Combustion device and gas turbine system

Abstract

A combustion device 30 comprises: a liner 110 having a combustion chamber 115 formed inside a side wall section 110b; a burner 40 that is provided to the liner and injects fuel into the combustion chamber; an air introduction part 111 that is provided at the burner or in the vicinity of the burner and introduces air into the combustion chamber; an isolated wall section 120a that is provided more radially outward of the liner than the side wall section and forms, together with the side wall section, an inner flow path 122 communicating with the air introduction part; an outer wall section 101b provided more radially outward of the liner than the isolated wall section and forms, together with the isolated wall section, an outer flow path 124; a plurality of communication holes 126 that are formed in the isolated wall section so as to be spaced apart from each other in the central axis direction of the liner and communicate the inner flow path and the outer flow path; and a partition wall 130 that is provided in the inner flow path and partitions the inner flow path in the central axis direction of the liner.

Description

Combustion equipment and gas turbine systems

[0001] This application claims the benefit of priority from Japanese Patent Application No. 2023-198331, filed on November 22, 2023, the contents of which are incorporated herein by reference.

[0002] 2. Description of the Related Art Gas turbine systems are used to generate power by burning fuel in a combustor. For example, Patent Document 1 discloses a gas turbine system that uses low-calorie fuel instead of fossil fuel. In this gas turbine system, a primary combustion zone where rich combustion is performed and a secondary combustion zone where lean combustion is performed are provided within a liner.

[0003] Patent No. 5591408

[0004] In the above-described gas turbine system, the liner is cooled by air supplied from the compressor to the outer passage. Furthermore, a portion of the air that has cooled the liner is supplied to the burner. In such a gas turbine system, if the flow rate of the air supplied to the burner decreases, there is a risk that the amount of harmful components, such as NOx, contained in the combustion gas will increase.

[0005] An object of the present disclosure is to provide a combustion device and a gas turbine system that are capable of suppressing an increase in harmful components in combustion gas.

[0006] In order to solve the above problems, the combustion device of the present disclosure comprises: a liner having a combustion chamber formed inside a side wall portion; a burner provided in the liner and for injecting fuel into the combustion chamber; an air inlet portion provided at or near the burner and for introducing air into the combustion chamber; a partition wall portion provided radially outward of the liner than the side wall portion and forming an inner flow passage communicating with the air inlet portion between the side wall portion; an outer wall portion provided radially outward of the liner than the partition wall portion and forming an outer flow passage between the partition wall portion; a plurality of communication holes formed in the partition wall portion at intervals in the central axial direction of the liner, for communicating the inner flow passage with the outer flow passage; and a partition wall provided in the inner flow passage and separating the inner flow passage in the central axial direction of the liner.

[0007] The combustion device may further include a second air introduction portion formed in the side wall portion at a position farther away from the burner in the central axis direction than the partition wall, and connecting the inner flow path and the combustion chamber.

[0008] The combustion chamber may include a primary region located closer to the burner than the second air introduction portion, and a secondary region located farther away from the burner in the central axis direction than the second air introduction portion, and the partition wall may be located radially outside the primary region.

[0009] In order to solve the above problems, a gas turbine system according to the present disclosure includes the above combustion device.

[0010] According to the present disclosure, an increase in harmful components in combustion gas can be suppressed.

[0011] 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 diagram explaining the operation of a combustion device according to an embodiment. Fig. 3 is a schematic diagram showing the configuration of a gas turbine system according to a first modified example. Fig. 4 is a schematic diagram showing the configuration of a gas turbine system according to a second modified example.

[0012] 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.

[0013] 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 10, a generator 20, and a combustion device 30. The combustion device 30 includes a burner 40, an ammonia tank 50, a flow control valve 60, and a combustor 100.

[0014] The turbocharger 10 includes a compressor 10 a and a turbine 10 b. The impeller of the compressor 10 a and the impeller of the turbine 10 b rotate as a unit. The impeller of the compressor 10 a and the impeller of the turbine 10 b are connected by a shaft.

[0015] The compressor 10a is provided in an intake air flow path 11. Air to be supplied to the combustor 100 flows through the intake air flow path 11. 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 11. The air taken in through the intake port passes through the compressor 10a and is sent to the combustor 100. The compressor 10a compresses the air and discharges it into the combustor 100.

[0016] The turbine 10b is provided in an exhaust flow path 12 connected to the combustor 100. Combustion gas discharged from the combustor 100 flows through the exhaust flow path 12. An exhaust port (not shown) through which the combustion gas is discharged to the outside is provided at the downstream end of the exhaust flow path 12. The combustion gas discharged from the combustor 100 passes through the turbine 10b and is sent to the exhaust port. The turbine 10b generates rotational power when an impeller of the turbine 10b is rotated by the combustion gas.

[0017] The generator 20 is connected to the turbocharger 10. The generator 20 generates electricity using the rotational power generated by the turbocharger 10.

[0018] The burner 40 of the combustion device 30 injects ammonia as fuel into the inside of the combustor 100. The burner 40 has a substantially cylindrical shape. The burner 40 is attached to a casing 101 (described later) of the combustor 100. The tip end of the burner 40 is located inside the casing 101, and the rear end of the burner 40 is located outside the casing 101.

[0019] An injection valve (not shown) is provided at the tip end of the burner 40. An ammonia tank 50 is connected to the rear end of the burner 40. Liquid ammonia is stored in the ammonia tank 50. A flow path connecting the ammonia tank 50 and the burner 40 is provided with a flow control valve 60. The ammonia stored in the ammonia tank 50 is supplied to the burner 40. The flow control valve 60 controls the flow rate of the ammonia supplied from the ammonia tank 50 to the burner 40. Note that the flow path connecting the ammonia tank 50 and the burner 40 may be provided with various devices (e.g., shut-off valves, check valves, various sensors, etc.) not shown in FIG. 1 .

[0020] The combustor 100 includes a casing 101. The casing 101 is configured in a generally cylindrical shape with a bottom, having a bottom surface 101a and an outer wall portion 101b. An opening 101c connected to the intake passage 11 is formed at the end of the outer wall portion 101b opposite the bottom surface 101a. A burner 40 is inserted into the bottom surface 101a of the casing 101. The burner 40 is located approximately in the center of the bottom surface 101a. In other words, the burner 40 is provided on the central axis of the casing 101.

[0021] A liner 110 is housed inside the casing 101. The liner 110 is configured in a generally cylindrical shape with a bottom, having a bottom 110a and a sidewall 110b. The central axis of the liner 110 generally coincides with the central axis of the casing 101. Therefore, the central axis of the liner 110 coincides with the central axis of the burner 40. Hereinafter, the central axis of the liner 110 may be simply referred to as the "central axis" or "center." Furthermore, the direction perpendicular to the central axis, i.e., the radial direction of the liner 110, will be simply referred to as the "radial direction."

[0022] The outer diameter of the liner 110 is smaller than the inner diameter of the casing 101. This forms an annular space between the liner 110 and the casing 101. Furthermore, the bottom 110a of the liner 110 is spaced apart from the bottom surface 101a of the casing 101 in the central axis direction. Therefore, a gap is formed between the bottom surface 101a of the casing 101 and the bottom 110a of the liner 110.

[0023] A burner insertion hole 110c is formed in the bottom 110a of the liner 110. The tip of the burner 40 is inserted into the burner insertion hole 110c. The inner diameter of the burner insertion hole 110c is larger than the outer diameter of the burner 40. As a result, an annular air introduction part 111 is formed in the bottom 110a of the liner 110, penetrating the bottom 110a in the central axis direction. In other words, the air introduction part 111 is provided in the vicinity of the burner 40, or more strictly, around the burner 40.

[0024] The liner 110 also includes a large diameter portion 112, a reduced diameter portion 113, and a small diameter portion 114. The large diameter portion 112 is located closer to the burner 40 than the reduced diameter portion 113 and the small diameter portion 114. The small diameter portion 114 is located farther away from the burner 40 in the central axial direction than the large diameter portion 112 and the reduced diameter portion 113. The inner diameter of the small diameter portion 114 is smaller than the inner diameter of the large diameter portion 112. The reduced diameter portion 113 connects the large diameter portion 112 and the small diameter portion 114. The diameter of the reduced diameter portion 113 decreases from the large diameter portion 112 toward the small diameter portion 114. In other words, the reduced diameter portion 113 has a tapered shape. However, the reduced diameter portion 113 may extend in the radial direction. An opening 114a, to which the exhaust flow path 12 is connected, is formed at the end of the small diameter portion 114 opposite the reduced diameter portion 113.

[0025] Here, the inner diameter of the large diameter portion 112 is substantially constant regardless of the position in the central axis direction. However, the inner diameter of the large diameter portion 112 may vary depending on the position in the central axis direction. For example, the large diameter portion 112 may have a tapered shape in which the diameter increases or decreases as the portion becomes farther away from the burner 40. Similarly, the inner diameter of the small diameter portion 114 may vary depending on the position in the central axis direction. For example, the small diameter portion 114 may have a tapered shape in which the diameter increases or decreases as the portion becomes farther away from the burner 40.

[0026] Furthermore, the entire liner 110 may have a tapered shape in which the diameter gradually decreases as it moves away from the burner 40. In this case, a certain range of the liner 110 on the burner 40 side becomes a large diameter portion 112, and a certain range on the side away from the burner 40 becomes a small diameter portion 114. Furthermore, the liner 110 may have a constant diameter from the bottom 110a to the opening 114a. In any case, the shape of the liner 110 is not limited to the example in FIG. 1.

[0027] A combustion chamber 115 is formed inside the side wall portion 110b, i.e., inside the liner 110. The air introduction portion 111 connects the combustion chamber 115 to a space formed between the bottom portion 110a of the liner 110 and the bottom surface 101a of the casing 101. The air introduction portion 111 introduces air into the combustion chamber 115.

[0028] Here, an air introduction section 111 that introduces air into the combustion chamber 115 is provided near the burner 40. That is, the air introduction section 111 is provided separately from the burner 40. However, the air introduction section 111 may also be provided in the burner 40. In this case, for example, the air introduction section 111 formed inside the burner 40 may be open to the space formed between the bottom 110a of the liner 110 and the bottom surface 101a of the casing 101. Even in this case, the air introduced into the air introduction section 111 is injected into the combustion chamber 115 via the burner 40. At this time, the air may be injected separately from the fuel, or may be mixed with the fuel in the burner 40 and injected as an air-fuel mixture.

[0029] Furthermore, the liner 110 is provided with a through hole 116 that penetrates the inside and outside of the side wall portion 110b. The through hole 116 penetrates the liner 110 in the radial direction. Here, a plurality of through holes 116 are provided in the liner 110. The plurality of through holes 116 are, for example, positioned at equal positions in the central axis direction of the liner 110 and spaced apart from one another in the circumferential direction. However, only one through hole 116 may be provided in the liner 110. Furthermore, when a plurality of through holes 116 are provided, the plurality of through holes 116 may be positioned at different positions in the central axis direction.

[0030] Here, the through hole 116 is provided in the large diameter portion 112. The through hole 116 is provided at a position farther away from the burner 40 than the central position of the large diameter portion 112 in the central axial direction. However, the through hole 116 may be provided in the reduced diameter portion 113 or the small diameter portion 114. The through hole 116 functions as a second air introduction portion that introduces air from the outside of the liner 110 into the combustion chamber 115. Note that, hereinafter, the air introduced into the combustion chamber 115 from the through hole 116 is referred to as dilution air.

[0031] 1, the combustion chamber 115 includes a primary region 115a located closer to the burner 40 than the through-hole 116, and a secondary region 115b provided at a position farther away from the burner 40 in the central axis direction than the primary region 115a. Here, the secondary region 115b is defined as a range farther away from the burner 40 in the central axis direction than the through-hole 116 (at its end on the burner 40 side).

[0032] The liner 110 is also provided with a second through hole 117 that penetrates the inside and outside of the side wall portion 110b. The second through hole 117 penetrates the liner 110 in the radial direction. The second through hole 117 is located closer to the opening 114a than the through hole 116. Here, the second through hole 117 is smaller than the through hole 116. However, the size of the second through hole 117 may be the same as or larger than the through hole 116. Here, multiple second through holes 117 are provided in the liner 110. The multiple second through holes 117 are, for example, positioned at equal positions in the central axial direction of the liner 110 and spaced apart from each other in the circumferential direction. However, only one second through hole 117 may be provided in the liner 110. Furthermore, when multiple second through holes 117 are provided, the multiple second through holes 117 may be positioned at different positions in the central axial direction.

[0033] An annular guide member 118 is provided inside the liner 110. The guide member 118 includes a guide surface 118a extending in the circumferential direction and a flange portion 118b extending radially outward from the guide surface 118a. The guide member 118 is provided radially inward of the second through hole 117, with the second through hole 117 facing the guide surface 118a. A small gap is formed between the guide surface 118a and the second through hole 117. The flange portion 118b is provided at the end of the guide surface 118a facing the burner 40. The radially outer side of the flange portion 118b is connected to the inner circumferential surface of the side wall portion 110b. As a result, the space formed between the second through hole 117 and the guide surface 118a is sealed on the burner 40 side and open on the opening 114a side.

[0034] The combustor 100 also includes a flow path forming member 120. The flow path forming member 120 is provided between the side wall portion 110b and the outer wall portion 101b. The flow path forming member 120 includes a separation wall portion 120a located radially outward of the side wall portion 110b and radially inward of the outer wall portion 101b. The separation wall portion 120a is radially separated from both the side wall portion 110b and the outer wall portion 101b. The separation wall portion 120a has an annular shape substantially parallel to the central axis direction and faces the outer wall portion 101b and the side wall portion 110b substantially parallel to each other. However, the separation wall portion 120a may have a tapered shape inclined with respect to the central axis. Alternatively, the diameter of the separation wall portion 120a may vary depending on the position in the central axis direction.

[0035] The flow path forming member 120 also has a first end 120b and a second end 120c. The first end 120b is provided at the end of the partition wall 120a that faces the burner 40 and extends radially outward from the partition wall 120a. The radially outer side of the first end 120b is connected to the outer wall 101b. The second end 120c is provided at the end of the partition wall 120a that faces the opening 114a and extends radially inward from the partition wall 120a. The radially inner side of the second end 120c is connected to the side wall 110b.

[0036] The space formed between the outer wall portion 101b and the side wall portion 110b is radially partitioned by the partition wall portion 120a. Specifically, the partition wall portion 120a is provided radially outward of the liner 110 relative to the side wall portion 110b, and forms an inner flow path 122 between the partition wall portion 120a and the side wall portion 110b. The outer wall portion 101b is also provided radially outward of the liner 110 relative to the partition wall portion 120a, and forms an outer flow path 124 between the partition wall portion 120a and the side wall portion 110b. In other words, the space formed between the outer wall portion 101b and the side wall portion 110b is partitioned by the partition wall portion 120a into an inner flow path 122 located radially inward of the partition wall portion 120a and an outer flow path 124 located radially outward of the partition wall portion 120a.

[0037] The inner flow passage 122 communicates with the air introduction section 111. The outer flow passage 124 is connected to the intake flow passage 11 at the opening 101c. The end of the outer flow passage 124 on the burner 40 side is sealed by a first end 120b. The end of the inner flow passage 122 on the opening 101c side is sealed by a second end 120c.

[0038] A plurality of communication holes 126 are formed in the partition wall portion 120a. The communication holes 126 are formed in the partition wall portion 120a at intervals in the central axial direction of the liner 110, and connect the inner flow path 122 and the outer flow path 124. In other words, the inner flow path 122 and the outer flow path 124 are connected via the plurality of communication holes 126. The communication holes 126 are also formed at intervals in the circumferential direction. Here, the communication holes 126 are smaller than the through holes 116. Note that, although the plurality of communication holes 126 are all the same size, a plurality of communication holes 126 with different sizes and shapes may be provided. The size, shape, and number of the communication holes 126 are merely an example and are not particularly limited.

[0039] The inner flow passage 122 is provided with a partition wall 130 that divides the inner flow passage 122 in the central axis direction of the liner 110. The partition wall 130 is formed in an annular shape, with its inner diameter end connected to the side wall portion 110b and its outer diameter end connected to the separation wall portion 120a. The partition wall 130 divides the inner flow passage 122 into a first inner flow passage 122a located on the burner 40 side and a second inner flow passage 122b located on the opening 114a side. The first inner flow passage 122a communicates with the air introduction portion 111. The second inner flow passage 122b communicates with the through hole 116. Therefore, the through hole 116 communicates between the second inner flow passage 122b and the combustion chamber 115. The through hole 116 is formed at a position farther away from the burner 40 in the central axis direction than the partition wall 130. Furthermore, since the primary region 115a is provided closer to the burner 40 than the through-hole 116, the partition wall 130 is located radially outward of the primary region 115a.

[0040] The communication holes 126 are provided on both sides in the central axis direction of the partition wall 130. In Fig. 1, the number of communication holes 126 provided on the burner 40 side of the partition wall 130 is equal to the number of communication holes 126 provided on the opening 114a side of the partition wall 130. However, the number of communication holes 126 provided on the burner 40 side of the partition wall 130 and the opening 114a side of the partition wall 130 may differ.

[0041] 2 is a diagram illustrating the operation of the combustion device 30 according to this embodiment. As shown in FIG. 2, the intake air flow path 11 is connected to the outer flow path 124, and air compressed by the compressor 10a is supplied to the outer flow path 124. The air sent to the outer flow path 124 is guided toward the burner 40 along the partition wall 120a, as indicated by the dashed-dotted arrow in the figure. The air flowing through the outer flow path 124 then flows from the communication holes 126 into the first inner flow path 122a and the second inner flow path 122b.

[0042] The air that has flowed into the first inner flow path 122a is injected from the air inlet 111 into the combustion chamber 115, particularly into the primary zone 115a. Ammonia, the flow rate of which is adjusted by the flow control valve 60, is supplied as fuel to the burner 40. Fuel is injected into the combustion chamber 115 from an injection valve provided at the tip of the burner 40. At this time, the fuel may be injected from the burner 40 in the direction of the central axis. Alternatively, the fuel may be injected in a direction that expands radially as it moves away from the burner 40.

[0043] The injection valve provided in the burner 40 is a pressure injection valve or an airflow injection valve. A pressure injection valve is a type of valve that atomizes a liquid by utilizing the pressure difference between the inside and outside of the pressure injection valve. An airflow injection valve is a type of valve that generates a film of the liquid to be injected and atomizes the liquid by utilizing the shear force between the film and the air. However, the configuration of the injection valve is not particularly limited. Also, although liquid ammonia is used as the fuel here, gaseous ammonia may also be used. Furthermore, in addition to ammonia, other fuels such as natural gas or hydrogen may also be used as the fuel supplied to the combustion chamber 115.

[0044] The fuel injected from the burner 40 is mixed with the air injected from the air inlet 111 to generate an air-fuel mixture. That is, the air-fuel mixture is supplied to the combustion chamber 115. The combustor 100 is provided with an ignition device (not shown), and ignition by the ignition device causes combustion in the combustion chamber 115. Combustion gas generated by the combustion is discharged into the exhaust flow path 12 connected to the opening 114a.

[0045] Here, the flow rates of air and fuel are adjusted so that the equivalence ratio of the air-fuel mixture in the primary zone 115a is fuel-rich, approximately 1.0 to 1.5. Therefore, combustion in the primary zone 115a is rich combustion. Meanwhile, through-holes 116 are formed in the liner 110, and dilution air is supplied to the combustion chamber 115 from the second inner flow passage 122b via the through-holes 116. In the secondary zone 115b, the dilution air is mixed with the air-fuel mixture, and combustion in the secondary zone 115b is lean combustion. Thus, in this embodiment, rich combustion is performed in the primary zone 115a, and lean combustion is performed in the secondary zone 115b.

[0046] Furthermore, the air that flows into the first inner flow passage 122a cools the side wall portion 110b of the liner 110 and is then injected from the air inlet portion 111 into the combustion chamber 115. On the other hand, the air that flows into the second inner flow passage 122b cools the side wall portion 110b of the liner 110 and is then introduced into the combustion chamber 115 from the through-holes 116 as dilution air. In other words, the side wall portion 110b on the burner 40 side of the partition wall 130 is cooled by the air supplied to the burner 40. On the other hand, the side wall portion 110b on the opening 114a side of the partition wall 130 is cooled by the air introduced into the combustion chamber 115 from the through-holes 116.

[0047] Here, when the flow rate of air supplied to the air inlet 111 decreases, NOx and unburned NH4 generated from ammonia ３ , N ２ If the partition wall 130 is not provided, the range of the inner flow path 122 through which the air supplied to the air introduction portion 111 passes becomes wider. In this case, it becomes difficult to design a system for supplying air at an appropriate flow rate and flow velocity to the air introduction portion 111. As a result, the flow rate of the air supplied to the air introduction portion 111 decreases, and emissions may increase. According to this embodiment, the partition wall 130 limits the flow range of the inner flow path 122 through which the air supplied to the air introduction portion 111 flows. As a result, air at an appropriate flow rate and flow velocity can be supplied to the air introduction portion 111.

[0048] The partition wall 130 also limits the range of the second inner flow passage 122b. That is, the cooling range of the dilution air supplied to the combustion chamber 115 from the through-holes 116 is limited. This increases the cooling effect of the liner 110 by the dilution air. In particular, in impingement cooling, which cools the liner 110 by flowing air along the side wall portion 110b, the cooling effect decreases when the amount of air flowing along the side wall portion 110b increases. In this embodiment, the area of ​​the side wall portion 110b facing each of the first inner flow passage 122a and the second inner flow passage 122b is reduced, thereby suppressing the amount of air flowing along the side wall portion 110b. This prevents a decrease in the cooling effect.

[0049] Furthermore, within the inner flow passage 122, the partition wall 130 is located at the most upstream position in the air flow direction. That is, the partition wall 130 is located at the most upstream position in each of the first inner flow passage 122a and the second inner flow passage 122b. Therefore, the partition wall 130 comes into contact with the air with the highest cooling capacity within the inner flow passage 122. When a flame-retardant fuel such as ammonia is used, the flame is likely to be located downstream of the outlet of the burner 40, and the temperature tends to rise in the vicinity of the center of the primary zone 115a in the central axis direction. By locating the partition wall 130, which comes into contact with the air with the highest cooling capacity, at a position where the temperature tends to rise, the cooling efficiency of the liner 110 is improved.

[0050] The secondary region 115b is provided with second through holes 117. The air that flows into the combustion chamber 115 from the second through holes 117 flows along the side wall portion 110b of the liner 110. This cools the area of ​​the side wall portion 110b of the liner 110 that surrounds the secondary region 115b.

[0051] Below, we will explain each of the modified examples of the above-mentioned embodiment. In the following, we will explain the configuration of each modified example that is different from the above-mentioned embodiment, and the same configuration as the above-mentioned embodiment will be given the same reference numerals as above, and detailed explanations will be omitted. Therefore, each of the modified examples described below has the same configuration as the above-mentioned embodiment unless otherwise specified.

[0052] FIG. 3 is a schematic diagram showing the configuration of a gas turbine system 1A according to a first modified example. The first modified example differs from the above embodiment in that the second through-hole 117 opens into the second inner flow passage 122b. The first modified example differs from the above embodiment in the length of the partition wall 120a in the central axis direction, but the other configurations are the same as those of the above embodiment. In the first modified example, the partition wall 120a is longer in the central axis direction than the above embodiment, and the second end portion 120c is provided closer to the opening 114a than the second through-hole 117. As a result, the through-hole 116 and the second through-hole 117 are provided in the second inner flow passage 122b. Therefore, a portion of the air that flows from the outer flow passage 124 into the second inner flow passage 122b via the communication hole 126 flows into the combustion chamber 115 through the through-hole 116, and another portion flows into the combustion chamber 115 through the second through-hole 117. The first modified example also achieves the same functions and effects as the above embodiment.

[0053] In the above embodiment and the first modified example, for example, one or more second through holes 117 and guide members 118 may be provided closer to the burner 40 than the through holes 116. In this case, the second through holes 117 and guide members 118 may be provided closer to the burner 40 than the partition wall 130, or closer to the opening 114a than the partition wall 130. In other words, cooling of the side wall portion 110b by the air flowing into the combustion chamber 115 from the second through holes 117 may be performed in the primary zone 115a.

[0054] 4 is a schematic diagram showing the configuration of a gas turbine system 1B according to a second modification. A combustor 100 according to the second modification is provided with a first liner 210 and a second liner 220 instead of the liner 110 of the above embodiment. The first liner 210 and the second liner 220 are housed inside a casing 101. The first liner 210 and the second liner 220 have a substantially cylindrical shape. The first liner 210 and the second liner 220 are separate bodies, i.e., configured from separate members.

[0055] Within the casing 101, the first liner 210 is provided closer to the burner 40 than the second liner 220. The outer diameters of the first liner 210 and the second liner 220 are smaller than the inner diameter of the casing 101. As a result, an outer flow passage 124 is formed between the casing 101 and the first liner 210 and the second liner 220.

[0056] The central axes of the first liner 210 and the second liner 220 substantially coincide with the central axes of the casing 101 and the burner 40. The first liner 210 is configured in a substantially bottomed cylindrical shape having a bottom 210a and a side wall 210b. A burner insertion hole 210c is formed in the bottom 210a of the first liner 210. The tip of the burner 40 is inserted into the burner insertion hole 210c. The inner diameter of the burner insertion hole 210c is larger than the outer diameter of the burner 40. As a result, an annular air introduction portion 111 is formed in the bottom 210a of the first liner 210, penetrating the bottom 210a in the central axis direction.

[0057] The first liner 210 also includes a large diameter portion 212, a reduced diameter portion 213, and a small diameter portion 214. The large diameter portion 212 is located closer to the burner 40 than the reduced diameter portion 213 and the small diameter portion 214. The small diameter portion 214 is located farther away from the burner 40 in the central axial direction than the large diameter portion 212 and the reduced diameter portion 213. The inner diameter of the small diameter portion 214 is smaller than the inner diameter of the large diameter portion 212. The reduced diameter portion 213 connects the large diameter portion 212 and the small diameter portion 214. The diameter of the reduced diameter portion 213 decreases from the large diameter portion 212 toward the small diameter portion 214. In other words, the reduced diameter portion 213 has a tapered shape. However, the reduced diameter portion 213 may extend in the radial direction. An opening 214a is formed in the end of the small diameter portion 214 opposite the reduced diameter portion 213.

[0058] In the second modified example, the inner diameter of the large diameter portion 212 of the first liner 210 is substantially constant regardless of the position in the central axis direction. However, the inner diameter of the large diameter portion 212 may vary depending on the position in the central axis direction. For example, the large diameter portion 212 may have a tapered shape in which the diameter increases or decreases as the portion becomes farther away from the burner 40. Similarly, the inner diameter of the small diameter portion 214 may vary depending on the position in the central axis direction. For example, the small diameter portion 214 may have a tapered shape in which the diameter increases or decreases as the portion becomes farther away from the burner 40.

[0059] Furthermore, the entire first liner 210 may have a tapered shape in which the diameter gradually decreases as it moves away from the burner 40. Furthermore, the first liner 210 may have a constant diameter from the bottom 210a to the opening 214a. In any case, the shape of the first liner 210 is not limited to the example in FIG. 4.

[0060] A first combustion chamber 215 is formed inside the large diameter portion 212, the reduced diameter portion 213, and the small diameter portion 214. That is, the first combustion chamber 215 is formed inside the first liner 210. Furthermore, a primary region 215a, which is indicated by a dashed-line enclosure in the figure, is formed inside the large diameter portion 212. A flow path forming member 120 is provided radially outward from the first liner 210. In the second modified example, an inner flow path 122 and an outer flow path 124 are also provided radially outward from the first liner 210. In the second modified example, a partition wall 130 is also provided between the side wall portion 210b of the first liner 210 and the separation wall portion 120a. Therefore, the inner flow path 122 facing the side wall portion 210b is divided into a first inner flow path 122a and a second inner flow path 122b by the partition wall 130.

[0061] The second liner 220 is composed of a substantially cylindrical member with openings 220a, 220b formed at both ends. The second liner 220 includes a second large diameter portion 222, a second reduced diameter portion 223, and a second small diameter portion 224. The second large diameter portion 222 is located closer to the burner 40 than the second reduced diameter portion 223 and the second small diameter portion 224. The second small diameter portion 224 is located farther away from the burner 40 in the central axial direction than the second large diameter portion 222 and the second reduced diameter portion 223. The inner diameter of the second small diameter portion 224 is smaller than the inner diameter of the second large diameter portion 222. The second reduced diameter portion 223 connects the second large diameter portion 222 and the second small diameter portion 224. The diameter of the second reduced diameter portion 223 decreases from the second large diameter portion 222 toward the second small diameter portion 224. That is, the second reduced diameter portion 223 has a tapered shape. However, the second reduced diameter portion 223 may extend in the radial direction. An opening 220a is formed in the end of the second large diameter portion 222 on the burner 40 side. Furthermore, an opening 220b connected to the exhaust flow path 12 is formed in the end of the second small diameter portion 224 located opposite the second reduced diameter portion 223.

[0062] In the second modified example, the inner diameter of the second large diameter portion 222 of the second liner 220 is substantially constant regardless of the position in the central axis direction. However, the inner diameter of the second large diameter portion 222 may vary depending on the position in the central axis direction. For example, the second large diameter portion 222 may have a tapered shape in which the diameter increases or decreases as the distance from the burner 40 increases. Similarly, the inner diameter of the second small diameter portion 224 may vary depending on the position in the central axis direction. For example, the second small diameter portion 224 may have a tapered shape in which the diameter increases or decreases as the distance from the burner 40 increases.

[0063] Furthermore, the entire second liner 220 may have a tapered shape in which the diameter gradually decreases as it moves away from the burner 40. Furthermore, the diameter of the second liner 220 may be constant from the opening 220a to the opening 220b. In any case, the shape of the second liner 220 is not limited to the example in FIG. 4.

[0064] A second combustion chamber 225 is formed inside the second large diameter portion 222, the second reduced diameter portion 223, and the second small diameter portion 224. That is, the second combustion chamber 225 is formed inside the second liner 220. A secondary region 225a, which is shown enclosed by a dashed line in the drawing, is formed inside the second large diameter portion 222. A second through hole 117 is formed in the second large diameter portion 222, and a guide member 118 is provided in the secondary region 225a.

[0065] The small diameter portion 214 of the first liner 210 is inserted into the opening 220a of the second liner 220. Therefore, the inner diameter of the second large diameter portion 222 of the second liner 220 is larger than the outer diameter of the small diameter portion 214 of the first liner 210. The end of the small diameter portion 214 of the first liner 210, where the opening 214a is formed, is located within the second liner 220. The outer peripheral surface of the small diameter portion 214 of the first liner 210 faces the inner peripheral surface of the second large diameter portion 222 of the second liner 220 in the radial direction. At this time, the outer peripheral surface of the small diameter portion 214 and the inner peripheral surface of the second large diameter portion 222 are spaced apart. In other words, the second liner 220 overlaps the first liner 210.

[0066] The first combustion chamber 215 in the first liner 210 and the second combustion chamber 225 in the second liner 220 communicate with each other through the opening 214a. In other words, the first liner 210 and the second liner 220 form one liner, and the first combustion chamber 215 and the second combustion chamber 225 form one combustion chamber.

[0067] Furthermore, an annular flow passage 230 is formed between the inner circumferential surface of the second large diameter portion 222 of the second liner 220 and the outer circumferential surface of the small diameter portion 214 of the first liner 210. The tip of the second large diameter portion 222, i.e., the opening 220a, is separated from the reduced diameter portion 213 of the first liner 210 in the central axial direction. This allows the flow passage 230 to communicate with the second inner flow passage 122b. In other words, the flow passage 230 functions as a second air inlet that introduces dilution air from the second inner flow passage 122b to the second combustion chamber 225. Therefore, the second modified example also achieves the same functions and effects as the above embodiment.

[0068] Furthermore, in the second modified example, the first liner 210 and the second liner 220 are configured as separate bodies, but the first liner 210 and the second liner 220 may be integrally molded. Alternatively, the first liner 210 and the second liner 220 may be configured as separate bodies and fixed by welding or with fixing members such as bolts. In this case, the first liner 210 and the second liner 220 can be easily attached to and detached from the casing 101. However, the first liner 210 and the second liner 220 may also be configured as separate bodies and attached to the casing 101 separately. In this case, thermal deformation of the first liner 210 and the second liner 220 is absorbed by the flow path 230, thereby improving durability.

[0069] The first modified example may be applied to the second modified example. That is, in FIG. 4, the second end 120c of the flow path forming member 120 may be located closer to the opening 220b than the second through hole 117. In the second modified example, the first liner 210 and the second liner 220 are configured as separate bodies. However, the first liner 210 and the second liner 220 may be integrally molded.

[0070] 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.

[0071] In the above, an example has been described in which the rotational power generated by the turbocharger 10 in the gas turbine systems 1, 1A, and 1B is used as energy to drive the generator 20. However, in the gas turbine system 1, the rotational power generated by the turbocharger 10 may be used for other purposes. Examples of other uses include driving a moving body such as a ship.

[0072] In the above, an example has been described in which the combustion device 30 is used in the gas turbine systems 1, 1A, and 1B. However, the combustion device 30 may be used in devices other than the gas turbine systems 1, 1A, and 1B. Examples of devices other than the gas turbine systems 1, 1A, and 1B include industrial furnaces that change the shape or properties of materials by combustion in a combustor.

[0073] 1, 1A, 1B: Gas turbine system 30: Combustion device 40: Burner 101b: Outer wall portion 110: Liner 110b, 210b: Side wall portion 111: Air introduction portion 115: Combustion chamber 115a, 215a: Primary region 115b, 225a: Secondary region 116: Through hole 120a: Partition wall portion 122: Inner flow path 124: Outer flow path 126: Communication hole 130: Partition wall 210: First liner 215: First combustion chamber 220: Second liner 225: Second combustion chamber 230: Flow path

Claims

1. A combustion device comprising: a liner having a combustion chamber formed inside a side wall portion; a burner provided in the liner for injecting fuel into the combustion chamber; an air inlet portion provided at or near the burner for introducing air into the combustion chamber; a partition wall portion provided radially outward of the liner than the side wall portion and forming an inner flow passage communicating with the air inlet portion between the side wall portion; an outer wall portion provided radially outward of the liner than the partition wall portion and forming an outer flow passage between the partition wall portion; a plurality of communication holes formed in the partition wall portion at intervals from each other in the central axial direction of the liner, communicating between the inner flow passage and the outer flow passage; and a partition wall provided in the inner flow passage and dividing the inner flow passage in the central axial direction of the liner.

2. The combustion device according to claim 1, further comprising: a second air inlet portion formed in the side wall portion at a position farther away from the burner in the central axis direction than the partition wall, and connecting the inner flow path with the combustion chamber.

3. A combustion device as described in claim 2, wherein the combustion chamber includes a primary region located closer to the burner than the second air inlet portion, and a secondary region located farther away from the burner in the central axial direction than the second air inlet portion, and the partition wall is located radially outside the primary region.

4. A gas turbine system comprising the combustion device according to claim 1.

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