Passage formation plate, split ring, stator vane, gas turbine, and manufacturing method of passage formation plate

Abstract

To inhibit damage of a ceramic layer included in a passage formation plate.SOLUTION: A passage formation plate has a base material, a bond coat layer formed in a part of a surface of the base material, and a ceramic layer formed on a surface of the bond coat layer. The base material has a main part and a protruding part. The main part has: a main part side surface facing an adjacent side which is close to an adjacent component; and a layer formation side surface facing the adjacent side and located closer to the passage side than the main part side surface and closer to the separation side than the main part side surface. The protruding part protrudes from an end at the side opposite to the passage side of the main part side surface toward the adjacent side. The protruding part has: a protruding passage side surface facing the passage side; and a layer formation recessed part recessed from the protruding passage side surface to the side opposite to the passage. The ceramic layer is not formed on the main part side surface. At least the bond coat layer of the bond coat layer and the ceramic layer is formed on a bottom surface of the layer formation recessed part.SELECTED DRAWING: Figure 7

Description

[Technical Field]

[0001] The present disclosure relates to a flow passage forming plate that defines a part of a combustion gas flow passage through which combustion gas flows, a segment ring and a stator blade including this flow passage forming plate, a gas turbine, and a method for manufacturing the flow passage forming plate. [Background technology]

[0002] A gas turbine includes a compressor that compresses air to generate compressed air, a combustor that burns fuel in the compressed air to generate combustion gas, a turbine driven by the combustion gas, and an intermediate casing. The compressor includes a compressor rotor that rotates about an axis and a compressor casing that covers the compressor rotor. The combustor includes a burner that injects fuel and a transition piece (or combustion duct) that sends combustion gas generated by fuel combustion to the turbine. The turbine includes a turbine rotor that rotates about an axis, a turbine casing that covers the turbine rotor, and multiple stator blade rows. The turbine rotor includes a rotor shaft centered on the axis and multiple rotor blade rows attached to the rotor shaft. The multiple rotor blade rows are aligned in the axial direction along which the axis extends. Each rotor blade row has multiple rotor blades aligned in the circumferential direction about the axis. The multiple stator blade rows are aligned in the axial direction and attached to the inner periphery of the turbine casing. Each of the multiple stator blade rows is arranged axially upstream of one of the multiple rotor blade rows. Each stator blade row has multiple stator blades arranged in the circumferential direction about the axis. A plurality of ring segments arranged in the circumferential direction are arranged in the portions between the multiple stator blade rows in the axial direction, that is, on the outer circumferential side of the portion in the axial direction where one of the rotor blade rows is located. The multiple ring segments define a portion of the outer circumferential side of the combustion gas flow path through which combustion gas flows in the turbine.

[0003] The compressor casing and the turbine casing are connected via an intermediate casing. The combustor is attached to this intermediate casing. The transition piece of the combustor is located inside the intermediate casing. Compressed air is discharged from the compressor into the intermediate casing. This compressed air flows into the combustor and is used to combust fuel.

[0004] Among the plurality of stator blade rows, the shroud of the first stage stator blade constituting the stator blade row located most upstream in the axial direction is connected to the outlet flange of the transition piece by an outlet seal (or combustion cylinder seal).

[0005] Among the above-mentioned components of a gas turbine, the shroud and the segmented ring of the stator vane are both flow path forming plates that define part of the combustion gas flow path. These flow path forming plates are both high-temperature parts exposed to high-temperature combustion gas.

[0006] Patent Document 1 below discloses a shroud of a first-stage stator vane adjacent to an outlet seal as a flow path forming plate. This shroud has a base material and a heat shield layer. The base material is formed of, for example, a nickel-based alloy. For example, as described in Patent Document 2 below, the heat shield layer has a metallic bond coat layer formed on a portion of the surface of the base material and a ceramic layer formed on the surface of the bond coat.

[0007] The base material has a main body and a protruding portion. The main body has a main flow path side and a main body side. The main body flow path side faces the flow path side, between the flow path side, which is the side approaching the combustion gas flow path, and the opposite side, which is the opposite side of the flow path side, in the direction away from the combustion gas flow path. The main body side faces the adjacent side, between the adjacent side, which is the side approaching the outlet seal, and the distant side, which is the opposite side of the adjacent side, in the alignment direction in which the base material and the adjacent outlet seal are aligned. The flow path side end of this main body side is connected to the adjacent side end of the main flow path side. The protruding portion protrudes to the adjacent side from a position on the main body side that is closer to the flow path than the main flow path side. The protruding portion has a protruding flow path side that faces the flow path side and a layer formation recess that is recessed from the protruding flow path side toward the opposite side of the flow path. The layer formation recess has a bottom surface that faces the flow path side, a first groove side that extends from the adjacent side end of the bottom surface toward the flow path side, and a second groove side that extends from the distant side end of the bottom surface toward the flow path side and connects to the main body side.

[0008] The heat shield layer is formed continuously on the side surface of the main body flow passage, the side surface of the main body, and the bottom surface of the layer formation recess.

[0009] The adjacent outlet seal has an overlap portion located on the flow path side of the shroud protrusion, and this overlap portion serves to prevent combustion gas from flowing out to the opposite side of the flow path from between the shroud, which serves as a flow path forming plate, and the adjacent outlet seal. [Prior art documents] [Patent documents]

[0010] [Patent Document 1] Patent Publication No. 2021-131041 [Patent Document 2] Japanese Patent Application Laid-Open No. 2015-004132 Summary of the Invention [Problem to be solved by the invention]

[0011] Both the vane and the outlet seal are exposed to high-temperature combustion gases and undergo thermal expansion. During this process, the outlet seal moves relative to the shroud of the vane in the juxtaposition direction. Furthermore, of the bond coat layer and ceramic layer that form the thermal barrier, it is much more difficult to control the thickness of the ceramic layer than the bond coat layer.

[0012] Therefore, as the outlet seal moves relative to the shroud of the vane in the aligning direction, a portion of the ceramic layer of the heat shield layer formed on the bottom surface of the layer formation recess and a portion of the ceramic layer of the heat shield layer formed on the side surface of the main body may come into contact with the overlapping portion of the outlet seal and be damaged.

[0013] Therefore, an object of the present disclosure is to provide a technique that can suppress damage to the ceramic layer of a flow passage forming plate that occurs due to relative movement of an adjacent component with respect to the flow passage forming plate. [Means for solving the problem]

[0014] In order to achieve the above object, a flow path forming plate according to one aspect of the invention comprises: A flow path forming plate is adjacent to an adjacent component that defines a portion of a combustion gas flow path through which combustion gas flows, and defines another portion of the combustion gas flow path. The plate includes a base material, a metallic bond coat layer formed on a portion of the surface of the base material, and a ceramic layer formed on the surface of the bond coat layer. The bond coat layer and the ceramic layer on the bond coat layer form a thermal barrier layer. The base material has a main body and a protrusion. The main body has a main body flow path side surface that faces the flow path side in a direction away from the combustion gas flow path, between a flow path side that is the side that approaches the combustion gas flow path and a counter-flow side that is the opposite side of the flow path side. In an arrangement direction in which the main body and the adjacent component are aligned, the main body side surface faces the adjacent side, between an adjacent side that is the side that approaches the adjacent component and a distant side that is the opposite side of the adjacent side. A layer formation side surface faces the adjacent side and is located closer to the flow path than the main body side surface and closer to the distant side than the main body side surface. The flow path side end of the layer formation side surface is connected to the adjacent side end of the main body flow path side surface. The protruding portion protrudes from the end of the main body side surface on the opposite side to the adjacent side. The protruding portion has a protruding flow path side surface facing the flow path side and a layer formation recess recessed from the protruding flow path side surface to the opposite side to the flow path side. The layer formation recess has a bottom surface facing the flow path side, a first groove side surface extending from the end of the bottom surface on the adjacent side to the flow path side, and a second groove side surface extending from the end of the bottom surface on the remote side to the flow path side and connect to the main body side surface. The heat shield layer is formed on the main body flow path side surface and the layer formation side surface. Of the bond coat layer and the ceramic layer, only the bond coat layer is formed on the main body side surface, or neither the bond coat layer nor the ceramic layer is formed. At least the bond coat layer of the bond coat layer and the ceramic layer is formed on the bottom surface of the layer formation recess, and the position of the layer formed on the bottom surface closest to the flow path is on the opposite side of the flow path from the protruding flow path side surface in the perspective direction, or is the position of the protruding flow path side surface in the perspective direction.

[0015] The adjacent component has an overlapping portion located on the flow path side of the protruding portion of the flow path plate to prevent combustion gas from flowing out from between the adjacent component and the flow path plate toward the opposite side of the flow path. Both the flow path plate and the adjacent component are exposed to high-temperature combustion gas and undergo thermal expansion. During this process, the adjacent component moves relative to the flow path plate in the juxtaposition direction. Furthermore, of the bond coat layer and ceramic layer that form the thermal barrier layer, it is much more difficult to control the thickness of the ceramic layer than the bond coat layer.

[0016] In this embodiment, the layer formed on the bottom surface of the protrusion does not have a portion located closer to the flow path than the protruding flow path side of the protrusion. Therefore, contact between a portion of the layer formed on the bottom surface of the protrusion and the overlapping portion of an adjacent product can be avoided when the adjacent product moves relative to the flow path forming plate in the alignment direction. Therefore, in this embodiment, even if there is a ceramic layer on the bottom surface of the protrusion, damage to this ceramic layer can be suppressed.

[0017] In this embodiment, no ceramic layer is formed on the side of the main body facing the overlap portion in the juxtaposition direction. Therefore, the ceramic layer does not come into contact with the overlap portion when the adjacent product moves relative to the flow path forming plate in the juxtaposition direction. Therefore, in this embodiment, damage to the ceramic layer can be suppressed from this viewpoint as well.

[0018] Here, if a bond coat layer is formed on the side surface of the main body facing the overlap portion in the lateral direction, the surface of this bond coat layer is referred to as the facing surface. Also, if a bond coat layer is not formed on the side surface of the main body facing the overlap portion in the lateral direction, this side surface of the main body is referred to as the facing surface. In this embodiment, as described above, a ceramic layer, the thickness of which is difficult to control, is not formed on the side surface of the main body facing the overlap portion in the lateral direction. Therefore, the position of the facing surface of the conduit forming plate facing the overlap portion in the lateral direction can be accurately controlled, taking into account the relative movement amount between the adjacent product and the conduit forming plate in the lateral direction. Therefore, contact between the facing surface of the conduit forming plate and the overlap portion can be easily avoided during the relative movement of the adjacent product in the lateral direction relative to the conduit forming plate.

[0019] In order to achieve the above object, one aspect of the invention provides a split ring comprising: In a segmented ring disposed on the outer periphery of a plurality of rotor blades arranged in a circumferential direction relative to the axis, the segmented ring is arranged in a plurality of circumferential directions, and defines a portion of the edge on the outer periphery of a combustion gas flow path through which combustion gas flows, the segmented ring constitutes a flow path forming plate in one aspect. Another segmented ring adjacent to the segmented ring that is the flow path forming plate on the first circumferential side constitutes the adjacent part. The approach / departure direction is a radial direction relative to the axis. The arrangement direction is the circumferential direction. The adjacent side is the first circumferential side of the first circumferential side and the second circumferential side in the circumferential direction. The distant side is the second circumferential side.

[0020] In this embodiment, damage to the ceramic layer of the split ring can be suppressed.

[0021] In order to achieve the above object, one aspect of the invention relates to a stator blade, a vane connected via an outlet seal to a combustor capable of burning fuel to generate combustion gas, the vane being aligned in an axial direction along an axis extending from the outlet seal, the vane being disposed in a combustion gas flow path through which the combustion gas from the combustor flows, the vane having an airfoil-shaped cross section perpendicular to the axis and extending in a radial direction about the axis, an inner shroud provided at the radially inner end of the vane body in the radial direction and defining a portion of the radially inner edge of the combustion gas flow path, and an outer shroud provided at the radially outer end of the vane body and defining a portion of the radially outer edge of the combustion gas flow path, the inner shroud being adjacent to the inner outlet seal on the downstream side of the axial direction, the inner shroud being adjacent to the outer outlet seal on the upstream side of the axial direction, the outer shroud being adjacent to the outer outlet seal on the downstream side of the axial direction. The inner shroud and the outer shroud both constitute the flow path forming plate in the one aspect. The inner outlet seal constitutes the adjacent part to the inner shroud. The outer outlet seal constitutes the adjacent part to the outer shroud. The approaching direction is the radial direction. The juxtaposition direction is the axial direction. The adjacent side is the upstream side of the axis. The separated side is the downstream side of the axis.

[0022] In this aspect, damage to the ceramic layer of the inner shroud and the ceramic layer of the outer shroud can be suppressed.

[0023] In order to achieve the above object, a gas turbine according to one aspect of the invention comprises: The gas turbine includes a flow passage forming plate according to the above aspect, a gas turbine rotor rotatable about an axis, and a gas turbine casing that covers the flow passage forming plate and the gas turbine rotor. The gas turbine rotor has a plurality of rows of moving blades arranged in an axial direction along the axis, and a rotor shaft to which the plurality of rows of moving blades are attached and that extends in the axial direction about the axis. The combustion gas flow passage is a space within the gas turbine casing that forms an annular shape around the axis, is located on the outer periphery of the rotor shaft, and extends in the axial direction.

[0024] In order to achieve the above object, a method for manufacturing a flow path forming plate according to one aspect of the invention comprises: A method for manufacturing a flow path forming plate adjacent to an adjacent component that defines a portion of a combustion gas flow path through which combustion gas flows and that defines another portion of the combustion gas flow path, includes the following steps: a base material forming step for forming a base material, a bond coat layer forming step for forming a metallic bond coat layer on a surface of the base material, a ceramic layer forming step for forming a ceramic layer on the surface of the bond coat layer, and a grinding step for grinding a portion of a thermal barrier layer formed by the bond coat layer and the ceramic layer on the bond coat layer. The base material formed in the base material forming step has a main body and a protrusion. The main body has a main body flow path side surface that faces the flow path side, of a flow path side and an opposite flow path side that is closer to the combustion gas flow path, in a direction away from the combustion gas flow path; a main body side surface that faces the adjacent side, of an adjacent side and a distant side that is closer to the adjacent component, in an arrangement direction of the main body and the adjacent component; and a layer forming side surface that faces the adjacent side and is located on the distant side of the main body flow path side surface. The flow path side end of the layer-forming side surface is connected to the adjacent side end of the main body flow path side surface. The protruding portion protrudes toward the adjacent side from a position on the main body side surface that is closer to the flow path than the layer-forming side surface. The protruding portion has a protruding flow path side surface facing the flow path side and a layer-forming recess recessed from the protruding flow path side surface toward the opposite flow path side. The layer-forming recess has a bottom surface facing the flow path side, a first groove side surface extending from the adjacent side end of the bottom surface toward the flow path side, and a second groove side surface extending from the remote side end of the bottom surface toward the flow path side and connecting to the main body side surface. In the bond coat layer forming process, the bond coat layer is formed on the main body flow path side surface, the layer-forming side surface, the main body side surface, and the bottom surface. In the ceramic layer forming process, the ceramic layer is formed on the surface of the bond coat layer formed in the bond coat layer forming process. The grinding process includes a first grinding process for grinding, when there is a portion of the heat shield layer formed in the layer formation recess that protrudes toward the flow path beyond the protruding flow path side, the portion of the heat shield layer formed in the layer formation recess that protrudes toward the flow path beyond the protruding flow path side, and a second grinding process for grinding at least the bond coat layer of the heat shield layer formed on the main body side. [Effects of the Invention]

[0025] According to one aspect of the present disclosure, damage to the ceramic layer of the flow passage forming plate due to relative movement of an adjacent component with respect to the flow passage forming plate can be suppressed. [Brief explanation of the drawings]

[0026] [Figure 1] 1 is a schematic cross-sectional view of a gas turbine in one embodiment according to the present disclosure. [Figure 2] 1 is a cross-sectional view of a main portion of a gas turbine in an embodiment according to the present disclosure. FIG. [Figure 3] 1 is a cross-sectional view of a first stage stator blade and its surroundings in a gas turbine according to an embodiment of the present disclosure. [Figure 4] FIG. 1 is a perspective view of a split ring in one embodiment according to the present disclosure. [Figure 5] FIG. 5 is a cross-sectional view taken along line VV in FIG. [Figure 6] FIG. 6 is a cross-sectional view taken along the line VI-VI in FIG. [Figure 7] FIG. 7 is a cross-sectional view taken along line VII-VII in FIG. [Figure 8] 1 is a flowchart illustrating a manufacturing procedure for a split ring according to an embodiment of the present disclosure. [Figure 9] 5 is a cross-sectional view taken along line VV in FIG. 4 after a base material forming step according to an embodiment of the present disclosure. [Figure 10] FIG. 5 is a cross-sectional view taken along line VV in FIG. 4 after the bond coat layer forming step of one embodiment according to the present disclosure. [Figure 11] FIG. 5 is a cross-sectional view taken along line VV in FIG. 4 after a ceramic layer forming step according to one embodiment of the present disclosure. [Figure 12] FIG. 4 is an explanatory diagram showing a first cutting step in one embodiment according to the present disclosure. [Figure 13] FIG. 10 is an explanatory diagram showing a second cutting step in one embodiment according to the present disclosure. [Figure 14] FIG. 10 is a cross-sectional view of an inner outlet seal and inner shroud in one embodiment according to the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0027] Hereinafter, embodiments of a flow path forming plate according to the present disclosure and a gas turbine including the flow path forming plate will be described in detail with reference to the drawings.

[0028] "Gas Turbine Embodiment" An embodiment of the gas turbine will be described with reference to FIGS.

[0029] As shown in FIG. 1, the gas turbine 10 of this embodiment includes a compressor 20 that compresses air A, a plurality of combustors 30 that burn fuel F in the air A compressed by the compressor 20 to generate combustion gas G, and a turbine 40 that is driven by the combustion gas G.

[0030] The compressor 20 has a compressor rotor 21 that rotates about an axis Ar, a compressor casing 25 that covers the compressor rotor 21, and multiple stator vane rows 26. The turbine 40 has a turbine rotor 41 that rotates about the axis Ar, a turbine casing 45 that covers the turbine rotor 41, and multiple stator vane rows 44. Note that, hereinafter, the direction in which the axis Ar extends will be referred to as the axial direction Da, the circumferential direction about the axis Ar will be simply referred to as the circumferential direction Dc, and the direction perpendicular to the axis Ar will be referred to as the radial direction Dr. Furthermore, one side of the axial direction Da will be referred to as the axial upstream side Dau, and the opposite side will be referred to as the axial downstream side Dad. Furthermore, the side of the radial direction Dr that approaches the axis Ar will be referred to as the radially inner side Dri, and the opposite side will be referred to as the radially outer side Dro.

[0031] The compressor 20 is disposed on the axial upstream side Dau with respect to the turbine 40 .

[0032] The compressor rotor 21 and the turbine rotor 41 are located on the same axis Ar and are connected to each other to form the gas turbine rotor 11. To this gas turbine rotor 11, for example, a rotor of a generator GEN is connected. The gas turbine 10 further includes an intermediate casing 16. This intermediate casing 16 is arranged between the compressor casing 25 and the turbine casing 45 in the axial direction Da. The compressor casing 25, the intermediate casing 16, and the turbine casing 45 are connected to each other to form the gas turbine casing 15.

[0033] As shown in FIGS. 1 and 2 , the compressor rotor 21 has a rotor shaft 22 extending in an axial direction Da about an axis Ar, and a plurality of rotor blade rows 23 attached to the rotor shaft 22. The plurality of rotor blade rows 23 are aligned in the axial direction Da. Each rotor blade row 23 is made up of a plurality of rotor blades 23a aligned in a circumferential direction Dc. One of the plurality of stator blade rows 26 is arranged on the axial downstream side Dad of each of the plurality of rotor blade rows 23. Each stator blade row 26 is provided inside a compressor casing 25. Each stator blade row 26 is made up of a plurality of stator blades 26a aligned in the circumferential direction Dc.

[0034] The turbine rotor 41 has a rotor shaft 42 extending in the axial direction Da centered on the axis Ar, and a plurality of rotor blade rows 43 attached to the rotor shaft 42. The plurality of rotor blade rows 43 are aligned in the axial direction Da. Each rotor blade row 43 is made up of a plurality of rotor blades 43a aligned in the circumferential direction Dc. One of the plurality of stator blade rows 44 is arranged on the axial upstream side Dau of each of the plurality of rotor blade rows 43. Each stator blade row 44 is provided inside a turbine casing 45. Each stator blade row 44 is made up of a plurality of stator blades 44a aligned in the circumferential direction Dc.

[0035] The annular space between the outer circumferential side of the rotor shaft 42 and the inner circumferential side of the turbine casing 45, in which the stator vanes 44a and the rotor blades 43a are arranged in the axial direction Da, forms a combustion gas flow path 49p through which the combustion gas G from the combustor 30 flows. This combustion gas flow path 49p is annular, centered on the axis Ar, and is long in the axial direction Da.

[0036] The turbine casing 45 has a plurality of ring segments 46, a plurality of heat shield rings 47, a blade ring 48, and a turbine casing main body 49. The plurality of ring segments 46 are located radially outwardly (Dro) of the rotor blade row 43, are aligned in the circumferential direction (Dc), and face the rotor blade row 43 in the radial direction (Dr). Each of the plurality of ring segments 46 defines a portion of the edge of the radially outwardly (Dro) of the combustion gas flow path 49p. Therefore, each of the plurality of ring segments 46 is a flow path forming plate. The blade ring 48 forms an annular shape centered on the axis Ar and is located radially outwardly (Dro) of the plurality of ring segments 46 and the stator blades 44a. Of the plurality of heat shield rings 47, one of the heat shield rings 47 is located between the ring segment 46 and the blade ring 48 in the radial direction (Dr) and connects the ring segment 46 and the blade ring 48. Furthermore, of the multiple heat shield rings 47, the remaining heat shield rings 47 are located between the stator blades 44a and the blade ring 48 in the radial direction Dr, and connect the stator blades 44a and the blade ring 48. The blade ring 48 is fixed to the inner peripheral side of the turbine casing body 49.

[0037] The multiple combustors 30 are attached to the intermediate casing 16, lined up in the circumferential direction Dc around the axis Ar. Each combustor 30 has a transition piece (or combustion piece) 32 in which fuel F is burned, and multiple burners 31 that inject fuel into the transition piece 32. The inner circumferential side of the transition piece 32 forms a combustion space (or combustion gas flow path) 39p. When the combustors 30 are attached to the intermediate casing 16, the transition piece 32 extends in a direction that includes a directional component toward the axial downstream side Dad.

[0038] 3, the stator vane 44a constituting the first-stage stator vane row 44 located on the most axially upstream side Dau among the plurality of stator vane rows 44 is connected to the transition piece 32 by outlet seals 80i, 80o. Note that, hereinafter, the first-stage stator vane 44a will be simply referred to as the stator vane 50.

[0039] The stator vane 50 has a blade body 51 having an airfoil-shaped cross section and shrouds 52 provided on both sides of the blade body 51 in the blade height direction. The shroud 52 provided on one side of the blade body 51 in the blade height direction is an inner shroud 52i, and the shroud 52 provided on the other side of the blade body 51 in the blade height direction is an outer shroud 52o. Both the inner shroud 52i and the outer shroud 52o extend in a direction perpendicular to the blade height direction. When the stator vane 50 is attached to the turbine casing 45, the blade height direction is the radial direction Dr. Furthermore, one side of the blade height direction is the radial outer side Dro, and the other side of the blade height direction is the radial inner side Dri. Therefore, the inner shroud 52i is provided on the radial inner side Dri of the blade body 51, and the outer shroud 52o is provided on the radial outer side Dro of the blade body 51. The inner shroud 52i defines a portion of the edge of the radially inner side Dri of the combustion gas flow path 49p. The outer shroud 52o defines the edge of the radially outer side Dro of the combustion gas flow path 49p. Therefore, both the inner shroud 52i and the outer shroud 52o are flow path forming plates.

[0040] The transition piece 32 has a cylinder 33 whose inner circumferential side forms a combustion space (or combustion gas flow path) 39p, and two outlet flanges 34i, 34o provided on the axial downstream side Dad of the cylinder 33. One of the two outlet flanges 34, the inner outlet flange 34i, extends from an end of the radially inner Dri on the axial downstream side Dad of the cylinder 33 toward the radially inner Dri. The other, outer outlet flange 34o, extends from an end of the radially outer Dro on the axial downstream side Dad of the cylinder 33 toward the radially outer Dro.

[0041] Of the two outlet seals 80i, 80o, the inner outlet seal 80i connects the inner outlet flange 34i of the transition piece 32 to the inner shroud 52i. The other, outer outlet seal 80o, connects the outer outlet flange 34o of the transition piece 32 to the outer shroud 52o. A combustion gas flow path 79p is formed between the inner outlet seal and the outer outlet seal. The inner outlet seal 80i defines the edge of the radially inner side Dri of this combustion gas flow path 79p. The outer outlet seal 80o defines the edge of the radially outer side Dro of this combustion gas flow path 79p.

[0042] Hereinafter, an embodiment of the stator vane 50 having the ring segment 46 as the flow passage forming plate, and the inner shroud 52i and the outer shroud 52o as the flow passage forming plates will be described.

[0043] "Embodiment of a split ring" Hereinafter, embodiments of segmented rings serving as flow path forming plates according to the present invention will be described with reference to Figures 4 to 13. Note that the segmented rings described below are all specific examples of the segmented ring 46 described in the "Embodiment of a Gas Turbine" above.

[0044] As shown in FIG. 5, the split ring 100 in this embodiment includes a base material 104, a bond coat layer 102 formed on a portion of the surface of the base material 104, and a ceramic layer 103 formed on the surface of the bond coat layer 102. The thermal barrier layer 101 is formed of the bond coat layer 102 and the ceramic layer 103 on the bond coat layer 102. The base material 104 is, for example, a nickel-based alloy. The bond coat layer 102 is, for example, formed of a metal such as CoNiCrAlY. The ceramic layer 103 is, for example, formed of a ZrO2-based ceramic.

[0045] As shown in FIGS. 4, 5 and 9, the base material 104 has a main body 110, a peripheral wall 131, a hook portion 135, and a protrusion 105.

[0046] The main body 110 is a rectangular plate-shaped member that extends in the axial direction Da and the circumferential direction Dc and has a thickness in the radial direction Dr. The main body 110 has a main body flow path side surface 111p facing the radially inner side Dri, a main body anti-flow path side surface 111a facing the radially outer side Dro and back-to-back with the main body flow path side surface 111p, a front end face 112f facing the axial upstream side Dau, a rear end face 112b facing the axial downstream side Dad, a first main body side surface 113a facing the circumferential first side Dc1 of a circumferential first side Dc1 and a circumferential second side Dc2 in the circumferential direction Dc, and a second main body side surface 113b facing the circumferential second side Dc2 and back-to-back with the first main body side surface 113a.

[0047] The main body 110 further includes a first layer-forming side surface 114a facing the circumferential first side Dc1 and positioned closer to the circumferential second side Dc2 than the first main body side surface 113a, and a second layer-forming side surface 114b facing the circumferential second side Dc2 and positioned closer to the circumferential first side Dc1 than the second main body side surface 113b. The radially inner end Dri of the first layer-forming side surface 114a is connected to the end of the main body flow path side surface 111p on the circumferential first side Dc1. The surface of a corner 115a between the main body flow path side surface 111p and the first layer-forming side surface 114a forms a smoothly curved surface that gradually curves toward the circumferential second side Dc2 as it approaches the radially inner Dri. The first main body side surface 113a is positioned radially outer than the first layer-forming side surface 114a. The radially inner end Dri of the second layer-forming side surface 114b is connected to the end of the main body flow path side surface 111p on the circumferential second side Dc2. The surface of a corner 115b between the main body flow path side surface 111p and the second layer forming side surface 114b forms a smoothly curved surface that gradually approaches the first circumferential side Dc1 as it moves radially inward Dri. The second main body side surface 113b is located radially outward Dro of the second layer forming side surface 114b.

[0048] The peripheral wall 131 protrudes from the main body 110 toward the radially outer side Dro along the outer circumferential edge of the main body 110. The peripheral wall 131 includes a front peripheral wall 131f protruding from the main body 110 toward the radially outer side Dro along a front end surface 112f of the main body 110, a rear peripheral wall 131b protruding from the main body 110 toward the radially outer side Dro along a rear end surface 112b of the main body 110, a first side peripheral wall 131sa protruding from the main body 110 toward the radially outer side Dro along a first main body side surface 113a of the main body 110, and a second side peripheral wall 131sb protruding from the main body 110 toward the radially outer side Dro along a second main body side surface 113b of the main body 110. The second side peripheral wall 131sb protrudes toward the radially outer side Dro from a position on the circumferential first side Dc1 beyond the second main body side surface 113b. A seal groove 139 recessed toward the second circumferential side Dc2 is formed in the second-side peripheral wall 131sb. Within the main body 110, a portion of the second-side peripheral wall 131sb toward the second circumferential side Dc2 and including the second main body side surface 113b forms an overlap portion 117. This overlap portion 117 has an overlap anti-flowpath side surface 118 facing the radially outer side Dro. The end of this overlap anti-flowpath side surface 118 on the second circumferential side Dc2 coincides with the end of the radially outer side Dro of the second main body side surface 113b included in the overlap portion 117.

[0049] A space formed by the main body 110 and the peripheral wall 131 and recessed radially outward Dro forms a cavity C into which cooling air flows to cool the ring segments.

[0050] The hook portion 135 has a front hook portion 135f protruding radially outward from the front peripheral wall 131f and a rear hook portion 135b protruding radially outward from the rear peripheral wall 131b. Both the front hook portion 135f and the rear hook portion 135b are attached to the heat insulating ring 47 described with reference to Figures 2 and 3.

[0051] The protrusion 105 protrudes from the end of the radially outer side Dro of the first main body side surface 113a toward the first circumferential side Dc1. The protrusion 105 has a protruding flow path side surface 106 facing the radially inner side Dri and a layer-forming recess 107 recessed from the protruding flow path side surface 106 toward the radially outer side Dro. The layer-forming recess 107 has a bottom surface 107c facing the radially inner side Dri, a first groove side surface 107a extending from the end of the bottom surface 107c on the first circumferential side Dc1 toward the radially inner side Dri, and a second groove side surface 107b extending from the end of the bottom surface 107c on the second circumferential side Dc2 toward the radially inner side Dri. The second groove side surface 107b is flush with the first main body side surface 113a and is connected to the first main body side surface 113a. A seal groove 109 recessed toward the second circumferential side Dc2 is formed in the protrusion 105. The position of this seal groove 109 in the radial direction Dr coincides with the position of the seal groove 139 formed in the second side peripheral wall 131sb described above in the radial direction Dr.

[0052] The main body 110 further has a plurality of rear end ejection passages 121, a plurality of front communication passages 122, a first side passage 123, a plurality of first side communication passages 124, a second side passage 125, a plurality of second side communication passages 126, and a plurality of second side ejection passages 127. The first side passage 123 extends in the axial direction Da along the first main body side surface 113a and opens at the rear end surface 112b of the main body 110. The second side passage 125 extends in the axial direction Da along the second main body side surface 113b and opens at the rear end surface 112b of the main body 110. All of the multiple rear end ejection passages 121 extend in the axial direction Da between the first side passage 123 and the second side passage 125 and open at the rear end surface 112b of the main body 110.

[0053] One ends of the multiple first side communication passages 124 all open at the corner between the main body 110 and the first side peripheral wall 131sa. The other ends of the multiple first side communication passages 124 all connect to the first side passages 123. Therefore, a portion of the cooling air in the cavity C flows into the first side passages 123 via the multiple first side communication passages 124. The cooling air that flows into the first side passages 123 is ejected from the rear end surface 112b. One ends of the multiple second side communication passages 126 all open at the corner between the main body 110 and the second side peripheral wall 131sb. The other ends of the multiple second side communication passages 126 all connect to the second side passages 125. One ends of the multiple second side ejection passages 127 all connect to the second side passages 125. The other ends of the multiple second side ejection passages 127 open at the second layer forming side surface 114b. As a result, a portion of the cooling air in cavity C flows into second side passages 125 via the multiple second side communication passages 126. A portion of the cooling air that flows into second side passages 125 flows into the multiple second side ejection passages 127. The cooling air that flows into the multiple second side ejection passages 127 is ejected from the second layer forming side surface 114b. The remainder of the cooling air that flows into second side passages 125 is ejected from rear end surface 112b.

[0054] As shown in FIGS. 6 and 9 , one end of each of the multiple front communicating passages 122 opens at a corner between the main body 110 and the front peripheral wall 131f. The multiple front communicating passages 122 extend from this one end toward the axial upstream side Dau and gradually toward the radially inward side Dri. The other end of each of the multiple front communicating passages 122 is connected to the axial upstream side Dau end of one of the multiple rear end ejection passages 121. Therefore, some of the cooling air in the cavity C flows into the multiple rear end ejection passages 121 via the multiple front communicating passages 122. The cooling air that flows into the multiple rear end ejection passages is ejected from the rear end face 112b.

[0055] 5, the bond coat layer 102 is continuously formed on the second layer forming side surface 114b, the main body flow path side surface 111p, the first layer forming side surface 114a, the first main body side surface 113a, and the bottom surface 107c of the layer formation recess 107. Note that the bond coat layer 102 may not be formed on the first main body side surface 113a. However, even when the bond coat layer 102 is formed on the first main body side surface 113a, the thickness of this bond coat layer 102 is thinner than the thickness of the bond coat layer 102 formed on the main body flow path side surface 111p.

[0056] The ceramic layer 103 is formed continuously on the surface of the bond coat layer 102 on the second layer-forming side surface 114b, the surface of the bond coat layer 102 on the main flow path side surface 111p, and the surface of the bond coat layer 102 on the first layer-forming side surface 114a. Whether the bond coat layer 102 is formed on the first main body side surface 113a or not, the ceramic layer 103 is not formed on the first main body side surface 113a. The ceramic layer 103 may not be formed on the surface of the bond coat layer 102 on the bottom surface 107c of the layer-forming recess 107. However, even if the ceramic layer 103 is formed on the surface of the bond coat layer 102 on the bottom surface 107c of the layer-forming recess 107, the thickness of this ceramic layer is thinner than the thickness of the ceramic layer 103 formed on the main flow path side surface 111p.

[0057] Corners 115a and 115b of main body 110 are easily heated by two-sided heating from combustion gas. Furthermore, if ceramic layer 103 is thick, the temperature difference between its surface and inner surface increases, and the thermal stress resulting from this temperature difference makes ceramic layer 103 more susceptible to damage. For this reason, in this embodiment, thickness tc of ceramic layer 103 on the curved surface of corner 115a between main body flow path side surface 111p and first layer-forming side surface 114a and on the curved surface of corner 115b between main body flow path side surface 111p and second layer-forming side surface 114b is slightly thinner than thickness tp of ceramic layer 103 formed on main body flow path side surface 111p.

[0058] Of the multiple ring segments 100 arranged in the circumferential direction Dc, one ring segment 100 is adjacent to another ring segment 100a on the first circumferential side Dc1. As shown in FIGS. 4 and 7, the protruding portion 105 of one ring segment 100 faces the second peripheral wall 131sb of the other ring segment 100a in the circumferential direction Dc. The seal plate 138 is fitted into the seal groove 109 of the protruding portion 105 of one ring segment 100 and the seal groove 139 of the second peripheral wall 131sb of the other ring segment 100a. The first main body side surface 113a of one ring segment 100 faces the second main body side surface 113b of the other ring segment 100a in the circumferential direction Dc. The first layer forming side surface 114a of one ring segment 100 faces the second layer forming side surface 114b of the other ring segment 100a in the circumferential direction Dc. The protruding flow passage side surface 106 of one ring segment 100 and the overlapping non-flow passage side surface 118 between the other segments face each other in the radial direction Dr. Therefore, the other ring segment 100a is adjacent to the one ring segment 100.

[0059] In this embodiment, the circumferential direction Dc is the arrangement direction Dl, the first circumferential side Dc1 is the adjacent side Dla, and the second circumferential side Dc2 is the distant side Dls. The radial direction Dr is the approach direction Dp, the radially inner side Dri is the flow path side Dpp, and the radially outer side Dro is the anti-flow path side Dpa.

[0060] Next, a manufacturing procedure for the split ring 100 of this embodiment will be described with reference to the flowchart shown in FIG.

[0061] First, the base material 104 shown in Fig. 9 is formed (base material forming step S1). The base material 104 is formed by casting or the like using a material for the base material 104 such as a nickel-based alloy.

[0062] Next, a bond coat layer 102 is formed on a portion of the surface of the base material 104 (bond coat layer forming step S2). As shown in Fig. 10 , here, the bond coat layer 102 is continuously formed on the second layer forming side surface 114b, the main body flow path side surface 111p, the first layer forming side surface 114a, the first main body side surface 113a, and the bottom surface 107c of the layer formation recess 107 among the surfaces of the base material 104.

[0063] 11, a ceramic layer 103 is formed on the surface of the bond coat layer 102 (ceramic layer forming step S3). Here, the ceramic layer 103 is continuously formed on the surface of the bond coat layer 102 on the second layer forming side surface 114b, the surface of the bond coat layer 102 on the main flow path side surface 111p, the surface of the bond coat layer 102 on the first layer forming side surface 114a, the surface of the bond coat layer 102 on the first main body side surface 113a, and the surface of the bond coat layer 102 on the bottom surface 107c of the layer formation recess 107. As a result, a thermal barrier layer 101 is continuously formed on the second layer forming side surface 114b, the main flow path side surface 111p, the first layer forming side surface 114a, the first main body side surface 113a, and the bottom surface 107c of the layer formation recess 107.

[0064] Next, a part of the thermal barrier layer 101 is ground (grinding step S4). This grinding step S4 includes a first grinding step S4a and a second grinding step S4b.

[0065] 12, in the first grinding step S4a, the grinding tool T1 is moved toward the separation side Dls (second circumferential side Dc2) along the protruding flow channel side surface 106 to grind the heat shield layer 101 on the bottom surface 107c of the layer formation recess 107. In this embodiment, since the depth dimension of the layer formation recess 107 is smaller than the thickness dimension of the heat shield layer 101 on the main flow channel side surface 111p, at least the ceramic layer 103 of the ceramic layer 103 and the bond coat layer 102 that form this heat shield layer 101 is ground.

[0066] If the depth of the layer formation recess 107 is smaller than the thickness of the heat shield layer 101 on the main flow path side surface 111p but larger than the thickness of the bond coat layer 102, only a portion of the ceramic layer 103 is ground away, and the bond coat layer 102 remains intact. In this case, the thickness of the ceramic layer 103 on the bottom surface 107c of the layer formation recess 107 is thinner than the thickness of the ceramic layer 103 on the main flow path side surface 111p. Also, if the depth of the layer formation recess 107 is smaller than the thickness of the bond coat layer 102 on the main flow path side surface 111p, all of the ceramic layer 103 and a portion of the bond coat layer 102 are ground away. In this case, only the bond coat layer 102 on the bottom surface 107c of the layer formation recess 107 remains.

[0067] In any of the above cases, the position of the layer formed on the bottom surface 107c closest to the flow channel Dpp (radially inner side Dri) is the position of the protruding flow channel side surface 106 in the far direction Dp (radial direction Dr). In other words, the layer formed on the bottom surface 107c and the protruding flow channel side surface 106 are flush with each other.

[0068] Furthermore, if the depth of the layer-forming recess 107 is greater than the thickness of the heat shield layer 101 on the main flow path side surface 111p, most of the ceramic layer 103 remains, and the bond coat layer 102 remains. In this case, the thickness of the heat shield layer 101 on the bottom surface 107c of the layer-forming recess 107 is substantially the same as the thickness of the heat shield layer 101 on the main flow path side surface 111p.

[0069] By performing this first grinding step S4a, the position of the layer formed on the bottom surface 107c closest to the flow channel Dpp becomes the same as the position of the protruding flow channel side surface 106 in the far-near direction Dp, or becomes closer to the protruding flow channel side surface 106 Dls. In other words, by performing this first grinding step S4a, there is no part of the layer formed on the bottom surface 107c that is located closer to the flow channel Dpp than the protruding flow channel side surface 106.

[0070] In the second grinding step S4b, as shown in FIG. 13 , the cutting edge of a grinding tool T2 is directed toward the first body side surface 113a to grind the thermal barrier layer 101 on the first body side surface 113a. In this embodiment, of the ceramic layer 103 and bond coat layer 102 that form the thermal barrier layer 101, at least the entire ceramic layer 103 is ground. By performing this second grinding step S4b, the bond coat layer 102 may remain on the first body side surface 113a, but may not remain on the first body side surface 113a. Even if the bond coat layer 102 remains on the first body side surface 113a, a portion of the bond coat layer 102 is ground away by the grinding tools T1 and T2, and the thickness of the bond coat layer 102 is thinner than the thickness of the bond coat layer 102 on the body flow path side surface 111p.

[0071] This completes the grinding step S4.

[0072] After the grinding step S4 is completed, the finishing step S5 is performed. For example, as shown in FIG. 11 , the opening of the second-side ejection passage 127 may be blocked by the material for forming the bond coat layer 102 and the material for forming the ceramic layer 103. In the finishing step S5, the material for forming the bond coat layer 102 and the material for forming the ceramic layer 103 that is blocking the passage is removed. Even if the passage is not blocked, the material for forming the bond coat layer 102 and the material for forming the ceramic layer 103 that remains in the passage is removed.

[0073] This completes the split ring 100.

[0074] Each of the multiple ring segments 100 is exposed to high-temperature combustion gas and undergoes thermal expansion. During this process, among the multiple ring segments 100 arranged in the circumferential direction Dc, one ring segment 100 is adjacent to a first circumferential side Dc1 of the other ring segment 100 as an adjacent component, and moves relative to the first ring segment 100 in the circumferential direction Dc (arrangement direction Dl). Furthermore, of the bond coat layer 102 and ceramic layer 103 that form the thermal barrier layer 101, it is much more difficult to control the thickness of the ceramic layer 103 than the bond coat layer 102.

[0075] In this embodiment, no portion of the layer formed on the bottom surface 107c of the protrusion 105 is located radially inward Dri (flow path side Dpp) of the protruding flow path side surface 106 of the protrusion 105. Therefore, when another adjacent divided ring 100a moves relative to one divided ring 100 in the circumferential direction Dc, contact between a portion of the layer formed on the bottom surface 107c of the protrusion 105 and the overlap portion 117 of the other divided ring 100a can be avoided. Therefore, in this embodiment, even if a ceramic layer 103 is present on the bottom surface 107c of the protrusion 105, damage to this ceramic layer 103 can be suppressed.

[0076] In this embodiment, the ceramic layer 103 is not formed on the first main body side surface 113a of one divided ring 100 that faces the overlap portion 117 of the other divided ring 100a in the circumferential direction Dc. Therefore, when the adjacent divided ring 100a moves relative to the one divided ring 100 in the circumferential direction Dc, the ceramic layer 103 does not come into contact with the overlap portion 117. Therefore, in this embodiment, damage to the ceramic layer 103 can be suppressed from this viewpoint as well.

[0077] Here, if a bond coat layer 102 is formed on the first body side surface 113a of one split ring 100 that faces the overlap portion 117 of the other split ring 100a in the circumferential direction Dc, the surface of this bond coat layer 102 is referred to as the opposing surface. Also, if a bond coat layer 102 is not formed on the first body side surface 113a of one split ring 100 that faces the overlap portion 117 of the other split ring 100a in the circumferential direction Dc, this first body side surface 113a is referred to as the opposing surface. In this embodiment, as described above, the ceramic layer 103, whose thickness is difficult to control, is not formed on the first body side surface 113a that faces the overlap portion 117 in the alignment direction Dl. Therefore, the position of the opposing surface facing the overlap portion 117 in the circumferential direction Dc can be accurately controlled, taking into account the relative movement between the one split ring 100 and the other split ring 100a in the circumferential direction Dc. Therefore, when the adjacent split ring 100a moves relative to the one split ring 100 in the circumferential direction Dc, contact between the opposing surface of the one split ring 100 and the overlap portion 117 of the other split ring 100a can be easily avoided.

[0078] In this embodiment, the ceramic layer 103 is not formed on the first main body side surface 113a. However, cooling air is ejected from the multiple second-side ejection passages 127 of the other ring segments 100a. This cooling air can prevent combustion gas from flowing between the first main body side surface 113a of one ring segment 100 and the second main body side surface 113b of the other ring segments 100a. Therefore, in this embodiment, thermal damage caused by combustion gas to the first main body side surface 113a of one ring segment 100 and the second main body side surface 113b of the other ring segments 100a can be reduced.

[0079] In this embodiment, the position of the flow path side Dpp among the layers formed on the bottom surface 107c of the protruding portion 105 is the position of the protruding flow path side surface 106 in the radial direction Dr, so there is no portion on the flow path side Dpp of the protruding portion 105 that catches on the overlap portion 117. Therefore, in this embodiment, the overlap portion 117 of another adjacent divided ring 100a can move smoothly relative to the protruding portion 105 of one divided ring 100 in the circumferential direction Dc.

[0080] "Embodiment of Stator Blade" Hereinafter, an embodiment of a stator vane having a flow passage forming plate according to the present invention will be described. The stator vane in this embodiment is a specific example of the first stage stator vane 50 described in the "Embodiment of a Gas Turbine" above.

[0081] As described above with reference to Fig. 3, the stator vane 50 in this embodiment has the blade body 51, the inner shroud 52i, and the outer shroud 52o. The inner shroud 52i is connected to the inner outlet flange 34i of the transition piece 32 via the inner outlet seal 80i. The outer shroud 52o is connected to the outer outlet flange 34o of the transition piece 32 via the outer outlet seal 80o.

[0082] The inner outlet flange 34i, the inner outlet seal 80i, and the inner shroud 52i are aligned in the axial direction Da. The inner outlet seal 80i is adjacent to the inner shroud 52i, which serves as a flow path forming plate, on the axial upstream side Dau. Therefore, the inner outlet seal 80i forms an adjacent part to the inner shroud 52i, which serves as a flow path forming plate.

[0083] The outer outlet flange 34o, the outer outlet seal 80o, and the outer shroud 52o are aligned in the axial direction Da. The outer outlet seal 80o is adjacent to the outer shroud 52o, which serves as a flow path forming plate, on the axial upstream side Dau. Therefore, the outer outlet seal 80o forms an adjacent part to the outer shroud 52o, which serves as a flow path forming plate.

[0084] The configuration of the outer outlet seal 80o is basically the same as the configuration of the inner outlet seal 80i. The configuration of the outer shroud 52o is basically the same as the configuration of the inner shroud 52i. Therefore, hereinafter, the inner outlet seal 80i and the inner shroud 52i will be described with reference to FIG. 14. Note that hereinafter, the inner shroud 52i will be referred to as the inner shroud 60. The arrangement direction Dl in which the inner outlet seal 80i and the inner shroud 60 are arranged is the axial direction Da. The adjacent side Dla in the arrangement direction Dl is the axial upstream side Dau. The distant side Dls in the arrangement direction Dl is the axial downstream side Dad. The direction Dp toward or away from the combustion gas flow path 49p is the radial direction Dr. The flow path side Dpp in the flow path direction Dp is the radial outer side Dro. The opposite flow path side Dpa in the flow path direction Dp is the radial inner side Dri.

[0085] The inner outlet seal 80i has a base material 84, a bond coat layer 82, and a ceramic layer 83. The bond coat layer 82 is formed on a portion of the surface of the base material 84. The ceramic layer 83 is formed on the surface of the bond coat layer 82. The thermal barrier layer 81 is formed of the bond coat layer 82 and the ceramic layer 83.

[0086] The base material 84 of the inner outlet seal 80i has a body portion 85, a transition piece connecting portion 86, and a stator vane connecting portion 87. The body portion 85 expands in directions including the axial direction Da and the circumferential direction Dc. The transition piece connecting portion 86 is provided at the end of the body portion 85 on the axial upstream side Dau. A flange fitting groove 86a is formed in this transition piece connecting portion 86, into which the inner outlet flange 34i of the transition piece 32 fits. The stator vane connecting portion 87 is provided in a portion of the body portion 85 that includes the end of the axial downstream side Dad. A shroud fitting groove 87a is formed in this stator vane connecting portion 87, into which a portion of the inner shroud 60 fits. The portion of the body portion 85 that includes the end of the axial downstream side Dad forms an overlap portion 88. The stator blade connection portion has this overlap portion 88 and a sandwiching portion 89 that is spaced apart radially inward Dri from the overlap portion 88. The shroud fitting groove 87a is formed by the overlap portion 88 and the sandwiching portion 89.

[0087] The heat shield layer 81 is formed on the surface of the radially outer side Dro of the body portion 85. The radially outer side Dro of the heat shield layer 81 formed on the surface of the radially outer side Dro of the body portion 85 becomes the combustion gas flow path 89p. Therefore, this heat shield layer 101 defines part of the edge of the radially inner side Dri of the combustion gas flow path 89p.

[0088] The inner shroud 60 serving as a flow passage forming plate also has a base material 64, a bond coat layer 62, and a ceramic layer 63. The thermal barrier layer 61 is formed by the bond coat layer 62 and the ceramic layer 63.

[0089] The base material 64 has a main body 70 and a protrusion 65 .

[0090] The main body 70 is a rectangular plate-shaped member that extends in the axial direction Da and the circumferential direction Dc and has a thickness in the radial direction Dr. The main body 70 has a main body flow path side surface 71 facing the radially inward direction Dri, a main body side surface 73 facing the axial upstream side Dau, and a layer-forming side surface 74 facing the axial upstream side Dau and located axially downstream Dad of the main body side surface 73. The radially outer end Dro of the layer-forming side surface 74 is connected to the axially upstream end Dau of the main body flow path side surface 71. The surface of a corner 75 between the main body flow path side surface 71 and the layer-forming side surface 74 forms a smoothly curved surface that gradually approaches the axial downstream side Dad as it approaches the radially outward direction Dro. The main body side surface 73 is located radially inward Dri of the layer-forming side surface 74.

[0091] The protrusion 65 protrudes toward the axial upstream side Dau from the end of the radially inner side Dri of the main body side surface 73. This protrusion 65 fits into the shroud fitting groove 87a of the inner outlet seal 80i. Therefore, this protrusion 65 is located radially inner Dri with respect to the overlap portion 88 of the inner outlet seal 80i and faces this overlap portion 88 in the radial direction Dr.

[0092] The protruding portion 65 has a protruding flow path side surface 66 facing the radially outer side Dro, and a layer-forming recessed portion 67 recessed radially inward Dri from the protruding flow path side surface 66. The layer-forming recessed portion 67 has a bottom surface 67c facing the radially outer side Dro, a first groove side surface 67a extending from an end of the bottom surface 67c on the axial upstream side Dau to the radially outer side Dro, and a second groove side surface 67b extending from an end of the bottom surface 67c on the axial downstream side Dad to the radially outer side Dro. The second groove side surface 67b is flush with and connected to the main body side surface 73.

[0093] The bond coat layer 62 is continuously formed on the main flow path side surface 71, the layer formation side surface 74, the main body side surface 73, and the bottom surface 67c of the layer formation recess 67. Note that the bond coat layer 62 may not be formed on the main body side surface 73. Even when the bond coat layer 62 is formed on the main body side surface 73, the thickness of this bond coat layer 62 is thinner than the thickness of the bond coat layer 62 formed on the main flow path side surface 71.

[0094] The ceramic layer 63 is formed continuously on the surface of the bond coat layer 62 on the main flow path side surface 71 and on the surface of the bond coat layer 62 on the layer formation side surface 74. Whether the bond coat layer 62 is formed on the main body side surface 73 or not, the ceramic layer 63 is not formed on the main body side surface 73. The ceramic layer 63 may not be formed on the surface of the bond coat layer 62 on the bottom surface 67c of the layer formation recess 67. Even when the ceramic layer 63 is formed on the surface of the bond coat layer 62 on the bottom surface 67c of the layer formation recess 67, the thickness of this ceramic layer 63 is thinner than the thickness of the ceramic layer 63 formed on the main flow path side surface 71.

[0095] In this embodiment, the thickness of the ceramic layer 63 on the curved surface of the corner 75 between the main flow path side 71 and the layer formation side 74 is slightly thinner than the thickness of the ceramic layer 63 formed on the main flow path side 71.

[0096] The manufacturing procedure for the inner shroud 60 described above is basically the same as the manufacturing procedure for the split ring 100 described with reference to Fig. 8. That is, the manufacturing of the inner shroud 60 also includes a base material forming step, a bond coat layer forming step, a ceramic layer forming step, a grinding step including a first grinding step and a second grinding step, and a finishing step.

[0097] Both the inner outlet seal 80i and the inner shroud 60 are exposed to high-temperature combustion gases and undergo thermal expansion. In this process, the inner outlet seal 80i, which is an adjacent part, moves relative to the inner shroud 60 in the axial direction Da (arrangement direction Dl).

[0098] In this embodiment, of the layer formed on the bottom surface 67c of the protrusion 65, there is no portion located radially outward Dro (flow path side Dpp) of the protruding flow path side surface 66 of the protrusion 65. Therefore, when the adjacent inner outlet seal 80i moves in the axial direction Da relative to the inner shroud 60, it is possible to avoid contact between a portion of the layer formed on the bottom surface 67c of the protrusion 65 and the overlap portion 88 of the inner outlet seal 80i. Therefore, in this embodiment, even if there is a ceramic layer 63 on the bottom surface 67c of the protrusion 65, damage to this ceramic layer 63 can be suppressed.

[0099] In this embodiment, the ceramic layer 63 is not formed on the main body side surface 73 of the inner shroud 60 that faces the overlap portion 88 of the inner outlet seal 80i in the axial direction Da. Therefore, when the adjacent inner outlet seal 80i moves relative to the inner shroud 60 in the axial direction Da, the ceramic layer 63 does not come into contact with the overlap portion 88. Therefore, in this embodiment, damage to the ceramic layer 63 can be suppressed from this viewpoint as well.

[0100] Here, if a bond coat layer 62 is formed on the body side surface 73 of the inner shroud 60 that faces the overlap portion 88 of the inner outlet seal 80i in the axial direction Da, the surface of this bond coat layer 62 is referred to as the opposing surface. Also, if a bond coat layer 62 is not formed on the body side surface 73 of the inner shroud 60 that faces the overlap portion 88 of the inner outlet seal 80i in the axial direction Da, this body side surface 73 is referred to as the opposing surface. As described above, in this embodiment, the ceramic layer 63, whose thickness is difficult to control, is not formed on the body side surface 73 that faces the overlap portion 88 in the alignment direction Dl. Therefore, the position of the opposing surface that faces the overlap portion 88 in the axial direction Da can be accurately controlled, taking into account the amount of relative movement between the inner shroud 60 and the inner outlet seal 80i in the axial direction Da. Therefore, when the adjacent inner outlet seal 80i moves relative to the inner shroud 60 in the axial direction Da, contact between the opposing surface of the inner shroud 60 and the overlap portion 88 of the inner outlet seal 80i can be easily avoided.

[0101] In this embodiment, the position of the radially outermost Dro (flow path side Dpp) among the layers formed on the bottom surface 67c of the protruding portion 65 is the position of the protruding flow path side surface 66 in the radial direction Dr, and therefore there is no portion on the radially outer side Dro of the protruding portion 65 that gets caught by the overlap portion 88. Therefore, in this embodiment, the overlap portion 88 of the inner outlet seal 80i can move smoothly relative to the protruding portion 65 of the inner shroud 60 in the axial direction Da.

[0102] "Variations" The ring segment 100 in the above embodiment has a plurality of second-side ejection passages 127 that can eject cooling air from the second layer forming side surface 114b. However, the ring segment 100 may have a plurality of first-side ejection passages that can eject cooling air from the first layer forming side surface 114a, instead of the plurality of second-side ejection passages 127. In this case, the plurality of first-side ejection passages communicate with the first-side passages 123.

[0103] In the above embodiments, one of the inner outlet seal 80i and the inner shroud 60 may have an ejection passage on the side of the one member facing the other member, through which cooling air can be ejected toward the other member.

[0104] The present disclosure is not limited to the above-described embodiments and modifications, and various additions, modifications, substitutions, partial deletions, etc. are possible within the scope of the conceptual idea and spirit of the present invention as derived from the content defined in the claims and their equivalents.

[0105] "Addendum" The flow path forming plate in the above embodiment can be understood, for example, as follows. (1) The flow path forming plate in the first embodiment is A flow path forming plate adjacent to an adjacent item that defines a portion of a combustion gas flow path through which combustion gas flows and that defines another portion of the combustion gas flow path has a base material (64, 104), a metallic bond coat layer (62, 102) formed on a portion of the surface of the base material (64, 104), and a ceramic layer (63, 103) formed on the surface of the bond coat layer (62, 102). The bond coat layer (62, 102) and the ceramic layer (63, 103) on the bond coat layer (62, 102) form a thermal barrier layer (61, 101). The base material (64, 104) has a main body (70, 110) and a protrusion (65, 105). The main body 70, 110 has a main body flow path side surface 71, 111p facing the flow path side Dpp, which is the side approaching the combustion gas flow path, and an anti-flow path side Dpa, which is the opposite side of the flow path side Dpp, in an approach-to-away direction Dp with respect to the combustion gas flow path, a main body side surface 73, 113a facing the adjacent side Dla, which is the side approaching the adjacent component, and a distant side Dls, which is the opposite side of the adjacent side Dla, in an arrangement direction Dl in which the main body 70, 110 and the adjacent component are arranged, and a layer formation side surface 74, 114a facing the adjacent side Dla and located closer to the flow path side Dpp than the main body side surface 73, 113a and on the distant side Dls than the main body side surface 73, 113a. An end of the flow path side Dpp of the layer formation side surface 74, 114a is connected to an end of the adjacent side Dla of the main body flow path side surface 71, 111p. The protruding portion 65, 105 protrudes from an end of the counter-channel side Dpa of the main body side surface 73, 113a toward the adjacent side Dla. The protruding portion 65, 105 has a protruding channel side surface 66, 106 facing the channel side Dpp and a layer-forming recess 67, 107 recessed from the protruding channel side surface 66, 106 toward the counter-channel side Dpa. The layer-forming recess 67, 107 has a bottom surface 67c, 107c facing the channel side Dpp, a first groove side surface 67a, 107a extending from an end of the bottom surface 67c, 107c on the adjacent side Dla to the channel side Dpp, and a second groove side surface 67b, 107b extending from an end of the bottom surface 67c, 107c on the distance side Dls to the channel side Dpp and connecting to the main body side surface 73, 113a. The heat shield layers 61, 101 are formed on the main flow path side surfaces 71, 111p and the layer formation side surfaces 74, 114a.Of the bond coat layer 62, 102 and the ceramic layer 63, 103, only the bond coat layer 62, 102 is formed on the main body side surface 73, 113a, or neither the bond coat layer 62, 102 nor the ceramic layer 63, 103 is formed. Of the bond coat layer 62, 102 and the ceramic layer 63, 103, at least the bond coat layer 62, 102 is formed on the bottom surface 67c, 107c of the layer formation recess 67, 107, and the position of the layer formed on the bottom surface 67c, 107c closest to the flow path side Dpp is on the anti-flow path side Dpa of the protruding flow path side surface 66, 106 in the far-near direction Dp, or is at the position of the protruding flow path side surface 66, 106 in the far-near direction Dp.

[0106] The adjacent components have overlapping portions 88, 117 located on the flow path side Dpp of the protruding portions 65, 105 of the flow path plate to prevent combustion gas from flowing out from between the adjacent components and the flow path plate toward the opposite flow path side Dpa. Both the flow path plate and the adjacent components are exposed to high-temperature combustion gas and undergo thermal expansion. During this process, the adjacent components move relative to the flow path plate in the alignment direction Dl. Furthermore, of the bond coat layers 62, 102 and ceramic layers 63, 103 that form the thermal barrier layers 61, 101, it is much more difficult to control the thickness of the ceramic layers 63, 103 than the bond coat layers 62, 102.

[0107] In this embodiment, no portion of the layer formed on the bottom surfaces 67c, 107c of the protrusions 65, 105 is located closer to the flow path side Dpp than the protruding flow path side surfaces 66, 106 of the protrusions 65, 105. This makes it possible to avoid contact between a portion of the layer formed on the bottom surfaces 67c, 107c of the protrusions 65, 105 and the overlapping portions 88, 117 of the adjacent products when the adjacent products move relative to the flow path forming plate in the arrangement direction Dl. Therefore, in this embodiment, even if the ceramic layer 63, 103 is present on the bottom surfaces 67c, 107c of the protrusions 65, 105, damage to the ceramic layer 63, 103 can be suppressed.

[0108] In this embodiment, the ceramic layers 63, 103 are not formed on the main body side surfaces 73, 113a that face the overlapping portions 88, 117 in the alignment direction Dl. Therefore, when an adjacent product moves relative to the flow path forming plate in the alignment direction Dl, the ceramic layers 63, 103 do not come into contact with the overlapping portions 88, 117. Therefore, in this embodiment, damage to the ceramic layers 63, 103 can be suppressed from this viewpoint as well.

[0109] Here, if a bond coat layer 62, 102 is formed on the main body side surface 73, 113a that faces the overlap portion 88, 117 in the alignment direction Dl, the surface of this bond coat layer 62, 102 is referred to as the facing surface. Also, if a bond coat layer 62, 102 is not formed on the main body side surface 73, 113a that faces the overlap portion 88, 117 in the alignment direction Dl, this main body side surface 73, 113a is referred to as the facing surface. In this embodiment, as described above, the ceramic layer 63, 103, whose thickness is difficult to control, is not formed on the main body side surface 73, 113a that faces the overlap portion 88, 117 in the alignment direction Dl. Therefore, the position of the facing surface of the conduit plate that faces the overlap portion 88, 117 in the alignment direction Dl can be accurately controlled, taking into account the relative movement between the adjacent product and the conduit plate in the alignment direction Dl. Therefore, contact between the opposing surfaces of the flow path forming plates and the overlapping portions 88, 117 can be easily avoided in the process of the adjacent products moving relative to the flow path forming plates in the arrangement direction Dl.

[0110] (2) The flow path forming plate in the second embodiment is In the flow path forming plate in the first embodiment, the position of the layer formed on the bottom surface 67c, 107c closest to the flow path Dpp is the position of the protruding flow path side surface 66, 106 in the far-near direction Dp.

[0111] In this embodiment, the position of the flow path side Dpp among the layers formed on the bottom surface 67c, 107c is the position of the protruding flow path side surface 66, 106 in the far-to-near direction Dp, so that the flow path side Dpp of the protruding portion 65, 105 does not have a catch portion for the overlap portion 88, 117. Therefore, in this embodiment, the overlap portion 88, 117 of the adjacent product can move smoothly relative to the protruding portion 65, 105 of the flow path forming plate in the arrangement direction Dl.

[0112] (3) The flow path forming plate in the third embodiment is In the flow path forming plate of the first or second embodiment, the depth dimension of the layer forming recess 67, 107 is smaller than the thickness dimension of the heat shield layer 61, 101 on the main flow path side surface 71, 111p.

[0113] After forming the base material 64, 104, suppose that a bond coat layer 62, 102 is uniformly formed on a portion of the surface of the base material 64, 104, and a ceramic layer 63, 103 is formed on the surface of the bond coat layer 62, 102. Then, when the grinding tool T1 is moved in the arrangement direction Dl along the protruding flow channel side surface 66, 106, a portion of the layer formed on the bottom surface 67c, 107c that is located closer to the flow channel side surface Dpp than the protruding flow channel side surface 66, 106 is ground. As a result, in this embodiment, the position of the layer formed on the bottom surface 67c, 107c that is closest to the flow channel side surface Dpp is the position of the protruding flow channel side surface 66, 106 in the approach direction Dp. Therefore, in this embodiment, the overlap portion 88, 117 of the adjacent product can smoothly move relative to the protruding portion 65, 105 of the flow channel forming plate in the arrangement direction Dl.

[0114] (4) The flow path forming plate in the fourth aspect is In the flow path forming plate in the third embodiment, the ceramic layer 63, 103 is present on the bottom surface 67c, 107c of the layer forming recess 67, 107, and the thickness of the ceramic layer 63, 103 is thinner than the thickness of the ceramic layer 63, 103 on the main flow path side surface 71, 111p.

[0115] In this embodiment, since the ceramic layers 63, 103 are present on the bottom surfaces 67c, 107c of the layer-forming recesses 67, 107, the heat-shielding effect of the bottom surfaces 67c, 107c can be improved.

[0116] (5) The flow path forming plate in the fifth aspect is In the flow path forming plate according to any one of the first to fourth embodiments, the surface of a corner 75, 115a, 115b between the main flow path side surface 71, 111p and the layer formation side surface 74, 114a forms a smoothly curved surface that gradually approaches the separation side Dls as it approaches the flow path side Dpp. The thickness of the ceramic layer 63, 103 on the curved surface is thinner than the thickness of the ceramic layer 63, 103 on the main flow path side surface 71, 111p.

[0117] The corners 75, 115a, 115b of the flow path side Dpp of the main body 70, 110 are easily heated by two-way heating due to combustion gas. Furthermore, if the ceramic layer 63, 103 is thick, the temperature difference between its surface and inner surface increases, and the thermal stress resulting from this temperature difference makes the ceramic layer 63, 103 more susceptible to damage. For this reason, in this embodiment, the thickness of the ceramic layer 63, 103 on the curved surface of the corner 75, 115a, 115b between the main flow path side surface 71, 111p and the layer formation side surface 74, 114a is made thinner than the thickness of the ceramic layer 63, 103 formed on the main flow path side surface 71, 111p.

[0118] The divided rings in the above embodiments can be understood, for example, as follows. (6) In the sixth aspect, the divided ring is A ring segment 100 is disposed on the outer periphery of a plurality of rotor blades arranged in a circumferential direction Dc relative to the axis Ar, and is arranged in the circumferential direction Dc to define a portion of the edge on the outer periphery of a combustion gas flow path through which combustion gas flows. The ring segment 100 forms a flow path forming plate in any one of the first to fifth embodiments. Of the ring segment 100 forming the flow path forming plate, one ring segment 100a is adjacent to the first circumferential side Dc1 of the first circumferential side Dc1 and the second circumferential side Dc2 in the circumferential direction Dc, and forms the adjacent part. The approach-to-departure direction Dp is the radial direction Dr relative to the axis Ar. The arrangement direction Dl is the circumferential direction Dc. The adjacent side Dla is the first circumferential side Dc1 of the first circumferential side Dc1 and the second circumferential side Dc2 in the circumferential direction Dc. The distant side Dls is the second circumferential side Dc2.

[0119] In this embodiment, damage to the ceramic layer 103 of the ring segment 100 can be suppressed.

[0120] (7) In the seventh aspect, the divided ring is In the divided ring of the sixth aspect, a portion of the main body 110 including an end of the second circumferential side Dc2, which is the separation side Dls, forms an overlap portion 117. The main body side surface 113a forms a first main body side surface 113a facing the first circumferential side Dc1. The layer formation side surface 114a forms a first layer formation side surface 114a facing the first circumferential side Dc1. The overlap portion 117 has an overlap anti-flow-path side surface 118 that faces the radially outer side Dro of the radially inner side Dri and the radially outer side Dro in the radial direction Dr and is located radially inner Dri than the protruding flow-path side surface 106, a second main body side surface 113b that faces the circumferential second side Dc2 and extends from an end of the overlap anti-flow-path side surface 118 on the circumferential second side Dc2 toward the radially inner side Dri, and a second layer-forming side surface 114b that faces the circumferential second side Dc2 and is located closer to the circumferential first side Dc1 than the second main body side surface 113b. An end of the radially inner side Dri of the second layer-forming side surface 114b is connected to an end of the main body flow-path side surface 111p on the circumferential second side Dc2. The heat shield layers 61, 101 are formed on the second layer-forming side surface 114b.

[0121] (8) In the eighth aspect, the divided ring is The split ring in the seventh embodiment has either a first side ejection passage that opens at the first layer forming side surface 114a and is capable of ejecting cooling air from the first layer forming side surface 114a to the circumferential first side Dc1, or a second side ejection passage 127 that opens at the second layer forming side surface 114b and is capable of ejecting cooling air from the second layer forming side surface 114b to the circumferential second side Dc2.

[0122] In this embodiment, the cooling air ejected from the ejection passages can prevent combustion gas from flowing between the first body side surface 113a of the divided ring 100 serving as the flow path forming plate and the second body side surface 113b of another divided ring 100a serving as the adjacent part. Therefore, in this embodiment, thermal damage caused by combustion gas to the first body side surface 113a of the divided ring 100 serving as the flow path forming plate and the second body side surface 113b of another divided ring 100a serving as the adjacent part can be prevented.

[0123] The stationary blade in the above embodiment can be understood, for example, as follows. (9) In the ninth aspect, the stationary blade is The stator vane 50 is connected via an outlet seal 80 to a combustor 30 capable of burning fuel to generate combustion gas, and is aligned with the outlet seal 80 in an axial direction Da along which an axis Ar extends. The stator vane 50 is disposed in a combustion gas flow path through which the combustion gas from the combustor 30 flows, and is equipped with: a blade body 51 whose cross section perpendicular to the axis Ar forms an airfoil shape and extends in a radial direction Dr relative to the axis Ar; an inner shroud 52i, 60 provided at an end of the radially inner Dri of a radially inner side Dri and a radially outer side Dro of the blade body 51 in the radial direction Dr, and which defines a part of an edge of the radially inner side Dri in the combustion gas flow path; and an outer shroud 52o provided at an end of the radially outer side Dro of the blade body 51, and which defines a part of the edge of the radially outer side Dro in the combustion gas flow path. The inner shroud 52i, 60 is adjacent to the inner outlet seal 80i on the axial downstream side Dad of the axial upstream side Dau and the axial downstream side Dad in the axial direction Da of the inner outlet seal 80i of the outlet seals 80 and the outer outlet seal 80o. The outer shroud 52o is adjacent to the axial downstream side Dad of the outer outlet seal 80o. The inner shroud 52i, 60 and the outer shroud 52o each constitute a flow path forming plate in any one of the first to fifth aspects. The inner outlet seal 80i constitutes the adjacent component to the inner shroud 52i, 60. The outer outlet seal 80o constitutes the adjacent component to the outer shroud 52o. The approach-to-reach direction Dp is the radial direction Dr. The arrangement direction Dl is the axial direction Da. The adjacent side Dla is the axial upstream side Dau. The separation side Dls is the axial downstream side Dad.

[0124] In this embodiment, damage to the ceramic layers of the inner shrouds 52i and 60 and the ceramic layer of the outer shroud 52o can be suppressed.

[0125] The gas turbine in the above embodiment can be understood as follows, for example. (10) A gas turbine according to a tenth aspect includes: The gas turbine includes a flow passage forming plate according to any one of the first to fifth aspects, a gas turbine rotor 11 rotatable about an axis Ar, and a gas turbine casing 15 covering the flow passage forming plate and the gas turbine rotor 11. The gas turbine rotor has a plurality of blade rows arranged in an axial direction Da along which the axis Ar extends, and a rotor shaft to which the plurality of blade rows are attached and which extends in the axial direction Da about the axis Ar. The combustion gas flow passage is a space within the gas turbine casing 15, which forms an annular shape around the axis Ar on the outer periphery of the rotor shaft and extends in the axial direction Da.

[0126] The method for manufacturing the flow path forming plate in the above embodiment can be understood, for example, as follows. (11) A method for manufacturing a flow path forming plate according to an eleventh aspect includes the steps of: A method for manufacturing a flow passage forming plate that is adjacent to an adjacent product that defines a portion of a combustion gas flow passage through which combustion gas flows and that defines another portion of the combustion gas flow passage, includes the steps of: a base material forming step S1 for forming a base material (64, 104); a bond coat layer forming step S2 for forming a metallic bond coat layer (62, 102) on a surface of the base material (64, 104); a ceramic layer forming step S3 for forming a ceramic layer (63, 103) on the surface of the bond coat layer (62, 102); and a grinding step S4 for grinding a portion of a thermal barrier layer (61, 101) formed by the bond coat layer (62, 102) and the ceramic layer (63, 103) on the bond coat layer (62, 102). The base material (64, 104) formed in the base material forming step S1 has a main body (70, 110) and protrusions (65, 105). The main body 70, 110 has a main body flow path side surface 71, 111p that faces the flow path side Dpp of a flow path side Dpp and an opposite flow path side Dpa that are sides that approach the combustion gas flow path in a direction Dp away from the combustion gas flow path, a main body side surface 73, 113a that faces the adjacent side Dla of an adjacent side Dla and a distant side Dls that are sides that approach the adjacent component in an arrangement direction Dl in which the main body 70, 110 and the adjacent component are arranged, and a layer formation side surface 74, 114a that faces the adjacent side Dla and is located closer to the distant side Dls than the main body flow path side surface 71, 111p. An end of the flow path side Dpp of the layer formation side surface 74, 114a is connected to an end of the adjacent side Dla of the main body flow path side surface 71, 111p. The protruding portion 65, 105 protrudes from a position on the opposite-channel side Dpa toward the adjacent-side Dla beyond the layer-formation side 74, 114a in the main body side surface 73, 113a. The protruding portion 65, 105 has a protruding channel side surface 66, 106 facing the channel side Dpp and a layer-formation recessed portion 67, 107 recessed from the protruding channel side surface 66, 106 toward the opposite-channel side Dpa. The layer-formation recessed portion 67, 107 has a bottom surface 67c, 107c facing the channel side Dpp, a first groove side surface 67a, 107a extending from an end of the bottom surface 67c, 107c on the adjacent-side Dla to the channel side Dpp, and a second groove side surface 67b, 107b extending from an end of the bottom surface 67c, 107c on the distance-side Dls to the channel side Dpp and connecting to the main body side surface 73, 113a.In the bond coat layer forming step S2, the bond coat layers 62, 102 are formed on the main body flow path side surfaces 71, 111p, the layer formation side surfaces 74, 114a, the main body side surfaces 73, 113a, and the bottom surfaces 67c, 107c. In the ceramic layer forming step S3, the ceramic layers 63, 103 are formed on the surfaces of the bond coat layers 62, 102 formed in the bond coat layer forming step S2. The grinding process S4 includes a first grinding process S4a for grinding the portion of the heat shield layer 61, 101 formed in the layer formation recess 67, 107 that protrudes toward the flow path side Dpp beyond the protruding flow path side surface 66, 106, in the heat shield layer 61, 101 formed in the layer formation recess 67, 107, and that protrudes toward the flow path side Dpp beyond the protruding flow path side surface 66, 106, and a second grinding process S4b for grinding at least the bond coat layer 62, 102 of the heat shield layer 61, 101 formed on the main body side surface 73, 113a. [Explanation of symbols]

[0127] 10: Gas turbine 11: Gas turbine rotor 15: Gas turbine casing 16: Intermediate casing 20: Compressor 21: Compressor rotor 22: Rotor shaft 23: Moving blade row 23a: Moving blade 25: Compressor casing 26: Stator blade row 26a: static wing 30: Combustor 31: Burner 32: Transition pipe (or combustion pipe) 33: Tube 34: Outlet flange 34i: Inner outlet flange 34o: Outer outlet flange 39p: Combustion space (or combustion gas flow path) 40: Turbine 41: Turbine rotor 42: Rotor shaft 43: Moving blade row 43a: Moving blade 44: Stator blade row 44a: static wing 45: Turbine casing 46: Divided ring 47: Heat shield ring 48: Wing ring 49: Turbine casing body 49p: Combustion gas flow path 50: Stator blade 51: Wing body 52: Shroud 52i,60: Inner shroud 52o: Outer shroud 61: Heat shield layer 62: Bond coat layer 63: Ceramic layer 64: Base material 65:Protrusion 66: Protruding flow channel side 67: Layer forming recess 67c: Bottom 67a: First groove side 67b: Second groove side 70: Main body 71: Main body flow channel side 73: Side of the main body 74:Layer formation side 75: Corner 80i: Inner exit seal 80o: Outer exit seal 81: Heat shield layer 82: Bond coat layer 83: Ceramic layer 84: Base material 85: Torso 86: Transition tube connection part 86a: Flange fitting groove 87: Stator blade connection part 87a: Shroud fitting groove 88;Overlap section 89: Clamping part 89p: Combustion gas flow path 100: Split ring 100a: Other division rings 101: Heat shield layer 102: Bond coat layer 103: Ceramic layer 104: Base material 105:Protrusion 106: Protruding flow channel side 107: Layer forming recess 107c: Bottom 107a: First groove side 107b: Second groove side 109: Seal groove 110:Main body 111p: Side of main body flow channel 111a: Side of main body opposite flow path 112f: Front end surface 112b: Rear end surface 113a: First main body side 113b: Second body side 114a: First layer forming side 114b: Second layer forming side 115a, 115b: Corner 117: Overlap section 118: Overlap counter flow path side 121: Rear end spout passage 122: Front communication path 123: First side passage 124: First side communication path 125:Second side passage 126:Second side communication path 127:Second side spout passage 131: Peripheral wall 131f: Front peripheral wall 131b: Rear peripheral wall 131sa: First side peripheral wall 131sb:Second side peripheral wall 135: Hook part 135f: Front hook 135b: Rear hook part 138: Seal plate 139: Seal groove A: Air G: Combustion gas F:Fuel C: Cavity T1, T2: Grinding tools Ar: Axis line Da: Axial direction Dau: Axis upstream side Dad: Downstream of the axis Dc: Circumferential direction Dc1: First side in circumferential direction Dc2: Second side in circumferential direction Dr: Radial direction Dri: Radial inner direction Dro: Radial outer side Dl: Arrangement direction Dla: adjacent side Dls: Separation side Dp: Perspective direction Dpp: Flow path side Dpa: Counter flow path side

Claims

1. A flow path forming plate is adjacent to an adjacent member that defines a part of a combustion gas flow path through which combustion gas flows, and defines another part of the combustion gas flow path, A base material and a metallic bond coat layer formed on a portion of the surface of the base material; a ceramic layer formed on the surface of the bond coat layer; and a thermal barrier layer is formed by the bond coat layer and the ceramic layer on the bond coat layer; the base material has a body and a protrusion; the main body has a main body flow path side surface that faces the flow path side between a flow path side that is the side that approaches the combustion gas flow path and an opposite flow path side that is the opposite side of the flow path side in a direction away from the combustion gas flow path; a main body side surface that faces the adjacent side between an adjacent side that is the side that approaches the adjacent item and a distant side that is the opposite side of the adjacent side in an arrangement direction in which the main body and the adjacent item are lined up; and a layer formation side surface that faces the adjacent side and is located on the flow path side of the main body side surface and on the distant side of the main body side surface, and an end of the layer formation side on the flow path side is connected to an end of the adjacent side of the main body flow path side surface, the protruding portion protrudes from the end of the side surface of the main body on the opposite side to the flow path toward the adjacent side, the protruding portion has a protruding flow path side surface facing the flow path side, and a layer formation recessed portion recessed from the protruding flow path side surface toward the opposite flow path side, the layer-forming recess has a bottom surface facing the flow path, a first groove side surface extending from an end of the bottom surface on the adjacent side toward the flow path, and a second groove side surface extending from an end of the bottom surface on the remote side toward the flow path and connected to the main body side surface, the heat shield layer is formed on the main flow path side surface and the layer formation side surface, On the side surface of the main body, only the bond coat layer out of the bond coat layer and the ceramic layer is formed, or neither the bond coat layer nor the ceramic layer is formed, At least the bond coat layer of the bond coat layer and the ceramic layer is formed on the bottom surface of the layer formation recess, and a position of the layer formed on the bottom surface closest to the flow path is on the opposite side of the flow path from the protruding flow path side surface in the perspective direction, or is a position on the protruding flow path side surface in the perspective direction. Flow path forming plate.

2. The flow path forming plate according to claim 1, a position of the layer formed on the bottom surface closest to the flow channel is a position on a side surface of the protruding flow channel in the perspective direction; Flow path forming plate.

3. The flow path forming plate according to claim 1, a depth dimension of the layer-forming recessed portion is smaller than a thickness dimension of the heat-shielding layer on the main body flow path side surface; Flow path forming plate.

4. The flow path forming plate according to claim 3, the ceramic layer is present on the bottom surface of the layer-forming recess, and the thickness of the ceramic layer is thinner than the thickness of the ceramic layer on the side surface of the main flow path; Flow path forming plate.

5. The flow path forming plate according to claim 1, a surface of a corner between the main flow path side surface and the layer formation side surface forms a smooth curved surface that gradually approaches the separation side as it approaches the flow path side; the thickness of the ceramic layer on the curved surface is thinner than the thickness of the ceramic layer on the main body flow path side surface; Flow path forming plate.

6. a ring segment disposed on an outer circumferential side of a plurality of rotor blades arranged in a circumferential direction relative to an axis, the ring segment being arranged in the circumferential direction and defining a portion of an edge on the outer circumferential side of a combustion gas flow path through which combustion gas flows, The divided ring forms the flow path forming plate according to any one of claims 1 to 5, Another divided ring adjacent to the divided ring forming the flow path forming plate on the first circumferential side of the first circumferential side and the second circumferential side in the circumferential direction constitutes the adjacent part, the perspective direction is a radial direction relative to the axis, the arrangement direction is the circumferential direction, the adjacent side is the first circumferential side, The separated side is the second circumferential side. split ring.

7. 7. The segmented ring according to claim 6, In the main body, a portion including an end on the second circumferential side, which is the separated side, forms an overlap portion, The main body side surface forms a first main body side surface facing the first circumferential side, the layer-forming side surface forms a first layer-forming side surface facing the first circumferential side, the overlap portion has an overlap counter-flow-path side surface that faces the radially outer side of the radially inner side and the radially outer side in the radial direction and is located radially inner than the protruding flow-path side surface; a second main body side surface that faces the second circumferential side and spreads from an end of the overlap counter-flow-path side surface on the second circumferential side toward the radially inner side; and a second layer-forming side surface that faces the second circumferential side and is located on the first circumferential side of the second main body side surface, and the radially inner end of the second layer-forming side surface is connected to an end of the main body flow-path side surface on the second circumferential side, The heat shield layer is formed on the second layer-forming side surface. split ring.

8. 8. The segmented ring according to claim 7, a first-side ejection passage that opens at the first-layer-forming side surface and is capable of ejecting cooling air from the first-layer-forming side surface to the first side in the circumferential direction, and a second-side ejection passage that opens at the second-layer-forming side surface and is capable of ejecting cooling air from the second-layer-forming side surface to the second side in the circumferential direction, split ring.

9. A stator vane connected via an outlet seal to a combustor capable of burning fuel to generate combustion gas, the stator vane being aligned in an axial direction along an axis of the stator vane, a blade body that is disposed in a combustion gas flow path through which the combustion gas from the combustor flows, the blade body having a blade shape in a cross section perpendicular to the axis and extending in a radial direction relative to the axis; an inner shroud provided at the radially inner end of the blade body in the radial direction, the inner shroud defining a portion of the radially inner edge of the combustion gas flow path; an outer shroud provided at the radially outer end of the blade body and defining a portion of the radially outer edge of the combustion gas flow path; Equipped with the inner shroud is adjacent to the inner outlet seal of the inner outlet seal and the outer outlet seal on the axial downstream side of the inner outlet seal, of the axial upstream side and the axial downstream side in the axial direction, the outer shroud is adjacent to the outer outlet seal on a downstream side of the axis, The inner shroud and the outer shroud each constitute a flow path forming plate according to any one of claims 1 to 5, the inner outlet seal forms the abutment against the inner shroud; the outer outlet seal forms the abutment against the outer shroud; the perspective direction is the radial direction, the arrangement direction is the axial direction, the adjacent side is the axial upstream side, The separated side is the downstream side of the axis. Static wing.

10. The flow path forming plate according to any one of claims 1 to 5, a gas turbine rotor rotatable about an axis; a gas turbine casing that covers the passage forming plate and the gas turbine rotor; Equipped with the gas turbine rotor includes a plurality of rotor blade rows arranged in an axial direction along which the axis extends, and a rotor shaft to which the plurality of rotor blade rows are attached, the rotor shaft extending in the axial direction with the axis as its center, the combustion gas flow path is a space within the gas turbine casing, the space being annular about the axis and located on an outer circumferential side of the rotor shaft, and extending in the axial direction. Gas turbine.

11. 1. A method for manufacturing a flow path forming plate that is adjacent to an adjacent item that defines a part of a combustion gas flow path through which combustion gas flows and that defines another part of the combustion gas flow path, comprising: a base material forming step of forming a base material; a bond coat layer forming step of forming a metallic bond coat layer on the surface of the base material; a ceramic layer forming step of forming a ceramic layer on the surface of the bond coat layer; a grinding step of grinding a portion of a thermal barrier layer formed by the bond coat layer and the ceramic layer on the bond coat layer; Run The base material formed in the base material forming step is a body and a protrusion; the main body has a main body flow path side surface that faces the flow path side of the flow path side that is the side that approaches the combustion gas flow path and an opposite flow path side in a direction away from the combustion gas flow path, a main body side surface that faces the adjacent side of the adjacent side that is the side that approaches the adjacent item and an opposite side in an arrangement direction in which the main body and the adjacent item are arranged, and a layer formation side surface that faces the adjacent side and is located on the more distant side than the main body flow path side surface, and an end of the layer formation side surface on the flow path side is connected to an end of the adjacent side of the main body flow path side surface, the protruding portion protrudes from a position on the side surface of the main body that is on the opposite side to the flow path than the layer formation side surface toward the adjacent side, the protruding portion has a protruding flow path side surface facing the flow path side, and a layer formation recessed portion recessed from the protruding flow path side surface toward the opposite flow path side, the layer-forming recess has a bottom surface facing the flow path, a first groove side surface extending from an end of the bottom surface on the adjacent side toward the flow path, and a second groove side surface extending from an end of the bottom surface on the remote side toward the flow path and connected to the main body side surface, In the bond coat layer forming step, the bond coat layer is formed on the main body flow path side surface, the layer formation side surface, the main body side surface, and the bottom surface, In the ceramic layer forming step, the ceramic layer is formed on the surface of the bond coat layer formed in the bond coat layer forming step, The grinding step includes: a first grinding step of grinding, when a portion of the heat shield layer formed in the layer formation recessed portion protrudes toward the flow channel beyond the protruding flow channel side surface, the portion of the heat shield layer formed in the layer formation recessed portion protruding toward the flow channel beyond the protruding flow channel side surface; a second grinding step of grinding at least the bond coat layer of the thermal barrier layer formed on the side surface of the main body; Including, A method for manufacturing a flow path forming plate.

Images