Combustion chamber tube, combustion chamber and gas turbine

Abstract

A combustion chamber tube having an inlet (331) and an outlet (330), the combustion chamber tube comprising: an inner tube (60), an interior of which is a flow path (64) for passing a combustion gas (G), wherein a first cooling flow path (74) through which a coolant (S) can flow is formed in a wall (70) forming the flow path (64), and an outer tube (62; 62a; 62b; 62c; 62e) provided on an outer periphery of the inner tube (60) and fixed to the inner tube (60), wherein a second cooling flow path (80) through which the coolant (S) can flow and which is connected to the first cooling flow path (74) is provided on a side of the outlet (330) of the combustion chamber tube between an outer peripheral surface of the inner tube (60) and an inner peripheral surface of the outer tube (62;62a;62b;62c;62e) is formed so that the coolant (S) that has flowed through the first cooling flow path (74) flows into the second cooling flow path (80), and the second cooling flow path (80) and a cooling-promoting structure (82; 82b; 82c; 82d; 82e) are formed in the outer tube (62; 62a; 62b; 62c; 62e), wherein the cooling-promoting structure (82; 82b; 82c; 82d; 82e) is formed between the second cooling flow path (80) and the first cooling flow path (74);

Description

The present invention relates to a combustor can and a combustor used in a gas turbine, and a gas turbine provided with the combustor.A gas turbine combustor generates high temperature combustion gas during operation of the gas turbine and is heated by the combustion gas as the generated combustion gas flows therethrough. Therefore, the combustion chamber distributes a gas such as air or steam as a coolant to cool each part, and thus suppresses a temperature rise. A known gas turbine combustor among this type of gas turbine combustor includes a combustor that cools a combustor tube (transition piece, combustion liner) of the combustor by means of a coolant (for example, Patent Document 1). The gas turbine disclosed in JP 2006-105 076 A sprays cooling air from a downstream end part of a transition piece toward a guide vane shroud that supports a guide vane.From DE 11 2015 005 425 T5, which is not prepublished, a combustion chamber of a gas turbine and a transition piece or combustion chamber tube therefor are known, which has a cylindrical shape and which has an inlet for combustion gas at one end and an outlet for the combustion gas at another end. A cooling medium introduction unit having a cooling medium inlet is provided at at least a portion of an outer circumferential portion in a circumferential direction on an outlet side of the transition piece. A cooling portion is provided at a portion that extends from the outlet of the transition piece to a predetermined position to the inlet and that is connected to the cooling medium introduction unit so that the cooling medium passes therefrom from the outlet to the inlet. A branch portion is formed in a predetermined region in the circumferential direction of the transition piece including a portion farthest from the cooling medium inlet so that a part of the cooling medium inside the cooling medium introduction unit can flow into the cooling portion.EP 2 623 744 A1 and US 2011 / 0 247 341 A1 disclose further combustion chambers for gas turbines and transition pieces or combustion pipes therefor, which have cooling flow paths formed in wall parts of the combustion pipe for introducing a coolant from the outside and for cooling the combustion pipe.The apparatus disclosed in JP 2006-105 076 A sprays cooling air from a transition piece toward a vane shroud to prevent entry of combustion gas between the transition piece and the vane shroud. Although the gas turbine disclosed in JP 2006-105 076 A can prevent burning of a clearance part between the transition piece and the vane shroud, this causes the cooling air to be sprayed into a combustion gas flow path. Therefore, the efficiency of the gas turbine (amount of energy that can be generated by combustion of a predetermined amount of fuel) decreases.An object of the present invention is to provide a combustor can efficiently cool a part of the combustor can where a temperature rises without spraying cooling air and enhance reliability without lowering the efficiency of the gas turbine, and a combustor and a gas turbine provided with this combustor.The present invention relates to a combustion chamber pipe having the features of claim 1 or 2.Further, the cooling promoting structure preferably has an uneven shape, and a distance from the inner pipe changes in a position-based manner.In addition, preferably, at least a part of protruding parts of the uneven shape of the cooling promoting structure is in contact with the inner pipe.In addition, preferably, the cooling promoting structure is a plurality of through holes through which the coolant flows.According to the invention of claim 2, the cooling promoting structure is formed on a side of the outer pipe that is located further on a rotation axis side of the gas turbine than the inner pipe.In addition, an end part on the outlet side is preferably configured to be connected to a guide blade shroud in which a guide blade is provided.According to the invention of claim 2, the cooling promoting structure is formed at least at one location within a range including a position intersecting an end part on an upstream side of the vane in a rotation direction of a gas turbine rotor.In addition, preferably, an end part on the outlet side is connected to a vane shroud in which a vane is provided, and the cooling promoting structure is provided in a range of 1 / 3P or more and 3P or less, where P corresponds to a pitch of the vanes in a rotation direction of a gas turbine rotor.In addition, it is preferable that an end part on the outlet side is joined to a vane shroud in which a vane is provided; the inner tube has a flange part extending toward the outer tube in an end part on the vane shroud side; and the combustor tube is provided with a welding part, on which an end part on the vane shroud side of the outer tube is joined to an end part of the flange part by welding.In addition, preferably, the welding part connects a surface of the flange part on a side opposite to the vane shroud side to the outer tube.The present invention also relates to a combustion chamber comprising the combustion chamber tube according to the invention.The present invention also relates to a gas turbine comprising a compressor, the above combustor for burning fuel and air compressed by the compressor to generate combustion gas, and a turbine driven by the combustion gas supplied from the combustor.The present invention can efficiently cool a part of a combustor can in which a temperature rises, and thus further enhance the reliability of the combustor can without lowering the efficiency of a gas turbine. FIG. 1 is a schematic configuration diagram of a gas turbine including a combustor according to the present embodiment. FIG. 2 is an enlarged view of the combustion chamber. FIG. 3 is a schematic view illustrating a relationship between a transition piece of the combustor and first stage vanes. FIG. 4 is a perspective view illustrating a part of the transition piece of the combustor. FIG. 5 is a perspective view illustrating a structure of an outlet of the transition piece of the combustor. FIG. 6 is a drawing for describing the transition piece of the combustor as viewed from an exhaust side. FIG. 7 is a cross-sectional view of the transition piece of the combustor and a vane shroud. FIG. 8 is a cross-sectional view taken along A-A in FIG. 7. FIG. 9 is a perspective view illustrating a schematic configuration of a cooling promoting structure. FIG. 10 is a schematic view illustrating another example of the relationship between the transition piece of the combustor and the first stage vanes. FIG. 11 is a cross-sectional view illustrating another example of the transition piece. FIG. 12 is a perspective view illustrating a schematic configuration of another example of the cooling promoting structure. FIG. 13 is a perspective view illustrating a schematic configuration of another example of the cooling promoting structure. FIG. 14 is a cross-sectional view illustrating another example of the transition piece. FIG. 15 is a cross-sectional view taken along B-B in FIG. 14. FIG. 16 is a cross-sectional view illustrating another example of the transition piece. FIG. 17 is a cross-sectional view taken along C-C in FIG. 16. FIG. 18 is a perspective view illustrating a schematic configuration of the cooling promoting structure illustrated in FIG. 16.Preferred embodiments of the present invention will be described with reference to the drawings.FIG. 1 is a schematic configuration view of a gas turbine including a combustor according to the present embodiment. As illustrated in FIG. 1, a gas turbine 1 includes, in order from an upstream side in a direction in which a fluid flows, a compressor 11, a gas turbine combustor (hereinafter referred to as a combustor) 12, a turbine 13, and an exhaust chamber 14. For example, a generator is connected to the turbine 13. The gas turbine includes a rotor (turbine shaft) 24 that can rotate about a rotational center axis L.The compressor 11 includes a compressor housing 16 connected to an air inlet port for receiving air and provided with a flow path in which air flows. The compressor 11 is provided with a plurality of vanes 17 and blades 18 alternately arranged in the air flow path in the compressor housing 16. The combustor 12 supplies fuel to compressed air (combustion air) compressed by the compressor 11 and generates combustion gas by combustion of an air-fuel mixture of the fuel and the combustion air. The turbine 13 has a turbine housing 20 provided with a flow path into which the combustion gas generated in the combustion chamber 12 flows. In the turbine 13, a plurality of vanes 21 and blades 22 are alternately arranged, which face inside the combustion gas flow path of the turbine casing 20 from upstream to downstream in a direction in which the combustion gas flows as a fluid. The vane 21 is supported in a vane shroud 50 which is part of the turbine casing 20. A clearance through which the combustion gas flows is formed inside the vane shroud 50. The vane shroud 50 fixes the vane 21 in the clearance through which the combustion gas flows. Further, the combustor 12 is connected to the vane shroud 50.The exhaust chamber 14 includes an exhaust diffuser 23 into which the combustion gas that has passed through the turbine 13 flows. The rotor 24 is disposed so as to penetrate center parts in a radial direction of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 14. An end part on the compressor 11 side of the rotor 24 is rotatably supported by a bearing part 25 centrally on the rotation center axis L, and an end part on the exhaust chamber 14 side thereof is rotatably supported by a bearing part 26 centrally on the rotation center axis L. A plurality of disk plates are secured to the rotor 24, and each of the blades 18 and 22 is connected thereto.In this type of gas turbine 1, the air taken in from the air inlet port 15 of the compressor 11 flows through the plurality of vanes 17 and blades 18, and is thereby compressed to become high-temperature, high-pressure compressed air. A predetermined fuel is supplied to the compressed air in the combustor 12, and thereby the compressed air becomes an air-fuel mixture with the fuel. The air-fuel mixture is burned in the combustion chamber 12 and thereby becomes combustion gas. A high-temperature, high-pressure combustion gas, which is an operating fluid generated in the combustion chamber 12, flows through the plurality of vanes 21 and blades 22 provided in the turbine 13, and rotates the rotor 24. Exhaust gas that has passed through the rotor 24 is discharged to the atmosphere as exhaust gas.FIG. 2 is an enlarged view of the combustion chamber. The combustion chamber 12 has a combustion chamber housing 30. The combustor casing 30 includes a combustor basket 32 provided inside an outer cylinder 31, and a transition piece 33 connected to a tip part of the combustor basket 32 and extends along a central axis La inclined with respect to the rotational central axis L. Here, in the gas turbine 1, a clearance between a shell casing 27 and the combustor casing 30 forms a combustor compressor casing 34, and the compressed air compressed in the compressor 11 is extracted into the combustor compressor casing. The compressed air drawn off into the combustion chamber compressor housing 34 flows into the combustion chamber basket 32 of the combustion chamber 12.The outer cylinder 31 is fixed to the shell case 27. A proximal end portion of the combustor basket 32 is supported by the outer cylinder 31, and the combustor basket 32 is disposed inside the outer cylinder 31 with a gap between it and the outer cylinder 31. An ignition nozzle 40 is provided along the central axis La in a central part of the combustor basket 32. A plurality of main nozzles 42 are uniformly spaced and provided in parallel to the ignition nozzle 40 at the periphery of the ignition nozzle 40 so as to surround the ignition nozzle 40.A proximal end of the transition piece 33 is formed into a cylindrical shape and connected to a tip of the combustor basket 32. The transition piece 33 is formed such that a cross-sectional area becomes smaller toward a tip side and the piece bulges, and is open to a first stage of the vanes 21 of the turbine 13. A distal end of the transition piece 33 is connected to the vane shroud 50. In the transition piece 33, an end part (proximal end) on the combustor basket 32 side forms an inlet 33I, and an end part (distal end) connected to the vane shroud 50 forms an outlet 33O. The transition piece 33 has a combustion chamber therein. In the combustor 12, the outer cylinder 31, the combustor basket 32, and the transition piece 33 form a combustor can. Further, in the combustor 12, the transition piece 33 forms a combustor can that is connected to the vane shroud 50.The transition piece 33 will be described below using FIGS. 3 to 9 in addition to FIG. 2. FIG. 3 is a schematic view illustrating a relationship between the transition piece of the combustor and first stage vanes. FIG. 4 is a perspective view illustrating a part of the transition piece of the combustor. FIG. 5 is a perspective view illustrating a structure of an outlet of the transition piece of the combustor. FIG. 6 is a drawing for describing the transition piece of the combustor as viewed from an exhaust side. FIG. 7 is a cross-sectional view of the transition piece of the combustor and the vane shroud. FIG. 8 is a cross-sectional view taken along A-A in FIG. 7, FIG. 9 is a perspective view illustrating a schematic configuration of a cooling promoting structure.The transition piece 33 is a cylindrical member, and as described above, one end of a cylindrical inner space thereof forms the inlet 33I for a combustion gas G, and the other end forms the outlet 33O for the combustion gas G. In the transition piece 33, the end part on the outlet 33O side is connected to the vane shroud 50. Further, the guide vane (first stage guide vane) 21 is provided on a downstream side of the outlet 33O of the transition piece 33 in the direction in which the combustion gas G flows. In the transition piece 33, the combustion gas G that has flowed in from the inlet 33I flows out of the outlet 33O and is guided to the turbine 13 illustrated in FIG. 1. The combustion gas G that has flowed out of the outlet 33O of the transition piece 33 flows between the vanes 21, Here, in the present embodiment, the pitch at which the vanes 21 are provided in the rotational direction is referred to as the pitch P. A region W will be described later. Further, an arrangement pitch of the transition pieces 33 is referred to as a pitch Wa. In the present embodiment, two of the vanes 21 are provided with respect to each transition piece 33, and the positions of the vanes 21 are the same with respect to each transition piece 33. In other words, in the gas turbine according to the present embodiment, the distance Wa between the transition pieces 33 corresponds to the pitch P of two of the vanes 21, thereby establishing the relationship Wa=2P.As illustrated in FIGS. 4 and 5, the transition piece 33 includes an inner tube 60 and an outer tube 62. The inner tube 60 and the outer tube 62 are joined by welding. The inner pipe 60 has a cylindrical shape, and thus is a cylindrical member, a space inside the cylinder of which forms a combustion gas flow path 64, through which combustion gas flows. The inner tube 60 has a shape in which a cross section of the tube has a deformed trapezoidal shape, and sides of the inner tube 60 extending along the rotation direction (rotation direction of the rotor 24) form arcs. The inner tube 60 is formed so that the width in the rotational direction becomes narrower toward the rotational center axis L.The outer tube 62 is provided on an outer periphery of the inner tube 60 and covers a part of the outer periphery of the inner tube 60. as illustrated in FIGS. 5 and 6, the outer tube 62 has four segments 66 a, 66 b, 66 c, and 66 d. The segment 66 afaces a surface on the rotation axis center side of the inner tube 60. In other words, the segment 66 ais provided further toward the rotation axis center than the inner pipe 60. the segment 66 bfaces an outer surface in the rotation axis direction of the inner pipe 60. In other words, the segment 66 bis disposed at a position farther from a rotation axis than the inner tube 60. The segments 66c and 66d respectively face two surfaces forming end surfaces in the rotational direction of the inner tube 60. An end part of the segment 66 ain the rotational direction is fixed to the segment 66 c, for example, by welding. An end part of the segment 66 bin the rotational direction is also fixed to the segment 66 c, for example, by welding. Further, the segments 66 a, 66 b, 66 c, and 66 dare fixed to the inner pipe 60 by welding, for example. In this manner, the outer tube 62 covers the entire outer periphery of the inner tube 60 via the segments 66 a, 66 b, 66 c, and 66 d. The outer tube 62 forms a single cylindrical shape from the segments 66 a, 66 b, 66 c, and 66 d.As illustrated in FIG. 7, the inner tube 60 includes an inner wall part 70 and a flange part (end part) 72 provided on an end surface on the vane shroud 50 side. The inner wall part 70 is the part configuring the cylinder of the inner pipe, and a region surrounded by the inner wall part 70 forms the combustion gas flow path 64. A clearance between the flange part 72 and the vane shroud 50 is a gap 58.A plurality of first cooling flow paths 74 are formed inside the inner wall part 70, in other words, inside the wall surrounding the combustion gas flow path 64. The plurality of first cooling flow paths 74 are formed in a wall extension direction and are aligned in a direction perpendicular to the direction in which the combustion gas flows. The first cooling flow path 74 is formed by connecting a flow path extending in the direction in which the combustion gas G flows, in other words, extending from the inlet 33I toward the outlet 33O, and a flow path extending in a direction separating from the combustion gas flow path 64 along the flange part 72 at an end on the outlet 33O side. Note that the first cooling flow path 74 may have a shape in which the flow path running in the direction separating from the combustion gas flow path 64 along the flange part 72 at the outlet 33O side end is connected to the same parts of the other first cooling flow paths 74. In other words, the flow path that extends in the direction separating from the combustion gas flow path 64 along the flange part 72 at the outlet 33O side end of the first cooling flow path 74 may be a flow path common to the plurality of first cooling flow paths 74.Next, as described above, the outer pipe 62 is a cylinder surrounding an outer circumferential surface of the inner pipe 60, in other words, a surface on an opposite side of an inner circumferential surface forming the combustion gas flow path 64. The outer tube 62 is fixed to the inner tube 60 by welding, for example. In the outer tube 62, a fixing part 78 is formed on a surface on an opposite side to the inner tube 60. The attachment part 78 is connected to the guide blade shroud 50.In the transition piece 33, a second cooling flow path 80 is formed between the inner tube 60 and the outer tube 62. The second cooling flow path 80 is a clearance between surfaces of the inner tube 60 and the outer tube 62 facing each other, in other words, a clearance between a surface on the outer peripheral side of the inner tube 60 and a surface on the inner peripheral side of the outer tube 62.As illustrated in FIGS. 7 to 9, in the outer tube 62, a cooling promoting structure 82 is formed in the second cooling flow path 80, in other words, in a surface facing the inner tube 60. The cooling promoting structure 82 is provided in the vicinity of a part of the second cooling flow path 80 connected to the first cooling flow path 74. Specifically, the cooling promoting structure 82 is provided in the vicinity of the flange part 72. The cooling promoting structure 82 according to the present embodiment is provided only on segment 66 aof the four segments 66 a, 66 b, 66 c, and 66 dwhich is located on an inner side in the rotation axis direction. Further, the cooling promoting structure 82 according to the present embodiment is provided on a part, in particular, in the region W, of the second cooling flow path 80 of the segment 66 ain the rotational direction. The region W is a region including the center point in the rotation direction of the outer tube 62.As illustrated in FIG. 8 in a cross section in which the cooling promoting structure 82 is provided, the transition piece 33 includes a clearance 90 which is a part in which the cooling promoting structure 82 is not provided and a space 92 which is a part in which the cooling promoting structure 82 is provided. In the clearance 90, end surfaces of the inner tube 60 and the outer tube 62 are substantially parallel, and a width between the inner tube 60 and the outer tube 62 is substantially constant even in a case where a position shifts in the rotational direction. On the other hand, as illustrated in FIGS. 7 to 9, the cooling promoting structure 82 is an uneven shape formed in a surface of the outer tube 62. Specifically, a plurality of protruding parts 84 are provided at predetermined intervals in the rotation direction. In the protruding part 84, a tip of a protrusion is in contact with the inner tube 60. In other words, in the transition piece 33, the clearance 92 is divided into a plurality of parts in the rotational direction. Further, in the transition piece 33, a surface of the outer tube 62 in the part where the clearance 92 of the cooling promoting structure 82 is formed is separated further from the inner tube 60 than in the clearance 90.In the transition piece 33, a coolant S supplied from a mechanism for supplying the coolant flows in the flow path of the first cooling flow path 74 extending from the inlet 33I toward the outlet 33O in the same direction as the combustion gas G. The coolant S having passed through the flow path of the first cooling flow path 74 extending from the inlet 33I toward the outlet 33O flows through the flow path extending along the flange part 72 in the direction separating from the combustion gas flow path 64, then this coolant flows through the second cooling flow path 80, When flowing into the second cooling flow path 80, this coolant flows through the cooling promoting structure 82, and then further flows to a downstream side in a flow direction.By providing the cooling promoting structure 82 in the transition piece 33, a surface area of the part of the outer pipe 62 of the part that comes into contact with the coolant S in the part in which the cooling promoting structure 82 is provided can be made larger than when the surface of the outer pipe 62 is made flat. Therefore, the cooling performance can be enhanced in the transition piece 33 in the vicinity of the flange part 72 where the gap 58 into which the combustion gas G flows is generated, thus making it possible to suppress a temperature rise at the end part of the flange part 72. Further, the coolant S flowing through the first cooling flow path 74 and the second cooling flow path 80 formed in the transition piece 33 flows inside the wall of the transition piece 33, and does not flow into a combustion gas flow path. Therefore, the cooling performance can be enhanced without the coolant S flowing into the combustion gas flow path 64. Therefore, the coolant S mixed with the combustion gas G can be reduced and a drop in the temperature of the combustion gas G upstream can be prevented, thereby making it possible to obtain more energy from the gas turbine, thereby making it possible to suppress a reduction in the efficiency of the gas turbine. Further, by providing the cooling promoting structure 82 in the transition piece 33 in a part where cooling is required, it is possible to increase the cooling performance in the part while maintaining a flow rate of the entire coolant supplied to the transition piece 33. Increasing the cooling performance while suppressing an increase in the flow rate of the coolant in this manner makes it possible to reduce the energy used to generate the coolant, thus making it possible to suppress a decrease in the efficiency of the gas turbine.Here, the cooling promoting structure 82 is preferably provided in the transition piece 33 in a region including a position intersecting an end part on the upstream side of the vane 21 in the rotation direction, as in the present embodiment. Therefore, it becomes possible to suppress a temperature rise at the end part of the position overlapping the upstream side of the vane 21, which is a region in which the combustion gas G does not easily flow through the combustion gas flow path 64 due to the presence of the vane 21 compared to other parts in the rotational direction, and in which the combustion gas flows into the gap 58 and the temperature tends to rise.In the transition piece 33, the cooling promoting structure 82 is preferably provided such that the end on the upstream side of the vane 21 is located in a range of 0.5 W or less from a center of the range W. In this way, a temperature rise can be suppressed efficiently.The area W in which the cooling promoting structure 82 is provided is preferably 1 / 3 or more and 3 times or less the total length of the side of the outer tube 62 on which the cooling promoting structure 82 is provided. In this way, a temperature rise can be suppressed efficiently. In addition, the range W is preferably 1 / 3P or more and 3P or less with respect to the pitch P of the vanes 21.In the transition piece 33, a height of the clearance 92 between two of the protruding parts 84 of the cooling promoting structure 82 is preferably not more than 2.5 times a width thereof. In other words, preferably, in the cooling promoting structure 82, the protruding part 84 is formed such that the clearance 92 satisfies the relationship [height≤5 x width]. Thereby, the cooling performance can be enhanced while suppressing an increase in pressure loss caused by the provision of the cooling promoting structure 82.Further, by configuring the protruding part 84 of the cooling promoting structure 82 as a structure that comes into contact with the inner pipe 60 in the transition piece 33, the outer pipe 62 can be positioned more accurately with respect to the inner pipe 60. Therefore, although the cooling promoting structure 82 is preferably configured as a structure in which the protruding part 84 comes into contact with the inner pipe 60, there may be a gap between the protruding part 84 and the inner pipe 60.Although the cooling promoting structure 82 is preferably provided in the above-described range in the transition piece 33, the structure may be provided over an entire range of the second cooling flow path 80 on the inner side in the rotational direction side. Further, the cooling promoting structure 82 may be provided in the transition piece 33 over the entire circumference of the second cooling flow path 80, in other words, in the segments 66 b, 66 c, and 66 d,in addition to the segment 66 b.FIG. 10 is a schematic view illustrating another example of the relationship between the transition piece of the combustor and the first stage vanes. The gas turbine according to the above-described embodiment has a structure in which two of the vanes 21 are provided with respect to each transition piece 33 in the rotation direction so that the distance Wa=2P; however, the gas turbine is not limited to this structure. The cooling promoting structure 82 is provided in a region Wb in a gas turbine illustrated in FIG. 10 including the transition piece 33 and vanes 21 a. In addition, in the gas turbine, three of the vanes 21 aare provided for each transition piece 33 in the rotation direction. In addition, the positions of the vanes 21 with respect to each transition piece 33 are the same. In other words, in the gas turbine illustrated in FIG. 10, a distance Wc between the transition pieces 33 corresponds to a pitch Pa of three of the vanes 21, thereby establishing the relationship Wc=3 Pa. Further, preferably, in a case where Wc=3P in this manner, the range Wb is 1 / 3 Pa or more and 3 Pa or less, as well as the above range W of the transition piece 33. In addition, although in the present embodiment, the pitches W and Wb of the transition pieces 33 are integral multiples of the pitches P and Pa of the vanes 21 and 21 a, the embodiment is not limited thereto, and thus may be a structure in which the pitches W and Wb of the transition pieces 33 are set to values other than the integral multiples of the pitches P and Pa of the vanes 21 and 21 a, in other words, in which the positions of the vanes 21 and 21 achange based on the position of the transition piece 33 in the circumferential direction.Here, preferably, the welded part between the inner tube 60 and the outer tube 62 is provided in the transition piece 33 in a surface facing the vane shroud 50. Preferably, the welding part is provided at a position visible when viewed from the vane shroud 50 side. This allows welding work to be easily performed. In addition, although in the above-described embodiment, the outer tube 62 and the inner tube 60 are fixed by welding, the outer tube 62 and the inner tube 60 may be manufactured by casting the two as a single body.FIG. 11 is a cross-sectional view illustrating another example of the transition piece. A transition piece 33 aillustrated in FIG. 11 has the same basic structure as the transition piece 33. In the transition piece 33 aillustrated in FIG. 11, the weld part is provided between a surface 102 of a flange part 72 aon an opposite side of a surface facing the vane shroud 50 and an outer tube 62 a. Specifically, the flange part 72 ais a plate of which a thickness up to an end part is constant and a groove is formed in the outer tube 62 a, and a welded part is provided between the surface 102 and the outer tube 62 aby welding the two.Providing the welding part in this manner in the surface 102 on the opposite side of the surface facing the vane shroud 50 in the transition piece 33 a makes it possible to produce a structure in which the welding part is not exposed in the surface facing the vane shroud 50. Therefore, the surface facing the vane shroud 50 of the transition piece 33 acan be limited to the flange part 72 a, whereby durability with respect to heat can be increased and a temperature rise with respect to a quantity of heat can be reduced. The welding part may also be configured to be less susceptible to being heated by the combustion gas G flowing into the gap 58.Further, the cooling performance in the transition piece 33 can be increased while suppressing a pressure loss increase by imparting an uneven shape extending in a direction following the flow of the coolant to the cooling promoting structure. Therefore, although the cooling promoting structure is preferably given an uneven shape extending in the direction following the flow of the coolant, the shape of the structure is not limited thereto. It is sufficient that the cooling promoting structure increases the cooling performance compared to a case where a surface of the outer pipe facing the inner pipe is a flat surface.FIG. 12 is a perspective view illustrating a schematic configuration of another example of the cooling promoting structure. A transition piece 33 billustrated in FIG. 12 has the same basic structure as the transition piece 33. Protruding parts 112 protruding toward the inner tube 60 are arranged two-dimensionally on a surface of an outer tube 62 bin a cooling promoting structure 82 bof the transition piece 33 b. In other words, the protruding parts 112 are provided in rows in the rotation direction, and are also provided in rows in a direction perpendicular to the rotation direction in the cooling promoting structure 82 b. Thereby, the cooling performance by the cooling promoting structure 82 bcan be increased even when it is a structure in which the protruding parts 112 are arranged two-dimensionally.FIG. 13 is a perspective view illustrating a schematic configuration of another example of the cooling promoting structure. A transition piece 33 cillustrated in FIG. 13 has the same basic structure as the transition piece 33. A plurality of protruding parts 122 protruding toward the inner pipe 60 are provided on a surface of an outer pipe 62 cin a cooling promoting structure 82 cof the transition piece 33 calong a direction in which the coolant S flows. In other words, the protruding parts 122 are provided in the cooling promoting structure 82 cin rows in a direction perpendicular to the rotation direction. Thereby, the cooling performance by the cooling promoting structure 82 cmay be increased even when the protruding parts 122 are provided in rows in the direction perpendicular to the rotation direction.FIG. 14 is a cross-sectional view illustrating another example of the transition piece. FIG. 15 is a cross-sectional view taken along B-B in FIG. 14. A transition piece 33 dillustrated in FIGS. 14 and 15 has the same basic structure as the transition piece 33. In a cooling promoting structure 82 dof the transition piece 33 d, a height of a surface of a part of an outer pipe 62 din which the cooling promoting structure 82 dis not provided and a height of a surface of a recessed part of the outer pipe 62 din which the cooling promoting structure 82 dis provided are the same height in a cross section in which the cooling promoting structure 82 dis provided in the transition piece 33 d. Further, a height of a part of a surface 130 of an inner pipe 60 din which the cooling promoting structure 82 dis not provided and a height of a surface 132 of a part of the inner pipe 60 din which the cooling promoting structure 82 dis provided are different heights in a cross section in which the cooling promoting structure 82 dis provided in the transition piece 33 d. In other words, the surface 132 is formed at a position closer to the exhaust flow path 64 than the surface 130, in other words, formed in a shape recessed with respect to the second cooling flow path 80.Thereby, the height of the surface of the inner pipe in the transition piece 33 dmay be changed in the cross section in which the cooling promoting structure 82 dis provided. Further, by making a distance between the outer tube and the inner tube, except for the protruding parts, larger in a region where the cooling promoting structure 82 dis provided than a distance between the outer tube and the inner tube in a region where the cooling promoting structure 82 dis not provided, a decrease in the total cross-sectional area of the flow path can be avoided by providing the cooling promoting structure 82 d. Therefore, cooling performance of a target part can be increased and a required position can be efficiently cooled while suppressing a pressure loss change in the second cooling flow path 80.In addition, although in the above-described embodiment, all of the cooling promoting structures are structures provided with a plurality of protruding parts, the structures are not limited thereto. FIG. 16 is a cross-sectional view illustrating another example of the transition piece. FIG. 17 is a cross-sectional view taken along C-C in FIG. 16, FIG. 18 is a perspective view illustrating a schematic configuration of the cooling promoting structure illustrated in FIG. 16. A transition piece 33 eillustrated in FIGS. 16 to 18 has the same basic structure as the transition piece 33. The transition piece 33 eincludes a cooling promoting structure 82 eand a protruding part 150. The protruding part 150 is provided on an outer tube 62 eand comes into contact with an inner tube 60 e. The protruding part 150 extends in the rotational direction. A plurality of through holes 152 are formed in the protruding part 150. The through hole 152 penetrates the convex part 150 and connects the first cooling flow path 74 to another part of the second cooling flow path 80.Thereby, a plurality of the through holes 152 that connect the first cooling flow path 74 to another part of the second cooling flow path 80 and through which the coolant S flows are formed in the cooling promoting structure 82 e. Since the coolant S flows through the through hole 152 formed in the protruding part 150 in the transition piece 33 e, a contact area between the coolant S and the outer tube 62 ecan be made larger, thus cooling performance can be improved. Although the cooling promoting structure 82 eaccording to the present embodiment is a structure having a protruding part 150, the structure may include two or three or more of such parts.Although the present embodiment and modified examples thereof have been described above, the present embodiment and modified examples thereof are not intended to be limited by the content described above. In addition, elements that can be easily understood by a person skilled in the art and elements that are actually the same as the above-described constituent elements of the present embodiment and the modified examples thereof, and elements that are within a so-called equivalent scope as these are included herein. Furthermore, the constituent elements described above may be combined as appropriate. Finally, the constituent elements may be omitted, replaced, and changed to the extent that it does not depart from the gist of the present embodiments and the modified examples thereof.Reference numerals denote reference numerals1 Gas turbine 11 Compressor 12 Combustor 13 Turbine 14 Exhaust chamber 15 Air inlet port 16 Compressor casing 17, 21 Guide vanes 18, 22 Moving blades 20 Turbine casing 23 Exhaust diffuser 24 Rotor 25, 26 Bearing parts 27 Shell casing 30 Combustor casing 31 Outer cylinder 32 Combustor basket 33 Transition piece 40 Ignition nozzle 42 Main nozzle 50 Guide vane shroud (shroud) 58 Gap 60 Inner pipe 62 Outer pipe 64 Combustion gas flow path 66 a, 66 b, 66 c, 66 dSegments 70 Inner wall part 72 Flange part (end part) 74 First cooling flow path 78 Fixing part 80 Second cooling flow path 82 Cooling promoting structure 84 Protruding part

Claims

A combustor can having an inlet (331) and an outlet (330), the combustor can comprising: an inner tube (60) of which an inner space is a flow path (64) for passing a combustion gas (G), wherein a first cooling flow path (74) through which a coolant (S) can flow is formed in a wall (70) forming the flow path (64); and an outer tube (62;62a;62b;62c;62e) provided on an outer periphery of the inner tube (60) and fixed to the inner tube (60), wherein a second cooling flow path (80) through which the coolant (S) can flow and connected to the first cooling flow path (74), In a combustor tube outlet (33O) side, between an outer peripheral surface of the inner tube (60) and an inner peripheral surface of the outer tube (62;62a;62b;62c;62e), the coolant (S) that has passed through the first cooling flow path (74) flows into the second cooling flow path (80), and the second cooling flow path (80) and a cooling promoting structure (82;82b;82c;82d;82e) are formed in the outer tube (62;62a;62b;62c;62e), the cooling promoting structure (82;82b;82c;82d;82e) being formed between the second cooling flow path (80) and the first cooling flow path (74).A combustor can having an inlet (331) and an outlet (33O), the combustor can comprising: an inner pipe (60) of which an inner space is a flow path (64) for passing a combustion gas (G), wherein a first cooling flow path (74) through which a coolant (S) can flow is formed in a wall (70) forming the flow path (64); and an outer pipe (62;62a;62b;62c;62e) provided on an outer periphery of the inner pipe (60) and fixed to the inner pipe (60), wherein a second cooling flow path (80) through which the coolant (S) can flow and connected to the first cooling flow path (74), in the vicinity of the outlet (33O) of the combustor can, between an outer circumferential surface of the inner tube (60) and an inner circumferential surface of the outer tube (62;62a;62b;62c;62e), a cooling promoting structure (82;82b;82c;82d;82e) is formed in the outer tube (62;62a;62b;62c;62e) within the second cooling flow path (80) in the vicinity of the first cooling flow path (74), and the cooling promoting structure (82;82b;82c;82d;82e) is formed on a side of the outer tube (62;62a;62b;62c;62e) that is further on a rotation axis side of a gas turbine (1) than the inner tube (60), and formed at at least one location within a range (W) including a position intersecting an upstream end part of a vane (21) in a rotation direction of a gas turbine rotor (24); wherein the cooling promoting structure (82; 82b; 82c; 82d; 82e) is disposed at an outlet side of the combustor can.The combustor can according to claim 1 or 2, wherein the cooling promoting structure (82;82b;82c;82d) has an uneven shape, a distance from the inner tube (60) changes in a position-based manner.The combustor can according to claim 3, wherein at least a part of protruding parts (84; 112; 122) of the uneven shape of the cooling promoting structure (82;82b;82c;82d) is in contact with the inner tube (60).The combustor can of claim 1 or 2, wherein the cooling promoting structure (82e) corresponds to a plurality of through holes (152) through which the coolant (S) flows in operation.The combustor can according to any one of claims 1 to 5, wherein an end part on the outlet side is configured to be connected to a guide vane shroud (50) in which a / the guide vane (21) is provided.The combustor can according to claim 6, wherein the cooling promoting structure (82;82b;82c;82d;82e) is provided in a / the range (W) of 1 / 3P or more and 3P or less, where P corresponds to a pitch of vanes (21) in a / the rotation direction of a / the gas turbine rotor (24).The combustor can according to claim 6 or 7, wherein the inner tube (60) has a flange part (72) that extends toward the outer tube (62) in an end part on the vane shroud side, and the combustor can is provided with a welding part at which the end part on the vane shroud side of the outer tube (62) is joined to an end part of the flange side by welding.The combustor liner according to claim 8, wherein the welding part connects a surface of the flange part (72) to the outer pipe (62) on a side opposite to the vane shroud side.A combustion chamber (12) comprising a combustion chamber tube according to any one of claims 1 to 9.A gas turbine (1) comprising: a compressor (11); a combustor (12) according to claim 10 for burning fuel and air compressed by the compressor (11) to generate combustion gas (G); and a turbine (13) arranged to be driven by the combustion gas (G) supplied from the combustor (12).

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