Gas turbine combustor and gas turbine

Abstract

A gas turbine combustor according to at least one embodiment of the present disclosure comprises: a combustion cylinder; and a plurality of side portion fuel nozzles provided on a side portion of the combustion cylinder. The plurality of side portion fuel nozzles include: a plurality of first side portion fuel nozzles disposed on the outer side in a radial direction of a gas turbine rotor when the combustion cylinder is attached to a casing covering an outer periphery of the rotor; and a plurality of second side portion fuel nozzles disposed on the inner side in the radial direction of the rotor when the combustion cylinder is attached to the casing. The plurality of second side portion fuel nozzles are disposed on the downstream side of the combustion cylinder with respect to the plurality of first side portion fuel nozzles.

Description

Gas turbine combustor and gas turbine

[0001] This application claims priority to Japanese Patent Application No. 2024-114136, filed with the Japan Patent Office on July 17, 2024, the contents of which are incorporated herein by reference.

[0002] 2. Description of the Related Art There is known a gas turbine combustor in which fuel can be supplied into a combustion liner from a fuel nozzle provided on a side of the combustion liner of the gas turbine combustor (see, for example, Patent Document 1).

[0003] Japanese Patent Application Laid-Open No. 2015-210075

[0004] In such a gas turbine combustor, if the combustion gas generated by the combustion of fuel supplied from a fuel nozzle provided on the side of the combustion liner remains in the combustion liner for a long time, NO ｘ Furthermore, in such a gas turbine combustor, if the combustion gas generated by the combustion of the fuel supplied from the fuel nozzles arranged on the upstream side of the combustion liner and the combustion gas generated by the combustion of the fuel supplied from the fuel nozzles arranged on the side of the combustion liner are not mixed well, NOx may be generated. ｘ There is a risk that the amount of

[0005] In view of the above circumstances, at least one embodiment of the present disclosure provides a gas turbine combustor having a fuel nozzle provided on a side of a combustion liner, in which a NO ｘ The purpose is to reduce the amount of

[0006] (1) A gas turbine combustor according to at least one embodiment of the present disclosure comprises: a combustion liner; and a plurality of side fuel nozzles provided on a side of the combustion liner, wherein the plurality of side fuel nozzles include: a plurality of first side fuel nozzles disposed radially outward of a rotor of a gas turbine when the combustion liner is attached to a casing that covers an outer periphery of the rotor; and a plurality of second side fuel nozzles disposed radially inward of the rotor when the combustion liner is attached to the casing, and the plurality of second side fuel nozzles are disposed downstream of the combustion liner relative to the plurality of first side fuel nozzles.

[0007] (2) A gas turbine according to at least one embodiment of the present disclosure includes: a compressor that generates compressed air; a gas turbine combustor having the configuration described in (1); and a turbine that is rotationally driven by combustion gas generated by the gas turbine combustor.

[0008] According to at least one embodiment of the present disclosure, in a gas turbine combustor having a fuel nozzle provided at the side of a combustion liner, ｘ The amount of generated heat can be reduced.

[0009] FIG. 1 is a schematic configuration diagram of a gas turbine according to an embodiment. FIG. 2 is a schematic diagram showing a combustor and an inlet portion of a turbine of a gas turbine according to an embodiment. FIG. 3 is a schematic cross-sectional view of a combustion liner according to an embodiment, showing a cross section as viewed from the arrows III-III in FIG. 2. FIG. 4 is a schematic cross-sectional view of a combustion liner according to an embodiment, showing a cross section as viewed from the arrows IV-IV in FIG. 2. FIG. 5 is a diagram comparing the cross section of the combustion liner shown in FIG. 3 with the cross section shown in FIG. 4. FIG. 6 is a cross-sectional view as viewed from the arrows VI in FIG. 2, showing a schematic arrangement of outlets of a plurality of combustors arranged at intervals in the circumferential direction of a rotor. FIG. 7 is a cross-sectional view of a combustion liner seen from the circumferential direction of the combustion liner, showing the vicinity of a first side fuel nozzle. FIG. 8 is a cross-sectional view of a combustion liner seen from the circumferential direction of the combustion liner, showing the vicinity of a second side fuel nozzle.

[0010] Several embodiments of the present disclosure will be described below with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of components described as embodiments or shown in the drawings are not intended to limit the scope of the present disclosure and are merely illustrative examples. For example, expressions expressing relative or absolute arrangements, such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial," not only strictly express such arrangements, but also express relative displacements with a tolerance or angle or distance to the extent that the same function is achieved. For example, expressions expressing the equality of things, such as "same," "equal," and "homogeneous," not only express strict equality, but also express tolerance or differences to the extent that the same function is achieved. For example, expressions expressing shapes such as a square or cylindrical shape not only express shapes such as a square or cylindrical shape in the strict geometric sense, but also express shapes including concave and convex portions, chamfered portions, etc., to the extent that the same effect is achieved. On the other hand, the expressions "comprise," "include," "have," "includes," or "have" of one element are not exclusive expressions that exclude the presence of other elements.

[0011] First, a gas turbine, which is an example of an application of a gas turbine combustor according to an embodiment, will be described with reference to Fig. 1 . Fig. 1 is a schematic configuration diagram of the gas turbine according to an embodiment. As shown in Fig. 1 , the gas turbine 1 includes a compressor 2 for generating compressed air, a gas turbine combustor (combustor) 4 for generating combustion gas using the compressed air and fuel, and a turbine 6 configured to be rotationally driven by the combustion gas. In the case of the gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6.

[0012] The compressor 2 includes a plurality of stator vanes 16 fixed to the compressor casing 10 side, and a plurality of moving blades 18 implanted in the rotor 8 so as to be arranged alternately with respect to the stator vanes 16. Air taken in from an air intake 12 is sent to the compressor 2, and this air is compressed as it passes through the plurality of stator vanes 16 and the plurality of moving blades 18, thereby becoming high-temperature, high-pressure compressed air.

[0013] The combustors 4 are supplied with fuel and compressed air generated by the compressor 2, and the fuel is combusted in the combustors 4 to generate combustion gas, which is a working fluid for the turbine 6. As shown in Figure 1, the gas turbine 1 has a plurality of combustors 4 arranged in a casing 20 along the circumferential direction around a rotor 8.

[0014] The turbine 6 has a combustion gas passage 28 formed by the turbine casing 22 and includes a plurality of stator vanes 24 and rotor blades 26 provided in the combustion gas passage 28. The stator vanes 24 and rotor blades 26 of the turbine 6 are provided downstream of the combustor 4 with respect to the flow of combustion gas. The stator vanes 24 are fixed to the turbine casing 22, and a plurality of stator vanes 24 arranged along the circumferential direction of the rotor 8 constitute a stator vane row. The rotor blades 26 are implanted in the rotor 8, and a plurality of rotor blades 26 arranged along the circumferential direction of the rotor 8 constitute a rotor blade row. The stator vane rows and rotor blade rows are arranged alternately in the axial direction of the rotor 8. In the turbine 6, combustion gas from the combustor 4 flows into the combustion gas passage 28 and passes through the stator vanes 24 and rotor blades 26, thereby driving the rotor 8 to rotate about the axis O. This drives a generator connected to the rotor 8 to generate electricity. After driving the turbine 6, the combustion gas is discharged to the outside via an exhaust chamber 30. With respect to the axial direction of the rotor 8, the downstream side of the flow of combustion gas flowing through the combustion gas passage 28 is referred to as the downstream side in the axial direction of the rotor 8, and the upstream side of the flow of combustion gas flowing through the combustion gas passage 28 is referred to as the upstream side in the axial direction of the rotor 8.

[0015] Next, the combustor 4 according to one embodiment will be described. Fig. 2 is a schematic diagram showing an inlet portion of the combustor 4 and the turbine 6 of the gas turbine 1 according to one embodiment.

[0016] In the gas turbine 1 according to some embodiments, each of the plurality of combustors 4 (see FIG. 1 ) arranged in the circumferential direction around the rotor 8 includes a combustion liner 36 provided in a combustor casing 32 defined by the casing 20, and a first combustion burner 38 and a plurality of second combustion burners 44 arranged to surround the first combustion burner 38, each of which is arranged in the combustion liner 36. That is, the combustion liner 36, the first combustion burner 38, and the second combustion burner 44 are housed in the casing 20.

[0017] The combustion liner (combustor liner) 36 has an inner liner 48 arranged around the first combustion burner 38 and the plurality of second combustion burners 44, and a transition piece 50 connected to the tip of the inner liner 48. The inner liner 48 and the transition piece 50 may be formed integrally. An acoustic device 60 for damping combustion vibrations may be provided on the outer periphery of the combustion liner 36.

[0018] The first combustion burner 38 is disposed along the direction of the central axis C of the combustion liner 36 (i.e., the axial direction of the combustor 4 and the combustion liner 36), and has a first fuel nozzle 40 for injecting fuel. Fuel is supplied to the first fuel nozzle 40 via a first fuel port 42.

[0019] The second combustion burner 44 has a second fuel nozzle 46 for injecting fuel. Fuel is supplied to the second fuel nozzle 46 through the second fuel port 43.

[0020] The combustor 4 further includes an outer casing 52 provided on the outer circumferential side of the inner casing 48 inside the casing 20. An air passage 54 through which compressed air flows is formed on the outer circumferential side of the inner casing 48 and on the inner circumferential side of the outer casing 52.

[0021] Compressed air generated by the compressor 2 (see FIG. 1) is supplied into the combustor casing 32 through the casing inlet 31, flows from the combustor casing 32 into an air passage 54 as combustion air, is changed in direction by a wall surface portion 53 provided along a plane perpendicular to the axial direction of the combustor 4, and flows into the first burner tube of the first combustion burner 38 and the second burner tube of the second combustion burner 44. In each burner tube, fuel injected from the fuel nozzle is mixed with the compressed air (combustion air), and this mixture flows into the combustion tube 36, where it is ignited and combusted, generating combustion gas FG.

[0022] The combustion gas FG generated by the combustion of fuel in the combustor 4 flows into the turbine 6 through an outlet 51 of the combustor 4 located at the downstream end of the transition piece 50 .

[0023] (Third Fuel Nozzle 70) FIG. 3 is a schematic cross-sectional view of the combustion liner 36 according to one embodiment, taken along the line III-III in FIG. 2 . FIG. 4 is a schematic cross-sectional view of the combustion liner 36 according to one embodiment, taken along the line IV-IV in FIG. 2 . FIG. 5 compares the cross-section of the combustion liner 36 shown in FIG. 3 with the cross-section shown in FIG. 4 , and shows the cross-section of the combustion liner 36 taken along the line III-III in FIG. 2 (i.e., FIG. 3 ), drawn with a two-dot chain line, superimposed on FIG. 4 . The combustor 4 according to one embodiment includes a plurality of third fuel nozzles 70 provided on the side of the combustion liner 36. That is, the third fuel nozzles 70 are fuel nozzles for supplying fuel into the combustion liner 36 from the side of the combustion liner 36. The third fuel nozzles 70 are fixed to, for example, the transition piece 50.

[0024] Fuel is supplied to the third fuel nozzles 70 via third fuel ports 74 (see FIG. 2 ). Note that fuel supply pipes extending from the third fuel ports 74 to the third fuel nozzles 70 are not shown in FIG. 2 .

[0025] The third fuel nozzle 70 according to one embodiment is configured to be able to inject a mixture of fuel supplied from a third fuel port 74 via a fuel supply pipe (not shown) and compressed air in the combustor casing 32 into the combustion liner 36. In the following description, when referring to fuel supplied and injected into the combustion liner 36 from the third fuel nozzle 70, the fuel supplied and injected into the combustion liner 36 from the third fuel nozzle 70 includes not only fuel but also compressed air.

[0026] When fuel is injected into the combustion liner 36 from the third fuel nozzle 70, the injected fuel is mixed with the combustion air in the combustion liner 36 and combusted. By injecting fuel into the combustion liner 36 from the third fuel nozzle 70, fuel can be supplied to a secondary combustion zone in a transition area downstream of the primary combustion zone where the fuel from the first fuel nozzle 40 and the second fuel nozzle 46 is combusted. This reduces nitrogen oxides (NO ｘ ) can be suppressed while improving combustion efficiency.

[0027] In the combustor 4 according to the embodiment, the plurality of third fuel nozzles 70 include a plurality of first side fuel nozzles 71 disposed radially outward of the rotor 8 when the combustion liner 36 is attached to the casing 20 of the gas turbine 1, and a plurality of second side fuel nozzles 72 disposed radially inward of the rotor 8 when the combustion liner 36 is attached to the casing 20. In the combustor 4 according to the embodiment, the plurality of second side fuel nozzles 72 are disposed downstream of the combustion liner 36 relative to the plurality of first side fuel nozzles 71. Note that in the combustor 4 according to the embodiment, all of the plurality of second side fuel nozzles 72 are disposed downstream of the combustion liner 36 relative to all of the plurality of first side fuel nozzles 71.

[0028] In the following description, when there is no need to particularly distinguish between the first side fuel nozzle 71 and the second side fuel nozzle 72, or when the first side fuel nozzle 71 and the second side fuel nozzle 72 are referred to collectively, the first side fuel nozzle 71 and the second side fuel nozzle 72, or the first side fuel nozzle 71 or the second side fuel nozzle 72, will be referred to as the third fuel nozzle 70.

[0029] With respect to the axial direction of the combustion cylinder 36, the downstream side of the flow of combustion gas FG flowing within the combustion cylinder 36 is referred to as the downstream side of the axial direction of the combustion cylinder 36, or simply as the downstream side of the combustion cylinder 36, and the upstream side of the flow of combustion gas FG flowing within the combustion cylinder 36 is referred to as the upstream side of the axial direction of the combustion cylinder 36, or simply as the upstream side of the combustion cylinder 36.

[0030] In the combustor 4 according to the embodiment, the plurality of first side fuel nozzles 71 are disposed downstream of the combustion liner 36 from the acoustic device 60 for attenuating combustion oscillation and relatively close to the acoustic device 60. The plurality of first side fuel nozzles 71 may be disposed at the same axial position of the combustion liner 36. In the combustor 4 according to the embodiment, the number of the plurality of first side fuel nozzles 71 may be two, or may be three or more.

[0031] In the combustor 4 according to one embodiment, the second side fuel nozzles 72 are disposed downstream of the combustion liner 36 relative to the first side fuel nozzles 71 and relatively close to the outlet 51 of the combustor 4. The second side fuel nozzles 72 may be disposed at the same axial position of the combustion liner 36. In the combustor 4 according to one embodiment, the number of the second side fuel nozzles 72 may be two or may be three or more.

[0032] In the combustor 4 according to one embodiment configured as described above, the central axis C of the combustion liner 36 is inclined with respect to the axial direction of the rotor 8 of the gas turbine 1 on the upstream side of the combustion liner 36 so as to move radially inward of the rotor 8 toward the downstream side in the axial direction of the rotor 8, but extends parallel to the axial direction of the rotor 8 at the outlet of the combustion liner 36 (the outlet section 51 of the combustor 4). In other words, the combustion liner 36 has a curved shape on the downstream side. When the first side fuel nozzle 71 and the second side fuel nozzle 72 are disposed at the same position along the central axis C of the combustion liner 36, the distance from the second side fuel nozzle 72 to the outlet of the combustion liner 36 (the outlet section 51 of the combustor 4) is longer than the distance from the first side fuel nozzle 71 to the outlet of the combustion liner 36 (the outlet section 51 of the combustor 4). Therefore, the combustion gas FG generated by the combustion of the fuel supplied from the second side fuel nozzle 72 remains in the combustion liner 36 for a longer period of time than the combustion gas FG generated by the combustion of the fuel supplied from the first side fuel nozzle 71 remains in the combustion liner 36. ｘ There is a risk that the amount of

[0033] Furthermore, as a result of extensive research by the inventors, it was found that if the first side fuel nozzle 71 and the second side fuel nozzle 72 are arranged at the same position along the central axis C of the combustion liner 36, it becomes difficult for the combustion gas FG generated by the combustion of the fuel supplied from the first fuel nozzle 40 and the second fuel nozzle 46, which are fuel nozzles arranged on the upstream side of the combustion liner 36, to mix with the combustion gas FG generated by the combustion of the fuel supplied from the third fuel nozzle 70, resulting in NO ｘ It was found that there is a risk of an increase in the amount of

[0034] Therefore, in the combustor 4 according to one embodiment, the second side fuel nozzles 72 are arranged downstream of the first side fuel nozzles 71 in the combustion liner 36, so that the first side fuel nozzles 71 and the second side fuel nozzles 72 are arranged at different positions in the axial direction of the combustion liner 36. This reduces the time that the combustion gas FG generated by the combustion of the fuel supplied from the second side fuel nozzles 72 remains in the combustion liner 36. ｘFurthermore, according to the combustor 4 according to one embodiment, the first side fuel nozzle 71 and the second side fuel nozzle 72 are positioned at different positions along the central axis C of the combustion liner 36, which facilitates mixing of the combustion gas FG generated by the combustion of the fuel supplied from the first fuel nozzle 40 and the second fuel nozzle 46 arranged upstream of the combustion liner 36 with the combustion gas FG generated by the combustion of the fuel supplied from the third fuel nozzle 70. As a result, the amount of NO ｘ The amount of generated heat can be reduced.

[0035] According to the gas turbine 1 including the combustor 4 according to one embodiment, NO in the gas turbine 1 ｘ The amount of generated heat can be reduced.

[0036] (Regarding Circumferential Radius of Curvature of Combustion Liner 36 About Central Axis C) In the combustor 4 according to one embodiment, the combustion liner 36 includes a first region 81 in which the multiple first side fuel nozzles 71 are arranged, and a second region 82 in which the multiple second side fuel nozzles 72 are arranged. The circumferential radius of curvature R1 of the first region 81 about the central axis C is smaller than the circumferential radius of curvature R2 of the second region 82 about the central axis C.

[0037] FIG. 6 is a cross-sectional view taken along the arrow VI in FIG. 2 , and schematically illustrates the arrangement of outlets 51 of multiple combustors 4 arranged at intervals in the circumferential direction of the rotor 8. When multiple combustors 4 are arranged at intervals in the circumferential direction of the rotor 8, if the shape of the outlets of the combustion liner 36 (the outlets 51 of the combustors 4) is configured to follow the outer edge of a partial ring shape centered on the rotor 8 as shown in FIG. 6 , the opening area of ​​the outlets of the combustion liner 36 (the outlets 51 of the combustors 4) can be relatively large. Therefore, the radial cross-sectional shape of the combustion liner 36 about the central axis C gradually changes from a cylindrical shape to a shape following the outer edge of the partial ring shape from the upstream side to the downstream side. When the radial cross-sectional shape of the combustion liner 36 about the central axis C is changed as described above, the circumferential radius of curvature about the central axis C gradually increases from the upstream side to the downstream side in the relatively radially outer regions of the rotor 8 and the relatively radially inner regions of the rotor 8 in the combustion liner 36. Therefore, when the radial cross-sectional shape of the combustion liner 36 about the central axis C is changed as described above, the radius of curvature R2 of the second region 82 about the central axis C tends to be larger than the radius of curvature R1 of the first region 81 about the central axis C. In other words, the radius of curvature R1 of the combustion liner 36 about the first region 81 about the circumferential direction is smaller than the radius of curvature R2 of the combustion liner 36 about the second region 82 about the circumferential direction.

[0038] As the combustion tube 36 moves from the upstream side to the downstream side, the cross-sectional shape of the combustion tube 36 transitions from a cylindrical shape to a shape that follows the outer edge of a partial ring shape, with the inner side of the partial ring shape being radially inward of the rotor 8.

[0039] (Regarding the fuel injection direction from the third fuel nozzle 70) Figure 7 is a cross-sectional view of the combustion tube 36, viewed from the circumferential direction of the combustion tube 36, showing the vicinity of the first side fuel nozzle 71. Figure 8 is a cross-sectional view of the combustion tube 36, viewed from the circumferential direction of the combustion tube 36, showing the vicinity of the second side fuel nozzle 72. In Figures 3, 4, 7, and 8, the outline arrow F represents the injection direction of fuel from the third fuel nozzle 70. The dashed line along the arrow F is the center line Cf of the fuel injection direction of the third fuel nozzle 70.

[0040] As described above, the central axis C of the combustion liner 36 is curved relatively downstream of the combustion liner 36. The direction in which the central axis C of the combustion liner 36 is curved is the radial direction of the rotor 8. In the upstream region of the combustion liner 36, the central axis C is not curved but extends linearly. In this way, the central axis C that extends linearly without being curved in the upstream region of the combustion liner 36 is referred to as the upstream central axis C. １ Also, the upstream center axis C １ The line extending downstream of the line 12 is the upstream center axis C １ Extension C of ＥＸ , or simply extension C ＥＸ It is called.

[0041] For example, as shown in FIG. 7 , in the combustor 4 according to one embodiment, the center line Cf of the fuel injection direction of each of the plurality of first side fuel nozzles 71 is aligned with the center axis of the upstream region of the combustion liner 36 (the upstream center axis C １ ), or the central axis C of the upstream region of the combustion liner 36 (upstream central axis C １ ) Extension C ＥＸ In contrast, the central axis C of the upstream region of the combustion liner 36 (upstream central axis C １ ), or extension C ＥＸ The inclination of the nozzles 40 and 46 is preferably such that the nozzles 40 and 46 are inclined toward the downstream side of the combustion tube 36 as they approach the nozzles 40 and 46. This facilitates mixing of the combustion gas FG generated by the combustion of the fuel supplied from the first fuel nozzle 40 and the second fuel nozzle 46, which are arranged upstream of the combustion tube 36, with the combustion gas FG generated by the combustion of the fuel supplied from the first side fuel nozzle 71. ｘ The amount of generated heat can be reduced.

[0042] Upstream center axis C １ , or extension C ＥＸ The inclination angle θa of the center line Cf of the fuel injection direction of each of the first side fuel nozzles 71 with respect to the orthogonal line Lr1 may be, for example, 1 degree or more and 45 degrees or less.

[0043] For example, as shown in FIG. 8 , in the combustor 4 according to one embodiment, the center line Cf of the fuel injection direction of each of the plurality of second side fuel nozzles 72 is aligned with the center axis C of the upstream region of the combustion liner 36 (the upstream center axis C １ ) Extension C ＥＸ In contrast, extension C ＥＸ Preferably, the inclination is such that the closer to the NO 30, the more downstream the combustion tube 36. This facilitates the mixing of the combustion gas FG generated by the combustion of the fuel supplied from the first fuel nozzle 40 and the second fuel nozzle 46 arranged on the upstream side of the combustion tube 36 and the combustion gas FG generated by the combustion of the fuel supplied from the second side fuel nozzle 72. ｘ The amount of generated heat can be reduced.

[0044] Extension line C ＥＸ The inclination angle θb of the center line Cf of the fuel injection direction of each of the second side fuel nozzles 72 with respect to the orthogonal line Lr2 may be, for example, 1 degree or more and 45 degrees or less.

[0045] (Regarding the Pair of First Side Fuel Nozzles 71 and the Pair of Second Side Fuel Nozzles 72) In the combustor 4 according to one embodiment, the plurality of first side fuel nozzles 71 may include a pair of first side fuel nozzles 71. In the combustor 4 according to one embodiment, the plurality of second side fuel nozzles 72 may include a pair of second side fuel nozzles 72. In the following description, the plurality of first side fuel nozzles 71 will be described as including a pair of first side fuel nozzles 71, and the plurality of second side fuel nozzles 72 will be described as including a pair of second side fuel nozzles 72.

[0046] 5 , for example, in the combustor 4 according to one embodiment, the angle θ2 formed by the center line Cf of the fuel injection direction from one of the pair of second side fuel nozzles 72 and the center line Cf of the fuel injection direction from the other of the pair of second side fuel nozzles 72 may be different from the angle θ1 formed by the center line Cf of the fuel injection direction from one of the pair of first side fuel nozzles 71 and the center line Cf of the fuel injection direction from the other of the pair of first side fuel nozzles 71. This facilitates mixing of the combustion gas FG generated by the combustion of the fuel supplied from the first fuel nozzle 40 and the second fuel nozzle 46 arranged upstream of the combustion tube 36 with the combustion gas FG generated by the combustion of the fuel supplied from the third fuel nozzle 70. ｘ The amount of generated heat can be reduced.

[0047] 5 , for example, in the combustor 4 according to one embodiment, the angle θ2 may be smaller than the angle θ1. By reducing the angle θ2 formed by the center line Cf of the fuel injection direction from the pair of second side fuel nozzles 72, the fuel injected from the pair of second side fuel nozzles 72 is dispersed and injected over a relatively wide range in the circumferential direction of the combustion tube 36 toward the radially outer side of the rotor 8 within the combustion tube 36. This facilitates mixing of the combustion gas FG generated by the combustion of the fuel supplied from the first fuel nozzle 40 and the second fuel nozzle 46 arranged upstream of the combustion tube 36 with the combustion gas FG generated by the combustion of the fuel supplied from the pair of second side fuel nozzles 72. Therefore, NO ｘ The amount of generated heat can be reduced.

[0048] Note that in the combustor 4 according to one embodiment, the angle θ2 may be greater than the angle θ1. In this case, when the pair of first side fuel nozzles 71 are disposed at a relatively large distance from each other in the circumferential direction of the combustion tube 36, the fuel injected from the pair of second side fuel nozzles 72 is injected into the combustion tube 36 toward the radially outer side of the rotor 8, into a region downstream of the region between the pair of first side fuel nozzles 71. Therefore, it is expected that the combustion gas FG generated when the fuel supplied from the first fuel nozzle 40 and the second fuel nozzle 46 passes through the region between the pair of first side fuel nozzles 71 and burns, and the combustion gas FG generated when the fuel supplied from the second side fuel nozzle 72 burns can be mixed. As a result, the NOx reduction can be achieved. ｘ The amount of generated heat can be reduced.

[0049] As described above, in the combustor 4 according to one embodiment, the central axis C of the combustion liner 36 is an upstream central axis C that extends linearly in the upstream region of the combustion liner 36. １ and at the outlet of the combustion liner 36 (the outlet portion 51 of the combustor 4), the upstream central axis C １ , i.e., in the axial direction of the rotor 8. In this way, the imaginary plane (imaginary plane PV) that includes the central axis C of the curved combustion liner 36 is a plane that extends in the radial direction of the rotor 8 and the axial direction of the rotor 8.

[0050] In the combustor 4 according to the embodiment, the pair of first side fuel nozzles 71 may be disposed symmetrically with respect to an imaginary plane PV when viewed along the central axis C of the combustion liner 36, as shown in FIGS. 3 and 5 . That is, in the combustor 4 according to the embodiment, the plurality of first side fuel nozzles 71 may include a pair of first side fuel nozzles 71 disposed such that a first distance D1 from the imaginary plane PV is equal across the imaginary plane PV, as shown in FIG. 5 . Furthermore, in the combustor 4 according to the embodiment, the center lines Cf of the injection directions of the fuel injected from the pair of first side fuel nozzles 71 may be symmetrical with respect to the imaginary plane PV when viewed along the central axis C of the combustion liner 36, as shown in FIGS. 3 and 5 . This is expected to promote mixing of the combustion gas FG generated by the combustion of the fuel supplied from the first fuel nozzle 40 and the second fuel nozzle 46 and the combustion gas FG generated by the combustion of the fuel supplied from the first side fuel nozzle 71, compared to a case in which the pair of first side fuel nozzles 71 are disposed asymmetrically with respect to the imaginary plane PV. This means NO ｘ The amount of generated heat can be reduced.

[0051] Similarly, in the combustor 4 according to the embodiment, the pair of second side fuel nozzles 72 may be disposed symmetrically with respect to the imaginary plane PV when viewed along the central axis C of the combustion liner 36, as shown in Figures 4 and 5 . That is, in the combustor 4 according to the embodiment, the plurality of second side fuel nozzles 72 may include a pair of second side fuel nozzles 72 disposed such that the second distances D2 from the imaginary plane PV are equal across the imaginary plane PV, as shown in Figure 5 . Furthermore, in the combustor 4 according to the embodiment, the center lines Cf of the injection directions of fuel injected from the pair of second side fuel nozzles 72 may be symmetrical with respect to the imaginary plane PV when viewed along the central axis C of the combustion liner 36, as shown in Figures 4 and 5 . This is expected to promote mixing of the combustion gas FG generated by the combustion of the fuel supplied from the first fuel nozzle 40 and the second fuel nozzle 46 and the combustion gas FG generated by the combustion of the fuel supplied from the second side fuel nozzle 72, compared to when the pair of second side fuel nozzles 72 are arranged asymmetrically across the imaginary plane PV. ｘ The amount of generated heat can be reduced.

[0052] In the combustor 4 according to the embodiment, a first distance D1 between each of the pair of first side fuel nozzles 71 and the imaginary plane PV may be greater than a second distance D2 between each of the pair of second side fuel nozzles 72 and the imaginary plane PV. The difference (D1-D2) between the first distance D1 and the second distance D2 may be less than the second distance D2. This increases the distance (D2+D2) between the pair of second side fuel nozzles 72 compared to when the difference (D1-D2) between the first distance D1 and the second distance D2 is greater than the second distance D2. Therefore, fuel injected from the pair of second side fuel nozzles 72 is dispersed over a relatively wide range in the circumferential direction of the combustion liner 36 toward the radially outer side of the rotor 8 within the combustion liner 36. This facilitates mixing of the combustion gas FG generated by the combustion of the fuel supplied from the first fuel nozzle 40 and the second fuel nozzle 46 arranged on the upstream side of the combustion tube 36 with the combustion gas FG generated by the combustion of the fuel supplied from the pair of second side fuel nozzles 72. ｘ The amount of generated heat can be reduced.

[0053] In the combustor 4 according to one embodiment, the separation distance (D1+D1) between the pair of first side fuel nozzles 71 on either side of the imaginary plane PV may be greater than the radius of the combustion tube 36 in a relatively upstream region where the radial cross-sectional shape of the combustion tube 36 about the central axis C is cylindrical.

[0054] The present disclosure is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations of these modifications.

[0055] The content described in each of the above embodiments can be understood as follows, for example. (1) A gas turbine combustor 4 according to at least one embodiment of the present disclosure includes a combustion liner 36 and a plurality of side fuel nozzles (third fuel nozzles 70) provided on a side of the combustion liner 36. The plurality of side fuel nozzles (third fuel nozzles 70) includes a plurality of first side fuel nozzles 71 disposed radially outward of the rotor 8 when the combustion liner 36 is attached to a casing 20 that covers an outer periphery of the rotor 8 of the gas turbine 1, and a plurality of second side fuel nozzles 72 disposed radially inward of the rotor 8 when the combustion liner 36 is attached to the casing 20. The plurality of second side fuel nozzles 72 are disposed downstream of the combustion liner 36 relative to the plurality of first side fuel nozzles 71.

[0056] According to the configuration (1) above, the second side fuel nozzles 72 are disposed downstream of the first side fuel nozzles 71 in the combustion liner 36, so that the combustion gas FG generated by the combustion of the fuel supplied from the second side fuel nozzles 72 remains in the combustion liner 36 for a shorter period of time. ｘ Furthermore, according to the configuration (1) above, the first side fuel nozzle 71 and the second side fuel nozzle 72 are positioned at different positions along the central axis C of the combustion tube 36, which facilitates mixing of the combustion gas FG generated by the combustion of the fuel supplied from the fuel nozzles (first fuel nozzle 40 and second fuel nozzle 46) located upstream of the combustion tube 36 with the combustion gas FG generated by the combustion of the fuel supplied from the side fuel nozzle (third fuel nozzle 70). This reduces the amount of NO ｘThe amount of generated heat can be reduced.

[0057] (2) In some embodiments, in the configuration described in (1) above, the plurality of first side fuel nozzles 71 may include a pair of first side fuel nozzles 71. The plurality of second side fuel nozzles 72 may include a pair of second side fuel nozzles 72. An angle θ2 formed between a centerline Cf of the fuel injection direction from one of the pair of second side fuel nozzles 72 and a centerline Cf of the fuel injection direction from the other of the pair of second side fuel nozzles 72 may be different from an angle θ1 formed between a centerline Cf of the fuel injection direction from one of the pair of first side fuel nozzles 71 and a centerline Cf of the fuel injection direction from the other of the pair of first side fuel nozzles 71.

[0058] According to the configuration (2) above, the combustion gas FG generated by the combustion of the fuel supplied from the fuel nozzles (first fuel nozzle 40 and second fuel nozzle 46) arranged on the upstream side of the combustion tube 36 and the combustion gas FG generated by the combustion of the fuel supplied from the side fuel nozzle (third fuel nozzle 70) are more likely to mix. ｘ The amount of generated heat can be reduced.

[0059] (3) In some embodiments, in the configuration described in (2) above, the angle θ2 between the center line Cf of the fuel injection direction from one of the pair of second side fuel nozzles 72 and the center line Cf of the fuel injection direction from the other of the pair of second side fuel nozzles 72 may be smaller than the angle θ1 between the center line Cf of the fuel injection direction from one of the pair of first side fuel nozzles 71 and the center line Cf of the fuel injection direction from the other of the pair of first side fuel nozzles 71.

[0060] According to the configuration of (3) above, by reducing the angle θ2 formed by the center line Cf of the fuel injection direction from the pair of second side fuel nozzles 72, the fuel injected from the pair of second side fuel nozzles 72 is dispersed and injected over a relatively wide range in the circumferential direction of the combustion tube 36 toward the radially outer side of the rotor 8 within the combustion tube 36. This facilitates mixing of the combustion gas FG generated by the combustion of the fuel supplied from the fuel nozzles (first fuel nozzle 40 and second fuel nozzle 46) arranged upstream of the combustion tube 36 with the combustion gas FG generated by the combustion of the fuel supplied from the pair of second side fuel nozzles 72. Therefore, NO ｘ The amount of generated heat can be reduced.

[0061] (4) In some embodiments, in any of the configurations (1) to (3) above, the combustion liner 36 may include a first region 81 in which the plurality of first side fuel nozzles 71 are arranged, and a second region 82 in which the plurality of second side fuel nozzles 72 are arranged. The radius of curvature R1 of the combustion liner 36 in the circumferential direction in the first region 81 may be smaller than the radius of curvature R2 of the combustion liner 36 in the second region 82.

[0062] When multiple combustors 4 are arranged at intervals around the rotor 8, if the shape of the outlet of the combustion liner 36 (the outlet portion 51 of the combustor 4) is a shape that follows the outer edge of a partial ring shape centered on the rotor 8, the opening area of ​​the outlet of the combustion liner 36 (the outlet portion 51 of the combustor 4) can be relatively large. Therefore, the radial cross-sectional shape of the combustion liner 36 about the central axis C gradually changes from a cylindrical shape to a shape that follows the outer edge of the partial ring shape from the upstream side to the downstream side. When the radial cross-sectional shape of the combustion liner 36 about the central axis C changes as described above, the circumferential radius of curvature of the combustion liner 36 about the central axis C gradually increases from the upstream side to the downstream side in a region of the combustion liner 36 that is relatively radially outer of the rotor 8 and a region of the combustion liner 36 that is relatively radially inner of the rotor 8. Therefore, when the radial cross-sectional shape of the combustion liner 36 about the central axis C is changed as described above, the radius of curvature R2 of the second region 82 about the central axis C tends to be larger than the radius of curvature R1 of the first region 81 about the central axis C. That is, as in the configuration of (4) above, the radius of curvature R1 of the combustion liner 36 about the first region 81 about the circumferential direction is smaller than the radius of curvature R2 of the combustion liner 36 about the second region 82 about the circumferential direction.

[0063] (5) In some embodiments, in any of the configurations (1) to (4) above, the center line Cf of the fuel injection direction of each of the plurality of first side fuel nozzles 71 is aligned with the center axis C of the upstream region of the combustion liner 36 (the upstream center axis C １ ), or the central axis C of the upstream region of the combustion liner 36 (upstream central axis C １ ) Extension C ＥＸ In contrast, the central axis C of the upstream region of the combustion liner 36 (upstream central axis C １ ), or extension C ＥＸ It is preferable that the inclination angle be such that it approaches the downstream side of the combustion tube 36 as it approaches the inclination angle.

[0064] According to the configuration of (5) above, the combustion gas FG generated by the combustion of the fuel supplied from the fuel nozzles (the first fuel nozzle 40 and the second fuel nozzle 46) arranged on the upstream side of the combustion tube 36 and the combustion gas FG generated by the combustion of the fuel supplied from the first side fuel nozzle 71 are more likely to mix together. ｘ The amount of generated heat can be reduced.

[0065] (6) In some embodiments, in any of the configurations (1) to (5) above, the center line Cf of the fuel injection direction of each of the plurality of second side fuel nozzles 72 is aligned with the center axis C of the upstream region of the combustion liner 36 (the upstream center axis C １ ) Extension C ＥＸ In contrast, extension C ＥＸ It is preferable that the inclination angle be such that it approaches the downstream side of the combustion tube 36 as it approaches the inclination angle.

[0066] According to the configuration of (6) above, the combustion gas FG generated by the combustion of the fuel supplied from the fuel nozzles (the first fuel nozzle 40 and the second fuel nozzle 46) arranged on the upstream side of the combustion tube 36 and the combustion gas FG generated by the combustion of the fuel supplied from the second side fuel nozzle 72 are more likely to mix. ｘ The amount of generated heat can be reduced.

[0067] (7) In some embodiments, in any of the configurations (1) to (6) above, the central axis C of the combustion liner 36 is an upstream central axis C that extends linearly in the upstream region of the combustion liner 36. １ and at the outlet of the combustion liner 36 (the outlet portion 51 of the combustor 4), the upstream central axis C １The first side fuel nozzles 71 may extend in a direction different from the direction of extension of the first side fuel nozzles 71. The first side fuel nozzles 71 may include a pair of first side fuel nozzles 71 arranged across an imaginary plane (imaginary plane PV) including the central axis C from the upstream region to the outlet, with the first side fuel nozzles 71 spaced apart at equal distances (first distance D1) from the imaginary plane PV. The second side fuel nozzles 72 may include a pair of second side fuel nozzles 72 arranged across the imaginary plane PV with the second side fuel nozzles 72 spaced apart at equal distances (second distance D2) from the imaginary plane PV. The first distance D1 between each of the pair of first side fuel nozzles 71 and the plane (imaginary plane PV) may be greater than the second distance D2 between each of the pair of second side fuel nozzles 72 and the plane (imaginary plane PV). The difference (D1 - D2) between the first distance D1 and the second distance D2 may be smaller than the second distance D2.

[0068] According to the configuration of (7) above, the distance (D2+D2) between the pair of second side fuel nozzles 72 is greater than when the difference (D1-D2) between the first distance D1 and the second distance D2 is greater than the second distance D2. Therefore, the fuel injected from the pair of second side fuel nozzles 72 is dispersed and injected over a relatively wide range in the circumferential direction of the combustion liner 36 toward the radially outer side of the rotor 8 within the combustion liner 36. This facilitates mixing of the combustion gas FG generated by the combustion of the fuel supplied from the fuel nozzles (first fuel nozzle 40 and second fuel nozzle 46) located upstream of the combustion liner 36 with the combustion gas FG generated by the combustion of the fuel supplied from the pair of second side fuel nozzles 72. Therefore, NO ｘ The amount of generated heat can be reduced.

[0069] (8) A gas turbine 1 according to at least one embodiment of the present disclosure includes: a compressor 2 that generates compressed air; a gas turbine combustor 4 having any of the configurations described above in (1) to (7); and a turbine 6 that is rotationally driven by combustion gas FG generated by the gas turbine combustor 4.

[0070] According to the configuration (8) above, in the gas turbine 1, NO ｘ The amount of generated heat can be reduced.

[0071] REFERENCE SIGNS LIST 1 Gas turbine 2 Compressor 4 Gas turbine combustor (combustor) 6 Turbine 8 Rotor 20 Casing 36 Combustor liner 40 First fuel nozzle 46 Second fuel nozzle 51 Outlet section 70 Third fuel nozzle 71 First side fuel nozzle 72 Second side fuel nozzle 81 First region 82 Second region

Claims

1. A gas turbine combustor comprising: a combustion liner; and a plurality of side fuel nozzles provided on a side of the combustion liner, wherein the plurality of side fuel nozzles include a plurality of first side fuel nozzles arranged radially outside the rotor when the combustion liner is attached to a casing that covers the outer periphery of the rotor of a gas turbine, and a plurality of second side fuel nozzles arranged radially inside the rotor when the combustion liner is attached to the casing, and the plurality of second side fuel nozzles are arranged downstream of the combustion liner relative to the plurality of first side fuel nozzles.

2. The gas turbine combustor according to claim 1, wherein the plurality of first side fuel nozzles include a pair of first side fuel nozzles, and the plurality of second side fuel nozzles include a pair of second side fuel nozzles, and an angle formed by a centerline of the fuel injection direction from one second side fuel nozzle of the pair of second side fuel nozzles and a centerline of the fuel injection direction from the other second side fuel nozzle of the pair of second side fuel nozzles is different from an angle formed by a centerline of the fuel injection direction from one first side fuel nozzle of the pair of first side fuel nozzles and a centerline of the fuel injection direction from the other first side fuel nozzle of the pair of first side fuel nozzles.

3. The gas turbine combustor according to claim 2, wherein an angle formed by a centerline of the fuel injection direction from one of the pair of second side fuel nozzles and a centerline of the fuel injection direction from the other of the pair of second side fuel nozzles is smaller than an angle formed by a centerline of the fuel injection direction from one of the pair of first side fuel nozzles and a centerline of the fuel injection direction from the other of the pair of first side fuel nozzles.

4. The gas turbine combustor according to any one of claims 1 to 3, wherein the combustion liner includes a first region in which the plurality of first side fuel nozzles are arranged and a second region in which the plurality of second side fuel nozzles are arranged, and a radius of curvature in the circumferential direction of the combustion liner in the first region is smaller than a radius of curvature in the circumferential direction of the combustion liner in the second region.

5. The gas turbine combustor according to any one of claims 1 to 3, wherein a center line of a fuel injection direction in each of the plurality of first side fuel nozzles is inclined, with respect to a central axis of an upstream region of the combustion liner or an extension of the central axis of the upstream region of the combustion liner, such that the center line approaches the central axis of the upstream region of the combustion liner or an extension of the central axis of the upstream region of the combustion liner, and approaches the central axis of the upstream region of the combustion liner or the extension.

6. The gas turbine combustor according to any one of claims 1 to 3, wherein a center line of a fuel injection direction from each of the plurality of second side fuel nozzles is inclined, with respect to an extension of a central axis of an upstream region of the combustion liner, so as to approach the extension line toward the downstream side of the combustion liner.

7. The gas turbine combustor according to any one of claims 1 to 3, wherein a central axis of the combustion liner includes an upstream central axis that extends linearly in an upstream region of the combustion liner, and extends, at an outlet of the combustion liner, in a direction different from the direction of extension of the upstream central axis, the plurality of first side fuel nozzles include a pair of first side fuel nozzles arranged at equal distances from an imaginary plane that includes the central axis from the upstream region to the outlet, and the plurality of second side fuel nozzles include a pair of second side fuel nozzles arranged at equal distances from the plane, and a first distance between each of the pair of first side fuel nozzles and the plane is greater than a second distance between each of the pair of second side fuel nozzles and the plane, and a difference between the first distance and the second distance is smaller than the second distance.

8. A gas turbine comprising: a compressor that generates compressed air; the gas turbine combustor according to any one of claims 1 to 3; and a turbine that is rotationally driven by combustion gas generated by the gas turbine combustor.

Images