Gas turbine combustor and gas turbine

Abstract

To suppress combustion vibration while maintaining good combustion performance.SOLUTION: The present disclosure relates to a gas turbine combustor having a burner assembly including a plurality of burners for forming a flame in a combustion chamber. The gas turbine combustor includes a plate body having an injection surface on which a plurality of injection holes for injecting a mixture of fuel and air in each of a plurality of burners into a combustion chamber are formed, and at least one resonator provided on the plate body. The resonator includes an acoustic chamber formed as an internal space in the plate body, and at least one communication hole that opens to the injection surface and communicates the acoustic chamber with the combustion chamber.SELECTED DRAWING: FIG. 4A

Description

[Technical Field]

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

[0002] Gas turbines are known that generate power by driving a turbine using combustion gas as a working fluid. In these gas turbines, combustion gas is generated by burning a mixture of fuel and air in a gas turbine combustor. However, combustion oscillations with a frequency band corresponding to the flame length formed by the mixture combustion of fuel and air can occur in these gas turbine combustors. To suppress such combustion oscillations, a resonator with an acoustic chamber is sometimes installed on the side surface of a cylindrical body defining the combustion chamber, at a position corresponding to the flame length formed in the combustion chamber and at the antinode position of an acoustic mode included in the combustion oscillations. The resonator has an acoustic liner connected to the combustion chamber via a perforated plate. The resonator matches the resonant frequency in the acoustic chamber with the combustion oscillations, directing pressure fluctuation energy in the combustion chamber into the acoustic chamber and converting it into thermal energy via the perforated plate, thereby achieving a damping effect.

[0003] In recent years, hydrogen and other highly combustible fuels have been used in gas turbines. When such highly combustible fuels are used, the flame length formed in the combustion chamber becomes short, on the order of several centimeters. When attempting to suppress combustion oscillations occurring under such combustion conditions with a short flame length using the aforementioned resonator, if the resonator is installed at a position corresponding to the flame length on the side surface of the cylindrical body defining the combustion chamber, as described above, there is a risk that the resonator will be positioned too close to the injection surface on which the injection holes for injecting the fuel-air mixture into the combustion chamber are formed. To address this issue, Patent Document 1 claims that combustion oscillations can be suppressed even when the flame length is short by installing a resonator on the injection surface on which the injection holes for injecting the fuel-air mixture into the combustion chamber are formed. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] Japanese Patent Application Laid-Open No. 2011-17523 Summary of the Invention [Problem to be solved by the invention]

[0005] In the above-mentioned Patent Document 1, a part of the injection surface provided with injection holes for injecting a mixture of fuel and air into the combustion chamber needs to be reserved as a space for installing a resonator adjacent to the combustion chamber. As a result, there must be an area on the injection surface where injection holes cannot be provided in order to install the resonator, which hinders the improvement of the performance of the gas turbine combustor.

[0006] At least one embodiment of the present disclosure has been made in view of the above circumstances, and an object of the present disclosure is to provide a gas turbine combustor and a gas turbine that are capable of suitably suppressing combustion oscillation while favorably maintaining combustion performance. [Means for solving the problem]

[0007] In order to solve the above problems, a gas turbine combustor according to at least one embodiment of the present disclosure comprises: 1. A gas turbine combustor having a burner assembly including a plurality of burners for forming a flame in a combustion chamber, a plate body having an injection surface on which a plurality of injection holes are formed for injecting a mixture of fuel and air into the combustion chamber in each of the plurality of burners; At least one resonator provided on the plate body; Equipped with The at least one resonator an acoustic chamber formed as an internal space in the plate body; At least one communication hole that opens to the injection surface and connects the acoustic chamber to the combustion chamber; Includes:

[0008] In order to solve the above problems, a gas turbine according to at least one embodiment of the present disclosure includes: A gas turbine combustor according to at least one embodiment of the present disclosure is provided. [Effects of the Invention]

[0009] According to at least one embodiment of the present disclosure, it is possible to provide a gas turbine combustor and a gas turbine that are capable of suitably suppressing combustion oscillation while favorably maintaining combustion performance. [Brief explanation of the drawings]

[0010] [Figure 1] FIG. 1 is a schematic configuration diagram illustrating a gas turbine according to an embodiment. [Figure 2] FIG. 2 is a cross-sectional view of the gas turbine combustor of FIG. 1. [Figure 3] FIG. 3 is an enlarged view of region B in FIG. 2. [Figure 4A] 4 is a diagram showing an example of the configuration of the resonator of FIG. 3, viewed from the ejection surface side. [Figure 4B] 4 is a diagram showing another example of the configuration of the resonator in FIG. 3, viewed from the ejection surface side. [Figure 5] 3 is a cross-sectional view showing another example of the configuration of the resonator in the plate body of FIG. 2. FIG. [Figure 6] This is a modification of FIG. [Figure 7] 4B is a cross-sectional view showing an example of a cross-sectional configuration along the central axis of a resonator provided in region D of FIG. 4A. FIG. [Figure 8] 4B is another variation of FIG. 4A. [Figure 9] 4 is another example of the configuration in region E of FIG. 3. [Figure 10] 4 is another example of the configuration of FIG. 3. DETAILED DESCRIPTION OF THE INVENTION

[0011] Hereinafter, several embodiments of the present disclosure will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of the configurations described as embodiments or shown in the drawings are merely illustrative examples and are not intended to limit the scope of the invention.

[0012] Fig. 1 is a schematic configuration diagram showing a gas turbine 100 according to one embodiment, and Fig. 2 is a cross-sectional view of a gas turbine combustor 4 in Fig. 1. The gas turbine 100 includes a compressor 2 for compressing air as an oxidant to be supplied to the gas turbine combustor 4 (i.e., generating compressed air A), the gas turbine combustor 4 for generating combustion gas by mixing and burning the compressed air A with fuel F from a fuel supply system (not shown), and a turbine 6 configured to be driven by the combustion gas discharged from the gas turbine combustor 4. In the case of the gas turbine 100 for power generation, a generator (not shown) is connected to the turbine 6, thereby making it possible to generate power using the rotational energy of the turbine 6.

[0013] In the gas turbine combustor 4, the fuel F supplied from a fuel supply system (not shown) is mixed with and combusted with the compressed air A, thereby generating the combustion gas. Examples of the fuel F combusted in the gas turbine combustor 4 include hydrogen, methane, light oil, heavy oil, jet fuel, natural gas, and gasified coal. The gas turbine 100 according to this embodiment may use any combination of one or more of these fuels, and handles a fuel F containing at least hydrogen.

[0014] The compressor 2 includes a compressor casing 10, an air inlet 12 provided on the inlet side of the compressor casing 10 for taking in air, a rotor 8 provided to penetrate both the compressor casing 10 and the turbine casing 22, and various blades arranged inside the compressor casing 10. The various blades include an inlet guide vane 14 provided on the air inlet 12 side, a plurality of stator vanes 16 fixed to the compressor casing 10 side, and a plurality of moving blades 18 provided on the rotor 8 so as to be arranged alternately with respect to the stator vanes 16. In this compressor 2, air taken in through the air inlet 12 passes through the plurality of stator vanes 16 and the plurality of moving blades 18 and is compressed to become high-temperature, high-pressure compressed air A. The high-temperature, high-pressure compressed air A is then sent from the compressor 2 to a gas turbine combustor 4 in a downstream stage.

[0015] The gas turbine combustors 4 are arranged in plurality at intervals in the circumferential direction around the rotor 8. To the gas turbine combustor 4, fuel F is supplied from a fuel supply system (not shown) and compressed air A is supplied from the compressor 2, and the two are mixed and burned to generate combustion gas, which is a working fluid for the turbine 6. The combustion gas is then sent from the gas turbine combustor 4 to the turbine 6 at a downstream stage.

[0016] The turbine 6 includes a turbine casing 22 and various blades arranged inside the turbine casing 22. The various blades include a plurality of stator vanes 24 fixed to the turbine casing 22 side and a plurality of moving blades 26 provided on the rotor 8 so as to be arranged alternately with respect to the stator vanes 24. In the turbine 6, combustion gas passes through the plurality of stator vanes 24 and the plurality of moving blades 26, thereby driving the rotor 8 to rotate. This drives a generator (not shown) connected to the rotor 8.

[0017] An exhaust chamber 30 is connected to the downstream side of the turbine casing 22 via an exhaust casing 28. The combustion gas that has driven the turbine 6 is discharged to the outside via the exhaust casing 28 and the exhaust chamber 30.

[0018] 2, the gas turbine combustor 4 includes an outer casing 20 having a substantially cylindrical shape that constitutes an outer casing, and a burner assembly 32 housed in the outer casing 20. An inner casing 25 that defines a combustion chamber 27 on the inside is connected to the downstream side of the burner assembly 32. The inner casing 25 has a substantially cylindrical shape with a smaller diameter than the outer casing 20, and defines the combustion chamber 27 in which a flame fr is formed by a plurality of burners 52 included in the burner assembly 32. An air flow path 40 is formed between the outer casing 20 and the inner casing 25 to introduce compressed air A generated by the compressor 2 into the burner assembly 32.

[0019] The burner assembly 32 has a plate body 50 configured to have a sufficient thickness along the central axis L. A plurality of air holes 51 are provided on the upstream end surface of the plate body 50 for introducing compressed air A from the air flow path 40 into each burner 52. The tips of a plurality of fuel nozzles 60, each having an outer diameter smaller than the inner diameter of the air hole 51, are inserted into each of the plurality of air holes 51. The plurality of fuel nozzles 60 are configured to supply fuel F from a fuel supply system (not shown) to each burner 52, and are provided to penetrate the outer casing 20 from the outside. Since the air holes 51 have an inner diameter larger than the outer diameter of the fuel nozzles 60, compressed air A can be introduced from the air flow path 40 to the burners 52 through a gap between the air holes 51 and the fuel nozzles 60.

[0020] The plate body 50 is formed with a plurality of mixing passages 58 for guiding a mixture Gm of fuel F supplied from the fuel nozzles 60 and compressed air A supplied from the air holes 51 toward the combustion chamber 27. The plurality of mixing passages 58 extend along the central axis L inside the plate body 50 and are approximately parallel to one another. The burner assembly 32 illustrated in Fig. 2 is a coaxial type in which the central axis of the fuel nozzles 60, which are fuel passages through which the fuel F flows, coincides with the central axis of the mixing passages 58 through which the mixture Gm flows.

[0021] The plate body 50 has an injection surface 53, which is a downstream end surface facing the combustion chamber 27. The injection surface 53 is provided with a plurality of injection holes 54 which respectively communicate with a plurality of mixing passages 58. The air-fuel mixture Gm guided by the mixing passages 58 is injected into the combustion chamber 27 through the injection holes 54 formed in the injection surface 53, thereby forming a flame fr in the combustion chamber 27.

[0022] 3 is an enlarged view of region B in FIG. 2. As shown in FIG. 3, at least one resonator 70 is provided on the injection surface 53 of the plate body 50. As described above, the fuel F handled in the gas turbine 100 according to this embodiment contains hydrogen, which has excellent combustibility, and therefore the length of the flame fr formed in the combustion chamber 27 is short, on the order of several centimeters. In order to suitably suppress combustion oscillation caused by such a flame fr with a short flame length, it is effective to arrange the resonator 70 near the flame fr. In this embodiment, by arranging the resonator 70 on the injection surface 53 in this way, combustion oscillation caused by a flame fr with a short flame length can be suitably suppressed.

[0023] The resonator 70 includes an acoustic chamber 71 and at least one communication hole 72. The acoustic chamber 71 is formed as an internal space of the plate body 50 and is connected to the combustion chamber 27 via the communication hole 72, thereby being configured integrally with the plate body 50. As described above, the plate body 50 is provided with a plurality of mixing channels 58, and the acoustic chamber 71 and the communication hole 72 are formed so as not to structurally interfere with these mixing channels 58. By configuring the resonator 70 integrally with the plate body 50 in this way, and by arranging the resonator 70 in the vicinity of the flame fr formed in the combustion chamber 27, combustion oscillation can be suitably suppressed even when the flame length of the flame fr is short.

[0024] At least one of the volume of the acoustic chamber 71 constituting the resonator 70, the number, diameter, and length of the communication holes 72 can be designed based on the frequency of the combustion oscillation to be suppressed by the resonator 70.

[0025] Fig. 4A is a diagram showing an example of the configuration of resonator 70 in Fig. 3, viewed from the ejection surface 53 side. In Fig. 4A, communication holes 72 formed on ejection surface 53 of resonator 70 are shown by solid lines, and acoustic chamber 71 formed inside plate body 50 is shown transparently by hatching.

[0026] The communication holes 72 of the resonator 70 can be arranged at any position on the injection surface 53 as long as they do not interfere with the injection holes 54 of the injection surface 53. Fig. 4A shows, as an example, a configuration in which the communication holes 72 are arranged in the center and periphery of a concentric region 73 of the injection surface 53, which is a severe thermal environment that is likely to affect combustibility (flame stability). In this embodiment, approximately concentric regions 73 of a predetermined radius are defined around a position P1 on the injection surface 53 through which the central axis L passes and positions P2 to P7 provided at predetermined intervals around position P1 in the circumferential direction. The injection holes 54 are arranged in these concentric regions 73, while the communication holes 72 are arranged in the center and on the outside of these concentric regions 73.

[0027] Furthermore, in the ejection surface 53, the communication holes 72 may be formed between the ejection holes 54 and the peripheral edge 53a of the ejection surface 53 (in other words, adjacent to the peripheral edge 53a). In Fig. 4A, for example, the communication holes 72 indicated by the reference numeral 72a are provided near the peripheral edge 53a of the ejection surface 53. In this way, the communication holes 72 may be provided in the remaining space in the ejection surface 53 near the peripheral edge 53a where no ejection holes 54 are provided.

[0028] Furthermore, in the injection surface 53, the communication hole 72 may be formed between multiple injection holes 54. In Fig. 4A, for example, the communication hole 72 designated by the reference symbol 72b is provided between the injection hole 54 in the central region 73 corresponding to the central position P1 and the injection holes 54 included in the central region 73 corresponding to the central positions P2 and P3 that are located outside the central region P1. In this way, the communication hole 72 may be provided in the remaining space between any two injection holes 54.

[0029] 4A, as will be described later with reference to Fig. 8, multiple communication holes 72 are provided to communicate with one acoustic chamber 71, but as in another configuration example shown in Fig. 4B, one communication hole 72 may be configured to communicate with one acoustic chamber 71. Fig. 4B is a view showing another configuration example of the resonator 70 in Fig. 3 from the ejection surface 53 side, and has a layout in common with the configuration example in Fig. 4A, except that the number of communication holes 72 communicating with one acoustic chamber 71 is one.

[0030] FIG. 5 is a cross-sectional view showing another example of the configuration of the resonator 70 in the plate body 50 of FIG.

[0031] In this configuration example, a plurality of resonators 70 are provided on the plate body 50. The plurality of resonators 70 includes an inner resonator 70a provided radially inward with respect to the central axis L, and an outer resonator 70b provided radially outward from the inner resonator 70a. The inner resonators 70a are arranged radially inward from the outer resonators 70b, at approximately equal intervals along the circumferential direction of the central axis L (along the outer edge of the central region 73). The outer resonators 70b are arranged radially outward from the inner resonators 70a, at approximately equal intervals along the circumferential direction of the central axis L (along the peripheral edge portion 53a).

[0032] The inner resonator 70a has an acoustic chamber 71a and a communication hole 72a, and the outer resonator 70b has an acoustic chamber 71b and a communication hole 72b. The acoustic chambers 71a and 71b may have different shapes. In this configuration example, as shown in Figure 5, the acoustic chamber 71a of the inner resonator 70a is configured to have a larger volume than the acoustic chamber 71b of the outer resonator 70b.

[0033] In this way, combustion oscillations with different frequencies can be suppressed by providing a plurality of resonators 70 with different configurations on the plate body 50. Note that the configuration of each resonator 70 shown in Fig. 5 is merely an example and is not limited to this.

[0034] 6 shows a modified example of FIG. 3. In this modified example, the plate body 50 has a purge air supply path 55 for supplying a portion of the compressed air A flowing through the air flow path 40 as purge air PA to the acoustic chamber 71. The purge air supply path 55 extends on the opposite side (toward the upstream side) from the communication hole 72 when viewed from the acoustic chamber 71, and is provided so as to communicate with the air flow path 40.

[0035] The purge air supply passage 55 is formed in the plate body 50 so as to have a flow path cross section smaller than that of the communication hole 72. This makes it possible to suitably prevent combustion gas from flowing back from the combustion chamber 27 into the acoustic chamber 71 via the communication hole 72 when purge air PA is supplied from the purge air supply passage 55 to the acoustic chamber 71.

[0036] Furthermore, as described above, if the cross section of the purge air supply path 55 is formed small, the pressure loss of the purge air PA flowing through the purge air supply path 55 is likely to increase. Therefore, in this modification, the upstream end face of the plate body 50 is partially carved out to provide a recess 57, thereby shortening the length of the purge air supply path 55. This makes it possible to suitably reduce the pressure loss of the purge air PA passing through the purge air supply path 55.

[0037] 7 is a cross-sectional view showing an example of the cross-sectional configuration along the central axis L of a resonator 70 provided in region D in FIG. 4A. In this configuration example, multiple resonators 70-1 to 70-4 provided on a plate body 50 have acoustic chambers 71 with different volumes, and are arranged in order along the circumferential direction. In particular, the distance between two adjacent resonators 70 is set to be shorter than the wavelength of the combustion oscillation to be absorbed. This makes it possible to damp the combustion oscillation regardless of the positions of the antinodes and nodes of the combustion oscillation waves that may occur.

[0038] Fig. 8 shows another modification of Fig. 4A. In this modification, an acoustic chamber 71 constituting a resonator 70 communicates with the combustion chamber 27 via a plurality of communication holes 72. The number and diameter of the communication holes 72 that connect one acoustic chamber 71 to the combustion chamber 27 can be changed as appropriate depending on the combustion oscillation to be suppressed.

[0039] Fig. 9 shows another example of the configuration in region E of Fig. 3. In this example, the ejection surface 53 is covered with a thermal barrier coating 80 such as TBC, thereby enhancing its heat resistance. In this case, as shown in Fig. 9, part of the thermal barrier coating 80 may extend into the communicating holes 72 that form the resonator 70.

[0040] In the above-described embodiments, the gas turbine combustor 4 provided with the resonator 70 is of a so-called coaxial type in which the central axis of the fuel nozzle 60, which is a fuel flow passage through which the fuel F flows, coincides with the central axis of the mixing flow passage 58 through which the air-fuel mixture Gm flows. The gas turbine combustor 4 provided with such a resonator 70 can also be applied to a so-called cross-flow type in which the central axis of a fuel flow passage 74, to which the fuel F is supplied from a fuel supply system (not shown), intersects with the axis of flow of the compressed air A introduced from the air flow passage 40, as shown in Fig. 10 . Fig. 10 shows a schematic configuration of such a cross-flow type gas turbine combustor 4 in which the resonator 70, which is composed of an acoustic chamber 71 and a communication hole 72, is provided on the injection surface 53, similar to the above-described coaxial type.

[0041] As described above, according to each of the above embodiments, at least one resonator 70 is provided in the plate body 50 constituting the burner assembly 32. The resonator 70 is configured such that an acoustic chamber 71 formed as an internal space in the plate body 50 communicates with the combustion chamber 27 via at least one communication hole 72. In particular, since the acoustic chamber 71 is configured as an internal space of the plate body 50, it is possible to arrange a compactly configured resonator 70 near the injection surface 53. As a result, even when the flame length formed in the combustion chamber 27 is short, combustion oscillation can be suitably suppressed by arranging the resonator 70 near the injection surface 53 close to the flame fr.

[0042] In addition, within the scope of the present disclosure, the components in the above-described embodiments may be replaced with well-known components as appropriate, and the above-described embodiments may be combined as appropriate.

[0043] The contents described in each of the above embodiments can be understood, for example, as follows.

[0044] (1) A gas turbine combustor according to one aspect includes: 1. A gas turbine combustor having a burner assembly including a plurality of burners for forming a flame in a combustion chamber, a plate body having an injection surface on which a plurality of injection holes are formed for injecting a mixture of fuel and air into the combustion chamber in each of the plurality of burners; At least one resonator provided on the plate body; Equipped with The at least one resonator an acoustic chamber formed as an internal space in the plate body; At least one communication hole that opens to the injection surface and connects the acoustic chamber to the combustion chamber; Includes:

[0045] According to the above aspect (1), at least one resonator is provided in the plate body constituting the burner assembly. The resonator is configured such that an acoustic chamber formed as an internal space in the plate body communicates with the combustion chamber via at least one communication hole. In particular, by configuring the acoustic chamber as an internal space of the plate body, it is possible to arrange a compactly configured resonator near the injection surface. As a result, even when the flame length formed in the combustion chamber is short, combustion oscillation can be suitably suppressed by arranging the resonator near the injection surface close to the flame.

[0046] (2) In another embodiment, in the above embodiment (1), The at least one resonator is integrally formed with the plate body.

[0047] According to the above aspect (2), the resonator having the acoustic chamber and the communication hole is integrally formed with the plate body constituting the burner assembly. As a result, by arranging the resonator in a compact configuration near the injection surface, combustion oscillation can be suitably suppressed even when the flame length formed in the combustion chamber is short.

[0048] (3) In another aspect, in the above aspect (1) or (2), The at least one communication hole is provided at a position on the injection surface where it does not interfere with the plurality of injection holes.

[0049] According to the above aspect (3), the communication hole that connects the acoustic chamber to the combustion chamber is provided on the injection surface so as not to interfere with the multiple injection holes provided on the injection surface. As a result, by arranging the resonator near the injection holes where the flame is formed, combustion oscillation can be suitably suppressed even when the flame length formed in the combustion chamber is short.

[0050] (4) In another embodiment, in any one of the above (1) to (3), The at least one communication hole is formed in the ejection surface between the plurality of ejection holes and a peripheral portion of the ejection surface.

[0051] According to the above aspect (4), by providing a communication hole that connects the acoustic chamber to the combustion chamber in the remaining space between the plurality of injection holes on the injection surface of the plate body and the peripheral portion of the injection surface where no injection holes are provided, it is possible to provide a resonator in the gas turbine combustor with an efficient layout.

[0052] (5) In another embodiment, in any one of the above (1) to (3), The at least one communication hole is formed between the plurality of injection holes in the injection surface.

[0053] According to the above aspect (5), by providing a communication hole that connects the acoustic chamber to the combustion chamber in the remaining space between the plurality of injection holes on the injection surface of the plate body and in which no injection holes are provided, it is possible to provide a resonator in the gas turbine combustor with an efficient layout.

[0054] (6) In another embodiment, in any one of the above (1) to (5), The plate body has a purge air supply passage for supplying a portion of the air to the acoustic chamber as purge air.

[0055] According to the above aspect (6), by supplying purge air from the purge air supply passage to the acoustic chamber, it is possible to suitably prevent combustion gas from flowing back from the combustion chamber to the acoustic chamber via the communication hole.

[0056] (7) In another embodiment, in the above embodiment (6), The purge air supply passage has a flow passage cross section smaller than that of the at least one communication hole.

[0057] According to the above aspect (7), the flow path cross section of the supply path for purge air is made smaller than the flow path area of ​​the communication hole with the combustion chamber, thereby suitably preventing the pressure loss from becoming excessive.

[0058] (8) In another embodiment, in any one of the above (1) to (7), The at least one resonator includes a plurality of resonators each having the acoustic chamber with a different volume.

[0059] According to the above-mentioned aspect (8), the gas turbine combustor includes the plurality of resonators, each having an acoustic chamber with a different volume, so that vibration suppression effect can be suitably exerted against combustion vibrations of a plurality of vibration frequencies.

[0060] (9) In another embodiment, in the above embodiment (8), The plurality of resonators are arranged such that the communication holes are aligned in the circumferential direction on the ejection surface.

[0061] According to the above aspect (9), a plurality of resonators having acoustic chambers with different volumes are provided on the plate body so that their respective communication holes are aligned in the circumferential direction, thereby effectively suppressing the vibration of combustion vibrations of a plurality of vibration frequencies.

[0062] (10) In another embodiment, in any one of the above (1) to (9), The acoustic chamber communicates with the combustion chamber via the plurality of communication holes.

[0063] According to the above aspect (10), the acoustic chamber constituting the resonator is configured to communicate with the combustion chamber via a plurality of communication holes, which allows the combustion vibration absorption characteristics of the acoustic chamber to be easily designed by the number and diameter of the communication holes.

[0064] (11) In another embodiment, in any one of the above (1) to (10), The injection surface is covered with a thermal barrier coating.

[0065] According to the above aspect (11), the injection surface of the plate body on which the injection holes and the communication holes are formed may be coated with a thermal barrier coating such as TBC to enhance heat resistance.

[0066] (12) In another embodiment, in any one of the above (1) to (11), At least one of the volume of the acoustic chamber, the number, diameter, and length of the at least one communication hole is designed based on the combustion oscillation frequency.

[0067] According to the above aspect (12), at least one of the volume of the acoustic chamber, the number of communication holes, the diameter, and the length is designed according to the frequency of combustion oscillation that may occur in a gas turbine combustor in which the burner assembly is mounted. As a result, the combustion oscillation that may occur in the gas turbine combustor can be suitably suppressed by the acoustic chamber that communicates with the flow path through which fuel flows via the communication holes.

[0068] (13) In another embodiment, in any one of the above (1) to (12), The central axis of the fuel flow passage through which the fuel flows and the central axis of the mixture flow passage through which the mixture flows are coaxial.

[0069] According to the above aspect (13), in a gas turbine combustor including a coaxial burner assembly in which the central axis of the fuel flow passage and the central axis of the mixing flow passage coincide with each other, combustion oscillation can be suitably prevented.

[0070] (14) In another embodiment, in any one of the above (1) to (12), The central axis of the fuel flow passage through which the fuel flows and the central axis of the mixture flow passage through which the mixture flows intersect with each other.

[0071] According to the above aspect (14), in a gas turbine combustor including a cross-flow type burner assembly in which the central axis of the fuel flow channel and the central axis of the mixing flow channel intersect with each other, combustion oscillation can be suitably prevented.

[0072] (15) In another embodiment, in any one of the above (1) to (14), The fuel includes hydrogen.

[0073] According to the above aspect (15), when hydrogen is used as fuel, the flame length formed in the combustion chamber becomes shorter, but by placing the resonator near the injection surface close to the flame, combustion oscillation can be suitably suppressed.

[0074] (16) A gas turbine according to one aspect includes: The gas turbine combustor according to any one of the above aspects (1) to (15) is provided.

[0075] According to the above aspect (16), by including the gas turbine combustor according to any of the above aspects, a gas turbine capable of suitably suppressing combustion oscillation can be realized. [Explanation of symbols]

[0076] 2 Compressor 4 Gas turbine combustor 6 Turbine 8 rotors 10 Compressor compartment 12 Air intake 14 Inlet guide vane 16 Stator blade 18 Moving blade 20 outer cylinder 22 Turbine casing 24 Stator blade 25 Inner cylinder 26 Moving blade 27 Combustion chamber 28 Exhaust compartment 30 Exhaust chamber 32 Burner assembly 40 air flow path 50 Plate body 51 Air vent 52 Burner 53 Injection surface 53a Periphery 54 Injection hole 55 Purge air supply line 57 Recess 58 Mixing channel 60 Fuel Nozzle 70 Resonator 72 Communication hole 73 Central area 80 Thermal Coating 100 Gas Turbine A. Compressed air F fuel Gm air-fuel mixture PA Purge Air fr flame

Claims

1. 1. A gas turbine combustor having a burner assembly including a plurality of burners for forming a flame in a combustion chamber, a plate body having an injection surface on which a plurality of injection holes are formed for injecting a mixture of fuel and air into the combustion chamber in each of the plurality of burners; At least one resonator provided on the plate body; Equipped with The at least one resonator an acoustic chamber formed as an internal space in the plate body; At least one communication hole that opens to the injection surface and connects the acoustic chamber to the combustion chamber; 1. A gas turbine combustor comprising:

2. The gas turbine combustor of claim 1 , wherein the at least one resonator is integral with the plate body.

3. 3. The gas turbine combustor according to claim 1, wherein the at least one communication hole is provided at a position on the injection surface so as not to interfere with the plurality of injection holes.

4. 3. The gas turbine combustor according to claim 1, wherein the at least one communication hole is formed between the plurality of injection holes in the injection surface and a peripheral portion of the injection surface.

5. The gas turbine combustor according to claim 1 or 2, wherein the at least one communication hole is formed between the plurality of injection holes in the injection surface.

6. 3. The gas turbine combustor according to claim 1, wherein the plate body has a purge air supply passage for supplying a portion of the air to the acoustic chamber as purge air.

7. The gas turbine combustor according to claim 6 , wherein the purge air supply passage has a flow passage cross section smaller than that of the at least one communication hole.

8. 3. The gas turbine combustor according to claim 1, wherein the at least one resonator includes a plurality of resonators each having the acoustic chamber with a different volume.

9. The gas turbine combustor according to claim 8 , wherein the plurality of resonators are arranged such that the communication holes are aligned along a circumferential direction on the injection surface.

10. 3. The gas turbine combustor according to claim 1, wherein the acoustic chamber communicates with the combustion chamber via a plurality of the communication holes.

11. 3. The gas turbine combustor according to claim 1, wherein the injection surface is covered with a thermal barrier coating.

12. 3. The gas turbine combustor according to claim 1, wherein at least one of a volume of the acoustic chamber, a number, a diameter, or a length of the at least one communication hole is designed based on a combustion oscillation frequency.

13. 3. The gas turbine combustor according to claim 1, wherein the combustor is of a coaxial type in which a central axis of the fuel flow passage through which the fuel flows and a central axis of the mixing flow passage through which the air-fuel mixture flows coincide with each other.

14. 3. The gas turbine combustor according to claim 1, wherein the combustor is of a cross-flow type in which a central axis of a fuel flow passage through which the fuel flows and a central axis of a mixing flow passage through which the air-fuel mixture flows intersect with each other.

15. 3. The gas turbine combustor according to claim 1, wherein the fuel comprises hydrogen.

16. A gas turbine comprising the gas turbine combustor according to claim 1 or 2.

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