GAS TURBINE AND METHOD FOR RUNNING BLADE RING PRODUCTION PROCESS

Abstract

A gas turbine (100) with: a compressor (11) configured to compress air, a combustion chamber (12) configured to mix a fuel with compressed air, which is compressed by the compressor (11), and to burn the compressed air which is mixed with the fuel, a turbine (13) configured to be rotated by combustion gas generated by the combustion chamber (12), a rotor (32) comprising a rotor body configured to rotate in an axial direction of rotation of a rotation axis (C) by rotation of the turbine (13), and a plurality of rotor blade stages aligned in an axial direction of the rotation axis (C) and attached to the rotor body, a housing (26) that covers an outer circumferential side of the rotor (32), a plurality of guide vane stages attached to an inner circumferential side of the housing (26) and arranged on the respective upstream sides of the impeller vane stages, and a plurality of impeller ring parts (150;250) provided on the housing (26) are formed in a ring shape centered around the axis of rotation (C) and cover the impeller stages and the guide vane stages, each of the impeller ring parts (150;250) has: a plurality of first cooling flow passages (161;261) arranged on an outer surface in a radial direction centered on the axis of rotation (C), extending in the axial direction and aligned in the axial direction of rotation, a plurality of second cooling flow passages (162;262) arranged on an inner side in the radial direction with respect to the first cooling flow passages (161;261), extending in the axial direction and aligned in the axial direction of rotation, a first return flow passage (165;265) that connects the end parts of each of the first cooling flow passages (161;261) and the second cooling flow passages (162;262) on the same side in the axial direction, a plurality of third cooling flow passages (163;263) arranged on an outside in the radial direction with respect to the first cooling flow passages (161;261), extending in the axial direction and aligned in the axial direction of rotation, and a second return flow passage (171;271) that connects the end parts of the third cooling flow passages (163;263) and the first cooling flow passages (161;261) on the same side in the axial direction, a first connecting flow passage (171;271) that connects the first cooling flow passages (161;261) together in the axial direction of rotation, and a second connecting flow passage (172;272) that connects the second cooling flow passages (162;262) to each other in the axial direction of rotation, and a third connecting flow passage (173;273) which connects the third cooling flow passages (163;263) together in the axial direction of rotation.

Description

[0001] The present invention relates to a gas turbine and a method for manufacturing (production) rotor blade ring parts.

[0002] A gas turbine consists of a compressor, a combustor, and a turbine. The compressor draws in and compresses the air, transforming it into compressed air at high temperature and high pressure. The combustor feeds fuel into this compressed air to burn it. The turbine rotates through the high-temperature, high-pressure combustion gas produced by the combustion of the compressed air. The turbine's rotation converts heat energy into rotational energy.

[0003] This type of gas turbine includes a casing for covering an outer peripheral side of a rotor and a plurality of stationary blade stages fixed to an inner peripheral side of the casing and arranged on the respective upstream sides of a plurality of moving blade stages. A plurality of moving blade ring members are arranged on the inner peripheral side of the casing. These ring members are formed in a ring shape centered around the rotation axis and cover the moving blade stages and the stationary blade stages. A flow passage for circulating a cooling medium that cools the moving blade ring member is formed in each of the moving blade members in an axial direction of the rotation axis (see, for example, JP 5 457 965 B2).

[0004] The gas turbine described above is intended to prevent the formation of a temperature distribution in the rotor blade ring parts in a radial direction centered on the rotation axis.

[0005] From US 4 526 226 A an impingement-cooled cooling structure for use in a turbine shroud assembly is known, which has a plurality of cavities and guide plates for directing a cooling fluid within the shroud.

[0006] DE 11 2014 004 738 T5 discloses a gas turbine comprising a compressor, a combustor, and a turbine. The compressor is provided with a cooling air flow passage on an inner circumferential surface side of a blade ring so that it faces a leading end of a plurality of blade bodies in the blade ring. This cooling air flow passage is formed as a cavity inside the blade ring. The cooling air flow passage has a plurality of distributors arranged at predetermined intervals along the flow direction of the compressed air in an air path, and coupling paths that couple this plurality of distributors in series.Specifically, the first manifold formed at an intermediate position in the flow direction of the compressed air in the air path of the blade ring, the second manifold arranged on the upstream side in the flow direction of the compressed air in the air path of the blade ring, and the third manifold arranged on the downstream side in the flow direction of the compressed air in the air path of the blade ring are provided as the cooling air flow passage. The first manifold and the second manifold are coupled to each other by the first coupling paths, and the second manifold and the third manifold are coupled to each other by the second coupling paths. Each of the manifolds is formed as a cavity having a ring shape around the rotation axis of a rotor inside the blade ring.The plurality of first coupling paths that couple the first manifold and the second manifold are formed on the outer peripheral side of the blade ring at predetermined intervals in the circumferential direction. The plurality of second coupling paths that couple the second manifold and the third manifold are formed further on the inner peripheral side of the blade ring than the first coupling paths at predetermined intervals in the circumferential direction. While these first coupling paths and the second coupling paths are arranged in a staggered manner with an offset in the circumferential direction, these coupling paths may be arranged at the same positions in the circumferential direction.

[0007] In view of the foregoing, it is an object of the present invention to provide a gas turbine that can prevent or reduce the formation of a temperature distribution in a radial direction of the blade ring parts, and a method for manufacturing blade ring parts.

[0008] A gas turbine according to the present invention comprises the features of claim 1.

[0009] According to the present invention, a plurality of first cooling flow passages are arranged on the outer side in the axial rotation direction in the radial direction, a plurality of second cooling flow passages are arranged on the inner side in the axial rotation direction in the radial direction, and the first cooling flow passages and the second cooling flow passages are returned to end portions on the same side in the axial direction through a return flow passage. Thus, a plurality of cooling flow passages arranged in the axial rotation direction of the rotation axis can be arranged at a plurality of stages in the radial direction. In this way, a moving blade ring part is cooled via a plurality of points in the radial direction so that a temperature distribution is prevented from forming in the radial direction of the moving blade ring part.

[0010] Further, in the gas turbine described above, the first cooling flow passages and the second cooling flow passages may be formed in a moving blade ring part main body, and a center of a first opening at which the second cooling flow passages are connected to the return flow passage may be arranged on an outer side in the radial direction away from a center of a second opening at which the second cooling flow passages are opened to an end part of the moving blade ring part main body on an upstream side in the axial direction.

[0011] According to the present invention, the second cooling flow passages can be brought closer to an inner peripheral surface of a blade ring member main body, thereby further improving cooling of the inner peripheral surface.

[0012] Further, in the gas turbine described above, the center of the second opening may be located on an inner side in the radial direction away from a lower surface facing an inner side in the radial direction of the return flow passage.

[0013] Further, in the gas turbine described above, the second cooling flow passages may be curved flow passages that are curved outward in the radial direction at a center point of the flow passages extending in an axial direction.

[0014] According to the present invention, a flow passage may be formed in the vicinity of an inner peripheral surface of the further inside of a cylindrical part in the blade ring part, thereby further improving cooling of the inner peripheral surface of the blade ring part.

[0015] In the gas turbine according to the invention, each of the blade ring parts includes a first connecting flow passage connecting the first cooling flow passages to each other in the axial rotation direction, and a second connecting flow passage connecting the second cooling flow passages to each other in the axial rotation direction.

[0016] According to the present invention, a cooling medium can circulate in an axial rotation direction through a first connecting flow passage and a second connecting flow passage. Thus, a temperature distribution can be prevented from forming in an axial rotation direction of the blade ring part.

[0017] Further, in the gas turbine described above, the first communication flow passage may be connected to a supply pipe where a cooling medium is supplied, and the second communication flow passage may be connected to a discharge pipe where the cooling medium is discharged.

[0018] According to the present invention, a cooling medium flows through a supply pipe, the first connecting flow passage, the first cooling flow passages, the return flow passage, the second cooling flow passages, and the second connecting flow passage in this order, and is discharged from a discharge pipe. Thus, the blade ring part can be efficiently cooled from the outside to the inside in the radial direction.

[0019] Furthermore, in the gas turbine described above, the discharge pipe may be connected to a cooling flow passage of the combustion chamber.

[0020] According to the present invention, a cooling medium that has cooled the blade ring part is supplied to a cooling flow passage of the combustion chamber. Thus, the cooling medium can be used efficiently.

[0021] Furthermore, the gas turbine described above may further comprise a bypass flow passage that bypasses the moving blade ring parts and connects the supply pipe to the discharge pipe, and a supply destination switching unit that switches a supply destination of the cooling medium between the moving blade ring parts and the bypass flow passage.

[0022] According to the present invention, when cooling of the moving blade ring part is reduced, for example, at startup of the gas turbine, a supply destination of a cooling medium is switched from the moving blade ring part to a bypass flow passage, whereby the cooling medium can bypass the moving blade ring part and flow.

[0023] Further, in the gas turbine described above, the bypass flow passage may be arranged away from a blade ring part main body in an axial direction.

[0024] According to the present invention, a temperature distribution can be prevented from generating in the blade ring part.

[0025] Further, in the gas turbine described above, the combustor may include a transition piece on the turbine side, each of the moving blade ring parts may include a plurality of transition piece connecting units arranged aligned in the axial rotation direction, and each of the transition piece connecting units may include a bypass connecting hole communicating with the bypass flow passage and a transition piece side connecting hole communicating with the transition piece side.

[0026] According to the present invention, a cooling medium can efficiently flow into a transition piece side through the bypass flow passage.

[0027] Further, in the gas turbine described above, the bypass flow passage may include a bypass connection pipe arranged in the axial rotation direction of the moving blade ring members.

[0028] According to the present invention, a cooling medium can flow through a bypass connection pipe in an axial rotation direction of the blade ring part. Thus, the temperature of the cooling medium flowing into the transition piece side can be uniformed in the rotation direction.

[0029] Furthermore, in the gas turbine described above, the bypass connecting pipe may include a thermal expansion absorbing unit that can deform depending on thermal deformation of the blade ring members.

[0030] According to the present invention, the bypass connecting pipe is deformed depending on the thermal deformation of the blade ring part. Thus, deformation of the bypass flow passage between the bypass connecting pipe and a transition piece connecting pipe can be prevented.

[0031] Furthermore, in the gas turbine described above, each of the moving blade ring parts may include a moving blade ring part main body provided with the first cooling flow passages, the second cooling flow passages, the return flow passage, a first recess that is a part of the first communication flow passage, and a second recess that is a part of the second communication flow passage, a first closing member that is attachably and detachably fixed to the moving blade ring part main body and closes the first recess so that the first communication flow passage of the first recess is formed, and the transition piece connecting units that are attachably and detachably fixed to the moving blade ring part main body and close the second recess so that the second communication flow passage with the second recess is formed.

[0032] Furthermore, in the gas turbine described above, the rotor blade ring members may have a plurality of return flow passages communicating with each other in the axial rotation direction.

[0033] According to the present invention, a cooling medium can be circulated through the return flow passage in the axial rotation direction. Thus, a temperature distribution can be prevented from forming in the axial rotation direction of the blade ring part.

[0034] Further, in the gas turbine described above, the first cooling flow passages and the second cooling flow passages may be arranged on a virtual straight line extending from the rotation axis in the radial direction.

[0035] According to the present invention, the second cooling flow passages are arranged close to the inner side in the radial direction of the blade ring part. Thus, the inner side in the radial direction of the blade ring part can be efficiently cooled.

[0036] Further, in the gas turbine described above, each of the moving blade ring parts may have a cavity supply flow passage passing through the radial direction, and the first cooling flow passages and the second cooling flow passages may be arranged at a position depending on the cavity supply flow passage.

[0037] According to the present invention, a cooling medium flowing through the first cooling flow passages and the second cooling flow passages directly cools heat input from the cavity supply flow passage side and interrupts heat transfer from the cavity supply flow passage to the inside of the blade ring part. Thus, a temperature distribution can be prevented from generating in the blade ring part.

[0038] Further, in the gas turbine described above, each of the moving blade ring parts may have a partition part protruding outward in the radial direction, and the first communication flow passage may be arranged at the end part.

[0039] According to the present invention, the blade ring member includes a partition, thereby improving rigidity of the blade ring member. The first communication flow passage is arranged on the inside of the partition, thereby preventing a radial temperature distribution from forming in a protrusion. Thus, thermal deformation of the partition can be effectively prevented.

[0040] In the gas turbine according to the invention, each of the moving blade ring parts has a plurality of third cooling flow passages arranged on an outer side in the radial direction with respect to the first cooling flow passages, extending in the axial direction and arranged aligned in the axial rotation direction, and a second return flow passage connecting end parts of the third cooling flow passages and the first cooling flow passages on a same side in the axial direction.

[0041] According to the present invention, a plurality of cooling flow passages aligned in an axial rotation direction of a rotation axis can be arranged at three or more stages in a radial direction, thereby efficiently cooling the blade ring member across the radial direction. Thus, temperature distribution from forming in the radial direction of the blade ring member can be effectively prevented.

[0042] A method for producing blade ring parts according to the present invention comprises the features of claim 17.

[0043] According to the present invention, a first closure member and a second closure member are attached to the blade ring part main body, thereby easily forming the first communication flow passage and the second communication flow passage. The first closure member and the second closure member are removable from the blade ring part main body, thereby easily exposing a first recess and a second recess to the outside.

[0044] According to the present invention, the first communication flow passage includes the first recess at one end portion in the axial direction, and the second communication flow passage includes the second recess at one end portion in the axial direction. By attaching and detaching the first closure member to the blade ring part main body, the first recess can be closed, and by attaching and detaching the second closure member to the blade ring part main body, the second recess can be closed.

[0045] The present invention can provide a gas turbine that can prevent a temperature distribution from forming in a radial direction of moving blade ring parts, and a method for manufacturing the moving blade ring parts. Fig. 1 is a schematic view illustrating the entire configuration of a gas turbine according to an embodiment. Fig. 2 is a cross-sectional view illustrating the vicinity of a moving blade ring part in a turbine according to a non-inventive example used to explain features of the invention. Fig. 3 is a cross-sectional view showing an example of the blade ring part in the turbine. Fig. 4 is a perspective view showing an example of the blade ring part. Fig. 5 is a systematic view illustrating cooling flow passages of the blade ring part. Fig. 6 is a systematic view illustrating a modification of the cooling flow passages of the blade ring part. Fig. Fig. 7 is a view showing the embodiment with a cross section along AA of Fig. 3 represents. Fig. 8 is a cross-sectional view illustrating an example of a blade ring part according to a first embodiment. Fig. 9 is a perspective view showing an example of a part of the blade ring part. Fig. 10 is a systematic view illustrating a cooling flow passage of the blade ring part. Fig. 11 is a view showing a shape with a cross section along BB of Fig. 8 represents. Fig. 12 is a cross-sectional view illustrating an example of a blade ring part according to a second embodiment. Fig. 13 is a perspective view showing an example of a part of the blade ring part. Fig. 14 is a flowchart illustrating a manufacturing process of the blade ring part.

[0046] Embodiments of a gas turbine and a method for manufacturing blade ring parts according to the present invention will now be described with reference to the accompanying drawings.

[0047] Fig. 1 is a schematic view illustrating the overall configuration of a gas turbine 100 according to an embodiment. As shown in Fig. 1, the gas turbine 100 includes a compressor 11, a combustor 12, and a turbine 13. The gas turbine 100 has an electric generator (not shown) coupled thereto and can generate electric power through the electric generator.

[0048] The compressor 11 includes an air intake chamber 20 for intake of air, is arranged by disposing an inlet guide vane (IGV) 22 in a compressor casing chamber 21, and a plurality of guide vanes 23 and a plurality of rotor blades 24 are alternately arranged in a flow direction of air (axial direction of a rotor 32, which will be described later), and has an air bleed chamber 25 provided on the outside thereof. This compressor 11 compresses air taken in by an air intake chamber 20 to generate compressed air of high temperature and high pressure, and supplies the compressed air to a casing chamber 14.

[0049] The combustor 12 receives compressed air of high temperature and high pressure, which is compressed by the compressor 11 and stored in the casing chamber 14, and fuel, and burns the compressed air and fuel to generate combustion gas. The turbine 13 has a plurality of guide vanes 27 and a plurality of rotor blades 28 arranged alternately in a turbine casing chamber 26 in a flow direction of the combustion gas (axial direction of the rotor 32, which will be described later). The turbine casing chamber 26 has an outlet chamber 30 formed on the downstream side in a flow direction of combustion gas through an outlet casing chamber 29, and the outlet chamber 30 includes an air outlet diffuser 31 coupled to the turbine 13. This turbine is driven by combustion gas from the combustor 12 and drives an electric generator (not shown) coupled to the same axis.

[0050] The rotor 32 (rotation axis) is arranged so that the rotor 32 passes through the compressor 11, the combustion chamber 12, the turbine 13, and a central portion of the discharge chamber 30. The rotor 32 is rotatable in an axial rotation direction of a rotation axis C (hereinafter referred to as the "axial rotation direction"). Specifically, the rotor 32 has its end portion on the compressor 11 side rotatably supported by a bearing 33, and its end portion on the discharge chamber 30 side rotatably supported by a bearing 34. The rotor 32 is fixed by superposing a plurality of disks to which the moving blades 24 are respectively mounted in the compressor 11.The rotor 32 is also fixed by superimposing a plurality of discs to which the moving blades 28 are respectively mounted in the turbine 13, and has its end portion on the side of the air intake chamber 20 coupled to a drive shaft of an electric generator (not shown).

[0051] In this gas turbine 100, the compressor housing chamber 21 in the compressor 11 is supported by a leg part 35, the turbine housing chamber 26 in the turbine 13 is supported by the leg part 36, and the exhaust chamber 30 is supported by a leg part 37.

[0052] Thus, in the compressor 11, air taken in from the air intake chamber 20 is compressed while passing through the IGV 22, the guide vanes 23, and the moving blades 24, so that it becomes compressed air of high temperature and high pressure. At the combustor 12, a predetermined fuel is supplied to this compressed air, and the fuel and the compressed air are burned. At the turbine 13, combustion gas G of high temperature and high pressure generated in the combustion chamber 12 flows through the guide vanes 27 and the moving blades 28 in the turbine 13, so that the rotor 32 is driven and rotated and an electric generator coupled to the rotor 32 is driven. In contrast, after kinetic energy is converted to pressure by the exhaust diffuser 31 in the exhaust chamber 30 and decelerated, the combustion gas G is exhausted to the atmosphere.A portion of the compressed air compressed by the compressor 11 is bled at a middle stage of the compressor 11 and supplied to the turbine housing chamber 26. The bleed air supplied to the turbine housing chamber 26 is stored in a turbine housing chamber space 26a and used for cooling high-temperature components and the like on the turbine side.

[0053] Fig. 2 is a cross-sectional view illustrating the vicinity of a blade ring part 50 in the turbine 13 according to a non-inventive example used to explain features of the invention. Fig. 3 is a cross-sectional view illustrating an example of the blade ring part 50 in the turbine 13. As shown in the Fig. 2 and Fig. 3, the turbine 13 includes the cylindrical turbine housing chamber (casing) 26. The turbine housing chamber 26 has the outlet housing chamber 29 having a cylindrical shape coupled to the downstream side in a flow direction of the combustion gas G. The outlet housing chamber 29 has the outlet chamber 30 (outlet diffuser 31) having a cylindrical shape arranged to the downstream side in a flow direction of the combustion gas G. The outlet chamber 30 has an outlet channel (not shown) provided to the downstream side in a flow direction of the combustion gas G.

[0054] On the inner peripheral part of the turbine housing chamber 26, an upstream-side outer partition part 42a and a downstream-side outer partition part 42b are integrally formed at a predetermined interval at the front and rear in the flow direction of the combustion gas G. Within these upstream-side outer partition part 42a and the downstream-side outer partition part 42b, the blade ring part 50, which is divided into two parts in the axial rotation direction and has an annular shape, is supported. This blade ring part 50 is fixed to a divided part in the axial rotation direction by a bolt and forms a cylindrical structure.

[0055] Fig. 4 is a perspective view illustrating a portion of the blade ring member 50. As shown in the Fig. 3 and Fig. 4, the moving blade ring member 50 mainly includes a moving blade ring member main body 50a which is a main part of the moving blade ring member 50, a transition piece connecting part 54 formed at a connecting part between the combustion chamber 12 and the moving blade ring member 50, and a bypass flow passage 68 which forms a flow passage in which a cooling medium P bypasses the moving blade ring member 50.

[0056] The moving blade ring member main body 50a includes a cylindrical member 51 having a cooling flow passage 60, a downstream inner partition member 52, and an upstream inner partition member 53 therein. The cylindrical member 51 is arranged parallel to the rotation axis C. The central axis of the cylindrical member 51 almost coincides with the rotation axis C. The downstream inner partition member 52 protrudes from an outer peripheral surface 51a of the cylindrical member 51 to the outside in the radial direction centered on the rotation axis C (hereinafter referred to as the "axial direction") and is provided in an annular manner in the axial rotation direction. In the axial direction of the rotation axis C (hereinafter referred to as the "radial direction"), the downstream inner partition member 52 is arranged at an end portion on the downstream side in the axial direction of the turbine 13 side of the cylindrical member 51.At one corner of the end portion of the downstream inner partition 52, an annular end portion recess 52a having a cross section formed in an L-shape is formed in the axial rotation direction. The downstream outer partition 42b, formed on the inner peripheral surface in the turbine housing chamber 26, is installed in the end portion recess 52a. A side surface 52b facing the downstream side in the axial direction of the downstream inner partition 52 forming the end portion recess 52a and a side facing the upstream side in the axial direction of the downstream outer partition 42b contact each other.Between the inner peripheral surface facing the inner side in the radial direction of the downstream outer partition part 42b and the inner peripheral surface 52c facing the outer side in the axial direction of the downstream inner partition part 52 forming the end part recess 52a, a gap is formed for accommodating a difference in thermal expansion in the radial direction of the blade ring part main body 50a. The upstream side in the axial direction indicates a direction in which the compressor 11 is viewed from the blade ring part 50, and the downstream side in the axial direction indicates a direction in which the discharge chamber 30 is viewed from the blade ring part 50.

[0057] The upstream inner partition member 53 is arranged on the upstream side in the axial direction relative to the downstream inner partition member 52, protrudes from the outer peripheral side 51a of the cylindrical member 51 to the outside in the radial direction, and is provided annularly in the axial rotation direction. A partition recess 53a is formed in the upstream inner partition member 53, which is formed in the axial rotation direction, and the upstream outer partition member 42a, which is formed on the inner peripheral surface of the turbine housing chamber 26, is incorporated. A surface facing the upstream side in the axial direction of the upstream-side outer partition member 42a and a side surface 53b facing the downstream side in the axial direction of the upstream-side inner partition member 53 forming the partition recess 53a contact each other, and a sealing surface is formed on the contact surface.By providing the sealing surface on the side surface 53b of the upstream inner partition member 53, air pressure is maintained in the housing chamber 14. A pressing unit (not shown) such as a spring is provided on a contact surface between the side surface 52b facing the downstream side in the axial direction of the downstream inner partition member 52 forming the end part recess 52a and a side facing the upstream side in the axial direction of the downstream outer partition member 42b. By using this pressing unit for pressing the blade ring part 50 to the upstream side in the axial direction through the side surface 52b, air in the casing chamber is prevented from leaking from a clearance formed on the sealing surface of the upstream side inner partition part 53 into the turbine casing chamber space 26a on the downstream side in the axial direction.

[0058] In addition, between the inner peripheral surface facing the inside in the radial direction of the upstream-side outer partition member 42a and the inner peripheral surface 53c facing the outside in the radial direction of the upstream-side inner partition member 53 forming the partition recess 53a, a gap is formed for absorbing a difference in thermal expansion in the radial direction of the turbine housing chamber 26 and the blade ring member main body 50a.Similarly, between a side surface facing the downstream side in the axial direction of the upstream-side outer partition member 42a and a side surface 53d facing the upstream side in the axial direction of the upstream-side inner partition member 53 forming the partition recess 53a, a space for absorbing a difference in thermal expansion in the axial direction of the turbine housing chamber 26 and the blade ring member main body 50a is formed.

[0059] The blade ring part main body 50a includes the cooling flow passage 60 in which the cooling medium P flows. The cooling flow passage 60 includes a first cooling flow passage 61 that cools the cylindrical part 51, a second cooling flow passage 62 located downstream in a flow direction of the cooling medium P in the first cooling flow passage 61, and a return flow passage 65 that connects the first cooling flow passage 61 to the second cooling flow passage 62. The first cooling flow passage 61 is located on the outside in the radial direction of the cylindrical part 51 and is located near an outer peripheral surface 51b of the cylindrical part 51a. The first cooling flow passage 61 extends almost parallel to the axial direction. A plurality of the first cooling flow passages 61 are arranged aligned in the axial rotation direction.

[0060] The second cooling flow passage 62 is arranged on the inner side in the radial direction away from the first cooling flow passage 61 in the cylindrical part 51 and is located near the inner peripheral surface 51b of the cylindrical part 51. The second cooling flow passage 62 extends almost linearly parallel to the axial direction. Thus, the second cooling flow passage 62 is almost parallel to the first cooling flow passage 61. A plurality of the second cooling flow passages 62 are arranged aligned in the axial rotation direction.

[0061] The return flow passage 65 connects end portions of the first cooling flow passage 61 and the second cooling flow passage 62 on the same side in the axial direction. The return flow passage 65 is arranged at an end portion of the downstream side in the axial direction of the blade ring part main body 50a. The return flow passage 65 is a flow passage for returning the cooling medium P flowing into the first cooling flow passage 61 to the second cooling flow passage 62. As shown in Fig. As shown in FIG. 3, the return flow passage 65 has a cross-sectional shape on a flat surface passing through the rotation axis C, which is a rectangular shape (cavity) extending on the outside in the radial direction. The first cooling flow passage 61 is connected on the outside in the radial direction of the return flow passage 65, and the second cooling flow passage 62 is connected on the inside in the radial direction thereof. The return flow passage 65 (return flow passage 75) may be formed in an annular shape along the axial rotation direction. Thus, the return flow passage 65 connects the first cooling flow passages 61 and the second cooling flow passages 62 in the axial rotation direction. When the return flow passage 65 (return flow passage 75) is formed in an annular shape along the axial rotation direction, the entire downstream inner partition part 52 is cooled.Thus, an upper end in the radial direction of a rectangular cross section of the return flow passage 65 is preferably formed near the inner peripheral surface 52c of the downstream inner partition part 52.

[0062] The moving blade ring part 50 may include a communication flow passage 70 that supplies the cooling medium P to a plurality of cooling flow passages 60 arranged annularly in the axial rotation direction of the moving blade ring part 50, or collects the cooling medium P from the cooling flow passages 60, and communicates with each of the cooling flow passages 60 in the axial rotation direction. The communication flow passage 70 includes a first communication flow passage 71 and a second communication flow passage 72. The first communication flow passage 71 connects the first cooling flow passages 61, which are aligned in the axial rotation direction, to each other in the axial rotation direction. The first communication flow passage 71 is provided on the inside in the upstream-side inner partition part 53. As shown in Fig. 3, the first communication flow passage 71 has a cross-sectional shape on a flat surface passing through the rotation axis C, which is a rectangular shape extending on the outside in the radial direction. Thus, in the upstream-side internal partition part 53, the cooling medium P can circulate even on the outside in the radial direction. The first communication flow passage 71 is connected to a supply pipe 81 (which will be described later) in which the cooling medium P is supplied through a receiving flow passage 66. In order to cool the entire upstream-side internal partition part 53, the first communication flow passage 71 preferably has a cross-sectional shape that is a rectangular cross-sectional shape, has a flow passage width in the radial direction that is wider than a flow passage width in the axial direction, and has a narrower flow passage width extending in the radial direction.And in addition, the upper end in the radial direction of the rectangular cross-sectional shape is preferably formed near the inner peripheral surface 53c of the upstream-side inner partition part 53.

[0063] The second cooling flow passage 62 is connected to a flow passage opening (second opening) 51e formed on an inner wall of the second communication flow passage 72 formed at an upstream end portion in the axial direction of the blade ring member main body 50a. A downstream end portion in the axial direction of the second cooling flow passage 62 is provided with a flow passage opening (first opening) 51d provided at the return flow passage 65 or the return communication flow passage 75. The second cooling flow passage 62 may be a flow passage that is not parallel to the first cooling flow passage 61 and is inclined on the inside in the radial direction while facing the upstream side in the axial direction.In this case, the center of the flow passage opening 51d is formed on the outer side in the radial direction, away from the center of the flow passage opening 51e. In addition, the center of the flow passage opening 51e may be formed on the inner side in the radial direction, compared to a bottom surface 65b on the inner side in the radial direction of the return flow passage 65 or the return connection flow passage 75. When the second cooling flow passage 62 is inclined toward the inner side in the radial direction, it is located further near the inner peripheral surface 51b side of the cylindrical part 51, so that the cooling of the inner peripheral surface 51b is further improved.

[0064] The second communication flow passage 72 connects the second cooling flow passages 62, which are aligned in the axial rotation direction, to each other in the axial rotation direction. For example, the second communication flow passage 72 is provided further upstream in the axial direction than the upstream inner partition part 53 in the cylindrical part 51 and on the inner side of the cylindrical part 51, which protrudes toward the combustion chamber 12 side. The second communication flow passage 72 is arranged on the inner side in the radial direction away from the first communication flow passage 71, near the inner peripheral surface 51b of the cylindrical part 51.

[0065] The second communication flow passage 72 has a cross section formed on an upstream end surface 51f of a main body on the upstream side in the axial direction of the cylindrical part 51, and is recessed from the upstream end surface 51f of the main body to the downstream side in the axial direction, and the cross section is formed as an annular groove-like communication opening 72a extending in the axial rotation direction. The second communication flow passage 72 has the second cooling flow passages 62 connected thereto through the flow passage opening 51e. The second communication flow passage 72 is connected to an outlet flow passage 54c of the transition piece connection part 54, which is located adjacent to the upstream end surface 51f of the main body on the upstream side in the axial direction.

[0066] As in the Fig. 3 and Fig. As shown in FIG. 4, the transition piece connecting part 54 is arranged on the downstream side in the axial direction depending on the number of installed combustors 12 and is arranged adjacent to the upstream side in the axial direction of the cylindrical part 51 of the blade ring part main body 50a. The transition piece connecting part 54 is a box-like closure member fixed to the upstream end surface of the main body 51f at the upstream end in the axial direction of the cylindrical part 51 of the blade ring part main body 50a. A plurality of transition piece connecting parts 54 are arranged on the downstream side in the axial direction adjacent to a transition piece 12a of the combustor 12 arranged on the upstream side in the axial direction of the blade ring part main body 50a, and are arranged aligned in the axial rotation direction.Each of the transition piece connecting parts 54 includes a connecting hole on the transition piece side 54a, which communicates with a cooling flow passage (not shown) formed on the side of the transition piece 12a (see . Fig. 2) formed by an exhaust pipe 82, a bypass flow passage (described later) connected to the bypass flow passage, and the exhaust flow passage 54c connected to the second connecting flow passage 72, collects the cooling medium P after cooling the cooling flow passage 60, and is connected to the connecting hole on the transition piece side 54a. The exhaust flow passage 54c is a flow passage extending upstream in the axial direction and is connected to the exhaust pipe 82 through the connecting hole on the transition piece side 54a formed at the upstream end in the axial direction of the transition piece connecting part 54. The exhaust pipe 82 is connected to a cooling flow passage (not shown) of the combustion chamber 12.The outlet flow passage 54c is connected to a bypass pipe 83 through the bypass flow passage 68 (which will be described later). The cooling medium P surrounding the blade ring member main body 50a and supplied to the bypass pipe 83 is supplied to the bypass flow passage 68 and discharged from the outlet flow passage 54c to the outlet pipe 82.

[0067] The following describes a bypass flow passage in which the cooling medium P bypasses the blade ring part without flowing into the blade ring part during start-up of the gas turbine, with reference to the Fig. 2, Fig. 3 and Fig. 4. At startup of the gas turbine 100, the moving blades 28 are shifted outward in the radial direction after a shift associated with high-speed rotation and a shift due to heat input from combustion gas overlap with each other. In contrast, at startup, when the cooling medium P is supplied to the moving blade ring part 50 without bypassing the moving blade ring part 50, the moving blade ring part 50 is cooled by the cooling medium P flowing into the moving blade ring part 50 and is shifted inward in the radial direction. After the shift, in a transition period before the gas turbine 100 reaches rated operation, a clearance between the leading end portion of the moving blades 28 and the moving blade ring part 50 may be smaller than a guideline value.To avoid this phenomenon, at the start-up of the gas turbine 100, the cooling medium P preferentially bypasses the blade ring part 50 without flowing through the blade ring part 50, and the cooling medium P is preferentially supplied to the blade ring part 50 during rated operation. In this way, in the operation transition period of the gas turbine 100, a displacement of the blade ring part 50 toward the inside in the radial direction due to the cooling medium P is reduced. In contrast, the blade ring part 50 is heated in a process by bleed air when a part of the bleed air from the compressor 11 flows through a cavity supply flow passage 55. In this way, a clearance can be prevented from becoming too small. Thus, a guideline clearance can be defined so as to shorten a start-up time of the gas turbine 100 and improve an efficiency of the gas turbine 100.

[0068] The bypass flow passage 68 is formed of a bypass inlet pipe 68a that receives the cooling medium P from a cooling medium circulation mechanism 80 (details will be described later), a bypass connecting pipe 68b that is annularly arranged in the axial rotation direction on the upstream side in the axial direction of the cylindrical part 51 and supplies the cooling medium P to the transition piece connecting part 54, a thermal expansion absorbing unit 68c that absorbs thermal expansion in the axial rotation direction of the bypass connecting pipe 68b, and an inlet connecting pipe 68d that connects the bypass connecting pipe 68b to the bypass connecting hole 54b formed on the transition piece connecting part 54.

[0069] In the Fig. In the example shown in Figure 4, the cylindrical bypass inlet pipe 68a is formed at two points in the axial rotation direction with respect to an upper half portion of one blade ring portion 50a. The bypass inlet pipe 68a includes an opening 68aa connected to the cooling medium circulation mechanism 80 on the outer side in the radial direction and an opening 68ab connected to the bypass connection pipe 68b on the inner side in the radial direction. The opening 68ab is connected to an opening 68ba formed on the outer peripheral side of the bypass connection pipe 68b. A part of the bypass connecting pipe 68b engages with the bypass inlet pipe 68a from a direction orthogonal to the bypass inlet pipe 68a, and a part of the bypass inlet pipe 68a and a part of the bypass connecting pipe 68b are connected to each other so as to pass through each other.The bypass inlet pipe 68a and the bypass connecting pipe 68b are connected to each other through the opening 68ab of the bypass inlet pipe 68a and the opening 68ba formed on the bypass connecting pipe 68b.

[0070] The bypass connection pipe 68b is arranged annularly in the axial rotation direction along an outer surface on the outside in the radial direction of the transition piece connection part 54 and is fixed to the connection part 54. The bypass connection pipe 68b is arranged close to a side surface 53e facing the upstream side in the axial direction of the upstream inner partition part 53, but the bypass connection pipe 68b and the side surface 53e are arranged away from each other without contacting each other. The reason why the bypass connection pipe 68b and the side surface 53e are separated from each other is to prevent the blade ring part main body 50a from being cooled by the cooling medium P flowing in the bypass flow passage 68, and to prevent a temperature distribution from being generated in the blade ring part main body 50a.

[0071] As described above, the bypass connecting pipe 68b, which extends in the axial rotation direction, is connected to a plurality of bypass inlet pipes 68a and the inlet connecting pipe 68d, which are coupled to the transition piece connecting part 54. The bypass connecting pipe 68b is formed from a plurality of connecting pipes. On both sides in the axial rotation direction of the bypass connecting pipe 68b, which encloses the bypass inlet pipe 68a and the inlet connecting pipe 68d, the thermal expansion absorbing unit 68c for absorbing thermal expansion of the bypass connecting pipe 68b in the axial rotation direction is arranged. A balance member, a U-shaped pipe deformed in the axial direction, or the like can be used as an example of the heat expansion absorbing unit 68c, but the heat expansion absorbing unit 68c is not limited to this example.The reason why the thermal expansion absorbing unit 68c is provided is that the bypass inlet pipes 68a and the transition piece connecting parts 54 are connected to the blade ring part main body 50a, and the point where the bypass connecting pipe 68b is connected to the bypass inlet pipes 68a and the inlet connecting pipe 68d cannot absorb thermal expansion in the axial rotation direction of the bypass connecting pipe 68b.

[0072] One end part of the inlet connecting pipe 68d communicates with the bypass connecting pipe 68b, and the other end part thereof communicates with the outlet flow passage 54c formed at the transition piece connecting part 54 through the bypass connecting hole 54b.

[0073] Fig. 5 is a systematic view illustrating a flow of the cooling flow passage 60 of the blade ring part 50. As described above, the first cooling flow passage 61, which is located on the outer peripheral surface side of the cylindrical part 51 in the blade ring part 50, is connected to the first communication flow passage 71, which is annularly formed in the axial direction on the upstream side in the axial rotation direction, and is connected to the return communication flow passage 75, which is annularly formed in the axial direction on the downstream side in the axial rotation direction. In addition, the cooling medium P flowing into the return communication flow passage 75 is returned inward in the radial direction in the return communication flow passage 75 and flows into the second cooling flow passage 62.The second cooling flow passage 62 is arranged on the inner side in the radial direction of the first cooling flow passage 61 and is located near the inner peripheral surface of the cylindrical part 51 in the blade ring part 50. The second cooling flow passage 62 is arranged parallel to the first cooling flow passage 61 along the axial direction, is connected to the return flow passage 75, which is annularly formed on the downstream side in the axial direction in the axial rotation direction, and is connected to the second communication flow passage 72 on the upstream side in the axial direction.

[0074] The example given in the Fig. 5 is an example in which the two first cooling flow passages 61 and the second cooling flow passages 62 are arranged as a set. Front and rear in the axial rotation direction of a set of cooling flow passages that combines the first cooling flow passages 61 with the second cooling flow passages 62, the cavity supply flow passage 55 ( Fig. 7), which will be described later, are arranged nearby so that the set of cooling flow passages is enclosed in the axial rotation direction. In addition, a plurality of sets of cooling flow passages, each consisting of the two first cooling flow passages 61 and the two second cooling flow passages 62, which are aligned in parallel in the axial rotation direction, are arranged in Fig. 5 are not shown, are formed corresponding to the positions of a plurality of the cavity supply flow passages 55 arranged in the axial rotation direction.

[0075] The first connecting flow passage 71 includes a plurality of intake flow passages 66 connected to the cooling medium circulation mechanism 80. The second connecting flow passage 72 is connected to the exhaust flow passage 54c extending upstream in the axial direction. A plurality of the exhaust flow passages 54c are arranged in the axial rotation direction corresponding to the position of the transition piece 12a in the combustion chamber 12 and are connected to the exhaust pipe 82 upstream in the axial direction.

[0076] The bypass flow passage 68 is located on the outside in the radial direction relative to the outlet flow passage 54c and is annular in the axial rotation direction. The bypass flow passage 68 includes a plurality of bypass inlet pipes 68a connected to the cooling medium circulation mechanism 80. The bypass flow passage 68 is provided with the annular bypass connecting pipe 68b and includes the inlet connecting pipe 68d connected in correspondence with the position of the axial rotation direction of the transition piece connecting part 54, and is connected to the bypass connecting pipe 68b and the transition piece connecting part 54.

[0077] Fig. Fig. 6 is a systematic view illustrating a modification of a flow of the cooling flow passage 60 according to the present example. In other words, the cooling flow passage 60 shown in Fig. 6, an example in which the return flow passage 75 is separated from the cooling flow passage 60 shown in Fig. 5 is omitted. The present modification includes, on the downstream side in the axial direction of the cylindrical part 51, the return flow passage 65 formed as a rectangular space (cavity) extending long in the radial direction. The first cooling flow passage 61 is connected to the return flow passage 65 on the outer side in the radial direction. The second cooling flow passage 62 is connected to the return flow passage 65 on the inner side in the radial direction. A plurality of the return flow passages 65 are arranged radially centered on the rotation axis C corresponding to the position of one set of the first cooling flow passages 61 and the second cooling flow passages 62 arranged in the axial rotation direction. The other cooling flow passage 60 is formed using the same configuration as that in the example.

[0078] Fig. Fig. 7 is a view showing the embodiment with a cross section along AA of Fig. 3. As in Fig. As shown in FIG. 7, the first cooling flow passages 61 and the second cooling flow passages 62 are arranged on a virtual straight line L1 extending from the rotation axis C in the radial direction. The blade ring part 50 includes the cavity supply flow passages 55 extending through the radial direction. The first cooling flow passages 61 and the second cooling flow passages 62 are arranged at the positions corresponding to the cavity supply flow passages 55. In the present example, the first cooling flow passages 61 and the second cooling flow passages 62 are arranged nearby so that the first cooling flow passages 61 and the second cooling flow passages 62 are sandwiched on both sides of the cavity supply flow passages 55 in the axial rotation direction.The upstream side of the cavity supply flow passages 55 communicates with the turbine housing chamber space 26a. Part of the bleed air supplied to the turbine housing chamber space 26a described above flows into the cavity supply flow passages 55 and is used to cool high-temperature components such as the stationary blade 27. In other words, a temperature of compressed air flowing into the cavity supply flow passages 55 is higher than that of the cooling temperature P supplied to the cooling flow passage 60 in the moving blade ring part 50. This configuration causes heat transferred from one side of compressed air flowing into the cavity supply flow passages 55 to the blade ring part 50 to be directly cooled by the cooling medium P flowing into the first cooling flow passages 61 and the second cooling flow passages 62.After cooling, heat transfer from the cavity supply flow passages 55 to the inside of the blade ring part 50 is stopped and a temperature distribution is prevented from generating in the blade ring part 50.

[0079] The cooling medium P supplied to the blade ring part 50 is supplied from the cooling medium circulation mechanism 80 which is independently as shown in Fig. 2. The cooling medium circulation mechanism 80 includes an air conditioner 84, a compressor 85, and a three-way valve (supply destination switching unit) 86. The air conditioner 84 takes in and cools air in a housing chamber (cooling medium P) around the combustion chamber 12 and supplies the air to the compressor 85. The compressor 85 compresses the air from the air conditioner 84 and supplies the compressed air to the three-way valve 86. The three-way valve 86 is connected to the compressor 85, the supply pipe 81, and the bypass pipe 83 described above. The supply pipe 81 is connected to the intake flow passage 66 in the moving blade ring part 50, and the bypass pipe 83 is connected to the bypass inlet pipe 68a. The three-way valve 86 can supply the air from the compressor 85 by switching between the supply pipe 81 and the bypass pipe 83.Thus, in a case of steady-state operation of the gas turbine 100, for supplying the cooling medium P to the blade ring part 50, the three-way valve 86 is redesigned so that the cooling medium P flows in from the supply pipe 81 side. During startup of the gas turbine 100, supplying the cooling medium P to the blade ring part 50 is not necessary, and the three-way valve 86 is designed so that the cooling medium P flows in from the bypass pipe 83 side.

[0080] In the moving blade ring member 50 configured as above, the cooling medium P supplied from the supply pipe 81 flows into the moving blade ring member main body 50a. The cooling medium P flowing into the moving blade ring member main body 50a flows with the cooling flow passage 60 and the communication flow passage 70, absorbs heat of the moving blade ring member main body 50a, and is discharged from the discharge pipe 82.

[0081] Specifically, the cooling medium P accommodated in the moving blade ring member main body 50a is supplied to the first communication flow passage 71 through the accommodation flow passage 66. The cooling medium P flows in the first communication flow passage 71 in the axial rotation direction and is supplied to the entire first communication flow passage 71 in the axial rotation direction. In addition, the cooling medium P flows from the first communication flow passage 71 to the first cooling flow passages 61. This cooling medium P flows into the first cooling flow passages 61 along the axial direction toward the turbine 13 side and is supplied to the return flow passage 65 (return communication flow passage 75).

[0082] The cooling medium P supplied to the return flow passage 75 flows into the return flow passage 75 in the axial rotation direction. In the case of a modification of the example in which the return flow passage 75 is not formed as shown in Fig. 6, the cooling medium P supplied to the return flow passage 65 flows in the radial direction along with the return flow passage 65 and is supplied to the second cooling flow passages 62.

[0083] The cooling medium P supplied to the second cooling flow passages 62 flows into the second cooling flow passages 62 along the axial direction toward the combustion chamber 12 side, and is supplied to the second connecting flow passage 72. Thus, in the moving blade ring part 50, the first cooling flow passages 61 and the second cooling flow passages 62, which are arranged aligned in the radial direction, each have an opposite flow passage in which the cooling medium P flows in a direction opposite to the axial direction formed therefrom. Thus, in the moving blade ring part 50, a flow of the cooling medium P in the radial direction is formed at a plurality of stages.

[0084] The cooling medium P supplied to the second communication flow passage 72 flows into the second communication flow passage 72 in the axial rotation direction and is supplied to the entire second communication flow passage 72 in the axial rotation direction. In addition, the cooling medium P is discharged from the second cooling flow passages 62 and is collected in the second communication flow passage 72 and flows into the exhaust flow passage 54c. This cooling medium P flows into the exhaust pipe 82 from the exhaust flow passage 54c and is supplied to a cooling flow passage (not shown) of the combustion chamber 12.

[0085] During startup of the gas turbine, the cooling medium P is not supplied to the blade ring member main body 50a and flows into the bypass flow passage 68 and is discharged to the exhaust pipe 82 through the exhaust flow passage 54c. At this time, the bypass flow passage 68 does not contact the blade ring member main body 50a. Thus, during startup of the gas turbine, the blade ring member main body 50a is cooled by the bypass flow passage 68, and there is no possibility of a temperature distribution forming in the blade ring member main body 50a.

[0086] The following describes a manufacturing process of the moving blade ring member 50 of the present example to explain features of the invention. The moving blade ring member main body 50a is produced by casting, sheet metal working, or the like. In this process, in the cylindrical part 51 and the upstream-side inner partition part 53 constituting the moving blade ring member main body 50a, the first communication flow passage 71 and the return flow passage 65 (return communication flow passage 75) located at the end in the axial direction to which each cooling flow passage is connected are formed as annular recesses in the axial rotation direction by machining. Subsequently, the first cooling flow passages 61 and the second cooling flow passages 62 are formed by machining using drilling.The first cooling flow passages 61 are drilled from the return flow passage 65 (return flow passage 75) side to the first connection flow passage 71 side. The second cooling flow passages 62 are drilled from the return flow passage 65 (return flow passage 75) side to the second connection flow passage 72 side, and are opened at the flow passage opening 51e formed at the second connection flow passage 72.Subsequently, a first closure member (cover plate 71a) and a second closure member (transition piece connecting part 54), and a cover plate 65a are welded to the blade ring part main body 50a, so that the first communication flow passage 71 and the second communication flow passage 72, and the return flow passage 65 (return connection flow passage 75), which are closed flow passages, are formed. Subsequently, the bypass flow passage 68 is attached to the transition piece connecting part 54, which is fixed to the blade ring part main body 50a. Through this manufacturing process, assembly of the blade ring part 50 is completed.

[0087] As described above, the gas turbine 100 according to the present example has, in the moving blade ring part 50, a plurality of first cooling flow passages 61 arranged on the outer side in the axial rotation direction in the radial direction, and a plurality of second cooling flow passages 62 arranged on the inner side in the axial rotation direction in the radial direction. In addition, the first cooling flow passages 61 are returned to the second cooling flow passages 62 at end portions on a same side in the axial direction through the return flow passage 65. In this way, a plurality of cooling flow passages 60 aligned in the axial rotation direction can be arranged at a plurality of stages in the radial direction.Thus, the rotor blade ring part 50 is cooled via a plurality of points in the radial direction such that the formation of a temperature distribution in the radial direction of the rotor blade ring part 50 is prevented or reduced.

[0088] A first embodiment is described below. Fig. 8 is a cross-sectional view illustrating an example of a part of a blade ring part 150 according to the first embodiment. Fig. 9 is a perspective view illustrating an example of the blade ring part 150 according to the present embodiment. Fig. 10 is a systematic view illustrating a cooling flow passage 160 according to the present embodiment. Fig. 11 is a view showing a shape with a cross section along BB of Fig. 9. The first embodiment differs from the example in that the cooling flow passage 160, provided at three stages in the radial direction, is included for the primary purpose of enhancing further cooling of a region on the upstream side of the intake flow passage 66 on the upstream side in the axial direction of an upstream-side inner partition part 153 and a cylindrical part 151 in a blade ring part main body 150a. In the first embodiment, differences from the example are mainly explained. Like reference numerals refer to like components in the blade ring part 50 according to the example, and explanation is omitted or simplified.

[0089] As in Fig. 8, the moving blade ring member 150 includes the moving blade ring member main body 150a, a transition piece connecting part 154, and a bypass flow passage 168. In addition, the moving blade ring member main body 150a includes the cylindrical part 151, a downstream side inner partition part 152, and the upstream side inner partition part 153. For example, in the moving blade ring member main body 150a in the moving blade ring member 150 according to the present embodiment, a thickness of the upstream side inner partition part 153 in the radial direction outward is thicker in the radial direction compared with the moving blade ring member main body 50a in the moving blade ring member 50 according to the first embodiment. In addition, the cylindrical part 151 on the inside in the radial direction of the upstream side inner partition part 153 has a cross section that is directed toward the upstream side in the axial direction and is thicker inward in the radial direction.

[0090] The cylindrical part 151 includes the cooling flow passage 160 and a connecting flow passage 170 in which the cooling medium P flows. The cooling flow passage 160 includes a first cooling flow passage 161 and a second cooling flow passage 162, and a return flow passage 165 (return flow passage 175) connecting the first cooling flow passage 161 to the second cooling flow passage 162. The communication flow passage 170 includes a first communication flow passage 171 and a second communication flow passage 172. The first communication flow passage 171 of the present embodiment is connected to the first cooling flow passage 161 on the inside in the radial direction of the first communication flow passage 171 and is connected to a third cooling flow passage 163, which will be described later, on the outside in the radial direction.In a similar manner to the return flow passage 75 of the example, the return flow passage 165 (return flow passage 175) may be an annular flow passage extending in the axial rotation direction.

[0091] The present embodiment differs from the example in that the second cooling flow passage 162 includes an upstream flow passage 162a connected to the return flow passage 165 (return flow passage 175), and a downstream flow passage 162b connected to the second connection flow passage 172 through a flow passage opening (second opening) 151e. The upstream flow passage 162a extends linearly from a flow passage opening (first opening) 151d, which is a connecting part, to the return flow passage 165 (return flow passage 175) toward an upstream side of the axial direction with an inward inclination in the radial direction.In addition, the upstream flow passage 162a changes an extending direction at a Q point, which is a center point, and is curved outward in the radial direction so as to be curved, and is connected to the downstream flow passage 162b. The downstream flow passage 162b extends further upstream in the axial direction and is connected to the second communication flow passage 172 through the flow passage opening 151e. In other words, the second cooling flow passage 162 forms a curved flow passage that is curved outward in the radial direction at the center point Q. In other words, the center of the flow passage opening 151d is formed on the outside in the radial direction with respect to the center of the flow passage opening 151e.The center of the flow passage opening 151e can be formed on the inner side in the radial direction relative to a bottom surface 165b on the inner side in the radial direction of the return flow passage 165 (return flow passage 175). In the cylindrical part 151, this configuration allows a flow passage to be formed further in the radial direction than the second cooling flow passage 62 of the example, and further improves the cooling of the surroundings of an inner peripheral surface 151b of the cylindrical part 151.

[0092] The second cooling flow passage 162 may be a flow passage formed linearly from the flow passage opening 151d to the flow passage opening 151e. This configuration facilitates maintenance and processing compared to a curved flow passage.

[0093] In the present embodiment, the upstream inner partition part 153 of the blade ring part main body 150a further includes the third cooling flow passage 163. The third cooling flow passage 163 is arranged on the outside in the radial direction with respect to the first cooling flow passage 161. A plurality of the third cooling flow passages 163 extend in the axial direction and are arranged aligned in the axial rotation direction. The first connecting flow passage 171 also serves as a second return flow passage that connects end parts of the third cooling flow passage 163 and the first cooling flow passage 161 on the same side in the axial direction. As shown in Fig. As shown in FIG. 11, the third cooling flow passage 163, the first cooling flow passage 161, and the second cooling flow passage 162 are arranged along a virtual straight line L2 extending from the rotation axis C in the radial direction. The third cooling flow passages 163 may be evenly arranged in the axial rotation direction on the outside in the radial direction with respect to the first cooling flow passage 161 and are not necessarily arranged along the virtual straight line L2.

[0094] In the present embodiment, the connecting flow passage 170 further includes a third connecting flow passage 173. The third connecting flow passage 173 connects the third cooling flow passages 163, which are aligned in the axial rotation direction, to each other in the axial rotation direction. The third connecting flow passage 173 is provided on the inside of the upstream-side internal partition part 153. The third connecting flow passage 173 is connected to the receiving flow passages 66 in which the cooling medium P is supplied. The other configurations of the cooling flow passage 160 and the connecting flow passage 170 are approximately the same as those of the cooling flow passage 60 and the cooling flow passage 70 in the example.

[0095] Fig. 10 illustrates the systematic view for a flow of the cooling flow passage 160 of the present embodiment. The systematic view of the present embodiment differs from the systematic view of the example in that the third cooling flow passage 163 and the third connecting flow passage 173 are added to the cooling flow passage 60 of the example, and the second cooling flow passage 162 has a curved shape ( Fig. 8), but the further configuration of the present embodiment is the same as that of the example. Fig. 10 illustrates that the return flow passage 175 is arranged at an end portion on the upstream side in the axial direction as a flow passage connecting the first cooling flow passage 161 and the second cooling flow passage 162. In a similar manner to the modification of the example shown in Fig. 6, the return flow passage 165 formed as a rectangular space (cavity) extending long in the radial direction may be included without providing the return connection flow passage 175.

[0096] In the present embodiment, the blade ring part 150 includes the transition piece connecting part 154 on the upstream side in the axial direction of the cylindrical part 151 and an end part of the combustor 12 side. A plurality of the transition piece connecting parts 154 are arranged aligned in the axial rotation direction. Each of the transition piece connecting parts 154 includes a transition piece side connecting hole 154a communicating with a cooling flow passage (not shown) formed on the transition piece 12a side through the outlet pipe 82, a bypass connecting hole 154b to which the bypass flow passage 168 (which will be described later) is connected, and an outlet flow passage 154c collecting the cooling medium P after cooling the flow passage 160 into the second cooling connecting flow passage 172 and connected to the transition piece side connecting hole 154a.

[0097] In a similar manner to the example, the bypass flow passage 168 is formed of the bypass inlet pipe 68a that receives the cooling medium P from the cooling medium circulation mechanism 80 described above, a bypass connection pipe 168b that is annularly arranged in the axial rotation direction on the upstream side in the radial direction of the cylindrical part 151 and supplies the cooling medium P to the transition piece connection part 154, a thermal expansion absorbing unit 168c that absorbs thermal expansion of the bypass connection pipe 168b, and an inlet connection pipe 168d that couples the bypass connection pipe 168b to the bypass connection hole 154b formed on the transition piece connection part 154. The bypass connection pipe 168b is arranged away from a side surface 153e at the upstream end in the axial direction of the upstream inner partition part 153 in the axial direction.Thus, there is no possibility that the flow of the cooling medium P flowing into the bypass flow passage 168 affects the temperature distribution of the blade ring part main body 150a. The detailed configuration of the bypass flow passage is the same as that of the example, and the detailed explanation is omitted.

[0098] The following describes a manufacturing process of the blade ring member 150 of the present embodiment. The blade ring member main body 150a is produced by casting, sheet metal working, or the like. In this process, in the cylindrical part 151 and the upstream-side inner partition part 153 constituting the blade ring member main body 150a, the communication flow passage 170 provided at the end of the axial direction, to which each cooling flow passage 160 is connected, is formed by machining. In other words, an annular recess extending in the axial rotation direction, which forms the first communication flow passage 171 and the second communication flow passage 172, and the return flow passage (return communication flow passage 175), is machined.The annular recess is formed in a groove shape, which is recessed from the upstream end in the axial direction or the downstream end in the axial direction of the cylindrical part 151 to the downstream side or the upstream side in the axial direction by machining. In addition, an annular recess extending in the axial rotation direction, which forms the third communication flow passage 173, is formed at a partition recess or groove 153a of the upstream-side inner partition part 153 by machining. A groove or recess of the third communication flow passage 173 is formed as a recessed part formed from a bottom surface 153c to the inner side in the radial direction along the axial rotation direction of the partition recess 153a.Subsequently, the first cooling flow passage 161 and the third communication flow passage 173 are formed by machining using punching and cutting. The first cooling flow passage 161 is punched or cut from the first communication flow passage 171 side to the return flow passage 165 (return communication flow passage 175) side. The third cooling flow passage 163 is punched or cut from the first communication flow passage 171 side to the third communication flow passage 173 side. Subsequently, the second cooling flow passage 162 is formed by machining using two-stage punching and cutting. In other words, the second cooling flow passage 162a in . Fig. 8 is formed at a first stage by machining using punching or cutting from the return flow passage 165 or the return connection flow passage 175 to the Q point on the upstream side in the axial direction. Subsequently, at a second stage, punching or cutting is applied from the second connection flow passage 172 side to the Q point on the downstream side in the axial direction by machining. When the Q point is reached, the second cooling flow passages 162a and 162b are integrated to form an entire flow passage of the second cooling flow passage 162.Subsequently, a first closure member (cover plate 171a) and a second closure member (transition piece connecting part 154), and a cover plate 173a, a cover plate 165a, or a cover plate 175a are welded to the blade ring member main body 150a, so that the first communication flow passage 171 and the second communication flow passage 172 and the return flow passage 165 or the return communication flow passage 175 are formed, which are closed flow passages. Subsequently, the bypass flow passage 168 is attached to the transition piece connecting part 154, which is fixed to the blade ring member main body 150a. Through this manufacturing process, the assembly of the blade ring member 150 is completed.

[0099] As above, in the blade ring part 150 according to the present embodiment, a plurality of cooling flow passages 160 aligned in the axial rotation direction can be arranged at three or more stages in the radial direction, thereby efficiently cooling the blade ring part 150 across the radial direction. Thus, temperature dispersion can be effectively prevented from forming in the radial direction of the blade ring part 150.

[0100] During startup of the gas turbine 100, the moving blade ring member 150 according to the present embodiment allows the cooling medium P to bypass the moving blade ring member main body 150a and efficiently flow into the transition piece 12a side through the bypass flow passage 168. Thus, the moving blade ring member 150 can be operated without affecting a temperature distribution on the moving blade ring member main body 150a, and startup of the gas turbine 100 can be shortened. The bypass connection pipe 168b includes the thermal expansion absorbing unit 168c, and heat stress generated in the bypass connection pipe 168b can be reduced.

[0101] A second embodiment is described below. Fig. 12 is a cross-sectional view illustrating an example of a part of a blade ring part 250 according to the second embodiment. Fig. 13 is a perspective view illustrating an example of the blade ring part 250. In the second embodiment, the second embodiment differs from the first embodiment in part of the configuration of the blade ring part 250, and differences from the first embodiment will be mainly explained. Similar reference numerals refer to similar components in the blade ring 150 according to the first embodiment, and explanations will be omitted or simplified.

[0102] As in the Fig. 12 and Fig. As shown in Fig. 13, the moving blade ring member 250 according to the present embodiment includes a moving blade ring member main body 250a, a transition piece forming part 254 (second closing member), and a bypass flow passage 268. In addition, the moving blade ring member main body 250a includes a cylindrical part 251, a downstream-side inner partition part 252, an upstream-side inner partition part 253, and a first closing member 251c. In the present embodiment, with respect to the cylindrical part 251 or the upstream-side inner partition part 253 in the moving blade ring member main body 250a, the closing member 251c is attachably and detachably fixed from the upstream side in the axial direction at a position corresponding to a first communication flow passage 271 by a fixed member BT such as bolts.The transition piece connecting part 254 (second locking member) is connected to an end part of the cylindrical part 251 projecting on the upstream side in the axial direction, but the connection with the cylindrical part 251 is made attachable and detachable from the upstream side in the axial direction by a fixed member BT such as bolts, similarly to the locking member 251c.

[0103] Similar to the first embodiment, a cooling flow passage 260 of the blade ring member main body 250a includes a first cooling flow passage 261, a second cooling flow passage 262, a third cooling flow passage 263, and a return flow passage 265 (return connection flow passage 275). In the present embodiment, similar to the first embodiment, the second cooling flow passage 262 includes an upstream flow passage 262a connected to the return flow passage 265 (return connection flow passage 275) and a downstream flow passage 262b connected to a second connection flow passage 272 through a flow passage opening (second opening) 251e.The upstream flow passage 262a extends from a flow passage opening (first opening) 251d, which is a connecting part, linearly with the return flow passage 265 (return connection flow passage 275) to the upstream axial direction while being inclined inward in the radial direction. In addition, the upstream flow passage 262a changes an extending direction at a Q point, which is a center point, and is curved outward in the radial direction to be curved, and is connected to the downstream flow passage 262b. The upstream flow passage 262b further extends upstream in the axial direction and is connected to the second connection flow passage 272 through the flow passage opening 251e. In other words, the second communication flow passage 262 forms a curved flow passage that is curved outward in the radial direction at the center point Q.In other words, the center of the flow passage opening 251d is formed on the outer side in the radial direction relative to the center of the flow passage opening 251e. The center of the flow passage opening 251e may be formed on the inner side in the radial direction relative to a bottom surface 265b on the inner side in the radial direction of the return flow passage 265 (return flow passage 275). In the cylindrical part 251, this configuration enables a flow passage formed more on the inner side in the radial direction than the second cooling flow passage 62 of the example, and causes the cooling of the surroundings of an inner peripheral surface 251b of the cylindrical part 251 to be improved. In addition, the second cooling flow passage 262 may be a flow passage formed linearly from the flow passage opening 251d to the flow passage opening 251e.With this configuration, maintenance and processing are simplified compared to a curved flow passage. Furthermore, a connecting flow passage 270 of the blade ring part main body 250a includes the first connecting flow passage 271, the second connecting flow passage 272, and the third connecting flow passage 273.

[0104] The first communication flow passage 271 of the blade ring member main body 250 is formed in an annular groove-like shape in the axial rotation direction as a first recess 257 open to the upstream side in the axial direction at an end part 253 on the upstream side in the axial direction of the cylindrical part 251 or the upstream-side inner partition part 253. The second communication flow passage 272 is formed in a circular groove-like shape in the axial rotation direction as a second recess 258 open to the upstream side in the axial direction at an upstream end surface of a main body 251f, which is an end part of the upstream side in the axial direction of the cylindrical part 251. The first recess 257 is closed by the first closure element 251c and forms the annular first connecting flow passage 271 with the first recess 257.Similarly, the second recess 258 is closed by the transition piece connecting part 254 (second closing element) and forms the annular second connecting flow passage 272 with the second recess 258.

[0105] The configuration of the transition piece connecting part 254 and the bypass flow passage 268 of the present embodiment is the same as that of the first embodiment. Since the transition piece connecting part 254 has the attachable / detachable configuration, the bypass flow passage 268 connected to the transition piece connecting part 254 also has the attachable / detachable configuration. In other words, the bypass inlet pipe 68a, a bypass connecting pipe 268b, a thermal expansion absorbing unit 268c, and an inlet connecting pipe 268d forming the bypass flow passage 268 also have an easily detachable configuration and an attachable / detachable configuration. The bypass connection pipe 268b is arranged away from the side surface 253e at the upstream end in the axial direction of the upstream inner partition part 253 in the axial direction.Thus, there is no possibility that the flow of the cooling medium P flowing in the bypass flow passage 268 affects the temperature distribution of the blade ring member main body 250a. The other configuration is the same as that of the first embodiment.

[0106] Fig. 14 is a flowchart illustrating a manufacturing process of the blade ring member according to the present embodiment. The blade ring member main body 250a is produced by casting, sheet metal working, or the like (S1). In this process, the cylindrical member 251 and the upstream inner partition member 253 constituting the blade ring member main body 250a, the communication flow passage 270 located at the end of the axial direction to which each cooling flow passage 260 is connected, are formed by machining. Specifically, the first recess 257 constituting the first communication flow passage 271 and the second recess 258 constituting the second communication flow passage 272 are formed by machining.The first recess 257 and the second recess 258 are recessed parts recessed from the side surface 253e, which is the upstream end in the axial direction of the upstream-side inner partition part 253 or the upstream end surface of the main body 251f at the upstream end of the axial direction of the cylindrical part 251 to the downstream side in the axial direction, and are formed by machining into an annular groove-like shape extending in the axial rotation direction. The third communication flow passage 273 is a recessed part recessed from a bottom surface 253c of a partition recess 253a on the outer surface side in the radial direction of the upstream-side inner partition part 253 to the inner side in the radial direction, and is formed by machining into an annular groove-like shape extending in the axial rotation direction.The return flow passage 265 or the return connection flow passage 275 is a recessed part recessed from one side of an outer surface of the end surface on the downstream side in the axial direction of the cylindrical part 251 to the upstream side in the axial direction, and is formed by mechanical processing as an annular recess extending in the axial rotation direction.

[0107] Subsequently, the first cooling flow passage 261 and the third cooling flow passage 263 are formed by machining using drilling (S2). The first cooling flow passage 261 is drilled from the first recess 257 side to the return connection flow passage 275 side. The third cooling flow passage 263 is drilled from the first recess 271 side to the third connection flow passage 273 side. The intake flow passage 66, which is formed on the downstream side in the axial direction of the upstream-side internal partition part 253, is formed by drilling from the downstream-side internal partition part 252 side to the third connection flow passage 273.

[0108] Subsequently, the second cooling flow passage 262 is formed by machining using two-stage drilling (S3). In other words, Fig.12, at a first stage, the second cooling flow passage 262a is formed from the return flow passage 265 or the return flow passage 275 to the Q point on the upstream side in the axial direction by machining using drilling. Subsequently, at a second stage, drilling is applied from the second projection 258 side to the Q point on the downstream side in the axial direction.

[0109] When the Q point is reached, the second cooling flow passages 262a and 262b are integrated to form an entire flow passage of the second cooling flow passage 262. At this stage, a cavity (connecting flow passage) connecting each cooling flow passage 260 to each cooling flow passage 260 is formed.

[0110] Subsequently, the first closure member 251c is attached to the first recess 257 so that the first communication flow passage 271 is formed (S4). In other words, the first closure member 251c is attachably and detachably fixed by a bolt to a position of the first recess 257 forming the first communication flow passage 271 so that the first recess 257 closes. In addition, cover plates 273a, 265a, 275a, and the like of the cavity forming each of the communication flow passages are attached to the blade ring member main body 250a by welding. In this way, a set of closed passages including the first communication flow passage 271 and the third communication flow passage 273, and the return communication flow passage 275 is formed.

[0111] Subsequently, the second closure member (transition piece connecting part 254) is attached to the second recess 258 so that the second communication flow passage 272 is formed (S5). In other words, the transition piece connecting part 254 is attachably and detachably fixed by a bolt to a position of the second recess 258 formed on the cylindrical part 251 of the blade ring part main body 250a so as to close the second recess 258. In this way, the closed second communication flow passage 272 is formed.

[0112] Subsequently, the bypass flow passage 268 is attached to the transition piece connecting part 254, which is fixed to the blade ring part main body 250a. Through this manufacturing process, assembly of the blade ring part 250 is complete.

[0113] In the blade ring part 250 of the present embodiment, the first recess or groove 257 and the second recess or groove 258 are exposed by removing the attachably and detachably attached transition piece connecting part 254 (second closing member) and the bypass flow passage 268 and the first closing member 251c. In this way, it is possible to perform an internal inspection of the first cooling flow passage 261 and the third cooling flow passage 263 from the first connecting flow passage 251 side. In this way, it is also possible to perform an internal inspection of the second cooling flow passage 262 from the second connecting flow passage 272 side. In other words, the first and second closing members have the attachable / detachable configuration.Thus, maintenance of the gas turbine, the internal inspection of the entire cooling flow passage 260 (the first cooling flow passage 261, the second cooling flow passage 262 and the third cooling flow passage 263) is made easy.

[0114] In this way, in the present invention, the blade ring member main body 250a can be easily formed by attaching the transition piece connecting part 254 (second closure member) and the first closure member 251c to the blade ring member main body 250a. During maintenance and the like of the gas turbine, the first recess 257 and the second recess 258 can be easily exposed to the outside by removing the transition piece connecting part 254 and the bypass flow passage 268 and the first closure member 251c from the blade ring member main body 250a. Thus, the internal inspection of the entire cooling flow passages 260a (first cooling flow passage 261, second cooling flow passage 262, and third cooling flow passage 263) can be made, and maintenance execution is simplified. List of reference symbols 11 compressors 12 Combustion chamber 12a transition piece 13 turbines 14 Housing chamber 20 Air intake chamber 21 Compressor housing chamber 22 Inlet guide vane 23.27 guide vane 24.28 rotor blade 25 bleed air chamber 26 Turbine housing chamber 29 Outlet housing chamber 30 Outlet chamber 31 Outlet diffuser 32 rotors 33,34 Storage 35,36,37 leg part 42a upstream external separator 42b downstream external separator 50,150,250 Blade ring part 50a,150a,250a rotor blade ring part main body 51,151,251 cylindrical part 51a,151a,251a Part outer peripheral surface of the cylindrical 51b,151b,251b Part inner peripheral surface of the cylindrical 51d,151d,251d opening) Flow passage opening (first 51e,151e,251e opening) Flow passage opening (second 52,152,252 downstream internal separator 53,153,253 upstream internal separator 54,154,254 Transition piece connecting part 54a,154a,254a Connection hole on transition piece side 54b,154b,254b bypass connection hole 54c,154c,254c closure element) Outlet flow passage (second 55,155,255 Cavity supply flow passage 60,160,260 Cooling flow passage 61,161,261 first cooling flow passage 62,162,262 second cooling flow passage 65,165,265 first return flow passage 65b,165b,265b lower surface 66 intake flow passage 68,168,268 Bypass flow passage 68a Bypass inlet pipe 68b,168b,268b bypass connecting pipe 68c,168c,268c thermal expansion absorbing unit 68d,168d,268d inlet connecting pipe 70,170,270 connecting flow passage 71,171,271 (second first connecting flow passage return flow passage) 72,172,272 second connecting flow passage 173,273 third connecting flow passage 75,175,275 Return flow passage 80 Cooling medium circulation mechanism 81 Supply pipe 82 Outlet pipe 83 Bypass pipe 84 Air conditioning 85 compressors 86 three-way valve 100 gas turbines 162a,262a upstream flow passage 162b,262b downstream flow passage 163,263 third cooling flow passage 173 third connecting flow passage 251c first closure element 257 first recess 258 second recess C rotation axis G Combustion gas L1,L2 virtual straight line P Cooling medium

Claims

[1] A gas turbine (100) with: a compressor (11) configured to compress air, a combustion chamber (12) configured to mix a fuel with compressed air compressed by the compressor (11) and to burn the compressed air mixed with the fuel, a turbine (13) configured to be rotated by combustion gas generated by the combustion chamber (12), a rotor (32) comprising a rotor main body configured to rotate in an axial rotation direction of a rotation axis (C) by rotation of the turbine (13), and a plurality of blade stages aligned in an axial direction of the rotation axis (C) and fixed to the rotor main body, a housing (26) covering an outer peripheral side of the rotor (32), a plurality of guide vane stages fixed to an inner peripheral side of the casing (26) and arranged on the respective upstream sides of the rotor blade stages, and a plurality of blade ring parts (150; 250) provided on the casing (26), formed in a ring shape centered around the axis of rotation (C), and covering the blade stages and the guide vane stages, wherein each of the blade ring parts (150;250) comprises: a plurality of first cooling flow passages (161; 261) arranged on an outer side in a radial direction centered on the rotation axis (C), extending in the axial direction, and arranged aligned in the axial rotation direction, a plurality of second cooling flow passages (162; 262) arranged on an inner side in the radial direction with respect to the first cooling flow passages (161; 261), extending in the axial direction and arranged aligned in the axial rotation direction, a first return flow passage (165; 265) connecting end portions of each of the first cooling flow passages (161; 261) and the second cooling flow passages (162; 262) on a same side in the axial direction, a plurality of third cooling flow passages (163; 263) arranged on an outer side in the radial direction with respect to the first cooling flow passages (161; 261), extending in the axial direction and arranged aligned in the axial rotation direction, and a second return flow passage (171; 271) connecting end portions of the third cooling flow passages (163; 263) and the first cooling flow passages (161; 261) on a same side in the axial direction, a first connecting flow passage (171; 271) connecting the first cooling flow passages (161; 261) to each other in the axial rotation direction, and a second connecting flow passage (172; 272) connecting the second cooling flow passages (162; 262) to each other in the axial rotation direction, and a third connecting flow passage (173;273) connecting the third cooling flow passages (163;263) to each other in the axial rotation direction. [2] The gas turbine (100) according to claim 1, wherein the first cooling flow passages (161; 261) and the second cooling flow passages (162; 262) are formed in a blade ring part main body (150a; 250a), and the second cooling flow passages (162; 262) are connected to the first return flow passage (165; 265) at a first opening (151d; 251d) and are opened to an end part of the blade ring part main body (150a; 250a) on an upstream side in the axial direction at a second opening (151e; 251e), and a center of the first opening (151d;251d) is arranged on an outer side of a center of the second opening (151e;251e) in the radial direction. [3] The gas turbine (100) according to claim 2, wherein the center of the second opening (151e; 251e) is located on an inner side in the radial direction with respect to a lower surface (165b, 265b) facing an inner side in the radial direction of the first return flow passage (165; 265). [4] The gas turbine (100) according to claim 2 or 3, wherein the second cooling flow passages (162; 262) are curved flow passages that are curved outward in the radial direction at a center point of the flow passages that extend in an axial direction. [5] The gas turbine (100) according to any one of claims 1 to 4, wherein the first connecting flow passage (171; 271) is connected to a supply pipe (81) where a cooling medium (P) can be supplied, and the second connecting flow passage (172; 272) is connected to an outlet pipe (82) where the cooling medium (P) can be discharged. [6] The gas turbine (100) according to claim 5, wherein the outlet pipe (82) is connected to a cooling flow passage of the combustor (12). [7] The gas turbine (100) according to claim 6, further comprising: a bypass flow passage (168; 268) bypassing the blade ring parts (150; 250) and connecting the supply pipe (81) to the outlet pipe (82), and a supply destination switching unit (86) configured to switch a supply destination of the cooling medium (P) between the moving blade ring parts (150; 250) and the bypass flow passage (168; 268). [8] The gas turbine (100) according to claim 7, wherein the bypass flow passage (168;268) is arranged away from a blade ring part main body (150a;250a) in an axial direction. [9] The gas turbine (100) according to claim 7 or 8, wherein the combustion chamber (12) comprises a transition piece (12a) on the turbine side, each of the blade ring parts (150; 250) has a plurality of transition piece connecting parts (154; 254) arranged aligned in the axial direction of rotation, and each of the transition piece connecting parts (164; 254) has a bypass communication hole (154c; 254c) communicating with the bypass flow passage (168; 268) and a communication hole (154a; 254a) on a transition piece side communicating with the transition piece side. [10] The gas turbine (100) according to claim 9, wherein the bypass flow passage (168; 268) comprises a bypass connection pipe (168b; 268b) arranged in the axial rotation direction of the blade ring parts (150; 250). [11] The gas turbine (100) according to claim 10, wherein the bypass connection pipe (168b; 268b) has a thermal expansion absorbing unit (168c; 268c) which can deform depending on the thermal deformation of the blade ring parts (150; 250). [12] The gas turbine (100) according to any one of claims 9 to 11, wherein each of the blade ring parts (250) comprises: a blade ring part main body (250a) provided with the first cooling flow passages (261), the second cooling flow passages (262), the first return flow passage (265), a first recess (257) which is a part of the first connecting flow passage (271), and a second recess (258) which is a part of the second connecting flow passage (272), a first closure member (251c) attachably and detachably secured to the blade ring part main body (250a) and closing the first recess (257) so that the first communication flow passage (271) is formed with the first recess (257), and the transition piece connecting parts (254) which are attachably and detachably fixed to the blade ring part main body (250a) and close the second recess (258) so that the second connecting flow passage (272) is formed with the second recess (258). [13] The gas turbine (100) according to any one of claims 1 to 12, wherein the blade ring members (150:250) have a plurality of the return flow passages (165,171;265,271) communicating with each other in the axial rotation direction. [14] The gas turbine (100) according to any one of claims 1 to 13, wherein the first cooling flow passages (161; 261) and the second cooling flow passages (162; 262) are arranged on a virtual straight line (L2) extending from the rotation axis (C) in the radial direction. [15] The gas turbine (100) according to any one of claims 1 to 14, wherein each of the blade ring parts (150; 250) has a cavity supply flow passage (155; 255) passing through the radial direction, and the first cooling flow passages (161;261) and the second cooling flow passages (162;262) are arranged at a position depending on the cavity supply flow passage (155;255). [16] The gas turbine (100) according to any one of claims 1 to 12, wherein each of the blade ring parts (150; 250) has a separating part (153; 253) projecting outward in the radial direction, and the first connecting flow passage (171;271) is arranged on the separating part (150;250). [17] A method for manufacturing a plurality of blade ring parts (150; 250) provided on a cylindrical casing (26) covering a rotor (32) in a gas turbine (100), formed in a ring shape centered on a rotational axis (C) of the rotor (32) and covering a blade stage and a guide vane stage, the method comprising: Forming a rotor blade ring part main body (150a; 250a) having a plurality of first cooling flow passages (161; 261), a plurality of second cooling flow passages (162; 262), a plurality of third cooling passages (163; 263), a first return flow passage (165; 265), a second return flow passage (171; 271), a first connecting flow passage (171; 271), a second connecting flow passage (172; 272), and a third connecting passage (173; 273), wherein the first cooling flow passages (161; 261) are arranged on an outer side in a radial direction centered on the rotation axis (C) extending in an axial direction and are arranged aligned in an axial rotation direction, wherein the second cooling flow passages (162; 262) on an inner side in the radial direction with respect to the first cooling flow passages (161;261) extending in the axial direction and arranged aligned in the axial rotation direction, wherein the third cooling flow passages (163; 263) are arranged on an outer side in the radial direction with respect to the first cooling flow passages (161; 261), extend in the axial direction and are arranged aligned in the axial rotation direction, wherein the first return flow passage (165; 265) connects end parts of each of the first cooling flow passages (161; 261) and the second cooling flow passages on a same side in the axial direction, wherein the second return flow passage (171; 271) connects end parts of the third cooling flow passages (163; 263) and the first cooling flow passages (161; 261) on a same side in the axial direction, wherein the first connecting flow passage (171; 271) connects the first Cooling flow passages (161;261) with each other in the axial rotation direction, the second connecting flow passage (172; 272) connects the second cooling flow passages (162; 262) with each other in the axial rotation direction, and the third connecting flow passage (173; 273) connects the third cooling flow passages (163; 263) with each other in the axial rotation direction; Forming the first cooling flow passages (161; 261) between the first connecting flow passage (171; 271) and the first return flow passage (165; 265), Forming the second cooling flow passages (162; 262) between the second connecting flow passage (172; 272) and the first return flow passage (165; 265) in two stages, Forming the third cooling flow passages (163; 263) between the third connecting flow passage (173; 273) and the first connecting flow passage (171; 271), Attaching a first closure element (171a; 251c) which closes the first connecting flow passage (171; 271) to the blade ring parts (150; 250) so that the first connecting flow passage (171; 271) is formed, and Attaching a second closure element (154;254) closing the second connecting flow passage (172;272) to the blade ring parts (150;250).

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