Combustion device and gas turbine system

Abstract

To improve durability of a liner.SOLUTION: A combustion device 30 comprises: a first liner 110 that has a large diameter part 112, and a small diameter part 114 that is smaller in diameter than the large diameter part and has an opening 114a formed at its end part, and in which a first combustion chamber 115 is formed; and a second liner 120 through which the small diameter part is inserted, and that has an opposing part 122 that faces an outer peripheral surface of the small diameter part at a distance, and inside which a second combustion chamber 125 communicating with the first combustion chamber is formed.SELECTED DRAWING: Figure 1

Description

Technical Field

[0001] The present disclosure relates to a combustion device and a gas turbine system.

Background Art

[0002] A gas turbine system that obtains power by burning fuel in a combustor is used. For example, Patent Document 1 discloses a gas turbine system in which a low-calorie fuel is used instead of a fossil fuel. According to this gas turbine system, a primary combustion region where rich combustion is performed and a secondary combustion region where lean combustion is performed are provided in a liner.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] In the above gas turbine system, the entire liner becomes high temperature due to combustion. Therefore, development of a technique for improving the durability of the liner is desired.

[0005] An object of the present disclosure is to provide a combustion device and a gas turbine system capable of improving the durability of a liner.

Means for Solving the Problems

[0006] In order to solve the above problems, the combustion device of the present disclosure has a large-diameter portion and a small-diameter portion that is smaller in diameter than the large-diameter portion and has an opening formed at an end portion, and a first liner in which a first combustion chamber is formed inside, The small-diameter portion is inserted therethrough, and it has an opposing portion that is spaced apart and opposed to the outer peripheral surface of the small-diameter portion, and a second liner in which a second combustion chamber communicating with the first combustion chamber is formed inside; It includes.

[0007] The opposing portion may be smaller in diameter than the large-diameter portion.

[0008] One or a plurality of through-holes provided in the second liner and penetrating the inside and outside of the second liner; It may further include.

[0009] The combustion device is One or a plurality of holes provided in the opposing portion on the large-diameter portion side of the through-hole and penetrating the inside and outside of the second liner; It may further include.

[0010] The combustion device is A protruding portion that protrudes from the inner peripheral surface of the second liner toward the center side of the second liner and surrounds the through-hole; It may further include.

[0011] The combustion device is A relief portion provided in the small-diameter portion and through which at least a part of the protruding portion is inserted; It may further include.

[0012] The combustion device is A reduced-diameter portion provided in the first liner, connecting the large-diameter portion and the small-diameter portion, and having a diameter that decreases as it goes from the large-diameter portion to the small-diameter portion; It may further include.

[0013] The combustion device is A spacer provided between the small-diameter portion and the opposing portion; It may further include.

[0014] The combustion device is The first liner and the second liner are each configured as separate bodies, A casing in which the first liner and the second liner are accommodated, and to which the first liner and the second liner are respectively attached, may be further provided.

[0015] To solve the above problems, the gas turbine system of the present disclosure includes the above combustion device.

Advantages of the Invention

[0016] According to the present disclosure, the durability of the liner can be improved.

Brief Description of the Drawings

[0017]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

Figure 7

Figure 8

Figure 9

Modes for Carrying Out the Invention

[0018] Embodiments of the present disclosure will be described with reference to the accompanying drawings below. The dimensions, materials, and other specific numerical values shown in the embodiments are merely examples for ease of understanding and do not limit the present disclosure unless otherwise specified. In the present specification and drawings, elements having substantially the same functions and configurations are denoted by the same reference numerals to avoid redundant description, and elements not directly related to the present disclosure are not shown.

[0019] 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 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.

[0020] The supercharger 10 has a compressor 10a and a turbine 10b. The impeller of the compressor 10a and the impeller of the turbine 10b rotate integrally. The impeller of the compressor 10a and the impeller of the turbine 10b are connected by a shaft.

[0021] The compressor 10a is provided in the intake passage 11. Air supplied to the combustor 100 flows through the intake passage 11. An intake port (not shown) through which air is taken in from the outside is provided at the upstream end of the intake passage 11. The air taken in from the intake port passes through the compressor 10a and is sent to the combustor 100. The compressor 10a compresses the air and discharges it to the combustor 100.

[0022] The turbine 10b is provided in the exhaust passage 12 connected to the combustor 100. Combustion gas discharged from the combustor 100 flows through the exhaust passage 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 passage 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 the impeller of the turbine 10b is rotated by the combustion gas.

[0023] The generator 20 is connected to the supercharger 10. The generator 20 generates electricity using the rotational power generated by the supercharger 10.

[0024] The burner 40 of the combustion device 30 injects ammonia as fuel into the interior of the combustor 100. The burner 40 has a substantially cylindrical shape. The burner 40 is attached to a casing 101 of the combustor 100 described later. The tip of the burner 40 is located inside the casing 101, and the rear end of the burner 40 is located outside the casing 101.

[0025] An injection valve (not shown) is provided at the tip 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 rate control valve 60 is provided in the flow path connecting the ammonia tank 50 and the burner 40. The ammonia stored in the ammonia tank 50 is supplied to the burner 40. The flow rate control valve 60 controls the flow rate of the ammonia supplied from the ammonia tank 50 to the burner 40. In addition, various devices (for example, shut-off valves, check valves, various sensors, etc.) whose illustration is omitted in FIG. 1 may be provided in the flow path connecting the ammonia tank 50 and the burner 40.

[0026] The combustor 100 includes a casing 101, a first liner 110, and a second liner 120. The casing 101 is configured in a substantially bottomed cylindrical shape having a bottom surface 101a and a peripheral wall portion 101b. The burner 40 is inserted through the bottom surface 101a of the casing 101. The burner 40 is located substantially at the center of the bottom surface 101a. In other words, the burner 40 is provided on the central axis of the casing 101.

[0027] Inside the casing 101, a first liner 110 and a second liner 120 are accommodated. The first liner 110 and the second liner 120 have a substantially cylindrical shape. The first liner 110 and the second liner 120 are separate from each other, that is, they are constituted by different members. Inside the casing 101, the first liner 110 is provided closer to the burner 40 side than the second liner 120. The outer diameters of the first liner 110 and the second liner 120 are smaller than the inner diameter of the casing 101. Thereby, an air flow path 102 is formed between the first liner 110 and the second liner 120 and the casing 101. The air flow path 102 is an annular flow path formed along the peripheral wall portion 101b of the casing 101.

[0028] The first liner 110 is attached to the casing 101 by an attachment member 111. Also, the second liner 120 is attached to the casing 101 by an attachment member 121. That is, the first liner 110 and the second liner 120 are each separately attached to the casing 101.

[0029] Here, the attachment members 111 and 121 are provided on the peripheral wall portion 101b of the casing 101. That is, the first liner 110 and the second liner 120 are attached to the peripheral wall portion 101b. However, the attachment members 111 and 121 may be provided, for example, on the bottom surface 101a of the casing 101. Also, for example, the attachment members 111 and 121 may be provided on other members provided in the air flow path 102.

[0030] Note that the attachment members 111 and 121 are constituted by, for example, a fixing fitting locked to the first liner 110 and the second liner 120 and bolts. In this case, the fixing fitting is fixed to the casing 101 by bolts. However, the configuration of the attachment members 111 and 121 and the attachment method of the first liner 110 and the second liner 120 are not limited to this. The first liner 110 and the second liner 120 may be attached to the casing 101, for example, by welding or press-fitting.

[0031] Further, for example, the second liner 120 may be attached to the first liner 110. In this case, the second liner 120 is attached to the casing 101 via the first liner 110. Alternatively, the first liner 110 may be attached to the second liner 120. In this case, the first liner 110 is attached to the casing 101 via the second liner 120.

[0032] The central axes of the first liner 110 and the second liner 120 substantially coincide with the central axis of the casing 101. Accordingly, the central axes of the first liner 110 and the second liner 120 coincide with each other. Further, the central axes of the first liner 110 and the second liner 120 coincide with the central axis of the burner 40. Hereinafter, the central axes of the first liner 110 and the second liner 120 may be simply referred to as "center". Also, the direction orthogonal to the central axis, that is, the radial direction of the first liner 110 and the second liner 120 is simply referred to as "radial direction".

[0033] The first liner 110 includes a burner insertion hole 110a on one end side in the central axis direction. The tip of the burner 40 is inserted into the burner insertion hole 110a. A gap communicating with the air flow path 102 is formed between the inner peripheral surface of the burner insertion hole 110a and the burner 40. Further, the first liner 110 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.

[0034] The small diameter portion 114 is located closer to the second liner 120 than the large diameter portion 112. The inner diameter of the small diameter portion 114 is smaller than the inner diameter of the large diameter portion 112. In other words, the small diameter portion 114 has a smaller diameter than the large diameter portion 112. An opening 114a is formed at an end of the small diameter portion 114 located on the side opposite to the reduced diameter portion 113. The reduced diameter portion 113 connects the large diameter portion 112 and the small diameter portion 114. The reduced diameter portion 113 has a smaller diameter as it extends from the large diameter portion 112 toward the small diameter portion 114. That is, the reduced diameter portion 113 has a tapered shape. However, the reduced diameter portion 113 may extend in the radial direction.

[0035] Also, 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 it is separated 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 it is separated from the burner 40. Furthermore, the entire first liner 110 may have a tapered shape in which the diameter gradually decreases as it is separated from the burner 40 side. In this case, a certain range on the burner 40 side of the first liner 110 becomes the large-diameter portion 112, and a certain range on the side separated from the burner 40 becomes the small-diameter portion 114. In any case, the shape of the first liner 110 is not limited to the example in FIG. 1, and it may include the large-diameter portion 112 and the small-diameter portion 114 provided at a position separated from the burner 40 with respect to the large-diameter portion 112 and having a smaller diameter than the large-diameter portion 112.

[0036] A first combustion chamber 115 is formed inside the large-diameter portion 112, the reduced-diameter portion 113, and the small-diameter portion 114. That is, the first combustion chamber 115 is formed inside the first liner 110. Here, the large-diameter portion 112 is longer in the axial direction than the reduced-diameter portion 113 and the small-diameter portion 114. The inside of the large-diameter portion 112 is the main part for burning fuel in the first combustion chamber 115. Here, the inside of the large-diameter portion 112 shown by the broken line in the figure in the first combustion chamber 115 is called the primary region 115a.

[0037] The second liner 120 is composed of a substantially cylindrical member having openings 120a and 120b formed at both ends. Here, the second liner 120 has a substantially constant diameter from one end where the opening 120a is formed to the other end where the opening 120b is formed. However, the second liner 120 may be configured in a tapered shape in which the diameter gradually increases or decreases from one end to the other end.

[0038] FIG. 2 is an enlarged view of the connection portion between the first liner 110 and the second liner 120 of the present disclosure. The small-diameter portion 114 of the first liner 110 is inserted into the opening 120a of the second liner 120. Therefore, the inner diameter of the second liner 120 is larger than the outer diameter of the small-diameter portion 114. Among the small-diameter portion 114, the end where the opening 114a is formed is located inside the second liner 120. Here, in the second liner 120, the portion facing the outer peripheral surface of the small-diameter portion 114 is defined as the facing portion 122. The facing portion 122 faces the outer peripheral surface of the small-diameter portion 114 at a distance. In other words, the second liner 120 overlaps the first liner 110 at the facing portion 122. Thereby, an annular flow path 130 is formed between the inner peripheral surface of the facing portion 122 and the outer peripheral surface of the small-diameter portion 114.

[0039] Note that the facing portion 122 of the second liner 120 is smaller in diameter than the large-diameter portion 112 of the first liner 110. Therefore, the flow path width of the flow path 130 is small. However, the diameter of the facing portion 122 may be equal to or larger than the diameter of the large-diameter portion 112. Also, the tip of the facing portion 122, that is, the opening 120a, is axially spaced from the reduced-diameter portion 113 of the first liner 110. In other words, the facing portion 122 is non-contact with the reduced-diameter portion 113. Thereby, the flow path 130 communicates with the air flow path 102.

[0040] Further, the second liner 120 is provided with a through hole 123 that penetrates the inside and outside of the second liner 120. The through hole 123 penetrates the second liner 120 in the radial direction. Here, a plurality of through holes 123 are provided in the second liner 120. The plurality of through holes 123 are, for example, equally spaced in the axial direction of the second liner 120 and are arranged at intervals in the circumferential direction. However, only one through hole 123 may be provided in the second liner 120. Also, when a plurality of through holes 123 are provided, the plurality of through holes 123 may have different positions in the axial direction.

[0041] The through hole 123 is provided at a position axially spaced from the opposing portion 122. In other words, the through hole 123 is provided at a position not radially opposed to the small diameter portion 114. Here, the through hole 123 is located on the opening 120b side, that is, the side separated from the first liner 110 and the burner 40, with respect to the central position of the second liner 120 in the central axis direction.

[0042] And a second combustion chamber 125 is formed inside the second liner 120. Here, among the second combustion chamber 125, the downstream side of the through hole 123, that is, the opening 120b side with respect to the through hole 123 is called the secondary region 125a. The secondary region 125a is a main part for burning fuel in the second combustion chamber 125. The second combustion chamber 125 communicates with the first combustion chamber 115 through the opening 114a of the small diameter portion 114. Also, the through hole 123 opens into the second combustion chamber 125. Thereby, the second combustion chamber 125 communicates with the air flow path 102 through the through hole 123.

[0043] Next, the operation of the combustion device 30 will be described with reference to FIGS. 1 and 2. As shown in FIG. 1, an intake air flow path 11 is connected to the air flow path 102, and the air compressed by the compressor 10a is supplied to the air flow path 102. The air sent to the air flow path 102 passes through the air flow path 102 as indicated by the dashed-dotted arrow in the figure, and is then injected into the first combustion chamber 115 from the burner insertion hole 110a of the first liner 110. Specifically, the air sent to the air flow path 102 passes between the inner peripheral surface of the burner insertion hole 110a and the outer peripheral surface of the burner 40 and is injected into the first combustion chamber 115, particularly the primary region 115a.

[0044] Also, ammonia whose flow rate is adjusted by the flow control valve 60 is supplied to the burner 40 as fuel. Fuel is injected from the injection valve provided at the tip of the burner 40 into the first combustion chamber 115. At this time, the fuel may be injected axially from the burner 40. Alternatively, the fuel may be injected in a direction that spreads radially as it separates from the burner 40.

[0045] Note that the injection valve provided in the burner 40 is a pressure injection valve or an air flow injection valve. The pressure injection valve is a type of valve that atomizes a liquid by utilizing the pressure difference inside and outside the pressure injection valve. The air flow injection valve is a type of valve that generates a film of the liquid to be injected and atomizes the liquid by utilizing the shearing force between the film and the air. However, the configuration of the injection valve is not particularly limited. Here, liquid ammonia is used as the fuel, but gaseous ammonia may also be used. In addition to ammonia, other fuels such as natural gas or hydrogen may be used as the fuel supplied to the first combustion chamber 115.

[0046] The fuel injected from the burner 40 and the air injected from the burner insertion hole 110a are mixed to generate a mixture. That is, the mixture is supplied to the first combustion chamber 115 and the second combustion chamber 125. The combustor 100 is provided with an ignition device (not shown), and combustion occurs in the first combustion chamber 115 and the second combustion chamber 125 by ignition by the ignition device. The combustion gas generated by combustion is discharged into the exhaust passage 12 connected to the second combustion chamber 125.

[0047] Here, in the primary region 115a, the flow rates of air and fuel are adjusted so that the equivalence ratio of the mixture becomes fuel-rich at about 1.0 to 1.5. Therefore, the combustion in the primary region 115a is rich combustion. On the other hand, through holes 123 are formed in the second liner 120, and air is supplied from the air passage 102 to the second combustion chamber 125 through the through holes 123. Hereinafter, the air supplied from the through holes 123 to the second combustion chamber 125 is referred to as dilution air.

[0048] In the secondary region 125a, dilution air is mixed into the mixture. At this time, the dimensions of the through holes 123 are set so that the combustion in the secondary region 125a becomes lean combustion. Thus, in the present embodiment, rich combustion is performed in the primary region 115a formed inside the first liner 110, and lean combustion is performed in the secondary region 125a formed inside the second liner 120.

[0049] Here, in order to reduce emissions such as NOx generated from ammonia, unburned NH 3 , N 2 O, etc., it is desirable to ensure a long residence time of the combustion gas in the primary region 115a. On the other hand, in order to reduce thermal NOx, it is desirable to shorten the residence time of the combustion gas in the secondary region 125a.

[0050] In this embodiment, the volume of the primary region 115a is larger than that of the secondary region 125a. For example, let the representative diameter of the primary region 115a be D1 and the representative diameter of the secondary region 125a be D2. In this case, the dimensional relationship between D1 and D2 is D1 > D2, for example, 1.1 ≦ D1 / D2 ≦ 1.5. Also, the primary region 115a has a sufficient length in the central axis direction compared to the secondary region 125a. Thereby, the residence time of the combustion gas in the primary region 115a becomes long, and the residence time of the combustion gas in the secondary region 125a becomes short.

[0051] Note that due to the swirling flow formed by the burner 40, the pressure near the center of the primary region 115a decreases, and a circulating flow may be formed. In this case, there is a possibility that the dilution air flowing into the second combustion chamber 125 from the through-hole 123 may flow backward into the primary region 115a. Also, there is a possibility that the dilution air flowing into the second combustion chamber 125 from the through-hole 123 may collide near the center of the second combustion chamber 125, and a part of it may flow backward into the primary region 115a. When the dilution air flows backward into the primary region 115a, the equivalence ratio in the primary region 115a decreases, and emissions increase.

[0052] In this embodiment, the through-hole 123 is provided at a position separated from the burner 40 and the primary region 115a rather than the central position in the axial center direction of the second liner 120. Further, since the representative diameter D2 of the secondary region 125a is smaller than the representative diameter D1 of the primary region 115a, the flow velocity in the secondary region 125a is high. Furthermore, as shown in FIG. 2, the inclination angle θ of the reduced-diameter portion 113 with respect to the central axis direction is, for example, 5 degrees or more and 45 degrees or less. Therefore, the reduced-diameter portion 113 increases the flow velocity of the combustion gas from the primary region 115a toward the secondary region 125a. As a result, the dilution air is less likely to flow backward into the primary region 115a.

[0053] In addition, the dilution air flowing into the second combustion chamber 125 from the through-hole 123 is jetted toward the high-velocity combustion gas. Therefore, the mixing of the dilution air is promoted, and the generation of emissions in the secondary region 125a is suppressed.

[0054] Here, inside the second liner 120, since the flow velocity of the combustion gas is high, the second liner 120 tends to become hot. In this embodiment, a flow path 130 is formed between the small-diameter portion 114 of the first liner 110 and the opposing portion 122 of the second liner 120. As shown by the solid-line arrow in FIG. 2, air is guided from the air flow path 102 to the flow path 130. The first liner 110 and the second liner 120 are cooled by the air flowing through the flow path 130. The durability of the first liner 110 and the second liner 120 is improved by the cooling effect brought about by the flow path 130.

[0055] In addition, the first liner 110 and the second liner 120 may be deformed and expanded by heat. At this time, the primary region 115a where rich combustion is performed becomes hotter than the secondary region 125a where lean combustion is performed. That is, a temperature difference occurs between the vicinity of the primary region 115a and the vicinity of the secondary region 125a.

[0056] Suppose that the first liner 110 and the second liner 120 are integrally formed and only one liner is provided. In this case, a primary region 115a and a secondary region 125a are formed within the single liner. As a result, two sites with significantly different deformation amounts and thermal expansion rates will exist in the single liner, increasing the load on the liner.

[0057] In the present embodiment, the first liner 110 and the second liner 120 are configured separately. And the first liner 110 and the second liner 120 are respectively attached to the casing 101 separately. Moreover, the first liner 110 and the second liner 120 are maintained in a non-contact state. Therefore, the deformation and expansion of the first liner 110 and the second liner 120 are absorbed by the flow path 130. Thus, in addition to the above cooling function, the flow path 130 also serves to absorb the deformation occurring in the first liner 110 and the second liner 120. As described above, according to the combustion device 30 and the gas turbine system 1 including the combustion device 30, durability can be improved.

[0058] Here, it is assumed that the first liner 110 and the second liner 120 are configured separately and are respectively attached to the casing 101 separately. However, the first liner 110 and the second liner 120 may be fixed to each other, for example, by welding or the like, to form a single integrated liner. In this case, the first liner 110 and the second liner 120 may be held within the casing 101 by, for example, a single mounting member 111. Alternatively, the integrated first liner 110 and second liner 120 may be attached to the bottom surface of the bottom surface 101a of the casing 101 in the central axis direction.

[0059] Various peripheral members such as other components and devices are provided around the casing 101. Therefore, the attachment and detachment operations of the first liner 110 and the second liner 120 to the casing 101 may be complicated. By integrating the first liner 110 and the second liner 120, the number of attachment locations is reduced, and the attachment operation is simplified. Also, by reducing the number of attachment locations, the adjustment with the peripheral members becomes easier, and the design work is simplified.

[0060] In addition, when the first liner 110 and the second liner 120 are integrated, the part for fixing them to each other is not particularly limited. However, it is desirable that at least a part of the small-diameter portion 114 is integrated with the first liner 110 and the second liner 120 so that it can move slightly with respect to the opposing portion 122 when thermally deformed.

[0061] Hereinafter, each modification of the above-described embodiment will be described. In the following, in each modification, the configuration different from the above-described embodiment will be described, and the same components as those in the above-described embodiment will be denoted by the same reference numerals, and the detailed description thereof will be omitted. Therefore, each modification described below has the same configuration as the above-described embodiment in parts where there is no particular notice.

[0062] FIG. 3 is an enlarged view of the connection portion between the first liner 110 and the second liner 120 according to the first modification. In the first modification, a plurality of hole portions 122a are formed in the second liner 120. The hole portions 122a are formed in the opposing portion 122 on the large-diameter portion 112 side rather than the through hole 123. The hole portions 122a penetrate the inside and outside of the opposing portion 122 in the radial direction. The hole portions 122a are smaller than the through hole 123. Here, a plurality of hole portions 122a having different positions in the central axis direction of the second liner 120 are provided. Also, a plurality of hole portions 122a having different positions in the circumferential direction of the second liner 120 are provided.

[0063] Air flows from the air flow path 102 into the flow path 130 through the hole portion 122a. The air that has flowed into the flow path 130 from the hole portion 122a collides with the small-diameter portion 114 of the first liner 110. As a result, the amount of air flowing through the flow path 130 increases, and the cooling function is improved.

[0064] In addition, in the first modification, a plurality of hole portions 122a smaller than the through hole 123 are provided, but the hole portion 122a may be configured to be larger than the through hole 123. Further, the plurality of hole portions 122a may have different sizes from each other. Further, the plurality of hole portions 122a may penetrate the inside and outside of the second liner 120 in a direction inclined with respect to the radial direction. In this case, the opening of the hole portion 122a located on the inner peripheral surface side of the second liner 120 may be located closer to the opening 120b side of the second liner 120 than the opening of the hole portion 122a located on the outer peripheral surface side of the second liner 120.

[0065] Further, the hole portion 122a is not limited to a plurality, and only one hole portion 122a may be provided. For example, the hole portion 122a may be configured by a long hole extending in the circumferential direction of the second liner 120. Further, the hole portion 122a may be configured by a long hole extending in the axial center direction of the second liner 120. A plurality of hole portions 122a configured by these long holes may be formed at intervals in the circumferential direction or the axial center direction. Furthermore, the hole portion 122a may have a shape that spirally extends in the circumferential direction of the second liner 120. In any case, as long as one or a plurality of hole portions 122a are provided in the opposing portion 122 on the large-diameter portion 112 side with respect to the through hole 123 and penetrate the inside and outside of the second liner 120.

[0066] FIG. 4 is an enlarged view of the connection portion between the first liner 110 and the second liner 120 according to the second modification. FIG. 5 is a cross-sectional view taken along line V-V of FIG. 4. In the second modification, as shown by cross-hatching in FIGS. 4 and 5, a plurality of spacers 132 are provided between the small-diameter portion 114 of the first liner 110 and the opposing portion 122 of the second liner 120. That is, in the second modification, a plurality of spacers 132 are provided in the flow path 130. Here, four spacers 132 are arranged at equal intervals in the circumferential direction of the second liner 120. However, the number of spacers 132 is not limited.

[0067] The spacer 132 contacts both the outer peripheral surface of the small-diameter portion 114 and the inner peripheral surface of the opposing portion 122. However, the spacer 132 may contact only one of the small-diameter portion 114 and the opposing portion 122. In this case, a gap is formed between the spacer 132 and the opposing portion 122, or between the spacer 132 and the small-diameter portion 114. Even when the first liner 110 or the second liner 120 is deformed by the spacer 132, the flow path width of the flow path 130 is ensured. Note that the spacer 132 may be integrally formed with the first liner 110 or the second liner 120, or may be constituted by a separate member from the first liner 110 and the second liner 120. Further, the spacer 132 may be attached to the first liner 110 or the second liner 120 by any method of fixing such as press-fitting, welding, or a fixing member such as a bolt.

[0068] FIG. 6 is an enlarged view of the connection portion between the first liner 110 and the second liner 120 according to the third modification. FIG. 7 is a view taken along the arrow VII in FIG. 6. In the third modification, a plurality of protrusions 120c protruding from the inner peripheral surface of the second liner 120 toward the center side of the second liner 120 are provided. The plurality of protrusions 120c are provided at intervals in the circumferential direction of the second liner 120. A through hole 123 penetrating the second liner 120 in the radial direction is provided in the protrusion 120c. Therefore, it can be said that the protrusion 120c is a wall portion surrounding the through hole 123. Here, the protrusion 120c is integrally formed with the second liner 120. However, the protrusion 120c may be formed of a separate member from the second liner 120 and attached to the second liner 120.

[0069] Also, in the third modification, the protrusion 120c is provided on the opposing portion 122. That is, the protrusion 120c is provided in a range radially opposed to the small-diameter portion 114 of the first liner 110. However, the protrusion 120c may be provided in a region not opposed to the small-diameter portion 114, that is, in a range separated from the burner 40 and the primary region 115a in the central axis direction more than the opening 114a of the small-diameter portion 114.

[0070] Furthermore, in the third modification, the protrusion 120c extends in the radial direction. However, the opening of the through hole 123 located on the outer peripheral surface side of the second liner 120 may be inclined in a direction located closer to the burner 40 and the primary region 115a than the opening of the through hole 123 located inside the second liner 120. In this case, the dilution air flowing into the second combustion chamber 125 from the through hole 123 easily flows into the secondary region 125a, and the effect of suppressing backflow is improved.

[0071] In addition, a relief portion 114b through which the protruding portion 120c is inserted is provided in the small-diameter portion 114. The number of relief portions 114b is the same as the number of protruding portions 120c. The relief portion 114b is a groove formed at the end of the small-diameter portion 114 on the opening 114a side. However, the relief portion 114b may be a hole through which the protruding portion 120c is inserted. The tip of the protruding portion 120c in the protruding direction is substantially flush with the inner peripheral surface of the small-diameter portion 114. The relief portion 114b and the protruding portion 120c maintain a non-contact dimensional relationship. However, a part of the relief portion 114b and the protruding portion 120c may be in contact with each other.

[0072] Here, the tip of the protruding portion 120c in the protruding direction is located closer to the center than the outer peripheral surface of the small-diameter portion 114. Therefore, there is no interference between the air flowing through the flow path 130 and the dilution air flowing from the through hole 123 into the interior of the second liner 120. As a result, the air flow in the flow path 130 is less likely to be disturbed, and the first liner 110 and the second liner 120 can be appropriately cooled. In addition, the dilution air is appropriately guided from the through hole 123 to the secondary region 125a, and the backflow to the primary region 115a side is suppressed.

[0073] Note that the tip of the protruding portion 120c in the protruding direction may be located closer to the center than the inner peripheral surface of the small-diameter portion 114. In this case, the dilution air is more likely to be guided by the center side of the secondary region 125a. Further, the tip of the protruding portion 120c in the protruding direction may be located radially outside the inner peripheral surface of the small-diameter portion 114. In this case, the possibility of inhibiting the flow of combustion gas from the primary region 115a to the secondary region 125a is reduced.

[0074] Note that at least a part of the protruding portion 120c may be inserted into the relief portion 114b. However, the entire protruding portion 120c may be provided at a position that is not radially opposed to the relief portion 114b. That is, the protruding portion 120c may be provided at a position displaced from the relief portion 114b in the central axis direction and not inserted into the relief portion 114b. Even in this case, since the relief portion 114b is provided in advance, even if the small-diameter portion 114 is thermally deformed in the central axis direction, interference between the protruding portion 120c and the small-diameter portion 114 can be avoided. However, when the entire protruding portion 120c is provided at a position that is not radially opposed to the small-diameter portion 114, the relief portion 114b is not essential.

[0075] FIG. 8 is a schematic diagram showing a combustor 100A according to a fourth modification. In the fourth modification, instead of the second liner 120 described above, a second liner 120A is provided. The second liner 120A includes a second small-diameter portion 142, a diameter-expanded portion 143, and a second large-diameter portion 144. The second small-diameter portion 142 is located closer to the burner 40 side than the diameter-expanded portion 143 and the second large-diameter portion 144. The second small-diameter portion 142 has the same configuration as the second liner 120 described in the above embodiment. Therefore, an opening 120a, an opposing portion 122, and a through-hole 123 are provided in the second small-diameter portion 142. Further, the small-diameter portion 114 of the first liner 110 is inserted into the second small-diameter portion 142.

[0076] The second large-diameter portion 144 is located farther from the first liner 110 in the central axis direction than the second small-diameter portion 142. The inner diameter of the second large-diameter portion 144 is larger than the inner diameter of the second small-diameter portion 142. In other words, the second large-diameter portion 144 has a larger diameter than the second small-diameter portion 142. An opening 120b described above is formed at an end portion of the second large-diameter portion 144 located on the side opposite to the diameter-expanded portion 143. The diameter-expanded portion 143 connects the second small-diameter portion 142 and the second large-diameter portion 144. The diameter of the diameter-expanded portion 143 increases as it goes from the second small-diameter portion 142 toward the second large-diameter portion 144. That is, the diameter-expanded portion 143 has a tapered shape. However, the diameter-expanded portion 143 may extend in the radial direction.

[0077] Inside the second small-diameter portion 142, the diameter-expanded portion 143, and the second large-diameter portion 144, a second combustion chamber 145 is formed. That is, the second combustion chamber 145 is formed inside the second liner 120A. According to the fourth modification, in the diameter-expanded portion 143, the mixing of dilution air and combustion gas is promoted, and emissions are further reduced.

[0078] FIG. 9 is a schematic diagram showing a combustor 100A according to a fifth modification. In the fifth modification, the positions of the second liner 120A and the through-hole 123 in the fourth modification are different, and other configurations are the same as those in the fourth modification. As shown in FIG. 9, in the fifth modification, a through-hole 123 is provided in the diameter-expanded portion 143. The central axis of the through-hole 123 provided in the diameter-expanded portion 143 is inclined in the radial direction so as to be more separated from the first combustion chamber 115 toward the inner side in the radial direction. Thereby, as indicated by the arrow of the dashed-dotted line in FIG. 9, dilution air flows into the second combustion chamber 145 in a direction away from the first combustion chamber 115. Therefore, according to the fifth modification, the backflow of dilution air into the first combustion chamber 115 is further suppressed.

[0079] In addition, in the fourth modification or the fifth modification, a second reduced portion with a reduced diameter may be provided at an end of the second large-diameter portion 144 on the side opposite to the diameter-expanded portion 143. Further, a cylindrical portion extending substantially parallel to the central axis direction may be further connected to the second reduced portion. Thereby, it becomes possible to increase the flow velocity of the combustion gas and guide it to the turbine 10b.

[0080] As described above, the embodiments of the present disclosure have been described with reference to the accompanying drawings. Needless to say, the present disclosure is not limited to such embodiments. It is obvious that those skilled in the art can conceive of various modification examples or correction examples within the scope described in the claims, and it is naturally understood that they also belong to the technical scope of the present disclosure.

[0081] In the above description, an example in which the rotational power generated by the supercharger 10 is used as energy for driving the generator 20 in the gas turbine system 1 has been described. However, in the gas turbine system 1, the rotational power generated by the supercharger 10 may be used for other purposes. Examples of other purposes include, for example, applications for driving a moving body such as a ship.

[0082] In the above description, an example in which the combustion device 30 is used in the gas turbine system 1 has been described. However, the combustion device 30 may be used in devices other than the gas turbine system 1. Examples of devices other than the gas turbine system 1 include, for example, industrial furnaces for changing the shape or properties of materials by combustion in a combustor.

[0083] In the example of FIG. 1 described above, the air sent from the compressor 10a to the combustor 100 passes between the outer peripheral surfaces of the first liner 110 and the second liner 120 and the inner peripheral surface of the casing 101 and is then sent to the first combustion chamber 115 and the second combustion chamber 125. However, the path of the air sent from the compressor 10a to the combustor 100 is not limited to the above example of the turn - flow type. For example, in the example of FIG. 1, air may be supplied to the air flow path 102 from the bottom surface 101a side or from the peripheral wall portion 101b side.

[0084] The above - described embodiments and various modifications can be combined with each other. Further, in the above - described embodiments and various modifications, it was assumed that two liners in which combustion chambers are formed inside are provided, but the number of liners may be three or more. In this case, a structure for cooling the liner may be provided for some or all of the liners. Examples of the structure for cooling the liner include, for example, film cooling, impingement cooling, convection cooling, effusion cooling, etc.

Explanation of Reference Numerals

[0085] 1 Gas turbine system 30 Combustion device 101 Casing 110 First liner 111 Mounting member 112 Large-diameter part 113 Reduced-diameter part 114 Small-diameter part 114a Opening 114b Relief part 115 First combustion chamber 120 Second liner 120c Protrusion 121 Mounting member 122 Opposing part 122a Hole part 123 Through-hole 125 Second combustion chamber 132 Spacer

Claims

1. A first liner having a large-diameter portion and a small-diameter portion that is smaller in diameter than the large-diameter portion and has an opening formed at an end, with a first combustion chamber formed inside; A second liner through which the small-diameter portion is inserted and having an opposing portion that is spaced apart and opposed to the outer peripheral surface of the small-diameter portion, with a second combustion chamber communicating with the first combustion chamber formed inside; A combustion device comprising the above.

2. The opposing portion is smaller in diameter than the large-diameter portion. The combustion device according to Claim 1.

3. One or more through-holes provided in the second liner and penetrating the inside and outside of the second liner; The combustion device according to Claim 1 or 2, further comprising the above.

4. One or more hole portions provided in the opposing portion on the large-diameter portion side of the through-hole and penetrating the inside and outside of the second liner; The combustion device according to Claim 3, further comprising the above.

5. A protruding portion protruding from the inner peripheral surface of the second liner toward the center side of the second liner and surrounding the through-hole; The combustion device according to Claim 3, further comprising the above.

6. A relief portion provided in the small-diameter portion and through which at least a part of the protruding portion is inserted; The combustion device according to Claim 5, further comprising the above.

7. A reduced-diameter portion provided in the first liner, connecting the large-diameter portion and the small-diameter portion, and having a diameter that decreases toward the small-diameter portion from the large-diameter portion; The combustion device according to Claim 1 or 2, further comprising the above.

8. A spacer provided between the small-diameter portion and the opposing portion; The combustion device according to Claim 1 or 2, further comprising the above.

9. The first liner and the second liner are each separately configured. A casing in which the first liner and the second liner are accommodated inside, and to which the first liner and the second liner are respectively attached; The combustion device according to Claim 1 or 2, further comprising the above.

10. Comprising the combustion device according to Claim 1. A gas turbine system.

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