gas turbine

Abstract

To provide a gas turbine which can inhibit variations in temperature distributions of multiple combustion chambers.SOLUTION: A gas turbine 10 includes a combustor 18, an air lead-out unit 40, an outer peripheral cover portion 74, an inner peripheral cover portion 21, and a fuel supply unit 23. A lead-out port 44 of the air lead-out unit 40 is located radially outside of one end portion of the combustor 18. The combustor 18 has a guide wall portion 62 which is provided so as to connect mutually-adjacent combustion cylinders 56 and guides air from an air flow path 78 to an inner space 86 via a communication path 96. Through holes 64 are formed on an outer peripheral surface of each of the combustion cylinders 56 and open to the inner space 86 to allow air in the inner space 86 to flow into the downstream side of a combustion chamber 66.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present invention relates to gas turbines. [Background technology]

[0002] The gas turbine includes a combustor, a fuel supply unit, an air outlet unit that outputs air supplied from a compressor to the combustor, an annular outer cover unit, and an annular inner cover unit (see, for example, Patent Document 1). The combustor includes, for example, multiple combustion tubes arranged in a ring shape. The fuel supply unit supplies fuel to upstream portions of the combustion chambers of the multiple combustion tubes. Each combustion tube has an air inlet for allowing air to flow into the upstream portion of the combustion chamber. The outer cover unit covers the combustor from the radially outer side of the combustor. The inner cover unit covers the combustor from the radially inner side of the combustor. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Utility Model Application Publication No. 63-61663 Summary of the Invention [Problem to be solved by the invention]

[0004] In the above-described gas turbine, when the outlet of the air outlet section is located radially outward from one end of the combustor and the air inlet is located at the other end of the combustor, the air introduced from the air outlet section flows through an air flow path between the combustor and the outer cover section. That is, the air flows through the air flow path from one end of the combustor to the other end. Therefore, the outer peripheral surface of the combustor can be cooled by the air flowing through the air flow path.

[0005] In such a combustor, if the flow path width of the air flow path (the spacing along the radial direction of the combustor) is set to be narrow, the flow velocity of the air flowing through the air flow path increases, making it possible to efficiently cool the outer circumferential surface of the combustor.

[0006] Furthermore, for example, if a through hole is formed in each combustion tube to introduce air flowing through the upstream part of the air flow path (the part close to the air inlet part) downstream of the upstream part of the combustion chamber, the combustion gas in the combustion chamber can be diluted by the air introduced into the combustion chamber from the through hole.

[0007] However, the narrower the air flow path width, the more easily the air flow velocity changes due to variations in component dimensions, making it difficult to uniform the flow rate and incidence angle of the air flowing into the combustion chambers from the through holes, and this tends to cause variations in the temperature distribution of the combustion gas in the multiple combustion chambers.In addition, in this case, air tends to stagnate in the inner space between the combustor and the inner cover, which can make it difficult to cool the outer surface of the combustion liner in a balanced manner.

[0008] The present invention aims to solve the above-mentioned problems. [Means for solving the problem]

[0009] One aspect of the present invention is a gas turbine including a compressor, a combustor having a plurality of combustion tubes arranged in an annular shape, an air outlet section that introduces air supplied from the compressor to the combustor, an annular outer cover section that covers the combustor from a radially outer side of the combustor, an annular inner cover section that covers the combustor from a radially inner side of the combustor, and a plurality of fuel supply sections that supply fuel to upstream portions of combustion chambers of the plurality of combustion tubes, wherein the combustor has a first end that is one end in an axial direction of the combustor and a second end that is the other end in the axial direction, an outlet port of the air outlet section is located radially outward of the first end, and a fuel supply section is provided between the combustor and the outer cover section to direct the air introduced from the air outlet section from the first end to the second end. an air flow path is formed through the combustor and the inner peripheral cover portion; an inner space is formed between the combustor and the inner peripheral cover portion, into which the air flows from the air flow path via a communication path provided at the second end of the combustor; each of the plurality of combustion tubes is provided with an air inlet located at the second end of the combustor and for allowing the air that has flowed through the air flow path to flow into the upstream part of the combustion chamber; the combustor has a guide wall portion that is provided to connect adjacent combustion tubes in the plurality of combustion tubes and guides the air from the air flow path to the inner space via the communication path; and a through hole that opens to the inner space and allows the air in the inner space to flow into the downstream side of the combustion chamber is formed on an outer peripheral surface of each of the plurality of combustion tubes. [Effects of the Invention]

[0010] According to the present invention, air guided from the air outlet portion flows into the inner space via the air flow path and the communication passage, and is then introduced downstream of the combustion chamber through the through-hole. This prevents air from stagnating in the inner space (by increasing the flow rate of air flowing through the inner space), allowing the outer peripheral surface of the combustion liner to be efficiently cooled without increasing the flow rate of air guided from the combustor. Furthermore, even if the flow path width of the air flow path is set relatively narrow, the flow rate and incident angle of the air flowing into the combustion chamber through the through-hole are unlikely to change even if there is variation in component dimensions. This reduces variation in temperature distribution among multiple combustion chambers. [Brief explanation of the drawings]

[0011] [Figure 1] FIG. 1 is a longitudinal sectional view of a gas turbine according to one embodiment of the present invention. [Figure 2] FIG. 2 is a cross-sectional view taken along line II-II in FIG. [Figure 3] FIG. 3 is a perspective, partial cross-sectional view of the combustor of FIG. [Figure 4] FIG. 4 is an enlarged view of FIG. [Figure 5] FIG. 5 is a cross-sectional view taken along line VV in FIG. DETAILED DESCRIPTION OF THE INVENTION

[0012] 1, a gas turbine 10 according to an embodiment of the present invention is used, for example, as a power source for a generator. The gas turbine 10 may also be used as a power source for an aircraft or a ship. The gas turbine 10 includes a turbine section 12, a compressor 14, a diffuser 16, a combustor 18, a casing member 19, an inner circumferential cover section 21, multiple fuel supply sections 23, and auxiliary equipment members 25.

[0013] The turbine section 12 has a turbine 20, a shaft 22, and a turbine housing 24. The turbine 20 is made of a heat-resistant metal material. The turbine 20 is configured as a radial turbine. The turbine 20 has a plurality of blades 27 that receive combustion gas introduced from the radially outer side.

[0014] The shaft 22 extends in one direction (the direction of the arrow X). One end of the shaft 22 (the end in the direction of the arrow X1) is connected to, for example, an output shaft (not shown). The output shaft may be the rotating shaft of a generator, or the rotating shaft of a propeller of an aircraft or ship. Note that, in cases where the gas turbine 10 is used as a jet engine, for example, an output shaft does not need to be connected to one end of the shaft 22. The other end of the shaft 22 (the end in the direction of the arrow X2) is connected to the turbine 20. The axis of the shaft 22 is located on the rotation axis of the turbine 20.

[0015] The turbine housing 24 accommodates the turbine 20. The turbine housing 24 covers the turbine 20 from the radially outer side. The turbine housing 24 has a turbine nozzle 26, a first housing 28, and a second housing 30. The turbine nozzle 26 is formed in an annular shape. The turbine nozzle 26 is arranged so as to cover the blades 27 of the turbine 20 from the radially outer side. The turbine nozzle 26 guides combustion gas guided from the combustor 18 to the blades 27 of the turbine 20. The turbine nozzle 26 is supported by the first housing 28 and the second housing 30.

[0016] The first housing 28 is formed in an annular shape so as to cover a portion of the turbine 20 in the direction of arrow X1 beyond the turbine nozzle 26 (one end of the turbine 20). The second housing 30 is formed in an annular shape so as to cover a portion of the turbine 20 in the direction of arrow X2 beyond the turbine nozzle 26 (the other end of the turbine 20). The second housing 30 extends in the direction of arrow X2 beyond the other end of the turbine 20. An exhaust port 32 facing in the direction of arrow X2 is formed at the extending end of the second housing 30. The exhaust port 32 exhausts combustion gas inside the turbine housing 24 to the outside.

[0017] The compressor 14 is configured as, for example, a centrifugal compressor. The compressor 14 has a compressor wheel 34 and a shroud case 36 that houses the compressor wheel 34. The compressor wheel 34 has an insertion hole 38 formed therein, into which the shaft 22 is inserted.

[0018] The rotation axis of the compressor wheel 34 is located on the axis of the shaft 22. The compressor wheel 34 is connected to the shaft 22 so as to rotate together with the shaft 22. The shaft 22 transmits the rotational force of the turbine 20 to the compressor wheel 34, causing the compressor wheel 34 to rotate.

[0019] The shroud case 36 covers the compressor wheel 34. The shroud case 36 has an opening (not shown) for allowing outside air to flow into the interior of the shroud case 36. The air inside the shroud case 36 is compressed as the compressor wheel 34 rotates.

[0020] The diffuser 16 includes an air outlet section 40 that outlets the air (compressed air) supplied from the compressor 14 to the combustor 18, and a diffuser housing 42 that covers the air outlet section 40. The air outlet section 40 is located radially outward of the compressor wheel 34. The air outlet section 40 guides the air supplied from the compressor 14 in the direction of arrow X2. An outlet port 44 of the air outlet section 40 faces in the direction of arrow X2.

[0021] The combustor 18 is formed into an annular shape and made of a heat-resistant metal material. The axis Ax1 of the combustor 18 is disposed coaxially with the turbine 20 and the shaft 22. The combustor 18 has a first end 18a which is one end in the axial direction of the combustor 18 (the end in the direction of arrow X1) and a second end 18b which is the other end in the axial direction (the end in the direction of arrow X2).

[0022] 1 to 3, the combustor 18 is formed in an annular shape. The outlet 44 of the air outlet portion 40 is located radially outward of a first end portion 18a of the combustor 18 (see FIG. 1). The combustor 18 has a plurality of combustion tubes 56, a plurality of communication pipes 58, an annular outlet portion 60, a plurality of guide walls 62, and a plurality of through-holes 64 (dilution holes).

[0023] The multiple combustion tubes 56 extend in the axial direction (direction of arrow X) of the combustor 18 (see FIGS. 1 and 3). In FIG. 2, the multiple combustion tubes 56 are arranged in an annular shape. Specifically, in the example of FIG. 2, seven combustion tubes 56 are arranged at equal intervals around the axis Ax1 of the combustor 18. Note that the number of combustion tubes 56 is not limited to seven. The combustion tubes 56 are formed in a cylindrical shape.

[0024] 1 and 3, an annular outlet portion 60 is connected to one end portion (the end portion in the direction of arrow X1) of the combustion liner 56. A swirl flow generating blade portion 69 having an air inlet 68 for introducing air into an upstream portion of a combustion chamber 66 inside the combustion liner 56 is provided at the other end portion (the end portion in the direction of arrow X2). The air inlet 68 is located at the second end portion 18b of the combustor 18. The air inlet 68 faces in the direction of arrow X2. The hole size (diameter) of the air inlet 68 is smaller than the inner diameter of the intermediate portion of the combustion liner 56 in the extension direction.

[0025] 1 , the swirl flow generating blade section 69 has an inner cylinder 71, an outer cylinder 73, and swirl vanes 75. A tip end of an injector 84 (described later) of the fuel supply section 23 is located inside the inner cylinder 71. A space through which air flows is formed between the inner cylinder 71 and the tip end of the injector 84. A space through which air flows is formed between the inner cylinder 71 and the outer cylinder 73. The swirl vanes 75 generate a swirl flow in the air flowing into the combustion chamber 66 from the air inlet 68. The swirl vanes 75 are provided between the inner cylinder 71 and the outer cylinder 73. Although not shown in detail, the swirl vanes 75 are also provided between the inner cylinder 71 and the tip end of the injector 84.

[0026] 2 and 3, the communication pipes 58 connect the combustion liner 56 that are adjacent in the circumferential direction of the combustor 18 to each other. The inner holes 70 of the communication pipes 58 connect the combustion chambers 66 of the combustion liner 56 that are adjacent in the circumferential direction of the combustor 18 to each other (see FIG. 2). The communication pipes 58 are located in the middle of the combustion liner 56 in the extension direction (FIGS. 2 and 3).

[0027] The annular outlet portion 60 is formed in a circular ring shape (see FIGS. 1 and 3). In FIG. 1, the annular outlet portion 60 is connected to the turbine nozzle 26. The annular outlet portion 60 has an annular outlet flow path 72 that communicates with the plurality of combustion chambers 66. The outlet flow path 72 guides combustion gas generated in the plurality of combustion chambers 66 to the turbine nozzle 26. The specific configurations of the plurality of guide wall portions 62 and the through hole 64 will be described later.

[0028] The casing member 19 has an outer circumferential cover portion 74 and an end cover portion 76. The outer circumferential cover portion 74 is formed in an annular shape (see FIG. 2). The outer circumferential cover portion 74 covers the combustor 18 from the radially outer side of the combustor 18.

[0029] 1, one end (end in the direction of arrow X1) of the outer circumferential cover portion 74 is connected to the diffuser housing 42. The other end (end in the direction of arrow X2) of the outer circumferential cover portion 74 is located in the direction of arrow X2 further than the second end 18b of the combustor 18. An air flow path 78 is formed between the combustor 18 and the outer circumferential cover portion 74, through which air introduced from the air outlet portion 40 flows from the first end 18a to the second end 18b of the combustor 18. The air flow path 78 extends in an annular shape.

[0030] 2, the outer circumferential cover portion 74 is formed such that outer circumferential recesses 80 and outer circumferential protrusions 82 are alternately and continuously arranged in the circumferential direction of the combustor 18. The outer circumferential recesses 80 are recessed radially inward of the combustor 18 so as to enter between adjacent combustion tubes 56. The outer circumferential recesses 80 protrude in an arc shape radially inward of the combustor 18. The outer circumferential protrusions 82 protrude radially outward of the combustor 18 so as to follow the outer circumferential surfaces of the plurality of combustion tubes 56. The outer circumferential protrusions 82 protrude in an arc shape radially outward of the combustor 18. This enables the flow path width of the air flow path 78 (the width along the radial direction of the combustor 18) to be set narrow.

[0031] 1, the end cover portion 76 is formed in an annular shape. The end cover portion 76 covers the combustor 18 from the direction of arrow X2. The end cover portion 76 extends radially inward of the combustor 18 from the end of the outer cover portion 74 in the direction of arrow X2. The end cover portion 76 covers the air inlet 68 of each combustion liner 56.

[0032] A fuel supply unit 23 is provided for each of the multiple combustion tubes 56. In other words, the number of fuel supply units 23 provided is the same as the number of combustion tubes 56. The fuel supply unit 23 has an injector 84. The tip of the injector 84 is inserted into the combustion chamber 66 from the air inlet 68 of the combustion tube 56. The center line (fuel injection port) of the injector 84 is located on the axis Ax2 of the combustion tube 56. The injector 84 extends along the axial direction of the combustion tube 56 (direction of arrow X). The injector 84 injects fuel into the combustion chamber 66. The injector 84 is attached to the end cover portion 76.

[0033] The inner circumferential cover portion 21 is formed in an annular shape (see FIG. 2). The inner circumferential cover portion 21 covers the combustor 18 from the radially inner side. One end of the inner circumferential cover portion 21 (the end in the direction of arrow X1) is connected to the annular outlet portion 60. The other end of the inner circumferential cover portion 21 (the end in the direction of arrow X2) is connected to the end cover portion 76. An inner space 86 is formed between the combustor 18 and the inner circumferential cover portion 21, into which air flows from the air flow path 78 via a communication passage 96 provided in the second end portion 18b of the combustor 18. The inner space 86 extends in an annular shape.

[0034] 2, the inner circumferential cover portion 21 is formed so that inner circumferential recesses 88 and inner circumferential protrusions 90 are alternately and continuously arranged in the circumferential direction of the combustor 18. The inner circumferential recesses 88 are recessed radially outward of the combustor 18 so as to fit between adjacent combustion tubes 56. The inner circumferential protrusions 90 protrude radially inward of the combustor 18 so as to fit along the outer peripheral surfaces of the combustion tubes 56. The inner circumferential protrusions 90 protrude in an arc shape radially inward of the combustor 18.

[0035] 3 and 4, the guide wall portion 62 is provided so as to connect the combustion tubes 56 that are adjacent in the circumferential direction of the combustor 18. In other words, the guide wall portion 62 is provided between the combustion tubes 56 that are adjacent in the circumferential direction of the combustor 18. The guide wall portion 62 guides air from the air flow path 78 to the inner space 86 via the communication passage 96 (see FIG. 4).

[0036] The guide wall portion 62 has a first wall portion 92 and a second wall portion 94. The first wall portion 92 extends from the communicating pipe 58 toward a first end 18a of the combustor 18 (in the direction of arrow X1). The first wall portion 92 extends in the direction of arrow X1 so as to be inclined radially outward of the combustor 18. The extending end of the first wall portion 92 is connected to the annular outlet portion 60. When viewed in the axial direction of the combustor 18, the first wall portion 92 protrudes in an arc shape radially outward of the combustor 18 (see FIG. 5 ). Note that the cross section of the first wall portion 92 may also protrude in an arc shape radially inward of the combustor 18.

[0037] 3 and 4, the second wall portion 94 extends from the communicating pipe 58 toward the second end 18b of the combustor 18 (in the direction of arrow X2). The extending end of the second wall portion 94 is positioned offset in the direction of arrow X1 from the other end of the combustion liner 56. When viewed from the axial direction of the combustor 18, the second wall portion 94 protrudes in an arc shape radially inward of the combustor 18 (see FIG. 3). Note that the cross section of the second wall portion 94 may also protrude in an arc shape radially outward of the combustor 18.

[0038] 4, the communicating pipe 58 and the guide wall portion 62 divide the space between the outer circumferential cover portion 74 and the inner circumferential cover portion 21 into an air flow path 78 located radially outward of the combustor 18 and an inner space 86 located radially inward of the combustor 18. In this case, the combustor 18 has a communicating passage 96 at a second end portion 18b (end portion in the direction of arrow X2) of the combustor 18 that communicates the air flow path 78 and the inner space 86 with each other.

[0039] As shown in FIGS. 4 and 5, two through holes 64 are provided for each combustion liner 56. These through holes 64 guide air in the inner space 86 to the downstream side of the combustion chamber 66. The through holes 64 are located between the first wall portion 92 and the inner circumferential cover portion 21. The through holes 64 are adjacent to the boundary between the first wall portion 92 and the annular outlet portion 60. The through holes 64 are formed in a position (the end portion in the direction of arrow X1) on the outer circumferential surface of the combustion liner 56 that is adjacent to the annular outlet portion 60. In FIG. 4, the through holes 64 are located further in the direction of arrow X1 than the communicating pipe 58. The through holes 64 are located radially outward of the combustor 18 than the communicating pipe 58.

[0040] As shown in Fig. 5, the through-holes 64 open radially inward of the combustion liner 56. In other words, they open toward the axis Ax2 of the combustion liner 56. The two through-holes 64 are at the same height in the axial direction of the combustion liner 56. The two through-holes 64 are arranged to face each other across the axis Ax2 of the combustion liner 56. The two through-holes 64 are positioned 180° apart in the circumferential direction of the combustion liner 56.

[0041] As shown in FIGS. 1 and 2 , the auxiliary member 25 includes one sensor 98 and two ignition devices 100. The sensor 98 detects a physical quantity of air flowing through the air flow path 78. Specifically, the sensor 98 is, for example, a pressure sensor that detects the pressure of the air flowing through the air flow path 78. The sensor 98 extends in one direction. The sensor 98 is attached to the outer circumferential recess 80 of the outer circumferential cover portion 74 so that its tip is exposed to the air flow path 78. The sensor 98 extends along the radial direction of the combustor 18 while attached to the outer circumferential cover portion 74. The sensor 98 is located in the direction of arrow X2 relative to the communicating pipe 58. However, the attachment position of the sensor 98 in the axial direction of the combustor 18 can be set as appropriate.

[0042] In FIG. 2 , the ignition device 100 is an igniter that discharges in the combustion chamber 66. The ignition device 100 extends in one direction. The ignition device 100 is attached to the outer peripheral recess 80 of the outer peripheral cover portion 74 so that its tip is exposed to the combustion chamber 66. The ignition device 100 is attached to a peripheral recess 80 that is different from the peripheral recess 80 to which the sensor 98 is attached. Furthermore, the two ignition devices 100 are attached to different peripheral recesses 80. In this case, the two ignition devices 100 are attached to the outer peripheral cover portion 74 so that they are furthest from each other in the circumferential direction of the combustor 18.

[0043] The ignition device 100 extends at an angle relative to the radial direction of the combustor 18 when attached to the outer peripheral cover portion 74. The tip of the ignition device 100 faces the axis Ax2 of the combustion tube 56. The ignition device 100 is arranged so that its position is aligned with the communicating pipe 58 in the axial direction of the combustor 18. There may be only one ignition device 100. However, if two ignition devices 100 are provided, the mixture (fuel and air) in the combustion chamber 66 can be ignited even if one of the ignition devices 100 fails.

[0044] 1 and 4, in the gas turbine 10 described above, air (compressed air) supplied from the compressor 14 is guided from the outlet 44 of the air outlet section 40 to the air flow path 78. The air guided from the outlet 44 to the air flow path 78 flows in the direction of arrow X2 along the guide wall section 62 and the combustion liner 56 to the second end 18b of the combustor 18, and then hits the end cover section 76 in the communication passage 96, turns 180°, and is guided to the inner space 86. At this time, part of the air flows into the combustion chamber 66 from the air inlet 68 (see FIG. 1).

[0045] In the combustion chamber 66, air flowing in from the air inlet 68 is mixed with fuel injected from the injector 84. When the gas turbine 10 starts up, the ignition device 100 discharges electricity in the combustion chamber 66. This generates a flame in the combustion chamber 66. The flame generated in the combustion chamber 66 by the ignition device 100 is transmitted to the combustion chamber 66 of the combustion liner 56 that does not have the ignition device 100 attached via the inner hole 70 of the communicating pipe 58 (see FIG. 2). This allows flames to be generated in the combustion chamber 66 of all the combustion liner 56. In each combustion chamber 66, the part of the combustion liner 56 along the axis Ax2 (the center part) becomes the hottest.

[0046] In this embodiment, the air introduced into the inner space 86 flows into the combustion chamber 66 through the two through-holes 64. At this time, as shown in FIG. 5 , the air flowing into the combustion chamber 66 from the two through-holes 64 collides (head-on collision) on the axis Ax2 of the combustion liner 56 downstream of the combustion chamber 66. This allows relatively low-temperature air to remain near the axis Ax2 (near the center) of the combustion liner 56. Therefore, the combustion gas in the center of the combustion chamber 66 can be diluted in a balanced manner. Note that a portion of the air that flows into the combustion chamber 66 from the through-holes 64 and collides head-on travels upstream of the combustion chamber 66 to be mixed with fuel and used for combustion. Therefore, the air required for combustion can be efficiently supplied to the combustion chamber 66.

[0047] The combustion chamber 66 is also cooled by the air flowing outside the combustor 18. Specifically, as shown in FIG. 4, the air flowing through the air flow passage 78 cools the outer peripheral surface of the combustion liner 56. In this embodiment, the outer peripheral cover portion 74 has an uneven shape that corresponds to the shape of the annularly arranged combustion liner 56, and therefore the flow passage width of the air flow passage 78 is set to be relatively narrow (see FIG. 2). Therefore, the flow velocity of the air flowing through the air flow passage 78 is increased, and the outer peripheral surface of the combustion liner 56 can be efficiently cooled.

[0048] Furthermore, in this embodiment, air in the inner space 86, where air tends to stagnate, flows into the combustion chamber 66 through the through holes 64, making it difficult for air to stagnate in the inner space 86. Therefore, the outer peripheral surface of the combustion liner 56 can be efficiently cooled by the air flowing through the inner space 86.

[0049] The combustion gases from the combustion chambers 66 join together in the outlet passage 72 of the annular outlet portion 60 and flow toward the turbine 20 via the turbine nozzle 26. This causes the turbine 20 to rotate. The rotational force of the turbine 20 is transmitted to the compressor wheel 34 via the shaft 22.

[0050] This embodiment has the following advantages.

[0051] According to this embodiment, the air guided from the air leading portion 40 flows into the inner space 86 via the air flow path 78 and the communication path 96, and is then introduced downstream of the combustion chamber 66 through the through-hole 64. This prevents air from accumulating in the inner space 86 (by increasing the flow rate of air flowing through the inner space 86), thereby efficiently cooling the outer peripheral surface of the combustion liner 56 without increasing the flow rate of air guided from the combustor 18. Furthermore, even when the flow path width of the air flow path 78 is set relatively narrow, the flow velocity of the air decreases before it is guided to the inner space 86. Therefore, even if there is variation in component dimensions, the flow rate and incident angle of the air flowing into the combustion chamber 66 through the through-hole 64 are unlikely to change. This makes it possible to suppress variation in temperature distribution among the plurality of combustion chambers 66.

[0052] The through-holes 64 open radially inward of each of the plurality of combustion tubes 56 .

[0053] With this configuration, the combustion gas in the center of the combustion chamber 66 can be diluted in a balanced manner.

[0054] Each of the plurality of combustion liner 56 has two through holes 64. The two through holes 64 are arranged to face each other across the axis Ax2 of the combustion liner 56.

[0055] According to this configuration, the air flowing in from the two through holes 64 can collide with each other in the center of the combustion chamber 66, so that the combustion gas in the center of the combustion chamber 66 can be diluted in a balanced manner.

[0056] The combustor 18 has a plurality of communication pipes 58 that communicate the combustion chambers 66 of adjacent combustion tubes 56. The guide wall portion 62 includes a first wall portion 92 that extends from the plurality of communication pipes 58 toward the first end portion 18a, and a second wall portion 94 that extends from the plurality of communication pipes 58 toward the second end portion 18b.

[0057] With this configuration, the rigidity of the combustor 18 can be improved.

[0058] The outer circumferential cover portion 74 is formed so that outer circumferential recesses 80 recessed radially inward of the combustor 18 to fit between adjacent combustion tubes 56 and outer circumferential protrusions 82 protruding radially outward of the combustor 18 to fit along the outer circumferential surface of the combustion tubes 56 are alternately and continuously arranged in the circumferential direction of the combustor 18.

[0059] With this configuration, the flow path width of the air flow path 78 can be easily set to be narrow. This increases the flow velocity of the air flowing through the air flow path 78, thereby efficiently cooling the outer peripheral surface of the combustion liner 56. Furthermore, air flows into the combustion chamber 66 from the through-holes 64 via the inner space 86, thereby increasing the flow velocity of the air flowing through the inner space 86, thereby efficiently cooling the outer peripheral surface of the combustion liner 56.

[0060] The guide wall portion 62 protrudes in an arc shape radially inward or radially outward of the combustor 18 when viewed in the axial direction of the combustor 18 .

[0061] With this configuration, the thermal stress occurring at the boundary between the guide wall portion 62 and the combustion liner 56 can be effectively alleviated.

[0062] This embodiment discloses the following.

[0063] The above embodiment is a gas turbine (10) including a compressor (14), a combustor (18) having a plurality of combustion tubes (56) arranged in an annular shape, an air outlet (40) that introduces air supplied from the compressor to the combustor, an annular outer cover (74) that covers the combustor from the radially outer side of the combustor, an annular inner cover (21) that covers the combustor from the radially inner side of the combustor, and a plurality of fuel supply units (23) that supply fuel to upstream portions of combustion chambers (66) of the plurality of combustion tubes, wherein the combustor has a first end (18a) that is one end in an axial direction of the combustor and a second end (18b) that is the other end in the axial direction, an outlet (44) of the air outlet unit is located radially outward of the first end, and a fuel supply unit (23) that supplies fuel to upstream portions of combustion chambers (66) of the plurality of combustion tubes between the combustor and the outer cover unit. an air flow path (78) is formed through the combustor and the inner peripheral cover portion to allow the air to flow from the air flow path toward the second end, an inner space (86) is formed between the combustor and the inner peripheral cover portion, and the air flows in from the air flow path via a communication path (96) provided at the second end of the combustor; each of the plurality of combustion tubes is provided with an air inlet (68) located at the second end of the combustor to allow the air that has flowed through the air flow path to flow into the upstream part of the combustion chamber; the combustor has a guide wall portion (62) that is provided to connect adjacent combustion tubes in the plurality of combustion tubes and guides the air from the air flow path to the inner space through the communication path; and a through hole (64) that opens into the inner space and allows the air in the inner space to flow into the downstream side of the combustion chamber is formed in an outer peripheral surface of each of the plurality of combustion tubes.

[0064] In the above gas turbine, the through-hole may open radially inward of each of the plurality of combustion liner.

[0065] In the above gas turbine, two of the through holes may be formed in each of the plurality of combustion liner, and the two through holes may be arranged to face each other across the axis of each of the plurality of combustion liner.

[0066] In the above-described gas turbine, the combustor may have a plurality of communication pipes (58) that communicate the combustion chambers of the adjacent combustion tubes, and the guide wall portion may include a first wall portion (92) extending from the plurality of communication pipes toward the first end of the combustor, and a second wall portion (94) extending from the plurality of communication pipes toward the second end of the combustor.

[0067] In the above-described gas turbine, the outer circumferential cover portion may be formed so that outer circumferential recesses (80) recessed radially inward of the combustor to fit between adjacent combustion tubes and outer circumferential protrusions (82) protruding radially outward of the combustor to fit along outer circumferential surfaces of the plurality of combustion tubes are alternately and continuously arranged in a circumferential direction of the combustor.

[0068] In the above gas turbine, the guide wall portion may project in an arc shape radially inward or radially outward of the combustor when viewed in the axial direction.

[0069] The present invention is not limited to the above disclosure, and various configurations can be adopted without departing from the gist of the present invention. [Explanation of symbols]

[0070] 10...Gas turbine 14...Compressor 18... Combustor 20... Turbine 21...inner circumferential cover portion 23...fuel supply portion 25...Auxiliary component 40...Air outlet section 44...Outlet 56...Combustion tube 58...Communication pipe 62...Guiding wall section 64...Through hole 66...Combustion chamber 68...Air inlet 74...Outer periphery cover 78...Air flow path 80...Outer peripheral recess 82...Outer peripheral convex portion 86...Inner space 92...First wall part 94...Second wall part 96...Communication passage 98...Sensor 100…Ignition device

Claims

1. A compressor and a combustor having a plurality of combustion tubes arranged in an annular manner; an air outlet portion that outputs the air supplied from the compressor to the combustor; an annular outer circumferential cover portion that covers the combustor from the radially outer side of the combustor; an annular inner circumferential cover portion that covers the combustor from a radially inner side of the combustor; a plurality of fuel supply units that supply fuel to upstream portions of the combustion chambers of the plurality of combustion tubes; A gas turbine comprising: the combustor has a first end portion that is one end portion in an axial direction of the combustor and a second end portion that is the other end portion in the axial direction, an outlet port of the air outlet portion is located radially outward from the first end portion; an air flow path is formed between the combustor and the outer circumferential cover portion, through which the air introduced from the air outlet portion flows from the first end portion toward the second end portion; an inner space into which the air flows from the air flow path via a communication passage provided at the second end of the combustor is formed between the combustor and the inner circumferential cover portion; each of the plurality of combustion tubes is provided with an air inlet located at the second end of the combustor for allowing the air that has flowed through the air flow path to flow into the upstream portion of the combustion chamber; the combustor has a guide wall portion that is provided to connect adjacent combustion tubes among the plurality of combustion tubes and guides the air from the air flow path to the internal space through the communication passage, a through-hole that opens into the inner space and allows the air in the inner space to flow into the downstream side of the combustion chamber is formed on the outer peripheral surface of each of the plurality of combustion liner.

2. 2. The gas turbine of claim 1, the through-holes open radially inwardly of each of the plurality of combustion tubes.

3. 3. The gas turbine of claim 2, Two of the through holes are formed in each of the plurality of combustion tubes, a gas turbine, wherein the two through holes are arranged to face each other across the axes of the plurality of combustion tubes.

4. 2. The gas turbine of claim 1, the combustor has a plurality of communication pipes that communicate the combustion chambers of the adjacent combustion tubes, The guide wall portion is a first wall portion extending from the plurality of communication pipes toward the first end of the combustor; a second wall extending from the plurality of communication pipes toward the second end of the combustor.

5. 2. The gas turbine of claim 1, the outer circumferential cover portion is formed so that outer circumferential concave portions recessed radially inward of the combustor to fit between adjacent ones of the combustion tubes and outer circumferential convex portions protruding radially outward of the combustor to follow outer circumferential surfaces of the plurality of combustion tubes are alternately and continuously arranged in a circumferential direction of the combustor.

6. A gas turbine according to any one of claims 1 to 5, the guide wall portion projects in an arc shape radially inward or radially outward of the combustor when viewed in the axial direction.

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