Gas turbine combustor and gas turbine

Abstract

A gas turbine combustor according to at least one embodiment disclosed herein comprises: an air hole plate having a plurality of air holes and positioned on the upstream side of a combustion cylinder; a plurality of fuel nozzles respectively corresponding to the plurality of air holes; a plurality of plate support parts that support the air hole plate and are disposed at intervals in the circumferential direction centered on the center axis of the combustion cylinder; and a nozzle support part that supports the plurality of fuel nozzles. The plurality of plate support parts are disposed at regular intervals in the circumferential direction and have respective first mating parts that mate with the nozzle support part when the respective plate support parts are attached to the nozzle support part. The nozzle support part has a plurality of second mating parts that mate with the respective first mating parts when the respective plate support parts are attached to the nozzle support part.

Description

Gas turbine combustor and gas turbine

[0001] This application claims priority to Japanese Patent Application No. 2024-065098, filed with the Japan Patent Office on April 15, 2024, the contents of which are incorporated herein by reference.

[0002] There is known a gas turbine combustor that has an air hole plate disposed between a fuel nozzle and a combustion chamber, and that is configured to eject a fuel flow and an air flow formed on the outer periphery of the fuel flow into the combustion chamber inside air holes formed in the air hole plate (see, for example, Patent Document 1).

[0003] Japanese Patent Application Laid-Open No. 2007-232234

[0004] In a gas turbine combustor having such a configuration, it is considered that the position of the central axis of the air hole and the position of the central axis of the fuel nozzle may become misaligned due to the difference in thermal expansion in the radial direction of the combustion liner between the air hole plate and the end cover that fixes the fuel nozzle during operation of the gas turbine. In other words, it is considered that the fuel nozzle may become eccentric with respect to the air hole due to the difference in thermal expansion.

[0005] If the fuel nozzle is off-center with respect to the air hole, the mixture of fuel and air will change, causing flashback and NO Ｘ This may lead to problems such as an increase in the temperature of the flame due to an undesirable increase in the fuel concentration near the air hole wall surface, which in turn increases the metal temperature of the air hole plate.

[0006] In view of the above circumstances, at least one embodiment of the present disclosure has an object to reduce the amount of eccentricity of a fuel nozzle with respect to an air hole in an air hole plate during operation of a gas turbine.

[0007] (1) A gas turbine combustor according to at least one embodiment of the present disclosure includes: an air hole plate having a plurality of air holes formed therein and located upstream of a combustion liner; and a plurality of fuel nozzles corresponding to the plurality of air holes, wherein, when viewed along a central axis of the combustion liner, an amount of misalignment between the central axis of the air hole and a central axis of the fuel nozzle corresponding to the air hole at room temperature is greater in a second region that is radially outward from the first region about the central axis of the combustion liner than in a first region of the air hole plate.

[0008] (2) A gas turbine according to at least one embodiment of the present disclosure includes: a compressor that generates compressed air; a gas turbine combustor having the configuration described in (1); and a turbine that is rotationally driven by combustion gas generated by the gas turbine combustor.

[0009] According to at least one embodiment of the present disclosure, the amount of eccentricity of the fuel nozzle relative to the air hole plate during operation of the gas turbine can be reduced.

[0010] 2A is a diagram illustrating a schematic configuration of a gas turbine including a gas turbine combustor according to some embodiments of the present disclosure. FIG. 2B is a schematic diagram illustrating an air hole plate of a burner in a gas turbine combustor according to some embodiments that is provided in the gas turbine shown in FIG. 1 , as viewed from the downstream axial direction, illustrating a state at room temperature. FIG. 2C is a schematic diagram illustrating an air hole plate of a burner in a gas turbine combustor according to some embodiments that is provided in the gas turbine shown in FIG. 1 , as viewed from the downstream axial direction, illustrating a state during operation of the gas turbine. FIG. 2A is a cross-sectional view taken along arrows III-III in FIG. 2A , illustrating a gas turbine combustor according to one embodiment, as viewed along arrows IV-IV in FIG. 2B . FIG. 2C is a cross-sectional view taken along arrows IV-IV in FIG. 2B , illustrating a gas turbine combustor according to another embodiment.

[0011] 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," "have," "includes," or "have" of one element are not exclusive expressions that exclude the presence of other elements.

[0012] A gas turbine combustor according to some embodiments of the present disclosure will be described with reference to Fig. 1. Fig. 1 shows a schematic configuration of a gas turbine including a gas turbine combustor according to some embodiments of the present disclosure. The gas turbine 1 shown in Fig. 1 includes an air compressor 110, a gas turbine combustor 100, and a turbine 180.

[0013] A gas turbine combustor 100 (hereinafter also referred to as the combustor 100) according to some embodiments includes a combustor liner (inner casing) 153, a liner flow sleeve (outer casing) 154, a transition piece 152, a transition piece flow sleeve 150, a burner 200, and a fuel system 300. Note that Fig. 1 shows the burner 200 and the fuel system 300 in a simplified manner. Note that the burner 200 and the fuel system 300 will be described later.

[0014] 1 , an air compressor 110 is rotationally driven by a turbine 180, compresses air (intake air) drawn from the atmosphere via an intake section (not shown), generates high-pressure air (combustion air) 120, and supplies the high-pressure air to a gas turbine combustor 100. The gas turbine combustor 100 mixes the high-pressure air 120 supplied from the air compressor 110 with fuel supplied from a fuel system 300, combusts the mixture, generates high-temperature combustion gas 170, and supplies the high-temperature combustion gas 170 to the turbine 180.

[0015] That is, in the gas turbine 1 shown in FIG. 1 , high-pressure air 120, which is combustion air discharged from an air compressor 110, is introduced into a casing 140 from a diffuser 130, and flows from an air inlet hole 151 provided in a transition piece flow sleeve 150 of the gas turbine combustor 100 into a flow passage formed in a gap between the transition piece flow sleeve 150 and a transition piece 152 disposed inside the transition piece flow sleeve 150.

[0016] The high-pressure air 120 that has flowed into the flow path formed in this gap then flows through the flow path formed in the gap between the combustor liner 153 of the gas turbine combustor 100 and a liner flow sleeve 154 that is arranged concentrically with the combustor liner 153 on the outer periphery of the combustor liner 153, then reverses its flow, mixes with fuel that is introduced from the fuel system 300 and injected from multiple fuel nozzles 210 that constitute the cluster nozzle, and combusts in the combustion chamber 160 inside the combustor liner 153 to form a flame 156, generating high-temperature, high-pressure combustion gas 170.

[0017] The high-temperature, high-pressure combustion gas 170 thus generated in the gas turbine combustor 100 flows down the transition piece 152 and is introduced into the turbine 180 .

[0018] In the turbine 180 that constitutes the gas turbine 1, the amount of work generated when the high-temperature, high-pressure combustion gas 170 introduced into the turbine 180 undergoes adiabatic expansion is converted into shaft rotational force by the turbine 180, thereby driving a generator 190 that is connected to the turbine 180 by a turbine shaft, and output is obtained from the generator 190.

[0019] The air compressor 110 and the generator 190 that constitute the gas turbine 1 are connected to the turbine 180 by a turbine shaft. However, the air compressor 110, the turbine 180, and the generator 190 do not have to be configured with a single turbine shaft, and may be configured with two or more turbine shafts.

[0020] Generally, gas turbines widely used in thermal power plants and the like have a configuration in which a plurality of gas turbine combustors are arranged radially around a turbine shaft.

[0021] FIG. 2A is a schematic view of an air hole plate 25 (described later) of a burner 200 in a gas turbine combustor 100 according to some embodiments that is provided in the gas turbine 1 shown in FIG. 1 , as viewed from the downstream axial direction, and illustrates a state at room temperature. FIG. 2B is a schematic view of the air hole plate 25 of the burner 200 in a gas turbine combustor 100 according to some embodiments that is provided in the gas turbine 1 shown in FIG. 1 , as viewed from the downstream axial direction, and illustrates a state during operation of the gas turbine 1. FIG. 3 is a cross-sectional view taken along the arrows III-III in FIG. 2A . FIG. 4A is a cross-sectional view taken along the arrows IV-IV in FIG. 2B of a gas turbine combustor 100 according to one embodiment. FIG. 4B is a view corresponding to the cross-sectional view taken along the arrows IV-IV in FIG. 2B , of a gas turbine combustor 100 according to another embodiment.

[0022] For convenience of illustration, the numbers of fuel nozzles 210 and air holes 250, which will be described later, are different between Figures 2A and 2B and Figure 3. Also, the fuel header 230 is not shown in Figures 4A and 4B.

[0023] In the following description, the direction along the central axis line AXc of the gas turbine combustor 100 will be referred to as the axial direction of the gas turbine combustor 100 or simply as the axial direction. A direction in which the combustion gas 170 flows along the axial direction will be referred to as the axial downstream side or simply as the downstream side, and a direction opposite to the flow of the combustion gas 170 will be referred to as the axial upstream side or simply as the upstream side. In the following description, a radial direction about the central axis line AXc of the gas turbine combustor 100 will be referred to as the radial direction of the gas turbine combustor 100 or simply as the radial direction, and a circumferential direction about the central axis line AXc of the gas turbine combustor 100 will be referred to as the circumferential direction of the gas turbine combustor 100 or simply as the circumferential direction.

[0024] In the gas turbine combustor 100 according to some embodiments, a central axis line AXc of the gas turbine combustor 100 is, for example, a central axis line of a cylindrical combustor liner 153. In the gas turbine combustor 100 according to some embodiments, the central axis line AXc of the combustor 100 coincides with a central axis line AXp of the air hole plate 25 and a central axis line AXs of a nozzle support portion 212, which will be described later, in a relatively upstream region of the combustor liner 153.

[0025] (Regarding the Gas Turbine Combustor 100) The gas turbine combustor 100 according to some embodiments is a gas turbine combustor that can combust, for example, hydrogen fuel and other fuels other than hydrogen fuel. In the gas turbine combustor 100 according to some embodiments, natural gas fuel is combusted as the other fuel. In the gas turbine combustor 100 according to some embodiments, it is possible to perform mono-fuel combustion of hydrogen fuel, mono-fuel combustion of natural gas fuel, or co-fuel combustion of hydrogen fuel and natural gas fuel. Note that the gas turbine combustor 100 according to some embodiments may be, for example, a mono-fuel combustion of hydrogen fuel or a mono-fuel combustion of natural gas.

[0026] In the gas turbine combustor 100 according to some embodiments, the burner 200 is provided at the axially upstream end of the combustor liner 153. In the gas turbine combustor 100 according to some embodiments, the burner 200 includes a fuel header 230 (see FIG. 1 ), a plurality of fuel nozzles 210, and an air hole plate 25.

[0027] The gas turbine combustor 100 according to some embodiments is a type of combustor called a cluster combustor. In the gas turbine combustor 100 according to some embodiments, a plurality of air holes 250 are formed in the air hole plate 25. The plurality of fuel nozzles 210 are arranged in one-to-one correspondence with the plurality of air holes 250 formed in the air hole plate 25 arranged closely and downstream of the fuel nozzles 210 in the axial direction.

[0028] (Nozzle Support Portion 212) In the gas turbine combustor 100 according to some embodiments, each of the plurality of fuel nozzles 210 is supported by the nozzle support portion 212. The nozzle support portion 212 is also referred to as an end cover, and has a cylindrical appearance having a central axis AXs coaxial with the central axis AXc of the combustor 100, and has a fuel header 230 (see FIG. 1 ) formed therein. Fuel can be supplied to the fuel header 230 from a fuel supply pipe 305. Each of the plurality of fuel nozzles 210 is configured to be able to inject the fuel supplied from the fuel supply pipe 305 via the fuel header 230 toward air holes 250 formed in the air hole plate 25.

[0029] A central axis AXn of each of the multiple fuel nozzles 210 extends parallel to a central axis AXs of the nozzle support portion 212 , that is, a central axis AXc of the combustor 100 .

[0030] (Air Hole Plate 25) In the gas turbine combustor 100 according to some embodiments, the air hole plate 25 has a cylindrical appearance having a central axis AXp coaxial with the central axis AXc of the combustor 100, and as described above, has the plurality of air holes 250 formed therein. The central axis AXh of each of the plurality of air holes 250 extends parallel to the central axis AXp of the air hole plate 25, i.e., the central axis AXc of the combustor 100.

[0031] (Plate Support Portion 26) The gas turbine combustor 100 according to some embodiments includes the plate support portion 26 that extends radially outward from the outer circumferential surface of the air hole plate 25 and supports the air hole plate 25. In the example shown in Figures 2A and 2B, the plate support portions 26 are arranged at six locations spaced apart in the circumferential direction. Note that it is preferable that the plate support portions 26 are arranged at at least three or more locations spaced apart in the circumferential direction. Furthermore, it is desirable that the plate support portions 26 are arranged at equal intervals in the circumferential direction, but the intervals between adjacent plate support portions 26 in the circumferential direction do not have to be equal.

[0032] (Ring-Shaped Member 27) The gas turbine combustor 100 according to some embodiments includes the ring-shaped member 27, which is disposed at a distance from the outer circumferential surface of the air hole plate 25 in the radial direction. A radially outer end of the plate support portion 26 is connected to an inner circumferential surface of the ring-shaped member 27. That is, the ring-shaped member 27 supports the air hole plate 25 via the plate support portion 26. In the gas turbine combustor 100 according to some embodiments, the ring-shaped member 27 is coupled to the nozzle support portion 212 by a fastening member such as a bolt.

[0033] (Problems of the Conventional Gas Turbine Combustor) In the gas turbine combustor 100 having the above-described configuration, it is considered that the position of the central axis AXh of the air hole 250 of the air hole plate 25 and the position of the central axis AXn of the fuel nozzle 210 may become misaligned due to a difference in thermal expansion in the radial direction between the air hole plate 25 and the nozzle support portion 212 that fixes the fuel nozzle 210, during operation of the gas turbine 1. In other words, it is considered that the fuel nozzle 210 may become eccentric with respect to the air hole 250 due to the difference in thermal expansion.

[0034] If the fuel nozzle 210 is off-center with respect to the air hole 250, the mixture state of fuel and air changes, which can cause flashback and NO Ｘ This may result in problems such as an increase in the temperature of the flame due to an undesired increase in the fuel concentration near the inner wall surface of the air hole 250, and an increase in the metal temperature of the air hole plate 25.

[0035] (Resolution of the aforementioned problem in the gas turbine combustor 100) Thus, in the gas turbine combustor 100 according to some embodiments, the position of the central axis AXh of the air hole 250 and the position of the central axis AXn of the fuel nozzle 210 are configured to be misaligned in advance at room temperature. Then, in the gas turbine combustor 100 according to some embodiments, when a thermal expansion difference in the radial direction occurs between the air hole plate 25 and the fuel nozzle 210 due to operation of the gas turbine combustor 100, the amount of misalignment between the central axis AXh of the air hole 250 and the central axis AXn of the fuel nozzle 210 is made smaller than the amount of misalignment at room temperature.

[0036] If it is assumed that the air hole plate 25 and the nozzle support portion 212 that supports the multiple fuel nozzles 210 each thermally expand in the radial direction around the central axis AXc of the gas turbine combustor 100, the difference in thermal expansion between the air hole plate 25 and the nozzle support portion 212 increases radially outward.

[0037] Therefore, the gas turbine combustor 100 according to some embodiments is configured as follows. That is, when viewed along the central axis AXc of the gas turbine combustor 100, a positional misalignment amount (e.g., an amount of eccentricity ΔP) between a central axis AXh of an air hole 250 and a central axis AXn of a fuel nozzle 210 corresponding to the air hole 250 at room temperature is larger in a second region R2 that is radially outwardly centered on the central axis AXc of the gas turbine combustor 100 than in the first region R1, as compared with the first region R1, as compared with the first region R1. Note that in FIGS. 2A and 2B , the first region R1 and the second region R2 are shown as ranges tentatively illustrated in FIGS. 2A and 2B , but the radial boundary position between the first region R1 and the second region R2 and the radially outer boundary position of the second region R2, which are indicated by dashed two-dot lines, are not limited to the radial positions tentatively illustrated in FIGS. 2A and 2B .

[0038] This makes it possible to reduce the eccentricity ΔP of the fuel nozzle 210 relative to the air hole 250 while the gas turbine 1 is in operation.

[0039] The gas turbine 1 according to some embodiments includes an air compressor 110 that generates compressed air, the gas turbine combustor 100 according to some embodiments described above, and a turbine 180 that is rotationally driven by combustion gas 170 generated by the gas turbine combustor 100. This prevents flashback and NO Ｘ This reduces the possibility of problems such as an increase in the temperature of the air hole plate 25 and an increase in the metal temperature of the air hole plate 25.

[0040] Furthermore, in the gas turbine combustor 100 according to some embodiments, it is preferable that the eccentricity amount ΔP at room temperature increases radially outward as shown in Fig. 3. That is, for example, in Fig. 3, an eccentricity amount ΔP1 between the air hole 250 and the fuel nozzle 210, which is disposed radially outward of the central axis AXc of the gas turbine combustor 100 and is disposed closest to the central axis AXc of the gas turbine combustor 100, is greater than an eccentricity amount ΔP2 between the air hole 250 and the fuel nozzle 210 disposed second closest to the central axis AXc of the gas turbine combustor 100. It is preferable that an eccentricity amount ΔP3 between the air hole 250 and the fuel nozzle 210 disposed third closest to the central axis AXc is greater than an eccentricity amount ΔP2 between the air hole 250 and the fuel nozzle 210 disposed second closest to the central axis AXc. In FIG. 3 , it is preferable that the eccentricity ΔP4 between the air hole 250 located fourth closest to the central axis AXc and the fuel nozzle 210 be greater than the eccentricity ΔP3 between the air hole 250 located third closest to the central axis AXc and the fuel nozzle 210.

[0041] This allows the eccentricity ΔP of the fuel nozzle 210 relative to the air hole 250 to be reduced over a wide area in the radial direction while the gas turbine 1 is in operation.

[0042] (Regarding Fitting State Between the Plate Support Portion 26 and the Nozzle Support Portion 212) The gas turbine combustor 100 according to some embodiments may include a plurality of plate supports 26 that are arranged at intervals in the circumferential direction. In the gas turbine combustor 100 according to some embodiments, as illustrated in FIGS. 4A and 4B , each of the plurality of plate supports 26 may have a first fitting portion 28 that fits with the nozzle support portion 212 when the plurality of plate supports 26 is attached to the nozzle support portion 212. The nozzle support portion 212 may have a plurality of second fitting portions 213 that fit with the first fitting portions 28 when the plurality of plate supports 26 is attached to the nozzle support portion 212. In the example illustrated in FIG. 4A , the first fitting portion 28 is a protrusion that protrudes upstream from an upstream surface 26u of the plate support portion 26, and the second fitting portion 213 is a recess that is recessed upstream from a downstream surface 212d of the nozzle support portion 212. In the example shown in Figure 4B, the first fitting portion 28 is a recess that is recessed downstream from the upstream surface 26u of the plate support portion 26, and the second fitting portion 213 is a protrusion that protrudes downstream from the downstream surface 212d of the nozzle support portion 212.

[0043] As a result, even when the air hole plate 25 and the nozzle support portion 212 thermally expand, the center position of the air hole plate 25 (the position of the central axis AXp) and the center position of the nozzle support portion 212 (the position of the central axis AXs) when viewed along the central axis AXc of the gas turbine combustor 100 are less likely to deviate from the central axis AXc of the gas turbine combustor 100. That is, by arranging the plurality of plate supports 26 at intervals in the circumferential direction and providing the first fitting portions 28 on the plate supports 26 thus arranged, the plurality of first fitting portions 28 are arranged in a dispersed manner in the circumferential direction. Therefore, compared to a case in which there is one first fitting portion 28 or a case in which the plurality of first fitting portions 28 are arranged only in a relatively narrow region in the circumferential direction, the first fitting portions 28, which serve as base points of movement of the air hole plate 25 relative to the nozzle support portion 212 due to the difference in thermal expansion between the nozzle support portion 212 and the air hole plate 25, are dispersed in the circumferential direction. Therefore, even if a difference in thermal expansion occurs between the nozzle support portion 212 and the air hole plate 25, it is possible to make it difficult for a relative positional deviation to occur between the position of the central axis AXp of the air hole plate 25 and the position of the central axis AXs of the nozzle support portion 212 when viewed along the central axis AXc of the gas turbine combustor 100.

[0044] If the relative positional misalignment between the position of the central axis AXp of the air hole plate 25 and the position of the central axis AXs of the nozzle support portion 212 becomes undesirably large, it may lead to problems such as not being able to reduce the eccentricity amount ΔP as expected during operation of the gas turbine 1 or, in some cases, the eccentricity amount ΔP even increasing. Therefore, according to the gas turbine combustor 100 according to some embodiments, it is possible to reduce such problems and make it easier to reduce the eccentricity amount ΔP of the fuel nozzle 210 with respect to the air hole 250 during operation of the gas turbine 1.

[0045] Furthermore, in the gas turbine combustor 100 according to some embodiments, it is preferable that the plurality of plate support portions 26 are arranged at equal intervals in the circumferential direction. This makes it possible to further reduce the likelihood of relative positional deviation between the central axis AXp of the air hole plate 25 and the central axis AXs of the nozzle support portion 212 when viewed along the central axis AXc of the gas turbine combustor 100, even if a thermal expansion difference occurs between the nozzle support portion 212 and the air hole plate 25. This makes it further easier to reduce the eccentricity of the fuel nozzle 210 with respect to the air hole 250 during operation of the gas turbine 1.

[0046] In the gas turbine combustor 100 according to some embodiments, as described above, one of the first fitting portion 28 and the second fitting portion 213 may include the protrusion 31 protruding in the axial direction centered on the central axis line AXc of the gas turbine combustor 100. The other of the first fitting portion 28 and the second fitting portion 213 may include the recess 32 engageable with the protrusion 31. This makes it less likely that undesired relative movement in the radial direction between the air hole plate 25 and the nozzle support portion 212 will occur, making it easier to reduce the eccentricity ΔP of the fuel nozzle 210 with respect to the air hole 250 during operation of the gas turbine 1.

[0047] In the gas turbine combustor 100 according to some embodiments, it is preferable that when each of the plurality of plate supports 26 is attached to the nozzle support 212, the protrusion 31 is loosely fitted into the recess 32. This allows for slight misalignment between the protrusion 31 and the recess 32 due to a difference in thermal expansion between the air hole plate 25 and the nozzle support 212, making it difficult for thermal stress to occur in the air hole plate 25 and the nozzle support 212.

[0048] The present disclosure is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations of these modifications.

[0049] The content described in each of the above embodiments can be understood as follows, for example. (1) A gas turbine combustor 100 according to at least one embodiment of the present disclosure includes an air hole plate 25 formed with a plurality of air holes 250 and positioned upstream of a combustion liner (a combustor liner 153), and a plurality of fuel nozzles 210 corresponding to the plurality of air holes 250. When viewed along a central axis of the combustion liner (the combustor liner 153) (the central axis AXc of the gas turbine combustor 100), a positional misalignment amount (e.g., an amount of eccentricity ΔP) between a central axis AXh of the air hole 250 and a central axis AXn of the fuel nozzle 210 corresponding to the air hole 250 at room temperature is greater in a second region R2 that is radially outward from the first region R1 about the central axis of the combustion liner (the combustor liner 153) (the central axis AXc of the gas turbine combustor 100) than in the first region R1.

[0050] During operation of the gas turbine 1, the temperature of the air hole plate 25 generally becomes higher than the temperature of the fuel nozzles 210. Therefore, if the air hole plate 25 and the nozzle support portion (nozzle support portion 212) that supports the plurality of fuel nozzles 210 each thermally elongate in the radial direction about the central axis of the combustion liner (combustor liner 153) (the central axis AXc of the gas turbine combustor 100), the difference in thermal elongation between the air hole plate 25 and the nozzle support portion (nozzle support portion 212) increases radially outward. Therefore, when viewed along the central axis AXc of the gas turbine combustor 100 of the combustion liner (combustor liner 153), the amount of misalignment (e.g., eccentricity ΔP) between the central axis AXh of the air hole 250 and the central axis AXn of the fuel nozzle 210 corresponding to the air hole 250 at room temperature is set so that the amount of misalignment in the second region R2 is larger than the amount of misalignment in the first region R1 of the air hole plate 25, and so that the amount of misalignment is smaller during operation of the gas turbine 1 than at room temperature.This makes it possible to reduce the amount of eccentricity ΔP of the fuel nozzle 210 with respect to the air hole 250 during operation of the gas turbine 1.

[0051] According to the configuration (1) above, the eccentricity ΔP of the fuel nozzle 210 relative to the air holes 250 of the air hole plate 25 during operation of the gas turbine 1 can be reduced. Ｘ This reduces the possibility of problems such as an increase in the temperature of the air hole plate 25 and an increase in the metal temperature of the air hole plate 25.

[0052] (2) In some embodiments, in the configuration of (1) above, the amount of misalignment (for example, the amount of eccentricity ΔP) at room temperature may increase radially outward.

[0053] As described above, if the air hole plate 25 and the nozzle support portion (nozzle support portion 212) that supports the plurality of fuel nozzles 210 each thermally elongate in the radial direction about the central axis of the combustion liner (combustor liner 153) (the central axis AXc of the gas turbine combustor 100), the difference in thermal elongation between the air hole plate 25 and the nozzle support portion 212 increases radially outward. According to the configuration (2) above, the eccentricity ΔP of the fuel nozzles 210 with respect to the air holes 250 can be reduced over a wide region in the radial direction during operation of the gas turbine 1.

[0054] (3) In some embodiments, the configuration described in (1) or (2) above may include a plurality of plate support portions 26 that support the air hole plate 25 and are arranged at intervals in the circumferential direction around a central axis line of the combustion liner (combustor liner 153) (central axis line AXc of the gas turbine combustor 100), and a nozzle support portion 212 that supports the plurality of fuel nozzles 210. Each of the plurality of plate support portions 26 may have a first fitting portion 28 that fits with the nozzle support portion 212 when the respective plate support portions 26 are attached to the nozzle support portion 212. The nozzle support portion 212 may have a plurality of second fitting portions 213 that fit with the respective first fitting portions 28 when the respective plate support portions 26 are attached to the nozzle support portion 212.

[0055] According to the configuration (3) described above, when viewed along the central axis of the combustion liner (combustor liner 153) (the central axis AXc of the gas turbine combustor 100), even when the air hole plate 25 and the nozzle support portion 212 thermally elongate, the central position (position of the central axis AXp) of the air hole plate 25 and the central position (position of the central axis AXs) of the nozzle support portion 212 are less likely to be deviated from the central axis of the combustion liner (combustor liner 153) (the central axis AXc of the gas turbine combustor 100). This makes it easier to reduce the eccentricity ΔP of the fuel nozzle 210 with respect to the air holes 250 during operation of the gas turbine 1.

[0056] (4) In some embodiments, in the configuration of (3) above, the plurality of plate support portions 26 may be arranged at equal intervals in the circumferential direction.

[0057] According to the configuration (4) described above, when viewed along the central axis of the combustion liner (combustor liner 153) (the central axis AXc of the gas turbine combustor 100), it is more likely that the central position (the position of the central axis AXp) of the air hole plate 25 and the central position (the position of the central axis AXs) of the nozzle support portion 212 will be less likely to be misaligned from the central axis of the combustion liner (combustor liner 153) (the central axis AXc of the gas turbine combustor 100) when the air hole plate 25 and the nozzle support portion 212 thermally elongate. This makes it more likely that the eccentricity of the fuel nozzle 210 with respect to the air hole 250 will be reduced during operation of the gas turbine 1.

[0058] (5) In some embodiments, in the configuration of (4) described above, one of the first fitting portion 28 and the second fitting portion 213 may include a protrusion 31 that protrudes in an axial direction centered on a central axis line of the combustion liner (the combustor liner 153) (the central axis line AXc of the gas turbine combustor 100). The other of the first fitting portion 28 and the second fitting portion 213 may include a recess 32 that is engageable with the protrusion 31.

[0059] According to the configuration (5) above, undesired relative movement in the radial direction between the air hole plate 25 and the nozzle support portion 212 is less likely to occur, making it easier to reduce the eccentricity ΔP of the fuel nozzle 210 relative to the air hole 250 during operation of the gas turbine 1.

[0060] (6) In some embodiments, in the configuration of (5) above, when each of the multiple plate support parts 26 is attached to the nozzle support part 212, the protrusion 31 may be configured to fit loosely into the recess 32.

[0061] According to the configuration (6) above, a slight misalignment between the protrusion 31 and the recess 32 due to the difference in thermal expansion between the air hole plate 25 and the nozzle support part 212 is tolerated, so that thermal stress is less likely to occur in the air hole plate 25 and the nozzle support part 212.

[0062] (7) A gas turbine 1 according to at least one embodiment of the present disclosure includes: a compressor (air compressor 110) that generates compressed air; a gas turbine combustor 100 having any of the configurations described above in (1) to (6); and a turbine 180 that is rotationally driven by combustion gas 170 generated by the gas turbine combustor 100.

[0063] According to the above configuration (7), flashback and NO Ｘ This reduces the possibility of problems such as an increase in the temperature of the air hole plate 25 and an increase in the metal temperature of the air hole plate 25.

[0064] REFERENCE SIGNS LIST 1 Gas turbine 25 Air hole plate 26 Plate support portion 28 First fitting portion 31 Protrusion 32 Recess 100 Gas turbine combustor 110 Compressor (air compressor) 153 Combustor liner (inner cylinder) 180 Turbine 210 Fuel nozzle 212 Nozzle support portion 213 Second fitting portion 250 Air hole

Claims

1. A gas turbine combustor comprising: an air hole plate having a plurality of air holes formed therein and located on the upstream side of a combustion liner; a plurality of fuel nozzles corresponding to each of the plurality of air holes; a plurality of plate support parts supporting the air hole plate and arranged at intervals in a circumferential direction around a central axis of the combustion liner; and a nozzle support part supporting the plurality of fuel nozzles, wherein each of the plurality of plate support parts is arranged at equal intervals in the circumferential direction and has a first fitting part that fits with the nozzle support part when each of the plurality of plate support parts is attached to the nozzle support part, and the nozzle support part has a plurality of second fitting parts that fit with each of the first fitting parts when each of the plurality of plate support parts is attached to the nozzle support part.

2. The gas turbine combustor according to claim 1, wherein one of the first fitting portion and the second fitting portion includes a protrusion that protrudes in an axial direction centered on a central axis of the combustion liner, and the other of the first fitting portion and the second fitting portion includes a recess that is engageable with the protrusion.

3. The gas turbine combustor according to claim 2, wherein when each of the plurality of plate supports is attached to the nozzle support, the protrusion is loosely fitted into the recess.

4. The gas turbine combustor according to any one of claims 1 to 3, wherein, when viewed along the central axis of the combustion liner, an amount of misalignment at room temperature between the central axis of one of the air holes and the central axis of the fuel nozzle corresponding to the one of the air holes is larger in a second region that is radially outward from the first region about the central axis of the combustion liner than in a first region of the air hole plate.

5. The gas turbine combustor according to claim 4, wherein the amount of misalignment at room temperature increases toward the outside in the radial direction.

6. A gas turbine comprising: a compressor that generates compressed air; the gas turbine combustor according to any one of claims 1 to 3; and a turbine that is rotationally driven by combustion gas generated by the gas turbine combustor.

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