JP2013040574A - Tail tube of combustor and gas turbine including the same - Google Patents

Abstract

PROBLEM TO BE SOLVED: To prevent cracks from growing while enhancing the cooling effect of a shell plate which forms a tail tube of combustor.SOLUTION: A plurality of cooling air flow passages 23 which extend in a direction along an axis line Ac are formed on the shell plate 21 and a cooling air entrance 24 open on the outer peripheral side of the shell plate and cooling air exits 25 open on the inner peripheral side of the shell plate are formed on each of the several cooling air flow passages. The cooling air exits of the several cooling air flow passages comprise several rows Ro and a plurality of cooling air exits 25 which comprise the rows Ro are aligned in a direction inclined to the axis line Ac. A mutual distance Dr of rows that are adjacent with each other among several rows Ro is larger than a mutual distance Do of the cooling air exits 25 that are adjacent with each other among the several cooling air exits that comprise the rows Ro.

Description

  The present invention relates to a transition piece of a combustor and a gas turbine including the same.

  The combustor of the gas turbine includes a tail tube that sends high-temperature and high-pressure combustion gas to the turbine. The body plate forming the tail tube has a structure for guiding the cooling air to the inner peripheral side in order to prevent the burnout. Specifically, a plurality of cooling air passages extending in a direction along the axis of the transition piece are formed in the body plate, and a cooling air inlet opening to the outer peripheral side of the body plate for each of the plurality of cooling air passages. And a cooling air outlet opening on the inner peripheral side of the body plate. The cooling air enters the cooling air passage from the cooling air inlet on the outer peripheral side of the transition piece and exits from the cooling air outlet to the inner peripheral side of the transition piece.

  In many cases, the cooling air outlets for the plurality of cooling air passages have substantially the same axial position of the transition piece. By the way, in recent years, in order to increase the thermal efficiency of the gas turbine, the temperature of the combustion gas flowing in the transition piece has been increased. For this reason, while increasing the quantity of the air cooling passages, the mutual space | interval of an air cooling passage is narrowed, and the cooling effect of a trunk plate is heightened. However, when the mutual spacing of the cooling air passages is narrowed in this way, as a result of the narrowing of the mutual spacing of the cooling air outlets, if a crack occurs starting from one cooling air outlet, the crack is easily connected to the adjacent cooling air outlet. This will encourage the growth of cracks.

  Therefore, in the following Patent Document 1, it is proposed to arrange the cooling air outlets for each of the plurality of cooling air passages in a staggered manner. As described above, when the cooling air outlets for each of the plurality of cooling air passages are arranged in a staggered manner, the positions of the adjacent cooling air outlets in the axial direction are different from each other even if the interval between the adjacent cooling air passages is narrowed. Therefore, a certain interval between adjacent cooling air outlets can be secured, and as a result, even if a crack occurs from one cooling air outlet, the growth of this crack can be suppressed to some extent.

JP 62-150543 A

  As described above, as the temperature of the combustion gas flowing in the transition piece increases more and more, it has been studied to further reduce the interval between the cooling air passages in order to further improve the cooling effect of the body plate. For this reason, even if the mutual space | interval of a cooling air path is narrowed further, the structure which can suppress the growth of a crack beyond the technique of patent document 1 is desired.

  Accordingly, the present invention provides a tail tube of a combustor capable of suppressing the growth of cracks and a gas turbine including the same, while enhancing the cooling effect of the body plate in order to meet such a demand. Objective.

A tail tube of a combustor according to the invention for achieving the above object is
In a tail cylinder of a combustor having a body plate formed in a cylindrical shape around an axis, in which high-temperature combustion gas flows on the inner peripheral side of the body plate and sends the combustion gas to a turbine, A plurality of cooling air passages extending in a direction along the axis, and a cooling air inlet of the cooling air passage opened to the outer peripheral side of the body plate and the cooling air passage for each of the plurality of cooling air passages; Cooling air outlets of the cooling air passages opened on the inner peripheral side of the body plate are formed, and the cooling air outlets for each of the plurality of cooling air passages form a plurality of rows, and The cooling air outlets are arranged in a direction inclined with respect to the axis, and the mutual interval between adjacent rows among the plurality of rows is the cooling air adjacent among the plurality of cooling air outlets constituting the row. It is characterized by being larger than the mutual interval of the outlets.

  Many of the cracks generated in the body plate are generated from a cooling air outlet where the thermal environment is severe and stress is concentrated. Moreover, this crack extends in a direction substantially perpendicular to the direction of the main stress. For this reason, when the main stress is generated in the direction in which the plurality of cooling air outlets constituting the row are arranged, that is, in the direction inclined with respect to the axis, cracks are generated from one cooling air outlet as a base point. Even if cracks are generated starting from another cooling air outlet adjacent to one cooling air outlet in the same row, it is possible to suppress both cracks from being connected in the tail tube.

  In the transition piece, the interval between adjacent cooling air outlets is larger than the interval between adjacent cooling air outlets in the column. For this reason, in the transition piece, a crack is generated starting from one cooling air outlet, and further, a crack is generated starting from another cooling air outlet in a row adjacent to the row including the one cooling air outlet. Even if it occurs, it is possible to suppress the connection of both cracks.

  Therefore, in the transition piece, a crack is generated from one cooling air outlet as a base point, and further, the crack is generated from another cooling air outlet adjacent to the one cooling air outlet in any direction. Even if this occurs, it is possible to suppress the connection of both cracks.

  That is, in the transition piece, even if the interval between the plurality of cooling air passages is narrowed in order to enhance the cooling effect of the body plate, the growth of cracks can be suppressed.

  Here, in the transition piece of the combustor, the right side of the combustion gas toward the downstream side in the upstream / downstream direction with reference to a virtual plane passing through the rotation axis of the turbine rotor and the axis of the turbine rotor It is preferable that the plurality of columns and the plurality of columns on the left side are all inclined to approach the virtual plane toward the downstream side.

  When high-temperature combustion gas flows through the cylindrically formed body plate, both sides of the body plate are set to the virtual plane as they go downstream. Main stress occurs in the direction of approach. For this reason, in the transition piece, all of the plurality of cooling air outlets constituting the rows of the portions on both sides are arranged in the direction along the main stress direction with reference to the virtual plane. Therefore, in the transition piece, it is possible to suppress the growth of cracks on both sides with respect to the virtual plane.

  Moreover, in the transition piece of the combustor, it is preferable that each of the plurality of rows is composed of three or more cooling air outlets.

  The interval between adjacent rows increases as the number of cooling air outlets constituting the row increases. For this reason, in the transition piece, a crack is generated starting from one cooling air outlet, and further, a crack is generated starting from another cooling air outlet in a row adjacent to the row including the one cooling air outlet. Even if it occurs, it is possible to further suppress the connection of both cracks.

  In the transition piece of the combustor, it is preferable that the row extending in a direction inclined with respect to the axis is formed on the downstream side including at least a central portion in the upstream and downstream direction of the combustion gas.

  The transition piece is generally getting smaller as its cross-sectional area goes downstream. For this reason, the flow velocity of the combustion gas in the transition piece gradually increases toward the downstream side. Therefore, the amount of heat input from the combustion gas is greater in the downstream portion than in the upstream portion of the transition piece. In the tail tube, in the downstream part where the amount of heat input from the combustion gas is relatively large, while suppressing the growth of cracks, the mutual spacing of the cooling air passages is narrowed to reduce the cooling effect of the part in the trunk plate. Can be increased.

  Here, in the transition piece of the combustor, the interval between the cooling air inlet and the cooling air outlet for each of the plurality of cooling air passages may be the same in the plurality of cooling air passages. In this case, the cooling air inlets for the plurality of cooling air passages are arranged in the same direction as the direction in which the row of cooling air outlets extends.

  Further, in the transition piece of the combustor, the row includes main stresses generated on the inner peripheral surface of the barrel plate when the combustion gas flows on the inner peripheral side of the barrel plate formed in a cylindrical shape. It is preferable to extend in a direction along the direction of.

  As described above, the crack extends in a direction substantially perpendicular to the direction of the main stress. For this reason, if the row extends in a direction along the direction of the main stress as in the case of the tail tube, a crack is generated starting from one cooling air outlet, and further, one cooling air in the same row. Even if a crack occurs starting from another cooling air outlet adjacent to the outlet, it is possible to suppress the connection of both cracks in the tail tube.

A gas turbine according to the invention for achieving the above object is as follows:
The combustor having the tail cylinder, a compressor for sending compressed air to the combustor, and the turbine driven by the combustion gas from the combustor.

  Since the gas turbine also has the transition piece, crack growth can be suppressed even if the interval between the plurality of cooling air passages is narrowed in order to enhance the cooling effect of the body plate forming the transition piece.

  In the present invention, a crack is generated starting from one cooling air outlet in the body plate forming the tail tube, and another cooling air that is adjacent to the one cooling air outlet regardless of the direction. Even if a crack occurs from the air outlet as a base point, it is possible to suppress the connection of both cracks.

  Therefore, according to the present invention, the growth of cracks can be suppressed even if the interval between the plurality of cooling air passages is narrowed in order to enhance the cooling effect of the body plate forming the tail tube.

It is a principal part notch perspective view of the transition piece in one Embodiment which concerns on this invention. It is a top view of a transition piece in one embodiment concerning the present invention. It is a principal part top view of the transition piece in one Embodiment which concerns on this invention. It is a principal part top view of the transition piece as a comparative example. It is a perspective view of a transition piece in one embodiment concerning the present invention. It is principal part sectional drawing of the gas turbine in one Embodiment which concerns on this invention. It is the whole side view which notched the principal part of the gas turbine in one Embodiment which concerns on this invention. It is a top view of a transition piece in the modification of one embodiment concerning the present invention. It is a top view of the transition piece in other modifications to one embodiment concerning the present invention.

  Hereinafter, an embodiment of a gas turbine according to the present invention will be described in detail with reference to FIGS.

  As shown in FIG. 7, the gas turbine according to the present embodiment generates a combustion gas by compressing outside air to generate compressed air and mixing the fuel from the fuel supply source with the compressed air and burning it. And a turbine 2 driven by combustion gas.

  The turbine 2 includes a casing 3 and a turbine rotor 4 that rotates within the casing 3. The turbine rotor 4 is connected to, for example, a generator (not shown) that generates electric power by the rotation of the turbine rotor 4. The plurality of combustors 10 are fixed to the casing 3 at equal intervals in the circumferential direction around the rotation axis Ar of the turbine rotor 4.

  As shown in FIG. 6, the combustor 10 includes a tail cylinder 20 that sends high-temperature and high-pressure combustion gas G to the turbine 2, and a fuel supplier 11 that supplies fuel and compressed air into the tail cylinder 20. ing. The fuel supplier 11 supplies pilot fuel X and compressed air A into the tail cylinder 20, and premixes the pilot burner 12 that forms a diffusion flame in the tail cylinder 20, the main fuel Y, and the compressed air A. And a plurality of nozzles 13 for supplying premixed gas into the tail cylinder 20 and forming a premixed flame in the tail cylinder 20.

  The tail cylinder 20 includes a trunk plate 21 formed in a cylindrical shape around the axis Ac, an upstream frame 27 attached to the upstream end of the trunk plate 21, and a downstream frame 28 attached to the downstream end of the trunk plate 21. A bypass pipe connection flange 29 for sending the compressed air A from the compressor 1 without passing through the fuel supplier 11 is provided upstream of the body plate 21.

  As shown in FIG. 5, the barrel plate 21 formed in a cylindrical shape has a circular cross section on the upstream side and a substantially rectangular cross section on the downstream side. Therefore, the upstream frame 27 has a circular shape, and the downstream frame 28 has a substantially rectangular shape. Further, the cross-sectional area of the cylindrical body plate 21 is gradually reduced from the upstream side toward the downstream side.

  The body plate 21 is formed such that a cross-sectional centroid perpendicular to a predetermined axis Ac is positioned on the axis Ac. In other words, the axis Ac is formed by connecting the cross-sectional centroids of the body plate 21 at each position in the upstream and downstream direction in which the combustion gas G flows. Moreover, in this embodiment, the cylindrical trunk | drum 21 is bilaterally symmetrical toward the downstream on the basis of the virtual plane P containing the axis line Ac of the tail cylinder 20, and the rotating axis Ar of the turbine rotor 4. FIG.

  As shown in FIG. 1, the body plate 21 is formed by bending a material obtained by joining two plates 21 o and 21 i. Of the two plates 21o, 21i constituting the body plate 21, a plurality of recesses are formed on the inner surface of the outer body plate 21o that forms the outer periphery side of the body plate 21, and extend in the direction along the axis Ac. The groove 22 is formed. An inner body plate 21i which is the other of the two plates 21o and 21i constituting the body plate 21 is joined to the inner peripheral surface of the outer body plate 21o. The opening of the groove 22 formed in the outer body plate 21 o is closed by the inner body plate 21 i to form a cooling air passage 23.

  In the body plate 21, for each of the plurality of cooling air passages 23, the cooling air inlet 24 of the cooling air passage 23 opened on the outer peripheral side of the body plate 21 and the cooling of the cooling air passage 23 opened on the inner peripheral side of the body plate 21 are provided. An air outlet 25 is formed. The cooling air outlets 25 for each of the plurality of cooling air passages 23 form a plurality of rows Ro, and the plurality of cooling air outlets 25 constituting the row Ro are arranged in a direction inclined with respect to the axis Ac. One row Ro is composed of three cooling air outlets 25 in this embodiment.

  The mutual distance Dio between the cooling air inlet 24 and the cooling air outlet 25 that form a pair for each of the plurality of cooling air passages 23 is substantially the same between the plurality of cooling air passages 23 as shown in FIG. Therefore, the cooling air inlets 24 for each of the plurality of cooling air passages 23 also form a plurality of rows Ri, like the cooling air outlet 25, and the plurality of cooling air inlets 24 constituting the row Ri are arranged in a row of the cooling air outlets 25. It is lined up in the direction in which Ro extends.

  As shown in FIGS. 2 and 5, each of the plurality of cooling air outlets 25 forming the row Ro is an upper body portion of the body plate 21 on the side far from the turbine rotor 4, and the combustion gas G It is formed in the downstream side part including the center part of the upstream / downstream direction. Therefore, the cooling air inlet 24 that forms a pair with the cooling air outlet 25 is also an upper trunk portion of the trunk plate 21 that is far from the turbine rotor 4 and includes a central portion in the upstream and downstream direction of the combustion gas G. It is formed on the side.

  The row Ri of the cooling air inlet 24 and the row Ro of the cooling air outlet 25 formed on both sides with respect to the virtual plane P including the axis Ac of the tail cylinder 20 and the rotation axis Ar of the turbine rotor 4 are both. Inclining toward the virtual plane P toward the downstream side. That is, with respect to the virtual plane P, the row Ri of the cooling air inlet 24 and the row Ro of the cooling air outlet 25 that are formed on the left side toward the downstream side are both on the right side toward the downstream side. The row Ri of the cooling air inlet 24 and the row Ro of the cooling air outlet 25 formed on the right side toward the downstream side are both inclined toward the left side as they go downstream. doing.

  As shown in FIG. 3, the mutual spacing Dr of the adjacent rows Ro among the plurality of rows Ro of the cooling air outlets 25 is equal to that of the adjacent cooling air outlets 25 among the plurality of cooling air outlets 25 constituting the row Ro. It is larger than the mutual interval Do.

  As shown in FIG. 6, most of the compressed air A from the compressor 1 is sent into the fuel supplier 11 of the combustor 10 and is injected into the tail cylinder 20 together with the fuel from the fuel supplier 11. In the transition piece 20, the fuel is combusted and a high-temperature combustion gas G is generated. This high-temperature combustion gas G flows into the turbine 2 from the tail cylinder 20 and rotates the turbine rotor 4.

  Further, in the transition piece 20, a part of the compressed air A from the compressor 1 serves as cooling air. It flows through. For this reason, the inner peripheral surface of the transition piece 20 is protected from the high-temperature combustion gas G by this cooling air. In the above description, the cooling air inlet 24 and the cooling air outlet 25 are described as being formed only on the downstream side portion of the upper body portion of the body plate 21. 21 is formed in each part.

  As shown in FIG. 2, when the combustion gas G flows on the inner peripheral side of the upper peripheral portion of the upper body portion of the trunk plate 21, the combustion gas G approaches the virtual plane P toward the downstream side. The principal stress σ in the direction is generated. In the present embodiment, the plurality of cooling air outlets 25 constituting the row Ro are arranged in a direction along the direction of the main stress σ, in other words, the row Ro of the cooling air outlet 25 has the main stress σ. It extends in a direction along the direction.

  As shown in FIG. 3, most of the cracks C generated in the body plate 21 are generated from a cooling air outlet 25 where the thermal environment is severe and stress is concentrated. Further, the crack C extends in a direction substantially perpendicular to the direction of the main stress σ.

  For this reason, when the plurality of cooling air outlets 25 constituting the row Ro are arranged in the direction along the direction of the main stress σ as in the present embodiment, the crack Ca is based on the one cooling air outlet 25a. In addition, even if a crack Cb is generated starting from another cooling air outlet 25b adjacent to one cooling air outlet 25a in the same row Ro, it is possible to suppress the connection of both cracks Ca and Cb. Can do.

  Further, in the present embodiment, as described above, the mutual interval Dr of the adjacent rows Ro of the cooling air outlets 25 is larger than the mutual interval Do of the adjacent cooling air outlets 25 in the row Ro. For this reason, a crack Ca is generated starting from one cooling air outlet 25a, and a crack Cc is starting from another cooling air outlet 25c in the row Ro adjacent to the row Ro including the one cooling air outlet 25a. Even if it generate | occur | produces, it can suppress that both cracks Ca and Cc are connected.

  By the way, in the technique described in Patent Document 1 described in the “Background Art” column, the cooling air outlets 35 for each of the plurality of cooling air passages 33 are arranged in a staggered manner as shown in FIG. Temporarily, one cooling air outlet 35a and the other cooling air outlet 35b adjacent on one side to the one cooling air outlet 35a are arranged in a direction along the direction of the main stress σ. And In this case, similarly to the above-described embodiment, even if a crack Ca is generated from one cooling air outlet 35a and a crack Cb is generated from the other cooling air outlet 35b, both cracks are generated. Ca and Cb can be prevented from being connected.

  However, in this case, the one cooling air outlet 35a and the other cooling air outlet 35c adjacent to the one cooling air outlet 35a on the other side are substantially perpendicular to the direction of the main stress σ. Furthermore, since the mutual distance Dd between the cooling air outlets 35a and 35c is relatively short, a crack Ca is generated from one cooling air outlet 35a, and a crack is generated from the other cooling air outlet 35c. When Cc is generated, there is a very high possibility that both cracks Ca and Cc are connected.

  That is, the technique described in Patent Document 1 may not be able to suppress the growth of cracks C.

  On the other hand, in the present embodiment, a crack Ca is generated starting from one cooling air outlet 25a, and another cooling air outlet 25b adjacent to this one cooling air outlet 25a regardless of the direction. , 25c, even if cracks Cb and Cc are generated, it is possible to prevent the two cracks Ca, Cb, Ca and Cc from being connected as described above. That is, in this embodiment, even if the mutual space | interval of the some cooling air channel | path 23 is narrowed, the growth of the crack C can be suppressed rather than the technique of patent document 1. FIG.

  In the above embodiment, as shown in FIG. 2, the plurality of rows Ri of the cooling air inlet 24 and the plurality of rows Ro of the cooling air outlet 25 are arranged in a direction V perpendicular to the virtual plane P of the tail cylinder 20. However, the present invention is not limited to this. For example, as shown in FIGS. 8 and 9, a plurality of rows Ri of the cooling air inlet 24 and a plurality of rows Ro of the cooling air outlet 25 are connected to the tail cylinder. You may arrange in the direction V inclined with respect to 20 axis line Ac.

  Further, in the above embodiment, the mutual interval Dio between the cooling air inlet 24 and the cooling air outlet 25 that form a pair for each cooling air passage 23 is substantially the same among the plurality of cooling air passages 23. The cooling air passages 23 need not be the same.

  Further, in the above embodiment, the row Ro of the cooling air outlets 25 is configured by the three cooling air outlets 25. However, as the number of the cooling air outlets 25 constituting the row Ro increases, the adjacent rows Ro become closer to each other. Since the interval Dr increases and the growth of the crack C can be further suppressed, the row Ro of the cooling air outlets 25 may be configured by four or more cooling air outlets 25.

  1: compressor, 2: turbine, 4: turbine rotor, 10: combustor, 20: tail cylinder, 21: body plate, 23: cooling air passage, 24: cooling air inlet, 25: cooling air outlet, Ac: tail Axis of cylinder, Ar: Rotation axis of turbine rotor, Ri: Row of cooling air inlet, Ro: Row of cooling air outlet

A tail tube of a combustor according to the invention for achieving the above object is
In a tail cylinder of a combustor having a body plate formed in a cylindrical shape around an axis, in which high-temperature combustion gas flows on the inner peripheral side of the body plate and sends the combustion gas to a turbine, A plurality of cooling air passages extending in a direction along the axis, and a cooling air inlet of the cooling air passage opened to the outer peripheral side of the body plate and the cooling air passage for each of the plurality of cooling air passages; Cooling air outlets of the cooling air passages opened on the inner peripheral side of the body plate are formed, and the cooling air outlets for each of the plurality of cooling air passages form a plurality of rows, and The cooling air outlets are arranged in a direction inclined with respect to the axis, and the mutual interval between adjacent rows among the plurality of rows is the cooling air adjacent among the plurality of cooling air outlets constituting the row. greater than the mutual spacing of the outlet, said column inner circumference of the cylinder plate formed in a cylindrical shape To when the combustion gas is flowing, characterized in that it extends in a direction along the direction of the main stress generated in the inner peripheral surface of the barrel plate.
Moreover, the transition piece of another combustor according to the invention for achieving the above object is
In a tail cylinder of a combustor having a body plate formed in a cylindrical shape around an axis, in which high-temperature combustion gas flows on the inner peripheral side of the body plate and sends the combustion gas to a turbine, A plurality of cooling air passages extending in a direction along the axis, and a cooling air inlet of the cooling air passage opened to the outer peripheral side of the body plate and the cooling air passage for each of the plurality of cooling air passages; Cooling air outlets of the cooling air passages opened on the inner peripheral side of the body plate are formed, and the cooling air outlets for each of the plurality of cooling air passages form a plurality of rows, and The cooling air outlets are arranged in a direction inclined with respect to the axis, and the mutual interval between adjacent rows among the plurality of rows is the cooling air adjacent among the plurality of cooling air outlets constituting the row. The row is larger than the mutual interval of the outlets, and the row is an inner circumference of the barrel plate formed in a cylindrical shape. To when the combustion gas is flowing, characterized in that it extends in a direction along the direction of the main stress generated in the inner peripheral surface of the barrel plate.

Many of the cracks generated in the body plate are generated from a cooling air outlet where the thermal environment is severe and stress is concentrated. Moreover, this crack extends in a direction substantially perpendicular to the direction of the main stress.
In addition, when high-temperature combustion gas flows in the cylindrically formed body plate, both sides of the body plate are virtually virtual toward the downstream side with respect to the virtual plane. A principal stress is generated in the direction approaching the plane. For this reason, in the transition piece, all of the plurality of cooling air outlets constituting the rows of the portions on both sides are arranged in the direction along the main stress direction with reference to the virtual plane. For this reason, even if a crack occurs from one cooling air outlet as a base point, and a crack occurs from another cooling air outlet adjacent to one cooling air outlet in the same row, the tail In a cylinder, it can suppress that both cracks connect.

Claims (7)

In a tail cylinder of a combustor having a body plate formed in a cylindrical shape around an axis, a high-temperature combustion gas flows on the inner peripheral side of the body plate, and sends the combustion gas to a turbine,
The body plate is formed with a plurality of cooling air passages extending in a direction along the axis, and the cooling air passages opened to the outer peripheral side of the body plate are provided for the plurality of cooling air passages. A cooling air inlet and a cooling air outlet of the cooling air passage opened to the inner peripheral side of the body plate are formed;
The cooling air outlets for each of the plurality of cooling air passages form a plurality of rows, and the plurality of cooling air outlets constituting the rows are arranged in a direction inclined with respect to the axis,
An interval between adjacent rows among the plurality of rows is greater than an interval between adjacent cooling air outlets among the plurality of cooling air outlets constituting the row.
Combustor tail tube characterized by that. In the transition piece of the combustor according to claim 1,
The plurality of columns on the right side and the plurality of the left side toward the downstream side in the upstream / downstream direction of the combustion gas with reference to a virtual plane passing through the rotation axis of the turbine rotor and the axis of the turbine Each of the columns is inclined to approach the virtual plane as it goes downstream.
Combustor tail tube characterized by that. In the transition piece of the combustor according to claim 1 or 2,
Each of the plurality of rows is composed of three or more cooling air outlets.
Combustor tail tube characterized by that. In the combustor of the combustor according to any one of claims 1 to 3,
The row extending in a direction inclined with respect to the axis is formed on the downstream side including at least a central portion in the upstream / downstream direction of the combustion gas,
Combustor tail tube characterized by that. In the combustor of the combustor according to any one of claims 1 to 4,
The interval between the cooling air inlet and the cooling air outlet for each of the plurality of cooling air passages is the same in the plurality of cooling air passages.
Combustor tail tube characterized by that. In the combustor of the combustor according to claim 1,
The row extends in a direction along a direction of main stress generated on the inner peripheral surface of the barrel plate when the combustion gas flows on the inner peripheral side of the barrel plate formed in a cylindrical shape. ,
Combustor tail tube characterized by that. The combustor having the transition piece according to any one of claims 1 to 6,
A compressor for sending compressed air to the combustor;
The turbine driven by the combustion gas from the combustor;
A gas turbine comprising:

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