33a. A swirling flow of air is generated within the chamber 13c. Hydrogen injected from the hydrogen injection port 31a is injected toward the swirling flow of air indicated by arrow C1. Therefore, the hydrogen injected from the hydrogen injection port 31a is mixed with air while swirling due to the swirling flow of air indicated by the arrow C1. Thereby, the burner 14 can be protected from flame. Furthermore, a reduction in NOx emissions is also achieved.

As described above, in the combustion device 10B according to the second modified example, in each flow path group 30, the hydrogen flow path 31 is disposed between the first air flow path 32 and the second air flow path 33 in a direction (specifically, a radial direction) intersecting the extension direction of the first air flow path 32 and the extension direction of the second air flow path 33. This suppresses interference between the first air flow path 32 or the second air flow path 33 and the hydrogen flow path 31 compared to the above-mentioned combustion device 10. Therefore, the degree of freedom in arranging the hydrogen flow path 31 is improved.

For example, as in the above example, by setting the extending direction of the hydrogen flow path 31 and the position of the hydrogen injection port 31a with respect to the first air injection port 32a and the second air injection port 33a, Hydrogen can be injected from the hydrogen injection port 31a toward the center of the swirling flow of air. This makes it difficult for hydrogen injected from the hydrogen injection port 31a to escape from the swirling flow of air. Therefore, hydrogen injected from the hydrogen injection port 31a can be appropriately mixed with air.

In the above, in each channel group 30, the hydrogen channel 31 is arranged in a direction intersecting the extending direction of the first air channel 32 and the extending direction of the second air channel 33 (specifically, the direction in which the hydrogen channel 31 is radially An example has been described in which the air conditioner is arranged between the first air flow path 32 and the second air flow path 33 in the direction). However, in only some of the flow path groups 30, the hydrogen flow path 31 is arranged so that the first air flow path 31 crosses the extending direction of the first air flow path 32 and the second air flow path 33. It may be arranged between the flow path 32 and the second air flow path 33. In at least one flow path group 30, the hydrogen flow path 31 is located at the first air flow path 32 in a direction intersecting the extending direction of the first air flow path 32 and the extending direction of the second air flow path 33. If it is arranged between the combustion device 10B and the second air flow path 33, the same effects as those of the combustion device 10B described above can be achieved.

Note that, like the combustion device 10 described above, in at least one channel group 30, the hydrogen channel 31 is aligned with the axis of the combustion chamber 13c, and one of the first air channel 32 and the second air channel 33 is aligned with the axis of the combustion chamber 13c. They may be arranged in parallel to the one flow path in a direction that is inclined with respect to the flow direction. For example, in the example of FIG. 2, the first air flow path 32 is inclined in the circumferential direction with respect to the axial direction of the combustion chamber 13c. The hydrogen flow path 31 is arranged in parallel with the first air flow path 32 in the circumferential direction. Even in such a case, the hydrogen injected from the hydrogen injection port 31a is mixed with air while swirling due to the swirling flow of air.

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 those skilled in the art can come up with various changes and modifications within the scope of the claims, and it is understood that these naturally fall within the technical scope of the present disclosure. be done.

In the above, an example has been described in which the rotational power generated by the supercharger 11 is used as energy to drive the generator 12 in the gas turbine system 1, the gas turbine system 1A, and the gas turbine system 1B. 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 is used for other purposes (for example, for driving a moving body such as a ship). Good too.

In the above, an example has been described in which the extending direction of the first air flow path 32 is inclined toward one side in the circumferential direction (clockwise direction in FIG. 2) with respect to the axial direction on the combustion chamber side. However, the extending direction of the first air flow path 32 is not limited to the above example. For example, the extending direction of the first air flow path 32 may be inclined in the radial direction with respect to the axial direction on the combustion chamber side. The extending direction of the first air flow path 32 may be different between each flow path group 30.

Similarly to the extending direction of the first air flow path 32, the direction in which the second air flow path 33 extends is not limited to the above example. For example, the extending direction of the second air flow path 33 may be inclined in the radial direction with respect to the axial direction on the combustion chamber side. However, the direction in which the second air flow path 33 extends intersects the direction in which the first air flow path 32 extends. The extending directions of the second air flow paths 33 may be different between each flow path group 30.

The extension direction of the hydrogen flow path 31 is not limited to the above example, as is the extension direction of the first air flow path 32. For example, the extension direction of the hydrogen flow path 31 may be inclined radially with respect to the combustion chamber side axial direction. Also, for example, in the gas turbine system 1 or gas turbine system 1A, the extension direction of the hydrogen flow path 31 may not coincide with the extension direction of either the first air flow path 32 or the second air flow path 33. Also, for example, in the gas turbine system 1B, the extension direction of the hydrogen flow path 31 may coincide with the extension direction of the first air flow path 32 or the second air flow path 33. The extension direction of the hydrogen flow path 31 may differ between each flow path group 30.

In the above, an example of the positional relationship between the hydrogen flow path 31, the first air flow path 32, and the second air flow path 33 in each flow path group 30 has been described with reference to each drawing. However, the positional relationship between the hydrogen flow path 31, the first air flow path 32, and the second air flow path 33 in each flow path group 30 is not limited to this example. For example, the second air flow path 33 may be provided outside the first air flow path 32 in the radial direction. The positional relationship between the hydrogen flow path 31, the first air flow path 32, and the second air flow path 33 may be different between each flow path group 30.

In the above, an example has been described in which a plurality of flow path groups 30 are arranged in parallel in the circumferential direction of the combustion chamber 13c. However, the arrangement of the plurality of channel groups 30 is not limited to this example. For example, a plurality of flow passage groups 30 arranged in parallel in the circumferential direction may be arranged in parallel in the radial direction of the combustion chamber 13c.

In the above example, 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 substantially cylindrical space. The shapes of burner plate 14a, burner plate 14aA, and burner plate 14aB may be changed as appropriate depending on the shape of combustion chamber 13c.

In the example of Figure 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 then is 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).

1: Gas turbine system 1A: Gas turbine system 1B: Gas turbine system 10: Combustion device 10A: Combustion device 10B: Combustion device 13c: Combustion chamber 14a: Burner plate 14aA: Burner plate 14aB: Burner plate 30: Channel group 31: Hydrogen flow path 31a: Hydrogen injection port 32: First air flow path 32a: First air injection port 33: Second air flow path 33a: Second air injection port 40: Manifold

Claims (7)

A combustion chamber;
a hydrogen flow path having a hydrogen nozzle facing the combustion chamber, a first air flow path having a first air nozzle facing the combustion chamber, and a second air flow path having a second air nozzle facing the combustion chamber and extending in a direction intersecting the first air flow path;
Equipped with
The plurality of flow passage groups are arranged side by side in the circumferential direction of the combustion chamber at intervals from each other.
Combustion device. In at least one group of channels, a plurality of hydrogen channels are provided;
The combustion device according to claim 1. In at least one of the flow path groups, the hydrogen flow path is disposed between the first air flow path and the second air flow path in a direction intersecting an extension direction of the first air flow path and an extension direction of the second air flow path.
A combustion device according to claim 1 or 2. In at least one of the flow passage groups, the hydrogen flow passage is arranged in parallel with one of the first air flow passage and the second air flow passage in a direction inclined with respect to an axial direction of the combustion chamber.
A combustion device according to claim 1 or 2. A burner plate is provided to close an end of the combustion chamber,
The burner plate is formed with the plurality of flow path groups.
Combustion device according to any one of claims 1 to 4. The burner plate is formed with a manifold that communicates with the plurality of hydrogen flow paths.
The combustion device according to claim 5. comprising the combustion device according to any one of claims 1 to 6,
gas turbine system.

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