Burner, combustor, and gas turbine

Abstract

This burner comprises: a plate that has formed therein a plurality of mixing flow passages being configured to have air supplied therein and extending along an axial direction, and that has an upstream-side end surface and a downstream-side end surface in the axial direction; a plurality of fuel nozzles that are configured so as to eject fuel into the plurality of mixing flow passages; a plurality of support parts for supporting the plurality of fuel nozzles on the plate; and a fuel flow passage that is formed inside the plate and that is for supplying the fuel to the plurality of fuel nozzles. The fuel flow passage: includes a plurality of axial passages that extend along the axial direction and that are for guiding the fuel to the plurality of fuel nozzles; and comprises, inside the plate, at least one cavity that is provided further radially outward than the plurality of fuel nozzles and the plurality of axial passages.

Description

Burner, Combustor, and Gas Turbine

[0001] This disclosure relates to a burner, a combustor, and a gas turbine. This application claims priority based on Japanese Patent Application No. 2024-221672 filed with the Japan Patent Office on December 18, 2024, and incorporates its content herein by reference.

[0002] As a burner of a combustor such as a gas turbine, there is a case where a burner is used that includes a plurality of mixing channels (holes) extending along the axial direction of the burner, and mixes air supplied to each mixing channel with fuel injected into the mixing channel and ejects it into the combustion chamber.

[0003] Patent Document 1 describes a burner including a plurality of mixing channels to which air is supplied, a plurality of fuel nozzles for injecting fuel, and a plurality of support portions that respectively connect the plurality of fuel nozzles and the channel walls of the mixing channels. The plurality of fuel nozzles are provided such that the central axis of each fuel nozzle coincides with the central axis of the mixing channel. In the mixing channel, the fuel ejected from the fuel nozzle and the air are mixed, and the air-fuel mixture flow formed thereby is ejected from the mixing channel into the combustion chamber of the combustor.

[0004] Japanese Unexamined Patent Application Publication No. 2021-173190

[0005] By the way, when forming a burner including a fuel nozzle supported on the inner wall surface of a mixing channel via a support portion, as in the burner described in Patent Document 1 for example, in the cooling process during or after the additional shaping, the member in which the mixing channel is formed may be deformed due to thermal contraction, and with this deformation, the tilting of the fuel nozzle (the inclination of the central axis of the fuel nozzle with respect to the central axis of the mixing channel) may occur. When the tilting of the fuel nozzle occurs, the mixing state of air and fuel in the mixing channel tends to become non-uniform, and there is a risk of abnormal combustion such as flashback.

[0006] In view of the above circumstances, at least one embodiment of the present invention aims to provide a burner, a combustor, and a gas turbine capable of suppressing the tilting of a fuel nozzle in a burner formed by additional shaping.

[0007] A burner according to at least one embodiment of the present invention comprises: a plate having an upstream end face and a downstream end face in the axial direction, having a plurality of mixing channels formed therein that are configured to be supplied with air and extend along the axial direction; a plurality of fuel nozzles configured to inject fuel into the plurality of mixing channels, each; a plurality of support parts for supporting the plurality of fuel nozzles on the plate, each; and a fuel channel formed inside the plate for supplying the fuel to the plurality of fuel nozzles, wherein the fuel channel extends along the axial direction and includes a plurality of axial passages for guiding the fuel to the plurality of fuel nozzles, each, and comprises at least one cavity provided inside the plate radially outward from the plurality of fuel nozzles and the plurality of axial passages.

[0008] Furthermore, a combustor according to at least one embodiment of the present invention comprises the burner described above and a combustion cylinder provided downstream of the burner.

[0009] Furthermore, a gas turbine according to at least one embodiment of the present invention comprises the above-described combustor and a turbine configured to be driven by the combustion gas from the combustor.

[0010] According to at least one embodiment of the present invention, a burner, a combustor, and a gas turbine are provided that can suppress the tilting of the fuel nozzle in a burner formed by additive molding.

[0011] This is a schematic diagram of a gas turbine according to one embodiment. This is a schematic cross-sectional view showing the combustor of a gas turbine according to one embodiment. This is a schematic cross-sectional view along the axial direction of a burner according to one embodiment. This is a diagram showing a cross-section perpendicular to the axial direction of a burner according to one embodiment. This is a diagram showing a cross-section perpendicular to the axial direction of a burner according to one embodiment. This is a diagram showing a cross-section perpendicular to the axial direction of a burner according to one embodiment. This is a schematic cross-sectional view along the axial direction of a burner according to one embodiment. This is a schematic cross-sectional view along the axial direction of a burner according to one embodiment. This is a schematic cross-sectional view along the axial direction of a burner according to one embodiment. This is a schematic cross-sectional view along the axial direction of a burner according to one embodiment.

[0012] Hereinafter, several embodiments of the present invention will be described with reference to the attached drawings. However, the dimensions, materials, shapes, relative arrangements, etc., of the components described as embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0013] First, a gas turbine, which is an example of an application for burners and combustors according to several embodiments, will be described with reference to Figure 1. Figure 1 is a schematic configuration diagram of a gas turbine according to one embodiment. As shown in Figure 1, the gas turbine 100 includes a compressor 2 for generating compressed air, a combustor 4 for generating combustion gas using compressed air and fuel, and a turbine 6 configured to be rotationally driven by the combustion gas. In the case of a gas turbine 100 for power generation, a generator (not shown) is connected to the turbine 6.

[0014] The compressor 2 includes a plurality of stationary vanes 16 fixed to the compressor casing 10 side, and a plurality of rotor blades 18 mounted on the rotor 8 so as to be alternately arranged with respect to the stationary vanes 16. Air taken in from the air intake 12 is supplied to the compressor 2, and this air is compressed by passing through the plurality of stationary vanes 16 and the plurality of rotor blades 18 to become high-temperature, high-pressure compressed air.

[0015] The combustor 4 is supplied with fuel and compressed air generated by the compressor 2. In the combustor 4, the fuel is burned, and combustion gas, which is the working fluid for the turbine 6, is generated. As shown in Figure 1, the gas turbine 100 has a plurality of combustors 4 arranged circumferentially around the central axis O of the rotor 8 within the casing 20.

[0016] The turbine 6 includes a plurality of stator blades 24 and rotor blades 26 provided in the combustion gas passage formed by the turbine casing 22. The stator blades 24 and rotor blades 26 of the turbine 6 are located downstream of the combustor 4 with respect to the flow of combustion gases. The stator blades 24 are fixed to the turbine casing 22 side, and a plurality of stator blades 24 arranged along the circumferential direction of the rotor 8 constitute a stator blade row. The rotor blades 26 are embedded in the rotor 8, and a plurality of rotor blades 26 arranged along the circumferential direction of the rotor 8 constitute a rotor blade row. The stator blade row and the rotor blade row are arranged alternately in the axial direction of the rotor 8.

[0017] In the turbine 6, combustion gas from the combustor 4 flows into the combustion gas passage and passes through multiple stationary blades 24 and multiple rotor blades 26, thereby driving the rotor 8 to rotate. This drives a generator connected to the rotor 8, generating electricity. After driving the turbine 6, the combustion gas is discharged to the outside through the exhaust chamber 30.

[0018] Figure 2 is a schematic cross-sectional view showing a combustor 4 of a gas turbine 100 according to one embodiment. As shown in Figure 2, the combustor 4 includes a burner 48 for burning fuel and a combustion cylinder 36 provided downstream of the burner 48 (i.e., closer to the turbine 6 than the burner 48).

[0019] The burner 48 includes a cylindrical member 34 provided along the axial direction (the direction of the central axis Q of the burner 48 or the combustion cylinder 36), a plate 50 supported by the cylindrical member 34 and having a plurality of mixing passages 56 formed inside, and a plurality of fuel nozzles 60 for injecting fuel into the plurality of mixing passages 56. The cylindrical member 34 is supported by the casing 20 by a support member 46 provided around the cylindrical member 34.

[0020] The plate 50 has an upstream end face 52 and a downstream end face 54, which are both ends in the axial direction. Each of the multiple mixing channels 56 is provided so as to extend axially through the interior of the plate 50. The upstream and downstream sides in the axial direction of the burner 48 refer to the upstream and downstream sides, respectively, in the direction of airflow through the multiple mixing channels 56 provided in the plate 50.

[0021] An air chamber 35 is formed between the casing 20 and the plate 50 in the axial direction, and compressed air from the compressor 2 is supplied to a plurality of mixing channels 56 via an air passage 40 and air chamber 35 formed on the outer circumference of the cylindrical member 34, and through an inlet opening (upstream end 56a of the mixing channel 56; see Figure 3) provided on the upstream end face 52 of the plate 50.

[0022] Inside each mixing channel 56, air supplied from the compressor 2 and fuel ejected from the fuel nozzle 60 are mixed as they flow downstream (i.e., toward the combustion cylinder 36), generating a premixed gas. The premixed gas generated in each mixing channel 56 is injected into the combustion chamber 38 formed by the combustion cylinder 36 from an outlet opening (downstream end 56b of the mixing channel 56; see Figure 3) provided on the downstream end face 54 of the plate 50, and is ignited by a pilot light (not shown) to begin combustion. Fuel may also be supplied to each fuel nozzle 60 from the fuel port 44.

[0023] Several embodiments of the burner 48 will be described in more detail below. The burner 48 described below is applied, for example, to the gas turbine 100 and combustor 4 described above.

[0024] Figures 3 and 4 are schematic cross-sectional views along the axial direction of a burner 48 according to one embodiment, respectively. Figures 5 and 6 are diagrams showing cross-sections perpendicular to the axial direction of a burner 48 according to one embodiment, and correspond to the A-A cross-section in Figure 3, respectively.

[0025] In some embodiments, as shown in Figures 3 to 6, for example, the burner 48 includes the plate 50 and a plurality of fuel nozzles 60.

[0026] As shown in Figures 3 to 6, each of the plurality of fuel nozzles 60 is supported on the plate 50 via a support portion 62. In the illustrated embodiment, each of the plurality of fuel nozzles 60 is a nozzle that extends along the axial direction. The fuel nozzles 60 may be provided coaxially with the mixing channel 56 in which the fuel nozzles 60 are located (i.e., the central axis of the fuel nozzle 60 coincides with the center line L of the mixing channel 56).

[0027] In some embodiments, as shown in Figures 3 to 6, for example, each of the multiple fuel nozzles 60 may be supported on the inner wall surface 57 of the mixing passage 56 via a support portion 62. As shown in Figures 3 to 6, the support portion 62 may include a strut 63, one end of which is connected to the inner wall surface 57 of the mixing passage 56 and the other end of which is connected to the fuel nozzle 60.

[0028] The support portion 62 may include one strut 63, for example, as shown in Figures 3 and 5. Alternatively, the support portion 62 may include two struts 63a and 63b, for example, as shown in Figure 4. In the exemplary embodiment shown in Figure 4, the two struts 63a and 63b are spaced approximately 180 degrees apart from each other with respect to the center line L of the mixing channel 56. Alternatively, the support portion 62 may include three or more struts 63.

[0029] The fuel passage 72 is configured to supply fuel to the fuel nozzles 60. As shown in Figures 3 to 6, the fuel passage 72 extends axially (in the direction of the central axis Q of the burner 48) and includes a plurality of axial passages 80 for guiding fuel to each of the plurality of fuel nozzles 60. The fuel passage 72 is also formed in the plate 50 and includes passages (not shown) for guiding fuel from the fuel port 44 (see Figure 2) to the plurality of axial passages 80.

[0030] In the exemplary embodiments shown in Figures 3 to 6, a fuel passage 82 is formed inside the support portion 62. Fuel from the fuel port 44 (see Figure 2) is supplied to the fuel injection hole 84 of the fuel nozzle 60 via a fuel flow path 72 (including a plurality of axial passages 80) provided inside the plate 50 and a fuel passage 82 provided inside the support portion 62, and is ejected into the mixing flow path 56 from the injection port 60a at the tip of the fuel nozzle 60.

[0031] The fuel supplied to the fuel nozzle 60 may be, for example, a gaseous fuel containing hydrocarbons, hydrogen, ammonia, or carbon monoxide (including, for example, natural gas or coal gasification gas).

[0032] In some embodiments, as shown in Figures 5 and 6, for example, the burner 48 may include a plurality of mixing channels 56 arranged around the central axis Q of the burner 48, and a plurality of fuel nozzles 60 arranged corresponding to each of the plurality of mixing channels 56.

[0033] In some embodiments, as shown in Figures 3 to 6, for example, the burner 48 includes a cavity 90 located radially outward from the plurality of fuel nozzles 60 and the plurality of axial passages 80 within the plate 50 (i.e., radially outward with respect to the central axis Q of the burner 48). That is, the cavity 90 is located in the outer peripheral portion of the plate 50, radially outward from the plurality of fuel nozzles 60 and the plurality of axial passages 80. The cavity 90 may also be located radially outward from the fuel nozzle 60 and axial passage 80 that are radially outward among the plurality of fuel nozzles 60 and the plurality of axial passages 80 within the plate 50.

[0034] In some embodiments, the plate 50 (including the fuel passage 72 and cavity 90), the multiple fuel nozzles 60, and the multiple support parts 62 constituting the burner 48 are integrally formed as a single additive manufacturing product. This additive manufacturing product may be formed, for example, by additive manufacturing using a powder bed method.

[0035] According to the above embodiment, a cavity 90 is provided inside the plate 50, radially outward from the plurality of fuel nozzles 60 and plurality of axial passages 80 supported by the plate 50 via the support portion 62. Therefore, during the additive manufacturing of the burner 48, which includes the plate 50, the plurality of fuel nozzles 60, and the plurality of support portions 62, or during the cooling process after additive manufacturing, even if the radially outward portion of the plate 50 (hereinafter referred to as the outer peripheral portion) of the plurality of fuel nozzles 60 shrinks due to heat, the cavity 90 can block the effect of this heat shrinkage on the fuel nozzles 60. In other words, the cavity 90 functions as an insulating layer that blocks the thermal influence on the outer peripheral portion of the fuel nozzles 60 during additive manufacturing. This makes it possible to suppress the tilting of the fuel nozzles 60 (inclination of the central axis of the fuel nozzle 60 with respect to the center line L of the mixing passage 56) due to the thermal shrinkage of the outer peripheral portion of the plate 50.

[0036] Furthermore, as shown in Figure 4, for example, by supporting the fuel nozzle 60 on the plate 50 with multiple struts 63 (two struts 63a and 63b in Figure 4), the tilting of the fuel nozzle 60 due to thermal contraction of the outer peripheral portion of the plate 50 can be suppressed more effectively compared to the case where only one strut 63 is provided to support each fuel nozzle 60.

[0037] In some embodiments, the cavity 90 may be provided so as to extend along the axial direction in a cross-section along the axial direction (see Figures 3 and 4). For example, the cavity 90 may extend in the axial direction over an extended region Rn (see Figure 4) of a plurality of fuel nozzles 60 and a plurality of support portions 62. In other words, the axial length Lc (see Figure 4) of the cavity 90 may be longer than the axial length of the extended region Rn (the length between the ends of the portion including the fuel nozzles 60 and support portions 62).

[0038] According to the above-described embodiment, since the cavity 90 extends in the axial direction over the extending region Rn of the plurality of fuel nozzles 60 and the plurality of support portions 62, even if the outer peripheral portion of the plate 50 shrinks due to thermal shrinkage during or after additive manufacturing of the burner 48, the cavity 90 can more effectively block the effect of this thermal shrinkage on the fuel nozzles 60. This makes it possible to more effectively suppress the tilting of the fuel nozzles 60 due to thermal shrinkage of the outer peripheral portion of the plate 50.

[0039] In some embodiments, the cavity 90 may be provided so as to extend along the circumferential direction in a cross section perpendicular to the axial direction (see Figures 5 and 6).

[0040] The cavity 90 may have a rectangular profile in a cross-section perpendicular to the axial direction, as shown in Figure 5, for example. Alternatively, the cavity 90 may have a profile in a rectangle that is curved in the circumferential direction (or a shape that follows the outer surface of the plate 50) in a cross-section perpendicular to the axial direction, as shown in Figure 6, for example.

[0041] As shown in Figures 5 and 6, a plurality of cavities 90 may be provided on the outer circumferential portion of the plate 50. The plurality of cavities 90 may be arranged along the circumferential direction.

[0042] According to the above-described embodiment, since the cavity 90 is provided to extend in the circumferential direction, it is possible to block the influence of thermal shrinkage of the outer peripheral portion of the plate 50, which may occur during additive manufacturing or the cooling process after additive manufacturing, on the fuel nozzle 60 over a certain wide area in the circumferential direction. This makes it possible to more effectively suppress the tilting of the fuel nozzle 60 due to thermal shrinkage of the outer peripheral portion of the plate 50.

[0043] Figures 7 to 11 are schematic cross-sectional views along the axial direction of a burner 48 according to one embodiment. Each of the burners 48 shown in Figures 7 to 11 has the cavity 90 described above, and in addition to the function of blocking the thermal effect of thermal shrinkage during the addition molding of the plate 50 to the fuel nozzle 60, the cavity 90 also has another function.

[0044] In some embodiments, fuel may be guided to the plurality of axial passages 80 through the cavity 90. That is, the cavity 90 may function as the fuel flow path 72.

[0045] For example, in the exemplary embodiment shown in FIG. 7, passages 92 and 94 are formed inside the plate 50 and are connected to one end and the other end of the cavity 90 in the axial direction, respectively. The passage 92 is adapted to supply fuel (e.g., fuel from the fuel port 44) from outside the plate 50. The passage 94 communicates with the plurality of axial passages 80. Therefore, for example, fuel from the fuel port 44 or the like is supplied to the plurality of fuel nozzles 60 through the passage 92, the cavity 90, the passage 94, and the plurality of axial passages 80.

[0046] According to the above-described embodiment, the cavity 90 having a function of blocking the influence of thermal contraction on the fuel nozzle 60 during the manufacture of the burner 48 can be used as the fuel flow path 72 during operation.

[0047] In some embodiments, the cavity 90 may be adapted to supply a cooling fluid for cooling the plate 50.

[0048] For example, in the exemplary embodiment shown in FIG. 8, passages 104 and 106 are formed inside the burner 48 and are connected to one end and the other end of the cavity 90 in the axial direction, respectively. Further, a cooling cavity 102 is formed at the downstream end of the plate 50. The passage 104 is adapted to supply a cooling fluid (e.g., air) from outside the plate 50. The passage 106 communicates with the cooling cavity 102. Therefore, the cooling fluid from outside the plate 50 is supplied to the cooling cavity 102 through the passage 104, the cavity 90, and the passage 106.

[0049] According to the above-described embodiment, the cavity 90 having a function of blocking the influence of thermal contraction on the fuel nozzle 60 during the manufacture of the burner 48 can be used as a passage for the cooling fluid for cooling the plate 50 (particularly, the downstream end portion or the like that becomes high temperature during operation) during operation.

[0050] In some embodiments, the cavity 90 may be used to measure the pressure in a space communicating with the cavity 90 (for example, the combustion chamber 38 of the combustor 4).

[0051] For example, in the exemplary embodiment shown in Figure 9, the cavity 90 has a downstream end 90a that opens to the downstream end face 54 of the plate 50. In this case, the space that the downstream end face 54 of the plate 50 faces (for example, the combustion chamber 38 of the combustor 4; see Figure 2) is in communication with the cavity 90. The burner 48 is also provided with a pressure sensor 96 capable of measuring the pressure inside the cavity 90.

[0052] According to the above embodiment, the cavity 90, which has the function of blocking the effect of thermal contraction on the fuel nozzle 60 during the manufacture of the burner 48, can be used during operation to measure the pressure in the space communicating with the cavity 90 (combustion chamber 38, etc.). Since fluctuations in the pressure of the combustion chamber 38 of the combustor 4 indicate combustion oscillations of the combustor 4, the state of combustion oscillations of the combustor 4 can be grasped by measuring the pressure of the combustion chamber 38.

[0053] In some embodiments, at least a portion of the thermocouple 108 may be inserted into the cavity 90, for example, as shown in Figure 10. In the exemplary embodiment shown in Figure 10, a passage 110 through which the thermocouple 108 can be inserted is provided at one end of the cavity 90 inside the plate 50, and the leading end portion of the thermocouple 108 is inserted into the cavity 90 through the passage 110. The thermocouple 108 is capable of measuring the temperature of the downstream end of the plate 50.

[0054] According to the above embodiment, the cavity 90, which has the function of blocking the effect of thermal contraction on the fuel nozzle 60 during the manufacture of the burner 48, can be used as a space for installing a thermocouple 108 for measuring the temperature of the plate 50, etc., during operation.

[0055] In some embodiments, as shown in Figure 11, for example, the cavity 90 may function as a cavity space for an acoustic liner to suppress combustion vibrations. In the exemplary embodiment shown in Figure 11, the cavity 90 has a downstream end 90a that opens to the downstream end face 54 of the plate 50, and a perforated plate 112 is provided at the downstream end 90a. The perforated plate 112 has a plurality of through holes 114 that connect the internal space of the cavity 90 with the space (combustion chamber 38, etc.) that the downstream end face 54 of the plate 50 faces.

[0056] According to the above-described embodiment, the cavity 90, which has the function of blocking the effect of thermal contraction on the fuel nozzle 60 during the manufacture of the burner 48, can be used as the cavity space of an acoustic liner to suppress combustion vibrations during operation.

[0057] The contents described in each of the above embodiments can be understood, for example, as follows:

[0058] [1] A burner (48) according to at least one embodiment of the present invention comprises: a plate (50) having an upstream end face (52) and a downstream end face (54) in the axial direction, having a plurality of mixing passages (56) formed therein that are configured to supply air to the interior and extend along the axial direction; a plurality of fuel nozzles (60) configured to inject fuel into the interior of the plurality of mixing passages, a plurality of support parts (62) for supporting the plurality of fuel nozzles on the plate, and a fuel passage (72) formed inside the plate for supplying the fuel to the plurality of fuel nozzles, wherein the fuel passage extends along the axial direction and includes a plurality of axial passages (80) for guiding the fuel to the plurality of fuel nozzles, and comprises at least one cavity (90) provided inside the plate radially outward from the plurality of fuel nozzles and the plurality of axial passages.

[0059] According to the configuration described in [1] above, a cavity is provided inside the plate radially outward from the multiple fuel nozzles and multiple axial passages supported by the plate via a support portion. Therefore, even if the outer peripheral portion of the plate (hereinafter referred to as the outer peripheral portion) of the plate shrinks due to thermal shrinkage during or after additive manufacturing of the burner, the cavity can block the effect of this thermal shrinkage on the fuel nozzles. This makes it possible to suppress the tilting of the fuel nozzles (inclination of the central axis of the fuel nozzle with respect to the central axis of the mixing passage) caused by the thermal shrinkage of the outer peripheral portion of the plate.

[0060] [2] In some embodiments, in the configuration of [1] above, the plate on which the fuel passage and the cavity are formed, the plurality of fuel nozzles, and the plurality of support parts form a single additive structure.

[0061] According to the configuration in [2] above, when the burner is formed as a single additive structure including a plate, a plurality of fuel nozzles, and a plurality of support parts, even if the outer peripheral portion of the plate shrinks due to thermal shrinkage during or after the additive manufacturing of the burner, the cavity can block the effect of this thermal shrinkage on the fuel nozzles. This makes it possible to suppress the tilting of the fuel nozzles due to the thermal shrinkage of the outer peripheral portion of the plate.

[0062] [3] In some embodiments, in the configuration of [1] or [2] above, the at least one cavity extends along the circumferential direction.

[0063] According to the configuration described in [3] above, since the cavity is provided to extend in the circumferential direction, it is possible to block the influence of thermal shrinkage of the outer peripheral portion of the plate, which may occur during additive manufacturing or the cooling process after additive manufacturing, on the fuel nozzle over a fairly wide area in the circumferential direction. This makes it possible to more effectively suppress the tilting of the fuel nozzle due to thermal shrinkage of the outer peripheral portion of the plate.

[0064] [4] In some embodiments, in any of the configurations [1] to [3] above, the fuel passage includes the at least one cavity, and the burner is configured such that the fuel from the at least one cavity is guided into the plurality of axial passages.

[0065] According to the configuration described in [4] above, the cavity that has the function of blocking the effect of thermal contraction on the fuel nozzle during the manufacture of the burner can be used as a fuel passage during operation.

[0066] [5] In some embodiments, in any of the configurations [1] to [3] above, the burner is configured to supply a cooling fluid for cooling the plate to the at least one cavity.

[0067] According to the configuration described in [5] above, the cavity that has the function of blocking the effect of thermal contraction on the fuel nozzle during the manufacture of the burner can be used as a passage for cooling fluid to cool the plate during operation.

[0068] [6] In some embodiments, in any of the configurations [1] to [3] above, the at least one cavity has a downstream end (90a) that opens to the downstream end face of the plate, and the burner is equipped with a pressure sensor (96) for measuring the pressure inside the at least one cavity.

[0069] According to the configuration described in [6] above, the cavity, which has the function of blocking the effect of thermal contraction on the fuel nozzle during the manufacture of the burner, can be used during operation to measure the pressure in the space (combustion chamber, etc.) that is in communication with the cavity.

[0070] [7] In some embodiments, in any of the configurations [1] to [3] above, the burner comprises a thermocouple (108) at least partially inserted into the at least one cavity.

[0071] According to the configuration described in [7] above, the cavity that has the function of blocking the effect of thermal contraction on the fuel nozzle during the manufacture of the burner can be used as a space for installing thermocouples for measuring the temperature of the plate, etc., during operation.

[0072] [8] In some embodiments, in any of the configurations [1] to [3] above, the at least one cavity has a downstream end (90a) portion that opens to the downstream end face of the plate, and the burner comprises a perforated plate (112) provided at the downstream end.

[0073] According to the configuration described in [8] above, the cavity that has the function of blocking the effect of thermal contraction on the fuel nozzle during the manufacture of the burner can be used as the cavity space of an acoustic liner to suppress combustion vibrations during operation.

[0074] [9] In some embodiments, in any of the configurations [1] to [8] above, each of the plurality of support members includes a plurality of struts (63a, 63b), one end of which is connected to the plate and the other end of which is connected to the fuel nozzle.

[0075] According to the configuration described in [9] above, each fuel nozzle is supported by the plate and a plurality of struts connected to the fuel nozzle. Therefore, compared to the case where only one strut is provided to support each fuel nozzle, the tilting of the fuel nozzle due to thermal contraction of the outer peripheral portion of the plate can be suppressed more effectively.

[0076]

[10] In some embodiments, in any of the configurations [1] to [9] above, each of the at least one cavity extends in the axial direction over the extending region (Rn) of the plurality of fuel nozzles and the plurality of support members.

[0077] According to the configuration of

[10] above, since the cavity extends in the axial direction over the extension regions of the multiple fuel nozzles and multiple support parts, even if the outer peripheral portion of the plate shrinks due to thermal shrinkage during or after additive manufacturing of the burner, the cavity can more effectively block the effect of this thermal shrinkage on the fuel nozzles. This makes it possible to more effectively suppress the tilting of the fuel nozzles due to thermal shrinkage of the outer peripheral portion of the plate.

[0078]

[11] A combustor (4) according to at least one embodiment of the present invention comprises a burner (48) described in any one of [1] to

[10] above, and a combustion cylinder (36) provided downstream of the burner.

[0079] According to the configuration described in

[11] above, a cavity is provided inside the plate radially outward from the multiple fuel nozzles and multiple axial passages supported by the plate via a support portion. Therefore, even if the outer peripheral portion of the plate (hereinafter referred to as the outer peripheral portion) of the plate shrinks due to thermal shrinkage during or after additive manufacturing of the burner, the cavity can block the effect of this thermal shrinkage on the fuel nozzles. This makes it possible to suppress the tilting of the fuel nozzles (inclination of the central axis of the fuel nozzle with respect to the central axis of the mixing passage) due to thermal shrinkage of the outer peripheral portion of the plate.

[0080]

[12] A gas turbine (100) according to at least one embodiment of the present invention comprises a combustor (4) as described in

[11] above, and a turbine (6) configured to be driven by combustion gas from the combustor.

[0081] According to the configuration described in

[12] above, a cavity is provided inside the plate radially outward from the multiple fuel nozzles and multiple axial passages supported by the plate via a support portion. Therefore, even if the outer peripheral portion of the plate (hereinafter referred to as the outer peripheral portion) of the plate shrinks due to thermal shrinkage during or after additive manufacturing of the burner, the cavity can block the effect of this thermal shrinkage on the fuel nozzles. This makes it possible to suppress the tilting of the fuel nozzles (inclination of the central axis of the fuel nozzle with respect to the central axis of the mixing passage) due to thermal shrinkage of the outer peripheral portion of the plate.

[0082] Although embodiments of the present invention have been described above, the present invention is not limited to the embodiments described above, and also includes modified forms of the embodiments described above, as well as forms that combine these forms as appropriate.

[0083] In this specification, expressions describing relative or absolute arrangements such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" shall not only describe such arrangements strictly, but also describe states of relative displacement with tolerances or angles or distances sufficient to achieve the same function. For example, expressions describing things being in an equal state such as "identical," "equal," and "homogeneous" shall not only describe states of being strictly equal, but also describe states where tolerances or differences exist to the extent that the same function is achieved. Furthermore, in this specification, expressions describing shapes such as quadrilaterals or cylindrical shapes shall not only describe geometrically precise quadrilaterals or cylindrical shapes, but also describe shapes including concave and concave parts, chamfered parts, etc., to the extent that the same effect is achieved. In addition, in this specification, expressions such as "equipment," "includes," or "possesses" a component are not exclusive expressions that exclude the existence of other components.

[0084] 2 Compressor 4 Combustor 6 Turbine 8 Rotor 10 Compressor casing 12 Air intake 16 Stationary blades 18 Rotor blades 20 Casing 22 Turbine casing 24 Stationary blades 26 Rotor blades 30 Exhaust chamber 34 Cylindrical member 35 Air chamber 36 Combustion cylinder 38 Combustion chamber 40 Air passage 44 Fuel port 46 Support member 48 Burner 50 Plate 52 Upstream end face 54 Downstream end face 56 Mixing passage 56a Upstream end 56b Downstream end 57 Inner wall surface 60 Fuel nozzle 60a Outlet 62 Support part 63 Strut 63a Strut 63b Strut 72 Fuel passage 80 Axial passage 82 Fuel passage 84 Fuel outlet 90 Cavity 90a Downstream end 92 Passage 94 Passage 96 Pressure sensor 100 Gas turbine 102 Cooling cavity 104 Passage 106 Passage 108 Thermocouple 110 Passage 112 Perforated plate 114 Through hole L Centerline O Central axis Q Central axis Rn Extended region

Claims

1. A burner comprising: a plate having an upstream end face and a downstream end face in the axial direction, with a plurality of mixing channels formed therein that are configured to supply air to the interior and extend along the axial direction; a plurality of fuel nozzles configured to inject fuel into the plurality of mixing channels, each; a plurality of support parts for supporting the plurality of fuel nozzles on the plate, each; and a fuel channel formed inside the plate for supplying the fuel to the plurality of fuel nozzles, wherein the fuel channel extends along the axial direction and includes a plurality of axial passages for guiding the fuel to the plurality of fuel nozzles, each; and at least one cavity provided inside the plate radially outward from the plurality of fuel nozzles and the plurality of axial passages.

2. The burner according to claim 1, wherein the plate on which the fuel passage and the cavity are formed, the plurality of fuel nozzles and the plurality of support parts form a single additive structure.

3. The burner according to claim 1 or 2, wherein the at least one cavity extends along the circumferential direction.

4. The burner according to claim 1 or 2, wherein the fuel passage includes the at least one cavity, and the fuel from the at least one cavity is guided to the plurality of axial passages.

5. The burner according to claim 1 or 2, configured such that a cooling fluid for cooling the plate is supplied to at least one cavity.

6. The burner according to claim 1 or 2, wherein the at least one cavity has a downstream end that opens to the downstream end face of the plate, and comprises a pressure sensor for measuring the pressure inside the at least one cavity.

7. The burner according to claim 1 or 2, comprising a thermocouple at least partially inserted into the at least one cavity.

8. The burner according to claim 1 or 2, wherein the at least one cavity has a downstream end that opens to the downstream end face of the plate, and comprises a perforated plate provided at the downstream end.

9. The burner according to claim 1 or 2, wherein each of the plurality of support parts includes a plurality of struts, each having one end connected to the plate and the other end connected to the fuel nozzle.

10. The burner according to claim 1 or 2, wherein each of the at least one cavities extends in the axial direction over the extending region of the plurality of fuel nozzles and the plurality of support portions.

11. A combustor comprising: a burner according to claim 1 or 2; and a combustion cylinder provided downstream of the burner.

12. A gas turbine comprising: a combustor according to claim 11; and a turbine configured to be driven by combustion gas from the combustor.

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