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: at least one first side-portion fuel nozzle disposed toward the radially outer side of a gas turbine rotor when the combustion cylinder is attached to a casing that covers the outer circumference of the rotor; and at least one second side-portion fuel nozzles disposed toward the radially inner side of the rotor when the combustion cylinder is attached to the casing. The effective area in a first fuel supply system that supplies fuel to the first side-portion fuel nozzle is smaller than the effective area in a second fuel supply system that supplies fuel to the second side-portion fuel nozzle.

Description

Gas turbine combustor and gas turbine

[0001] This application claims priority to Japanese Patent Application No. 2024-128780, filed with the Japan Patent Office on August 5, 2024, the contents of which are incorporated herein by reference.

[0002] There are known gas turbine combustors that can supply fuel into a combustion liner from a fuel nozzle provided on a side of the combustion liner of the gas turbine combustor. For example, in a gas turbine combustor described in Patent Document 1, the fuel-to-air ratio in the fuel nozzle provided on the side of the combustion liner can be changed.

[0003] JP 2010-159955 A

[0004] If the position of the fuel nozzle on the side of the combustion tube is different, the flow of combustion air in the vehicle cabin and the temperature of the fuel supplied to the fuel nozzle will differ, resulting in NO ｘ However, Patent Document 1 does not disclose how to specifically change the fuel-to-air ratio depending on the position of the fuel nozzle.

[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 flashbacks and the likelihood of flashbacks occurring.

[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: at least one first side fuel nozzle 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 at least one second side fuel nozzle disposed radially inward of the rotor when the combustion liner is attached to the casing, and an effective area of ​​a first fuel supply system that supplies fuel to the first side fuel nozzle is smaller than an effective area of ​​a second fuel supply system that supplies the fuel to the second side fuel nozzle.

[0007] (2) A gas turbine combustor according to at least one embodiment of the present disclosure includes: a combustion liner; and at least one side fuel nozzle provided at a side of the combustion liner, wherein the at least one side fuel nozzle has: at least one upstream fuel injection hole arranged on an upstream side of the combustion liner; and at least one downstream fuel injection hole arranged on a downstream side of the combustion liner with respect to the at least one upstream fuel injection hole, and an effective area of ​​an upstream fuel supply system that supplies fuel to the upstream fuel injection hole is smaller than an effective area of ​​a downstream fuel supply system that supplies the fuel to the downstream fuel injection hole.

[0008] (3) 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.

[0009] (4) 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 (2); and a turbine that is rotationally driven by combustion gas generated by the gas turbine combustor.

[0010] 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, ｘThis reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0011] 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 a turbine inlet portion of a gas turbine according to an embodiment. FIG. 3 is a schematic cross-sectional view of a combustion liner according to an embodiment. FIG. 4 is a diagram for explaining a fuel supply pipe for supplying fuel to a third fuel nozzle. FIG. 5 is a schematic cross-sectional view taken along arrows VI-VI in FIG. 5. FIG. 6 is a schematic enlarged view of a fuel supply unit.

[0012] 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.

[0013] 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.

[0014] 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.

[0015] 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.

[0016] 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. The direction in which the axis O of the rotor 8 extends is referred to as the axial direction of the rotor 8. 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. Furthermore, the radial direction centered on the axis O of the rotor 8 is referred to as the radial direction of the rotor 8, and the circumferential direction centered on the axis O of the rotor 8 is referred to as the circumferential direction of the rotor 8.

[0017] 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.

[0018] 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.

[0019] 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.

[0020] 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.

[0021] 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.

[0022] 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.

[0023] Compressed air generated by the compressor 2 (see FIG. 1) is supplied into the combustor casing 32 via 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 to generate combustion gas.

[0024] Combustion gas 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 .

[0025] In the following description, the direction in which the central axis C of the combustion cylinder 36 extends will be referred to as the axial direction of the combustion cylinder 36. With respect to the axial direction of the combustion cylinder 36, the downstream side of the flow of combustion gas FG flowing through the combustion cylinder 36 will be referred to as the downstream side in the axial direction of the combustion cylinder 36, or simply as the downstream side of the combustion cylinder 36. The upstream side of the flow of combustion gas FG flowing through the combustion cylinder 36 will be referred to as the upstream side in the axial direction of the combustion cylinder 36, or simply as the upstream side of the combustion cylinder 36. Furthermore, the circumferential direction centered on the central axis C of the combustion cylinder 36 will be referred to as the circumferential direction of the combustion cylinder 36, and the radial direction centered on the central axis C of the combustion cylinder 36 will be referred to as the radial direction of the combustion cylinder 36. The central axis C of the combustion cylinder 36 is curved relatively downstream of the combustion cylinder 36. The direction in which the central axis C of the combustion cylinder 36 curves is the radial direction of the rotor 8. That is, the central axis C of the combustion liner 36 exists within a plane PV (see FIG. 3) that extends in the radial and axial directions of the rotor 8 .

[0026] (Third Fuel Nozzle 70) Figure 3 is a schematic cross-sectional view of the combustion liner 36 according to one embodiment, showing a cross section taken along the line III-III in Figure 2. Figure 4 is a diagram for explaining a fuel supply pipe 80 for supplying fuel to the third fuel nozzle 70, and corresponds to a diagram in which the fuel supply pipe 80 is deployed in the circumferential direction of the combustion liner 36. The combustor 4 according to one embodiment includes a plurality of third fuel nozzles 70 provided on a side portion 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 portion of the combustion liner 36. The third fuel nozzles 70 are fixed to, for example, the transition piece 50.

[0027] Fuel is supplied to the third fuel nozzles 70 via third fuel ports 74 (see FIG. 2 ). In FIG. 2 , of the fuel supply pipes extending from the third fuel ports 74 to the respective third fuel nozzles 70, a fuel supply pipe 80 within the combustor casing 32 is indicated by a two-dot chain line.

[0028] As will be described later, the third fuel nozzle 70 according to one embodiment is configured to be able to inject into the combustion liner 36 a mixture M of fuel supplied from the third fuel port 74 via a fuel supply pipe 80 and compressed air in the combustor casing 32. When the mixture M is injected into the combustion liner 36 from the third fuel nozzle 70, the injected mixture M is combusted. By injecting the mixture M from the third fuel nozzle 70 into the combustion liner 36, it is possible to supply fuel to a secondary combustion zone in a transition portion 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.

[0029] In one embodiment of the combustor 4, the plurality of third fuel nozzles 70 include at least one first side fuel nozzle 71 that is arranged radially outside the rotor 8 when the combustion liner 36 is attached to the casing 20 that covers the outer periphery of the rotor 8 of the gas turbine 1, and at least one second side fuel nozzle 72 that is arranged radially inside the rotor 8 when the combustion liner 36 is attached to the casing 20.

[0030] 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.

[0031] In the combustor 4 according to one embodiment, the number of the at least one first side fuel nozzle 71 may be two, as shown in FIG. 3, or may be three or more.

[0032] In one embodiment of the combustor 4 , the at least one second side fuel nozzle 72 may be two, as shown in FIG. 3 , or may be three or more.

[0033] (Regarding the Fuel Supply Pipe 80) The gas turbine 1 according to one embodiment includes a fuel supply pipe 80 for supplying fuel to the third fuel nozzle 70. In the gas turbine 1 according to one embodiment, there is more space in a radially outer region of the rotor 8 relative to the combustor 4 than in a radially inner region of the rotor 8. Therefore, the fuel supply pipe 80 for supplying fuel to the third fuel nozzle 70 can be easily arranged by being disposed in a radially outer region of the rotor 8 relative to the combustion liner 36 and extending from the upstream side to the downstream side of the combustion liner 36. Therefore, in a downstream region of the fuel supply pipe 80 extending from the upstream side to the downstream side of the combustion liner 36 to supply fuel to the second side fuel nozzle 72, the fuel supply pipe 80 is disposed so as to extend along the outer peripheral surface of the rotor 8 from the radially outer region to the radially inner region of the rotor 8.

[0034] For example, as shown in FIG. 4 , a fuel supply pipe 80 according to one embodiment may include an axially extending portion 81 extending in the axial direction of the combustion tube 36 from the upstream side to the downstream side of the combustion tube 36 in a region radially outward of the rotor 8 relative to the combustion tube 36, and a circumferentially extending portion 82 extending from the axially extending portion 81 to one and the other circumferentially of the combustion tube 36. In the fuel supply pipe 80 according to one embodiment, the downstream end of the axially extending portion 81 is connected to a circumferential distribution portion 83. The upstream end of the circumferentially extending portion 82 extending to one circumferential side of the combustion tube 36 and the circumferentially extending portion 82 extending to the other circumferential side of the combustion tube 36 in the fuel flow direction are each connected to the circumferential distribution portion 83. Note that the circumferentially extending portion 82 may also extend in the axial direction of the combustion tube 36.

[0035] The circumferentially extending portion 82 extending on one circumferential side of the combustion tube 36 and the circumferentially extending portion 82 extending on the other circumferential side of the combustion tube 36 each branch into two fuel supply pipes 80 at a branch portion 84. One of the two fuel supply pipes 80 branched at the branch portion 84 is a first supply pipe 85 for supplying fuel to the first side fuel nozzle 71, and the other of the two fuel supply pipes 80 branched at the branch portion 84 is a second supply pipe 86 for supplying fuel to the second side fuel nozzle 72.

[0036] In the following description, the section from the inlet end (branch portion 84) of the first supply pipe 85 to the outlet end 155a of the fuel injection holes 155 (see FIG. 8 ) described later will be referred to as a first fuel supply system 101, and the section from the inlet end (branch portion 84) of the second supply pipe 86 to the outlet end 155a of the fuel injection holes 155 will be referred to as a second fuel supply system 102. The first fuel supply system 101 and the second fuel supply system 102 include fuel injection holes 155. In the fuel supply pipe 80 according to one embodiment, all of the fuel flowing into a given first fuel supply system 101 is supplied to a given first side fuel nozzle 71. That is, all of the fuel supplied to a given first side fuel nozzle 71 is supplied from a given first fuel supply system 101. Similarly, in the fuel supply pipe 80 according to one embodiment, all of the fuel flowing into a given second fuel supply system 102 is supplied to a given second side fuel nozzle 72. That is, all fuel supplied to one second side fuel nozzle 72 is supplied from one second fuel supply system 102 .

[0037] In the gas turbine 1 according to one embodiment, compressed air from the compressor 2 is supplied as combustion air to the combustor casing 32 in which the combustor 4 is disposed from a region relatively inside in the radial direction of the rotor 8. Therefore, the compressed air tends to flow more easily into the second side fuel nozzle 72 than into the first side fuel nozzle 71. Therefore, the ratio of fuel to air (F / A) in the mixture M injected from the third fuel nozzle 70 tends to be greater in the first side fuel nozzle 71 than in the second side fuel nozzle 72.

[0038] Furthermore, in the combustor 4 according to the embodiment, the second side fuel nozzles 72 are disposed at a position farther circumferentially around the combustion liner 36 from the circumferential distribution section 83 than the first side fuel nozzles 71. Therefore, the length of the second supply pipe 86 is longer than the length of the first supply pipe 85, and therefore the temperature of the fuel supplied to the second side fuel nozzles 72 is higher than the temperature of the fuel supplied to the first side fuel nozzles 71. Therefore, even if the volumetric flow rate of the fuel supplied to the first side fuel nozzles 71 is the same as the volumetric flow rate of the fuel supplied to the second side fuel nozzles 72, the mass flow rate of the fuel supplied to the first side fuel nozzles 71 is greater than the mass flow rate of the fuel supplied to the second side fuel nozzles 72. If the mass flow rate of the fuel supplied to the first side fuel nozzles 71 is greater than the mass flow rate of the fuel supplied to the second side fuel nozzles 72, the fuel-to-air ratio (F / A) in the mixture M injected from the third fuel nozzles 70 will be greater for the first side fuel nozzles 71 than for the second side fuel nozzles 72.

[0039] If the ratio of fuel to air (F / A) in the mixture M changes depending on the position of the third fuel nozzle 70, NO ｘ This may increase the amount of steroids produced or cause flashbacks.

[0040] Therefore, in the combustor 4 according to one embodiment, the effective area of ​​the first fuel supply system 101 is made smaller than the effective area of ​​the second fuel supply system 102. The effective area here is Cd×A, which is the actual cross-sectional area A of the first fuel supply system 101 and the second fuel supply system 102 multiplied by the flow coefficient Cd of the first fuel supply system 101 and the second fuel supply system 102. The flow coefficient Cd is a value that takes into account the lengths of the flow paths in the first fuel supply system 101 and the second fuel supply system 102.

[0041] In the combustor 4 according to the one embodiment, as described above, the effective area of ​​the first fuel supply system 101 is smaller than the effective area of ​​the second fuel supply system 102, and therefore the first flow rate Q1 of the fuel injected from the first side fuel nozzle 71 is smaller than the second flow rate Q2 of the fuel injected from the second side fuel nozzle 72.

[0042] Therefore, the combustor 4 according to the embodiment can reduce the difference between the fuel to air ratio (F / A) in the mixture M injected from the first side fuel nozzle 71 and the fuel to air ratio (F / A) in the mixture M injected from the second side fuel nozzle 72. ｘ This reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0043] Furthermore, according to the gas turbine 1 according to one embodiment, since the above-described combustor 4 is included, NO ｘ This reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0044] As will be described later, each of the third fuel nozzles 70 has at least one fuel injection hole 155. In order to make the effective area in the first fuel supply system 101 smaller than the effective area in the second fuel supply system 102, the diameter of the fuel injection holes 155 in the first side fuel nozzle 71 may be made smaller than the diameter of the fuel injection holes 155 in the second side fuel nozzle 72. That is, by making the diameter of the fuel injection holes 155 in the first side fuel nozzle 71 smaller than the diameter of the fuel injection holes 155 in the second side fuel nozzle 72, the total value ΣS1 of the areas S1 of all the fuel injection holes 155 in the first side fuel nozzle 71 may be made smaller than the total value ΣS2 of the areas S2 of all the fuel injection holes 155 in the second side fuel nozzle 72. This reduces the difference between the fuel to air ratio (F / A) in the mixture M injected from the first side fuel nozzle 71 and the fuel to air ratio (F / A) in the mixture M injected from the second side fuel nozzle 72, thereby reducing the NO ｘ This reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0045] Furthermore, in order to make the effective area of ​​the first fuel supply system 101 smaller than the effective area of ​​the second fuel supply system 102, the number of fuel injection holes 155 in the first side fuel nozzle 71 may be smaller than the number of fuel injection holes 155 in the second side fuel nozzle 72. This reduces the difference between the fuel to air ratio (F / A) in the mixture M injected from the first side fuel nozzle 71 and the fuel to air ratio (F / A) in the mixture M injected from the second side fuel nozzle 72, thereby reducing the NO ｘ This reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0046] 4, the first fuel supply system (first supply pipe 85) may have a restriction 90 for restricting the flow rate of fuel injected from the first side fuel nozzle 71. This reduces the difference between the fuel to air ratio (F / A) in the mixture M injected from the first side fuel nozzle 71 and the fuel to air ratio (F / A) in the mixture M injected from the second side fuel nozzle 72, thereby reducing the NO ｘ 4, the restrictor 90 is, for example, an orifice 91, but may be another type of restrictor such as a pipe nozzle instead of the orifice 91.

[0047] (Regarding the structure of the third fuel nozzle 70) Fig. 5 is a schematic plan view of the third fuel nozzle 70. Fig. 6 is a schematic cross-sectional view taken along the line VI-VI in Fig. 5. Fig. 7 is a schematic cross-sectional view taken along the line VII-VII in Fig. 6. Fig. 8 is a schematic enlarged view of the fuel supply unit 150. The third fuel nozzle 70 includes a substantially cylindrical nozzle body 125 having an outlet opening 141 formed therein that communicates with the interior of the combustion liner 36. The outlet opening 141 is an injection port for injecting the air-fuel mixture M toward the interior of the combustion liner 36.

[0048] In the following description, the direction in which the axis S of the nozzle body 125 extends may be referred to as the "nozzle axial direction." Furthermore, the circumferential direction and radial direction based on the axis S may be referred to as the "nozzle circumferential direction" and the "nozzle radial direction," respectively. The "inner side in the nozzle radial direction" is the side approaching the axis S, and the "outer side in the nozzle radial direction" is the side moving away from the axis S.

[0049] The nozzle body 125 includes a top plate portion 130 extending in a direction perpendicular to the nozzle axial direction, a plurality of fuel supply portions 150 erected from the top plate portion 130 toward the outlet opening 141 along the nozzle axial direction, and a circumferentially extending portion 180 connected to connection end portions 149 of each of the plurality of fuel supply portions 150. The connection end portions 149 are end portions of each fuel supply portion 150 (more specifically, each fuel body portion 151 described later) on the outlet opening 141 side.

[0050] The multiple fuel supply units 150 are arranged at intervals in the nozzle circumferential direction (see FIGS. 5 and 7 ), and two fuel supply units 150 adjacent to each other in the nozzle circumferential direction define an introduction flow path 159 (see FIG. 7 ) for introducing air supplied from the outside to the inside in the nozzle radial direction. The multiple introduction flow paths 159 are arranged at intervals in the nozzle circumferential direction. Each introduction flow path 159 extends radially, and the inlet of each introduction flow path 159 opens radially outward.

[0051] The circumferentially extending portion 180 extends in the nozzle circumferential direction so as to connect to each of the connection end portions 149. The circumferentially extending portion 180 has a first peripheral edge portion 181 extending in the nozzle circumferential direction. The top plate portion 130 has a second peripheral edge portion 134 that faces the first peripheral edge portion 181 in the nozzle axial direction. The first peripheral edge portion 181 and the second peripheral edge portion 134 define air inlets 129 for introducing air into each of the introduction channels 159 from the outside in the nozzle radial direction. The air inlets 129 have a bell-mouth shape in which the inner diameter of the air inlet 129 increases toward the outside in the nozzle radial direction.

[0052] 7 and 8, each of the plurality of fuel supply units 150 has a fuel body 151, a fuel chamber 153 formed inside the fuel body 151, and a fuel injection hole 155 (see FIG. 8) for guiding the fuel in the fuel chamber 153 to an introduction passage 159. The fuel supplied from the fuel injection hole 155 to the introduction passage 159 mixes with air P introduced by the introduction passage 159. As a result, an air-fuel mixture M containing fuel and air is generated.

[0053] 6, the nozzle body 125 further includes a main flow path forming portion 160 that forms a main flow path 169 for guiding the air-fuel mixture M along the nozzle axial direction to the outlet opening 141. The main flow path forming portion 160 is cylindrical in shape, the axis of which substantially coincides with the axis S, and the outlet opening 141 is formed at one end of the main flow path forming portion 160.

[0054] The nozzle body 125 further includes a pointed protrusion 170 that protrudes from the top plate portion 130 toward the outlet opening 141. The pointed protrusion 170 is disposed radially inward of the plurality of introduction channels 159 (see FIG. 7 ) and has a shape that tapers toward the outlet opening 141. In this example, the pointed protrusion 170 is integrally formed from the same material as the top plate portion 130. The pointed protrusion 170 has a guide side surface 172 that extends in the nozzle circumferential direction to surround the axis S, and the guide side surface 172 extends in a curved manner toward the outlet opening 141 as it moves radially inward of the nozzle.

[0055] The process by which the third fuel nozzle 70 generates the air-fuel mixture M will now be outlined. A portion of the compressed air (air) in the combustor casing 32 is introduced into each of the multiple inlet passages 159 from the radially outer side (arrow P). At the same time, fuel in the fuel chamber 153 is supplied from the fuel injection holes 155 to the inlet passages 159 (arrow Q), generating the air-fuel mixture M. The air-fuel mixture M, which is guided inward in the nozzle axial direction by each of the multiple inlet passages 159, is guided along the nozzle axial direction by the guide side surface 172 toward the outlet opening 141, and then passes through the main passage 169 and flows into the combustion liner 36.

[0056] (Fuel Supply Unit 150) The configuration of the fuel supply unit 150 will be described in detail with reference to FIG.

[0057] 5 and 6 further includes a fuel introduction hole 131 (see FIG. 5). There is one fuel introduction hole 131, and a fuel supply passage (not shown) extending in the nozzle circumferential direction is formed inside the top plate 130. The fuel introduction hole 131 is connected to the circumferentially extending portion 82 of the fuel supply pipe 80, i.e., the downstream end of either the first supply pipe 85 or the second supply pipe 86.

[0058] 8, a fuel chamber 153 is formed inside the fuel body 151 of each fuel supply unit 150. Fuel supplied from a fuel supply passage (not shown) inside the top plate 130 flows into each fuel chamber 153, and the fuel inside the fuel chamber 153 is supplied to the introduction passage 159 from the fuel injection holes 155 described above.

[0059] As shown in FIG. 8, in each of the plurality of fuel supply units 150, a plurality of fuel injection holes 155 are arranged on each of both end surfaces of the fuel body 151 in the nozzle circumferential direction.

[0060] 8, each of the fuel injection holes 155 is configured to supply fuel to the introduction passage 159 in a direction perpendicular to the nozzle radial direction (arrow T). That is, each fuel injection hole 155 opens in a direction perpendicular to the nozzle radial direction. More specifically, the angle of the center line (not shown) of each fuel injection hole 155 with respect to the nozzle radial direction is equal to or greater than 85 degrees and equal to or less than 95 degrees.

[0061] Furthermore, the fuel body 151 of each fuel supply unit 150 has a streamlined shape extending along the nozzle radial direction. More specifically, the radius of curvature of the outer end 157 of the fuel body 151 in the nozzle radial direction is larger than the radius of curvature of the inner end 154 of the fuel body 151. Furthermore, in each fuel supply unit 150, a center line Z connecting points at equal nozzle circumferential distances from both end faces of the fuel body 151 in the nozzle circumferential direction is a straight line extending along the nozzle radial direction. The acute angle formed by the center line Z and the nozzle radial direction is 10 degrees or less, and more preferably, the center line Z is parallel to the nozzle radial direction. Note that if the fuel body 151 is considered to be a blade (stator vane), the center line Z corresponds to a camber line.

[0062] In the combustor 4 according to one embodiment, each of the plurality of third fuel nozzles 70 includes at least one upstream fuel injection hole 155U disposed upstream of the combustion liner 36 and at least one downstream fuel injection hole 155D disposed downstream of the at least one upstream fuel injection hole 155U in the combustion liner 36. For example, in the example shown in Fig. 7 , in each of the third fuel nozzles 70, the fuel injection holes 155 provided in two fuel bodies 151 located relatively upstream of the combustion liner 36 are referred to as the upstream fuel injection holes 155U, and the fuel injection holes 155 provided in the other fuel bodies 151 are referred to as the downstream fuel injection holes 155D.

[0063] Within the combustion liner 36, the combustion gas FG generated by the combustion of the fuel injected from the first fuel nozzle 40 and the second fuel nozzle 46, which are disposed upstream of the third fuel nozzle 70, merges with the air-fuel mixture M injected from the third fuel nozzle 70. As a result, the static pressure within the combustion liner 36 upstream of the third fuel nozzle 70 is higher than the static pressure within the combustion liner 36 downstream of the third fuel nozzle 70. Furthermore, the combustion gas FG generated by the combustion of the fuel injected from the first fuel nozzle 40 and the second fuel nozzle 46, which are disposed upstream of the combustion liner 36, bends the air-fuel mixture M injected from the third fuel nozzle 70 toward the downstream side of the combustion liner 36. As a result, the injection velocity of the compressed air injected from the third fuel nozzle 70 into the combustion liner 36 decreases upstream of the combustion liner 36, which may result in flashback in the region where the injection velocity is reduced. This issue is a problem that the combustor 4 faces regardless of whether the third fuel nozzle 70 is the first side fuel nozzle 71 or the second side fuel nozzle 72, i.e., regardless of the circumferential position of the third fuel nozzle 70 around the combustion liner 36.

[0064] Therefore, in the combustor 4 according to the embodiment, the effective area of ​​the upstream fuel supply system 100U that supplies fuel to the upstream fuel injection holes 155U is smaller than the effective area of ​​the downstream fuel supply system 100D that supplies fuel to the downstream fuel injection holes 155D. Here, the upstream fuel supply system 100U extends from an inlet (not shown) of the fuel chamber 153 in the fuel body 151 where the upstream fuel injection holes 155U are formed to an end 155a on the outlet side of the upstream fuel injection holes 155U and includes the upstream fuel injection holes 155U. The downstream fuel supply system 100D extends from an inlet (not shown) of the fuel chamber 153 in the fuel body 151 where the downstream fuel injection holes 155D are formed to an end 155a on the outlet side of the downstream fuel injection holes 155D and includes the downstream fuel injection holes 155D. This makes it difficult for the fuel-to-air ratio (F / A) to become large in the region where the injection velocity is reduced, thereby reducing the possibility of flashback occurring in the region.

[0065] Furthermore, according to the gas turbine 1 according to one embodiment, since the above-described combustor 4 is included, NO ｘ This reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0066] In order to make the effective area of ​​the upstream fuel supply system 100U smaller than the effective area of ​​the downstream fuel supply system 100D, the diameter of the upstream fuel injection holes 155U may be made smaller than the diameter of the downstream fuel injection holes 155D. That is, by making the diameter of the upstream fuel injection holes 155U smaller than the diameter of the downstream fuel injection holes 155D, the total value ΣSu of the areas Su of all the upstream fuel injection holes 155U may be made smaller than the total value ΣSd of the areas Sd of all the downstream fuel injection holes 155D. This makes it difficult for the fuel-to-air ratio (F / A) to become large in the region where the injection velocity is reduced, thereby reducing the possibility of flashback occurring in that region.

[0067] In order to make the effective area of ​​upstream fuel supply system 100U smaller than the effective area of ​​downstream fuel supply system 100D, the number of upstream fuel injection holes 155U may be smaller than the number of downstream fuel injection holes 155D. This makes it difficult for the fuel to air ratio (F / A) to become large in the region where the injection velocity is reduced, thereby reducing the possibility of flashback occurring in that region.

[0068] The present disclosure is not limited to the above-described embodiments, and includes modifications of the above-described embodiments and appropriate combinations of these modifications. For example, the above-described embodiments for making the effective area of ​​the first fuel supply system 101 smaller than the effective area of ​​the second fuel supply system 102, such as making the diameter of the fuel injection holes 155 different between the first side fuel nozzle 71 and the second side fuel nozzle 72, making the number of fuel injection holes 155 different between the first side fuel nozzle 71 and the second side fuel nozzle 72, and providing the throttle 90 in the first supply pipe 85, may be implemented in appropriate combinations. Similarly, for example, the above-mentioned embodiment for making the effective area in the upstream fuel supply system 100U smaller than the effective area in the downstream fuel supply system 100D, in which the hole diameters of the upstream fuel injection holes 155U and the downstream fuel injection holes 155D are different, and the number of the upstream fuel injection holes 155U and the number of the downstream fuel injection holes 155D are different, may be implemented in combination.

[0069] The above-mentioned embodiments for making the effective area in the first fuel supply system 101 smaller than the effective area in the second fuel supply system 102 and the embodiments for making the effective area in the upstream fuel supply system 100U smaller than the effective area in the downstream fuel supply system 100D may be implemented in appropriate combination.

[0070] The content described in each of the above embodiments can be understood, for example, as follows. (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 sides of the combustion liner 36. The plurality of side fuel nozzles (third fuel nozzles 70) include at least one first side fuel nozzle 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 at least one second side fuel nozzle 72 disposed radially inward of the rotor 8 when the combustion liner 36 is attached to the casing 20. An effective area of ​​a first fuel supply system 101 that supplies fuel to the first side fuel nozzle 71 is smaller than an effective area of ​​a second fuel supply system 102 that supplies fuel to the second side fuel nozzle 72.

[0071] According to the configuration (1) above, the effective area of ​​the first fuel supply system 101 is smaller than the effective area of ​​the second fuel supply system 102, so it is possible to reduce the difference between the fuel to air ratio (F / A) in the mixture M injected from the first side fuel nozzle 71 and the fuel to air ratio (F / A) in the mixture M injected from the second side fuel nozzle 72. ｘ This reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0072] (2) In some embodiments, in the configuration described in (1) above, each of the multiple side fuel nozzles (third fuel nozzle 70) may have at least one fuel injection hole 155. The sum ΣS1 of the areas S1 of all the fuel injection holes 155 in the first side fuel nozzle 71 may be smaller than the sum ΣS2 of the areas S2 of all the fuel injection holes 155 in the second side fuel nozzle 72.

[0073] According to the configuration (2) above, the effective area of ​​the first fuel supply system 101 can be made smaller than the effective area of ​​the second fuel supply system 102, so that the difference between the fuel to air ratio (F / A) in the mixture M injected from the first side fuel nozzle 71 and the fuel to air ratio (F / A) in the mixture M injected from the second side fuel nozzle 72 can be reduced.ｘ This reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0074] (3) In some embodiments, in the configuration described in (1) or (2) above, each of the multiple side fuel nozzles (third fuel nozzle 70) may have at least one fuel injection hole 155. The number of fuel injection holes 155 in the first side fuel nozzle 71 may be fewer than the number of fuel injection holes 155 in the second side fuel nozzle 72.

[0075] According to the configuration (3) above, the effective area of ​​the first fuel supply system 101 can be made smaller than the effective area of ​​the second fuel supply system 102, so that the difference between the fuel to air ratio (F / A) in the mixture M injected from the first side fuel nozzle 71 and the fuel to air ratio (F / A) in the mixture M injected from the second side fuel nozzle 72 can be reduced. ｘ This reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0076] (4) In some embodiments, in any of the configurations (1) to (3) above, the first fuel supply system (first supply pipe 85) may have a restriction 90 for restricting the flow rate of fuel injected from the first side fuel nozzle 71.

[0077] According to the configuration (4) above, the effective area of ​​the first fuel supply system 101 can be made smaller than the effective area of ​​the second fuel supply system 102, so that the difference between the fuel to air ratio (F / A) in the mixture M injected from the first side fuel nozzle 71 and the fuel to air ratio (F / A) in the mixture M injected from the second side fuel nozzle 72 can be reduced. ｘ This reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0078] (5) In some embodiments, in any of the configurations (1) to (4) above, each of the multiple side fuel nozzles (third fuel nozzle 70) may have at least one upstream fuel injection hole 155U located upstream of the combustion liner 36 and at least one downstream fuel injection hole 155D located downstream of the at least one upstream fuel injection hole 155U in the combustion liner 36. The effective area of ​​the upstream fuel supply system 100U that supplies fuel to the upstream fuel injection hole 155U may be smaller than the effective area of ​​the downstream fuel supply system 100D that supplies fuel to the downstream fuel injection hole 155D.

[0079] Within the combustion liner 36, combustion gas FG generated by combustion of fuel injected from the fuel nozzles (first fuel nozzle 40 and second fuel nozzle 46) arranged upstream of the combustion liner 36 relative to the side fuel nozzle (third fuel nozzle 70) merges with the air-fuel mixture M injected from the side fuel nozzle (third fuel nozzle 70). As a result, the static pressure within the combustion liner 36 upstream of the side fuel nozzle (third fuel nozzle 70) is higher than the static pressure within the combustion liner 36 downstream of the side fuel nozzle (third fuel nozzle 70). Furthermore, the combustion gas FG generated by combustion of fuel injected from the fuel nozzles (first fuel nozzle 40 and second fuel nozzle 46) arranged upstream of the combustion liner 36 relative to the side fuel nozzle (third fuel nozzle 70) bends the air-fuel mixture M injected from the side fuel nozzle (third fuel nozzle 70) toward the downstream side of the combustion liner 36. As a result, the velocity of the compressed air injected from the side fuel nozzle (third fuel nozzle 70) into the combustion chamber 36 decreases upstream of the combustion chamber 36, and flashback may occur in the area where the velocity of the compressed air decreases.

[0080] According to the configuration of (5) above, the effective area of ​​upstream fuel supply system 100U is smaller than the effective area of ​​downstream fuel supply system 100D that supplies fuel to downstream fuel injection holes 155D, so the fuel to air ratio (F / A) is less likely to become large in the region where the injection velocity is reduced, thereby reducing the possibility of flashback occurring in the region where the injection velocity is reduced.

[0081] (6) A gas turbine combustor 4 according to at least one embodiment of the present disclosure includes a combustion liner 36 and at least one side fuel nozzle (third fuel nozzle 70) provided on a side of the combustion liner 36. The at least one side fuel nozzle (third fuel nozzle 70) includes at least one upstream fuel injection hole 155U arranged on the upstream side of the combustion liner 36 and at least one downstream fuel injection hole 155D arranged on a downstream side of the combustion liner 36 with respect to the at least one upstream fuel injection hole 155U. An effective area of ​​an upstream fuel supply system 100U that supplies fuel to the upstream fuel injection hole 155U is smaller than an effective area of ​​a downstream fuel supply system 100D that supplies fuel to the downstream fuel injection hole 155D.

[0082] As described above, the compressed air injected from the side fuel nozzle (third fuel nozzle 70) is ejected into the combustion liner 36 at a reduced injection velocity upstream of the combustion liner 36. As a result, flashback may occur in the region where the injection velocity is reduced.

[0083] According to the configuration of (6) above, the effective area of ​​upstream fuel supply system 100U is smaller than the effective area of ​​downstream fuel supply system 100D, so the fuel to air ratio (F / A) is less likely to become large in the region where the injection velocity is reduced, thereby reducing the possibility of flashback occurring in the region where the injection velocity is reduced.

[0084] (7) In some embodiments, in the configuration of (6) above, the sum ΣSu of the areas Su of all the upstream fuel injection holes 155U may be smaller than the sum ΣSd of the areas Sd of all the downstream fuel injection holes 155D.

[0085] According to the configuration of (7) above, the effective area of ​​upstream fuel supply system 100U can be made smaller than the effective area of ​​downstream fuel supply system 100D, so that the fuel to air ratio (F / A) in the region where the injection velocity is reduced is less likely to become large, thereby reducing the possibility of flashback occurring in the region where the injection velocity is reduced.

[0086] (8) In some embodiments, in the configuration described in (6) or (7) above, the number of upstream fuel injection holes 155U may be less than the number of downstream fuel injection holes 155D.

[0087] According to the configuration of (8) above, the effective area of ​​upstream fuel supply system 100U can be made smaller than the effective area of ​​downstream fuel supply system 100D, so that the fuel to air ratio (F / A) in the region where the injection velocity is reduced is less likely to become large, thereby reducing the possibility of flashback occurring in the region where the injection velocity is reduced.

[0088] (9) 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 one of the configurations described above in (1) to (5); and a turbine 6 that is rotationally driven by combustion gas generated by the gas turbine combustor 4.

[0089] According to the above configuration (9), NO ｘ This reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0090] (10) 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 (6) to (8); and a turbine 6 that is rotationally driven by combustion gas generated by the gas turbine combustor 4.

[0091] According to the above configuration (10), NO ｘ This reduces the amount of flashbacks and the likelihood of flashbacks occurring.

[0092] REFERENCE SIGNS LIST 1 Gas turbine 2 Compressor 4 Gas turbine combustor (combustor) 8 Rotor 36 Combustion liner (combustor liner) 70 Third fuel nozzle 100U Upstream fuel supply system 100D Downstream fuel supply system 101 First fuel supply system 102 Second fuel supply system 155 Fuel injection hole 155U Upstream fuel injection hole 155D Downstream fuel injection hole

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 at least one first side fuel nozzle 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 at least one second side fuel nozzle arranged radially inside the rotor when the combustion liner is attached to the casing, wherein the effective area of ​​a first fuel supply system that supplies fuel to the first side fuel nozzle is smaller than the effective area of ​​a second fuel supply system that supplies fuel to the second side fuel nozzle.

2. The gas turbine combustor according to claim 1, wherein each of the plurality of side fuel nozzles has at least one fuel injection hole, and a total value of areas of all of the fuel injection holes in the first side fuel nozzle is smaller than a total value of areas of all of the fuel injection holes in the second side fuel nozzle.

3. The gas turbine combustor according to claim 1 or 2, wherein each of the plurality of side fuel nozzles has at least one fuel injection hole, and the number of the fuel injection holes in the first side fuel nozzle is smaller than the number of the fuel injection holes in the second side fuel nozzle.

4. A gas turbine combustor according to claim 1 or 2, wherein the first fuel supply system has a restriction for restricting the flow rate of the fuel injected from the first side fuel nozzle.

5. The gas turbine combustor according to claim 1 or 2, wherein each of the plurality of side fuel nozzles includes at least one upstream fuel injection hole arranged upstream of the combustion liner, and at least one downstream fuel injection hole arranged downstream of the combustion liner relative to the at least one upstream fuel injection hole, and wherein an effective area of ​​an upstream fuel supply system that supplies the fuel to the upstream fuel injection hole is smaller than an effective area of ​​a downstream fuel supply system that supplies the fuel to the downstream fuel injection hole.

6. A gas turbine combustor comprising: a combustion liner; and at least one side fuel nozzle provided on a side of the combustion liner, wherein the at least one side fuel nozzle has at least one upstream fuel injection hole arranged upstream of the combustion liner, and at least one downstream fuel injection hole arranged downstream of the combustion liner relative to the at least one upstream fuel injection hole, and wherein an effective area of ​​an upstream fuel supply system that supplies fuel to the upstream fuel injection hole is smaller than an effective area of ​​a downstream fuel supply system that supplies the fuel to the downstream fuel injection hole.

7. A gas turbine combustor according to claim 6, wherein a total value of the areas of all of said upstream fuel injection holes is smaller than a total value of the areas of all of said downstream fuel injection holes.

8. A gas turbine combustor according to claim 6 or 7, wherein the number of the upstream fuel injection holes is smaller than the number of the downstream fuel injection holes.

9. A gas turbine comprising: a compressor that generates compressed air; the gas turbine combustor according to claim 1 or 2; and a turbine that is rotationally driven by combustion gas generated by the gas turbine combustor.

10. A gas turbine comprising: a compressor that generates compressed air; the gas turbine combustor according to claim 6 or 7; and a turbine that is rotationally driven by combustion gas generated by the gas turbine combustor.

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