Gas turbine and method for manufacturing blade ring

Abstract

The present invention provides a gas turbine and a method for manufacturing a blade ring portion. In the gas turbine, a plurality of blade ring portions (50) have: a plurality of first cooling channels (61) arranged on the radially outer side with a rotating shaft as the center, extending in the axial direction, and arranged in an axially surrounding direction; a plurality of second cooling channels (62) arranged at a position radially inner than the first cooling channels (61), extending in the axial direction, and arranged in an axially surrounding direction; and a return channel (65) connecting the ends of the first cooling channels (61) and the second cooling channels (62) on the same side in the axial direction to each other.

Description

[0001] This application is a divisional application of a patent application with an application date of May 10, 2018, an application number of 201880031759.2, and an invention name of “Gas turbine, and method for manufacturing a blade ring portion”. Technical Field

[0002] The present invention relates to a gas turbine and a method for manufacturing a blade ring. Background Art

[0003] The gas turbine has a compressor, a combustor, and a turbine. The compressor takes in air and compresses it to make it high-temperature and high-pressure compressed air. The combustor supplies fuel to the compressed air and burns it. The turbine rotates with the high-temperature and high-pressure combustion gas generated by the combustion of the compressed air. The rotation of the turbine converts thermal energy into rotational energy.

[0004] Such a gas turbine has: a casing that covers the outer peripheral side of a rotor; and a plurality of stationary blade segments that are fixed to the inner peripheral side of the casing and arranged on the upstream side of each of the plurality of moving blade segments. A plurality of blade rings are arranged on the inner peripheral side of the casing, forming a ring shape with the rotating shaft as the center, and covering the moving blade segments and the stationary blade segments. Inside the blade ring, a flow path for a cooling medium to cool the blade ring is formed along the axial direction of the rotating shaft (for example, refer to Patent Document 1).

[0005] Prior art literature

[0006] Patent Literature

[0007] Patent Document 1: Japanese Patent No. 5457965 Summary of the invention

[0008] Problems to be solved by the invention

[0009] In the above-mentioned gas turbine, it is desired to suppress the formation of a temperature distribution in the radial direction around the rotation axis of the blade ring portion.

[0010] The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a gas turbine capable of suppressing the formation of a temperature distribution in the radial direction of the blade ring portion, and a method for manufacturing the blade ring portion.

[0011] Solutions to Solve Problems

[0012] A gas turbine according to one embodiment of the present invention comprises: a compressor for compressing air; a combustor for mixing fuel with the compressed air compressed by the compressor and burning the mixture; a turbine for rotating by means of combustion gas generated by the combustor; a rotor having a rotor body for rotating in a periaxial direction of a rotating shaft by means of the rotation of the turbine, and a plurality of moving blade segments fixed to the rotor body in a manner arranged in an axial direction of the rotating shaft; a casing for covering the outer peripheral side of the rotor; a plurality of stationary blade segments fixed to the inner peripheral side of the casing and arranged on the upstream side of each of the plurality of moving blade segments; and a plurality of blade rings, It is arranged on the casing, formed into a ring shape with the rotating shaft as the center, and covers the moving blade segment and the stationary blade segment, and the plurality of blade ring portions have: a plurality of first cooling flow paths, which are arranged on the radial outer side with the rotating shaft as the center, extend along the axial direction, and are arranged in the axial direction; a plurality of second cooling flow paths, which are arranged at a position closer to the radial inner side than the first cooling flow paths, extend along the axial direction, and are arranged in the axial direction; and a return flow path, which connects the ends of the first cooling flow path and the second cooling flow path on the same side of the axial direction to each other.

[0013] According to the present invention, a plurality of first cooling channels are arranged on the radially outer side in the axial direction, and a plurality of second cooling channels are arranged on the radially inner side in the axial direction. The ends of the first cooling channels and the second cooling channels on the same side in the axial direction are folded back due to the folded channels, so that a plurality of cooling channels arranged in the axial direction of the rotating shaft can be arranged in multiple stages in the radial direction. As a result, the blade ring is cooled in the range of multiple locations in the radial direction, so that the temperature distribution in the radial direction of the blade ring can be suppressed.

[0014] In addition, in the above-mentioned gas turbine, the first cooling flow path and the second cooling flow path can be formed in the blade ring body, and the center of the first opening connecting the second cooling flow path to the return flow path is arranged at a position radially outer than the center of the second opening of the second cooling flow path at the end opening on the upstream side of the axial direction of the blade ring body.

[0015] According to the present invention, the second cooling flow path can be brought close to the inner peripheral surface of the blade ring body, so that cooling of the inner peripheral surface is further enhanced.

[0016] Furthermore, in the above-described gas turbine, the center of the second opening may be arranged radially inward of a bottom surface of the return flow path that faces radially inward.

[0017] Furthermore, in the above-mentioned gas turbine, the second cooling flow path may be a bent flow path that bends radially outward in the middle of a flow path extending in the axial direction.

[0018] According to the present invention, the flow path can be formed near the inner peripheral surface of the cylindrical portion of the blade ring portion, thereby further strengthening the cooling of the inner peripheral surface of the blade ring portion.

[0019] In the above-mentioned gas turbine, the blade ring portion may include a first communication flow path connecting the first cooling flow paths to each other in the circumferential direction, and a second communication flow path connecting the second cooling flow paths to each other in the circumferential direction.

[0020] According to the present invention, the cooling medium can flow in the axial direction via the first communication flow passage and the second communication flow passage, and thus it is possible to suppress the formation of a temperature distribution in the axial direction of the blade ring portion.

[0021] In the above-mentioned gas turbine, the first communication flow path may be connected to a supply pipe for supplying a cooling medium, and the second communication flow path may be connected to a discharge pipe for discharging the cooling medium.

[0022] According to the present invention, the cooling medium flows from the supply pipe through the first connecting flow path, the first cooling flow path, the return flow path, the second cooling flow path, the second connecting flow path in sequence and is discharged from the discharge pipe, thereby effectively cooling the blade ring from the radial outside to the inside.

[0023] Furthermore, in the above-mentioned gas turbine, the discharge pipe may be connected to a cooling flow path of the combustor.

[0024] According to the present invention, the cooling medium after cooling the blade ring portion is supplied to the cooling flow path of the combustor, so the cooling medium can be effectively used.

[0025] Furthermore, the gas turbine may further include: a bypass flow path that bypasses the blade ring portion and connects the supply pipe and the discharge pipe; and a supply destination switching portion that switches a supply destination of the cooling medium between the blade ring portion and the bypass flow path.

[0026] According to the present invention, when it is desired to suppress cooling of the blade ring portion, such as at the start-up of the gas turbine, the supply destination of the cooling medium is switched from the blade ring portion to the bypass flow path, so that the cooling medium can flow around the blade ring portion.

[0027] Furthermore, in the above-mentioned gas turbine, the bypass flow path may be arranged so as to be separated from the blade ring portion main body in the axial direction.

[0028] According to the present invention, it is possible to suppress the occurrence of temperature distribution in the blade ring portion.

[0029] In addition, in the above-mentioned gas turbine, the combustor may have a tail cylinder on the turbine side, the blade ring portion may have a plurality of tail cylinder connecting portions arranged along the axial direction, and the tail cylinder connecting portion may include a bypass connecting hole connected to the bypass flow path, and a tail cylinder side connecting hole connected to the tail cylinder side.

[0030] According to the present invention, the cooling medium can be efficiently caused to flow toward the transition piece side via the bypass flow passage.

[0031] Furthermore, in the above-mentioned gas turbine, the bypass flow path may include a bypass connecting pipe arranged along the circumferential direction of the blade ring portion.

[0032] According to the present invention, the cooling medium can flow in the circumaxial direction of the blade ring portion via the bypass connection pipe, so the temperature of the cooling medium flowing toward the transition piece can be made uniform in the circumaxial direction.

[0033] Furthermore, in the above-mentioned gas turbine, the bypass connecting pipe may include a thermal expansion absorbing portion that can be deformed according to thermal deformation of the blade ring portion.

[0034] According to the present invention, the bypass connecting pipe is deformed according to the thermal deformation of the blade ring portion, so that deformation of the bypass flow path between the bypass connecting pipe and the transition piece connecting pipe can be suppressed.

[0035] In addition, in the above-mentioned gas turbine, the blade ring portion may include: a blade ring portion main body, which is provided with the first cooling flow path, the second cooling flow path, the return flow path, a part of the first connecting flow path, namely a first groove portion, and a part of the second connecting flow path, namely a second groove portion; a first blocking member, which is fastened to the blade ring portion main body in a manner that can be loaded and unloaded, blocks the first groove portion, thereby forming the first connecting flow path between the first blocking member and the first groove portion; and the tail cylinder connecting portion, which is fastened to the blade ring portion main body in a manner that can be loaded and unloaded, blocks the second groove portion, thereby forming the second connecting flow path between the tail cylinder connecting portion and the second groove portion.

[0036] Furthermore, in the above-mentioned gas turbine, in the blade ring portion, the return flow paths may communicate with each other in the circumferential direction.

[0037] According to the present invention, since the cooling medium can flow in the circumferential direction via the return flow path, it is possible to suppress the formation of a temperature distribution in the circumferential direction of the blade ring portion.

[0038] Furthermore, in the above-mentioned gas turbine, the first cooling flow path and the second cooling flow path may be arranged on a virtual straight line extending from the rotation shaft in the radial direction.

[0039] According to the present invention, the second cooling flow path is densely arranged on the radially inner side of the blade ring portion, thereby making it possible to effectively cool the radially inner side of the blade ring portion.

[0040] Furthermore, in the above-mentioned gas turbine, the blade ring portion may include a cavity supply flow path penetrating in the radial direction, and the first cooling flow path and the second cooling flow path may be arranged at positions corresponding to the cavity supply flow path.

[0041] According to the present invention, the cooling medium flowing in the first cooling flow path and the second cooling flow path is configured to directly cool the heat input from the cavity supply flow path side and block the heat transfer from the cavity supply flow path to the inside of the blade ring part, thereby being able to suppress the generation of temperature distribution in the blade ring part.

[0042] Furthermore, in the above-mentioned gas turbine, the blade ring portion may include a partition wall portion projecting outward in the radial direction, and the first communication flow path may be arranged in the partition wall portion.

[0043] According to the present invention, the rigidity of the blade ring can be improved by providing the partition wall, and the radial temperature distribution in the protrusion can be suppressed by arranging the first communication flow path inside the partition wall. Thus, thermal deformation of the partition wall can be effectively suppressed.

[0044] In addition, in the above-mentioned gas turbine, the blade ring portion may have: a plurality of third cooling flow paths, which are arranged at a position closer to the outside of the radial direction than the first cooling flow paths, extend along the axial direction, and are arranged along the axial direction; and a second return flow path, which connects the end portions of the third cooling flow path and the first cooling flow path on the same side of the axial direction.

[0045] According to the present invention, three or more cooling channels arranged in the circumferential direction of the rotating shaft can be radially arranged, thereby effectively cooling the blade ring in the radial direction, thereby more effectively suppressing the formation of temperature distribution in the blade ring in the radial direction.

[0046] In a method for manufacturing a blade ring portion according to one embodiment of the present invention, a plurality of blade ring portions are provided on a cylindrical casing covering a rotor of a gas turbine, the blade ring portions are formed into a ring shape with the rotating shaft of the rotor as the center, and cover the moving blade segment and the stationary blade segment. The method for manufacturing the blade ring portion comprises: a process of forming a blade ring portion main body, the blade ring portion main body having: a plurality of first cooling flow paths, which are arranged on the radially outer side with the rotating shaft as the center, extend in the axial direction, and are arranged in an axial direction; a plurality of second cooling flow paths, which are arranged at a position closer to the radially inner side than the first cooling flow paths, extend in the axial direction, and are arranged in an axial direction; a folded flow path, which connects the first cooling flow path with and the ends of the second cooling flow path on the same side of the axial direction are connected to each other; a first connecting flow path, which connects the first cooling flow paths to each other in the axial direction; and a second connecting flow path, which connects the second cooling flow paths to each other in the axial direction; a process of forming the first cooling flow path between the first connecting flow path and the return flow path; a process of forming the second cooling flow path between the second connecting flow path and the return flow path in two stages; a process of installing a first blocking member that blocks the first connecting flow path on the blade ring portion to form the first connecting flow path; and a process of installing a second blocking member that blocks the second connecting flow path on the blade ring portion.

[0047] According to the present invention, the first and second communication channels can be easily formed by fastening the first and second blocking members to the blade ring body, and the first and second grooves can be easily exposed to the outside by removing the first and second blocking members from the blade ring body.

[0048] According to the present invention, the first connecting flow path may include a first groove at the end portion in the axial direction, the second connecting flow path may include a second groove at the end portion in the axial direction, the first blocking member may be fastened to the leaf ring body in a detachable manner so as to block the first groove, and the second blocking member may be fastened to the leaf ring body in a detachable manner so as to block the second groove.

[0049] Effects of the Invention

[0050] According to the present invention, it is possible to provide a gas turbine capable of suppressing the formation of a temperature distribution in the radial direction of the blade ring portion, and a method for manufacturing the blade ring portion. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Figure 1 It is a schematic diagram showing the overall structure of the gas turbine according to the first embodiment.

[0052] Figure 2 It is a cross-sectional view showing the vicinity of a blade ring portion of a turbine.

[0053] Figure 3 This is a cross-sectional view showing an example of a blade ring portion of a turbine.

[0054] Figure 4 It is a perspective view showing an example of the blade ring part.

[0055] Figure 5 This is a system diagram of the cooling flow path of the blade ring.

[0056] Figure 6 It is a system diagram of a modified example of the cooling flow path of the blade ring portion.

[0057] Figure 7 It is shown along Figure 3 Figure 2 shows the structure of the AA section.

[0058] Figure 8 This is a cross-sectional view showing an example of a blade ring portion according to the second embodiment.

[0059] Fig. 9 It is a perspective view showing an example of a part of the blade ring portion.

[0060] Fig.10 This is a system diagram of the cooling flow path of the blade ring.

[0061] Fig.11 It is shown along Figure 8 Figure 2 shows the shape of the BB cross section.

[0062] Fig.12 This is a cross-sectional view showing an example of a blade ring portion according to the third embodiment.

[0063] Fig.13 It is a perspective view showing an example of a part of the blade ring portion.

[0064] Fig.14 1 is a flowchart showing the manufacturing process of the blade ring portion.

[0065] Description of Reference Numerals

[0066] 11. Compressor

[0067] 12 Burner

[0068] 12a Tail tube

[0069] 13 Turbine

[0070] 14 Engine Room

[0071] 20 Suction chamber

[0072] 21 Compressor room

[0073] 22 Inlet guide vane

[0074] 23, 27 Stationary blades

[0075] 24, 28 Moving blades

[0076] 25 Vacuum Chamber

[0077] 26 Turbine Room

[0078] 29 Exhaust room

[0079] 30 Exhaust Chamber

[0080] 31 Exhaust Diffuser

[0081] 32 Rotor

[0082] 33, 34 bearing part

[0083] 35, 36, 37 Legs

[0084] 42a Upstream side outer partition wall

[0085] 42b Downstream side outer partition wall

[0086] 50, 150, 250 leaf ring

[0087] 50a, 150a, 250a Leaf ring body

[0088] 51, 151, 251 Cylinder

[0089] 51a, 151a, 251a Outer circumference of cylindrical portion

[0090] 51b, 151b, 251b Inner circumference of the cylinder

[0091] 51d, 151d, 251d Flow path opening (first opening)

[0092] 51e, 151e, 251e flow path opening (second opening)

[0093] 52, 152, 252 Downstream inner wall

[0094] 53, 153, 253 Upstream inner wall

[0095] 54, 154, 254 Tail cylinder connection portion (second blocking member)

[0096] 54a, 154a, 254a Tail cylinder side connecting hole

[0097] 54b, 154b, 254b Bypass connection hole

[0098] 54c, 154c, 254c discharge flow path

[0099] 55, 155, 255 cavity supply flow path

[0100] 60, 160, 260 cooling flow path

[0101] 61, 161, 261 first cooling flow path

[0102] 62, 162, 262 Second cooling flow path

[0103] 65, 165, 265 return flow path

[0104] 65b, 165b, 265b bottom

[0105] 66 Take in flow path

[0106] 68, 168, 268 Bypass flow path

[0107] 68a Bypass inlet pipe

[0108] 68b, 168b, 268b Bypass connection pipe

[0109] 68c, 168c, 268c Thermal expansion absorption part

[0110] 68d, 168d, 268d inlet connection pipe

[0111] 70, 170, 270 connecting flow path

[0112] 71, 171, 271 First communication flow path

[0113] 72, 172, 272 Second communication flow path

[0114] 75, 175, 275 Return connection flow path

[0115] 80 Cooling medium circulation mechanism

[0116] 81 Supply piping

[0117] 82 Discharge piping

[0118] 83 Bypass piping

[0119] 84 Cooler

[0120] 85 Compressor

[0121] 86 Three-way valve

[0122] 100 Gas Turbine

[0123] 162a, 262a Upstream flow path

[0124] 162b, 262b Downstream flow path

[0125] 163, 263 Third cooling flow path

[0126] 173 Third connecting flow path

[0127] 251c First blocking member

[0128] 257 First slot

[0129] 258 Second slot

[0130] C Rotation axis

[0131] G Combustion gas

[0132] L1, L2 imaginary straight line

[0133] P Cooling medium. DETAILED DESCRIPTION

[0134] Hereinafter, an embodiment of a gas turbine and a method for manufacturing a blade ring of the present invention will be described based on the accompanying drawings. It should be noted that the present invention is not limited to the embodiment. In addition, the constituent elements of the following embodiments include elements that can be easily replaced by a person skilled in the art, or substantially the same elements.

[0135] <First Embodiment>

[0136] Figure 1 1 is a schematic diagram showing the overall structure of the gas turbine 100 according to the present embodiment. Figure 1 As shown, the gas turbine 100 includes a compressor 11, a combustor 12, and a turbine 13. The gas turbine 100 is connected to a generator (not shown) and can generate electric power through the generator.

[0137] The compressor 11 has an intake chamber 20 for taking in air, an inlet guide vane (IGV: Inlet Guide Vane) 22 is arranged in the compressor casing 21, and a plurality of stationary blades 23 and a plurality of moving blades 24 are alternately arranged along the flow direction of air (the axial direction of the rotor 32 described later), and an exhaust chamber 25 is provided outside the compressor 11. The compressor 11 generates high-temperature and high-pressure compressed air by compressing the air taken in from the intake chamber 20, and supplies the compressed gas to the casing 14.

[0138] The combustor 12 is supplied with fuel and high-temperature, high-pressure compressed air compressed by the compressor 11 and stored in the chamber 14, and generates combustion gas by burning them. In the turbine chamber 26 of the turbine 13, a plurality of stationary blades 27 and a plurality of moving blades 28 are alternately arranged along the flow direction of the combustion gas (the axial direction of the rotor 32 described later). In addition, in the turbine chamber 26, an exhaust chamber 30 is arranged on the downstream side of the flow direction of the combustion gas across the exhaust chamber 29, and the exhaust chamber 30 has an exhaust diffuser 31 connected to the turbine 13. The turbine is driven by the combustion gas from the combustor 12, thereby driving a generator (not shown) connected on the same axis.

[0139] The rotor (rotating shaft) 32 is arranged in a manner that passes through the center of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 30. The rotor 32 is capable of rotating in the axial direction around the rotation axis C (hereinafter, marked as "around the axial direction"). Specifically, the end of the rotor 32 on the compressor 11 side is supported by a bearing portion 33 so as to be rotatable, and the end on the exhaust chamber 30 side is supported by a bearing portion 34 so as to be rotatable. In addition, the rotor 32 has a plurality of discs equipped with each moving blade 24 fixed in an overlapping manner in the compressor 11. In addition, the rotor 32 has a plurality of discs equipped with each moving blade 28 fixed in an overlapping manner in the turbine 13, and the end on the intake chamber 20 side is connected to a drive shaft of a generator (not shown).

[0140] Furthermore, in the gas turbine 100 , the compressor casing 21 of the compressor 11 is supported by the leg portion 35 , the turbine casing 26 of the turbine 13 is supported by the leg portion 36 , and the exhaust chamber 30 is supported by the leg portion 37 .

[0141] Therefore, in the compressor 11, the air taken in from the intake chamber 20 is compressed through the inlet guide vane 22, the plurality of stationary vanes 23 and the moving blades 24, thereby becoming high-temperature, high-pressure compressed air. In the combustor 12, a predetermined fuel is supplied to the compressed air and burned. In the turbine 13, the high-temperature, high-pressure combustion gas G generated by the combustor 12 passes through the plurality of stationary vanes 27 and the moving blades 28 in the turbine 13, thereby driving the rotor 32 to rotate, and further driving the generator connected to the rotor 32. On the other hand, the combustion gas G is released into the atmosphere after the kinetic energy is converted into pressure and decelerated by the exhaust diffuser 31 of the exhaust chamber 30. It should be noted that a part of the compressed air compressed by the compressor 11 is extracted at the intermediate stage of the compressor 11 and supplied to the turbine chamber 26. The extracted air supplied to the turbine chamber 26 is accumulated in the turbine chamber space 26a and is used to cool the high-temperature components on the turbine side.

[0142] Figure 2 It is a cross-sectional view showing the vicinity of the blade ring portion 50 of the turbine 13 . Figure 3 1 is a cross-sectional view showing an example of the blade ring portion 50 of the turbine 13. Figure 2 as well as Figure 3 As shown, the turbine 13 has a cylindrical turbine chamber (housing) 26. In the turbine chamber 26, a cylindrical exhaust chamber 29 is connected to the downstream side of the flow direction of the combustion gas G. In the exhaust chamber 29, a cylindrical exhaust chamber 30 (exhaust diffuser 31) is arranged on the downstream side of the flow direction of the combustion gas G. In the exhaust chamber 30, an exhaust duct (not shown) is provided on the downstream side of the flow direction of the combustion gas G.

[0143] An upstream outer partition wall portion 42a and a downstream outer partition wall portion 42b are integrally formed in the inner peripheral portion of the turbine chamber 26 at a predetermined interval in front and behind the flow direction of the combustion gas G. A blade ring portion 50 having a ring shape divided into two parts in the axial direction is supported inside the upstream outer partition wall portion 42a and the downstream outer partition wall portion 42b. The blade ring portion 50 is fastened by bolts at the divided portion in the axial direction to form a cylindrical structure.

[0144] Figure 4 is a perspective view showing a portion of the leaf ring portion 50. Figure 3 as well as Figure 4 As shown, the blade ring portion 50 mainly includes: a blade ring portion body 50a which is the main part of the blade ring portion 50, a tail pipe connecting portion 54 which forms a connecting portion between the combustor 12 and the blade ring portion 50, and a bypass flow path 68 which forms a flow path for the cooling medium P to bypass the blade ring portion 50.

[0145] The blade ring body 50a includes: a cylindrical portion 51 having a cooling flow path 60 inside, a downstream inner partition wall portion 52, and an upstream inner partition wall portion 53. The cylindrical portion 51 is arranged parallel to the rotation axis C. The central axis of the cylindrical portion 51 is substantially consistent with the rotation axis C. The downstream inner partition wall portion 52 protrudes from the outer peripheral surface 51a of the cylindrical portion 51 to the outside in the radial direction (hereinafter, marked as "radial direction") centered on the rotation axis C, and is provided in an annular shape along the axial direction. The downstream inner partition wall portion 52 is arranged at the end of the downstream side of the axial direction of the turbine 13 side of the cylindrical portion 51 in the axial direction of the rotation axis C (hereinafter, marked as "axial direction"). An annular end groove portion 52a is formed at the corner of the end of the downstream inner partition wall portion 52, and the annular end groove portion 52a is formed in an L-shaped cross section along the axial direction. The downstream outer partition wall portion 42b formed on the inner circumferential surface of the turbine chamber 26 is embedded in the end groove portion 52a, and the side surface 52b of the downstream inner partition wall portion 52 of the end groove portion 52a, which faces the downstream side in the axial direction, contacts the surface of the downstream outer partition wall portion 42b facing the upstream side in the axial direction. It should be noted that a gap for absorbing the radial thermal expansion difference of the blade ring body 50a is formed between the inner circumferential surface of the downstream outer partition wall portion 42b facing the radial inner side and the inner circumferential surface 52c of the downstream inner partition wall portion 52 of the end groove portion 52a, which faces the radial outer side. Here, the upstream side in the axial direction refers to the direction from the blade ring portion 50 to observe the compressor 11, and the downstream side in the axial direction refers to the direction from the blade ring portion 50 to observe the exhaust chamber 30.

[0146] The upstream inner bulkhead portion 53 is arranged at a position closer to the upstream side in the axial direction than the downstream inner bulkhead portion 52, and the upstream inner bulkhead portion 53 protrudes radially outward from the outer peripheral surface 51a of the cylindrical portion 51 and is arranged in an annular shape along the axial direction. A bulkhead groove portion 53a formed along the axial direction is formed in the upstream inner bulkhead portion 53, and the upstream outer bulkhead portion 42a formed on the inner peripheral surface of the turbine chamber 26 is embedded in the upstream inner bulkhead portion 53. The surface of the upstream outer bulkhead portion 42a facing the upstream side in the axial direction contacts the side surface 53b of the upstream inner bulkhead portion 53 forming the bulkhead groove portion 53a facing the downstream side in the axial direction, and a sealing surface is formed on the contact surface. The air pressure in the machine chamber 14 is maintained by providing a sealing surface on the side surface 53b of the upstream inner bulkhead portion 53. It should be noted that a pressing mechanism such as a spring (not shown) is provided on the contact surface between the side surface 52b of the downstream inner partition wall portion 52 that forms the end groove portion 52a and the surface of the downstream outer partition wall portion 42b that faces the upstream side in the axial direction. The pressing mechanism presses the blade ring portion 50 toward the upstream side in the axial direction via the side surface 52b, thereby preventing the chamber air from leaking from the gap generated on the sealing surface of the upstream inner partition wall portion 53 to the turbine chamber space 26a on the downstream side in the axial direction.

[0147] In addition, a gap for absorbing the difference in radial thermal expansion between the turbine chamber 26 and the blade ring body 50a is formed between the inner circumferential surface of the upstream side outer partition wall portion 42a facing inward in the radial direction and the inner circumferential surface 53c of the upstream side inner partition wall portion 53 forming the partition wall groove portion 53a facing outward in the radial direction. Similarly, a gap for absorbing the difference in axial thermal expansion between the turbine chamber 26 and the blade ring body 50a is formed between the side surface of the upstream side outer partition wall portion 42a facing downstream in the axial direction and the side surface 53d of the upstream side inner partition wall portion 53 forming the partition wall groove portion 53a facing upstream in the axial direction.

[0148] The blade ring body 50a has a cooling flow path 60 for the cooling medium P to flow. The cooling flow path 60 has: a first cooling flow path 61 for cooling the cylindrical portion 51, a second cooling flow path 62 arranged on the downstream side of the first cooling flow path 61 in the flow direction of the cooling medium P, and a return flow path 65 connecting the first cooling flow path 61 and the second cooling flow path 62. The first cooling flow path 61 is arranged on the radially outer side of the cylindrical portion 51 and is arranged close to the outer peripheral surface 51b of the cylindrical portion 51a. The first cooling flow path 61 extends in a manner substantially parallel to the axial direction. A plurality of first cooling flow paths 61 are arranged in a line around the axis.

[0149] The second cooling channel 62 is arranged in the cylindrical portion 51 at a position radially inward of the first cooling channel 61 and close to the inner peripheral surface 51b of the cylindrical portion 51. The second cooling channel 62 extends linearly in a manner substantially parallel to the axial direction. Therefore, the second cooling channel 62 is substantially parallel to the first cooling channel 61. A plurality of second cooling channels 62 are arranged in a line around the axis.

[0150] The return flow path 65 connects the ends of the first cooling flow path 61 and the second cooling flow path 62 on the same side in the axial direction. The return flow path 65 is arranged at the end of the downstream side in the axial direction of the blade ring body 50a. The return flow path 65 is a flow path that turns the cooling medium P flowing in the first cooling flow path 61 back to the second cooling flow path 62. Figure 3As shown, the cross-sectional shape of the return flow path 65 at the plane passing through the rotation axis C is a rectangular space (cavity) extending radially outward. The first cooling flow path 61 is connected to the return flow path 65 on the radial outside of the return flow path 65, and the second cooling flow path 62 is connected to the return flow path 65 on the radial inside of the return flow path 65. In addition, the return flow path 65 (the return connecting flow path 75) can also be formed into a ring shape along the axial direction. Therefore, the return flow path 65 connects the multiple first cooling flow paths 61 with the multiple second cooling flow paths 62 in the axial direction. It should be noted that when the return flow path 65 (the return connecting flow path 75) is formed into a ring shape along the axial direction, in order to cool the entire downstream inner bulkhead portion 52, it is preferred that the radial upper end of the rectangular cross-section of the return flow path 65 is formed close to the inner circumferential surface 52c of the downstream inner bulkhead portion 52.

[0151] The blade ring portion 50 may have a connecting flow path 70, which supplies the cooling medium P to a plurality of cooling flow paths 60 arranged in a ring shape along the axial direction of the blade ring portion 50, or collects the cooling medium P from a plurality of cooling flow paths 60, and is connected to each cooling flow path 60 in the axial direction. The connecting flow path 70 has a first connecting flow path 71 and a second connecting flow path 72. The first connecting flow path 71 connects the first cooling flow paths 61 arranged in the axial direction to each other in the axial direction. The first connecting flow path 71 is disposed inside the upstream inner partition wall portion 53. As shown in FIG. Figure 3 As shown, the cross-sectional shape of the first communicating flow path 71 at the plane passing through the rotation axis C is a rectangular shape extending radially outward. Therefore, inside the upstream inner bulkhead 53, the refrigerant medium P can also be circulated radially outward. The first communicating flow path 71 is connected to the supply pipe 81 (described later) for supplying the cooling medium P via the intake flow path 66. It should be noted that, in order to cool the entire upstream inner bulkhead 53, it is preferred that the cross-sectional shape of the first communicating flow path 71 adopts a rectangular cross-sectional shape, the radial flow path width of the rectangular cross-sectional shape is wider than the flow path width in the axial direction, and has an elongated flow path width extending radially. In addition, the radial upper end of the rectangular cross-section is preferably formed to be close to the inner circumferential surface 53c of the upstream inner bulkhead 53.

[0152] The second cooling flow path 62 is connected to a flow path opening (second opening) 51e formed on the inner wall of the second connecting flow path 72, and the second connecting flow path 72 is formed at the end of the upstream side in the axial direction of the blade ring body 50a. The end of the downstream side in the axial direction of the second cooling flow path 62 is connected to the flow path opening (first opening) 51d provided in the return flow path 65 or the return connecting flow path 75. In addition, the second cooling flow path 62 may not be parallel to the first cooling flow path 61, but may be inclined toward the upstream side in the axial direction and radially inward. In this case, the center of the flow path opening 51d is formed at a position radially outward than the center of the flow path opening 51e. In addition, the center of the flow path opening 51e may also be formed at a position radially inward than the bottom surface 65b on the radial inner side of the return flow path 65 or the return connecting flow path 75. If the second cooling flow path 62 is inclined radially inward, the second cooling flow path 62 is disposed closer to the inner peripheral surface 51 b of the cylindrical portion 51 , so that cooling of the inner peripheral surface 51 b is further enhanced.

[0153] The second communication flow path 72 connects the second cooling flow paths 62 arranged in the axial direction with each other in the axial direction. The second communication flow path 72 is provided inside the cylindrical portion 51 protruding toward the combustor 12, for example, at a position on the upstream side in the axial direction of the cylindrical portion 51 relative to the upstream inner partition wall portion 53. In addition, the second communication flow path 72 is arranged closer to the inner peripheral surface 51b of the cylindrical portion 51 at a position on the radially inner side than the first communication flow path 71.

[0154] The second communication flow path 72 is formed on the main body upstream side end surface 51f on the upstream side in the axial direction of the cylindrical portion 51, has a cross section that is recessed from the main body upstream side end surface 51f toward the downstream side in the axial direction, and is formed into a communication opening 72a in the shape of an annular groove extending in the circumaxial direction. The second communication flow path 72 is connected to the second cooling flow path 62 via the flow path opening 51e. In addition, the second communication flow path 72 is connected to the discharge flow path 54c of the tail cylinder connection portion 54, which is arranged adjacent to the main body upstream side end surface 51f on the upstream side in the axial direction.

[0155] Next, if Figure 3 as well as Figure 4As shown, the tail cylinder connection portion 54 is arranged on the downstream side in the axial direction in a manner corresponding to the number of burners 12 installed, and the tail cylinder connection portion 54 is arranged adjacent to the upstream side in the axial direction of the cylindrical portion 51 of the blade ring body 50a. The tail cylinder connection portion 54 is a box-shaped block member, fixed to the main body upstream side end surface 51f at the upstream end in the axial direction of the cylindrical portion 51 of the blade ring body 50a. The tail cylinder connection portion 54 is arranged on the downstream side in the axial direction adjacent to the tail cylinder 12a of the burner 12 arranged on the upstream side in the axial direction of the blade ring body 50a, and a plurality of tail cylinder connection portions 54 are arranged in an axial direction. The tail cylinder connection portion 54 has: a tail cylinder side connecting hole 54a, which is connected to the tail cylinder 12a (refer to Figure 2 ) side cooling flow path (not shown); bypass connection hole 54b, which is connected to the bypass flow path (described later); discharge flow path 54c, which is connected to the second communication flow path 72, collects the cooling medium P after cooling the cooling flow path 60, and is connected to the tail tube side communication hole 54a. The discharge flow path 54c is a flow path extending to the upstream side in the axial direction, and is connected to the discharge pipe 82 via the tail tube side communication hole 54a formed at the upstream end in the axial direction of the tail tube connection part 54. The discharge pipe 82 is connected to the cooling flow path (not shown) of the combustor 12. In addition, the discharge flow path 54c is connected to the bypass pipe 83 via the bypass flow path 68 (described later). The cooling medium P bypassing the blade ring body 50a and supplied to the bypass pipe 83 is supplied to the bypass flow path 68, and is discharged from the discharge flow path 54c to the discharge pipe 82.

[0156] Next, refer to Figure 2 , Figure 3 as well as Figure 4The bypass flow path for bypassing the blade ring portion without causing the cooling medium P to flow into the blade ring portion at the time of starting the gas turbine will be described below. At the time of starting the gas turbine 100, the displacement of the moving blade 28 accompanying the high-speed rotation overlaps with the displacement caused by the heat input from the combustion gas, so that the moving blade 28 is displaced toward the radial outer side. On the other hand, at the time of starting, when the cooling medium P is supplied to the blade ring portion 50 without bypassing (bypassing) the blade ring portion 50, the blade ring portion 50 is cooled by the cooling medium P flowing in the blade ring portion 50, so that the blade ring portion 50 is displaced toward the radial inner side. As a result, in the transition period before the gas turbine 100 reaches the rated operation, the clearance between the front end of the moving blade 28 and the blade ring portion 50 may become smaller than an appropriate value. In order to avoid this phenomenon, it is preferable to bypass the blade ring portion 50 without causing the cooling medium P to flow through the blade ring portion 50 at the time of starting the gas turbine 100, and supply the cooling medium P to the blade ring portion 50 during the rated operation. Thus, it is possible to suppress the radially inward displacement of the blade ring 50 caused by the cooling medium P during the operation transition period of the gas turbine 100. On the other hand, in the process in which a part of the bleed air from the compressor 11 passes through the cavity supply flow path 55, the blade ring 50 is heated by the bleed air. Thus, it is possible to avoid the clearance becoming too small. As a result, it is possible to set an appropriate clearance, thereby shortening the start-up time of the gas turbine 100 and improving the efficiency of the gas turbine 100.

[0157] The bypass flow path 68 includes: a bypass inlet pipe 68a, which receives the cooling medium P from a cooling medium circulation mechanism 80 (described in detail later); a bypass connecting pipe 68b, which is arranged in an annular shape along the axial direction on the upstream side of the cylindrical portion 51 in the axial direction and supplies the cooling medium P to the tail cylinder connecting portion 54; a thermal expansion absorption portion 68c, which absorbs the thermal expansion of the bypass connecting pipe 68b in the axial direction; and an inlet connecting pipe 68d, which connects the bypass connecting pipe 68b to the bypass connecting hole 54b formed in the tail cylinder connecting portion 54.

[0158] exist Figure 4In the example shown, the bypass inlet pipe 68a is formed with a cylindrical bypass inlet pipe 68a at two locations in the axial direction relative to the blade ring portion 50a of one upper half. The bypass inlet pipe 68a is provided with an opening 68aa connected to the cooling medium circulation mechanism 80 on the radially outer side, and an opening 68ab connected to the bypass connecting pipe 68b on the radially inner side. The opening 68ab is connected to an opening 68ba formed on the outer peripheral surface of the bypass connecting pipe 68b. A part of the bypass connecting pipe 68b is inserted into the bypass inlet pipe 68a from a direction orthogonal to the bypass inlet pipe 68a, so that a part of the bypass inlet pipe 68a and a part of the bypass connecting pipe 68b are joined in a mutually penetrating manner. The bypass inlet pipe 68a and the bypass connecting pipe 68b are connected to each other via the opening 68ab of the bypass inlet pipe 68a and the opening 68ba formed in the bypass connecting pipe 68b.

[0159] The bypass connection pipe 68b is arranged in an annular shape along the outer surface of the radially outer side of the tail cylinder connection portion 54 and in the axial direction, and is fixed to the tail cylinder connection portion 54. In addition, the bypass connection pipe 68b is arranged on the upstream side in the axial direction so as to be close to the side surface 53e of the upstream inner partition wall portion 53 facing the upstream side in the axial direction, but the two are arranged separately so as not to contact each other. The two are separated to prevent the blade ring portion main body 50a from being cooled by the cooling medium P flowing in the bypass flow path 68, thereby preventing the temperature distribution from being generated in the blade ring portion main body 50a.

[0160] In addition, as described above, the bypass connection pipe 68b extending in the axial direction is connected to a plurality of bypass inlet pipes 68a and a plurality of inlet connection pipes 68d connected to the tail cylinder connection portion 54. The bypass connection pipe 68b is formed by a plurality of connection pipes. On both sides of the bypass connection pipe 68b in the axial direction sandwiching the bypass inlet pipe 68a and the inlet connection pipe 68d, a thermal expansion absorbing portion 68 is arranged to absorb the thermal expansion of the bypass connection pipe 68b in the axial direction. As an example, a bellows or a U-shaped pipe deformed in the axial direction can be used for the thermal expansion absorbing portion 68c, but it is not limited to this example. The reason for providing the thermal expansion absorbing portion 68c is that the bypass inlet pipe 68a and the tail cylinder connection portion 54 are fixed to the blade ring portion main body 50a, so the portion where the bypass connection pipe 68b is connected to the bypass inlet pipe 68a and the inlet connection pipe 68d cannot absorb the thermal expansion of the bypass connection pipe 68b in the axial direction.

[0161] One end of the inlet connecting pipe 68 d communicates with the bypass connecting pipe 68 b , and the other end communicates with the discharge flow path 54 c formed in the tail cylinder connecting portion 54 via the bypass connecting hole 54 b .

[0162] Figure 5: is a system diagram showing the flow of the cooling flow path 60 of the blade ring part 50. As described above, the first cooling flow path 61 arranged on the outer peripheral surface side of the cylindrical part 51 of the blade ring part 50 is connected to the first communication flow path 71 formed in an annular shape along the axial direction on the upstream side in the axial direction, and is connected to the return communication flow path 75 formed in an annular shape along the axial direction on the downstream side in the axial direction. In addition, the cooling medium P flowing into the return communication flow path 75 is turned back in the radially inner direction in the return communication flow path 75, and flows into the second cooling flow path 62. The second cooling flow path 62 is arranged on the radially inner side of the first cooling flow path 61, and is arranged close to the inner peripheral surface of the cylindrical part 51 of the blade ring part 50. The second cooling flow path 62 is arranged in parallel with the first cooling flow path 61 in the axial direction, is connected to the return communication flow path 75 formed in an annular shape along the axial direction on the downstream side in the axial direction, and is connected to the second communication flow path 72 on the upstream side in the axial direction.

[0163] Figure 5 In the example shown, two first cooling channels 61 and two second cooling channels 62 are arranged as a group. Before and after the axial direction of a group of cooling channels that combine the first cooling channels 61 and the second cooling channels 62, the cavity supply channel 55 (described later) is Figure 7 ) are arranged close to each other in the axial direction so as to sandwich the cooling flow path. Figure 5 Although not shown, for the cooling flow path blocks arranged in the axial direction and composed of two first cooling flow paths 61 and two second cooling flow paths 62, multiple blocks are arranged in a manner corresponding to the positions of multiple cavity supply flow paths 55 arranged in the axial direction.

[0164] The first communication flow path 71 includes a plurality of intake flow paths 66 connected to the cooling medium circulation mechanism 80. In addition, the second communication flow path 72 is connected to the discharge flow path 54c extending to the upstream side in the axial direction. A plurality of discharge flow paths 54c are arranged in the circumferential direction in a manner corresponding to the position of the tail pipe 12a of the combustor 12, and are connected to the discharge pipe 82 on the upstream side in the axial direction.

[0165] The bypass flow path 68 is arranged at a position radially outward from the discharge flow path 54c and is formed in an annular shape along the axial direction. The bypass flow path 68 includes a plurality of bypass inlet pipes 68a connected to the cooling medium circulation mechanism 80. In addition, the bypass flow path 68 includes a bypass connecting pipe 68b formed in an annular shape, and has an inlet connecting pipe 68d connected to the bypass connecting pipe 68b and the tail cylinder connecting portion 54, and the inlet connecting pipe 68d is connected in a manner corresponding to the position of the tail cylinder connecting portion 54 in the axial direction.

[0166] Figure 6 : is a system diagram showing a modified example of the flow of the cooling flow path 60 of the present embodiment. That is, Figure 6The cooling flow path 60 shown is a folded communication path 75 from Figure 5 An example of a cooling flow path 60 shown in FIG. 1 is removed. That is, in this modified example, a return flow path 65 formed as a rectangular space (cavity) extending long in the radial direction is provided on the downstream side of the cylindrical portion 51 in the axial direction. The first cooling flow path 61 is connected to the return flow path 65 on the radially outer side, and the second cooling flow path 62 is connected to the return flow path 65 on the radially inner side. The return flow path 65 is radially arranged with the rotation axis C as the center in a manner corresponding to the position of a group of first cooling flow paths 61 and second cooling flow paths 62 arranged in the axial direction. The other cooling flow paths 60 are formed with the same structure as the first embodiment.

[0167] Figure 7 It is shown along Figure 3 The structure of the AA section in FIG. Figure 7 As shown, the first cooling flow path 61 and the second cooling flow path 62 are arranged on an imaginary straight line L1 extending radially from the rotation axis C. The blade ring portion 50 has a cavity supply flow path 55 that penetrates in the radial direction. The first cooling flow path 61 and the second cooling flow path 62 are arranged at positions corresponding to the cavity supply flow path 55. In the present embodiment, the first cooling flow path 61 and the second cooling flow path 62 are adjacently arranged in the axial direction in a manner of sandwiching both sides of the cavity supply flow path 55. However, the upstream side of the cavity supply flow path 55 is connected to the turbine chamber space 26a. A portion of the aforementioned exhaust air supplied to the turbine chamber space 26a flows in the cavity supply flow path 55 and is used to cool high-temperature components such as the stator blades 27. That is, the temperature of the compressed air flowing in the cavity supply flow path 55 becomes a temperature higher than that of the cooling medium P supplied to the cooling flow path 60 of the blade ring portion 50. With this structure, the heat transferred from the compressed air flowing in the cavity supply flow path 55 to the blade ring portion 50 is directly cooled by the cooling medium P flowing in the first cooling flow path 61 and the second cooling flow path 62. As a result, the heat transfer from the cavity supply flow path 55 to the inside of the blade ring portion 50 can be blocked, thereby suppressing the occurrence of temperature distribution in the blade ring portion 50.

[0168] It should be noted that if Figure 2As shown, the cooling medium P supplied to the blade ring portion 50 is supplied from a cooling medium circulation mechanism 80 provided separately. The cooling medium circulation mechanism 80 includes a cooler 84, a compressor 85, and a three-way valve (supply destination switching unit) 86. The cooler 84 takes in the engine room air (cooling medium P) around the combustor 12 and cools it, and then sends it to the compressor 85. The compressor 85 compresses the air from the cooler 84 and sends it to the three-way valve 86. The three-way valve 86 is connected to the above-mentioned compressor 85, the supply piping 81, and the bypass piping 83. The supply piping 81 is connected to the intake flow path 66 of the blade ring portion 50, and the bypass piping 83 is connected to the bypass inlet pipe 68a. The three-way valve 86 can switch the air from the compressor 85 to be supplied to the piping 81 or the bypass piping 83. Therefore, when the gas turbine 100 is in steady-state operation, the three-way valve 86 is switched so that the cooling medium P flows toward the supply pipe 81 to supply the cooling medium P to the blade ring portion 50. When the gas turbine 100 is started, the supply of the cooling medium P to the blade ring portion 50 is unnecessary, so the three-way valve 86 is switched so that the cooling medium P flows toward the bypass pipe 83.

[0169] In the blade ring 50 configured as described above, the cooling medium P supplied from the supply pipe 81 flows into the inside of the blade ring body 50a. The cooling medium P flowing into the inside of the blade ring body 50a flows along the cooling flow path 60 and the communication flow path 70, absorbs the heat of the blade ring body 50a, and is discharged from the discharge pipe 82.

[0170] Specifically, the cooling medium P taken into the inside of the blade ring body 50a is supplied to the first connecting flow path 71 via the intake flow path 66. The cooling medium P flows in the axial direction inside the first connecting flow path 71 and is supplied in a manner that covers the entire axial direction of the first connecting flow path 71. In addition, the cooling medium P flows from the first connecting flow path 71 to the first cooling flow path 61. The cooling medium P flows toward the turbine 13 side in the axial direction in the first cooling flow path 61 and is supplied to the return flow path 65 (the return connecting flow path 75).

[0171] The cooling medium P supplied to the return communication flow path 75 flows in the circumaxial direction inside the return communication flow path 75. Figure 6 In the case of the modified example of the first embodiment shown in FIG. 7 which does not include the return communication flow path 75 , the cooling medium P supplied to the return flow path 65 flows radially inward along the return flow path 65 and is supplied to the second cooling flow path 62 .

[0172] The cooling medium P supplied to the second cooling flow path 62 flows in the second cooling flow path 62 toward the combustor 12 side along the axial direction, and is supplied to the second communication flow path 72. In this way, in the blade ring portion 50, the first cooling flow path 61 and the second cooling flow path 62 arranged in a radial direction form an opposing flow path for the cooling medium P to flow in the opposite direction along the axial direction. Therefore, in the blade ring portion 50, multiple stages of the flow of the cooling medium P are formed in the radial direction.

[0173] The cooling medium P supplied to the second communication flow path 72 flows in the axial direction inside the second communication flow path 72, and is supplied so as to cover the entire axial direction of the second communication flow path 72. In addition, the cooling medium P is discharged from the second cooling flow path 62, gathers in the second communication flow path 72, and flows to the discharge flow path 54c. The cooling medium P flows from the discharge flow path 54c to the discharge pipe 82, and is supplied to the cooling flow path (not shown) of the combustor 12.

[0174] Furthermore, when the gas turbine is started, the cooling medium P is not supplied to the blade ring body 50a but flows to the bypass flow path 68, and is discharged to the discharge pipe 82 via the discharge flow path 54c. At this time, the bypass flow path 68 does not come into contact with the blade ring body 50a, so when the gas turbine is started, the blade ring body 50a is cooled by the bypass flow path 68, and a temperature distribution is not formed inside the blade ring body 50a.

[0175] The manufacturing process of the blade ring 50 of the present embodiment is described below. First, the blade ring body 50a is made by casting or sheet metal. In this process, in the cylindrical portion 51 and the upstream inner partition wall portion 53 constituting the blade ring body 50a, the first connecting flow path 71 and the return flow path 65 (the return connecting flow path 75) for connecting each cooling flow path and arranged at the end in the axial direction are formed into an annular groove along the axial direction by mechanical processing. Next, the first cooling flow path 61 and the second cooling flow path 62 are formed by mechanical processing based on perforation. For the first cooling flow path 61, the perforation processing is performed from the return flow path 65 (the return connecting flow path 75) side toward the first connecting flow path 71 side. For the second cooling flow path 62, the perforation processing is performed from the return flow path 65 (the return connecting flow path 75) side toward the second connecting flow path 72 side, and the flow path opening 51e formed in the second connecting flow path is opened. Next, the first blocking member (cover plate 71a), the second blocking member (tail cylinder connection portion 54) and the cover plate 65a are mounted on the blade ring portion body 50a by welding, thereby forming the closed flow paths, namely the first communication flow path 71, the second communication flow path 72 and the return flow path 65 (the return communication flow path 75). Next, the bypass flow path 68 is mounted on the tail cylinder connection portion 54 fixed to the blade ring portion body 50a. Through this manufacturing process, the assembly of the blade ring portion 50 is completed.

[0176] As described above, in the gas turbine 100 of the present embodiment, in the blade ring portion 50, a plurality of first cooling channels 61 are arranged in the axial direction on the radially outer side, and a plurality of second cooling channels 62 are arranged in the axial direction on the radially inner side. In addition, the ends of the first cooling channels 61 and the second cooling channels 62 on the same side in the axial direction are folded back by the folded channels 65. Therefore, a plurality of cooling channels 60 arranged in the axial direction can be arranged in multiple stages in the radial direction. As a result, the blade ring portion 50 is cooled in the range of multiple locations in the radial direction, so that the formation of temperature distribution in the radial direction of the blade ring portion 50 can be suppressed.

[0177] <Second Embodiment>

[0178] Next, a second embodiment will be described. Figure 8 It is a cross-sectional view showing an example of a part of the blade ring portion 150 according to the second embodiment. Fig. 9 It is a perspective view showing an example of the blade ring portion 150 according to the present embodiment. Fig.10 It is a system diagram of the cooling flow path 160 according to the present embodiment. Fig.11 It is shown along Fig. 9 The second embodiment is mainly aimed at further strengthening the cooling of the upstream area of ​​the intake flow path 66 at the upstream inner partition wall portion 153 of the blade ring body 150a and the upstream side of the cylindrical portion 151 in the axial direction, and is different from the first embodiment in that three stages of cooling flow paths 160 are provided in the radial direction. In the second embodiment, the description will be centered on the differences from the first embodiment. It should be noted that the same components as those of the blade ring 50 of the first embodiment are marked with the same reference numerals, and the description is omitted or simplified.

[0179] like Figure 8 As shown in FIG. 1 , the blade ring 150 includes a blade ring body 150a, a tail cylinder connection portion 154, and a bypass flow path 168. Furthermore, the blade ring body 150a includes a cylindrical portion 151, a downstream inner partition wall portion 152, and an upstream inner partition wall portion 153. Compared with the blade ring body 50a of the blade ring 50 of the first embodiment, in the blade ring body 150a of the blade ring 150 of the present embodiment, for example, the radial thickness of the upstream inner partition wall portion 153 becomes thicker toward the radial outer side. In addition, the cylindrical portion 151 on the radial inner side of the upstream inner partition wall portion 153 has a cross-sectional shape that becomes thicker toward the upstream side in the axial direction and toward the radial inner side.

[0180] The cylindrical portion 151 has a cooling flow path 160 and a connecting flow path 170 for the cooling medium P to flow. The cooling flow path 160 has a first cooling flow path 161, a second cooling flow path 162, and a return flow path 165 (a return connecting flow path 175) for connecting the first cooling flow path 161 and the second cooling flow path 162. The connecting flow path 170 has a first connecting flow path 171 and a second connecting flow path 172. It should be noted that the first connecting flow path 171 in the present embodiment is connected to the first cooling flow path 161 on the radial inner side of the first connecting flow path 171, and is connected to the third cooling flow path 163 described later on the radial outer side. In addition, the return flow path 165 (the return connecting flow path 175) can be an annular flow path extending in the axial direction like the return flow path 75 in the first embodiment.

[0181] In the present embodiment, the second cooling flow path 162 has an upstream flow path 162a connected to the return flow path 165 (return communication flow path 175), and a downstream flow path 162b connected to the second communication flow path 172 via a flow path opening (second opening) 151e, which is different from the first embodiment. The upstream flow path 162a extends linearly from the connection portion of the upstream flow path 162a and the return flow path 165 (return communication flow path 175), that is, the flow path opening (first opening) 151d, toward the upstream side in the axial direction, in a state of being inclined inward in the radial direction. In addition, the upstream flow path 162a changes the extension direction at the middle point, that is, the Q point, and bends radially outward to bend, and then connects to the downstream flow path 162b. The downstream flow path 162b further extends to the upstream side in the axial direction, and connects to the second communication flow path 172 via the flow path opening 151e. That is, the second cooling flow path 162 is formed as a bent flow path that bends radially outward at the midpoint Q. That is, the center of the flow path opening 151d is formed at a position radially outward than the center of the flow path opening 151e. In addition, the center of the flow path opening 151e can also be formed at a position radially inward than the bottom surface 165b on the radial inner side of the return flow path 165 (the return connecting flow path 175). In this structure, in the cylindrical portion 151, a flow path can be formed at a position radially inward than the second cooling flow path 62 of the first embodiment, thereby further strengthening the cooling near the inner circumferential surface 151b of the cylindrical portion 151.

[0182] Alternatively, the second cooling channel 162 may be formed in a straight line from the channel opening 151d to the channel opening 151e. Such a structure is easier to maintain and process than a bent channel.

[0183] In addition, in the present embodiment, the upstream inner partition wall portion 153 of the blade ring portion main body 150a also has a third cooling flow path 163. The third cooling flow path 163 is arranged at a position radially more outward than the first cooling flow path 161. The third cooling flow path 163 extends in the axial direction, and a plurality of the third cooling flow paths 163 are arranged in an axial direction. In addition, the first connecting flow path 171 also serves as a second return flow path that connects the ends of the third cooling flow path 163 and the first cooling flow path 161 on the same side of the axial direction. Fig.11 As shown, the third cooling channel 163, the first cooling channel 161, and the second cooling channel 162 are arranged on an imaginary straight line L2 extending radially from the rotation axis C. It should be noted that the third cooling channel 163 only needs to be evenly arranged in the axial direction at a position radially outer than the first cooling channel 161, and may not be arranged on the imaginary straight line L2.

[0184] In addition, in the present embodiment, the connecting flow path 170 further includes a third connecting flow path 173. The third connecting flow path 173 connects the third cooling flow paths 163 arranged in the axial direction to each other in the axial direction. The third connecting flow path 173 is arranged inside the upstream inner partition wall portion 153. The third connecting flow path 173 is connected to the intake flow path 66 for supplying the cooling medium P. It should be noted that the other structures of the cooling flow path 160 and the connecting flow path 170 are substantially the same as the cooling flow path 60 and the connecting flow path 70 in the first embodiment.

[0185] The system diagram of the flow of the cooling flow path 160 of this embodiment is as follows Fig.10 The system diagram of this embodiment adds a third cooling channel 163 and a third connecting channel 173, and the shape of the second cooling channel 162 has a bent shape ( Figure 8 ), which is different from the cooling flow path 60 of the first embodiment, but the other structures are the same as the first embodiment. Fig.10 In the embodiment, as a flow path connecting the first cooling flow path 161 and the second cooling flow path 162, a return communication flow path 175 is arranged at the end portion on the downstream side in the axial direction. Figure 6 Similarly to the modified example of the first embodiment shown, the return communication flow path 175 may not be provided, but the return flow path 165 formed as a rectangular space (cavity) extending long in the radial direction may be provided.

[0186] In addition, in the present embodiment, the blade ring portion 150 has a tail cylinder connection portion 154 at the end portion on the combustor 12 side, on the upstream side in the axial direction of the cylindrical portion 151. A plurality of tail cylinder connection portions 154 are arranged in a row in the axial direction. The tail cylinder connection portion 154 has: a tail cylinder side communication hole 154a, which is connected to a cooling flow path (not shown) formed on the tail cylinder 12a side via the exhaust pipe 82; a bypass connection hole 154b, which is connected to a bypass flow path 168 (described later); and a discharge flow path 154c, which collects the cooling medium P after cooling the cooling flow path 160 in the second communication flow path 172, and is connected to the tail cylinder side communication hole 154a.

[0187] As in the first embodiment, the bypass flow path 168 includes: a bypass inlet pipe 68a that receives the cooling medium P from the aforementioned cooling medium circulation mechanism 80; a bypass connecting pipe 168b that is annularly arranged along the axial direction on the upstream side of the cylindrical portion 151 and supplies the cooling medium P to the tail cylinder connecting portion 154; a thermal expansion absorbing portion 168c that absorbs the thermal expansion of the bypass connecting pipe 168b; and an inlet connecting pipe 168d that connects the bypass connecting pipe 168b to the bypass connecting hole 154b formed in the tail cylinder connecting portion 154. The bypass connecting pipe 168b is arranged in a manner that is away from the side surface 153e of the upstream end in the axial direction of the upstream inner partition wall portion 153 in the axial direction. Therefore, the flow of the cooling medium P flowing in the bypass flow path 168 does not affect the temperature distribution of the blade ring portion main body 150a. The detailed structure of the bypass flow path is the same as that of the first embodiment, and a detailed description is omitted.

[0188] The manufacturing process of the blade ring portion 150 of the present embodiment is described below. First, the blade ring portion main body 150a is made by casting or sheet metal. In this process, in the cylindrical portion 151 and the upstream inner partition wall portion 153 constituting the blade ring portion main body 150a, a connecting flow path 170 for connecting each cooling flow path 160 and arranged at the end in the axial direction is formed by machining. That is, an annular groove portion extending in the circumaxial direction is machined, and the annular groove portion forms a first connecting flow path 171, a second connecting flow path 172, and a return flow path (a return connecting flow path 175). By machining, the annular groove portion is formed into a groove shape that is recessed from the upstream end in the axial direction of the cylindrical portion 151 to the downstream side in the axial direction, or a groove shape that is recessed from the downstream end in the axial direction of the cylindrical portion 151 to the upstream side. Furthermore, an annular groove portion that forms the third connecting flow path 173 and extends in the axial direction is formed in the partition groove portion 153a of the upstream inner partition portion 153 by mechanical processing. The groove portion of the third connecting flow path 173 is formed as a recessed portion that is recessed from the bottom surface 153c toward the radial inner side along the axial direction of the partition groove portion 153a. Next, the first cooling flow path 161 and the third flow path 173 are formed by mechanical processing based on punching. For the first cooling flow path 161, punching processing is performed from the first connecting flow path 171 side toward the return flow path 165 (return connecting flow path 175) side. For the third cooling flow path 163, punching processing is performed from the first connecting flow path 171 side toward the third connecting flow path 173 side. Next, the second cooling flow path 162 is formed by mechanical processing based on two-stage punching. That is, in Figure 8 In the first stage, the second cooling flow path 162a is formed by mechanical processing based on perforation from the return flow path 165 or the return connecting flow path 175 toward the Q point on the upstream side in the axial direction. Next, as the second stage, perforation processing is performed by mechanical processing from the second connecting flow path 172 side toward the Q point on the downstream side in the axial direction. When reaching the Q point, the second cooling flow paths 162a and 162b are combined to form the overall flow path of the second cooling flow path 162. Next, the first blocking member (cover plate 171a), the second blocking member (tail cylinder connection part 154) and the cover plate 173a or the cover plate 165a or the cover plate 175a are installed on the blade ring body 150a by welding processing to form a closed flow path, namely the first connecting flow path 171, the second connecting flow path 172 and the return flow path 165 or the return connecting flow path 175. Next, the bypass flow passage 168 is mounted on the tail cylinder connection portion 154 fixed to the blade ring portion main body 150a. Through this manufacturing process, the assembly of the blade ring portion 150 is completed.

[0189] As described above, in the blade ring 150 of this embodiment, three or more stages of cooling channels 160 arranged in the circumferential direction can be radially arranged. Thus, the blade ring 150 is effectively cooled in the radial direction, and the formation of a temperature distribution in the blade ring 150 in the radial direction can be more effectively suppressed.

[0190] In addition, in the blade ring portion 150 of the present embodiment, when the gas turbine 100 is started, the cooling medium P can be made to bypass the blade ring portion main body 150a and flow efficiently to the tail pipe 12a side through the bypass flow path 168. Therefore, it is possible to operate the gas turbine 100 without affecting the temperature distribution of the blade ring portion main body 150a, thereby shortening the start-up time of the gas turbine 100. In addition, the bypass connecting pipe 168b is provided with the heat expansion absorbing portion 168c, so that the thermal stress generated in the bypass connecting pipe 168b can be suppressed.

[0191] <Third Embodiment>

[0192] Next, a third embodiment will be described. Fig.12 It is a cross-sectional view showing an example of a part of the blade ring portion 250 according to the third embodiment. Fig.13 2 is a perspective view showing an example of a blade ring portion 250. In the third embodiment, the structure of a part of the blade ring portion 250 is different from that of the second embodiment, so the description will be centered on the differences from the second embodiment. It should be noted that the same reference numerals are given to the same components as those of the blade ring portion 150 of the second embodiment, and the description is omitted or simplified.

[0193] like Fig.12 as well as Fig.13 As shown in FIG. 1 , the blade ring 250 of the present embodiment includes a blade ring body 250a, a tail cylinder connection portion 254 (second blocking member), and a bypass flow path 268. Furthermore, the blade ring body 250a includes a cylindrical portion 251, a downstream inner partition wall portion 252, an upstream inner partition wall portion 253, and a first blocking member 251c. In the present embodiment, the following structure is adopted: with respect to the cylindrical portion 251 or the upstream inner partition wall portion 253 of the blade ring body 250a, the blocking member 251c is fixed to a position corresponding to the radial first communication flow path 271 by a fixing member BT such as a bolt so as to be detachable from the upstream side in the axial direction. In addition, the tail cylinder connecting portion 254 (second blocking member) is connected to the end portion of the cylindrical portion 251 protruding to the upstream side in the axial direction, but similarly to the blocking member 251c, the connection between the tail cylinder connecting portion 254 and the cylindrical portion 251 is configured to be attachable and detachable from the upstream side in the axial direction by a fixing member BT such as a bolt.

[0194] Similar to the second embodiment, the cooling channel 260 of the blade ring body 250a includes a first cooling channel 261, a second cooling channel 262, a third cooling channel 263, and a return channel 265 (a return communication channel 275). In this embodiment, similar to the second embodiment, the second cooling channel 262 includes an upstream channel 262a connected to the return channel 265 (a return communication channel 275), and a downstream channel 262b connected to the second communication channel 272 via a channel opening (a second opening) 251e. The upstream channel 262a extends linearly from the connection portion between the upstream channel 262a and the return channel 265 (a return communication channel 275), that is, the channel opening (a first opening) 251d, toward the upstream side in the axial direction, while being inclined radially inward. In addition, the upstream flow path 262a changes its extension direction at the middle point Q and bends radially outward to bend, and then connects to the downstream flow path 262b. The downstream flow path 262b further extends to the upstream side in the axial direction and connects to the second connecting flow path 272 via the flow path opening 251e. That is, the second cooling flow path 262 forms a bent flow path that bends radially outward at the middle point Q. That is, the center of the flow path opening 251d is formed at a position that is radially outward than the center of the flow path opening 251e. In addition, the center of the flow path opening 251e can also be formed at a position that is radially inward than the bottom surface 265b on the radial inner side of the return flow path 265 (the return connecting flow path 275). In this structure, in the cylindrical portion 251, a flow path can be formed at a position that is radially inward than the second cooling flow path 62 of the first embodiment, so that the cooling near the inner peripheral surface 251b of the cylindrical portion 251 can be further strengthened. In addition, the second cooling flow path 262 may also be formed in a straight line from the flow path opening 251d to the flow path opening 251e. If such a structure is adopted, maintenance is easier and processing is also easier than a bent flow path. In addition, the connecting flow path 270 of the blade ring body 250a includes a first connecting flow path 271, a second connecting flow path 272, and a third connecting flow path 273.

[0195] In addition, the first communication flow path 271 of the blade ring body 250 is formed in an annular groove shape along the axial direction as a first groove portion 257 opening toward the upstream side in the axial direction at the end portion 253e of the upstream side of the cylindrical portion 251 or the upstream side inner partition wall portion 253 in the axial direction. The second communication flow path 272 is formed in an annular groove shape along the axial direction as a second groove portion 258 opening toward the upstream side in the axial direction at the end portion 251f of the upstream side of the cylindrical portion 251 in the axial direction. The first groove portion 257 is blocked by the first blocking member 251c, so that the annular first communication flow path 271 is formed between the first blocking member 251c and the first groove portion 257. Similarly, the second groove portion 258 is blocked by the tail cylinder connection portion 254 (second blocking member), so that the annular second communication flow path 272 is formed between the tail cylinder connection portion 254 and the second groove portion 258.

[0196] In addition, the structure of the tail cylinder connection part 254 and the bypass flow path 268 in this embodiment is the same as that of the second embodiment. It should be noted that the tail cylinder connection part 254 adopts a structure that can be loaded and unloaded, so the bypass flow path 268 connected to the tail cylinder connection part 254 also adopts a structure that can be loaded and unloaded. That is, the bypass inlet pipe 68a, the bypass connection pipe 268b, the thermal expansion absorption part 268c, and the inlet connection pipe 268d that constitute the bypass flow path 268 are also structures that are easy to disassemble and can be loaded and unloaded. In addition, the bypass connection pipe 268b is configured in a manner that the side surface 253e of the upstream end in the axial direction away from the upstream inner partition wall part 253 in the axial direction. Therefore, the flow of the cooling medium P flowing in the bypass flow path 268 will not affect the temperature distribution of the blade ring part main body 250a. The other structures are the same as those of the second embodiment.

[0197] Fig.14A flowchart of the manufacturing process of the blade ring portion in the present embodiment is shown. First, the blade ring portion main body 250a is manufactured by casting or sheet metal, etc. (S1). In this process, in the cylindrical portion 251 and the upstream inner partition wall portion 253 constituting the blade ring portion main body 250a, a connecting flow path 270 for connecting each cooling flow path 260 and arranged at the end in the axial direction is formed by machining. Specifically, the first groove portion 257 forming the first connecting flow path 271 and the second groove portion 258 forming the second connecting flow path 272 are formed by machining. The first groove portion 257 and the second groove portion 258 are recessed portions that are recessed from the upstream end in the axial direction of the upstream inner partition wall portion 253, i.e., the side surface 253e or the upstream end in the axial direction of the cylindrical portion 251 toward the downstream side in the axial direction, and are formed into an annular groove shape extending in the circumaxial direction by machining. In addition, the third communication flow path 273 is a recessed portion that is recessed radially inward from the bottom surface 253c of the partition groove portion 253a on the radial outer surface side of the upstream inner partition portion 253, and is formed into an annular groove extending in the axial direction by mechanical processing. The return flow path 265 or the return communication flow path 275 is a recessed portion that is recessed from the outer surface side of the downstream end surface in the axial direction of the cylindrical portion 251 toward the upstream side in the axial direction, and is formed into an annular groove extending in the axial direction by mechanical processing.

[0198] Next, the first cooling channel 261 and the third cooling channel 263 are formed by mechanical processing based on perforation (S2). For the first cooling channel 261, perforation processing is performed from the first groove portion 257 side toward the return connecting channel 275 side. For the third cooling channel 263, perforation processing is performed from the first groove portion 271 side toward the third connecting channel 273 side. In addition, the intake channel 66 formed on the downstream side of the axial direction of the upstream inner partition portion 253 is formed from the downstream inner partition portion 252 side toward the third connecting channel 273 by perforation processing.

[0199] Next, the second cooling channel 262 is formed by two-stage drilling machining (S3). Fig.12 In the first stage, the second cooling channel 262a is formed by machining based on perforation from the return channel 265 or the return connecting channel 275 toward the Q point on the upstream side in the axial direction. Next, as the second stage, perforation processing is performed from the second groove 258 side toward the Q point on the downstream side in the axial direction. When reaching the Q point, the second cooling channels 262a and 262b are combined to form the entire channel of the second cooling channel 262. In this stage, the cavities (connecting channels) connecting the cooling channels 260 and the cooling channels 260 are formed.

[0200] Next, the first blocking member 251c is installed in the first groove 257 to form the first communication flow path 271 (S4). That is, the first blocking member 251c is bolted to the position of the first groove 257 forming the first communication flow path 271 in a detachable manner, thereby blocking the first groove 257. In addition, the cover plates 273a, 265a, 275a, etc. that form the cavities of each communication flow path are installed on the leaf ring body 250a by welding. Thus, the closed first communication flow path 271, the third communication flow path 273, and the return communication flow path 275 are formed.

[0201] Next, the second blocking member (transition sleeve connection portion 254) is attached to the second groove portion 258 to form the second communication flow path 272. That is, the transition sleeve connection portion 254 is detachably attached to the position of the second groove portion 258 formed in the cylindrical portion 251 of the blade ring portion main body 250a by bolt fastening, thereby blocking the second groove portion 258. Thus, the closed second communication flow path 272 is formed.

[0202] Next, the bypass flow path 268 is mounted on the tail cylinder connection portion 254 fixed to the blade ring portion main body 250a. Through this manufacturing process, the assembly of the blade ring portion 250 is completed.

[0203] It should be noted that the blade ring portion 250 of the present embodiment can easily release the first groove portion 257 and the second groove portion 258 by removing the tail cylinder connection portion 254 (second blocking member), the bypass flow path 268, and the first blocking member 251c that are installed in a detachable manner. Therefore, the internal inspection of the first cooling flow path 261 and the third cooling flow path 263 can be performed from the first communication flow path 271 side. In addition, the internal inspection of the second cooling flow path 262 can be performed from the second communication flow path 272 side. That is, the first blocking member and the second blocking member adopt a detachable structure, so that when maintaining the gas turbine, the internal inspection of all cooling flow paths 260 (the first cooling flow path 261, the second cooling flow path 262, and the third cooling flow path 263) can be easily performed.

[0204] Thus, in the present embodiment, by fastening the tail cylinder connection portion 254 (second blocking member) and the first blocking member 251c to the blade ring portion main body 250a, the blade ring portion main body 250a can be easily formed. In addition, when the gas turbine is maintained, the tail cylinder connection portion 254, the bypass flow path 268 and the first blocking member 251c are removed from the blade ring portion main body 250a, and the first groove portion 257 and the second groove portion 258 can be easily exposed to the outside. Therefore, the internal inspection of all cooling flow paths 260 (first cooling flow path 261, second cooling flow path 262, third cooling flow path 263) can be performed, and the maintenance work becomes easy.

Claims

1. A gas turbine comprising: A compressor, which compresses the air; a combustor that mixes fuel with the compressed air compressed by the compressor and burns the fuel; a turbine that is rotated by combustion gases generated by the combustor; a rotor having a rotor body that rotates in a periaxial direction of a rotating shaft by the rotation of the turbine, and a plurality of moving blade segments fixed to the rotor body in a manner arranged in an axial direction of the rotating shaft; a housing covering an outer peripheral side of the rotor; a plurality of stationary blade segments fixed to the inner peripheral side of the casing and arranged on the upstream side of each of the plurality of moving blade segments; as well as a plurality of blade rings, which are provided on the housing, are formed in a ring shape with the rotating shaft as the center, and cover the moving blade segment and the stationary blade segment; The plurality of leaf ring portions have: A plurality of first cooling channels are arranged on the outer side in the radial direction around the rotating shaft, extend along the axial direction, and are arranged in the circumaxial direction; a plurality of second cooling channels, which are arranged at a position further inward in the radial direction than the first cooling channels, extend along the axial direction, and are arranged in the circumaxial direction; a return flow path connecting the ends of the first cooling flow path and the second cooling flow path on the same side of the axial direction; a plurality of third cooling channels, which are arranged at a position further outward in the radial direction than the first cooling channels, extend along the axial direction, and are arranged in the circumaxial direction; a second return flow path connecting the third cooling flow path and the first cooling flow path at ends on the same side of the axial direction; as well as A flow path is provided along the cavity penetrating in the radial direction, through which compressed air compressed by the compressor and used for cooling the stationary blade segment flows. The first cooling flow path and the second cooling flow path are arranged at positions corresponding to the cavity supply flow path with the cavity supply flow path interposed therebetween.

2. The gas turbine according to claim 1, wherein: The first cooling flow path and the second cooling flow path are formed in the blade ring body. The second cooling flow path is connected to the return flow path at a first opening, and the second cooling flow path is connected to the second opening at the end on the upstream side in the axial direction of the blade ring body, and the center of the first opening is arranged at a radially outer position than the center of the second opening.

3. The gas turbine according to claim 2, wherein: The center of the second opening is arranged radially inward of a bottom surface of the return flow path that faces radially inward.

4. The gas turbine according to claim 2, wherein: The second cooling flow path is a bent flow path that bends radially outward in the middle of a flow path extending in the axial direction.

5. The gas turbine according to claim 1, wherein: The blade ring portion includes a first communication flow path that connects the first cooling flow paths with each other in the circumferential direction, and a second communication flow path that connects the second cooling flow paths with each other in the circumferential direction.

6. The gas turbine according to claim 5, wherein: The first communication flow path is connected to a supply pipe for supplying a cooling medium. The second communication flow path is connected to a discharge pipe for discharging the cooling medium.

7. The gas turbine according to claim 6, wherein: The discharge pipe is connected to a cooling flow path of the burner.

8. The gas turbine according to claim 7, wherein: The gas turbine also has: a bypass flow path that bypasses the blade ring portion and connects the supply pipe and the discharge pipe; and A supply destination switching unit switches a supply destination of the cooling medium between the blade ring unit and the bypass flow path.

9. The gas turbine according to claim 8, wherein: The bypass flow path is arranged to be away from the blade ring body in the axial direction.

10. The gas turbine according to claim 8, wherein: The combustor has a tail pipe on the turbine side. The blade ring portion has a plurality of tail cylinder connecting portions arranged along the axial direction. The transition piece connection portion includes a bypass connection hole communicating with the bypass flow path, and a transition piece side communication hole communicating with a transition piece side of the combustor.

11. The gas turbine according to claim 10, wherein: The bypass flow path includes a bypass connecting pipe disposed along the circumferential direction of the blade ring portion.

12. The gas turbine according to claim 11, wherein: The bypass connection pipe includes a thermal expansion absorbing portion that can be deformed according to thermal deformation of the blade ring portion.

13. The gas turbine according to claim 10, wherein: The leaf ring portion has: A blade ring body, which is provided with the first cooling flow path, the second cooling flow path, the return flow path, a first groove portion, and a second groove portion; a first blocking member detachably fastened to the blade ring body and blocking the first groove to form the first communication flow path between the first blocking member and the first groove; and The transition piece connection portion is detachably fastened to the blade ring portion main body and blocks the second groove portion to form the second communication flow path between the transition piece connection portion and the second groove portion.

14. The gas turbine according to claim 1, wherein: In the blade ring portion, the return flow paths communicate with each other in the circumferential direction.

15. The gas turbine according to claim 1, wherein: The first cooling flow path and the second cooling flow path are arranged on a virtual straight line extending from the rotation axis in the radial direction.

16. The gas turbine according to claim 5, wherein: The blade ring portion has a partition wall portion protruding outward in the radial direction. The first communication flow path is arranged in the partition wall portion.

17. A method for manufacturing a blade ring portion, wherein a plurality of blade ring portions are provided on a cylindrical housing covering a rotor of a gas turbine, the blade ring portions are formed in a ring shape with a rotating shaft of the rotor as the center, and cover a moving blade segment and a stationary blade segment, the method comprising: The process of forming a blade ring body, wherein the blade ring body has: a plurality of first cooling channels, which are arranged on the radially outer side with the rotating shaft as the center, extend in the axial direction, and are arranged in the circumferential direction; a plurality of second cooling channels, which are arranged at a position closer to the radially inner side than the first cooling channels, extend in the axial direction, and are arranged in the circumferential direction; a plurality of third cooling channels, which are arranged at a position closer to the radially outer side than the first cooling channels, extend in the axial direction, and are arranged in the circumferential direction; a folded channel, which connects the first cooling channel, the second cooling channel, and the third cooling channel. The ends of the cooling flow path and the third cooling flow path on the same side of the axial direction are connected to each other; a first connecting flow path that connects the first cooling flow paths to each other in the axial direction; a second connecting flow path that connects the second cooling flow paths to each other in the axial direction; a third connecting flow path that connects the third cooling flow paths to each other in the axial direction; and a cavity supply flow path that is sandwiched by the first cooling flow path and the second cooling flow path and is arranged closely in the axial direction, and through which compressed air compressed by the compressor of the gas turbine used for cooling the stationary blade section flows; forming the first cooling flow path between the first connecting flow path and the return flow path; forming the second cooling flow path between the second communicating flow path and the return flow path in two stages; forming the third cooling flow path between the third communicating flow path and the first communicating flow path; a step of attaching a first blocking member for blocking the first communication flow path to the blade ring portion to form the first communication flow path; and A step of attaching a second blocking member for blocking the second communication flow path to the blade ring portion.

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