Combustor and gas turbine

Abstract

The combustor of the present application has a combustor plate having a downstream end surface orthogonal to a combustor axis, a nozzle section configured by a plurality of first nozzle sets that inject a premixed gas of air and fuel from the downstream end surface side, and a second nozzle that injects fuel from the downstream end surface, a plurality of the nozzle sections being provided at intervals from each other in a direction orthogonal to the combustor axis, the second nozzle injecting fuel from a partitioned region between the nozzle sections in the downstream end surface.

Description

Technical Field

[0001] This invention relates to burners and gas turbines.

[0002] This application claims priority to Japan Patent Application No. 2022-56000, filed with the Japan Patent Office on March 30, 2022, the contents of which are incorporated herein by reference. Background Technology

[0003] For example, Patent Document 1 discloses a cluster burner as an example of a burner used in a gas turbine.

[0004] The aforementioned cluster burner has main nozzles (first nozzles) arranged side-by-side to inject a premixed gas of air and fuel, and pilot nozzles (second nozzles) for generating a pilot flame for flame stabilization. The main nozzles are arranged in a cluster to form nozzle sections. These nozzle sections are arranged in a ring shape, with the pilot nozzle located at the center of the ring. The pilot flame generated by the pilot nozzle ensures the flame stability of the main flame generated by each main nozzle.

[0005] Existing technical documents

[0006] Patent documents

[0007] Patent Document 1: U.S. Patent Application Publication No. 2014 / 0116054 Summary of the Invention

[0008] The problem that the invention aims to solve

[0009] However, in burners like the one described above, there are instances where flame stability decreases depending on the fuel and operating conditions.

[0010] In addition, simply increasing the diameter of the pilot nozzle to ensure flame stability will encroach on the installation area of ​​the main nozzle, resulting in a decrease in burner performance.

[0011] The present invention was made to solve the above-mentioned problems, and aims to provide a burner and a gas turbine that can improve flame stability while maintaining burner performance.

[0012] Solution for solving the problem

[0013] To address the aforementioned issues, the burner of the present invention comprises: a burner plate having a downstream end face orthogonal to the burner axis; a nozzle section configured by a plurality of first nozzles that inject a premixed gas of air and fuel from the downstream end face; and a second nozzle that injects fuel from the downstream end face, wherein a plurality of the nozzle sections are spaced apart from each other in a direction orthogonal to the burner axis, and the second nozzle injects the fuel from a segmented area between the nozzle sections in the downstream end face.

[0014] The gas turbine of the present invention comprises: a compressor that generates air; the aforementioned burner that combusts a premixed gas generated by mixing fuel in the compressed air to generate combustion gas; and a turbine driven by the combustion gas.

[0015] Invention Effects

[0016] The burner and gas turbine according to the present invention can improve flame stability while maintaining burner performance. Attached Figure Description

[0017] Figure 1 This is a schematic diagram showing the general structure of a gas turbine according to the first embodiment of the present invention.

[0018] Figure 2 This is a longitudinal sectional view showing the schematic structure of a burner according to the first embodiment of the present invention.

[0019] Figure 3 This is a diagram obtained by viewing the downstream end face of the burner plate of the burner according to the first embodiment of the present invention from the downstream side.

[0020] Figure 4 This is a longitudinal sectional view of the main part of the burner plate of the burner according to the first embodiment of the present invention.

[0021] Figure 5 This is a diagram obtained by viewing the downstream end face of the burner plate of the burner according to the second embodiment of the present invention from the downstream side.

[0022] Figure 6 This is a diagram obtained by viewing the downstream end face of the burner plate of the burner according to the third embodiment of the present invention from the downstream side.

[0023] Figure 7 This is a diagram obtained by viewing the downstream end face of the burner plate of the burner according to the fourth embodiment of the present invention from the downstream side.

[0024] Figure 8 This is a longitudinal sectional view of the main part of the burner plate of the burner according to the fourth embodiment of the present invention.

[0025] Figure 9 This is a diagram showing a modified example of the burner plate of a burner according to an embodiment of the present invention. Detailed Implementation

[0026] <First Implementation>

[0027] The following is for reference Figures 1-4 The first embodiment of the present invention will be described in detail.

[0028] like Figure 1 As shown, the gas turbine 1 of this embodiment includes a compressor 2 for compressing air A, a burner 3 for generating combustion gas C, and a turbine 4 driven by the combustion gas C.

[0029] Multiple burners 3 are arranged circumferentially around the rotating shaft of the gas turbine 1. The burners 3 mix fuel with compressed air A from the compressor 2 and combust them to generate high-temperature, high-pressure combustion gas C.

[0030] <Burner>

[0031] The following is for reference Figures 2-4 The structure of burner 3 will be described.

[0032] like Figure 2 As shown, the burner 3 has an outer cylinder 10, an end cover 11, an inner cylinder 15, a support 17, a burner plate 20, a main nozzle 30 as a first nozzle, and a pilot nozzle 40 as a second nozzle.

[0033] <Outer cylinder>

[0034] The cylinder is cylindrical with the burner axis O (hereinafter referred to as axis O) which is the center of the burner 3.

[0035] <End Cover>

[0036] End cap 11 is positioned on one side of the outer cylinder 10 along the axis O direction. Figure 2 The end of the outer cylinder 10 is sealed with a disc-shaped end cap (on the left side). The end cap 11 abuts against the end of the outer cylinder 10 on one side along the axis O. Inside the end cap 11, a first fuel manifold 12 and a second fuel manifold 13 are formed as spaces. Main fuel F1, serving as the first fuel, is supplied to the first fuel manifold 12 from the outside. Pilot fuel F2, serving as the second fuel, is supplied to the second fuel manifold 13 from the outside. The main fuel F1 and pilot fuel F2 are, for example, hydrogen, natural gas, or a mixture thereof.

[0037] <Inner tube>

[0038] The inner cylinder 15 is coaxially disposed inside the outer cylinder 10. The inner cylinder 15 is cylindrical, extending along the axis O direction inside the outer cylinder 10. The end of the inner cylinder 15 on one side of the axis O direction is separated from the end cover 11 in the axis O direction. The outer diameter of the inner cylinder 15 is smaller than the inner diameter of the outer cylinder 10. Therefore, an annular flow path is formed between the outer circumferential surface of the inner cylinder 15 and the inner circumferential surface of the outer cylinder 10. Air A compressed by the compressor 2 flows from the other side of the axis O direction (…). Figure 2 The flow path is oriented towards the right side of the axis O (in the middle).

[0039] <Support section>

[0040] Support portions 17 are members extending along the axis O, and multiple such portions are provided at intervals in the circumferential direction. The end of each support portion 17 on one side of the axis O direction is fixed to the inner circumferential side of the outer cylinder 10 to the surface of the end plate facing the other side of the axis O direction. Air A flowing between the outer cylinder 10 and the inner cylinder 15 to one side of the axis O direction reverses its flow direction when passing between adjacent support portions 17.

[0041] <Burner Plate>

[0042] The burner plate 20 is in the shape of a disk centered on axis O. The burner plate 20 is arranged to be coaxially embedded inside the inner cylinder 15. The burner plate 20 has an upstream end face 21 and a downstream end face 22.

[0043] <Upstream end face>

[0044] The upstream end face 21 is the end face of the burner plate 20 facing the direction of axis O, and is a plane orthogonal to axis O. The upstream end face 21 is located at the same position in the direction of axis O as the end face of the inner cylinder 15 facing the direction of axis O.

[0045] Downstream end face

[0046] The downstream end face 22 is the end face of the burner plate 20 facing the opposite side of the axis O, and is a plane orthogonal to the axis O. The downstream end face 22 is located on the side of the axis O direction closer than the end face of the inner cylinder 15 facing the opposite side of the axis O direction. Thus, a space is formed by dividing the inner circumferential surface of the inner cylinder 15 and the downstream end face 22 of the burner plate 20. This space becomes the combustion space of the burner 3.

[0047] <Main Nozzle>

[0048] like Figure 2 as well as Figure 3 As shown, the main nozzle 30 extends further downstream from the downstream end face 22 of the burner plate 20 (to the other side in the direction of axis O). Figure 2(On the right side) Air A is ejected and premixed with the main fuel F1 to form the main flame F.

[0049] Multiple main nozzles 30 are provided, and each main nozzle 30 is composed of a mixing pipe 31 and a fuel supply pipe 32.

[0050] Mixing pipe 31 is a pipe extending along axis O, supplying air A from the upstream side (the side along axis O). Figure 2 (The mixture flows in from the left side). In this embodiment, the mixing tube 31 is formed as a hole extending along the axis O, passing through the upstream end face 21 and downstream end face 22 of the burner plate 20. The mixing tube 31 extends linearly along the axis O and has the same inner diameter within the axis O direction. The inner side of the mixing tube 31 forms a flow path with one side along the axis O as the upstream side and the other side along the axis O as the downstream side. Multiple mixing tubes 31 are arranged side by side at intervals along a direction orthogonal to the axis O.

[0051] Multiple fuel supply pipes 32 are provided in a one-to-one relationship with each mixing pipe 31. The fuel supply pipes 32 supply main fuel F1 into the mixing pipes 31. The main fuel F1 supplied into the mixing pipes 31 mixes with the air A flowing in the mixing pipes 31 to generate a premixed gas M. Furthermore, the opening of the mixing pipe 31 (the opening of the main nozzle 30) at the downstream end face 22 of the burner plate 20 becomes the outlet of the premixed gas M.

[0052] The fuel supply pipe 32 is a tubular component extending along the axis O, with one end fixed to the end cap 11. The fuel supply pipe 32 communicates with the first fuel manifold 12 within the end cap 11 on one side of the axis O. Main fuel F1 is introduced from the first fuel manifold 12 into the fuel supply pipe 32. The other end of the fuel supply pipe 32 on the other side of the axis O is inserted from the upstream end face 21 of the burner plate 20 in the mixing pipe 31. That is, the fuel-ejecting tip of the fuel supply pipe 32 is located within the mixing pipe 31.

[0053] <Pilot Nozzle>

[0054] Pilot nozzle 40 injects pilot fuel F2 from downstream end face 22.

[0055] The pilot nozzle 40 is a tubular component extending along the axis O, with one end fixed to the end cap 11 on one side of the axis O direction. The pilot nozzle 40 communicates with the second fuel manifold 13 inside the end cap 11 on one side of the axis O direction. Pilot fuel F2 is introduced from the second fuel manifold 13 into the pilot nozzle 40.

[0056] The portion of the pilot nozzle 40 on the other side of the axis O direction penetrates the burner plate 20 within the range of the upstream end face 21 and the downstream end face 22. The front end of the pilot nozzle 40, which is the end on the other side of the axis O direction, is located at the same position as the downstream end face 22 in the axis O direction. Thus, the pilot nozzle 40 can spray fuel from the downstream end face 22 of the burner plate 20. Multiple pilot nozzles 40 are provided at intervals in a direction orthogonal to the axis O.

[0057] <Nozzle Section>

[0058] In this embodiment, such as Figure 3 As shown, a nozzle section S is formed by assembling and arranging multiple main nozzles 30. The nozzle section S is a bundle formed by assembling and arranging multiple main nozzles 30. When viewing the downstream end face 22 of the burner plate 20 from the downstream side, the nozzle section S can be identified as the area formed by the assembly of openings of the main nozzles 30.

[0059] In this embodiment, multiple nozzle segments S are arranged at intervals in a direction orthogonal to the axis O. In each nozzle segment S, adjacent main nozzles 30 are spaced closer together. The interval between nozzle segments S is larger than the interval between adjacent main nozzles 30 in each nozzle segment S. The region between the nozzle segments S that forms such intervals is called a segmentation region D. The segmentation region D extends in a strip or line shape along the downstream end face 22 in a direction orthogonal to the axis O, separating adjacent nozzle segments S from each other. As described above, the width of the segmentation region D (the dimension of the segmentation region D on the downstream end face 22 orthogonal to the extension direction) is larger than the interval between the main nozzles 30 in each segment. Therefore, the segmentation region D can be easily visually confirmed by observing the downstream end face 22.

[0060] In this embodiment, the nozzle section S has a central section S1 and an outer peripheral section S2.

[0061] The central section S1 is formed by main nozzles 30 arranged in the center of the burner plate 20 including axis O. That is, the central section S1 is located in the center of the burner plate 20.

[0062] The outer peripheral side section S2 is formed by the main nozzles 30 arranged radially outward from the central section S1 in the burner plate 20. Multiple outer peripheral side sections S2 are arranged at intervals (five in this embodiment) radially outward from the central section S1, separated by a dividing region D. Multiple outer peripheral side sections S2 are arranged at intervals in the circumferential direction. Adjacent outer peripheral side sections S2 are arranged at intervals separated by the dividing region D.

[0063] The region between the central segment S1 and the outer peripheral segment S2 in the segmented region D, which separates them, is called the annular region D1. The annular region D1 extends in a ring shape, surrounding the axis O.

[0064] The regions in the segmented region D that separate adjacent peripheral segments S2 from each other are called radial regions D2. Multiple radial regions D2 are arranged radially (five in this embodiment) extending radially along axis O. The radially inner end of each radial region D2 connects to the annular region D1. The radially outer end of each radial region D2 connects to the outer periphery of the burner plate 20.

[0065] <Configuration of the second nozzle>

[0066] like Figure 3 As shown, multiple pilot nozzles 40, which serve as the second nozzle, are distributed in such a way that they inject pilot fuel F2 from the segmented region D in the downstream end face 22. That is, the pilot nozzles 40 are arranged in such a way that they penetrate the region between adjacent nozzle segments S in the burner plate 20. Furthermore, the tip of the pilot nozzle 40 that injects pilot fuel F2 is located within the segmented region D.

[0067] In this embodiment, the pilot nozzle 40 injects fuel from the connection points where the circumferential region in the segmented region D connects to each radial region D2. That is, the front ends of the pilot fuel F2 injected from the pilot nozzle 40 are respectively distributed at the aforementioned multiple connection points.

[0068] <Effects>

[0069] The operation and effects of the burner 3 in this embodiment will be explained next.

[0070] like Figure 2 As shown, during the operation of the gas turbine 1, air A enters each mixing pipe 31 of the main nozzle 30 from the upstream side, and flows downstream within the mixing pipe 31. When main fuel F1 is supplied into the mixing pipe 31 from the front end of the fuel supply pipe 32 in this state, air A mixes with main fuel F1 within the mixing pipe 31 to generate premixed gas M. The premixed gas M is injected from the opening of the mixing pipe 31 in the downstream end face 22 of the burner plate 20, i.e., the opening of the main nozzle 30.

[0071] On the other hand, such as Figure 4As shown, when pilot fuel F2 is injected from the tip of the pilot nozzle 40 on the downstream end face 22, the pilot fuel F2 ignites, thereby generating a pilot flame P as a diffusion flame. The premixed gas M ejected from the main nozzle 30 burns starting from this pilot flame P, thereby generating a main flame F as a premixed flame. Furthermore, under the action of the pilot flame P of the pilot nozzle 40, the flame stability of the main flame F is ensured, and a stable combustion reaction is sustained. The combustion gas C generated through this combustion is sent to the turbine 4.

[0072] In this embodiment, multiple pilot nozzles 40 are distributed in a dispersed manner within the segmented region D. Therefore, it is possible to maintain overall flame stability of the multiple main nozzles 30 while reducing the size of the pilot flame P formed by the pilot nozzles 40. Furthermore, with the reduction in the size of the pilot flame P, the flame length of the main flame F becomes shorter, burnout is improved, and the generation of unburned fuel is suppressed. As a result, flame stability as a whole in the burner 3 can be ensured.

[0073] In addition, instead of increasing the size of a single pilot nozzle 40, smaller pilot nozzles 40 are distributed in the segmented area D, thereby avoiding encroachment on the installation area of ​​the main nozzle 30.

[0074] If increasing the diameter of the pilot nozzle 40 results in a smaller installation area for the main nozzle 30, then the number of mixing tubes 31 will correspondingly decrease. In this case, the pressure drop of air A increases, resulting in a reduction in the performance of the burner 3.

[0075] In this embodiment, by distributing multiple pilot nozzles 40 in the segmented area D where the main nozzle 30 was not initially configured, the installation space for the main nozzle 30 can be ensured as before. Therefore, the performance of the burner 3 can be maintained.

[0076] Furthermore, in this embodiment, the pilot nozzle 40 is configured to inject fuel from the connection point where the annular region D1 and the radial region D2 are connected in the segmented region D. Therefore, the pilot flame P of the pilot nozzle 40 can be used to ensure the flame stability of the three nozzle segments S that are in contact with the connection point. That is, the flame stability of multiple nozzle segments S can be ensured by using one pilot nozzle 40, thus enabling efficient use of the installation space.

[0077] <Second Implementation>

[0078] Next, refer to Figure 5 The second embodiment of the present invention will be described. In the second embodiment, the same reference numerals are used to mark the same components as in the first embodiment, and detailed descriptions are omitted.

[0079] In the second embodiment, the location of the pilot nozzle 40 is different from that in the first embodiment.

[0080] That is, in the second embodiment, multiple pilot nozzles 40 are provided at intervals along the extension direction of the annular region D1 of the segmented region D. In other words, multiple pilot nozzles 40 are provided not only at the connection point where the annular region D1 connects to the radial region D2, but also in the portion between adjacent connection points in the annular region D1 (three in this embodiment).

[0081] Furthermore, in the radial region D2 of the segmented region D, a plurality of pilot nozzles 40 are provided at intervals along the extending direction of the radial region D2.

[0082] Furthermore, in this embodiment, an outer peripheral region R, radially outer of the outer peripheral section S2 in the downstream end face 22 of the burner plate 20, is also provided as a third nozzle for injecting pilot fuel F2, with an outer peripheral pilot nozzle 41. The outer peripheral region R is the ineffective space between the outer peripheral section S2 and the outer peripheral edge of the burner plate 20. In this edge, a plurality of outer peripheral pilot nozzles 41 are provided at intervals in the circumferential direction.

[0083] In the second embodiment, multiple pilot nozzles 40 are distributed in a mesh pattern within the entire area of ​​the segmented region D, thereby expanding the flame stabilization region within the multiple nozzle segments S. Therefore, the flame length of the main flame F can be further shortened, and the generation of unburned portions can be suppressed.

[0084] Furthermore, by setting the peripheral pilot nozzle 41 not only in the segmented region D but also in the outer peripheral section S2 in such ineffective spaces, it is possible to further improve the flame stability of the nozzle section S as a whole while maintaining the performance of the burner 3.

[0085] Next, refer to Figure 6 The third embodiment of the present invention will be described. In the third embodiment, the same reference numerals are used to mark the same components as in the first embodiment, and detailed descriptions are omitted.

[0086] In the third embodiment, the inner pilot nozzle 42, which serves as the fourth nozzle, is disposed in the region within the nozzle section S.

[0087] That is, the inner pilot nozzle 42 is configured to inject fuel from the region inside the outer peripheral section S2 of the nozzle section S.

[0088] In this embodiment, because multiple pilot nozzles 40 are distributed in the segmented region D, the diameter of the inner pilot nozzles 42 disposed within the nozzle section S can be reduced. Therefore, the flame stability of the main nozzle 30 inside the nozzle section S can be ensured without significantly encroaching on the area of ​​the main nozzle 30. That is, the flame stability of the main nozzle 30 located far from the segmented region D can be particularly ensured, and the flame length of the main flame F is shortened, further reducing the generation of unburned portions.

[0089] Next, refer to Figure 7 as well as Figure 8 The fourth embodiment of the present invention will be described. In the fourth embodiment, the same reference numerals are used to refer to the same constituent elements as in the first embodiment, and detailed descriptions are omitted.

[0090] In the fourth embodiment, the fuel concentration in the main nozzles 30 of each nozzle section S is different from that in each other.

[0091] Here, the main nozzle 30 of each nozzle section S that is adjacent to the segmented region D is designated as the outer nozzle 30A, and the main nozzle 30 that is located inside the nozzle section S (not adjacent to the segmented region D) is designated as the inner nozzle 30B.

[0092] In this embodiment, the fuel concentration of the premixed gas M ejected from the outer nozzle 30A is set to be higher than the fuel concentration of the premixed gas M ejected from the inner nozzle 30B. This fuel concentration setting can be achieved, for example, by appropriately providing a throttling orifice in the first fuel manifold 12 and adjusting the flow rate of the main fuel F1 supplied to each fuel supply pipe 32. Alternatively, it can be appropriately set by providing a throttling orifice in the fuel supply pipe 32 or by changing the diameter of the fuel supply pipe 32.

[0093] With this structure, the combustion reaction of the main flame F of the outer nozzle 30A adjacent to the segmented region D is promoted. Therefore, the main flame F, which originates from the pilot flame P of the pilot nozzle 40 located in the segmented region D, can be shifted upstream. As a result, the flame length of the main flame F can be shortened, and the generation of unburned portions can be further suppressed.

[0094] <Other Implementation Methods>

[0095] The embodiments of the present invention have been described above, but the present invention is not limited thereto and can be appropriately modified without departing from the technical concept of the invention.

[0096] For example, the structure of the main nozzle 30, which has a mixing pipe 31 and a fuel supply pipe 32, has been described, but it is also possible to have a structure in which the main fuel F1 is injected from the inner circumferential surface of the mixing pipe 31 instead of the fuel supply pipe 32.

[0097] For example, here is... Figure 9 As shown in the modified examples, the burner plate 20 in each embodiment can also be composed of multiple segments 25 when viewed from the axis O. The boundaries between each segment 25 are called dividing lines. Each segment 25 is provided with a nozzle section S, and the dividing region D is the region including the dividing lines between the segments 25. Therefore, the pilot nozzle 40 is arranged on the dividing lines in a manner that it is sandwiched between adjacent segments 25. By arranging the pilot nozzle 40 between the dividing lines between each segment 25 in this way, the burner 3 can be easily assembled. In addition, the fuel system can be easily changed for each nozzle section S, thus increasing the degree of freedom in the combustion scheme.

[0098] For example, in the first embodiment, an example is described in which the pilot nozzle 40 is arranged at all the connection points connecting the annular region D1 and the radial region D2 in the segmented region D, but this is not a limitation. The pilot nozzle 40 may also be arranged only at a portion of the multiple connection points.

[0099] For example, in the second embodiment, an example is described in which multiple pilot nozzles 40 are provided in both the annular region D1 and the radial region D2 within the segmented region D, but this is not a limitation. For example, it is also possible to have a structure in which at least one of the annular region D1 and the radial region D2 is provided with pilot nozzles 40. That is, pilot nozzles 40 can be distributed in a dispersed manner in at least one of the annular region D1 and the radial region D2.

[0100] In the third embodiment, the inner pilot nozzle 42, which serves as the fourth nozzle, is provided only in the outer peripheral section S2. However, it is also possible that the inner pilot nozzle 42 is provided in the area within the central section S1. Alternatively, the inner pilot nozzle 42 may not be provided in the area within the outer peripheral section S2, but may be provided only in the area within the central section S1.

[0101] In the fourth embodiment, the fuel concentration of the outer nozzle 30A is higher than that of the inner nozzle 30B, but this is not a limitation. For example, the main fuel F1 of the outer nozzle 30A and the main fuel F1 of the inner nozzle 30B may be different types of fuel, with the main fuel F1 of the outer nozzle 30A being a more flammable fuel than that of the inner nozzle 30B. For example, the hydrogen ratio of the fuel in the outer nozzle 30A may be increased compared to that in the inner nozzle 30B. As a result, the combustion reaction of the main flame F in the outer nozzle 30A is also promoted, thus achieving the same effect as in the fourth embodiment.

[0102] Alternatively, the structure can be configured as follows: the pilot fuel F2 of the pilot nozzle 40 can be set to a more flammable type of fuel, thereby further ensuring flame stability.

[0103] <Postscript>

[0104] The burner 3 and gas turbine 1 described in each embodiment are as follows, for example.

[0105] (1) The burner 3 of the first embodiment has: a burner plate 20 having a downstream end face 22 orthogonal to the burner axis O; a nozzle section S configured by a plurality of first nozzles 30 that inject a premixed gas M of air A and fuel from the downstream end face 22; and a plurality of second nozzles 40 that inject fuel from the downstream end face 22. The nozzle section S is provided with a plurality of nozzles spaced apart from each other in a direction orthogonal to the burner axis O, and each second nozzle 40 injects the fuel from a partition region D between the nozzle sections S in the downstream end face 22.

[0106] With this structure, a premixed flame generated by the first nozzle 30 is formed, starting from the diffused flame of the second nozzle 40. In this design, multiple second nozzles 40 are dispersedly arranged in the segmented region D, thus reducing the size of the diffused flame and improving flame stability. Furthermore, the second nozzles 40 are positioned in the ineffective space between nozzle segments S, therefore they do not encroach on the installation area of ​​the first nozzle 30. Thus, a reduction in the performance of the burner 3 can be avoided.

[0107] (2) The burner 3 of the second embodiment may also be based on the burner 3 of the first embodiment, and as the nozzle section S, it includes: a central section S1, which is disposed in the central part of the burner plate 20 including the burner axis O; and a plurality of peripheral side sections S2, which are spaced apart radially outside the burner axis O of the central section S1 and are arranged spaced apart from each other in the circumferential direction of the burner axis O. The segmented region D includes: an annular region D1, which is the region between the central section S1 and the plurality of peripheral side sections S2 and extends in an annular shape surrounding the burner axis O; and a radial region D2, which is the region between the adjacent peripheral side sections S2 and extends radially along the burner axis O.

[0108] By dispersing the second nozzle 40 in a segmented region D with an annular region D1 and a radial region D2, it is possible to maintain the performance of the burner 3 while improving flame stability.

[0109] (3) The burner 3 of the third scheme can also be based on the burner 3 of the second scheme, in which the second nozzle 40 injects the fuel from the connection part where the annular region D1 and the radial region D2 are connected in the segmented region D.

[0110] Therefore, the flame stability of multiple nozzle sections S adjacent to these connection points can be ensured by using the second nozzle 40 disposed at the connection point.

[0111] (4) The burner 3 of the fourth scheme may be based on the burner 3 of the second or third scheme, wherein the second nozzle 40 is arranged in a plurality of such nozzles along the extension direction of at least one of the annular region D1 and the radial region D2 of the segmented region D.

[0112] By arranging multiple second nozzles 40 along the extension direction of the segmented region D, the flame stability of the first nozzle 30 can be guaranteed over a large area of ​​the nozzle section S.

[0113] (5) The fifth embodiment of the burner 3 may be based on the burner 3 of any one of the second to fourth embodiments, and the burner 3 may also have a third nozzle 41 for injecting fuel from the outer peripheral region R of the outer peripheral section S2 in the downstream end face 22.

[0114] By setting a third nozzle 41 not only in the segmented region D but also in the outermost peripheral side of the outer peripheral section S2, the flame stability of the nozzle section S as a whole can be further improved while maintaining the performance of the burner 3.

[0115] (6) The burner 3 of the sixth embodiment may also be based on the burner 3 of any one of the second to fifth embodiments, and the burner 3 may further include a fourth nozzle 42 for injecting fuel from the area within the nozzle section S in the downstream end face 22.

[0116] This ensures the flame stability of the first nozzle 30, which is far from the segmentation region D.

[0117] (7) The burner 3 of the seventh scheme can also be based on the burner 3 of any one of the first to sixth schemes, wherein the fuel concentration of the first nozzle 30 of the plurality of first nozzles 30 in the nozzle section S that is adjacent to the segmented region D is higher than the fuel concentration of the other first nozzles 30 of the plurality of first nozzles 30 in the nozzle section S.

[0118] As a result, the combustion reaction of the premixed flame in the first nozzle 30 adjacent to the segmented region D is promoted. Consequently, the premixed flame, originating from the diffused flame of the second nozzle 40 located in the segmented region D, shifts upstream, and the flame length becomes shorter. As a result, the generation of unburned portions is suppressed, and flame stability is ensured.

[0119] (8) The burner 3 of the eighth scheme may be based on the burner 3 of any one of the first to seventh schemes, wherein the fuel of the first nozzle 30 of the plurality of first nozzles 30 of the nozzle section S that is arranged adjacent to the segmented region D is a type of fuel that is more flammable than the fuel of the other first nozzles 30 of the plurality of first nozzles 30 of the nozzle section S.

[0120] As a result, similar to (7), the combustion reaction of the premixed flame of the first nozzle 30 adjacent to the segmented region D is promoted, resulting in the suppression of the generation of unburned parts and the guarantee of flame stability.

[0121] (9) The burner 3 of the ninth scheme can also be based on the burner 3 of any one of the first to eighth schemes, wherein the burner plate 20 is composed of multiple segments 25 when viewed from the axis O of the burner 3, and each segment 25 is provided with the nozzle section S, and the segmented area D is the area including the dividing line between the segments 25.

[0122] The second nozzle 40 can be arranged between the dividing lines of each segment 25, thus facilitating the assembly of the burner 3. Furthermore, the fuel system can be easily modified for each nozzle section S, thereby increasing the flexibility of the combustion scheme.

[0123] (10) The gas turbine 1 of the tenth embodiment includes: a compressor 2 that generates air A; a combustor 3 of any one of the first to ninth embodiments that combusts a premixed gas M generated by mixing fuel in the air A compressed by the compressor 2 to generate combustion gas C; and a turbine 4 that is driven by the combustion gas C.

[0124] Explanation of reference numerals in the attached figures

[0125] 1. Gas turbine

[0126] 2. Compressor

[0127] 3. Burner

[0128] 4. Turbine

[0129] 10 outer cylinder

[0130] 11 End caps

[0131] 12 First Fuel Manifold

[0132] 13 Second Fuel Manifold

[0133] 15 Inner cylinder

[0134] 17 Support section

[0135] 20 Burner Plate

[0136] 21. Upstream end face

[0137] 22 Downstream end face

[0138] 25 segments

[0139] 30 Main Nozzle

[0140] 30A Outer Nozzle

[0141] 30B Inner Nozzle

[0142] 31 Mixing tube

[0143] 32 Fuel supply pipe

[0144] 40 Pilot Nozzle

[0145] 41 Peripheral pilot nozzle

[0146] 42 Inner pilot nozzle

[0147] S Nozzle Section

[0148] S1 Central Section

[0149] S2 peripheral section

[0150] D. Segmentation Region

[0151] D1 Circular Area

[0152] D2 Radial Region

[0153] R peripheral region

[0154] F Main Flame

[0155] P pilot flame

[0156] F1 Main Fuel

[0157] F2 pilot fuel

[0158] A air

[0159] M premixed gas

[0160] C Combustion Gas

[0161] O axis

[0162] F1 Main Fuel

[0163] F2 pilot fuel.

Claims

1. A burner, wherein, The burner has: The burner plate has a downstream end face orthogonal to the burner axis; The nozzle section is configured by a plurality of first nozzles arranged to generate a premixed flame by injecting a premixed gas of air and fuel from the downstream end face side; as well as Multiple second nozzles inject fuel from the downstream end face to generate a diffuse flame. The nozzle sections are arranged in multiple intervals in a direction orthogonal to the burner axis. The end of each of the second nozzles on the downstream end face is located in a segmented region within the downstream end face formed between the plurality of nozzle segments and arranged such that adjacent nozzle segments are spaced apart.

2. The burner according to claim 1, wherein, The nozzle section includes: The central section, which is disposed in the central portion of the burner plate including the burner axis; and Multiple peripheral side sections are arranged radially spaced apart from each other on the burner axis of the central section and circumferentially spaced apart from each other. The segmented region includes: An annular region, which is the area between the central section and the plurality of the outer peripheral sections and extends in an annular shape surrounding the burner axis; and The radial region is the area between adjacent peripheral side sections and extends radially along the burner axis.

3. The burner according to claim 2, wherein, The second nozzle injects the fuel from the connection point where the annular region and the radial region in the segmented region are connected.

4. The burner according to claim 2 or 3, wherein, The second nozzles are arranged in a plurality of such nozzles along the extension direction of at least one of the annular region and the radial region of the segmented region.

5. The burner according to claim 2 or 3, wherein, The burner also includes a third nozzle for injecting fuel from the radially outer peripheral region of the outer peripheral section in the downstream end face.

6. The burner according to claim 2 or 3, wherein, The burner also includes a fourth nozzle for injecting fuel from a region within the nozzle section of the downstream end face.

7. The burner according to any one of claims 1 to 3, wherein, The fuel concentration of the first nozzle among the plurality of first nozzles in the nozzle section that is adjacent to the segmented region is higher than the fuel concentration of the other first nozzles among the plurality of first nozzles in the nozzle section.

8. The burner according to any one of claims 1 to 3, wherein, The fuel of the first nozzle among the plurality of first nozzles in the nozzle section that is disposed adjacent to the segmented area is a type of fuel that is more flammable than the fuel of the other first nozzles among the plurality of first nozzles in the nozzle section.

9. The burner according to any one of claims 1 to 3, wherein, The burner plate is composed of multiple segments when viewed from the burner's axial direction. Each of the aforementioned segments is provided with a nozzle section. The segmented region is the area that includes the dividing lines between the segmented elements.

10. A gas turbine, wherein, The gas turbine includes: A compressor, which generates air; The burner according to any one of claims 1 to 3, wherein a premixed gas generated by mixing fuel with compressed air in a compressor is combusted to generate combustion gases; and A turbine, which is driven by the combustion gases.

11. A burner, wherein, The burner has: The burner plate has a downstream end face orthogonal to the burner axis; The nozzle section is configured by a plurality of first nozzles that inject a premixed gas of air and fuel from the downstream end face side; as well as Multiple second nozzles inject fuel from the downstream end face. The nozzle sections are arranged in multiple intervals in a direction orthogonal to the burner axis. The burner plate is composed of multiple segments when viewed from the burner's axial direction. Each of the aforementioned segments is provided with a nozzle section. Each of the second nozzles injects the fuel from the segmented area between the nozzle sections in the downstream end face. The segmented region is the area that includes the dividing lines between the segmented elements.

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