Combustor and gas turbine

Abstract

To provide a combustor capable of improving flame stability while maintaining performance of the combustor, and a gas turbine.SOLUTION: A combustor has: a combustor plate having a downstream end surface perpendicular to a combustor axial line; a nozzle segment in which a plurality of first nozzles for injecting premixed gas of air and fuel from a downstream end surface side is collectively arranged; and a second nozzle that injects fuel from the downstream end surface. A plurality of nozzle segments is provided at intervals from each other in a direction perpendicular to the combustor axial line. The second nozzle injects fuel from a divided region between the nozzle segments on the downstream end surface.SELECTED DRAWING: Figure 3

Description

[Technical field]

[0001] The present disclosure relates to combustors and gas turbines. [Background technology]

[0002] For example, Patent Document 1 discloses a cluster combustor as an example of a combustor used in a gas turbine.

[0003] The cluster combustor has main nozzles (first nozzles) arranged in parallel to each other and injecting a premixed gas of air and fuel, and pilot nozzles (second nozzles) that generate a pilot flame for flame stabilization. A plurality of main nozzles are arranged together to form a nozzle segment. The nozzle segments are arranged in a ring shape, and a pilot nozzle is provided at the center of the ring. The pilot flame from the pilot nozzle ensures the flame stabilization of the main flame from each main nozzle. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] US Patent Application Publication No. 2014 / 0116054 Summary of the Invention [Problem to be solved by the invention]

[0005] However, in the above-mentioned combustor, the flame stability may be deteriorated depending on the fuel and the operating conditions. Furthermore, simply increasing the diameter of the pilot nozzle in order to ensure flame stability entails an increase in the installation area of ​​the main nozzle, resulting in a problem of reduced combustor performance.

[0006] The present disclosure has been made to solve the above-mentioned problems, and has an object to provide a combustor and a gas turbine that can improve flame stability while maintaining combustor performance. [Means for solving the problem]

[0007] In order to achieve the above object, a combustor according to the present disclosure includes a combustor plate having a downstream end face intersecting a combustor axis, a nozzle segment including a plurality of first nozzles arranged in a collective arrangement to generate a premixed flame by injecting a premixed gas of air and fuel from the downstream end face, and a plurality of second nozzles arranged to generate a diffusion flame by injecting fuel from the downstream end face, wherein the nozzle segments are provided at intervals from each other in a direction intersecting the combustor axis, and an end portion of each of the second nozzles on the downstream end face side has A plurality of the above The nozzle segments are formed with a gap therebetween and are located at a dividing region in the downstream end surface interposed between adjacent nozzle segments such that adjacent nozzle segments are spaced apart. A combustor according to the present disclosure includes: a combustor plate having a downstream end surface intersecting a combustor axis; a nozzle segment including a plurality of first nozzles arranged collectively to inject a premixed gas of air and fuel from the downstream end surface; and a plurality of second nozzles arranged collectively to inject fuel from the downstream end surface. the plurality of nozzle segments are provided at intervals in a direction intersecting the combustor axis, the combustor plate is composed of a plurality of partitions divided into a plurality of partitions as viewed from the combustor axis direction, the nozzle segment is provided in each of the partitions, each of the second nozzles injects the fuel from a partition region between the nozzle segments in the downstream end face, and the partition region includes a partition line between the partitions.

[0008] The gas turbine according to the present disclosure includes a compressor that generates air, the above-mentioned combustor that generates combustion gas by burning a premixed gas generated by mixing fuel with the air compressed by the compressor, and a turbine driven by the combustion gas. Effect of the Invention

[0009] According to the combustor and gas turbine of the present disclosure, it is possible to improve flame stability while maintaining the combustor performance. [Brief description of the drawings]

[0010] [Figure 1] FIG. 1 is a schematic diagram showing a schematic configuration of a gas turbine according to a first embodiment of the present disclosure. [Diagram 2] FIG. 1 is a vertical cross-sectional view showing a schematic configuration of a combustor according to a first embodiment of the present disclosure. [Diagram 3] FIG. 2 is a view of a downstream end surface of a combustor plate of the combustor according to the first embodiment of the present disclosure, as viewed from the downstream side. [Figure 4] FIG. 2 is a longitudinal cross-sectional view of a main portion of a combustor plate of the combustor according to the first embodiment of the present disclosure. [Diagram 5] FIG. 11 is a view of a downstream end surface of a combustor plate of a combustor according to a second embodiment of the present disclosure, as viewed from the downstream side. [Figure 6] FIG. 11 is a view of a downstream end surface of a combustor plate of a combustor according to a third embodiment of the present disclosure, as viewed from the downstream side. [Figure 7] FIG. 11 is a view of a downstream end surface of a combustor plate of a combustor according to a fourth embodiment of the present disclosure, as viewed from the downstream side. [Figure 8] FIG. 11 is a longitudinal cross-sectional view of a main portion of a combustor plate of a combustor according to a fourth embodiment of the present disclosure. [Figure 9] FIG. 13 illustrates a modification of a combustor plate of a combustor according to an embodiment of the present disclosure. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0011] First Embodiment Hereinafter, a first embodiment of the present invention will be described in detail with reference to FIGS. As shown in FIG. 1, a gas turbine 1 according to this embodiment has a compressor 2 that compresses air A, a combustor 3 that generates combustion gas C, and a turbine 4 driven by the combustion gas C. A plurality of combustors 3 are provided at intervals in the circumferential direction around the rotating shaft of the gas turbine 1. The combustors 3 mix fuel with the air A compressed by the compressor 2, combust the air, and generate high-temperature and high-pressure combustion gas C.

[0012] <Combustor> The configuration of the combustor 3 will be described below with reference to FIGS. As shown in FIG. 2, the combustor 3 includes an outer casing 10, an end cover 11, an inner casing 15, a support portion 17, a combustor plate 20, a main nozzle 30 as a first nozzle, and a pilot nozzle 40 as a second nozzle.

[0013] <Outer cylinder> The tubular body has a cylindrical shape centered on a combustor axis O (hereinafter simply referred to as the axis O) which is the center of the combustor 3.

[0014] <End cover> The end cover 11 is disk-shaped and closes one end of the external cylinder 10 in the axial O direction (the left side in FIG. 2). The end cover 11 is in contact with the one end of the external cylinder 10 in the axial O direction. A first fuel header 12 and a second fuel header 13 are formed inside the end cover 11 as spaces. A main fuel F1 as a first fuel is supplied from the outside to the first fuel header 12. A pilot fuel F2 as a second fuel is supplied from the outside to the second fuel header 13. As the main fuel F1 and the pilot fuel F2, for example, hydrogen, natural gas, or a mixed fuel of these is used.

[0015] <Inner cylinder> The inner cylinder 15 is disposed coaxially inside the outer cylinder 10. The inner cylinder 15 has a cylindrical shape extending in the direction of the axis O inside the outer cylinder 10. One end of the inner cylinder 15 in the direction of the axis O is separated from the end cover 11 in the direction of the axis O. The outer diameter of the inner cylinder 15 is smaller than the outer diameter of the inner cylinder 15. As a result, an annular flow path is formed between the outer peripheral surface of the inner cylinder 15 and the inner peripheral surface of the outer cylinder 10. Air A compressed by the compressor 2 flows through this flow path from the other side in the direction of the axis O (the right side in FIG. 2) toward the one side in the direction of the axis O.

[0016] <Support part> The support parts 17 are members extending in the direction of the axis O, and a plurality of them are provided at intervals in the circumferential direction. An end of each support part 17 on one side in the direction of the axis O is fixed to a surface of an end plate facing the other side in the direction of the axis O on the inner peripheral side of the outer cylinder 10. Air A that has flowed between the outer cylinder 10 and the inner cylinder 15 on one side in the direction of the axis O reverses its flow direction to the other side in the direction of the axis O when passing between adjacent support parts 17.

[0017] <Combustor plate> The combustor plate 20 has a disk shape centered on an axis O. The combustor plate 20 is provided so as to be coaxially fitted inside the inner cylinder 15. The combustor plate 20 has an upstream end surface 21 and a downstream end surface 22.

[0018] <Upstream end face> The upstream end face 21 is an end face of the combustor plate 20 facing one side in the direction of the axis O, and has a planar shape perpendicular to the axis O. The upstream end face 21 is disposed at the same position in the direction of the axis O as the end face of the inner cylinder 15 on one side in the direction of the axis O.

[0019] <Downstream end face> The downstream end surface 22 is an end surface of the combustor plate 20 facing the other side in the direction of the axis O, and has a planar shape perpendicular to the axis O. The downstream end surface 22 is located on one side in the direction of the axis O with respect to the end surface of the inner cylinder 15 on the other side in the direction of the axis O. As a result, a space is defined by the inner circumferential surface of the inner cylinder 15 and the downstream end surface 22 of the combustor plate 20. This space is used as a combustion space of the combustor 3.

[0020] <Main nozzle> As shown in Figures 2 and 3, the main nozzle 30 forms a main flame F by ejecting a premixed gas M of air A and a main fuel F1 further downstream (the other side in the direction of the axis O, the right side in Figure 2) from the downstream end surface 22 of the combustor plate 20. A plurality of main nozzles 30 are provided, and each main nozzle 30 is composed of a mixing tube 31 and a fuel supply tube 32.

[0021] The mixing tube 31 is a tube extending in the direction of the axis O, into which air A flows in from the upstream side (one side in the direction of the axis O, the left side in FIG. 2). The mixing tube 31 in this embodiment is formed as a hole extending in the direction of the axis O so as to penetrate from the upstream end face 21 to the downstream end face 22 of the combustor plate 20. The mixing tube 31 extends linearly in the direction of the axis O, and has a uniform inner diameter along the direction of the axis O. The inside of the mixing tube 31 is a flow path in which one side in the direction of the axis O is the upstream side and the other side in the direction of the axis O is the downstream side. A plurality of mixing tubes 31 are arranged side by side at intervals from each other in a direction perpendicular to the axis O.

[0022] A plurality of fuel supply pipes 32 are provided in a one-to-one relationship corresponding to each mixing tube 31. The fuel supply pipes 32 supply main fuel F1 into the mixing tube 31. The main fuel F1 supplied into the mixing tube 31 is mixed with air A flowing inside the mixing tube 31 to generate premixed gas M. An opening of the mixing tube 31 (an opening of the main nozzle 30) on the downstream end surface 22 of the combustor plate 20 serves as an outlet for the premixed gas M.

[0023] The fuel supply pipe 32 is a tubular member extending in the direction of the axis O, and one end of the fuel supply pipe 32 in the direction of the axis O is fixed to the end cover 11. The fuel supply pipe 32 is connected to the inside of the first fuel header 12 in the end cover 11 at one side in the direction of the axis O. The main fuel F1 is introduced into the fuel supply pipe 32 from the first fuel header 12. The other end of the fuel supply pipe 32 in the direction of the axis O is inserted into the mixing tube 31 from the upstream end face 21 side of the combustor plate 20. In other words, the tip of the fuel supply pipe 32 from which fuel can be ejected is located inside the mixing tube 31.

[0024] <Pilot nozzle> The pilot nozzle 40 injects pilot fuel F2 from the downstream end face 22. The pilot nozzle 40 is a tubular member extending in the direction of the axis O, and has one end portion in the direction of the axis O fixed to the end cover 11. The pilot nozzle 40 is connected to the inside of the second fuel header 13 in the end cover 11 on one side in the direction of the axis O. Pilot fuel F2 is introduced into the pilot nozzle 40 from the second fuel header 13.

[0025] The portion of the pilot nozzle 40 on the other side in the direction of the axis O penetrates the combustor plate 20 between the upstream end face 21 and the downstream end face 22. A tip, which is the end of the pilot nozzle 40 on the other side in the direction of the axis O, is positioned at the same position in the direction of the axis O as the downstream end face 22. This enables the pilot nozzle 40 to eject fuel from the downstream end face 22 of the combustor plate 20. The multiple pilot nozzles 40 are provided at intervals in a direction perpendicular to the axis O.

[0026] <Nozzle segment> In this embodiment, as shown in Fig. 3, a plurality of main nozzles 30 are arranged together to form a nozzle segment S. The nozzle segment S is a bundle formed by arranging a plurality of main nozzles 30 together. When the downstream end surface 22 of the combustor plate 20 is viewed from the downstream side, the nozzle segment S can be confirmed as a region where the openings of the main nozzles 30 are gathered together.

[0027] In this embodiment, a plurality of nozzle segments S are provided at intervals in a direction perpendicular to the axis O. In each nozzle segment S, the interval between adjacent main nozzles 30 is narrow. The interval between the nozzle segments S is larger than the interval between adjacent main nozzles 30 in each nozzle segment S. The area between the nozzle segments S forming the interval between such nozzle segments S is defined as a divided area D. The divided area D extends in a strip or line shape in a direction perpendicular to the axis O along the downstream end surface 22 so as to divide the adjacent nozzle segments S. As described above, the width of the divided area D (the dimension on the downstream end surface 22 perpendicular to the extension direction of the divided area D) is larger than the interval between the main nozzles 30 in each segment. Therefore, the divided area D can be easily visually recognized by looking at the downstream end surface 22.

[0028] In this embodiment, the nozzle segments S include a central segment S1 and an outer circumferential segment S2. The central segment S1 is formed by the main nozzles 30 collectively arranged in the central portion of the combustor plate 20 including the axis O. That is, the central segment S1 is arranged in the center of the combustor plate 20.

[0029] The outer periphery side segment S2 is formed by the main nozzles 30 collectively arranged radially outside the central segment S1 of the combustor plate 20. A plurality of outer periphery side segments S2 (five in this embodiment) are arranged radially outside the central segment S1 at intervals via a dividing region D. A plurality of outer periphery side segments S2 are provided at intervals in the circumferential direction. Adjacent outer periphery side segments S2 are arranged at intervals via the dividing region D.

[0030] The region between the central segment S1 and the outer circumferential segment S2 in the divided region D that divides them is defined as an annular region D1. The annular region D1 extends annularly so as to surround the axis O. A region that divides the adjacent outer periphery side segments S2 in the divided region D is defined as a radial region D2. A plurality of radial regions D2 (five in this embodiment) are provided radially so as to extend in the radial direction of the axis O. A radially inner end of each radial region D2 is connected to the annular region D1. A radially outer end of each radial region D2 is connected to the outer periphery of the combustor plate 20.

[0031] <Arrangement of the second nozzle> 3, a plurality of pilot nozzles 40 as second nozzles are distributed and arranged so as to inject pilot fuel F2 from divided region D in downstream end face 22. That is, pilot nozzles 40 are provided so as to penetrate a region between adjacent nozzle segments S in combustor plate 20. The tip of pilot nozzle 40 that injects pilot fuel F2 is positioned within divided region D.

[0032] In the present embodiment, the pilot nozzle 40 injects fuel from a connection point between the circumferential region and each radial region D2 in the divided region D. That is, the tips of the pilot nozzle 40, which inject pilot fuel F2, are disposed in a dispersed manner at each of the multiple connection points.

[0033] <Action and effect> Next, the operation and effects of the combustor 3 according to this embodiment will be described. 2, during operation of the gas turbine 1, air A enters each mixing tube 31 of the main nozzle 30 from the upstream side, and the air A flows through the mixing tube 31 toward the downstream side. When main fuel F1 is supplied into the mixing tube 31 from the tip of the fuel supply pipe 32 in this state, the air A and the main fuel F1 are mixed in the mixing tube 31 to generate premixed gas M. The premixed gas M is injected from the opening of the mixing tube 31 at the downstream end surface 22 of the combustor plate 20, i.e., the opening of the main nozzle 30.

[0034] On the other hand, as shown in Fig. 4, when pilot fuel F2 is injected from the tip of the pilot nozzle 40 on the downstream end face 22, the pilot fuel F2 is ignited to generate a pilot flame P as a diffusion flame. The premixed gas M injected from the main nozzle 30 is combusted starting from this pilot flame P to generate a main flame F as a premixed flame. The pilot flame P of the pilot nozzle 40 ensures flame stability of the main flame F, and a stable combustion reaction continues. The combustion gas C generated by such combustion is sent to the turbine 4.

[0035] Here, in this embodiment, the multiple pilot nozzles 40 are arranged in a dispersed manner in the divided regions D. Therefore, it is possible to ensure flame stability of the multiple main nozzles 30 as a whole while reducing the scale of the pilot flame P by the pilot nozzle 40. In addition, as the pilot flame P is reduced in scale, the flame length of the main flame F is shortened and burnout is improved, making it possible to suppress the generation of unburned fuel. As a result, it is possible to ensure flame stability of the combustor 3 as a whole.

[0036] Moreover, by distributing small pilot nozzles 40 in divided regions D rather than increasing the size of one pilot nozzle 40, it is possible to avoid encroaching on the installation area of ​​the main nozzles 30. If the diameter of the pilot nozzle 40 is increased, and as a result the installation area of ​​the main nozzle 30 is reduced, the number of mixing tubes 31 will be reduced accordingly. In this case, the pressure loss of the air A increases, resulting in a decrease in the performance of the combustor 3. In this embodiment, by distributing the multiple pilot nozzles 40 in the divided region D where the main nozzles 30 were not originally arranged, it is possible to ensure the installation space for the main nozzles 30 as before. Therefore, it is possible to maintain the performance of the combustor 3.

[0037] Furthermore, in this embodiment, the pilot nozzle 40 is configured to inject the fuel from a connection point between the annular region D1 and the radial region D2 in the divided region D, so that the pilot flame P of the pilot nozzle 40 can ensure flame stability of the three nozzle segments S that contact these connection points. In other words, since a single pilot nozzle 40 can ensure flame stability for a large number of nozzle segments S, the installation space can be used effectively.

[0038] Second Embodiment Next, a second embodiment of the present invention will be described with reference to Fig. 5. In the second embodiment, components similar to those in the first embodiment are given the same reference numerals, and detailed description thereof will be omitted. In the second embodiment, the location of the pilot nozzle 40 is different from that in the first embodiment.

[0039] That is, in the second embodiment, a large number of pilot nozzles 40 are provided at intervals in the extension direction of the annular region D1 of the divided region D. That is, a plurality of pilot nozzles 40 (three in this embodiment) are provided not only at the connection portion between the annular region D1 and the radial region D2 but also in a portion between adjacent connection portions in the annular region D1. Furthermore, in the radial region D2 of the divided region D, a plurality of pilot nozzles 40 are provided at intervals in the extending direction of the radial region D2.

[0040] In the present embodiment, an outer circumferential pilot nozzle 41 is also provided as a third nozzle for injecting pilot fuel F2 in an outer circumferential region R radially outside the outer circumferential segment S2 in the downstream end face 22 of the combustor plate 20. The outer circumferential region R is a dead space between the outer circumferential segment S2 and the outer circumferential edge of the combustor plate 20. A plurality of outer circumferential pilot nozzles 41 are provided in this outer circumferential edge at intervals in the circumferential direction.

[0041] In the second embodiment, a large number of pilot nozzles 40 are distributed in a mesh pattern over the entire divided region D, thereby expanding the flame-holding region over the entire nozzle segments S. This makes it possible to further shorten the flame length of the main flame F and suppress the generation of unburned fuel.

[0042] Furthermore, by installing the outer circumferential pilot nozzle 41 not only in the divided region D but also in a dead space on the outer circumferential side of the outer circumferential segment S2, it is possible to further improve the flame stability of the nozzle segment S as a whole while maintaining the performance of the combustor 3.

[0043] Next, a third embodiment of the present invention will be described with reference to Fig. 6. In the third embodiment, components similar to those in the first embodiment are given the same reference numerals, and detailed description thereof will be omitted. In the third embodiment, an inner pilot nozzle 42 as a fourth nozzle is disposed in a region within the nozzle segment S. That is, the inner pilot nozzle 42 is disposed so as to be able to inject fuel from a region of the nozzle segment S that is on the inside of the outer circumferential side segment S2.

[0044] In this embodiment, since a plurality of pilot nozzles 40 are distributed in the divided region D, the diameter of the inner pilot nozzle 42 installed in the nozzle segment S can be made small. Therefore, the flame stability of the main nozzle 30 inside the nozzle segment S can be ensured without significantly eroding the installation area of ​​the main nozzle 30. That is, it is possible to ensure the flame stability of the main nozzle 30 located particularly away from the divided region D, and to further reduce the generation of unburned fuel by shortening the flame length of the main flame F.

[0045] Next, a fourth embodiment of the present invention will be described with reference to Figures 7 and 8. In the fourth embodiment, the same components as those in the first embodiment are given the same reference numerals, and detailed description thereof will be omitted. In the fourth embodiment, the fuel concentrations in the main nozzles 30 of each nozzle segment S are made different from each other.

[0046] Here, among the main nozzles 30 of each nozzle segment S, the main nozzles 30 arranged adjacent to the divided region D are referred to as outer nozzles 30A, and the main nozzles 30 arranged more inwardly in the nozzle segment S than the outer nozzles 30A (main nozzles 30 not adjacent to the divided region D) are referred to as inner nozzles 30B.

[0047] 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. Setting of such a fuel concentration can be realized, for example, by providing an orifice appropriately in the first fuel header 12 to adjust the flow rate of the main fuel F1 supplied to each fuel supply pipe 32. Alternatively, the fuel concentration may be appropriately set by providing an orifice in the fuel supply pipe 32 or by changing the diameter of the fuel supply pipe 32.

[0048] This configuration promotes the combustion reaction of the main flame F of the outer nozzle 30A adjacent to the divided region D. Therefore, the main flame F originating from the pilot flame P of the pilot nozzle 40 arranged in the divided 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 fuel can be further suppressed.

[0049] <Other embodiments> Although the embodiment of the present invention has been described above, the present invention is not limited to this, and can be modified as appropriate without departing from the technical concept of the invention.

[0050] For example, the main nozzle 30 has been described as having the mixing pipe 31 and the fuel supply pipe 32, but the main fuel F1 may be injected from the inner circumferential surface of the mixing pipe 31 instead of the fuel supply pipe 32. Here, for example, as in a modification shown in Fig. 9, the combustor plate 20 of each embodiment may be configured with a plurality of divided segments 25 when viewed from the axis O of the combustor 3. Boundaries between the segments 25 are defined as parting lines. A divided region D in which the nozzle segment S is provided in each of the segments 25 is a region that includes the parting lines between the segments 25. Therefore, the pilot nozzle 40 is disposed on the parting line so as to be sandwiched between the adjacent segments 25. By disposing the pilot nozzle 40 between the parting lines between the segments 25 in this manner, the combustor 3 can be easily assembled. Furthermore, since it is easy to change the fuel system for each nozzle segment S, the degree of freedom of the combustion mode can be improved.

[0051] For example, in the first embodiment, an example has been described in which the pilot nozzles 40 are disposed at all of the connection points between the annular region D1 and the radial region D2 in the divided region D, but the present invention is not limited to this. The pilot nozzles 40 may be disposed at only some of the multiple connection points.

[0052] For example, in the second embodiment, an example has been described in which a plurality of pilot nozzles 40 are provided in both the annular region D1 and the radial region D2 of the divided region D, but the present invention is not limited to this. For example, a configuration in which the pilot nozzles 40 are provided in at least one of the annular region D1 and the radial region D2 may also be used. That is, it is sufficient that the pilot nozzles 40 are distributed in at least one of the annular region D1 and the radial region D2.

[0053] In the third embodiment, the inner pilot nozzle 42 as a fourth nozzle is provided only in the outer peripheral segment S2, but the inner pilot nozzle 42 may also be provided in the region within the central segment S1. Also, the inner pilot nozzle 42 may not be provided in the region within the outer peripheral segment S2, and may be provided only in the region within the central segment S1.

[0054] In the fourth embodiment, the fuel concentration in the outer nozzle 30A is higher than that in the inner nozzle 30B, but the present invention is not limited to this. For example, the main fuel F1 in the outer nozzle 30A and the main fuel F1 in the inner nozzle 30B may be different types of fuel, and the main fuel F1 in the outer nozzle 30A may be a fuel that is more flammable than the main fuel F1 in the inner nozzle 30B. For example, the ratio of hydrogen in the fuel in the outer nozzle 30A may be increased compared to the fuel in the inner nozzle 30B. This also promotes the combustion reaction of the main flame F in the outer nozzle 30A, thereby achieving the same effects as the fourth embodiment. Moreover, the pilot fuel F2 in the pilot nozzle 40 may be a more flammable type of fuel, so as to ensure better flame stability.

[0055] <Additional Notes> The combustor 3 and the gas turbine 1 described in each embodiment can be understood, for example, as follows.

[0056] (1) A combustor 3 according to a first aspect includes a combustor plate 20 having a downstream end surface 22 perpendicular to a combustor axis O, a nozzle segment S in which a plurality of first nozzles 30 that eject premixed gas M of air A and fuel from the downstream end surface 22 side are collectively arranged, and a plurality of second nozzles 40 that eject fuel from the downstream end surface 22, the plurality of nozzle segments S are provided at intervals from each other in a direction perpendicular to the combustor axis O, and each of the second nozzles 40 ejects the fuel from a divided region D between the nozzle segments S at the downstream end surface 22.

[0057] With this configuration, a premixed flame is formed by the first nozzle 30, starting from the diffusion flame of the second nozzle 40. In this embodiment, since a plurality of second nozzles 40 are distributed and arranged in the divided region D, the scale of the diffusion flame can be reduced, and flame stability can be improved. In addition, since the second nozzle 40 is provided in the dead space between the nozzle segments S, it does not encroach on the installation area of ​​the first nozzle 30. Therefore, a decrease in the performance of the combustor 3 can be avoided.

[0058] (2) A combustor 3 according to a second aspect is the combustor 3 described in (1), wherein the nozzle segment S includes a central segment S1 disposed in a center portion of the combustor plate 20 including the combustor axis O, and a plurality of outer-periphery side segments S2 disposed at intervals on the radial outside of the central segment S1 about the combustor axis O and at intervals from each other in a circumferential direction of the combustor axis O, and the divided region D includes: an annular region D1 between the central segment S1 and the plurality of outer-periphery side segments S2, the annular region D1 extending annularly around the combustor axis O, and a radial region D2 between adjacent outer-periphery side segments S2, the radial region D2 extending in the radial direction of the combustor axis O.

[0059] By distributing the second nozzles 40 in the divided region D having such an annular region D1 and a radial region D2, it is possible to maintain the performance of the combustor 3 while improving the flame stability.

[0060] (3) The combustor 3 according to a third aspect is the combustor 3 according to (2), wherein the second nozzle 40 injects the fuel from a connection point between the annular region D1 and the radial region D2 in the divided region D.

[0061] This makes it possible for the second nozzles 40 disposed at the connection points to ensure flame stability for the multiple nozzle segments S adjacent to these connection points.

[0062] (4) The combustor 3 according to a fourth aspect is the combustor 3 according to (2) or (3), wherein the second nozzles 40 are arranged in plurality along an extension direction of at least one of the annular region D1 and the radial region D2 of the dividing region D.

[0063] By arranging a plurality of second nozzles 40 along the extending direction of the divided region D, the flame stability of the first nozzle 30 can be ensured over a wide range of the nozzle segment S.

[0064] (5) The combustor 3 according to a fifth aspect is the combustor 3 of any one of (2) to (4), further including a third nozzle 41 that injects fuel from an outer circumferential side region R on the radially outer side of the outer circumferential side segment S2 at the downstream end surface 22.

[0065] By installing the third nozzle 41 not only in the divided region D but also in a dead space, such as the further outer periphery of the outer periphery side segment S2, it is possible to further improve the flame stability of the nozzle segment S as a whole while maintaining the performance of the combustor 3.

[0066] (6) The combustor 3 according to a sixth aspect is the combustor 3 of any one of (2) to (5), further comprising a fourth nozzle 42 that injects fuel from a region within the nozzle segment S at the downstream end surface 22.

[0067] This makes it possible to ensure the flame stability of the first nozzle 30 located away from the divided region D.

[0068] (7) The combustor 3 according to a seventh aspect is any one of the combustors 3 of (1) to (6), wherein the fuel concentration of the first nozzle 30 arranged adjacent to the division region D among the multiple first nozzles 30 of the nozzle segment S is higher than the fuel concentration of the other first nozzles 30.

[0069] This promotes the combustion reaction of the premixed flame of the first nozzle 30 adjacent to the divided region D. Therefore, the premixed flame originating from the diffusion flame of the second nozzle 40 arranged in the divided region D transitions to the upstream side, shortening the flame length. As a result, the generation of unburned fuel is suppressed, and flame stability is ensured.

[0070] (8) The combustor 3 according to an eighth aspect is the combustor 3 according to any one of (1) to (7), wherein the fuel of the first nozzle 30 arranged adjacent to the division region D among the multiple first nozzles 30 of the nozzle segment S is a type of fuel that is more combustible than the fuel of the other first nozzles 30.

[0071] As a result, similarly to (7), the combustion reaction of the premixed flame in the first nozzle 30 adjacent to the divided region D is promoted, so that the generation of unburned fuel is suppressed and flame stability is ensured.

[0072] (9) A combustor 3 according to a ninth aspect is the combustor 3 described in any of (1) to (8), wherein the combustor plate 20 is composed of a plurality of partition bodies 25 when viewed in a direction of an axis O of the combustor 3, the nozzle segment S is provided in each of the partition bodies 25, and the partition region D is a region including a partition line between the partition bodies 25.

[0073] Since the second nozzle 40 can be disposed between the parting lines between the segments 25, the combustor 3 can be easily assembled. In addition, since it is easy to change the fuel system for each nozzle segment S, the degree of freedom in the combustion mode can be improved.

[0074] (10) A gas turbine 1 according to a tenth aspect is a gas turbine 1 including a compressor 2 that generates air A, a combustor 3 of any one of (1) to (9) that generates combustion gas C by burning a premixed gas M generated by mixing fuel with the air A compressed by the compressor 2, and a turbine 4 driven by the combustion gas C. [Explanation of symbols]

[0075] 1. Gas turbine 2. Compressor 3. Combustor 4. Turbine 10 Outer cylinder 11 End cover 12 First fuel header 13 Second fuel header 15 Inner cylinder 17 Support part 20 Combustor plate 21 Upstream end face 22 Downstream end face 25 split body 30 Main nozzle 30A Outer Nozzle 30B Inner nozzle 31 Mixing tube 32 Fuel supply pipe 40 Pilot Nozzle 41 Outer pilot nozzle 42 Inner pilot nozzle S Nozzle Segment S1 Central segment S2 Outer segment D division area D1 Annular region D2 Radial area R Outer area F Main flame P Pilot flame F1 main fuel F2 pilot fuel A. Air M Premixed gas C. Combustion gas O axis F1 main fuel F2 pilot fuel

Claims

1. a combustor plate having a downstream end surface intersecting a combustor axis; a nozzle segment including a plurality of first nozzles arranged in a group to generate a premixed flame by injecting a premixed gas of air and fuel from the downstream end surface side; a plurality of second nozzles for generating a diffusion flame by injecting fuel from the downstream end surface, The nozzle segments are provided in a plurality of spaces spaced apart from one another in a direction intersecting the combustor axis, a combustor, wherein an end portion of each of the second nozzles on the downstream end surface side is formed between a plurality of the nozzle segments and is located in a divided region in the downstream end surface interposed between the nozzle segments such that the nozzle segments adjacent to each other are arranged at a distance from each other.

2. The nozzle segment includes: a central segment disposed in a central portion of the combustor plate including the combustor axis; a plurality of outer circumferential segments spaced apart from one another in a circumferential direction of the combustor axis and spaced apart from one another in a radial direction outward from the central segment along the combustor axis; Including, The divided regions are: an annular region between the central segment and the plurality of outer peripheral segments, the annular region extending annularly around the combustor axis; a radial region between adjacent outer circumferential segments, the radial region extending in a radial direction of the combustor axis; The combustor of claim 1 , comprising:

3. The second nozzle is The combustor according to claim 2 , wherein the fuel is injected from a connection point between the annular region and the radial region in the divided region.

4. The second nozzle is The combustor according to claim 2 or 3, wherein a plurality of the first and second grooves are arranged along an extension direction of at least one of the annular region and the radial region of the dividing region.

5. The combustor according to claim 2 , further comprising a third nozzle configured to inject fuel from an outer circumferential region on a radially outer side of the outer circumferential segment at the downstream end surface.

6. The combustor of claim 2 , further comprising a fourth nozzle configured to inject fuel from a region within the nozzle segment at the downstream end face.

7. 7. The combustor according to claim 1, wherein a fuel concentration of the first nozzle arranged adjacent to the division region among the plurality of first nozzles of the nozzle segment is higher than a fuel concentration of the other first nozzles.

8. 8. The combustor according to claim 1, wherein fuel in the first nozzle arranged adjacent to the division region among the plurality of first nozzles of the nozzle segment is a type of fuel that is more combustible than fuel in other first nozzles.

9. the combustor plate is composed of a plurality of divided bodies as viewed in the combustor axial direction, The nozzle segment is provided in each of the divided bodies, The combustor according to claim 1 , wherein the divided region is a region including a dividing line between the divided bodies.

10. a combustor plate having a downstream end surface intersecting a combustor axis; a nozzle segment including a plurality of first nozzles arranged in a group to inject a premixed gas of air and fuel from the downstream end surface side; a plurality of second nozzles that inject fuel from the downstream end surface; having The nozzle segments are provided in a plurality of spaces spaced apart from one another in a direction intersecting the combustor axis, the combustor plate is composed of a plurality of divided bodies as viewed in the combustor axial direction, The nozzle segment is provided in each of the divided bodies, Each of the second nozzles injects the fuel from a divided region between the nozzle segments on the downstream end surface, The divided region is a region including a dividing line between the divided bodies.

11. A compressor for generating air; The combustor according to any one of claims 1 to 10, wherein the combustor generates a combustion gas by combusting a premixed gas generated by mixing fuel with air compressed by a compressor; a turbine driven by the combustion gas; A gas turbine comprising:

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