Two-stage combustion nozzle, and gas turbine combustor

Abstract

A nozzle main body of this two-stage combustion nozzle includes: a top plate portion that extends in a direction orthogonal to a nozzle axial direction of the two-stage combustion nozzle; a plurality of fuel supply portions that are provided upright from the top plate portion along the nozzle axial direction and are arranged spaced apart in a nozzle circumferential direction of the two-stage combustion nozzle, two of the fuel supply portions that are adjacent to one other in the nozzle circumferential direction defining an introduction flow passage for introducing air from the outside to the inside in the nozzle radial direction of the two-stage combustion nozzle; and a main flow passage forming portion that forms a main flow passage for guiding a mixed fluid, including fuel supplied from fuel supply holes of each of the plurality of fuel supply portions and the air introduced by the introduction flow passage, along the nozzle axial direction to an outlet opening. The top plate portion has at least one first auxiliary air introduction hole disposed outward, in the nozzle radial direction, of each of the inside end portions of the plurality of fuel supply portions.

Description

Two-stage combustion nozzle and gas turbine combustor

[0001] This disclosure relates to a two-stage combustion nozzle for supplying a mixed fluid containing fuel and air to a two-stage combustion region in a combustion chamber of a gas turbine, and a gas turbine combustor. This application claims priority to Japanese Patent Application No. 2024-024168, filed with the Japan Patent Office on February 21, 2024, the contents of which are incorporated herein by reference.

[0002] Conventionally, gas turbine combustors employing a two-stage combustion system have been known. For example, a gas turbine combustor disclosed in Patent Document 1 includes a combustion liner that defines a combustion chamber, a cap assembly (combustor) disposed at one end of the combustion liner, and a fuel nozzle (two-stage combustion nozzle) disposed on a side wall of the combustion liner. The fuel nozzle is disposed downstream of the cap assembly in the direction of combustion gas flow through the combustion liner.

[0003] JP 2014-77627 A

[0004] Inside the two-stage combustion nozzle, a mixed fluid containing fuel and air flows toward the combustion chamber. It is preferable that the fuel contained in the mixed gas flows toward the combustion chamber without being ignited upstream inside the two-stage combustion nozzle. It is also preferable that the two-stage combustion nozzle is compact.

[0005] An object of the present disclosure is to provide a compact two-stage combustion nozzle and gas turbine combustor that can provide good combustion and air supply to the combustion chamber.

[0006] a nozzle body having an outlet opening communicating with the combustion chamber, the nozzle body including: a top plate portion extending in a direction perpendicular to a nozzle axis direction of the two-stage combustion nozzle; a plurality of fuel supply portions erected from the top plate portion along the nozzle axis direction and arranged at intervals in a nozzle circumferential direction of the two-stage combustion nozzle, wherein two adjacent fuel supply portions in the nozzle circumferential direction define an introduction flow path for introducing the air from the outer side to the inner side in a nozzle radial direction of the two-stage combustion nozzle; and a main flow path forming portion forming a main flow path for guiding a mixed fluid containing the fuel supplied from the fuel supply holes of each of the plurality of fuel supply portions and the air introduced by the introduction flow path to the outlet opening along the nozzle axial direction, the top plate portion having at least one first auxiliary air introduction hole arranged outward in the nozzle radial direction than an inner end portion of each of the plurality of fuel supply portions.

[0007] A gas turbine combustor according to at least one embodiment of the present disclosure includes: the combustion liner defining the combustion chamber; a combustor for supplying the fuel to the combustion liner; and the above-described two-stage combustion nozzle disposed downstream of the combustor in a flow direction of combustion gas in the combustion chamber.

[0008] According to the present disclosure, it is possible to provide a compact two-stage combustion nozzle and a gas turbine combustor that can effectively supply fuel and air to a combustion chamber.

[0009] FIG. 4 is a schematic diagram showing a gas turbine according to an embodiment. FIG. 5 is a schematic diagram of a gas turbine combustor according to an embodiment. FIG. 6 is a schematic diagram of a two-stage combustion nozzle according to a first embodiment. FIG. 7 is a schematic cross-sectional view taken along the arrows A-A in FIG. 3. FIG. 8 is a schematic diagram of a top plate portion as viewed in the nozzle axial direction according to an embodiment. FIG. 9 is a schematic enlarged schematic diagram of a fuel supply portion according to an embodiment. FIG. 10 is a schematic enlarged schematic partial view of a nozzle main body as viewed in the nozzle radial direction. FIG. 11 is a schematic diagram of a two-stage combustion nozzle according to a second embodiment. FIG. 12 is a schematic diagram of a protrusion and a fuel supply portion 50 as viewed in the nozzle radial direction. FIG. 13 is a schematic diagram of a protrusion as viewed in the nozzle axial direction. FIG. 14 is a schematic diagram of a two-stage combustion nozzle according to a third embodiment. FIG. 15 is a schematic diagram of a mounting plate as viewed in the nozzle radial direction. FIG. 16 is a schematic diagram of a two-stage combustion nozzle according to a fourth embodiment.

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

[0011] <Overview of Gas Turbine 100> Fig. 1 is a schematic diagram showing a gas turbine 100 according to an embodiment of the present disclosure. The gas turbine 100 includes a compressor 2 for generating compressed air, a gas turbine combustor 4 for generating combustion gas using the 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 this rotating shaft 9.

[0012] In the gas turbine combustor 4, a mixed gas containing compressed air delivered from the compressor 2 and fuel supplied from a fuel supply unit (not shown) is combusted to generate combustion gas as a working fluid that drives the turbine 6. The turbine 6 is driven by the combustion gas flowing into it, and the generator 5 generates electricity as a result of the rotation of the rotary shaft 9. Note that the fuel supplied to the gas turbine combustor 4 may be hydrogen, methane, light oil, heavy oil, jet fuel, natural gas, gasified coal, or a combination of any two or more of these. Hereinafter, the compressed air delivered from the compressor 2 to the gas turbine combustor 4 may be simply referred to as "air."

[0013] <Outline of Gas Turbine Combustor 4> FIG. 2 is a schematic diagram of a gas turbine combustor 4 according to an embodiment of the present disclosure. The gas turbine combustor 4 includes a combustion liner 40 that defines a combustion chamber 47, a combustor 8 provided at one end of the combustion liner 40, and a two-stage combustion nozzle 20 provided on a sidewall 42 of the combustion liner 40. The combustor 8 is configured to inject fuel and air along the axial direction of the combustion liner 40. The fuel injected from the combustor 8 mixes with the air to generate a mixed gas, which is ignited, and a flame is generated inside the combustion chamber 47. Combustion gas, which serves as a mainstream high-temperature gas generated in the combustion chamber 47, flows downstream (to the right in the example of FIG. 2). The two-stage combustion nozzle 20 is disposed downstream of the combustor 8 in the flow direction of the combustion gas, and is configured to inject fuel and air along the radial direction of the combustion liner 40. The fuel and air are injected into the combustion chamber 47 from the two-stage combustion nozzle 20, causing second-stage combustion in the combustion chamber 47. The space within the combustion chamber 47 where the second stage combustion occurs is a so-called two-stage combustion region. In this example, a plurality of two-stage combustion nozzles 20 are arranged at equal intervals along the circumferential direction of the combustion liner 40.

[0014] An example of the configuration of the combustor 8 is disclosed in Japanese Patent Application Laid-Open No. 2013-096303. A detailed description of the configuration will be omitted here, but the outline is as follows. The combustor 8 includes a pilot burner disposed at the center of the combustion tube 40 and multiple main burners disposed at equal intervals around the pilot burner. The pilot burner has a pilot nozzle that supplies pilot fuel and a tubular member that surrounds the tip of the pilot nozzle. A pilot air passage is formed between the tubular member and the pilot nozzle, and air (pilot air) flows through the pilot air passage. The main burner includes a main nozzle that supplies main fuel and a main air passage formed around the main nozzle that supplies main air. The main fuel injected from the main nozzle is mixed with main air supplied through the main air passage to form a premixed gas.

[0015] <Outline of the two-stage combustion nozzle according to the first embodiment> Figure 3 is a schematic diagram of the two-stage combustion nozzle 21 (20) according to the first embodiment. The two-stage combustion nozzle 21 includes a substantially cylindrical nozzle body 25 having an outlet opening 41 formed therein that communicates with the combustion chamber 47 of the combustion liner 40. The outlet opening 41 is an injection port for injecting the mixed fluid toward the two-stage combustion region of the combustion chamber 47.

[0016] In the following description, the direction in which the axis S of the nozzle body 25 extends may be referred to as the "nozzle axial direction." Furthermore, the circumferential direction and radial direction based on the axis S may be referred to as the "nozzle circumferential direction" and the "nozzle radial direction," respectively. The "inner side in the nozzle radial direction" is the side approaching the axis S, and the "outer side in the nozzle radial direction" is the side moving away from the axis S.

[0017] The nozzle body 25 includes a top plate portion 30 extending in a direction perpendicular to the nozzle axial direction, a plurality of fuel supply portions 50 erected from the top plate portion 30 toward the outlet opening 41 along the nozzle axial direction, and a circumferentially extending portion 80 connected to connection end portions 49 of each of the plurality of fuel supply portions 50. The connection end portions 49 are end portions of each fuel supply portion 50 (more specifically, each fuel body portion 51 described later) on the outlet opening 41 side.

[0018] The multiple fuel supply units 50 are arranged at intervals in the nozzle circumferential direction (see FIG. 4), and two fuel supply units 50 adjacent to each other in the nozzle circumferential direction define an introduction flow path 59 (see FIG. 4) for introducing air supplied from the outside to the inside in the nozzle radial direction. The multiple introduction flow paths 59 are arranged at intervals in the nozzle circumferential direction. Each introduction flow path 59 extends radially, and the inlet of each introduction flow path 59 opens radially outward.

[0019] The circumferentially extending portion 80 extends in the nozzle circumferential direction so as to connect to each connection end portion 49. The circumferentially extending portion 80 has a first peripheral edge portion 81 extending in the nozzle circumferential direction. The first peripheral edge portion 81 is located outward from the outer ends 57 of each of the multiple fuel supply portions 50 in the nozzle radial direction. The top plate portion 30 also has a second peripheral edge portion 34 that faces the first peripheral edge portion 81 in the nozzle axial direction. The first peripheral edge portion 81 and the second peripheral edge portion 34 define air inlets 29 for introducing air from the radially outer side into each introduction flow path 59. In this embodiment, the air introduced by the air inlets 29 (arrow P) accounts for 50% or more of the air released from the outlet opening 41. The air inlets 29 have a bell-mouth shape in which the inner diameter of the air inlets 29 increases toward the outer side in the nozzle radial direction.

[0020] 3 and 4, each of the plurality of fuel supply units 50 has a fuel body 51, a fuel chamber 53 formed inside the fuel body 51, and a fuel supply hole 55 (see FIG. 6) for guiding the fuel in the fuel chamber 53 to an introduction passage 59. The fuel supplied from the fuel supply hole 55 to the introduction passage 59 mixes with air introduced by the introduction passage 59. This generates a mixed fluid containing fuel and air.

[0021] 3, air (auxiliary air) other than the air supplied from the air inlet 29 to the inlet of the introduction flow path 59 is added to the mixed fluid. The amount of the auxiliary air supplied is half or less, more specifically, one-fourth or less, of the amount of air supplied to the inlet of the introduction flow path 59.

[0022] The auxiliary air includes first auxiliary air. The first auxiliary air is supplied into the nozzle main body 25 via at least one first auxiliary air inlet hole 31 formed in the top plate portion 30. The first auxiliary air inlet hole 31 is located outward of the inner end portion 54 (see FIG. 6 ) of each fuel body portion 51 in the nozzle radial direction. The first auxiliary air inlet hole 31 is a hole that penetrates the top plate portion 30 in the nozzle axial direction, and the first auxiliary air passing through the first auxiliary air inlet hole 31 may be supplied to the introduction passage 59 via an auxiliary air chamber 52 (see FIG. 6 ) described below, or may be supplied directly to the introduction passage 59 without passing through the auxiliary air chamber 52.

[0023] In some embodiments, the auxiliary air may further include second auxiliary air, third auxiliary air, and fourth auxiliary air, which will be described in detail below.

[0024] 3, the nozzle body 25 further includes a main flow path forming section 60 that forms a main flow path 69 for guiding the mixed fluid along the nozzle axial direction to the outlet opening 41. The main flow path forming section 60 is cylindrical in shape, the axis of which substantially coincides with the axis S, and the outlet opening 41 is formed at one end of the main flow path forming section 60.

[0025] The nozzle body 25 further includes a pointed protrusion 70 that protrudes from the top plate portion 30 toward the outlet opening 41. The pointed protrusion 70 is disposed radially inward of the plurality of introduction channels 59 (see FIG. 4 ) and has a shape that tapers toward the outlet opening 41. In this example, the pointed protrusion 70 is integrally formed from the same material as the top plate portion 30. The pointed protrusion 70 has a guide side surface 72 that extends in the nozzle circumferential direction to surround the axis S, and the guide side surface 72 extends in a curved manner toward the outlet opening 41 as it moves radially inward of the nozzle.

[0026] The process by which the two-stage combustion nozzle 21 generates a mixed fluid will now be outlined. A portion of the compressed air (air) generated by the compressor 2 (see FIG. 1 ) is introduced into each of the multiple inlet passages 59 from the radially outer side (arrow P). At the same time, fuel in the fuel chamber 53 is supplied to the inlet passages 59 through the fuel supply holes 55, generating a mixed fluid. Additionally, first auxiliary air, which is air supplied through the first auxiliary air inlet holes 31 in the top plate 30, flows into the nozzle body 25 and is added to the mixed fluid (arrow I). The mixed fluid guided inward in the nozzle axial direction by each of the multiple inlet passages 59 is guided by the guide side surface 72 toward the outlet opening 41 along the nozzle axial direction (arrow Q). The mixed fluid then passes through the main passage 69 and flows into the combustion chamber 47 (arrow R).

[0027] According to the above configuration, each of the multiple introduction passages 59 extends along the nozzle radial direction, thereby enabling the two-stage combustion nozzle 21 to be made compact in the nozzle axial direction. Furthermore, because the first auxiliary air supplied from the first auxiliary air introduction holes 31 is guided to the main passage 69, the fuel concentration of the mixed fluid near the inner end 54 of the fuel supply unit 50 can be reduced. This makes it possible to suppress flame holding within the nozzle body 25 due to unintended fuel ignition within the main passage 69, etc. Therefore, a compact two-stage combustion nozzle 21 (20) that can efficiently supply fuel and air to the combustion chamber 47 is realized.

[0028] Furthermore, since the guide side surface 72 curves toward the outlet opening 41 as it moves toward the inside in the nozzle radial direction, pressure loss can be suppressed when guiding the mixed fluid flowing from the outside to the inside in the nozzle radial direction toward the outlet opening 41.

[0029] Furthermore, because the air inlet 29 has a bell-mouth shape, it is possible to reduce pressure loss of the air supplied from the air inlet 29 to each inlet flow passage 59 and to make the velocity distribution of the air at the air inlet 29 uniform. This realizes a compact two-stage combustion nozzle 21 that uniformly introduces the required air. In particular, in an embodiment in which the amount of air introduced by the air inlet 29 accounts for 50% or more of the amount of air released from the outlet opening 41, the other inlets that introduce air can be made compact, thereby realizing a further compact two-stage combustion nozzle 21.

[0030] <Top Plate 30 and Fuel Supply Section 50> The configurations of the top plate 30 and the fuel supply section 50 of the two-stage combustion nozzle 21 according to the first embodiment will be described in detail with reference to FIGS.

[0031] The top plate portion 30 shown in Fig. 5 further has a fuel introduction hole (not shown). The number of fuel introduction holes is one, and a fuel supply passage (not shown) extending in the nozzle circumferential direction is formed inside the top plate portion 30. A fuel chamber 53 is formed inside the fuel body portion 51 of each fuel supply portion 50 shown in Fig. 6. Fuel supplied from the fuel supply passage flows into each fuel chamber 53, and the fuel in the fuel chamber 53 is supplied to the introduction flow path 59 from the fuel supply hole 55 described above.

[0032] 5, the at least one first auxiliary air introduction hole 31 provided in the top plate portion 30 is a plurality of first auxiliary air introduction holes 31 arranged at intervals in the nozzle circumferential direction. Furthermore, as shown in FIG. 6, an auxiliary air chamber 52 is formed inside the fuel body portion 51 of each fuel supply portion 50. First auxiliary air is introduced into each auxiliary air chamber 52 from each first auxiliary air introduction hole 31 (see FIG. 5).

[0033] 6, the fuel supply unit 50 further has an auxiliary air hole 58 that connects the auxiliary air chamber 52 with the space outside the fuel supply unit 50. The first auxiliary air in the fuel body 51 is supplied from the auxiliary air hole 58 and added to the mixed fluid (arrow F in FIGS. 3 and 6).

[0034] According to the above configuration, the first auxiliary air in the auxiliary air chamber 52 is added to the mixed fluid through the auxiliary air holes 58. During the design stage of the two-stage combustion nozzle, the layout constraints imposed when arranging the auxiliary air holes 58 are smaller than the constraints imposed when arranging the first auxiliary air inlet holes 31 in the top plate portion 30, particularly in the nozzle axial direction. This allows for a more optimal supply position for the first auxiliary air, enabling the first auxiliary air to be well mixed with the fuel and air. This reduces the fuel concentration in the mixed fluid and suppresses flame stabilization within the nozzle body 25.

[0035] 6 , in each of the multiple fuel supply sections 50, the fuel supply holes 55 are arranged further outward in the nozzle radial direction than the auxiliary air holes 58. In this example, multiple fuel supply holes 55 are arranged on each of both end faces of the fuel body 51 in the nozzle circumferential direction, and all of the fuel supply holes 55 are arranged further outward in the nozzle radial direction than the auxiliary air holes 58.

[0036] According to the above configuration, the fuel supply holes 55 can be disposed radially outward of the nozzle. This lengthens the flow path through which the fuel and air mix, thereby promoting the mixing of the fuel and air. This makes it possible to prevent the fuel concentration from increasing locally in the mixed fluid.

[0037] 6 , each of the fuel supply holes 55 is configured to supply fuel to the introduction passage 59 in a direction perpendicular to the nozzle radial direction (arrow T). That is, each fuel supply hole 55 opens in a direction perpendicular to the nozzle radial direction. More specifically, the angle of the center line (not shown) of each fuel supply hole 55 with respect to the nozzle radial direction is 85 degrees or more and 95 degrees or less. With this configuration, the flow direction of the fuel supplied from the fuel supply hole 55 and the flow direction of the air introduced by the introduction passage 59 are approximately perpendicular to each other, further promoting mixing of the fuel and air.

[0038] Furthermore, the fuel body 51 of each fuel supply unit 50 has a streamlined shape extending along the nozzle radial direction. More specifically, the radius of curvature of the outer end 57 of the fuel body 51 in the nozzle radial direction is larger than the radius of curvature of the inner end 54 of the fuel body 51. Furthermore, in each fuel supply unit 50, a center line Z connecting points at equal nozzle circumferential distances from both end faces of the fuel body 51 in the nozzle circumferential direction is a straight line extending along the nozzle radial direction. The acute angle formed by the center line Z and the nozzle radial direction is 10 degrees or less, and more preferably, the center line Z is parallel to the nozzle radial direction. If the fuel body 51 is considered to be a blade (stator vane), the center line Z corresponds to a camber line.

[0039] According to the above configuration, it is possible to suppress the wake of the mixed fluid radially inside the nozzle radial direction of the inner end 54 of each fuel supply unit 50. This makes it possible to further reduce the fuel concentration near the inner end 54 of the fuel supply unit 50, and to suppress flame stabilization inside the nozzle body 25.

[0040] In some embodiments, the auxiliary air holes 58 are formed in the inner end portions 54 of the fuel bodies 51, and the auxiliary air holes 58 open toward the inside in the nozzle radial direction. The auxiliary air holes 58 may have a slit shape that is long in the nozzle axial direction. With the above configuration, the wake of the mixed fluid on the inside in the nozzle radial direction of each fuel supply portion 50 can be further suppressed, and the fuel concentration near the inner end portions 54 of the fuel supply portions 50 can be further reduced.

[0041] 3 , in some embodiments of the present disclosure, second auxiliary air may further be supplied from the top plate portion 30 to the main flow path 69. More specifically, the top plate portion 30 may further have inner auxiliary air introduction holes 35 arranged radially inward of the plurality of first auxiliary air introduction holes 31, and the second auxiliary air passes through the inner auxiliary air introduction holes 35. In addition, an inner-projection flow path 75 is formed inside the pointed projection 70.

[0042] The projection internal flow passage 75 includes an extension flow passage 76 extending along the axis S, multiple projection internal guide flow passages 77 branching from the extension flow passage 76, and a projection internal central flow passage 79 extending from the extension flow passage 76 toward the outlet opening 41. The extension flow passage 76 cooperates with the inner auxiliary air inlet holes 35 to form a single flow passage, and all of the second auxiliary air introduced through the inner auxiliary air inlet holes 35 is guided to the extension flow passage 76. A portion of the second auxiliary air flowing through the extension flow passage 76 is distributed to the multiple projection internal guide flow passages 77 and guided from each projection internal guide flow passage 77 to the guide side surface 72. The remaining second auxiliary air flowing through the extension flow passage 76 is discharged from the projection internal central flow passage 79 toward the outlet opening 41 along the nozzle axial direction. The multiple projection internal guide flow passages 77 are arranged at equal intervals around the nozzle circumferential direction. The projection internal central flow passage 79 is a flow passage centered on the axis S and extends parallel to the nozzle axial direction.

[0043] According to the above configuration, the second auxiliary air discharged from the guide side surface 72 and the second auxiliary air discharged from the central flow path 79 inside the protrusion can be added to the mixed fluid flowing toward the outlet opening 41, thereby making the fuel concentration in the mixed fluid uniform.

[0044] <Guide Wall 90> The guide wall 90 will be described with reference to FIGS. 3 and 7 (FIG. 7 illustrates the nozzle circumferential direction linearly). The nozzle body 25 further includes a plurality of guide wall portions 90. The guide wall portions 90 extend from the circumferentially extending portion 80 toward the outlet opening 41 and are spaced apart in the nozzle circumferential direction. Two of the guide wall portions 90 that are adjacent in the nozzle circumferential direction define an auxiliary air guide passage 99. The auxiliary air guide passage 99 is configured to guide third auxiliary air supplied from the outer side to the inner side in the nozzle radial direction to the main passage 69 (arrow U in FIG. 3). The auxiliary air guide passage 99 is located closer to the outlet opening 41 than the introduction passage 59 in the nozzle axial direction. The number of guide wall portions 90 may be greater than the number of fuel supply portions 50.

[0045] The circumferentially extending portion 80 may have a plurality of first communication holes 91 (see FIG. 3 ) for guiding a portion of the third auxiliary air in the auxiliary air guide passage 99 to the auxiliary air chambers 52 of the plurality of fuel supply units 50, respectively. In this case, the third auxiliary air is introduced into the auxiliary air chamber 52 in addition to the first auxiliary air (arrow V), and the first auxiliary air and the second auxiliary air are discharged from the auxiliary air holes 58. The number of the plurality of first communication holes 91 is the same as the number of the plurality of fuel supply units 50.

[0046] According to the above configuration, the third auxiliary air can be added to the mixed fluid flowing toward the outlet opening 41, thereby homogenizing the fuel concentration in the mixed fluid. Furthermore, since the third auxiliary air is introduced into the auxiliary air chamber 52 in addition to the first auxiliary air, the amount of auxiliary air supplied from the auxiliary air holes 58 can be increased, thereby further reducing the fuel concentration in the mixed fluid. Furthermore, since the guide wall portion 90 defining the auxiliary air guide passage 99 extends from the circumferential extending portion 80 toward the outlet opening 41, the auxiliary air guide passage 99 is disposed between the fuel supply hole 55 and the combustion chamber 47 in the nozzle axial direction. This allows for a gentle temperature gradient inside the nozzle body 25 and suppresses flame stabilization in the nozzle body 25 due to unintended fuel ignition in the main passage 69, for example.

[0047] 7 , each of the guide wall portions 90 further has a communication opening 95 that communicates with each of two auxiliary air holes 58 that are adjacent in the nozzle circumferential direction. The communication opening 95 penetrates the guide wall portion 90 in the nozzle circumferential direction. With the above configuration, the pressure among the multiple auxiliary air guide passages 99 can be made uniform. As a result, the third auxiliary air can be evenly supplied from the multiple auxiliary air guide passages 99 to the multiple auxiliary air chambers 52, respectively.

[0048] <Supply of Film Air> As shown in Fig. 3 , the circumferentially extending portion 80 further has an inner wall portion 89 disposed opposite the inner circumferential surface 68 of the main flow passage forming portion 60. The inner wall portion 89 faces the inner circumferential surface 68 over the entire length of the main flow passage forming portion 60 in the nozzle circumferential direction. The inner wall portion 89 is supported by inner end portions 94 in the nozzle radial direction of each of the multiple guide wall portions 90. The inner wall portion 89 and the inner circumferential surface 68 of the main flow passage forming portion 60 define a film air flow passage 88. The film air flow passage 88 is configured to cause at least a portion of the third auxiliary air guided by the multiple auxiliary air guide passages 99 to flow along the inner circumferential surface 68 toward the outlet opening 41 (arrow W).

[0049] According to the above configuration, film-like auxiliary air (film air) is supplied from the film air flow path 88 to the combustion liner 40 (arrow W), thereby suppressing flashback, in which the flame in the combustion chamber 47 flows back into the main flow path 69.

[0050] <Two-stage combustion nozzle according to second embodiment> A two-stage combustion nozzle 22 (20) according to a second embodiment will be described with reference to Figures 8 to 10. Note that the same components as those in the two-stage combustion nozzle 21 according to the first embodiment are given the same reference numerals in the drawings, and their description will be omitted below. Also, in Figures 9 and 10, the nozzle circumferential direction is illustrated as a straight line.

[0051] As shown in FIG. 8 , the circumferentially extending portion 80 of the two-stage combustion nozzle 22 may further include a plurality of second communication holes 92 spaced apart in the nozzle circumferential direction. The number of second communication holes 92 is the same as the number of introduction passages 59, and each second communication hole 92 is configured to directly guide a portion of the third auxiliary air flowing through each auxiliary air guide passage 99 to each introduction passage 59 (arrow G). Each second communication hole 92 is positioned offset in the nozzle circumferential direction with respect to each fuel supply unit 50. With this configuration, the third auxiliary air guided by the second communication holes 92 is added to the mixed fluid, thereby further reducing the fuel concentration in the mixed fluid.

[0052] The circumferentially extending portion 80 may further include a first peripheral edge portion 81 and a plurality of protrusions 10. The first peripheral edge portion 81 extends in the nozzle circumferential direction, outward of the outer ends 57 of the plurality of fuel supply portions 50 in the nozzle circumferential direction. The plurality of protrusions 10 are cylindrical and protrude from the first peripheral edge portion 81 toward the top plate portion 30 in the nozzle axial direction. The plurality of protrusions 10 are arranged at equal intervals in the nozzle circumferential direction over the entire length of the first peripheral edge portion 81 in the nozzle circumferential direction. As shown in FIG. 9 , the nozzle circumferential range of each of the plurality of protrusions 10 is completely included in the nozzle circumferential range of one of the plurality of introduction channels 59. With the above configuration, air hits the plurality of protrusions 10 before flowing into the introduction channel 59, and a secondary flow of air (not shown) is generated at the inlet of the introduction channel 59. This promotes mixing of air and fuel.

[0053] 8 , the protrusions 13 of each of the plurality of protrusions 10 are positioned closer to the top plate portion 30 in the nozzle axial direction than the ends 57E of the outer end portions 57 of each of the plurality of fuel supply portions 50, which are located on the circumferentially extending portion 80 side. In other words, each of the protrusions 13 is positioned closer to the top plate portion 30 in the nozzle axial direction than the end faces 87 of the circumferentially extending portions 80 on the top plate portion 30 side, which serve as the air flow path surface. This configuration can further strengthen the secondary flow of air generated at the inlet of the introduction flow path 59, thereby promoting mixing of air and fuel. However, the present disclosure is not limited thereto. The protrusions 13 may be positioned at the same nozzle axial position as the ends 57E of the fuel supply portions 50, or may be positioned closer to the outlet opening 41 than the nozzle axial position.

[0054] 10 , the plurality of protrusions 10 may include a plurality of first protrusions 11 and a plurality of second protrusions 12. The plurality of first protrusions 11 are arranged at intervals in the nozzle circumferential direction, and the plurality of second protrusions 12 are arranged at intervals in the nozzle circumferential direction at positions in the nozzle radial direction that are shifted from the first protrusions 11. With the above configuration, the secondary flow of air generated at the inlet of the introduction flow passage 59 can be further strengthened, and mixing of air and fuel can be promoted.

[0055] Returning to FIG. 8 , the top plate portion 30 may further include a plurality of second auxiliary air introduction holes 32 arranged alternately with the plurality of fuel supply units 50 in the nozzle circumferential direction. The second auxiliary air introduction holes 32 are configured to introduce the fourth auxiliary air into the plurality of introduction flow paths 59 (arrow H). The second auxiliary air introduction holes 32 are holes that penetrate the top plate portion 30 in the nozzle axial direction. The number of the second auxiliary air introduction holes 32 is the same as the number of introduction flow paths 59. In the nozzle radial direction, the second auxiliary air introduction holes 32 are arranged more inward than the plurality of first auxiliary air introduction holes 31 and more outward than the inner auxiliary air introduction holes 35. With the above configuration, the fourth auxiliary air passing through the second auxiliary air introduction holes 32 can be added to the mixed fluid, thereby reducing the concentration of fuel in the mixed fluid.

[0056] <Two-stage combustion nozzle according to a third embodiment> A two-stage combustion nozzle 23 (20) according to a third embodiment will be described with reference to Figures 11 and 12. Note that the same components as those in the two-stage combustion nozzles 21 and 22 described above are given the same reference numerals in the drawings, and their description will be omitted below. Also, in Figure 12, the nozzle circumferential direction is illustrated as a straight line.

[0057] The nozzle body 25 of the two-stage combustion nozzle 23 may further include a mounting plate 110 that is attached to the first peripheral edge portion 81 of the circumferentially extending portion 80 and the second peripheral edge portion 34 of the top plate portion 30 and extends in the nozzle circumferential direction. The mounting plate 110 is a plate-like plate having a thickness in the nozzle radial direction, and is a curved plate that is attached to the first peripheral edge portion 81 and the second peripheral edge portion 34 over the entire length of the nozzle body 25 in the nozzle circumferential direction.

[0058] As shown in Figure 12, the mounting plate 110 has a plurality of openings 112 arranged at intervals in the nozzle circumferential direction. The openings 112 are holes that penetrate the mounting plate 110 in the nozzle radial direction. The nozzle axial range of the openings 112 completely includes the outer end 57 of one of the fuel supply units 50. Furthermore, the nozzle radial range of the openings 112 completely includes the outer end 57 of one of the fuel supply units 50. With the above configuration, air passing through the plurality of openings 112 is guided to the introduction flow path 59. A secondary flow of air is generated when the air passes through the openings 112, which can promote mixing of the air and fuel.

[0059] <Two-stage combustion nozzle according to fourth embodiment> A two-stage combustion nozzle 24 (20) according to a fourth embodiment will be described with reference to Figure 13. Note that the same components as those in the above-described two-stage combustion nozzles 21 to 23 are given the same reference numerals in the drawings, and their description will be omitted or will not be repeated below.

[0060] In the fourth embodiment, a sidewall 42 of a combustion liner 40 includes a sidewall inner circumferential surface 43 that defines a combustion chamber 47, a sidewall outer circumferential surface 44 opposite to the sidewall inner circumferential surface 43, and a sidewall flow passage forming portion 46. The sidewall flow passage forming portion 46 forms a sidewall cooling flow passage 45 through which cooling air flows in the axial direction of the combustion liner 40 between the sidewall inner circumferential surface 43 and the sidewall outer circumferential surface 44. The cooling air is compressed air sent from the compressor 2 to the gas turbine combustor 4. The compressed air is preferably cooled by a cooler (not shown).

[0061] The main passage forming portion 60 of the two-stage combustion nozzle 24 includes an outer peripheral surface 67 opposite to the inner peripheral surface 68 described above, and a nozzle cooling passage forming portion 66 that forms a nozzle cooling passage 65. The nozzle cooling passage 65 is disposed between the inner peripheral surface 68 and the outer peripheral surface 67 and communicates with the sidewall cooling passage 45 of the combustion liner 40. Therefore, cooling air flows through the nozzle cooling passage 65. The nozzle cooling passage 65 is disposed on the outlet opening 41 side with respect to at least a portion of the auxiliary air guide passage 99. In this example, the nozzle cooling passage 65 is disposed within the nozzle axial range of the film air passage 88 and is disposed on the outlet opening 41 side with respect to the entire auxiliary air guide passage 99.

[0062] The nozzle cooling flow passage 65 includes an annular cooling flow passage 61 extending in the nozzle circumferential direction so as to surround the main flow passage 69, radially extending flow passages 62 extending linearly from the annular cooling flow passage 61 toward the outside in the nozzle radial direction, and a nozzle axially extending flow passage 63 extending from the outer end of the radially extending flow passage 62 in the nozzle radial direction toward the opposite side from the outlet opening 41. The annular cooling flow passage 61 extends continuously over the entire length of the nozzle body 25 in the nozzle circumferential direction.

[0063] The flow of cooling air will be outlined below. Cooling air is supplied to the sidewall cooling passage 45 from the axial side of the combustion liner 40 opposite the combustor 8 (see FIG. 2 ) (arrow A1). The cooling air supplied from the sidewall cooling passage 45 to the nozzle cooling passage 65 flows into the annular cooling passage 61 via the nozzle axially extending passage 63 and the radially extending passage 62 (arrows A2 and A3). The cooling air flowing through the annular cooling passage 61 passes through the radially extending passage 62 and the nozzle axially extending passage 63, both of which are on the combustor 8 side (arrows A4 and A5), and then flows into the sidewall cooling passage 45 (arrow A6).

[0064] According to the above configuration, the nozzle cooling passage 65 is disposed on the outlet opening 41 side of at least a portion of the auxiliary air guide passage 99, so that the portion of the main passage forming portion 60 on the outlet opening 41 side can be cooled. Therefore, the temperature gradient of the nozzle body 25 in the nozzle axial direction can be made gentle. This makes it possible to suppress flame stabilization in the nozzle body 25 due to unintended ignition of fuel in the main passage 69, for example.

[0065] Furthermore, because the annular cooling flow path 61 surrounds the main flow path 69 in the nozzle circumferential direction, the cooling air can sufficiently cool the main flow path forming portion 60 of the nozzle main body 25. Additionally, the configuration in which the nozzle axial direction extending flow path 63 is provided can expand the range in the nozzle axial direction over which the cooling air cools the main flow path forming portion 60. This can further reduce the temperature gradient of the nozzle main body 25 in the nozzle axial direction.

[0066] <Summary> The contents described in the above-described embodiments can be understood, for example, as follows.

[0067] 1) A two-stage combustion nozzle (20, 21, 22, 23, 24) according to at least one embodiment of the present disclosure is a two-stage combustion nozzle arranged on a side wall (42) of a combustion liner (40) that defines a combustion chamber (47) of a gas turbine (100) for supplying air and fuel to the combustion chamber, the two-stage combustion nozzle comprising: a nozzle body having an outlet opening (41) that communicates with the combustion chamber, a top plate portion (30) extending in a direction perpendicular to a nozzle axis direction of the two-stage combustion nozzle; and a plurality of fuel supply portions (50) that are erected from the top plate portion along the nozzle axis direction and are arranged at intervals in a nozzle circumferential direction of the two-stage combustion nozzle, wherein two adjacent fuel supply portions (50) in the nozzle circumferential direction define an introduction flow path (59) for introducing the air from the outer side to the inner side in the nozzle radial direction of the two-stage combustion nozzle. a main flow path forming portion (60) that forms a main flow path (69) for guiding a mixed fluid containing the fuel supplied from the fuel supply holes (55) of each of the plurality of combustion supply portions and the air introduced by the introduction flow path to the outlet opening along the nozzle axial direction, wherein the top plate portion has at least one first auxiliary air introduction hole (31) that is positioned outward in the nozzle radial direction from inner ends (54) of each of the plurality of combustion supply portions.

[0068] According to the configuration of 1) above, the introduction passage extends along the nozzle radial direction, allowing the two-stage combustion nozzle to be made compact in the nozzle axial direction. Furthermore, the first auxiliary air, which is the auxiliary air supplied from the first auxiliary air introduction hole, is guided into the main passage, reducing the fuel concentration of the mixed fluid near the inner end of the fuel supply section. This makes it possible to suppress flame holding within the nozzle body, which may be caused by unintended fuel ignition within the main passage. This achieves a compact two-stage combustion nozzle that can efficiently supply fuel and air to the combustion chamber.

[0069] 2) In some embodiments, in the two-stage combustion nozzle described in 1) above, the at least one first auxiliary air introduction hole is a plurality of first auxiliary air introduction holes (31) arranged at intervals in the circumferential direction of the nozzle, an auxiliary air chamber (52) is formed inside each of the plurality of fuel supply sections into which first auxiliary air that has passed through any of the plurality of first auxiliary air introduction holes is introduced, and each of the plurality of fuel supply sections has an auxiliary air hole (58) communicating with the auxiliary air chamber.

[0070] According to the configuration of 2) above, the first auxiliary air in the auxiliary air chamber is added to the mixed fluid through the auxiliary air holes. In the design phase of the two-stage combustion nozzle, the layout constraints imposed when arranging the auxiliary air holes are smaller than the constraints imposed when arranging the first auxiliary air inlet holes, particularly in the nozzle axial direction. This allows for a more optimal supply position for the first auxiliary air, enabling the first auxiliary air to be mixed well with the fuel and air. This reduces the fuel concentration in the mixed fluid and suppresses flame stabilization within the nozzle body.

[0071] 3) In some embodiments, in the two-stage combustion nozzle described in 2) above, in each of the plurality of fuel supply sections, the fuel supply hole is arranged further outward in the nozzle radial direction than the auxiliary air hole.

[0072] According to the configuration of 3) above, the fuel supply hole can be disposed radially outward of the nozzle. This lengthens the flow path through which the fuel mixes with the air, promoting the mixing of the fuel and air. This prevents the fuel concentration from increasing locally in the mixed fluid.

[0073] 4) In some embodiments, in the two-stage combustion nozzle described in 2) or 3) above, the fuel supply hole is configured to supply the fuel to the introduction passage along a direction perpendicular to the nozzle radial direction.

[0074] According to the configuration of 4) above, the flow direction of the fuel supplied from the fuel supply hole and the flow direction of the air introduced by the introduction flow path are approximately perpendicular to each other, thereby promoting mixing of the fuel and air.

[0075] 5) In some embodiments, in the two-stage combustion nozzle according to any one of 2) to 4) above, each of the plurality of fuel supply portions has a streamlined shape extending along the nozzle radial direction.

[0076] According to the configuration of 5), wake of the mixed fluid can be suppressed radially inward of the inner ends of the fuel supply sections, thereby further reducing the fuel concentration near the inner ends of the fuel supply sections and suppressing flame holding within the nozzle body.

[0077] 6) In some embodiments, the two-stage combustion nozzle described in 5) above, wherein the auxiliary air holes are formed at the inner end of each of the plurality of fuel supply sections.

[0078] According to the configuration of 6) above, the wake of the mixed fluid can be further suppressed on the inner side of each fuel supply portion in the nozzle radial direction, and the fuel concentration in the vicinity of the inner end portion of the fuel supply portion can be further reduced.

[0079] 7) In some embodiments, in the two-stage combustion nozzle described in any one of 1) to 6) above, the nozzle body further includes a pointed protrusion (10) that protrudes from the top plate portion toward the outlet opening on the inner side in the nozzle radial direction than the plurality of introduction passages and tapers toward the outlet opening side, and the pointed protrusion has a guide side surface (72) that is a guide side surface for guiding the mixed fluid that is introduced toward the inner side in the nozzle radial direction by each of the plurality of introduction passages along the nozzle axial direction, and that curves toward the outlet opening side as it moves toward the inner side in the nozzle radial direction.

[0080] According to the above configuration 7), pressure loss can be suppressed when the mixed fluid flowing from the outside to the inside in the nozzle radial direction is guided to the outlet opening side.

[0081] 8) In some embodiments, in the two-stage combustion nozzle described in 7) above, the nozzle body further includes a circumferential extending portion (80) that is connected to connection ends (49) that are ends of each of the plurality of fuel supply units on the outlet opening side in the nozzle axial direction and extends in the nozzle circumferential direction, the circumferential extending portion has a first peripheral edge portion (81) that extends in the nozzle circumferential direction and is located outside of outer ends of each of the plurality of fuel supply units in the nozzle radial direction, the top plate portion has a second peripheral edge portion (34) that faces the first peripheral edge portion in the nozzle axial direction, the first peripheral edge portion and the second peripheral edge portion define an air inlet (29) that guides the air to the introduction flow path, and the air inlet has a bell-mouth shape in which an inner diameter of the air inlet increases toward the outside in the radial direction.

[0082] The configuration of 8) above reduces the pressure loss of the air passing through the air inlet and makes the velocity distribution of the air at the air inlet uniform. This realizes a compact two-stage combustion nozzle that uniformly introduces the required amount of air. In particular, in an embodiment in which the amount of air introduced by the air inlet accounts for 50% or more of the amount of air released from the outlet opening, other inlets that introduce air can be made compact, thereby realizing a further compact two-stage combustion nozzle.

[0083] 9) In some embodiments, in the two-stage combustion nozzle described in 7) or 8) above, the top plate portion further has an inner auxiliary air inlet hole (35) arranged radially inward of the at least one first auxiliary air inlet hole, and a protrusion internal flow path (75) is formed inside the pointed protrusion to guide second auxiliary air that has passed through the inner auxiliary air inlet hole to the guide side surface.

[0084] According to the above configuration 9), the second auxiliary air can be added to the mixed fluid flowing toward the outlet opening, so that the fuel concentration in the mixed fluid can be made uniform.

[0085] 10) In some embodiments, in the two-stage combustion nozzle of any of 7) to 9) above, the top plate portion further has an inner auxiliary air inlet hole (35) that is arranged radially inward of the at least one first auxiliary air inlet hole, and a central flow passage (79) inside the pointed protrusion is formed for discharging second auxiliary air that has passed through the inner auxiliary air inlet hole toward the outlet opening along the nozzle axial direction.

[0086] The configuration 10) above provides the same technical advantages as the configuration 9) above.

[0087] 11) In some embodiments, in the two-stage combustion nozzle described in any one of 2) to 6) above, the nozzle body further includes: a circumferential extending portion (80) connected to connection ends (49) that are ends of each of the plurality of fuel supply portions on the outlet opening side in the nozzle axial direction, and extending in the nozzle circumferential direction; and a plurality of guide wall portions (90) that stand from the circumferential extending portion toward the outlet opening side and are arranged at intervals in the nozzle circumferential direction, and two of the plurality of guide wall portions that are adjacent in the nozzle circumferential direction define auxiliary air guide flow paths (99) for guiding third auxiliary air supplied from the outer side to the inner side in the nozzle radial direction to the main flow path.

[0088] According to the configuration of 11) above, third auxiliary air can be added to the mixed fluid flowing toward the outlet opening, thereby making the concentration of the mixed fluid uniform. Furthermore, since the guide wall portion defining the auxiliary air guide passage extends from the circumferential extending portion toward the outlet opening, the auxiliary air guide passage is disposed between the fuel injection holes and the combustion chamber in the nozzle axial direction. This makes it possible to reduce the temperature gradient inside the nozzle body and to suppress flame stabilization in the nozzle body due to unintended fuel ignition in the main passage.

[0089] 12) In some embodiments, in the two-stage combustion nozzle described in 11) above, the circumferential extending portion has a plurality of first communication holes (91) for guiding at least a portion of the third auxiliary air in the auxiliary air guide passage to the auxiliary air chamber.

[0090] According to the configuration of 12), the third auxiliary air is introduced into the auxiliary air chamber in addition to the first auxiliary air, which increases the amount of auxiliary air supplied from the auxiliary air hole and further reduces the fuel concentration in the mixed fluid.

[0091] 13) In some embodiments, in the two-stage combustion nozzle described in 11) or 12) above, each of the plurality of guide wall portions has a communication opening hole (95) that communicates with each of the two auxiliary air guide passages that are adjacent to each other in the nozzle circumferential direction.

[0092] According to the configuration of 13), the pressure among the plurality of auxiliary air guide passages can be made uniform, thereby allowing the third auxiliary air to be uniformly supplied from the plurality of auxiliary air guide passages to the plurality of auxiliary air chambers, respectively.

[0093] 14) In some embodiments, in the two-stage combustion nozzle described in any one of 11) to 13) above, the circumferentially extending portion has a plurality of second communication holes (92) for guiding a portion of the third auxiliary air flowing through the plurality of auxiliary air guide passages to the plurality of introduction passages, respectively.

[0094] According to the above configuration 14), the third auxiliary air introduced through the second communication hole is added to the mixed fluid, thereby further reducing the fuel concentration in the mixed fluid.

[0095] 15) In some embodiments, in the two-stage combustion nozzle described in any one of 11) to 14) above, the circumferential extension portion further has an inner wall portion (89) supported by inner ends (94) of each of the plurality of guide wall portions in the nozzle radial direction and arranged opposite an inner peripheral surface (68) of the main flow path forming portion, and the inner wall portion and the main flow path forming portion define a film air flow path (88) for flowing at least a portion of the third auxiliary air guided by the plurality of auxiliary air guide passages along the inner peripheral surface of the main flow path forming portion toward the outlet opening.

[0096] According to the configuration of 15) above, film air is supplied from the film air flow passage into the fuel chamber, which makes it possible to suppress flashback, in which the flame in the fuel chamber flows back into the main flow passage.

[0097] 16) In some embodiments, in the two-stage combustion nozzle described in any one of 11) to 15) above, the circumferentially extending portion has: a first peripheral edge portion (81) extending in the nozzle circumferential direction outside the outer ends (57) of each of the plurality of fuel supply portions in the nozzle radial direction; and a plurality of protrusions (10) protruding from the first peripheral edge portion toward the top plate portion in the nozzle axial direction and arranged at intervals in the nozzle circumferential direction, wherein the nozzle circumferential range of each of the plurality of protrusions is included in the nozzle circumferential range of any one of the plurality of introduction flow paths.

[0098] According to the configuration of 16) above, a secondary flow of air is generated at the inlet of the introduction passage, which can promote the mixing of air and fuel.

[0099] 17) In some embodiments, in the two-stage combustion nozzle described in 16) above, the tip (13) of each of the plurality of protrusions is positioned closer to the top plate portion in the nozzle axial direction than the end (57E) of the outer end of each of the plurality of fuel supply portions on the circumferentially extending portion side.

[0100] According to the configuration of 17) above, the secondary flow of air generated at the inlet of the introduction passage can be further strengthened, and the mixing of air and fuel can be promoted.

[0101] 18) In some embodiments, in the two-stage combustion nozzle described in 16) or 17) above, the plurality of protrusions include a plurality of first protrusions (10) arranged at intervals in the nozzle circumferential direction, and a plurality of second protrusions (10) arranged at intervals in the nozzle circumferential direction at nozzle radial positions offset from the first protrusions, and the plurality of first protrusions and the plurality of second protrusions are arranged alternately in the nozzle circumferential direction.

[0102] According to the configuration of 18) above, the secondary flow of air generated at the inlet of the introduction passage can be further strengthened, and the mixing of air and fuel can be promoted.

[0103] 19) In some embodiments, the two-stage combustion nozzle is described in any one of 11) to 18) above, wherein the circumferentially extending portion has a first peripheral edge portion (81) located outward in the nozzle radial direction relative to each of the plurality of fuel supply portions, the top plate portion has a second peripheral edge portion (34) facing the first peripheral edge portion in the nozzle axial direction, and the nozzle body further includes an attachment plate (110) attached to the first peripheral edge portion and the second peripheral edge portion and extending in the nozzle circumferential direction, the attachment plate having a plurality of openings (112) formed therein and spaced apart in the nozzle circumferential direction.

[0104] According to the configuration of 19) above, the air passing through the plurality of openings is guided to the introduction flow path. A secondary flow of the air is generated when the air passes through the openings, which can promote mixing of the air and fuel.

[0105] 20) In some embodiments, in the two-stage combustion nozzle described in any one of 1) to 19) above, the top plate portion further has a plurality of second auxiliary air introduction holes (32) arranged alternately with the plurality of combustion supply portions in the nozzle circumferential direction, for introducing fourth auxiliary air into the plurality of introduction flow paths, respectively.

[0106] According to the configuration of 20) above, the fourth auxiliary air passing through the second auxiliary air inlet can be added to the mixed fluid, so that the concentration of fuel in the mixed fluid can be reduced.

[0107] 21) In some embodiments, in the two-stage combustion nozzle described in any one of 14) to 18) above, the side wall of the combustion liner includes: a side wall inner peripheral surface (43) that defines the combustion chamber; a side wall outer peripheral surface (44) opposite the side wall inner peripheral surface; and a side wall flow path forming portion (46) that forms a side wall cooling flow path (45) between the side wall inner peripheral surface and the side wall outer peripheral surface through which cooling air flows in the axial direction of the combustion liner; the main flow path forming portion includes: an outer peripheral surface (67) opposite the inner peripheral surface; and a nozzle cooling flow path forming portion (66) that forms a nozzle cooling flow path (65) that is formed between the inner peripheral surface and the outer peripheral surface and is in communication with the side wall cooling flow path; and the nozzle cooling flow path is arranged on the outlet opening side with respect to at least a portion of the auxiliary air guide flow path.

[0108] According to the configuration of 21) above, the nozzle cooling passage is disposed on the outlet opening side of at least a portion of the auxiliary air guide passage, so that the temperature gradient of the nozzle body in the nozzle axial direction can be made gentle, thereby making it possible to suppress flame holding in the nozzle body due to unintended fuel ignition in the main passage, etc.

[0109] 22) In some embodiments, in the two-stage combustion nozzle described in 21) above, the nozzle cooling flow path includes an annular cooling flow path (61) extending in the nozzle circumferential direction, and a radially extending flow path (62) extending linearly from the annular cooling flow path toward the outside in the nozzle radial direction.

[0110] According to the configuration of 22) above, the annular cooling passage surrounds the main passage in the nozzle circumferential direction, so that the cooling air can sufficiently cool the main passage forming portion of the nozzle body, thereby making it possible to further moderate the temperature gradient of the nozzle body in the nozzle axial direction.

[0111] 23) In some embodiments, in the two-stage combustion nozzle described in 22) above, the nozzle cooling passage further includes a nozzle axially extending passage (63) extending from an outer end of the radially extending passage in the nozzle radial direction toward the opposite side from the outlet opening.

[0112] According to the configuration of 23) above, the range in the nozzle axial direction in which the main flow passage forming portion is cooled by the cooling air can be expanded, thereby making it possible to further moderate the temperature gradient of the nozzle body in the nozzle axial direction.

[0113] 24) A gas turbine combustor (4) according to an embodiment of the present disclosure comprises: the combustion liner (40) that defines the combustion chamber (47); a combustor (8) that supplies the fuel to the combustion liner; and a two-stage combustion nozzle according to any one of 1) to 23) above, that is arranged downstream of the combustor in a flow direction of combustion gas in the combustion chamber.

[0114] According to the configuration 24) above, the same technical advantages as those of the configuration 1) above can be obtained.

[0115] DESCRIPTION OF SYMBOLS 2: Compressor 4: Gas turbine combustor 5: Generator 6: Turbine 8: Combustor 9: Rotating shaft 10: Protrusion 11: First protrusion 12: Second protrusion 13: Tip 20, 21, 22, 23, 24: Two-stage combustion nozzle 25: Nozzle body 29: Air inlet 30: Top plate portion 31: First auxiliary air inlet hole 32: Second auxiliary air inlet hole 34: Second peripheral portion 35: Inner auxiliary air inlet hole 40: Combustion liner 41: Outlet opening 42: Side wall 43: Side wall inner peripheral surface 44: Side wall outer peripheral surface 45: Side wall cooling channel 46: Side wall channel forming portion 47: Combustion chamber 49: Connection end portion 50: Fuel supply portion 51: Fuel body portion 52 : Auxiliary air chamber 53 : Fuel chamber 54 : Inner end 55 : Fuel supply hole 57 : Outer end 57E : End 58 : Auxiliary air hole 59 : Inlet passage 60 : Main passage forming portion 61 : Annular cooling passage 62 : Radially extending passage 63 : Nozzle axially extending passage 65 : Nozzle cooling passage 66 : Nozzle cooling passage forming portion 67 : Outer peripheral surface 68 : Inner peripheral surface 69 : Main passage 70 : Pointed projection 72 : Guide side surface 75 : Protrusion internal passage 76 : Center side internal passage 77 : Protrusion internal guide passage 79 : Protrusion internal central passage 80 : Circumferentially extending portion 81 : First peripheral edge portion 87 : End face 88 : Film air passage 89 : Inner wall portion 90 : Guide wall portion 91 : First communication hole 92: Second communication hole 94: Inner end portion 95: Communication opening hole 99: Auxiliary air guide passage 100: Gas turbine 110: Mounting plate 112: Opening S: Axis line Z: Center line

Claims

1. A two-stage combustion nozzle arranged on a side wall of a combustion liner that defines a combustion chamber of a gas turbine, for supplying air and fuel to the combustion chamber, comprising: a nozzle body having an outlet opening formed therein that communicates with the combustion chamber, the nozzle body including: a top plate portion extending in a direction perpendicular to a nozzle axial direction of the two-stage combustion nozzle; a plurality of fuel supply portions erected from the top plate portion along the nozzle axial direction and arranged at intervals in the nozzle circumferential direction of the two-stage combustion nozzle, wherein two adjacent fuel supply portions in the nozzle circumferential direction define an introduction flow path for introducing the air from the outer side to the inner side in the nozzle radial direction of the two-stage combustion nozzle; and a main flow path forming portion that forms a main flow path for guiding a mixed fluid containing the fuel supplied from the fuel supply holes of each of the plurality of fuel supply portions and the air introduced by the introduction flow path to the outlet opening along the nozzle axial direction, wherein the top plate portion has at least one first auxiliary air introduction hole arranged outward in the nozzle radial direction than the inner ends of each of the plurality of fuel supply portions.

2. A two-stage combustion nozzle as set forth in claim 1, wherein the at least one first auxiliary air introduction hole is a plurality of first auxiliary air introduction holes arranged at intervals in the circumferential direction of the nozzle, an auxiliary air chamber is formed inside each of the plurality of fuel supply sections into which first auxiliary air that has passed through any of the plurality of first auxiliary air introduction holes is introduced, and each of the plurality of fuel supply sections has an auxiliary air hole communicating with the auxiliary air chamber.

3. A two-stage combustion nozzle according to claim 2, wherein in each of said plurality of fuel supply sections, said fuel supply holes are arranged further outward in the nozzle radial direction than said auxiliary air holes.

4. A two-stage combustion nozzle according to claim 2 or 3, wherein the fuel supply hole is configured to supply the fuel to the introduction passage along a direction perpendicular to the nozzle radial direction.

5. A two-stage combustion nozzle according to claim 2 or 3, wherein each of the plurality of fuel supply sections has a streamlined shape extending along the nozzle radial direction.

6. A two-stage combustion nozzle according to claim 5, wherein the auxiliary air holes are formed at the inner end of each of the plurality of fuel supply sections.

7. A two-stage combustion nozzle as set forth in any one of claims 1 to 3, wherein the nozzle body further includes a pointed protrusion that protrudes from the top plate portion toward the outlet opening on the inner side in the nozzle radial direction than the plurality of introduction passages and that tapers toward the outlet opening side, the pointed protrusion having a guide side surface for guiding the mixed fluid that is introduced toward the inner side in the nozzle radial direction by each of the plurality of introduction passages along the nozzle axial direction, the guide side surface curving toward the outlet opening side as it moves toward the inner side in the nozzle radial direction.

8. The two-stage combustion nozzle according to claim 7, wherein the nozzle body is connected to connection ends, which are ends of each of the plurality of fuel supply units on the outlet opening side in the nozzle axial direction, and further includes a circumferential extending portion extending in the nozzle circumferential direction, the circumferential extending portion having a first peripheral edge portion extending in the nozzle circumferential direction and outward from outer ends of each of the plurality of fuel supply units in the nozzle radial direction, the top plate portion having a second peripheral edge portion opposing the first peripheral edge portion in the nozzle axial direction, the first peripheral edge portion and the second peripheral edge portion defining an air inlet that guides the air to the introduction flow path, and the air inlet has a bell-mouth shape in which an inner diameter of the air inlet increases toward the outside in the radial direction.

9. A two-stage combustion nozzle as set forth in claim 7, wherein the top plate portion further has an inner auxiliary air inlet hole disposed radially inward of the at least one first auxiliary air inlet hole, and a projection internal guide flow path is formed inside the pointed projection for guiding second auxiliary air that has passed through the inner auxiliary air inlet hole to the guide side surface.

10. A two-stage combustion nozzle as set forth in claim 7, wherein the top plate portion further has an inner auxiliary air inlet hole disposed radially inward of the at least one first auxiliary air inlet hole, and a central flow passage is formed inside the pointed protrusion to discharge second auxiliary air that has passed through the inner auxiliary air inlet hole toward the outlet opening along the nozzle axial direction.

11. A two-stage combustion nozzle as set forth in claim 2 or 3, wherein the nozzle body further includes: a circumferential extending portion connected to connection ends, which are ends of each of the plurality of fuel supply portions on the outlet opening side in the nozzle axial direction, and extending in the nozzle circumferential direction; and a plurality of guide wall portions erected from the circumferential extending portion toward the outlet opening side and arranged at intervals in the nozzle circumferential direction, wherein two of the plurality of guide wall portions adjacent to each other in the nozzle circumferential direction define auxiliary air guide flow paths for guiding third auxiliary air supplied from the outer side to the inner side in the nozzle radial direction to the main flow path.

12. A two-stage combustion nozzle as set forth in claim 11, wherein the circumferentially extending portion has a plurality of first communication holes for guiding at least a portion of the third auxiliary air in the auxiliary air guide passage to the auxiliary air chamber.

13. A two-stage combustion nozzle as set forth in claim 11, wherein each of the plurality of guide wall portions has a communication opening hole that communicates with each of two of the auxiliary air guide passages that are adjacent in the nozzle circumferential direction.

14. A two-stage combustion nozzle as set forth in claim 11, wherein the circumferentially extending portion has a plurality of second communication holes for guiding a portion of the third auxiliary air flowing through the plurality of auxiliary air guide passages to the plurality of introduction passages, respectively.

15. A two-stage combustion nozzle as set forth in claim 11, wherein the circumferential extending portion further has an inner wall portion supported by inner ends in the nozzle radial direction of each of the plurality of guide wall portions and arranged opposite the inner peripheral surface of the main flow path forming portion, and the inner wall portion and the main flow path forming portion define a film air flow path for causing at least a portion of the third auxiliary air guided by the plurality of auxiliary air guide passages to flow along the inner peripheral surface of the main flow path forming portion toward the outlet opening.

16. A two-stage combustion nozzle as set forth in claim 11, wherein the circumferential extending portion has: a first peripheral edge portion extending in the nozzle circumferential direction, outward of the outer ends of each of the plurality of fuel supply portions in the nozzle radial direction; and a plurality of protrusions protruding from the first peripheral edge portion toward the top plate portion in the nozzle axial direction and arranged at intervals in the nozzle circumferential direction, and the nozzle circumferential range of each of the plurality of protrusions is included in the nozzle circumferential range of any one of the plurality of introduction flow paths.

17. A two-stage combustion nozzle as set forth in claim 16, wherein the tip of each of the plurality of protrusions is positioned closer to the top plate portion in the nozzle axial direction than the end of the outer end of each of the plurality of fuel supply portions on the side of the circumferentially extending portion.

18. A two-stage combustion nozzle as described in claim 16, wherein the plurality of protrusions comprises: a plurality of first protrusions arranged at intervals in the nozzle circumferential direction; and a plurality of second protrusions arranged at intervals in the nozzle circumferential direction at nozzle radial positions offset from the first protrusions, and the plurality of first protrusions and the plurality of second protrusions are arranged alternately in the nozzle circumferential direction.

19. A two-stage combustion nozzle as set forth in claim 11, wherein the circumferentially extending portion has a first peripheral edge portion located outward in the nozzle radial direction than each of the plurality of fuel supply portions, the top plate portion has a second peripheral edge portion facing the first peripheral edge portion in the nozzle axial direction, and the nozzle body further includes an attachment plate attached to the first peripheral edge portion and the second peripheral edge portion and extending in the nozzle circumferential direction, the attachment plate having a plurality of openings formed therein and spaced apart in the nozzle circumferential direction.

20. A two-stage combustion nozzle as set forth in any one of claims 1 to 3, wherein the top plate portion further has a plurality of second auxiliary air introduction holes arranged alternately with the plurality of combustion supply portions in the circumferential direction of the nozzle, the second auxiliary air introduction holes being for respectively introducing fourth auxiliary air into the plurality of introduction flow paths.

21. A two-stage combustion nozzle as set forth in claim 14, wherein the side wall of the combustion liner includes: a side wall inner peripheral surface that defines the combustion chamber; a side wall outer peripheral surface opposite to the side wall inner peripheral surface; and a side wall flow path forming portion that forms a side wall cooling flow path between the side wall inner peripheral surface and the side wall outer peripheral surface for cooling air to flow in the axial direction of the combustion liner; and the main flow path forming portion includes an outer peripheral surface opposite to the inner peripheral surface; and a nozzle cooling flow path forming portion that forms a nozzle cooling flow path that is formed between the inner peripheral surface and the outer peripheral surface and communicates with the side wall cooling flow path; and the nozzle cooling flow path is arranged on the outlet opening side with respect to at least a portion of the auxiliary air guide flow path.

22. A two-stage combustion nozzle as set forth in claim 21, wherein the nozzle cooling passage includes: an annular cooling passage extending in the circumferential direction of the nozzle; and radially extending passages extending linearly from the annular cooling passage toward the outside in the radial direction of the nozzle.

23. A two-stage combustion nozzle according to claim 22, wherein the nozzle cooling passage further includes a nozzle axially extending passage extending from an outer end of the radially extending passage in the nozzle radial direction toward an opposite side to the outlet opening.

24. A gas turbine combustor comprising: a combustion liner that defines the combustion chamber; a combustor that supplies the fuel to the combustion liner; and a two-stage combustion nozzle according to any one of claims 1 to 3, which is arranged downstream of the combustor in the flow direction of combustion gas in the combustion chamber.

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