Gas turbine combustor and gas turbine

Abstract

The gas turbine combustor according to at least one embodiment of the present disclosure is provided with: a combustion cylinder that comprises a combustion chamber therein; an air hole plate, in which a plurality of air holes extending in the axial direction of the combustion cylinder are formed, and which is located upstream of the combustion chamber; a cylindrical member which comprises in the interior thereof an internal space that extends in the axial direction, and which is located on the side opposite the combustion cylinder with respect to the air hole plate; and a top hat section that comprises a head end section that is located on the side opposite the air hole plate with respect to the cylindrical member. The cylindrical member comprises an opening section that is formed in a side section of the cylindrical member and is for drawing air within a combustor compartment into an internal space. When the top hat section is attached to a casing that demarcates the combustor compartment, at least part of the opening section is located further into the interior of the combustor compartment than the inner peripheral surface of the casing.

Description

Gas turbine combustor and gas turbine

[0001] This application claims priority to Japanese Patent Application No. 2023-097170, filed with the Japan Patent Office on June 13, 2023, the contents of which are incorporated herein by reference.

[0002] In response to societal demands for reducing environmental impact, the reduction of NOx emissions has recently been emphasized in the development of gas turbine combustors. Uniformly distributed combustion is known as one method for reducing NOx emissions. Uniformly distributed combustion is a method in which fuel and air are uniformly distributed and supplied to a combustion chamber for combustion, thereby reducing NOx emissions by suppressing the occurrence of localized high-temperature regions. Many gas turbine combustors that employ uniformly distributed combustion have been proposed, including one equipped with multiple fuel nozzles and multiple air holes arranged coaxially with each nozzle (see, for example, Patent Document 1).

[0003] Japanese Patent Application Laid-Open No. 2003-148734

[0004] In gas turbine combustors, a cylindrical outer circumferential flow passage is provided around the outer periphery of the inner liner (combustor liner), and compressed air from the compressor is passed through this outer circumferential flow passage to cool the inner liner. The compressed air passing through the outer circumferential flow passage is turned back at the end of the combustor and supplied to the combustion chamber where it is burned together with fuel.

[0005] However, with this type of airflow path bent back at the end of the combustor, the cross-sectional area of ​​the outer airflow path becomes small unless the size of the outer cylinder positioned around the inner cylinder can be increased. This increases the flow velocity at the bent portion of the airflow path, potentially causing separation of the compressed air at the bent portion, resulting in a deviation in the airflow rate of the compressed air flowing into the air holes. Deviation in the airflow rate also leads to a deviation in the fuel-air ratio between the air holes, resulting in a local increase in flame temperature in regions with high fuel concentrations, which in turn leads to an increase in NOx emissions. Furthermore, the separation of the compressed air increases pressure loss, potentially reducing the efficiency of the entire gas turbine. Therefore, suppressing the separation of the compressed air and improving the deviation in the airflow rate between the air holes are important challenges for achieving uniformly distributed combustion.

[0006] In view of the above circumstances, at least one embodiment of the present disclosure has an object to provide a gas turbine combustor and a gas turbine that can suppress separation of compressed air and reduce bias in air flow rates between air holes.

[0007] (1) A gas turbine combustor according to at least one embodiment of the present disclosure comprises: a combustion liner having a combustion chamber therein; an air hole plate located upstream of the combustion liner, the air hole plate having a plurality of air holes extending in an axial direction of the combustion liner; a tubular member having an internal space extending in the axial direction therein, the tubular member being located on an opposite side of the combustion liner with the air hole plate; and a top hat portion having a head end portion located on the opposite side of the air hole plate with respect to the tubular member, wherein the tubular member has an opening formed in a side portion of the tubular member for taking air from inside the combustor casing into the internal space, and at least a part of the opening is configured to be located more interior of the combustor casing than an inner circumferential surface of the casing when the top hat portion is attached to a casing that defines the combustor casing.

[0008] (2) A gas turbine according to at least one embodiment of the present disclosure includes: a gas turbine combustor having the configuration described in (1); and the casing that defines the combustor casing.

[0009] According to at least one embodiment of the present disclosure, it is possible to reduce the bias in the air flow rate between the air holes.

[0010] It is a schematic configuration diagram of a gas turbine according to one embodiment. It is a cross-sectional view showing the vicinity of a combustor. It is a diagram for explaining the structure of a main part of a combustor according to some embodiments. It is a diagram showing a cross section of an air hole plate of a 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] First, a gas turbine, which is an example of an application of a gas turbine combustor according to some embodiments, will be described with reference to Fig. 1 and Fig. 2 . Fig. 1 is a schematic configuration diagram of a gas turbine according to one embodiment. Fig. 2 is a cross-sectional view showing the vicinity of a combustor 4. As shown in Fig. 1 , the gas turbine 1 includes a compressor 2 for generating compressed air, a gas turbine combustor (combustor) 4 for generating combustion gas using the compressed air and fuel, and a turbine 6 configured to be rotationally driven by the combustion gas. In the case of the gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6.

[0013] The compressor 2 includes a plurality of stator vanes 16 fixed to a casing 11 of a compressor casing 10 via a blade ring (not shown), and a plurality of moving blades 18 implanted in the rotor 8 so as to be arranged alternately with respect to the stator vanes 16. Air taken in from an air intake 12 is sent to the compressor 2, and this air is compressed as it passes through the plurality of stator vanes 16 and the plurality of moving blades 18, thereby becoming high-temperature, high-pressure compressed air.

[0014] The combustors 4 are supplied with fuel and compressed air generated by the compressor 2, and the fuel is combusted in the combustors 4 to generate combustion gas G, which is a working fluid for the turbine 6. As shown in Figures 1 and 2 , the gas turbine 1 has a plurality of combustors 4 arranged circumferentially around the rotor 8 within a casing 20 that defines a combustor casing 40. Compressed air compressed by the compressor 2 is supplied to the combustor casing 40.

[0015] The turbine 6 includes a plurality of stator vanes 24 and rotor blades 26 provided in a combustion gas passage 27 in the turbine casing 22. The stator vanes 24 and rotor blades 26 of the turbine 6 are provided downstream of the combustor 4 with respect to the flow of the combustion gas G (downstream in the axial direction of the rotor 8). In the following description, with respect to the axial direction of the rotor 8, the downstream side of the direction in which the combustion gas G flows in the combustion gas passage 27 will be referred to as the downstream side in the axial direction of the rotor 8, and the upstream side of the direction in which the combustion gas G flows in the combustion gas passage 27 will be referred to as the upstream side in the axial direction of the rotor 8.

[0016] The stator vanes 24 are fixed to the turbine casing 22, and a plurality of the stator vanes 24 arranged along the circumferential direction of the rotor 8 constitute a stator vane row. The moving blades 26 are implanted in the rotor 8, and a plurality of the moving blades 26 arranged along the circumferential direction of the rotor 8 constitute a moving blade row. The stator vane rows and moving blade rows are arranged alternately in the axial direction of the rotor 8. In the turbine 6, combustion gas G from the combustor 4 flows into a combustion gas passage 27 and passes through the plurality of stator vanes 24 and the plurality of moving blades 26 from the upstream side to the downstream side in the axial direction of the rotor 8, thereby driving the rotor 8 to rotate, which drives a generator connected to the rotor 8 to generate electricity. After driving the turbine 6, the combustion gas G is discharged to the outside via an exhaust chamber 30.

[0017] 3 is a diagram illustrating a structure of a main part of the combustor 4 according to some embodiments. As shown in FIGS. 2 and 3 , the combustor 4 includes a combustion liner 54 having a combustion chamber 52 therein, an air hole plate 56 having a plurality of air holes 58 formed therein and positioned upstream of the combustion liner 54, a tubular member 60 positioned on the opposite side of the combustion liner 54 from the air hole plate 56, and a top hat portion 70 having a head end portion 72 positioned on the opposite side of the tubular member 60 from the air hole plate 56.

[0018] In the following description, the direction in which the central axis AX of the combustion cylinder 54 extends will also be simply referred to as the axial direction. Furthermore, with respect to the axial direction, the downstream side in the flow direction of the combustion gas G inside the combustion cylinder 54 will be referred to as the axial downstream side or simply the downstream side, and the upstream side in the flow direction of the combustion gas G inside the combustion cylinder 54 will be referred to as the axial upstream side or simply the upstream side. The circumferential direction about the central axis AX of the combustion cylinder 54 will also be simply referred to as the circumferential direction. For ease of explanation, the central axis AX of the combustion cylinder 54 will be extended upstream, and the orientations of the air hole plate 56, the tubular member 60, and the top hat portion 70 will also be described based on the central axis AX of the combustion cylinder 54.

[0019] In the combustor 4 according to some embodiments, a transition piece 55 is provided downstream of the combustion liner 54. The transition piece 55 may be configured integrally with the combustion liner 54.

[0020] (Air hole plate 56) In the combustor 4 according to some embodiments, the air hole plate 56 is, for example, a thick-walled disk-shaped member having a plurality of through holes extending in the thickness direction formed as the air holes 58. The air hole plate 56 has the above-mentioned plurality of air holes 58 formed therein, extending in the extension direction of the central axis AX of the combustion liner 54. In the combustor 4 according to some embodiments, the air hole plate 56 is attached to a tubular member 60, which will be described later.

[0021] (Cylindrical Member 60) In the combustor 4 according to some embodiments, the cylindrical member 60 has an internal space 64 extending in the axial direction therein, and is located on the axial upstream side of the air hole plate 56, opposite to the combustion liner 54. The cylindrical member 60 has an opening 62 formed in a side portion 60s of the cylindrical member 60, for introducing compressed air (hereinafter also simply referred to as air) in the combustor casing 40 into the internal space 64.

[0022] The opening 62 has a relatively short flow path 60c extending radially from an outer opening end 62a facing radially outward of the cylindrical member 60 to an inner opening end 62b facing radially inward of the cylindrical member 60. The opening 62 has a bell-mouth shape in which an inner circumferential surface 60i defining the flow path 60c is formed so that the flow path area decreases radially inward from the outer opening end 62a. That is, the opening 62 has a guide portion 66 for guiding compressed air flowing from the side of the cylindrical member 60 into the internal space 64 of the cylindrical member 60. A plurality of openings 62 are formed around the entire circumference at intervals in the circumferential direction in an upstream region of a side portion 60s of the cylindrical member 60.

[0023] As described above, the internal space 64 of the tubular member 60 extends in the axial direction, and the opening 62 having the relatively short flow path 60c extending in the radial direction is located in the upstream region of the side portion 60s. Therefore, in a cross-sectional view along the axial direction, the tubular member 60 forms an L-shaped flow path through which compressed air can flow, consisting of the flow path 60c and the internal space 64.

[0024] 3, a plurality of fuel nozzles 80 are arranged in the internal space 64 of the cylindrical member 60. The plurality of fuel nozzles 80 are provided to correspond to the plurality of air holes 58, respectively, and each extend in the axial direction.

[0025] (Top hat portion 70) In the combustor 4 according to some embodiments, the top hat portion 70 includes a head end portion 72 located upstream in the axial direction of the cylindrical member 60, and a flange portion 74 formed at a position away from the head end portion 72 on the axially upstream side. The flange portion 74 is attached to the casing 20 that defines the combustor casing 40 (see FIG. 2 ). When the flange portion 74 is attached to the casing 20, the top hat portion 70 is configured to be located in the inlet portion 21 that defines a cylindrical space 21a that protrudes from an inner circumferential surface 20i of the casing 20 that defines the combustor casing 40 toward the outside of the combustor casing 40.

[0026] In the combustor 4 configured as described above, the compressed air in the combustor casing 40 flows from the opening 62 into the internal space 64 of the tubular member 60 and flows toward the plurality of air holes 58 in the air hole plate 56. At this time, as shown by arrow a in Figure 3, the compressed air flows radially inward along the flow path 60c of the opening 62 and flows into the internal space 64, and then changes its flow direction by 90 degrees toward the axial downstream side and flows toward the plurality of air holes 58 in the air hole plate 56.

[0027] The compressed air that has flowed into the internal space 64 flows into the plurality of air holes 58 of the air hole plate 56 and flows downstream while being mixed with fuel injected from the plurality of fuel nozzles 80 inside the plurality of air holes 58. The fuel and air mixed in the air hole plate 56 are ignited by an ignition device (not shown), and a flame is formed in the combustion chamber 52 inside the combustion tube 54, generating combustion gas G.

[0028] 4 is a cross-sectional view of an air hole plate 56 of a combustor 4 according to another embodiment. In the combustor 4 according to the another embodiment, a fuel injection hole 53 is provided on an inner circumferential surface 58i of each of the plurality of air holes 58, and fuel can be injected from the fuel injection hole 53 into the air holes 58. That is, in the combustor 4 according to some embodiments, fuel may be injected into the air holes 58 from the fuel injection hole 53 provided on the inner circumferential surface 58i of each of the plurality of air holes 58, rather than injecting fuel into the air holes 58 from a plurality of fuel nozzles 80 arranged in the internal space 64 of the tubular member 60.

[0029] The combustor 4 according to some embodiments described above may have the following features. That is, in the combustor 4 according to some embodiments, when the top hat portion 70 is attached to the casing 20 that defines the combustor casing 40, at least a portion of the opening 62 may be configured to be located more internally of the combustor casing 40 than an inner circumferential surface 20i of the casing 20. Note that in the combustor 4 illustrated in FIG. 2 , the entire opening 62 is configured to be located more internally of the combustor casing 40 than the inner circumferential surface 20i of the casing 20.

[0030] At least a portion of the opening 62 formed in the side portion 60s of the cylindrical member 60 is located more internally than the inner circumferential surface 20i of the casing 20 in the combustor casing 40, thereby making it possible to suppress the flow velocity of the compressed air in the combustor casing 40 when it flows into the opening 62. Furthermore, because the opening 62 is formed in the side portion 60s of the cylindrical member 60, it is easy to make the opening area of ​​the opening 62 relatively large, making it possible to suppress the flow velocity of the compressed air in the combustor casing 40 when it flows into the opening 62. This makes it possible to reduce bias in the air flow rate of the compressed air flowing from the internal space 64 of the cylindrical member 60 into the plurality of air holes 58.

[0031] According to the gas turbine 1 including the combustor 4 according to some of the embodiments described above, it is possible to reduce the bias in the air flow rate of the compressed air flowing from the internal space 64 of the cylindrical member 60 into the plurality of air holes 58, as described above, and therefore it is possible to reduce NOx emissions and also reduce the pressure loss when passing through each air hole 58, thereby reducing the decrease in the efficiency of the entire gas turbine 1.

[0032] In the combustor 4 according to some of the above-described embodiments, the openings 62 may be formed in a position closer to the head end portion 72 in the axial direction than the air hole plate 56. That is, as described above, the openings 62 may be formed in an upstream region of the side portion 60 s of the tubular member 60. In order for the flow of compressed air that has flowed from the side portion 60 s of the tubular member 60 through the openings 62 into the internal space 64 of the tubular member 60 to be turned axially downstream, it is desirable to ensure a certain degree of axial distance from the openings 62 to the air hole plate 56. Therefore, if the openings 62 are formed in the upstream region of the side portion 60 s, the axial distance from the openings 62 to the air hole plate 56 can be made longer than when the openings 62 are formed in the downstream region of the side portion 60 s, thereby reducing bias in the air flow rate of the compressed air flowing into the multiple air holes 58.

[0033] In the combustor 4 according to some of the above-described embodiments, the opening 62 may have a guide portion 66 for guiding the air flowing into the internal space 64 of the cylindrical member 60 from the side of the cylindrical member 60. This makes it difficult for the flow of compressed air flowing into the internal space 64 of the cylindrical member 60 to be turbulent, and can reduce bias in the air flow rate of the compressed air flowing into the plurality of air holes 58.

[0034] In the combustor 4 according to some of the above-described embodiments, as shown in FIG. 2 , the opening 62 may be configured to be located more internally of the combustor casing 40 than the inner circumferential surface 20i of the casing 20 when the top hat portion 70 is attached to the casing 20. This can further suppress the flow velocity of the compressed air inside the combustor casing 40 when it flows into the opening 62. Therefore, it is possible to further reduce the bias in the air flow rate of the compressed air flowing from the internal space 64 of the cylindrical member 60 into the plurality of air holes 58.

[0035] The combustor 4 according to some of the embodiments described above may be provided with a plurality of fuel nozzles 80 extending in the axial direction, each corresponding to the plurality of air holes 58. The plurality of fuel nozzles 80 may be disposed within the internal space 64 of the tubular member 60. This makes it easier for the compressed air to flow in the axial direction along the outer peripheries 80 a of the plurality of fuel nozzles 80 disposed within the internal space 64 of the tubular member 60.

[0036] In the combustor 4 according to some of the above-described embodiments, it is preferable that the tubular member 60 is attached to the head end portion 72 as shown in FIG. 3 . This makes it possible to realize support of the tubular member 60, at least a portion of which is located inside the combustor casing 40, with a simple configuration. The top hat portion 70 having the head end portion 72 is attached to the casing by the flange portion 74. Therefore, the tubular member 60 is attached to the casing via the top hat portion 70.

[0037] In the combustor 4 according to some of the above-described embodiments, the top hat portion 70 may include a flange portion 74 attached to the casing 20. The head end portion 72 may be formed at a position axially separated from the flange portion 74 toward the tubular member 60, i.e., at a position separated from the flange portion 74 on the axial downstream side. This allows the tubular member 60 to be brought closer to the combustor casing 40 that is separated from the flange portion 74 on the axial downstream side.

[0038] Note that, in the top hat portion 70, the axial positional relationship between the flange portion 74 and the head end portion 72 may be defined such that, when the flange portion 74 is attached to the casing 20, at least a portion of the opening 62 of the tubular member 60 attached to the head end portion 72 is located more internal to the combustor casing 40 than the inner circumferential surface 20i of the casing 20. This makes it possible to easily position the tubular member 60 such that at least a portion of the opening 62 is located more internal to the combustor casing 40 than the inner circumferential surface 20i of the casing 20.

[0039] 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.

[0040] The content described in each of the above embodiments can be understood as follows, for example. (1) A gas turbine combustor 4 according to at least one embodiment of the present disclosure includes: a combustion liner 54 having a combustion chamber 52 therein; an air hole plate 56 located upstream of the combustion liner 54 and having a plurality of air holes 58 formed therein extending in an axial direction of the combustion liner 54; a tubular member 60 having an internal space 64 extending in the axial direction therein and located on the opposite side of the combustion liner 54 from the air hole plate 56; and a top hat portion 70 having a head end portion 72 located on the opposite side of the tubular member 60 from the air hole plate 56. The tubular member 60 includes an opening 62 formed in a side portion 60s of the tubular member 60, through which air within the combustor casing 40 is introduced into the internal space 64. When the top hat portion 70 is attached to a casing 20 that defines the combustor casing 40, at least a portion of the opening 62 is configured to be located more interior of the combustor casing 40 than an inner circumferential surface 20i of the casing 20.

[0041] According to the above-described configuration (1), the gas turbine combustor 4 is configured such that at least a portion of the opening 62 formed in the side portion 60s of the cylindrical member 60 is located more internally than the inner circumferential surface 20i of the casing 20 in the combustor casing 40, thereby making it possible to suppress the flow velocity of the compressed air inside the combustor casing 40 when it flows into the opening 62. Moreover, since it is easy to make the opening area of ​​the opening 62 relatively large, it is possible to suppress the flow velocity of the compressed air inside the combustor casing 40 when it flows into the opening 62. This makes it possible to suppress separation of the compressed air flowing from the internal space 64 of the cylindrical member 60 into the plurality of air holes 58 and to reduce bias in the air flow rate of the compressed air.

[0042] (2) In some embodiments, in the configuration of (1) above, the opening 62 may be formed at a position closer to the head end portion 72 than the air hole plate 56 in the axial direction.

[0043] In order for the flow of compressed air that has flowed from the side portion 60s of the tubular member 60 through the opening 62 into the internal space 64 of the tubular member 60 to be redirected axially downstream, it is desirable to ensure a certain degree of axial distance from the opening 62 to the air hole plate 56. According to the configuration (2) above, the axial distance from the opening 62 to the air hole plate 56 can be made longer than when the opening 62 is formed axially closer to the air hole plate 56 than the head end portion 72, thereby reducing bias in the flow rate of compressed air flowing into the multiple air holes 58.

[0044] (3) In some embodiments, in the configurations (1) or (2) above, the opening 62 may have a guide portion 66 for guiding air flowing into the internal space 64 of the tubular member 60 from the side of the tubular member 60.

[0045] According to the configuration (3) above, the flow of compressed air flowing into the internal space 64 of the cylindrical member 60 is less likely to be disturbed, and unevenness in the air flow rate of the compressed air flowing into the multiple air holes 58 can be reduced.

[0046] (4) In some embodiments, in the configurations described in (1) to (3) above, the opening 62 may be configured to be located more internally of the combustor casing 40 than the inner circumferential surface 20i when the top hat portion 70 is attached to the casing 20.

[0047] According to the above configuration (4), it is possible to further suppress the flow velocity of the compressed air inside the combustor casing 40 when it flows into the opening 62. This makes it possible to further reduce the bias in the air flow rate of the compressed air that flows from the internal space 64 of the cylindrical member 60 into the plurality of air holes 58.

[0048] (5) In some embodiments, the configurations described in (1) to (4) above may further include a plurality of fuel nozzles 80 extending in the axial direction, each corresponding to one of the plurality of air holes 58. The plurality of fuel nozzles 80 may be disposed within the internal space 64 of the tubular member 60.

[0049] According to the configuration (5) above, compressed air can easily flow in the axial direction along the outer peripheries 80 a of the plurality of fuel nozzles 80 arranged in the internal space 64 of the cylindrical member 60 .

[0050] (6) In some embodiments, in the configurations (1) to (5) above, the tubular member 60 may be attached to the head end portion 72 .

[0051] According to the above configuration (6), the cylindrical member 60, at least a portion of which is located inside the combustor casing 40, can be supported with a simple configuration.

[0052] (7) In some embodiments, in the configurations (1) to (6) above, the top hat portion 70 may have a flange portion 74 attached to the casing 20. The head end portion 72 may be formed at a position axially spaced from the flange portion 74 toward the tubular member 60.

[0053] According to the above configuration (7), the tubular member 60 can be brought closer to the combustor casing 40 that is axially separated from the flange portion 74 .

[0054] (8) A gas turbine 1 according to at least one embodiment of the present disclosure includes the gas turbine combustor 4 having the configurations described in (1) to (7) above, and a casing 20 that defines a combustor casing 40.

[0055] According to the configuration (8) above, it is possible to reduce the bias in the air flow rate of the compressed air flowing from the internal space 64 of the tubular member 60 into the multiple air holes 58, thereby reducing NOx emissions and reducing the pressure loss when passing through each air hole 58, thereby reducing the decrease in the efficiency of the entire gas turbine 1.

[0056] REFERENCE SIGNS LIST 1 Gas turbine 2 Compressor 4 Gas turbine combustor (combustor) 6 Turbine 8 Rotor 20 Casing 20i Inner peripheral surface 21 Inlet portion 21a Space 40 Combustor casing 52 Combustion chamber 54 Combustion liner 56 Air hole plate 58 Air hole 60 Cylindrical member 60s Side portion 62 Opening 64 Internal space 66 Guide portion 70 Top hat portion 72 Head end portion 74 Flange portion 80 Fuel nozzle

Claims

1. A gas turbine combustor comprising: a combustion liner having a combustion chamber therein; an air hole plate located upstream of the combustion liner and having a plurality of air holes formed therein extending in an axial direction of the combustion liner; a tubular member having an internal space extending in the axial direction and located on an opposite side of the combustion liner with respect to the air hole plate; and a top hat portion having a head end portion located on the opposite side of the tubular member with respect to the air hole plate, wherein the tubular member has an opening formed in a side portion of the tubular member for taking in air from a combustor casing into the internal space, and at least a part of the opening is configured to be located more inside the combustor casing than an inner circumferential surface of the casing when the top hat portion is attached to a casing that defines a combustor casing.

2. The gas turbine combustor according to claim 1, wherein the opening is formed at a position along the axial direction closer to the head end portion than the air hole plate.

3. The gas turbine combustor according to claim 1 or 2, wherein the opening has a guide portion for guiding air flowing into the internal space of the tubular member from a side of the tubular member.

4. The gas turbine combustor according to claim 1 or 2, wherein the opening is configured to be located more inwardly of the combustor casing than the inner circumferential surface when the top hat portion is attached to the casing.

5. The gas turbine combustor according to claim 1 or 2, further comprising: a plurality of fuel nozzles extending in the axial direction corresponding to each of the plurality of air holes, the plurality of fuel nozzles being disposed within the internal space of the tubular member.

6. The gas turbine combustor according to claim 1 or 2, wherein the tubular member is attached to the head end portion.

7. The gas turbine combustor according to claim 1 or 2, wherein the top hat portion has a flange portion attached to the casing, and the head end portion is formed at a position away from the flange portion in the axial direction toward the tubular member.

8. A gas turbine comprising: the gas turbine combustor according to claim 1 or 2; and the casing defining the combustor casing.