Gas turbine combustor

Abstract

To provide a gas turbine combustor capable of suppressing flashback.SOLUTION: A gas turbine combustor includes a combustion cylinder defining a combustion chamber, a combustor for supplying fuel to the combustion chamber, and a two-stage combustion nozzle arranged in a downstream side of a flow direction of combustion gas in the combustion chamber with respect to the combustor. The two-stage combustion nozzle includes a nozzle flow passage forming part which forms a nozzle flow passage having a nozzle injection port formed on an inner peripheral surface of the combustion cylinder, and a seal air flow passage forming part which forms a seal air flow passage having a seal air injection port at least a part of which is arranged upstream of the flow direction of the combustion gas with respect to a nozzle center axis which is a center line of the two-stage combustion nozzle.SELECTED DRAWING: Figure 3A

Description

[[Technical Field]]

[0001] The present disclosure relates to a gas turbine combustor employing a two-stage combustion method. [[Background Art]]

[0002] Conventionally, gas turbine combustors incorporated into gas turbines are known. For example, a gas turbine combustor adopting the two-stage combustion method disclosed in Patent Document 1 includes a fuel injector as a second-stage nozzle. The fuel injector includes a premixed gas injection port that injects premixed gas, and a cooling air injection port that injects compressed air serving as cooling air. Since this fuel injector has a configuration that protrudes greatly into the combustion chamber of the combustion cylinder, a large amount of heat is transferred from the combustion gas generated in the combustion cylinder to the fuel injector. The compressed air serving as cooling air functions to suppress an excessive temperature rise of the fuel injector. [[Prior Art Literature]] [[Patent Literature]]

[0003] [[Patent Document 1]] Japanese Unexamined Patent Publication No. 2015-200493 [[Summary of the Invention]] [[Problem to be Solved by the Invention]]

[0004] According to the findings of the inventors, when a configuration in which the premixed gas injection port is disposed near the inner peripheral surface of the combustion cylinder is applied to the above-described fuel injector, there is a risk that horseshoe vortices of combustion gas generated on the inner peripheral surface flow into the premixed gas injection port. In this case, flashback, in which a flame is generated inside the fuel injector, may occur, and the fuel injector may be burned out.

[0005] An object of the present disclosure is to provide a gas turbine combustor capable of suppressing flashback. [[Means for Solving the Problem]]

[0006] A gas turbine combustor according to at least one embodiment of the present disclosure is A combustion cylinder that defines the combustion chamber, A combustor for supplying fuel to the combustion chamber, With respect to the combustor, a two-stage combustion nozzle is positioned downstream in the direction of combustion gas flow within the combustion chamber. A gas turbine combustor equipped with, The aforementioned two-stage combustion nozzle is A nozzle channel forming section that forms a nozzle channel having a nozzle injection port formed on the inner circumferential surface of the combustion cylinder, A seal air passage forming section that forms a seal air passage having a seal air injection port which is positioned at least partially upstream of the nozzle central axis, which is the center line of the two-stage combustion nozzle, in the flow direction of the combustion gas, Includes. [Effects of the Invention]

[0007] According to this disclosure, a gas turbine combustor capable of suppressing flashback can be provided. [Brief explanation of the drawing]

[0008] [Figure 1] A schematic diagram showing a gas turbine according to one embodiment. [Figure 2] A schematic diagram of a gas turbine combustor according to one embodiment. [Figure 3A] A schematic diagram of a two-stage combustion nozzle according to the first embodiment. [Figure 3B] A schematic diagram of a two-stage combustion nozzle according to the second embodiment. [Figure 3C] A schematic diagram of a two-stage combustion nozzle according to the third embodiment. [Figure 4A] A schematic diagram showing a two-stage combustion nozzle to which the configuration described in the first example is applied. [Figure 4B] A schematic diagram showing another two-stage combustion nozzle to which the configuration described in the first example is applied. [Figure 4C] A schematic diagram showing yet another two-stage combustion nozzle to which the configuration described in the first example is applied. [Figure 5A]Schematic diagram showing a two-stage combustion nozzle to which the configuration according to the second example is applied. [Figure 5B] Schematic diagram showing the two-stage combustion nozzle of Fig. 5A as viewed in the axial direction of the nozzle central axis C. [Figure 5C] Cross-sectional view of the partition wall taken along the line A-A in Fig. 5A. [Figure 6A] Schematic diagram showing a two-stage combustion nozzle to which the configuration according to the third example is applied. [Figure 6B] Schematic diagram showing another two-stage combustion nozzle to which the configuration according to the third example is applied. [Figure 7A] Schematic diagram showing a two-stage combustion nozzle to which the configuration according to the fourth example is applied (with the inner flow path wall omitted). [Figure 7B] Schematic diagram showing a two-stage combustion nozzle to which the configuration according to the fourth example is applied (with one end of the nozzle flow path wall partially omitted). [Figure 8A] Schematic diagram showing a two-stage combustion nozzle to which the configuration according to the fifth example is applied. [Figure 8B] Schematic diagram showing an example of a more specific configuration of the two-stage combustion nozzle of Fig. 8A. [Figure 8C] Schematic diagram showing another example of a more specific configuration of the two-stage combustion nozzle of Fig. 8B. [Figure 9] Schematic diagram showing a two-stage combustion nozzle to which the configuration according to the sixth example is applied. MODE FOR CARRYING OUT THE INVENTION

[0009] Hereinafter, several embodiments of the present disclosure will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, and the like of the components described in the embodiments or shown in the drawings are not intended to limit the scope of the present disclosure thereto, and are merely illustrative examples. For example, expressions representing relative or absolute arrangements such as "in a certain direction", "along a certain direction", "parallel", "perpendicular", "central", "concentric", or "coaxial" not only strictly represent such arrangements, but also represent a state of relative displacement within a tolerance, or at an angle or distance that allows the same function to be obtained. For example, expressions indicating that things are equal, such as "identical", "equal" and "homogeneous", shall not only mean strictly equal states, but also mean states with tolerances or differences to an extent that the same function can be obtained. For example, expressions describing shapes such as quadrilateral shape and cylindrical shape shall not only mean quadrilateral shape and cylindrical shape in a strictly geometric sense, but also mean shapes including uneven portions, chamfered portions and the like within a range where the same effect can be obtained. On the other hand, the expressions "comprising", "including" or "having" one component is not an exclusive expression excluding the presence of other components. Note that the same reference numerals are given to the same configurations, and the description thereof may be omitted.

[0010] <1. Overview of Gas Turbine 100> Figure 1 is a schematic diagram showing a gas turbine 100 according to one embodiment of the present disclosure. The gas turbine 100 comprises a compressor 2 for generating compressed air, a gas turbine combustor 4 for generating combustion gas using compressed air and fuel, and a turbine 6 configured to be driven by the combustion gas discharged from the gas turbine combustor 4. In the gas turbine 100, which may be, for example, a single-shaft gas turbine, the compressor 2 and the turbine 6 are connected by a rotating shaft 9, and a generator 5 is further connected to the rotating shaft 9.

[0011] In the gas turbine combustor 4, a mixed gas including compressed air delivered from the compressor 2 and fuel supplied from a fuel supply unit (not shown) is combusted, and combustion gas as a working fluid for driving the turbine 6 is generated. The turbine 6 is driven by the combustion gas flowing into the turbine 6, and the generator 5 generates power as the rotating shaft 9 rotates. Examples of the fuel supplied to the gas turbine combustor 4 include hydrogen, methane, light oil, heavy oil, jet fuel, natural gas, gasified coal, or any combination of two or more thereof. Hereinafter, the compressed air sent from the compressor 2 to the gas turbine combustor 4 may be referred to as "combustion air".

[0012] <2. Overview of Gas Turbine Combustor 4> Figure 2 is a schematic diagram of a gas turbine combustor 4 according to one embodiment of the present disclosure. The gas turbine combustor 4 comprises a combustion cylinder 40 that defines a combustion chamber 47, a combustor 8 provided at one end of the combustion cylinder 40, and a two-stage combustion nozzle 20 provided on the cylindrical wall of the combustion cylinder 40. The combustor 8 is configured to inject fuel and combustion air along the axial direction of the combustion cylinder 40. The mixed gas produced by the mixing of fuel and combustion air injected from the combustor 8 ignites, and a flame is generated inside the combustion chamber 47. The combustion gas, which is the main high-temperature gas generated in the combustion chamber 47, flows downstream (to the right in the example of Figure 2). Hereinafter, the direction of combustion gas flow in the combustion chamber 47 may be referred to as the "combustion gas flow direction." The two-stage combustion nozzle 20 is positioned downstream of the combustor 8 in the combustion gas flow direction and is configured to inject fuel and combustion air along the radial direction of the combustion cylinder 40. Fuel and combustion air injected from the two-stage combustion nozzle 20 are injected into the combustion chamber 47, causing a second stage of combustion to occur within the combustion chamber 47. In this example, multiple two-stage combustion nozzles 20 are arranged at equal intervals along the circumferential direction of the combustion cylinder 40.

[0013] An example of the configuration of the combustor 8 is disclosed in Japanese Patent Publication No. 2013-096303. A detailed explanation of its configuration is omitted in this paper, but the outline is as follows. The combustor 8 includes a pilot burner positioned at the center of the combustion cylinder 40 and a plurality of main burners arranged at equal intervals surrounding the pilot burner. The pilot burner has a pilot nozzle for supplying pilot fuel and a cylindrical member provided to surround the tip of the pilot nozzle. The cylindrical member forms a pilot air passage between itself and the pilot nozzle, and combustion air (pilot air) flows through the pilot air passage. The main burner includes a main nozzle for supplying main fuel and a main air passage formed around the main nozzle for supplying main air. The main fuel injected from the main nozzle is mixed with the main air supplied through the main air passage to become a premixed gas.

[0014] <3. Overview of the 2-stage combustion nozzle 20> Figures 3A, 3B, and 3C are schematic diagrams showing the two-stage combustion nozzle 21(20) according to the first embodiment, the two-stage combustion nozzle 22(20) according to the second embodiment, and the two-stage combustion nozzle 23(20) according to the third embodiment, respectively. The fluid injected from the two-stage combustion nozzle 20 includes a premixed gas containing fuel and combustion air, and sealing air (details will be described later), which is part of the compressed air (combustion air) supplied from the compressor 2. The premixed gas and sealing air may be mixed in the combustion chamber 47, mixed inside the two-stage combustion nozzle 20, or mixed in both.

[0015] The two-stage combustion nozzles 21-23 (20) include main body sections 11-13 installed in the combustion cylinder 40 and nozzle flow path forming sections 31-33 provided in the main body sections 11-13. The nozzle flow path forming sections 31-33 form nozzle flow paths 121-123 having nozzle injection ports 201-203. Premixed gas and sealing air flow through the nozzle flow paths 121-123, and the nozzle injection ports 201-203 inject the premixed gas and sealing air. Hereinafter, the central axis of the two-stage combustion nozzle 20 may be referred to as the "nozzle central axis C," the circumferential direction of the nozzle central axis C may be referred to as the "nozzle circumferential direction," and the radial direction of the nozzle central axis C may be referred to as the "nozzle radial direction." The nozzle central axis C is also the center line of the main body sections 11-13. The radial direction of the combustion cylinder 40 may also be referred to as the "combustion cylinder radial direction." The nozzle central axis C extends in the combustion cylinder radial direction.

[0016] The nozzle flow path forming sections 31-33 have nozzle flow path walls 71-73 that are connected to the inner circumferential surface 48 of the combustion cylinder 40. The nozzle flow path walls 71-73 include portions that extend along the diameter direction of the combustion cylinder, and these portions are connected to the inner circumferential surface 48. The nozzle flow path wall ends 711-713, which are one end of the nozzle flow path walls 71-73 in the diameter direction of the combustion cylinder, form the nozzle injection ports 201-203.

[0017] The nozzle inlet openings 201-203 are formed on the inner circumferential surface 48 of the combustion cylinder 40. In this paper, "nozzle inlet openings 201-203 formed on the inner circumferential surface 48" is a concept that includes nozzle inlet openings 201-203 that are located at the same radial position as the inner circumferential surface 48 in the radial direction of the combustion cylinder. Furthermore, the term "nozzle inlet 201-203 formed on the inner circumferential surface 48" is a concept that includes nozzle inlet 201-203 located outside the inner circumferential surface 48 in the combustion cylinder diameter direction. In this case, the distance from the nozzle inlet 201-203 to the inner circumferential surface 48 in the combustion cylinder diameter direction is 20% or less of the diameter of the circularly formed nozzle inlet 201-203. Furthermore, the term "nozzle inlet 201-203 formed on the inner circumferential surface 48" is a concept that includes nozzle inlet 201-203 positioned inward from the inner circumferential surface 48 in the combustion cylinder diameter direction. In this case, the distance from the nozzle inlet 201-203 to the inner circumferential surface 48 in the combustion cylinder diameter direction is 5% or less of the diameter of the circularly formed nozzle inlet 201-203.

[0018] The two-stage combustion nozzles 21-23 further include seal air passage forming sections 51-53 provided in the main body sections 11-13. The seal air passage forming sections 51-53 form seal air passages 141-143 having seal air injection ports 41-43. Seal air flows through the seal air passages 141-143.

[0019] The seal air passages 141 and 142 shown in Figures 3A and 3B are passages included in the nozzle passages 121 and 122. The specific configuration is as follows: The seal air passage forming sections 51 and 52 include inner passage walls 81 and 82 located inside the nozzle passage wall 71. Furthermore, the aforementioned nozzle passage walls 71 and 72 are also components of the seal air passage forming sections 51 and 52, and the seal air passages 141 and 142 are formed between the nozzle passage walls 71 and 72 and the inner passage walls 81 and 82.

[0020] The inner flow channel wall 81, illustrated in Figure 3A, extends along the diameter of the combustion cylinder, surrounding the nozzle central axis C. Inside the inner flow channel wall 81, a premixed gas flow channel 91 is formed through which the premixed gas flows. One end of the inner flow channel wall 81, the inner flow channel wall end 811, forms a premixed gas injection port 813 for injecting the premixed gas. The premixed gas flow channel 91 constitutes a part of the nozzle flow channel 121. The inner flow channel wall 82, illustrated in Figure 3B, extends along the diameter direction of the combustion cylinder. A premixed gas flow channel 92 is formed between the inner flow channel wall 82 and the nozzle flow channel wall 72, through which the premixed gas flows. The premixed gas flow channel 92 constitutes a part of the nozzle flow channel 122. One end of the inner flow channel wall 82, the inner flow channel wall end 812, and the aforementioned nozzle flow channel wall end 712 form a premixed gas injection port 823 for injecting the premixed gas. The premixed gas injectors 813 and 823 illustrated in Figures 3A and 3B constitute part of the nozzle injectors 201 and 202. With this configuration, the premixed gas and sealing air are mixed in the combustion chamber 47 after being injected from the two-stage combustion nozzle 20. However, this disclosure is not limited thereto, and for example, in the two-stage combustion nozzle 21, a configuration may be adopted in which the premixed gas and sealing air are mixed before passing through the nozzle injector 201 (details will be described later). The same applies to the two-stage combustion nozzle 22. Note that the premixed gas injectors 813 and 823 are examples of fuel injectors for injecting fuel.

[0021] The premixed gas flow paths 91 and 92 have a plurality of air supply ports 95 located on the opposite side of the premixed gas injection ports 813 and 823, and a plurality of fuel supply ports 96 located between the premixed gas injection ports 813 and 823 and the plurality of air supply ports 95. The premixed gas is generated when the combustion air supplied from the plurality of air supply ports 95 and the fuel supplied from the plurality of fuel supply ports 96 are mixed. The premixed gas flow paths 91 and 92 are examples of fuel flow paths through which fuel flows.

[0022] The seal air passage 143 shown in Figure 3C is a passage located on the opposite side of the nozzle central axis C from the nozzle passage wall 73, and is a separate passage from the nozzle passage 123. The seal air injection port 43 opens in the nozzle passage wall 73. With this configuration, the premixed gas and seal air are mixed inside the two-stage combustion nozzle 20 before injection. In this example, multiple seal air injection ports 43 are arranged at equal intervals in the circumferential direction of the nozzle. The seal air injection ports 43 are configured to inject seal air toward the nozzle injection port 203. Preferably, the acute angle θ between the center line P of the outlet side flow path 143A, which includes the seal air injection ports 43, and the nozzle central axis C is less than 30 degrees.

[0023] In the nozzle flow path 123 illustrated in Figure 3C, multiple air supply ports 95, similar to those in Figures 3A and 3B, are provided on the opposite side of the nozzle injection port 203 from the multiple seal air injection ports 43, and multiple fuel supply ports 96, similar to those in Figures 3A and 3B, are provided between the multiple seal air injection ports 43 and the multiple air supply ports 95. The premixed gas generated by mixing combustion air and fuel is mixed with at least a portion of the seal air supplied from the multiple air supply ports 95 before being injected from the nozzle injection port 203.

[0024] At least a portion of each of the seal air inlets 41 to 43 shown in Figures 3A to 3C is positioned upstream of the nozzle central axis C in the direction of combustion gas flow. More specifically, the seal air inlets 41 and 43 are positioned upstream and downstream of the nozzle central axis C in the direction of combustion gas flow, while the seal air inlet 42 is positioned only upstream of the nozzle central axis C in the direction of combustion gas flow.

[0025] According to the inventors' findings, as the combustion gas, which is the main high-temperature gas generated inside the combustion chamber 47, flows downstream, a horseshoe vortex S of the combustion gas is formed on the inner circumferential surface 48. If the horseshoe vortex S flows into the nozzle inlet 201-203, there is a risk of flashback, which is ignition inside the two-stage combustion nozzle 20. In this regard, at least a portion of the seal air inlet 41-43 is positioned upstream of the nozzle central axis C in the direction of combustion gas flow, so that the seal air passes through the region of the nozzle inlet 201-203 that is upstream of the nozzle central axis C in the direction of combustion gas flow. The flow of seal air in the nozzle inlet 201-203 suppresses the inflow of the horseshoe vortex S into the nozzle inlet 201-203. In other words, the seal air plays a sealing role in preventing the combustion gas, which is the main high-temperature gas, from flowing into the nozzle inlet 201-203. This realizes a gas turbine combustor 4 that can suppress flashback.

[0026] In the embodiment illustrated in Figures 3A and 3B, the nozzle channel walls 71 and 72 are also components of the seal air channel forming sections 51 and 52, and seal air channels 141 and 142 are formed between the nozzle channel walls 71 and 72 and the inner channel walls 81 and 82. With this configuration, the inner channel walls 81 and 82 not only form premixed gas channels 91 and 92, but also seal air channels 141 and 142. As a result, the gas turbine combustor 4 can be simplified in configuration compared to the case where a dedicated channel wall for forming the seal air channel 143 is placed outside the nozzle channel walls 71 and 72.

[0027] Furthermore, the seal air passage 142 shown in Figure 3B is positioned only on the upstream side in the combustion gas flow direction with respect to the nozzle central axis C. With this configuration, flashback can be effectively suppressed while keeping the total flow rate of air used as seal air from the compressed air (combustion air) delivered from the compressor 2 low.

[0028] Furthermore, as described above, in the embodiment illustrated in Figure 3C, the seal air passage forming section 53 is positioned on the opposite side of the nozzle central axis C from the nozzle passage wall 73, and the seal air injection port 43 opens in the nozzle passage wall 73. With the above configuration, it becomes possible to freely adjust the position of the seal air injection port 43 in the axial direction of the nozzle central axis C during the design stage of the two-stage combustion nozzle 20. This makes it possible to achieve both the sealing air preventing the inflow of horseshoe vortices S and the sealing air mixing well with the premixed gas inside the combustion chamber 47.

[0029] <4. Details of possible additional configurations for the 2-stage combustion nozzle 21(20)> Referring to Figures 4A to 9, additional configurations applicable to the two-stage combustion nozzle 21 will be described. Below, the configurations from the first example to the seventh example will be described in order. Note that only one of the configurations from the first to the seventh example may be applied to the two-stage combustion nozzle 21, or any combination of two or more of these configurations may be applied to the two-stage combustion nozzle 21.

[0030] <4-1. Configuration related to the first example> The configuration relating to the first example will be explained with reference to Figures 4A to 4C. Figures 4A to 4C are schematic diagrams showing two-stage combustion nozzles 21A, 21B, and 21C(21) to which the configuration relating to the first example is applied, and show the two-stage combustion nozzle 21 in an axial view along the nozzle central axis C. Figures 4A to 4C show different types of configurations relating to the first example.

[0031] The nozzle flow path walls 71A, 71B, 71C(71) of the two-stage combustion nozzles 21A, 21B, 21C(21) have an upstream flow path wall 76A, 76B, 76C(76) positioned upstream in the combustion gas flow direction with respect to the nozzle central axis C, and a downstream flow path wall 79A, 79B, 79C(79) positioned downstream in the combustion gas flow direction with respect to the nozzle central axis C. The seal air flow paths 141A, 141B, 141C(141) have an upstream seal air flow path 146A, 146B, 146C(146) formed by the upstream flow path wall 76 and the inner flow path wall 81, and a downstream seal air flow path 149A, 149B, 149C(149) formed by the downstream flow path wall 79 and the inner flow path wall 81.

[0032] The inner channel wall 81, as illustrated in Figures 4A and 4B, is surrounded by upstream channel walls 76A and 76B and downstream channel walls 79A and 79B along the circumferential direction of the nozzle. The nozzle channel walls 71A and 71B are circular in shape when viewed along the axial direction of the nozzle central axis C. On the other hand, in the example shown in Figure 4C, the upstream channel wall 76C is the same semicircular shape as the upstream channel walls 76A and 76B, but the downstream channel wall 79C is an arc shape with a shorter circumference than the upstream channel wall 76C. The nozzle channel wall 71C is C-shaped when viewed along the axial direction of the nozzle central axis C and is positioned to surround only a portion of the inner channel wall 81 in the circumferential direction of the nozzle.

[0033] According to the configuration of the first example shown in Figures 4A to 4C, the seal air passages 141A to 141C (141) have upstream seal air passages 146A, 146B, 146C (146) and downstream seal air passages 149A, 149B, 149C (149). As a result, the seal air injected from the seal air injection port 41 passes not only through the region upstream of the nozzle central axis C at the nozzle injection ports 201A to 201C (201), but also through the region downstream of the nozzle central axis C, making it possible to uniformly mix the premixed gas containing fuel injected from the nozzle injection port 201 with the seal air.

[0034] Furthermore, as shown in Figure 4B, in an axial view along the nozzle central axis C, the flow area of ​​the upstream seal air passage 146B is larger than the flow area of ​​the downstream seal air passage 149B. In other words, in a cross-section perpendicular to the nozzle central axis C, the flow area of ​​the upstream seal air passage 146B is larger than the flow area of ​​the downstream seal air passage 149B. This relative size of the flow areas is achieved by eccentricating the inner flow passage wall 81 with respect to the nozzle flow passage wall 71 such that the axis of the cylindrically formed inner flow passage wall 81 is located downstream of the nozzle central axis C in the combustion gas flow direction. The horseshoe vortex S generated on the inner circumferential surface 48 of the combustion cylinder 40 tends to flow into the nozzle injection port 201 upstream of the nozzle central axis C in the combustion gas flow direction (this is evident from the flow direction of the horseshoe vortex S illustrated by the arrow in Figure 3A). In this regard, with the above configuration, the flow rate of sealing air flowing through the upstream sealing air passage 146B increases, so that the flow of sealing air can more effectively suppress the inflow of horseshoe vortices S. As a result, the gas turbine combustor 4 can more reliably suppress flashback.

[0035] As shown in Figure 4C, the length of the upstream flow channel wall 76C in the nozzle circumferential direction is longer than the length of the downstream flow channel wall 79C in the nozzle circumferential direction (the length of the downstream flow channel wall 79C in the nozzle circumferential direction is the sum of dimensions L1 and L2). With the above configuration, the flow rate of sealing air flowing through the upstream sealing air flow channel 146C is increased, so the flow of sealing air can more effectively suppress the inflow of horseshoe vortices S. As a result, the gas turbine combustor 4 can more reliably suppress flashback. Furthermore, in an embodiment in which sealing air is not required downstream of the nozzle central axis C in the combustion gas flow direction, the sealing air can be concentrated upstream of the nozzle central axis C in the combustion gas flow direction, so flashback can be suppressed more effectively.

[0036] <4-2. Configuration related to the second example> The configuration relating to the second example will be explained with reference to Figures 5A to 5C. Figures 5A and 5B are schematic diagrams showing a two-stage combustion nozzle 21D to which the configuration relating to the second example is applied. Figure 5C is a cross-sectional view of the partition wall 55 in the direction of the arrow AA in Figure 5A.

[0037] The two-stage combustion nozzle 21D(21) shown in Figure 5A further includes at least one partition wall 55 in addition to the configuration of the two-stage combustion nozzle 21A(21) illustrated in Figure 3A. The partition wall 55 is connected to the nozzle flow path wall 71A and the inner flow path wall 81 in the seal air passage 141. The partition wall 55 also extends along the nozzle central axis C. As shown in Figure 5B, multiple partition walls 55 may be arranged at equal intervals along the nozzle circumferential direction. Each partition wall 55 defines two adjacent spaces in the nozzle circumferential direction, and the flow of sealing air between the two spaces is restricted by the partition wall 55. Note that there may be only one partition wall 55.

[0038] The sealing air at the sealing air injection port 41 may be pushed downstream in the combustion gas flow direction along the nozzle circumferential direction due to the influence of the horseshoe vortex S flow. In this regard, the inclusion of at least one partition wall 55 in the two-stage combustion nozzle 21D allows the partition wall 55 to restrict the flow of sealing air in the nozzle circumferential direction. Therefore, the uneven distribution of the sealing air at the sealing air injection port 41 in the nozzle circumferential direction is suppressed, and the flow of sealing air at the sealing air injection port 41 can be made smoother.

[0039] As illustrated in Figure 5A, the partition wall 55 has a front end 55A and a rear end 55B. The front end 55A is the downstream end of the partition wall 55 in the direction of seal air flow (i.e., the direction of seal air flow in the seal air passage 141). The rear end 55B is the end of the partition wall 55 opposite to the front end 55A. The front end 55A is positioned upstream of the seal air injection port 41 in the direction of seal air flow. The shortest distance from the front end 55A to the seal air injection port 41 (dimension M, shown as the distance in the combustion cylinder diameter direction) is preferably 50% or less of the inner diameter of the circularly formed nozzle injection port 201. Furthermore, the axial length of the partition wall 55 is preferably 50% or more of the diameter of the nozzle injection port 201.

[0040] With the above configuration, the presence of the partition wall 55 suppresses the uneven distribution of the injected sealing air in the circumferential direction. As a result, even when the pressure in the combustion chamber 47 is high upstream in the gas flow direction where sealing air is required, sufficient sealing air can be supplied.

[0041] As illustrated in Figure 5C, at least one of the front end 55A or the rear end 55B may be streamlined. In the example shown in the figure, both the front end 55A and the rear end 55B are streamlined. More specifically, the length of the front end 55A in the nozzle circumferential direction decreases as you move downstream in the seal air flow direction, and the length of the rear end 55B in the nozzle circumferential direction decreases as you move upstream in the seal air flow direction. Both the front end 55A and the rear end 55B are connected to the nozzle flow path wall 71A and the inner flow path wall 81.

[0042] With the above configuration, it is possible to suppress the stagnation of the sealing air flowing toward the sealing air injection port 41.

[0043] <4-3. Configuration related to the third example> Referring to Figures 6A and 6B, the configuration relating to the third example will be explained. Figures 6A and 6B are schematic diagrams showing two-stage combustion nozzles 21E and 21F(21) to which the configuration relating to the third example is applied. Figures 6A and 6B show different types of configurations relating to the third example.

[0044] The two-stage combustion nozzles 21E and 21F (21) shown in Figures 6A and 6B include a turbulator 57 in addition to the configuration of the two-stage combustion nozzle 21A (21) illustrated in Figure 3A. More specifically, the nozzle flow path wall 71A (71) has an inner surface 77 facing the inner flow path wall 81, the inner flow path wall 81 has an outer surface 88 facing the nozzle flow path wall 71A, and the turbulator 57 is provided on at least one of the inner surface 77 or the outer surface 88. The turbulator 57 illustrated in Figures 6A and 6B is provided on both the inner surface 77 and the outer surface 88, but it may also be provided on only one of the inner surface 77 or the outer surface 88. The turbulators 57 may be provided on the inner surface 77 along its entire length in the nozzle circumferential direction, or they may be provided only on a portion of the inner surface 77 in the nozzle circumferential direction. Multiple turbulators 57 provided only on a portion of the inner surface 77 may be arranged on the inner surface 77 at equal intervals along the nozzle circumferential direction. Similarly, the turbulators 57 may be provided on the outer surface 88 along its entire length in the nozzle circumferential direction, or they may be provided only on a portion of the outer surface 88 in the nozzle circumferential direction. Turbulators 57 provided only on a portion of the outer surface 88 may be arranged on the outer surface 88 at equal intervals along the nozzle circumferential direction.

[0045] With the above configuration, the turbulator 57 is provided in the seal air passage 141, which generates a secondary flow of seal air in the seal air passage 141. Because the flow of seal air injected from the seal air injection port 41 is disturbed, the seal air that has finished performing its sealing function to prevent the inflow of horseshoe vortices S and is flowing toward the center of the combustion chamber 47 mixes easily with the premixed gas containing fuel. As a result, the high-temperature combustion gas and the seal air are quickly mixed inside the combustion chamber 47, which can reduce the ambient combustion gas temperature. Therefore, the generation of NOx can be suppressed.

[0046] As shown in Figure 6A, in one embodiment of the present disclosure, the turbulator 57 is preferably positioned at least upstream of the nozzle central axis C in the combustion gas flow direction. This configuration promotes the mixing of the sealing air, which has finished its sealing function of preventing the inflow of horseshoe vortices S, with the premixed gas containing fuel. This mixed air mixes with the already burned gas located upstream in the combustion gas flow direction inside the combustion chamber 47, and the temperature of the already burned gas decreases, thereby suppressing the generation of NOx.

[0047] As shown in Figure 6B, the turbulator 57 according to other embodiments of the present disclosure may be positioned only downstream of the nozzle central axis C in the combustion gas flow direction. Downstream of the nozzle inlet 201 in the combustion gas flow direction, the horseshoe vortex S is less likely to flow into the nozzle inlet 201. In other words, the seal air flowing downstream of the nozzle central axis C may not need to prevent the inflow of the horseshoe vortex S. In this respect, the above configuration makes it possible to actively disturb the flow of the seal air, thereby promoting the mixing of the seal air with the premixed gas containing the fuel.

[0048] <4-4. Configuration related to the fourth example> The configuration relating to the fourth example will be explained with reference to Figures 7A and 7B. Figures 7A and 7B are schematic diagrams showing a two-stage combustion nozzle 21G(21) to which the configuration relating to the fourth example is applied. For the sake of clarity, the inner flow path wall 81G (see Figure 7B) is omitted from Figure 7A, and the nozzle flow path wall end 711G (see Figure 7A) is partially omitted from Figure 7B.

[0049] The nozzle flow path wall 71G(71) of the two-stage combustion nozzle 21G(21) shown in Figure 7A has one end portion 711G(711) of the nozzle flow path wall that forms the nozzle injection port 201G(201). The one end portion 711G of the nozzle flow path wall extends in a zigzag pattern along the circumferential direction of the nozzle. The inner flow channel wall 81G(81) of the two-stage combustion nozzle 21G(21) shown in Figure 7B has an inner flow channel wall end 811G(811) that forms a premixed gas injection port 813G(813). The inner flow channel wall end 811G extends in a zigzag pattern along the circumferential direction of the nozzle. Furthermore, this disclosure is not limited to the case where both the nozzle channel wall end 711G(711) and the inner channel wall end 811G(811) extend in a zigzag pattern. Either the nozzle channel wall end 711G(711) or the inner channel wall end 811G(811) may extend in a zigzag pattern. In this case, the other may extend linearly along the circumferential direction of the nozzle.

[0050] According to the above configuration, a secondary flow of sealing air is generated at the sealing air injection port 41G(41) formed by one end 811G of the inner flow channel wall and one end 711G of the nozzle flow channel wall. As the flow of sealing air injected from the sealing air injection port 41G(41) is disturbed, the sealing air that has finished performing its sealing function to prevent the inflow of horseshoe vortices S and is flowing toward the center of the combustion chamber 47 is more easily mixed with the fuel. As a result, the surrounding high-temperature combustion gas and sealing air are quickly mixed inside the combustion chamber 47, which reduces the ambient combustion gas temperature and suppresses the generation of NOx.

[0051] <4-5. Configuration related to the fifth example> Referring to Figures 8A to 8D, the configuration relating to the fifth example will be explained. Figure 8A is a schematic diagram showing a two-stage combustion nozzle 21H(21) to which the configuration relating to the fifth example is applied. Figures 8B and 8C are schematic diagrams showing two-stage combustion nozzles 21I, 21J(21H) which are more specific versions of the two-stage combustion nozzle 21H in Figure 8A.

[0052] As shown in Figure 8A, the inner flow channel wall 81H(81) of the two-stage combustion nozzle 21H(21) has an inner flow channel wall end portion 811H(811) that forms the premixed gas injection port 813H(813). The nozzle flow channel wall 71H(71) of the two-stage combustion nozzle 21H shown in the same figure extends parallel to the nozzle central axis C, but as will be described later, a part of the nozzle flow channel wall 71H may be non-parallel to the nozzle central axis C (see Figure 8C). The inner flow channel wall end portion 811H is positioned upstream of the nozzle injection port 201H(201) in the sealing air flow direction. With the above configuration, the inner flow channel wall end portion 811H can be kept away from the combustion gas, which is the high-temperature main gas flowing through the combustion chamber 47, and thus burnout of the inner flow channel wall end portion 811H can be suppressed. When this configuration is adopted, the seal air injection port 41H(41), formed by one end 811H of the inner flow channel wall and the nozzle flow channel wall 71H, is positioned upstream of the nozzle injection port 201H in the direction of seal air flow. Therefore, at least a portion of the seal air is injected from the nozzle injection port 201H after being mixed with the premixed gas.

[0053] The two-stage combustion nozzle 21I (21H) illustrated in Figure 8B has an inner flow channel wall 81I (81H), and one end 811I (811H) of the inner flow channel wall 81H has an inner tapered surface 815. The inner tapered surface 815 faces inward in the nozzle radial direction (i.e., toward the nozzle central axis C), and is inclined to move away from the nozzle central axis C as it approaches the combustion chamber 47. The two-stage combustion nozzle 21J(21H) illustrated in Figure 8C has an inner flow channel wall 81J(81H), and one end 811J(811H) of the inner flow channel wall 81J has an outer tapered surface 818. The outer tapered surface 818 faces outward in the diameter direction of the nozzle (i.e., opposite to the nozzle central axis C) and is inclined to approach the nozzle central axis C as it approaches the combustion chamber 47. According to the configuration in which one end portion 811H of the inner flow channel wall has either an outer tapered surface 818 or an inner tapered surface 815, the shape of the one end portion 811H of the inner flow channel wall tapers, so that the accumulation of premixed gas near the one end portion 811H of the inner flow channel wall (for example, in the region R within the two-stage combustion nozzle 20H located downstream of the one end portion 811H of the inner flow channel wall in the direction of seal air flow) can be suppressed. As a result, the nozzle injection port 201H can inject the premixed gas with force. Note that the one end portion 811H of the inner flow channel wall in this disclosure is not limited to having only one of the inner tapered surface 815 or the outer tapered surface 818, but may have both the inner tapered surface 815 and the outer tapered surface 818. In this case as well, the above-mentioned advantage of suppressing the accumulation of premixed gas can be obtained.

[0054] As illustrated in Figure 8C, the nozzle flow path wall 71J(71H) of the two-stage combustion nozzle 21J(21H) may have an opposing inclined surface 75. The opposing inclined surface 75 faces the outer surface 88 and is inclined to approach the nozzle central axis C as it approaches the nozzle injection port 201J(201H). In the same figure, as an example, the opposing inclined surface 75 is parallel to the outer surface 88.

[0055] According to the above configuration, the flow area of ​​the sealing air passage 141J (141H) of the two-stage combustion nozzle 21J is suppressed as it approaches the sealing air injection port 41J (41H), thus preventing a weakening of the sealing air's force at the sealing air injection port 41J. This allows the premixed gas to be forcefully injected from the nozzle injection port 201J (201H) while suppressing the inflow of the horseshoe vortex S into the nozzle injection port 201J.

[0056] <4-6. Configuration related to the sixth example> Referring to Figure 9, the configuration relating to the sixth example will be explained. Figure 9 is a schematic diagram showing a two-stage combustion nozzle 21K(21) to which the configuration relating to the sixth example is applied. The nozzle inlet 201K(201) and the premixed gas inlet 813K(813) of the two-stage combustion nozzle 21K(21) exhibit an elongated oval shape in the direction of combustion gas flow when viewed in the axial direction of the nozzle central axis C.

[0057] In an embodiment in which the nozzle inlet 201K(201) is oval-shaped, if the "nozzle inlet 201 formed on the inner circumferential surface 48 of the combustion cylinder 40" is positioned outside the inner circumferential surface 48 in the combustion cylinder diameter direction, then the distance between the inner circumferential surface 48 and the nozzle inlet 201 in the combustion cylinder diameter direction is 20% or less of the hydraulic diameter of the nozzle inlet 201K. Furthermore, in an embodiment in which the nozzle inlet 201K(201) is oval-shaped, if the "nozzle inlet 201 formed on the inner circumferential surface 48 of the combustion cylinder 40" is positioned inward from the inner circumferential surface 48 in the combustion cylinder diameter direction, then the distance between the inner circumferential surface 48 and the nozzle inlet 201 in the combustion cylinder diameter direction is 5% or less of the hydraulic diameter of the nozzle inlet 201K. Furthermore, the two-stage combustion nozzle 21K may include a partition wall 55 (see Figure 5A). In this case, it is preferable that the shortest distance (distance in the direction of the combustion cylinder diameter) from the tip 55A of the partition wall 55 to the sealing air injection port 41K (41) is 25% or less of the length of the nozzle injection port 201K in the direction of combustion gas flow.

[0058] <4-7. Supplementary Explanation> This disclosure is not limited to the application of the configurations described in the first to seventh examples above to the two-stage combustion nozzle 21. At least one of these configurations may be applied to the two-stage combustion nozzles 22 and 23. Further details are omitted to avoid repetition.

[0059] <5. Summary> The contents described in some of the embodiments above can be understood, for example, as follows:

[0060] 1) A gas turbine combustor (4) according to at least one embodiment of the present disclosure is A combustion cylinder (40) that defines the combustion chamber (47), A combustor (8) for supplying fuel to the combustion chamber, With respect to the combustor, a two-stage combustion nozzle (20) is positioned downstream in the direction of combustion gas flow within the combustion chamber. A gas turbine combustor equipped with, The aforementioned two-stage combustion nozzle is Nozzle flow path forming section (31-33) that forms nozzle flow paths (121-123) having nozzle injection ports (201-203) formed on the inner circumferential surface of the combustion cylinder, A seal air passage forming section (51-53) is formed, having a seal air inlet (41-43) which is positioned at least partially upstream of the combustion gas flow direction with respect to the nozzle central axis (C), which is the center line of the two-stage combustion nozzle, and a seal air passage forming section (51-53) is formed, the seal air passage forming section (51-53) having a seal air inlet (41-43) which is positioned upstream of the combustion gas flow direction, Includes.

[0061] According to the configuration described in 1) above, the sealing air injected from the sealing air inlet passes through the region of the nozzle inlet upstream of the nozzle's central axis. The flow of sealing air at the nozzle inlet suppresses the inflow of horseshoe vortices (S) of high-temperature combustion gases generated on the inner surface of the combustion chamber into the nozzle inlet. This enables the realization of a gas turbine combustor that can suppress flashback.

[0062] 2) In some embodiments, the gas turbine combustor described in 1) above, The nozzle flow path forming section has nozzle flow path walls (71-73) that are connected to the inner circumferential surface of the combustion cylinder. The aforementioned seal air passage forming portion is The nozzle flow path wall and, An inner flow path wall (81, 82) is positioned inside the nozzle flow path wall and forms a fuel flow path (premixed gas flow path 91, 92) through which the fuel flows, It also includes.

[0063] According to the configuration described in 2) above, the inner flow path wall not only forms the fuel flow path but also the sealing air flow path. This simplifies the configuration of the gas turbine combustor compared to the case where a dedicated flow path wall for forming the sealing air flow path is located outside the nozzle flow path wall.

[0064] 3) In some embodiments, the gas turbine combustor described in 2) above, The nozzle channel wall is With respect to the nozzle central axis, the upstream flow path wall (76) is positioned on the upstream side in the flow direction of the combustion gas, A downstream flow path wall (79) is positioned downstream of the nozzle central axis in the flow direction of the combustion gas, It has, The aforementioned sealing air passage is The upstream seal air passage (146) is formed by the upstream passage wall and the inner passage wall, The downstream seal air passage (149) is formed by the downstream passage wall and the inner passage wall, It holds.

[0065] According to the configuration described in 3) above, the sealing air injected from the sealing air inlet passes not only through the region upstream of the nozzle's central axis at the nozzle inlet, but also through the region downstream of the nozzle's central axis. This makes it possible to evenly mix the fuel injected from the nozzle inlet with the sealing air.

[0066] 4) In some embodiments, the gas turbine combustor described in 3) above, In the cross-section of the seal air passage perpendicular to the nozzle central axis, the flow area of ​​the upstream seal air passage is larger than the flow area of ​​the downstream seal air passage.

[0067] Horseshoe vortices generated on the inner surface of the combustion chamber tend to flow into the nozzle injection port upstream of the nozzle's central axis in the direction of combustion gas flow. In this regard, according to the configuration of 4) above, the flow rate of sealing air flowing through the upstream sealing air passage is increased, so the flow of sealing air can more effectively suppress the inflow of horseshoe vortices. As a result, the gas turbine combustor can more reliably suppress flashback.

[0068] 5) In some embodiments, the gas turbine combustor described in 3) or 4) above, The length of the upstream seal air passage in the nozzle circumferential direction, which is the direction circumferential to the nozzle's central axis, is longer than the length of the downstream seal air passage in the nozzle circumferential direction.

[0069] According to the configuration in 5) above, the flow rate of sealing air flowing through the upstream sealing air passage is increased, and for the same reasons as in 4) above, the gas turbine combustor can more reliably suppress flashback. In addition, since the sealing air can be concentrated upstream of the nozzle central axis C in the direction of combustion gas flow, flashback can be suppressed more effectively.

[0070] 6) In some embodiments, the gas turbine combustor described in 2) above, The sealing air passage is formed only on the upstream side of the flow direction of the combustion gas with respect to the nozzle central axis.

[0071] According to the configuration in 6) above, only on the upstream side with respect to the nozzle central axis seal Since an air passage is formed, the gas turbine combustor seal This method effectively suppresses flashbacks while reducing the total airflow.

[0072] 7) In some embodiments, a gas turbine combustor according to any of 2) to 6) above, The two-stage combustion nozzle further includes a partition wall (55) connected to the nozzle flow path wall and the inner flow path wall in the sealing air passage.

[0073] The sealing air at the sealing air injection port may be pushed downstream in the direction of the combustion gas flow along the nozzle circumferential direction due to the influence of the horseshoe vortex flow. In this regard, according to the configuration of 7) above, even in this case, the partition wall can restrict the flow of sealing air in the nozzle circumferential direction. Therefore, the bias in the pressure distribution of the sealing air at the sealing air injection port in the nozzle circumferential direction is suppressed, and the flow of sealing air at the sealing air injection port can be made smoother.

[0074] 8) In some embodiments, the gas turbine combustor described in 7) above, The partition wall has a tip portion (55A) which is the downstream end in the direction of the flow of the sealing air in the sealing air passage, The tip of the partition wall is positioned upstream of the sealing air injection port in the flow direction of the sealing air.

[0075] According to the configuration described in 8) above, the presence of a partition wall suppresses the uneven distribution of the injected sealing air in the circumferential direction. As a result, even when the pressure in the combustion chamber 47 is high upstream in the gas flow direction in which sealing air is required, sufficient sealing air can be supplied.

[0076] 9) In some embodiments, the gas turbine combustor described in 7) or 8) above, The aforementioned partition wall is, The tip portion (55A), which is the downstream end in the direction of the flow of the sealing air in the sealing air passage, The rear end (55B), which is the end opposite to the aforementioned tip, It has, At least one of the aforementioned front end or rear end is streamlined.

[0077] According to the configuration in 9) above, the stagnation of the sealing air flowing toward the sealing air injection port is suppressed, so that the sealing air is forcefully ejected from the sealing air injection port. Therefore, the inflow of horseshoe vortices into the nozzle injection port can be further suppressed.

[0078] 10) In some embodiments, a gas turbine combustor according to any of 2) to 9) above, The nozzle channel wall has an inner surface (77) facing the inner channel wall, The inner channel wall has an outer surface (88) facing the nozzle channel wall, The two-stage combustion nozzle further includes a turbulator (57) provided on at least one of the inner surface or the outer surface.

[0079] According to the configuration described in 10) above, the presence of a turbulator in the seal air passage generates a secondary flow of seal air within the seal air passage. Because the flow of seal air injected from the seal air injection port is disturbed, the seal air, having finished its sealing function of preventing the inflow of horseshoe vortices, flows toward the center of the combustion chamber and mixes easily with the fuel. As a result, the high-temperature combustion gas and seal air are rapidly mixed inside the combustion chamber, reducing the ambient combustion gas temperature. Therefore, the generation of NOx can be suppressed.

[0080] 11) In some embodiments, the gas turbine combustor described in 10) above, The turbulator is positioned at least upstream of the nozzle's central axis in the direction of the combustion gas flow.

[0081] According to the configuration described in 11) above, the sealing air, having finished its sealing function of preventing the inflow of horseshoe vortices, can be promoted to mix with the fuel. This mixed air then mixes with the already burned gas located upstream in the combustion gas flow direction inside the combustion chamber, lowering the temperature of the already burned gas and thus suppressing the generation of NOx.

[0082] 12) In some embodiments, the gas turbine combustor described in 10) above, The turbulator is positioned only downstream of the nozzle's central axis in the direction of combustion gas flow.

[0083] Downstream of the nozzle inlet in the direction of combustion gas flow, there is a low tendency for horseshoe vortices to flow into the nozzle inlet. In other words, the sealing air flowing downstream of the nozzle's central axis may not need to prevent the inflow of horseshoe vortices. In this respect, the configuration described in 12) above makes it possible to actively disturb the flow of the sealing air, thereby promoting the mixing of the sealing air with the fuel.

[0084] 13) In some embodiments, a gas turbine combustor according to any of 2) to 11) above, The inner flow channel wall has one end portion (811, 812) of the inner flow channel wall that forms a fuel injection port (813, 823) for injecting the fuel, The nozzle channel wall has one end portion (711-713) of the nozzle channel wall that forms the nozzle injection port. At least one of the inner channel wall end or the nozzle channel wall end extends in a zigzag pattern along the nozzle circumferential direction, which is the circumferential direction of the nozzle central axis.

[0085] According to the configuration described in 13) above, a secondary flow of sealing air is generated at the sealing air injection port formed by one end of the inner flow channel wall and one end of the nozzle flow channel wall. Because the flow of sealing air injected from the sealing air injection port is disturbed, the sealing air that has finished performing its sealing function to prevent the inflow of horseshoe vortices and is flowing toward the center of the combustion chamber is more easily mixed with the fuel. This suppresses combustion failure in the combustion chamber.

[0086] 14) In some embodiments, a gas turbine combustor according to any of 2) to 13) above, The inner flow channel wall has one end portion (811, 812) of the inner flow channel wall that forms a fuel injection port (813, 823), The end of the inner flow channel wall is positioned upstream of the nozzle injection port in the direction of the sealing air flow in the sealing air channel.

[0087] According to the configuration described in 14) above, one end of the inner flow path wall can be kept away from the combustion gas flowing through the combustion chamber, thereby suppressing damage to one end of the inner flow path wall.

[0088] 15) In some embodiments, the gas turbine combustor described in 14) above, The fuel injection port is a premixed gas injection port configured to inject a premixed gas containing the fuel and combustion air, The end of the inner channel wall is, An outer tapered surface (818) that faces outward in the nozzle radial direction, which is the radial direction of the nozzle central axis, and is inclined to approach the nozzle central axis as it approaches the combustion chamber, or The inner tapered surface (815) faces inward in the diameter direction of the nozzle and is inclined to move away from the central axis of the nozzle as it approaches the combustion chamber. It has at least one of the following:

[0089] According to the configuration described in 15) above, one end of the inner flow channel wall tapers, which prevents the premixed gas from accumulating near that end. As a result, the nozzle can forcefully inject the premixed gas.

[0090] 16) In some embodiments, the gas turbine combustor described in 15) above, The inner channel wall has the outer tapered surface at one end, The nozzle flow path wall has an opposing inclined surface (75) that faces the outer tapered surface and is inclined so as it approaches the nozzle injection port, it approaches the nozzle central axis.

[0091] According to the configuration described in 16) above, the flow area of ​​the seal air passage is suppressed from increasing as it approaches the seal air injection port, thus preventing a weakening of the force of the seal air at the seal air injection port. As a result, the gas turbine combustor can forcefully inject the premixed gas from the nozzle injection port and suppress the inflow of horseshoe vortices into the nozzle injection port.

[0092] 17) In some embodiments, the gas turbine combustor described in 1) above, The nozzle flow path forming section has nozzle flow path walls (711-713) that are connected to the inner circumferential surface of the combustion cylinder, The seal air passage forming portion is positioned on the opposite side of the nozzle central axis from the nozzle passage wall, The sealing air injection port is configured to open in the nozzle flow path wall and to inject sealing air toward the nozzle injection port.

[0093] According to the configuration described in 17) above, the position of the sealing air injection port can be freely designed. This makes it possible to achieve both the sealing air preventing the inflow of horseshoe vortices and the sealing air mixing well with the fuel inside the combustion chamber. [Explanation of symbols]

[0094] 4: Gas turbine combustor 6: Turbine 8: Combustor 20: 2 Stepped combustion nozzle 31-33: Nozzle flow path forming section 40: Combustion cylinder 41-43: Seal air nozzle 47: Combustion chamber 48: Inner surface 55: Partition wall 55A: Tip 55B: Rear end 57: Turbulator 71-73: Nozzle flow path wall 75: Opposing Inclined Surface 76: Upstream channel wall 77: Inner surface 79: Downstream channel wall 81,82: Inner channel wall 88 :Outer surface 100: Gas Turbine 121~123: Nozzle flow path 141~143: Seal air passage 146: Upstream seal air passage 149: Downstream seal air passage 201~203: Nozzle spray nozzle 711~713: One end of the nozzle flow path wall 811,812: One end of inner channel wall 813: Premixed gas injection nozzle 815: Inner tapered surface 818: Outer tapered surface 823: Premixed gas injection nozzle C: Nozzle central axis P: Center line

Claims

1. A combustion cylinder that defines the combustion chamber, A combustor for supplying fuel to the combustion chamber, A two-stage combustion nozzle is positioned downstream of the combustion gas flow direction in the combustion chamber relative to the combustor. A gas turbine combustor equipped with, The aforementioned two-stage combustion nozzle is A nozzle channel forming section that forms a nozzle channel having a nozzle injection port formed on the inner circumferential surface of the combustion cylinder, A seal air passage forming section that forms a seal air passage having a seal air injection port which is positioned at least partially upstream of the flow direction of the combustion gas with respect to the nozzle central axis which is the center line of the two-stage combustion nozzle, Includes, The nozzle channel forming section has a nozzle channel wall that is connected to the inner circumferential surface of the combustion cylinder, The aforementioned seal air passage forming portion is The nozzle flow path wall and, An inner flow path wall is positioned inside the nozzle flow path wall and forms a fuel flow path through which the fuel flows, It further includes, The two-stage combustion nozzle further includes a partition wall connected to the nozzle flow path wall and the inner flow path wall in the sealing air passage, The aforementioned partition wall is, The tip portion, which is the downstream end in the direction of the flow of the sealing air in the sealing air passage, The rear end, which is the end opposite to the aforementioned tip, It has, At least one of the aforementioned front end or rear end has a streamlined shape. Gas turbine combustor.

2. A combustion cylinder that defines a combustion chamber, A combustor for supplying fuel to the combustion chamber, A two-stage combustion nozzle is positioned downstream of the combustion gas flow direction in the combustion chamber relative to the combustor. A gas turbine combustor equipped with, The aforementioned two-stage combustion nozzle is A nozzle channel forming section that forms a nozzle channel having a nozzle injection port formed on the inner circumferential surface of the combustion cylinder, A seal air passage forming section that forms a seal air passage having a seal air injection port which is positioned at least partially upstream of the flow direction of the combustion gas with respect to the nozzle central axis which is the center line of the two-stage combustion nozzle, Includes, The nozzle channel forming section has a nozzle channel wall that is connected to the inner circumferential surface of the combustion cylinder, The aforementioned seal air passage forming portion is The nozzle flow path wall and, An inner flow path wall is positioned inside the nozzle flow path wall and forms a fuel flow path through which the fuel flows, It further includes, The nozzle channel wall has an inner surface facing the inner channel wall, The inner channel wall has an outer surface facing the nozzle channel wall, The two-stage combustion nozzle further includes a turbulator provided on at least one of the inner surface or the outer surface, The turbulator is positioned only downstream of the nozzle's central axis in the direction of the combustion gas flow. Gas turbine combustor.

3. The nozzle channel wall is An upstream flow path wall is positioned on the upstream side of the flow direction of the combustion gas with respect to the nozzle central axis, A downstream flow path wall is positioned downstream of the nozzle's central axis in the flow direction of the combustion gas, It has, The aforementioned sealing air passage is The upstream seal air passage is formed by the upstream passage wall and the inner passage wall, The downstream seal air passage is formed by the downstream passage wall and the inner passage wall, Having, The gas turbine combustor according to claim 2.

4. In the cross-section of the seal air passage perpendicular to the nozzle central axis, the flow area of ​​the upstream seal air passage is larger than the flow area of ​​the downstream seal air passage. The gas turbine combustor according to claim 3.

5. The length of the upstream seal air passage in the nozzle circumferential direction, which is the direction circumferential to the nozzle central axis, is longer than the length of the downstream seal air passage in the nozzle circumferential direction. The gas turbine combustor according to claim 3 or 4.

6. The sealing air passage is formed only on the upstream side of the flow direction of the combustion gas with respect to the central axis of the nozzle. The gas turbine combustor according to claim 2.

7. The two-stage combustion nozzle further includes a partition wall connected to the nozzle flow path wall and the inner flow path wall in the sealing air passage. The gas turbine combustor according to claim 2 or 3.

8. The partition wall has a tip portion which is the downstream end in the direction of the seal air flow in the seal air passage, The tip of the partition wall is positioned upstream of the sealing air nozzle in the flow direction of the sealing air. The gas turbine combustor according to claim 7.

9. The aforementioned partition wall is, The tip portion, which is the downstream end in the direction of the flow of the sealing air in the sealing air passage, The rear end, which is the end opposite to the aforementioned tip, It has, At least one of the aforementioned front end or rear end has a streamlined shape. The gas turbine combustor according to claim 7.

10. The nozzle channel wall has an inner surface facing the inner channel wall, The inner channel wall has an outer surface facing the nozzle channel wall, The two-stage combustion nozzle further includes a turbulator provided on at least one of the inner surface or the outer surface. The gas turbine combustor according to claim 1.

11. The turbulator is positioned at least upstream of the nozzle's central axis in the direction of the combustion gas flow. The gas turbine combustor according to claim 10.

12. The turbulator is positioned only downstream of the nozzle's central axis in the direction of the combustion gas flow. The gas turbine combustor according to claim 10.

13. A combustion cylinder that defines a combustion chamber, A combustor for supplying fuel to the combustion chamber, A two-stage combustion nozzle is positioned downstream of the combustion gas flow direction in the combustion chamber relative to the combustor. A gas turbine combustor equipped with, The aforementioned two-stage combustion nozzle is A nozzle channel forming section that forms a nozzle channel having a nozzle injection port formed on the inner circumferential surface of the combustion cylinder, A seal air passage forming section that forms a seal air passage having a seal air injection port which is positioned at least partially upstream of the flow direction of the combustion gas with respect to the nozzle central axis which is the center line of the two-stage combustion nozzle, Includes, The nozzle channel forming section has a nozzle channel wall that is connected to the inner circumferential surface of the combustion cylinder, The aforementioned seal air passage forming portion is The nozzle flow path wall and, An inner flow path wall is positioned inside the nozzle flow path wall and forms a fuel flow path through which the fuel flows, It further includes, The inner flow channel wall has one end of the inner flow channel wall that forms a fuel injection port for injecting the fuel, The nozzle channel wall has one end of the nozzle channel wall that forms the nozzle injection port, At least one of the inner channel wall end or the nozzle channel wall end extends in a zigzag pattern along the nozzle circumferential direction, which is the circumferential direction of the nozzle central axis. Gas turbine combustor.

14. The inner flow channel wall has one end of the inner flow channel wall that forms a fuel injection port, The end of the inner flow channel wall is positioned upstream of the nozzle injection port in the direction of the sealing air flow in the sealing air channel. The gas turbine combustor according to claim 2 or 3.

15. The fuel injection port is a premixed gas injection port configured to inject a premixed gas containing the fuel and combustion air, The end of the inner channel wall is, An outer tapered surface that faces outward in the nozzle radial direction, which is the radial direction of the nozzle central axis, and that slopes toward the nozzle central axis as it approaches the combustion chamber, or The inner tapered surface faces inward in the diameter direction of the nozzle and slopes away from the nozzle's central axis as it approaches the combustion chamber. Having at least one of the following, The gas turbine combustor according to claim 14.

16. The inner channel wall has the outer tapered surface at one end, The nozzle flow path wall is an opposing inclined surface facing the outer tapered surface, and has an opposing inclined surface that is inclined to approach the nozzle central axis as it approaches the nozzle injection port. The gas turbine combustor according to claim 15.

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