Stator blade and gas turbine with the same

Abstract

To suppress damage to a blocking plate joined to a shroud.SOLUTION: A stator blade comprises a blade body, a second shroud, a blade air passage, and a blocking plate fixed to the second shroud. A recess part is formed in the second shroud. The blade air passage penetrates the blade body and a second shroud body in the blade height direction. The blocking plate partitions a cooling air space in the recess part from a space on a blade-height second side relative to the cooling air space. The blocking plate comprises: a passage-facing part which faces the blade air passage in the blade height direction; a transition part which is connected around the passage-facing part; and an outer peripheral part which is connected around the transition part and at least a part of which is joined to a peripheral wall. The passage-facing part is positioned on the blade-height second side relative to a connection part with the transition part in the outer peripheral part.SELECTED DRAWING: Figure 6

Description

Technical Field

[0001] The present disclosure relates to a stator vane and a gas turbine including the same.

Background Art

[0002] A gas turbine includes a compressor capable of compressing air to generate compressed air, a combustor capable of burning fuel in the compressed air to generate combustion gas, and a turbine drivable by the combustion gas. The turbine includes a rotor that rotates about an axis and a turbine casing that covers the rotor. The rotor has a rotor shaft that extends in the axial direction about the axis and a plurality of moving blade rows attached to the rotor shaft. The plurality of moving blade rows are arranged at intervals in the axial direction. Each of the plurality of moving blade rows has a plurality of moving blades arranged in the circumferential direction with respect to the axis. Inside the turbine casing, a plurality of stator vane rows are provided. The plurality of stator vane rows are arranged at intervals in the axial direction. Each of the plurality of stator vane rows has a plurality of stator vanes arranged in the circumferential direction with respect to the axis.

[0003] Patent Document 1 below discloses a stator vane of a gas turbine. This stator vane has a blade body extending in the radial direction with respect to the axis, an outer shroud provided on the radially outer side of the blade body, an inner shroud provided on the radially inner side of the blade body, and a blade cooling air passage. The blade body of the stator vane is arranged in a combustion gas flow path through which combustion gas passes. The outer shroud extends in a direction perpendicular to the radial direction in which the blade body extends, and has an outer shroud body that defines the radially outer edge of the combustion gas flow path, and a peripheral wall protruding radially outward from the outer peripheral edge of the outer shroud body. The outer shroud body and the peripheral wall jointly form a recess that is recessed radially inward on the radially outer side of the outer shroud body. The inner shroud extends in a direction perpendicular to the radial direction in which the blade body extends, and has an inner shroud body that defines the radially inner edge of the combustion gas flow path, and a peripheral wall protruding radially inward from the outer peripheral edge of the inner shroud body. The inner shroud body and the peripheral wall jointly form a recess that is recessed radially outward on the radially inner side of the inner shroud body. The opening of this recess is blocked by a blocking plate joined to the edge of this opening. The blade cooling air passage penetrates the outer shroud body, the blade body, and the inner shroud body in the radial direction.

[0004] This stator vane further includes an insert (or insert cylinder) arranged in the blade air passage. The insert has a cylindrical body extending in the radial direction and forming a cylindrical shape. A plurality of impingement holes penetrating from the inner peripheral side to the outer peripheral side are formed in this cylindrical body. In this stator vane, the cooling air that has flowed into the recess of the outer shroud flows into the insert in the blade cooling air passage. After this cooling air passes through the plurality of impingement holes of the insert, it flows into the recess formed on the radially inner side of the inner shroud body.

Prior Art Document

Patent Document

[0005]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0006] In the technology described in Patent Document 1 above, while the inner shroud is exposed to high-temperature combustion gas, the plugging plate joined to the inner shroud is in contact with cooling air and not exposed to the combustion gas. For this reason, a thermal expansion difference may occur between the inner shroud and the plugging plate, and there is a risk that the joint portion between the inner shroud and the plugging plate or the plugging plate may be damaged.

[0007] Therefore, an object of the present disclosure is to provide a stator vane capable of suppressing damage to a plugging plate joined to a shroud and a joint portion between the shroud and the plugging plate, and a gas turbine including the same.

Means for Solving the Problems

[0008] As one aspect of the invention for achieving the above object, a stator vane An airfoil-shaped cross-section, a wing body extending in a wing height direction having a direction component perpendicular to the cross-section, a wing air passage extending in the wing height direction inside the wing body through which cooling air can flow, a first shroud provided at an end on a first side of the wing height of the wing body, a second shroud provided at an end on a second side of the wing height opposite to the first side of the wing height of the wing body, and a blocking plate fixed to the second shroud. The first shroud has a first shroud body that extends in a direction perpendicular to the wing height direction from the end on the first side of the wing height of the wing body. The second shroud has a second shroud body that extends in a direction perpendicular to the wing height direction from the end on the second side of the wing height of the wing body, and a peripheral wall that protrudes from the outer peripheral edge of the second shroud body to the second side of the wing height. The second shroud body and the peripheral wall together form a concave portion that is concave on the first side of the wing height on the second side of the wing height of the second shroud body. The wing air passage penetrates the first shroud body, the wing body, and the second shroud body in the wing height direction. The blocking plate is disposed at a distance from the second shroud body on the second side of the wing height, and partitions the cooling air space in the concave portion and the space on the second side of the wing height from the cooling air space. The blocking plate has a passage facing portion that faces the wing air passage in the wing height direction, a transition portion connected around the passage facing portion, and an outer peripheral portion connected around the transition portion and at least partially joined to the peripheral wall. The passage facing portion is located on the second side of the wing height from the outer peripheral portion. The transition portion is formed to gradually face the second side of the wing height as it approaches the passage facing portion from the outer peripheral portion.

[0009] The first shroud, the airfoil, and the second shroud are exposed to the high-temperature combustion gas G. On the other hand, the plugging plate joined to the second shroud is in contact with the cooling air and not exposed to the combustion gas G. Therefore, a thermal expansion difference occurs between the second shroud and the plugging plate. In this aspect, even if a thermal expansion difference occurs between the second shroud and the plugging plate, the connection portions of the passage facing portion and the transition portion and the connection portion of the transition portion and the outer peripheral portion are deformed, and the plugging plate can accept this thermal expansion difference without difficulty. Thus, in this aspect, damage to the joint portion between the second shroud and the plugging plate and the plugging plate can be suppressed.

[0010] Also, in this aspect, the distance between the passage facing portion and the second shroud main body is larger than at least the distance between the connection portion with the transition portion and the second shroud main body in the outer peripheral portion. If the distance between the passage facing portion and the second shroud main body is made the same as the distance between the connection portion with the transition portion and the second shroud main body in the outer peripheral portion, this aspect can increase the distance between the passage facing portion and the second shroud main body. Therefore, in this aspect, it is possible to suppress a pressure drop of the cooling air due to the cooling air colliding with the passage facing portion of the plugging plate. Thus, in this aspect, the cooling air that has passed through the blade air passage and flowed into the recess of the second shroud can be effectively used for cooling the second shroud and the like.

[0011] As one aspect of the invention for achieving the above object, a gas turbine includes: a stator blade as the one aspect, a rotor rotatable about an axis, and a turbine casing covering the rotor. The stator blade is attached inside the turbine casing such that the blade height direction is the radial direction with respect to the axis.

Advantages of the Invention

[0012] According to one aspect of the present disclosure, damage to the plugging plate joined to the shroud and the joint portion between the shroud and the plugging plate can be suppressed.

Brief Description of the Drawings

[0013]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

Figure 7

Figure 8

Figure 9

Figure 10

Figure 11

Figure 12

Figure 13

Figure 14

Figure 15

Figure 16

Mode for Carrying Out the Invention

[0014] Hereinafter, an embodiment of the present disclosure and its modifications will be described in detail with reference to the drawings.

[0015] "Embodiment of Gas Turbine" An embodiment of the gas turbine will be described with reference to FIGS. 1 and 2.

[0016] As shown in FIG. 1, the gas turbine in this embodiment includes a compressor 10 capable of compressing outside air A to generate compressed air Acom, a combustor 20 capable of burning fuel F from a fuel supply source in the compressed air Acom to generate combustion gas G, and a turbine 30 drivable by the combustion gas G.

[0017] The compressor 10 has a compressor rotor 11 that rotates about an axis Ar, a compressor casing 18 that covers the compressor rotor 11, and a plurality of stationary blade rows 15. The turbine 30 has a turbine rotor 31 that rotates about the axis Ar, a turbine casing 38 that covers the turbine rotor 31, and a plurality of stationary blade rows 35. Hereinafter, the direction in which the axis Ar extends is defined as the axial direction Da, the circumferential direction centered on this axis Ar is simply defined as the circumferential direction Dc, and the direction perpendicular to the axis Ar is defined as the radial direction Dr. Also, one side in the axial direction Da is defined as the upstream side Dau of the axis, and the opposite side is defined as the downstream side Dad of the axis. Further, the side approaching the axis Ar in the radial direction Dr is defined as the inner side Dri in the radial direction, and the opposite side is defined as the outer side Dro in the radial direction.

[0018] The compressor 10 is arranged on the upstream side Dau of the axis with respect to the turbine 30.

[0019] The compressor rotor 11 and the turbine rotor 31 are located on the same axis Ar and are connected to each other to form the gas turbine rotor 1. For example, the rotor of a generator GEN is connected to this gas turbine rotor 1. The gas turbine further includes an intermediate casing 6. This intermediate casing 6 is arranged between the compressor casing 18 and the turbine casing 38 in the axial direction Da. The compressor casing 18, the intermediate casing 6, and the turbine casing 38 are connected to each other to form the gas turbine casing 8.

[0020] As shown in FIGS. 1 and 2, the compressor rotor 11 has a rotor shaft 12 that extends in the axial direction Da about the axis Ar, and a plurality of moving blade rows 13 attached to the rotor shaft 12. The plurality of moving blade rows 13 are arranged in the axial direction Da. Each moving blade row 13 is composed of a plurality of moving blades arranged in the circumferential direction Dc. On the downstream side Dad in the axial direction of each of the plurality of moving blade rows 13, one of the plurality of stationary blade rows 15 is arranged. Each stationary blade row 15 is provided inside the compressor casing 18. Each stationary blade row 15 is composed of a plurality of stationary blades arranged in the circumferential direction Dc.

[0021] The turbine rotor 31 has a rotor shaft 32 that extends in the axial direction Da about the axis Ar, and a plurality of moving blade rows 33 attached to the rotor shaft 32. The plurality of moving blade rows 33 are arranged in the axial direction Da. Each moving blade row 33 is composed of a plurality of moving blades arranged in the circumferential direction Dc. On the upstream side Dau in the axial direction of each of the plurality of moving blade rows 33, one of the plurality of stationary blade rows 35 is arranged. Each stationary blade row 35 is provided inside the turbine casing 38. Each stationary blade row 35 is composed of a plurality of stationary blades arranged in the circumferential direction Dc.

[0022] An annular space between the outer peripheral side of the rotor shaft 32 and the inner peripheral side of the turbine casing 38, where the moving blade row 33 and the stationary blade row 35 are arranged in the axial direction Da, forms a combustion gas flow path 39 through which the combustion gas G from the combustor 20 flows. This combustion gas flow path 39 is annular about the axis Ar and extends in the axial direction Da.

[0023] Inside the turbine casing 38, in addition to a plurality of stationary blade rows 35, a plurality of split rings 37 are provided. The plurality of split rings 37 are located at the position in the axial direction Da where the moving blade row 33 exists and are located radially outside Dro of the moving blade row 33. Thus, the plurality of split rings 37 are located between the plurality of stationary blade rows 35 arranged in the axial direction Da. The split ring 37 defines a part of the edge of the radially outer Dro of the combustion gas flow path 39.

[0024] The combustor 20 is attached to the intermediate casing 6. As shown in FIG. 2, the combustor 20 has a tail pipe (or combustion cylinder) 22 in which fuel F burns internally and a plurality of burners 21 for injecting fuel into the tail pipe 22.

[0025] A cooling device 40 is connected to the gas turbine of the present embodiment. This cooling device 40 has a bleed line 41, a cooler 42, a boost compressor 43, and a cooling air line 44. One end of the bleed line 41 is connected to the intermediate casing 6, and the other end of the bleed line 41 is connected to the suction port of the boost compressor 43. This bleed line 41 can bleed the compressed air in the intermediate casing 6 outside the gas turbine casing 8. The cooler 42 is provided in the bleed line 41 and can cool the compressed air flowing through the bleed line 41. The boost compressor 43 can boost the compressed air cooled by the cooler 42. The cooling air line 44 has one end and a plurality of other ends. One end of the cooling air line 44 is connected to the discharge port of the boost compressor 43. The plurality of other ends of the cooling air line 44 are connected to any one of a plurality of high-temperature components such as stationary blades exposed to the combustion gas G. This cooling air line 44 can guide the compressed air from the boost compressor 43 as cooling air Acl to the high-temperature components.

[0026] "Embodiment of the Stationary Vane" The embodiment of the stationary vane will be described with reference to FIGS. 3 to 10. Note that all the stationary vanes described below are the stationary vanes that constitute the stationary vane row 35 described in the above "Embodiment of the Gas Turbine".

[0027] As shown in FIGS. 3 to 5, the stationary vane of the present embodiment has a vane body, an inner shroud (second shroud) 60i, an outer shroud (first shroud) 60o, a plurality of vane air passages 56, a plurality of leading-edge injection passages 59f, and a plurality of trailing-edge injection passages 59b.

[0028] The vane body has an airfoil-shaped cross section and extends in a vane height direction Dr having a direction component perpendicular to the cross section. As shown in FIG. 2, when this stationary vane is attached to the turbine casing 38, the vane height direction Dr becomes the radial direction Dr. This vane body (36b) is disposed in a combustion gas flow path 39 (see FIG. 2) through which the combustion gas G flows. The inner shroud is provided at the end of the vane height second side Dri of both sides in the vane height direction Dr of the vane body. In other words, the inner shroud is provided at the end of the vane body on the radially inner side Dri. The inner shroud defines the radially inner edge of the annular combustion gas flow path 39. The outer shroud is provided at the end of the vane height first side Dro of both sides in the vane height direction Dr of the vane body. In other words, the outer shroud is provided at the end of the vane body on the radially outer side Dro. The outer shroud defines the radially outer edge of the annular combustion gas flow path 39. Hereinafter, the vane height direction Dr will be referred to as the radial direction Dr. Also, the vane height first side Dro will be referred to as the radially outer side Dro, and the vane height second side Dri will be referred to as the radially inner side Dri.

[0029] The airfoil has a leading edge 52, a trailing edge 53, a pressure surface connecting the leading edge 52 and the trailing edge 53, and a suction surface connecting the leading edge 52 and the trailing edge 53 and facing the pressure surface. The leading edge 52, the trailing edge 53, the pressure surface, and the suction surface all extend in the radial direction Dr. The leading edge is the end on the upstream side Dau of the axis in the airfoil. The trailing edge is the end on the downstream side Dad of the axis in the airfoil. The pressure surface is a concave surface, and the suction surface is a convex surface. The pressure surface faces the circumferential pressure side Dcp which is on one side of the circumferential direction Dc. The suction surface faces the circumferential suction side Dcn which is on the other side of the circumferential direction Dc.

[0030] The inner shroud (second shroud) 60i has an inner shroud body (second shroud body) 61i and a peripheral wall as shown in FIGS. 4 and 5. The inner shroud body extends in a direction perpendicular to the radial direction Dr from the end on the inner side Dri of the airfoil in the radial direction. This inner shroud body has a gas path surface facing the outer side Dro in the radial direction, a counter gas path surface facing the inner side Dri in the radial direction, a front end surface 62f which is the end surface on the upstream side Dau of the axis, a rear end surface 62b which is the end surface on the downstream side Dad of the axis, a pressure side end surface 63p which is the end surface on the circumferential pressure side Dcp, and a suction side end surface 63n which is the end surface on the circumferential suction side Dcn. The front end surface 62f and the rear end surface 62b are substantially parallel. Also, the pressure side end surface 63p and the suction side end surface 63n are substantially parallel. Therefore, when viewed from the radial direction Dr, the inner shroud body forms a parallelogram shape.

[0031] The peripheral wall protrudes radially inward Dri from the anti-gas path surface of the inner shroud body. This peripheral wall is provided along the end face of the inner shroud body. The peripheral wall has a front wall 65f and a rear wall 65b that face each other in the axial direction Da, and a positive pressure side wall 65p and a negative pressure side wall 65n that face each other in the circumferential direction Dc. The front wall 65f is provided at a position along the front end face 62f of the inner shroud body. The rear wall 65b is provided at a position along the rear end face 62b of the inner shroud body. The positive pressure side wall 65p is provided at a position along the positive pressure side end face 63p of the inner shroud body. The negative pressure side wall 65n is provided at a position along the negative pressure side end face 63n of the inner shroud body. In the inner shroud, a recess that is recessed radially outward Dro is formed by the inner shroud body and the peripheral wall. Note that the surface of the positive pressure side Dcp in the circumferential direction of the positive pressure side wall 65p and the positive pressure side end face 63p of the inner shroud body are flush. Also, the surface of the negative pressure side Dcn in the circumferential direction of the negative pressure side wall 65n and the negative pressure side end face 63n of the inner shroud body are flush. Although the rear wall 65b is formed along the rear end face 62b of the inner shroud body, it is formed on the upstream side Dau in the axial direction from the rear end face 62b.

[0032] Among the plurality of stator blade rows 35 shown in FIG. 2, a retainer that protrudes radially inward Dri from the positive pressure side wall 65p and the negative pressure side wall 65n of the inner shroud is provided on the stator blades that constitute any one of the stator blade rows 35. This retainer is located between the front wall 65f and the rear wall 65b in the axial direction Da, and is formed from the positive pressure side end face 63p to the negative pressure side end face 63n. This retainer contacts the radially outer Dro end of the inner cover 7 fixed to the gas turbine casing 8, and serves to support the radially inner Dri portion of the stator blade by the radially outer Dro end of the inner cover 7.

[0033] The outer shroud (first shroud) 60o has, as shown in FIGS. 3 and 5, an outer shroud body (first shroud body) 61o, a peripheral wall 65o, a front hook 68f, and a rear hook 68b. The outer shroud body extends in a direction perpendicular to the radial direction Dr from the end on the radially outer side Dro of the blade body. The outer shroud body also has, similar to the inner shroud body, a gas path surface, a counter gas path surface, a front end surface 62f, a rear end surface 62b, a positive pressure side end surface 63p, and a negative pressure side end surface 63n. The outer shroud body also forms a parallelogram shape when viewed from the radial direction Dr, similar to the inner shroud body. Note that the gas path surface of the inner shroud body faces the radially outer side Dro, while the gas path surface of the outer shroud body faces the radially inner side Dri.

[0034] The peripheral wall 65o protrudes radially outward Dro from the counter gas path surface of the outer shroud body. This peripheral wall 65o is provided along the end surface of the outer shroud body. The peripheral wall 65o of the outer shroud also has, similar to the peripheral wall of the inner shroud, a front wall 65f, a rear wall 65b, a positive pressure side wall 65p, and a negative pressure side wall 65n. The front wall 65f is provided at a position along the front end surface 62f of the outer shroud body. The rear wall 65b is provided at a position along the rear end surface 62b of the outer shroud body. The positive pressure side wall 65p is provided at a position along the positive pressure side end surface 63p of the outer shroud body. The negative pressure side wall 65n is provided at a position along the negative pressure side end surface 63n of the outer shroud body. A recess is formed in the outer shroud, which is recessed toward the radially inner side Dri by the outer shroud body and the peripheral wall 65o. Note that the surface on the positive pressure side Dcp in the circumferential direction of the positive pressure side wall 65p and the positive pressure side end surface 63p of the outer shroud body are flush. Also, the surface on the negative pressure side Dcn in the circumferential direction of the negative pressure side wall 65n and the negative pressure side end surface 63n of the outer shroud body are flush.

[0035] The front hook 68f is formed to protrude radially outward Dro from the front wall 65f. Also, the rear hook 68b is formed to protrude radially outward Dro from the rear wall 65b. Both the front hook 68f and the rear hook 68b serve to attach the stator blade to the turbine casing 38.

[0036] As shown in FIGS. 3 and 5, the plurality of wing air passages 56 include a first wing air passage, a second wing air passage 56b, and a third wing air passage 56c. The first wing air passage, the second wing air passage 56b, and the third wing air passage 56c are arranged in this order along the camber line CL of the wing body from the side of the leading edge 52 of the wing body toward the side of the trailing edge 53. The first wing air passage, the second wing air passage 56b, and the third wing air passage 56c all extend in the radial direction Dr. The first wing air passage penetrates the outer shroud body, the wing body, and the inner shroud body in the radial direction Dr. Therefore, this first wing air passage is open at the radially outer end Dro and the radially inner end Dri. That is, the first wing air passage has an outer opening 56ao that is the opening at the radially outer end Dro and an inner opening 56ai that is the opening at the radially inner end Dri. The radially inner end Dri of the second wing air passage 56b opens on the anti-gas path surface of the inner shroud body. That is, the second wing air passage 56b has an inner opening 56bi that is the opening at the radially inner end Dri. The radially outer end Dro of this second wing air passage 56b is closed by the outer shroud body. The radially inner end Dri of the third wing air passage 56c is closed by the inner shroud body, and the radially outer end Dro of this third wing air passage 56c is closed by the outer shroud body. The radially outer portion Dro of the second wing air passage 56b and the radially outer portion Dro of the third wing air passage 56c communicate with each other.

[0037] The first wing air passage, the second wing air passage 56b, and the third wing air passage 56c are all defined by a plurality of passage defining surfaces. A part of the cooling air Acl flowing through the first wing air passage is injected into the combustion gas flow path 39 (see FIG. 2) outside the wing body from the vicinity of the leading edge of the wing body, so that the plurality of leading edge injection passages 59f penetrate the leading edge portion of the wing body from the passage defining surface of the first wing air passage. A part of the cooling air Acl flowing through the third wing air passage 56c is injected into the combustion gas flow path 39 outside the wing body from the trailing edge 53 of the wing body, so that the plurality of trailing edge injection passages 59b penetrate the trailing edge portion of the wing body from the passage defining surface of the third wing air passage 56c.

[0038] As shown in FIG. 5, the stator vane of the present embodiment further includes an outer impingement plate 95o, an inner impingement plate 95i, an insert cylinder 70, an insert support 80, and a blocking plate 90.

[0039] As shown in FIGS. 3 and 5, the outer impingement plate 95o is fixed to the outer shroud. This outer impingement plate 95o is disposed within the recess of the outer shroud, partitioning the recess of the outer shroud into a radially outer space Dro and a radially inner space Dri. A plurality of impingement holes 95h penetrating in the radial direction Dr are formed in the outer impingement plate 95o. Cooling air Acl from the cooling device 40 described with reference to FIG. 2 flows into the space in the recess of the outer shroud that is radially outer Dro than the outer impingement plate 95o. This cooling air Acl passes through the plurality of impingement holes 95h of the outer impingement plate 95o and impinges and cools the anti-gas path surface of the outer shroud body. The cooling air Acl that has impinged and cooled the anti-gas path surface is jetted out of the outer shroud body, for example, from the front end surface 62f and / or the rear end surface 62b of the outer shroud body. The outer opening 56ao of the first vane air passage described above is located radially outer Dro than the outer impingement plate 95o. Therefore, a part of the cooling air Acl from the cooling device 40 flows into the first vane air passage through this outer opening 56ao.

[0040] The blocking plate 90 is fixed to the inner shroud. This blocking plate 90 is disposed at a distance radially inner Dri from the inner shroud body, partitioning the cooling air space within the recess of the inner shroud from the space that is radially inner Dri than the cooling air space. The blocking plate 90 has a front blocking plate 90f disposed upstream Dau of the axis from the retainer and a rear blocking plate 90b disposed downstream Dad of the axis from the retainer.

[0041] The inner impingement plate 95i is disposed within the recess of the inner shroud and partitions the aforementioned cooling air space into a first space S1 in the radially outer direction Dro and a second space S2 in the radially inner direction Dri. A plurality of impingement holes 95h penetrating from the second space S2 to the first space S1 are formed in the inner impingement plate 95i.

[0042] The insert cylinder 70 is cylindrical and is disposed within the first vane air passage. The insert support 80 is fixed to the inner shroud body so as to support the insert cylinder 70.

[0043] As shown in FIGS. 5 and 6, the insert cylinder 70 has a cylindrical body 71 extending in the radial direction Dr, a flange portion 73 that narrows the air passage within the cylindrical body 71, and a groove side wall portion 74.

[0044] The cylinder body 71 has openings at the radially outer end Dro and the radially inner end Dri. A plurality of impinge holes 71h penetrating from the inner peripheral side toward the outer peripheral side are formed in the cylinder body 71. The flange portion 73 is annular. The outer peripheral edge of the annular flange portion 73 is joined to the inner peripheral surface of the cylinder body 71. This flange portion 73 projects from a position closer to the radially inner side Dri of the cylinder body 71 toward the inner peripheral side within the inner peripheral surface of the cylinder body 71. Therefore, the air passage within the cylinder body 71 is narrowed by this flange portion 73. In the present embodiment, the projected area of the flange portion 73 in the blade height direction Dr is 1 / 2 or more of the area in the direction perpendicular to the blade height direction Dr of the air flow path within the cylinder body 71. The groove side wall portion 74 is cylindrical and is connected to the inner peripheral edge of the flange portion 73 and extends radially inward Dri from this flange portion 73. The annular groove side wall portion 74 penetrates the inner impinge plate 95i. Therefore, the radially inner end Dri of the groove side wall portion 74 is located radially inward Dri of the inner impinge plate 95i and radially inward Dri of the blocking plate 90. The outer peripheral surface of the annular groove side wall portion 74 faces the inner peripheral surface of the radially inner end portion 72 including the radially inner end Dri within the annular cylinder body 71 with a gap therebetween. The annular groove side wall portion 74 and the annular cylinder body 71 are connected by the annular flange portion 73. Therefore, an annular protruding piece insertion groove 76 having the annular flange portion 73 as the groove bottom is formed between the annular groove side wall portion 74 and the annular cylinder body 71. This protruding piece insertion groove 76 is recessed radially outward Dro.

[0045] As shown in FIGS. 6 to 8, the insert support 80 has a support plate 81 that extends in a direction perpendicular to the radial direction Dr and is fixed to the anti-gas path surface of the inner shroud body, a position regulating protruding piece 82 provided on the support plate 81, and a first pressing portion 83a and a second pressing portion 83b also provided on the support plate 81.

[0046] The support plate 81 has a support plate opening 81o that penetrates in the radial direction Dr at a portion facing the region on the inner circumferential side of the cylindrical body 71. The annular groove side wall portion 74 of the insert cylinder 70 is inserted into this support plate opening 81o. The position regulating protruding piece 82 protrudes in the radially outer direction Dro from the support plate 81 in a cylindrical shape over the entire circumference of the opening edge of the support plate opening 81o. This cylindrical position regulating protruding piece 82 enters into the annular protruding piece insertion groove 76 of the insert cylinder 70. For this reason, the inner circumferential surface of the cylindrical position regulating protruding piece 82 faces the outer circumferential surface of the annular groove side wall portion 74 of the insert cylinder 70, and the outer circumferential surface of the cylindrical position regulating protruding piece 82 faces the inner circumferential surface of the radially inner end portion 72 including the end on the radially inner side Dri in the annular cylindrical body 71 of the insert cylinder 70. Note that the insert cylinder 70 is engaged with the insert support 80 so as to be relatively movable.

[0047] The end on the radially outer side Dro of the insert cylinder 70 is connected to the edge of the outer opening 56ao of the first wing air passage (see FIG. 5). On the other hand, the radially inner end portion 72 of the insert cylinder 70 is restricted from moving in the direction perpendicular to the radial direction Dr by the annular position regulating protruding piece 82 in the insert support 80, but is allowed to move in the radial direction Dr with respect to the insert support 80. For this reason, in the present embodiment, while the movement of the insert cylinder 70 in the direction perpendicular to the radial direction Dr can be restricted, the thermal expansion difference in the radial direction Dr between the insert cylinder 70 and the wing body can be allowed.

[0048] As shown in FIG. 8, the plurality of passage defining surfaces that define the first wing air passage include a first passage defining surface that extends in the radial direction Dr, and a second passage defining surface that is connected to the first passage defining surface, extends in the radial direction Dr, and expands in a direction intersecting the first passage defining surface. The first passage defining surface faces the circumferential positive pressure side Dcp and is a surface that defines the edge on the circumferential negative pressure side Dcn of the first wing air passage. The second passage defining surface faces the axial upstream side Dau and is a surface that defines the edge on the axial downstream side Dad of the first wing air passage.

[0049] As shown in FIGS. 6 to 8, the first pressing portion 83a protrudes radially outward Dro from the support plate 81, is located on the side of the first passage defining surface rather than the position regulating protrusion 82 in the direction perpendicular to the radial direction Dr, and has a first contact surface 84a that contacts the first passage defining surface. The second pressing portion 83b protrudes radially outward Dro from the support plate 81, is located on the side of the second passage defining surface rather than the position regulating protrusion 82 in the direction perpendicular to the radial direction Dr, and has a second contact surface 84b that contacts the second passage defining surface.

[0050] As shown in FIGS. 4 to 6, the front plugging plate 90f has a passage facing portion 91 that faces the first vane air passage in the radial direction Dr, a transition portion 92 connected around the passage facing portion 91, and an outer peripheral portion 93 connected around the transition portion 92 and at least a part of which is connected to the peripheral wall of the inner shroud. The passage facing portion 91 is located radially inward Dri of the outer peripheral portion 93. The transition portion 92 is formed to gradually go radially inward Dri as it approaches the passage facing portion 91 from the outer peripheral portion 93. The outer peripheral portion 93 has a curved portion 93a that gradually goes radially inward Dri as it moves away from the passage facing portion 91 in the direction perpendicular to the radial direction Dr. The edge of this curved portion 93a is connected to the retainer.

[0051] Next, the manufacturing method of the stationary vane described above will be described according to the flowchart shown in FIG. 9.

[0052] First, prepare a stationary vane body, an outer impingement plate 95o, an inner impingement plate 95i, a plugging plate 90, an insert cylinder 70, and an insert support 80 (preparation step S10).

[0053] The stationary vane body is an integrated structure of an outer shroud, a vane body, and an inner shroud. This stationary vane body is formed by, for example, casting or the like.

[0054] Next, arrange the insert cylinder 70 (cylinder arrangement step S11). In this cylinder arrangement step S11, at least a part of the end of the insert cylinder 70 on the radially outer side Dro is joined to the outer shroud body 61o by welding or the like.

[0055] Next, the insert support 80 is fixed to the stator vane body (support fixing step S12). This support fixing step S12 includes an arrangement step S12a, a pressing step S12b, and a joining step S12c. In the arrangement step S12a, first, the position regulating protrusion 82 of the insert support 80 is opposed to the radially inner end portion 72 of the cylinder body 71. Specifically, the position regulating protrusion 82 of the insert support 80 enters the protrusion insertion groove 76 between the cylinder body 71 of the insert cylinder 70 and the groove side wall portion 74, and the insert cylinder 70 is arranged so that the outer peripheral surface of the annular position regulating protrusion 82 faces the inner peripheral surface of the cylinder body 71. Further, in the arrangement step S12a, as shown in FIG. 10, the first contact surface 84a of the insert support 80 is opposed to the first passage defining surface 57a of the first vane air passage 56a, and the second contact surface 84b of the insert support 80 is opposed to the second passage defining surface 57b of the first vane air passage 56a. In the pressing step S12b, as shown in FIG. 8, the first contact surface 84a is pressed against the first passage defining surface 57a, and the second contact surface 84b is pressed against the second passage defining surface 57b. In the joining step S12c, with the first contact surface 84a in contact with the first passage defining surface 57a and the second contact surface 84b in contact with the second passage defining surface 57b, the outer peripheral edge of the support plate 81 is joined to the anti-gas path surface 64a of the inner shroud body 61i.

[0056] Next, the outer impingement plate 95o is joined to the outer shroud, and the inner impingement plate 95i is joined to the inner shroud (impingement plate arrangement step S13).

[0057] Next, the blocking plate 90 is joined to the inner shroud (blocking plate arrangement step S14).

[0058] Thus, the stator vane in the present embodiment is completed. Note that the timing of arranging the insert cylinder 70 so that the position regulating protrusion 82 of the insert support 80 enters the protrusion insertion groove 76 of the insert cylinder 70, that is, the execution timing of the arrangement step S12a, may be after the cylinder arrangement step S11 or before the cylinder arrangement step S11.

[0059] Referring to FIGS. 5 and 6, the flow of cooling air within the stator vanes will be described.

[0060] Within the recess of the outer shroud, in the space radially outside Dro from the outer impingement plate 95o, the cooling air Acl from the cooling device 40 described with reference to FIG. 2 flows in. A part of this cooling air Acl passes through the plurality of impingement holes 95h of the outer impingement plate 95o and impingement-cools the anti-gas path surface of the outer shroud body. The cooling air Acl that has impingement-cooled the anti-gas path surface is jetted outside the outer shroud body from, for example, the front end surface 62f and / or the rear end surface 62b of the outer shroud body. Also, another part of the cooling air Acl flows into the cylinder body 71 of the insert cylinder 70 disposed within the first vane air passage.

[0061] The cooling air Acl that has flowed into the cylinder body 71 of the insert cylinder 70 flows radially inward Dri within the cylinder body 71. In this process, a part of the cooling air Acl passes through the plurality of impingement holes 71h of the cylinder body 71. The remaining cooling air Acl flows into the second space S2 between the plugging plate 90 and the inner impingement plate 95i within the recess of the inner shroud via the annular groove side wall portion 74 fixed to the cylinder body 71. Thus, the annular groove side wall portion 74 fixed to the cylinder body 71 forms a guide cylinder portion that guides the cooling air Acl flowing into the cylinder body 71 into the second space S2.

[0062] The cooling air Acl that has passed through the plurality of impingement holes 71h of the cylinder body 71 impingement-cools the passage defining surface that defines the first vane air passage. The cooling air Acl that has impingement-cooled the passage defining surface flows into the plurality of leading edge jet passages 59f. The portion near the leading edge of the vane body is convectively cooled by the cooling air Acl flowing through the plurality of leading edge jet passages 59f. This cooling air Acl is jetted from the vicinity of the leading edge of the vane body into the combustion gas flow path 39 outside the vane body.

[0063] The cooling air Acl that has flowed into the second space S2 within the recess of the inner shroud passes through a plurality of impingement holes 95h of the inner impingement plate 95i and impingement-cools the anti-gas-passage surface of the inner shroud body. The cooling air Acl that has impingement-cooled the anti-gas-passage surface of the inner shroud body flows into the second blade air passage 56b and flows in the second blade air passage 56b toward the radially outer side Dro. As the cooling air Acl flows in the second blade air passage 56b, it convectively cools around the second blade air passage 56b within the blade body.

[0064] Thereafter, the cooling air Acl flows into the third blade air passage 56c and flows in the third blade air passage 56c toward the radially inner side Dri. As the cooling air Acl flows in the third blade air passage 56c, it convectively cools around the third blade air passage 56c within the blade body. Further, the cooling air Acl flows into a plurality of trailing-edge injection passages 59b. The portion near the trailing edge of the blade body is convectively cooled by the cooling air Acl flowing through the plurality of trailing-edge injection passages 59b. This cooling air Acl is injected from the vicinity of the trailing edge of the blade body into the combustion gas flow path 39 outside the blade body.

[0065] In the present embodiment, as described above, the insert cylinder 70 is not joined to the insert support 80 so as to allow for the thermal expansion difference in the radial direction Dr between the insert cylinder 70 and the blade body. For this reason, a part of the cooling air Acl that has flowed into the space radially inner Dri than the inner shroud body may leak through the gap between the insert support 80 and the insert cylinder 70 into the space on the outer peripheral side of the cylinder body 71 within the first blade air passage. If the flow rate of the cooling air Acl that leaks through the gap between the insert support 80 and the insert cylinder 70 into the space on the outer peripheral side of the cylinder body 71 within the first blade air passage increases, the pressure difference between the space on the inner peripheral side of the cylinder body 71 and the space on the outer peripheral side of the cylinder body 71 decreases. For this reason, the speed at which the cooling air Acl on the inner peripheral side of the cylinder body 71 passes through the plurality of impingement holes 71h of the cylinder body 71 decreases, and the impingement cooling effect on the passage defining surface that defines the first blade air passage decreases.

[0066] In this embodiment, the gap between the insert support 80 and the insert cylinder 70 becomes the gap between the protruding piece insertion groove 76 and the position regulating protruding piece 82 that has entered the groove 76. Therefore, the flow path of the cooling air Acl formed by this gap undulates in the radial direction Dr and becomes a bent flow path. Accordingly, in this embodiment, the resistance of the cooling air Acl flowing through the flow path formed by the gap between the insert support 80 and the insert cylinder 70 increases. In particular, the resistance of the cooling air Acl at the corner in this flow path increases.

[0067] Also, in this embodiment, since the flange portion 73 that narrows the air passage in the cylinder body 71 is provided in the cylinder body 71, the pressure of the cooling air Acl that has passed through the flange portion 73 in the cylinder body 71 can be reduced. In particular, in this embodiment, the projected area of the flange portion 73 in the blade height direction Dr is 1 / 2 or more of the area in the direction perpendicular to the blade height direction Dr of the air flow path in the cylinder body 71. Therefore, in this embodiment, the pressure of the cooling air Acl flowing out of the cylinder body 71 and flowing into the gap between the insert support 80 and the insert cylinder 70 can be reduced.

[0068] As described above, in this embodiment, the resistance of the cooling air Acl flowing through the flow path formed by the gap between the insert support 80 and the insert cylinder 70 increases, and the pressure of the cooling air Acl flowing into the gap between the insert support 80 and the insert cylinder 70 decreases. Therefore, the flow rate of the cooling air Acl leaking into the space on the outer peripheral side of the cylinder body 71 within the first blade air passage can be reduced. Thus, in this embodiment, it is possible to suppress a decrease in the impingement cooling effect on the passage defining surface that defines the first blade air passage.

[0069] In this embodiment, as described above, the position regulating protrusion piece 82 of the insert support 80 can regulate the relative position in the direction perpendicular to the radial direction Dr of the insert cylinder 70 with respect to the insert support 80. Further, in this embodiment, since the first contact surface 84a of the insert support 80 is in contact with the first passage defining surface and the second contact surface 84b of the insert support 80 is in contact with the second passage defining surface, the relative position in the direction perpendicular to the radial direction Dr of the insert support 80 with respect to the first wing air passage can be accurately determined. For this reason, in this embodiment, the distances from the outer peripheral surface of the cylinder body 71 of the insert cylinder 70 to a plurality of passage defining surfaces including the first passage defining surface and the second passage defining surface can be accurately set to the target distances. Therefore, in this embodiment, the impingement cooling performance of the plurality of passage defining surfaces by the cooling air Acl ejected from the plurality of impingement holes 71h of the cylinder body 71 can be appropriately managed.

[0070] The outer shroud, the blade body, and the inner shroud are exposed to the high-temperature combustion gas G. On the other hand, the plugging plate 90 joined to the inner shroud is in contact with the cooling air Acl and is not exposed to the combustion gas G. For this reason, a thermal expansion difference occurs between the inner shroud and the plugging plate 90. In this embodiment, even if a thermal expansion difference occurs between the inner shroud and the plugging plate 90, the connection portion between the passage facing portion 91 and the transition portion 92 and the connection portion between the transition portion 92 and the outer peripheral portion 93 are deformed, and the plugging plate 90 can accept this thermal expansion difference without difficulty. Therefore, in this embodiment, damage to the joint portion between the inner shroud and the plugging plate 90 and the plugging plate 90 can be suppressed. Further, even if a thermal expansion difference occurs between the inner shroud and the plugging plate 90, damage at the joint portion between the curved portion 93a in the outer peripheral portion 93 and the retainer can be suppressed by the deformation of the curved portion 93a in the outer peripheral portion 93.

[0071] In addition, in the present embodiment, the distance between the passage facing portion 91 and the inner shroud main body is larger than at least the distance between the connection portion with the transition portion 92 in the outer peripheral portion 93 and the inner shroud main body. In the present embodiment, the distance between the passage facing portion 91 and the inner shroud main body can be made larger than when the distance between the passage facing portion 91 and the inner shroud main body is adjusted to the distance between the connection portion with the transition portion 92 in the outer peripheral portion 93 and the inner shroud main body. Therefore, in the present embodiment, it is possible to suppress a pressure drop of the cooling air Acl due to the cooling air Acl colliding with the passage facing portion 91 of the blocking plate 90. Thus, in the present embodiment, the cooling air Acl that has passed through the insert cylinder 70 in the first blade air passage and has flowed into the recess of the inner shroud can be effectively used for cooling the inner shroud and the like. Further, in the present embodiment, it is possible to avoid the blocking plate 90 interfering with the end on the radially inner side Dri of the groove side wall portion (guide cylinder portion) 74 due to thermal expansion of a part of the stator blades.

[0072] "First Modification Example of Insert Cylinder and Insert Support" As shown in FIG. 11, the insert support 80a in this modification example is different from the insert support 80 in the above embodiment. On the other hand, the insert cylinder 70 in this modification example is the same as the insert cylinder 70 in the above embodiment.

[0073] The insert support 80a in this modification example has a throttle ring 85 in addition to the support plate 81, the position regulating projection 82, the first pressing portion 83a, and the second pressing portion 83b that the insert support 80 in the above embodiment has. The throttle ring 85 is fixed to the surface facing the radially inner side Dri of the support plate 81. This throttle ring 85 has a throttle opening 85o into which the annular groove side wall portion 74 of the insert cylinder 70 is inserted. The average distance d2 between the throttle opening 85o and the annular groove side wall portion 74 is narrower than the average distance d1 between the annular position regulating projection 82 of the insert support 80a and the annular groove side wall portion 74 of the insert cylinder 70.

[0074] Therefore, in this modification, the flow rate of the cooling air Acl flowing into the gap between the insert support 80a and the insert cylinder 70 can be reduced in the space Dri radially inside the inner shroud body. Thus, in the present embodiment, the flow rate of the cooling air Acl leaking into the space on the outer peripheral side of the cylinder body 71 in the first blade air passage can be reduced.

[0075] "Second Modification Example of Insert Cylinder and Insert Support" As shown in FIG. 12, the insert cylinder 70b in this modification example is different from the insert cylinder 70 in the above-described embodiment. On the other hand, the insert support 80 in this modification example is the same as the insert support 80 in the above-described embodiment.

[0076] As shown in FIG. 12, the insert cylinder 70b in this modification example, similar to the insert cylinder 70 in the above-described embodiment, has a cylindrical body 71b extending in the radial direction Dr and forming a cylindrical shape, a flange portion 73b that narrows the air passage inside the cylindrical body 71b, and a groove side wall portion 74b. The insert cylinder 70b in this modification example further has a groove bottom portion 75b.

[0077] In this modified example, the radially inner end Dri of the cylindrical body 71b is located radially inward Dri of the inner impingement plate 95i and radially inward Dri of the blocking plate 90. Similar to the cylindrical body 71 in the above embodiment, the radially outer end Dro and the radially inner end Dri of this cylindrical body 71b are open. Therefore, the cooling air Acl flowing into the cylindrical body 71b from the opening on the radially outer side Dro of the cylindrical body 71b can flow through the inside of this cylindrical body 71b and into the second space S2 between the blocking plate 90 and the inner impingement plate 95i in the recess of the inner shroud. Thus, this cylindrical body 71b forms a guide cylindrical portion that guides the cooling air Acl flowing into the cylindrical body 71b into the second space S2. A plurality of impingement holes 71h penetrating from the inner peripheral side toward the outer peripheral side are also formed in this cylindrical body 71b. The flange portion 73b is annular. The outer peripheral edge of the annular flange portion 73b is joined to the inner peripheral surface of the cylindrical body 71b. This flange portion 73b projects from a position closer to the radially inner side Dri of the cylindrical body 71b toward the inner peripheral side in the inner peripheral surface of the cylindrical body 71b. Therefore, the air passage in the cylindrical body 71b is narrowed by this flange portion 73b. The groove bottom portion 75b is annular. The outer peripheral edge of the annular groove bottom portion 75b is joined to the outer peripheral surface of the cylindrical body 71b. This groove bottom portion 75b projects from a position closer to the radially inner side Dri of the cylindrical body 71b toward the outer peripheral side in the outer peripheral surface of the cylindrical body 71b. The groove side wall portion 74b is cylindrical, joined to the outer peripheral edge of the annular groove bottom portion 75b, and extends radially inward Dri. The inner peripheral surface of the annular groove side wall portion 74b faces the outer peripheral surface of the annular cylindrical body 71b with a gap therebetween. Therefore, an annular protruding piece insertion groove 76b is formed between the annular groove side wall portion 74b and the annular cylindrical body 71b. This protruding piece insertion groove 76b is recessed radially outward Dro. The annular position regulating protruding piece 82 of the insert support 80 fits into this annular protruding piece insertion groove 76b.

[0078] In the insert cylinder 70 in the above embodiment, a protruding piece insertion groove 76 is formed on the inner peripheral side of the cylindrical body 71. On the other hand, in the insert cylinder 70b in this modified example, a protruding piece insertion groove 76b is formed on the outer peripheral side of the cylindrical body 71b.

[0079] As described above, also in this modified example, the gap between the insert support 80 and the insert cylinder 70b becomes the gap between the protruding piece insertion groove 76b and the position regulating protruding piece 82 that enters into this groove 76b. Therefore, the flow path of the cooling air Acl formed by this gap undulates in the radial direction Dr and becomes a bent flow path. Accordingly, also in this modified example, similar to the above-described embodiment, the resistance of the cooling air Acl flowing through the flow path formed by the gap between the insert support 80 and the insert cylinder 70b increases.

[0080] Also, in this modified example, since a flange portion 73b for narrowing the air passage in the cylinder body 71b is provided in the cylinder body 71b, the pressure of the cooling air Acl that has passed through the flange portion 73b in the cylinder body 71b can be reduced. Therefore, also in this modified example, the pressure of the cooling air Acl that flows out from the inside of the cylinder body 71b and flows into the gap between the insert support 80 and the insert cylinder 70b can be decreased.

[0081] As described above, also in this modified example, similar to the above-described embodiment, the resistance of the cooling air Acl flowing through the flow path formed by the gap between the insert support 80 and the insert cylinder 70b increases, and the pressure of the cooling air Acl flowing into the gap between the insert support 80 and the insert cylinder 70b decreases. For this reason, the flow rate of the cooling air Acl that leaks out into the space on the outer peripheral side of the cylinder body 71b within the first blade air passage can be reduced. Thus, also in this modified example, a decrease in the impingement cooling effect with respect to the passage defining surface that defines the first blade air passage can be suppressed.

[0082] Also in this modified example, the end on the radially inner side Dri of the cylinder body 71b that forms the guide cylinder portion is located on the radially outer side Dro of the blocking plate 90 and on the radially inner side Dri of the inner impingement plate 95i. However, the passage facing portion 91 of the blocking plate 90 is located on the radially inner side Dri of the outer peripheral portion 93 of this blocking plate 90. For this reason, it is possible to avoid the blocking plate 90 interfering with the end on the radially inner side Dri of the cylinder body 71b that forms the guide cylinder portion due to thermal expansion of a part of the stationary blades.

[0083] Note that a diaphragm ring 85 described in the first modification example may be provided on the support plate 81 of the insert support 80 in this modification example.

[0084] "Third Modification Example of Insert Tube and Insert Support" As shown in FIG. 13, the insert tube 70c in this modification example is different from the insert tube 70 in the above embodiment. Also, the insert support 80c in this modification example is different from the insert support 80 in the above embodiment.

[0085] The insert tube 70c in this modification example has, similar to the insert tube 70 in the above embodiment, a cylindrical body 71 extending in the radial direction Dr and forming a cylindrical shape, and a flange portion 73c that narrows the air passage inside the cylindrical body 71. However, the insert tube 70c in this modification example does not have the groove bottom portion and the groove side wall portion of the insert tube 70 in the above embodiment. Therefore, the protruding piece insertion groove 76 of the insert tube 70 in the above embodiment is not formed in the insert tube 70c in this modification example. The cylindrical body 71 has, similar to the cylindrical body 71 in the above embodiment, an opening at the end on the outer side Dro in the radial direction and the end on the inner side Dri in the radial direction. A plurality of impinge holes 71h penetrating from the inner peripheral side toward the outer peripheral side are also formed in this cylindrical body 71. The flange portion 73c forms an annular shape. The outer peripheral edge of the annular flange portion 73c is joined to the inner peripheral surface of the cylindrical body 71. This flange portion 73c protrudes toward the inner peripheral side of the cylindrical body 71 from a position closer to the inner side Dri in the radial direction of the cylindrical body 71 among the inner peripheral surface of the cylindrical body 71. For this reason, the air passage inside the cylindrical body 71 is narrowed by this flange portion 73c.

[0086] The insert support 80c in this modification example has, similar to the insert support 80 in the above embodiment, a support plate 81 that extends in a direction perpendicular to the radial direction Dr and is fixed to the anti-gas path surface of the inner shroud body, a position regulating protruding piece 82c, a first pressing portion 83a, a second pressing portion 83b, a groove side wall portion 87, and a guide cylinder portion 88. The position regulating protruding piece 82c, the first pressing portion 83a, the second pressing portion 83b, the groove side wall portion 87, and the guide cylinder portion 88 are all provided on the support plate 81.

[0087] The support plate 81 has a support plate opening 81o that penetrates in the radial direction Dr at a portion facing the region on the inner peripheral side of the cylindrical body 71. The position regulating projection piece 82c forms a cylinder shape and projects radially outward in the radial direction Dro over the entire circumference of the opening edge of the support plate opening 81o. This position regulating projection piece 82c is located on the inner peripheral side of the cylindrical body 71 and faces the inner peripheral surface at the radially inner end 72 of the cylindrical body 71. Therefore, this position regulating projection piece 82c forms an inner position regulating projection piece. The groove side wall portion 87 forms a cylinder shape and projects radially outward in the radial direction Dro from the support plate 81 over the entire circumference of the opening edge of the support plate opening 81o. This groove side wall portion 87 is located on the outer peripheral side of the cylindrical body 71 and faces the outer peripheral surface at the radially inner end 72 of the cylindrical body 71. Therefore, this groove side wall portion 87 forms an outer position regulating projection piece. In the support plate 81, the portion located between the position regulating projection piece 82c and the groove side wall portion 87, that is, between the inner position regulating projection piece 82c and the outer position regulating projection piece 87, forms the groove bottom portion 81c. In this insert support 80c, an annular cylindrical body insertion groove 89 is formed between the inner position regulating projection piece 82c and the outer position regulating projection piece 87. This cylindrical body insertion groove 89 is recessed radially inward in the radial direction Dri. The radially inner end 72 of the cylindrical body 71 enters this cylindrical body insertion groove 89.

[0088] The first pressing portion 83a projects radially outward in the radial direction Dro from the support plate 81 and is located on the side of the first passage defining surface (see FIG. 8) rather than the inner position regulating projection piece 82c and the outer position regulating projection piece 87 in the direction perpendicular to the radial direction Dr, and has a first contact surface 84a (see FIG. 8) that contacts the first passage defining surface. The second pressing portion 83b projects radially outward in the radial direction Dro from the support plate 81 and is located on the side of the second passage defining surface (see FIG. 8) rather than the inner position regulating projection piece 82c and the outer position regulating projection piece 87 in the direction perpendicular to the radial direction Dr, and has a second contact surface 84b (see FIG. 8) that contacts the second passage defining surface.

[0089] The guide cylinder portion 88 forms a cylinder shape and projects radially inward in the radial direction Dri over the entire circumference of the opening edge of the support plate opening 81o. The radially inner end in the radial direction Dri of this guide cylinder portion 88 is located within the second space S2. Therefore, the guide cylinder portion 88 can guide the cooling air Acl that has flowed into the cylindrical body 71 to the second space S2.

[0090] As described above, in this modified example, the gap between the insert support 80c and the insert cylinder 70c becomes the gap between the cylinder insertion groove 89 and the radially inner end portion 72 of the cylinder 71 that has entered the groove 89. Therefore, the flow path of the cooling air Acl formed by this gap undulates in the radial direction Dr and becomes a bent flow path. Accordingly, also in this modified example, as in the above-described embodiment and the second modified example, the resistance of the cooling air Acl flowing through the flow path formed by the gap between the insert support 80c and the insert cylinder 70c increases.

[0091] Also, in this modified example, since a flange portion 73c for narrowing the air passage in the cylinder 71 is provided in the cylinder 71, the pressure of the cooling air Acl that has passed through the flange portion 73c in the cylinder 71 can be reduced. Therefore, also in this modified example, the pressure of the cooling air Acl that flows out from the inside of the cylinder 71 and flows into the gap between the insert support 80c and the insert cylinder 70c can be reduced.

[0092] As described above, also in this modified example, as in the above-described embodiment and the second modified example, the resistance of the cooling air Acl flowing through the flow path formed by the gap between the insert support 80c and the insert cylinder 70c increases, and the pressure of the cooling air Acl flowing into the gap between the insert support 80c and the insert cylinder 70c decreases. Therefore, the flow rate of the cooling air Acl leaking into the space on the outer peripheral side of the cylinder 71 within the first blade air passage can be reduced. Thus, also in this modified example, a decrease in the impingement cooling effect on the passage defining surface that defines the first blade air passage can be suppressed.

[0093] Also in this modified example, the radially inner Dri end of the guide cylinder portion 88 is located on the radially outer Dro side of the blocking plate 90 rather than on the radially inner Dri side of the inner impingement plate 95i. However, the passage facing portion 91 of the blocking plate 90 is located on the radially inner Dri side of the outer peripheral portion 93 of the blocking plate 90. Therefore, it is possible to avoid the blocking plate 90 interfering with the radially inner Dri end of the guide cylinder portion 88 due to thermal expansion of a part of the stationary blade.

[0094] "Fourth Modification Example of Insert Tube and Insert Support" As shown in FIGS. 14 and 15, the insert tube 70 in this modification example is the same as the insert tube 70 in the above-described embodiment. On the other hand, the insert support 80d in this modification example is different from the insert support 80 in the above-described embodiment.

[0095] As shown in FIGS. 14 and 15, the insert support 80d in this modification example has, similar to the insert support 80 in the above-described embodiment, a support plate 81 that extends in a direction perpendicular to the radial direction Dr and is fixed to the anti-gas path surface of the inner shroud main body, a position regulating protrusion piece 82 provided on the support plate 81, and a first pressing portion 83da and a second pressing portion 83db also provided on the support plate 81.

[0096] The first pressing portion 83da in this modification example also protrudes from the support plate 81 in the radially outer direction Dro, similar to the first pressing portion 83a in the above-described embodiment, is located on the side of the first passage defining surface rather than the position regulating protrusion piece 82 in the direction perpendicular to the radial direction Dr, and has a first contact surface 84a that contacts the first passage defining surface. Also, the second pressing portion 83db in this modification example also protrudes from the support plate 81 in the radially outer direction Dro, similar to the first pressing portion 83a in the above-described embodiment, is located on the side of the second passage defining surface rather than the position regulating protrusion piece 82 in the direction perpendicular to the radial direction Dr, and has a second contact surface 84b that contacts the second passage defining surface.

[0097] In this modification example, a first groove 86a that is recessed in the radially inner direction Dri and into which the end 71i of the radially inner side Dri of the cylindrical body 71 enters is formed between the annular position regulating protrusion piece 82 and the first pressing portion 83da. Further, in this modification example, a second groove 86b that is recessed in the radially inner direction Dri and into which the end 71i of the radially inner side Dri of the cylindrical body 71 enters is formed between the annular position regulating protrusion piece 82 and the second pressing portion 83db.

[0098] In this modification example, even if the insert support 80d has the first pressing portion 83da and the second pressing portion 83db, the end 71i of the inner diameter side Dri of the cylindrical body 71 enters the first groove 86a and the second groove 86b, so that the position of the end 71i of the inner diameter side Dri of the cylindrical body 71 can be brought closer to the position of the anti-gas path surface of the inner shroud body. Therefore, in this modification example, while maintaining the overlap amount in the radial direction Dr between the cylindrical body 71 and the position regulating protruding piece 82, the position of the impinge hole 71h formed at the innermost side in the radial direction Dri in the cylindrical body 71 can be brought closer to the position of the anti-gas path surface of the inner shroud body.

[0099] "Fifth Modification Example of Insert Cylinder and Insert Support" This modification example is different from the fourth modification example only in the insert support, and other configurations in this modification example are the same as those in the fourth modification example.

[0100] As shown in FIG. 16, the insert support 80e in this modification example, similar to the insert support 80d in the fourth modification example, has a support plate 81 that extends in a direction perpendicular to the radial direction Dr and is fixed to the anti-gas path surface of the inner shroud body, a position regulating protruding piece 82 provided on the support plate 81, and a first pressing portion 83ea and a second pressing portion 83eb also provided on the support plate 81.

[0101] Also in this modification example, similar to the fourth modification example, a first groove 86a that is recessed in the radial inner side Dri and into which the end 71i of the inner diameter side Dri of the cylindrical body 71 enters is formed between the annular position regulating protruding piece 82 and the first pressing portion 83ea. Further, in this modification example, a second groove 86b that is recessed in the radial inner side Dri and into which the end 71i of the inner diameter side Dri of the cylindrical body 71 enters is formed between the annular position regulating protruding piece 82 and the second pressing portion 83eb.

[0102] However, in this modified example, the second pressing portion 83eb is separated from the first pressing portion 83ea. Therefore, in this modified example, when moving the processing tool in the direction along the first contact surface 84a to process the first groove 86a between the first pressing portion 83ea and the position regulating protruding piece 82, the processing tool can be moved to the position where the second pressing portion 83eb exists in the direction along the first contact surface 84a. Also, in this modified example, when moving the processing tool in the direction along the second contact surface 84b to process the second groove 86b between the second pressing portion 83eb and the position regulating protruding piece 82, the processing tool can be moved to the position where the first pressing portion 83ea exists in the direction along the second contact surface 84b. Thus, in this modified example, the first groove 86a and the second groove 86b can be easily processed.

[0103] "Modified Example" The stationary blades in the above embodiments and each modified example have three blade air passages 56. However, the stationary blades may have four or more blade air passages 56.

[0104] In the stationary blades in the above embodiments and each modified example, among the plurality of blade air passages 56, the insert cylinders 70, 70b, 70c are arranged in the first blade air passage on the most upstream side Dau of the axis. However, the insert cylinders 70, 70b, 70c may be arranged in the blade air passage 56 on the downstream side Dad of the axis from the first blade air passage on the most upstream side Dau of the axis.

[0105] In the above-described embodiments and each modification, the first passage defining surface that defines the blade air passage 56 of the stator vane faces the circumferential direction positive pressure side Dcp and is a surface that defines the edge of the circumferential direction negative pressure side Dcn of the first blade air passage. Alternatively, the second passage defining surface faces the axial upstream side Dau and is a surface that defines the edge of the axial downstream side Dad of the first blade air passage. However, both the first passage defining surface and the second passage defining surface extend in the radial direction Dr, and the second passage defining surface may be connected to the first passage defining surface and extend in a direction intersecting the first passage defining surface. For example, assume that the first passage defining surface faces the circumferential direction positive pressure side Dcp and is a surface that defines the edge of the circumferential direction negative pressure side Dcn of the blade air passage 56. In this case, if the passage defining surface that faces the axial downstream side Dad and defines the edge of the axial upstream side Dau of the blade air passage 56 is connected to the first passage defining surface and extends in a direction intersecting the first passage defining surface, this passage defining surface may be used as the second passage defining surface.

[0106] Furthermore, the present disclosure is not limited to the above-described one embodiment and modifications. Various additions, changes, replacements, partial deletions, etc. are possible without departing from the conceptual ideas and spirit of the present invention derived from the content defined in the claims and their equivalents.

[0107] "Supplementary Note" The stator vanes in the above-described embodiments and modifications can be understood, for example, as follows. (1) The stator vane in the first aspect is A blade body having a cross section forming an airfoil and extending in a blade height direction Dr having a direction component perpendicular to the cross section, a blade air passage extending through the blade body in the blade height direction Dr through which cooling air Acl can flow, a first shroud provided at an end of the blade body on a first blade height side Dro in the blade height direction Dr, a second shroud provided at an end of the blade body on a second blade height side Dri opposite to the first blade height side Dro, and a plugging plate 90 fixed to the second shroud. The first shroud has a first shroud body that extends in a direction perpendicular to the blade height direction Dr from the end of the blade body on the first blade height side Dro. The second shroud has a second shroud body that extends in a direction perpendicular to the blade height direction Dr from the end of the blade body on the second blade height side Dri, and a peripheral wall that protrudes from the outer peripheral edge of the second shroud body toward the second blade height side Dri. The second shroud body and the peripheral wall jointly form a recess that is concave toward the first blade height side Dro on the second blade height side Dri of the second shroud body. The blade air passage penetrates the first shroud body, the blade body, and the second shroud body in the blade height direction Dr. The plugging plate 90 is disposed at a distance from the second shroud body toward the second blade height side Dri, and partitions a cooling air space in the recess and a space on the second blade height side Dri of the cooling air space. The plugging plate 90 has a passage facing portion 91 that faces the blade air passage in the blade height direction Dr, a transition portion 92 connected around the passage facing portion 91, and an outer peripheral portion 93 connected around the transition portion 92 and at least partially joined to the peripheral wall. The passage facing portion 91 is located on the second blade height side Dri of the connection portion with the transition portion 92 in the outer peripheral portion 93. The transition portion 92 is formed to gradually face the second blade height side Dri as it approaches the passage facing portion 91 from the outer peripheral portion 93.

[0108] The first shroud, the airfoil body, and the second shroud are exposed to the high-temperature combustion gas G. On the other hand, the plugging plate 90 joined to the second shroud is in contact with the cooling air Acl and not exposed to the combustion gas G. For this reason, a thermal expansion difference occurs between the second shroud and the plugging plate 90. In this embodiment, even if a thermal expansion difference occurs between the second shroud and the plugging plate 90, the connection portion between the passage facing portion 91 and the transition portion 92 and the connection portion between the transition portion 92 and the outer peripheral portion 93 are deformed, and the plugging plate 90 can reasonably accommodate this thermal expansion difference. Therefore, in this embodiment, damage to the joint portion between the second shroud and the plugging plate 90 and the plugging plate 90 can be suppressed.

[0109] Also, in this embodiment, the distance between the passage facing portion 91 and the second shroud main body is larger than at least the distance between the connection portion with the transition portion 92 and the second shroud main body in the outer peripheral portion 93. If the distance between the passage facing portion 91 and the second shroud main body is made the same as the distance between the connection portion with the transition portion 92 and the second shroud main body in the outer peripheral portion 93, this embodiment can increase the distance between the passage facing portion 91 and the second shroud main body. For this reason, in this embodiment, it is possible to suppress a pressure drop of the cooling air Acl due to the cooling air Acl colliding with the passage facing portion 91 of the plugging plate 90. Therefore, in this embodiment, the cooling air Acl that has passed through the airfoil air passage and flowed into the concave portion of the second shroud can be effectively used for cooling the second shroud and the like.

[0110] (2) The stator vane in the second embodiment is In the stator vane 50 in the first embodiment, the outer peripheral portion 93 has a curved portion 93a that gradually faces the second side Dri of the airfoil height in a direction perpendicular to the airfoil height direction Dr as it moves away from the passage facing portion 91.

[0111] In this aspect, even if a thermal expansion difference occurs between the second shroud and the plugging plate 90, in addition to the connection portion between the passage facing portion 91 and the transition portion 92 and the connection portion between the transition portion 92 and the outer peripheral portion 93, the curved portion 93a in the outer peripheral portion 93 deforms, and the plugging plate 90 can reasonably accommodate this thermal expansion difference. Therefore, in this aspect, damage to the joint portion between the second shroud and the plugging plate 90 and the plugging plate 90 can be suppressed.

[0112] (3) The stator vane in the third aspect is In the stator vane 50 in the second aspect, the blade body has a leading edge 52, a trailing edge 53, a pressure surface connecting the leading edge 52 and the trailing edge 53, and a suction surface that forms a back-to-back relationship with the pressure surface and connects the leading edge 52 and the trailing edge 53. The second shroud has a retainer connected to the peripheral wall. The peripheral wall of the second shroud has a positive pressure side wall 65p that exists on the positive pressure side Dcp where the pressure surface exists with respect to the blade body and with respect to the suction surface, and a negative pressure side wall 65n that exists on the negative pressure side Dcn opposite to the positive pressure side Dcp with respect to the blade body. The retainer is connected to the positive pressure side wall 65p and the negative pressure side wall 65n. The curved portion 93a is joined to the retainer.

[0113] In this aspect, by deforming the curved portion 93a, damage to the joint portion between the curved portion 93a and the retainer in the outer peripheral portion 93 can be suppressed.

[0114] (4) The stator vane in the fourth aspect is In the stator vane 50 in any one of the first to third aspects, there are provided insert cylinders 70, 70b, 70c at least partially disposed in the blade air passage, and insert supports 80, 80a, 80c, 80d, 80e for supporting the insert cylinders 70, 70b, 70c. The insert cylinders 70, 70b, 70c extend in the blade height direction Dr and form a cylindrical shape, and are each open at an end on the first blade height side Dro and an end on the second blade height side Dri, and have a cylindrical body 71, 71b in which a plurality of impinge holes 71h penetrating from the inner peripheral side to the outer peripheral side are formed. The insert supports 80, 80a, 80c, 80d, 80e have a support plate 81 extending in a direction perpendicular to the blade height direction Dr, and position restricting projecting pieces 82, 82c projecting from the support plate 81 to the first blade height side Dro. The support plate 81 has a support plate opening 81o penetrating in the blade height direction Dr at a portion facing the inner peripheral side region of the cylindrical body 71, 71b in the blade height direction Dr. The position restricting projecting pieces 82, 82c project from the support plate 81 to the first blade height side Dro over the entire circumference of the opening edge of the support plate opening 81o, face the inner peripheral surface or the outer peripheral surface of the cylindrical body 71, 71b, and restrict the relative position of the insert cylinders 70, 70b, 70c in a direction perpendicular to the blade height direction Dr with respect to the insert supports 80, 80a, 80c, 80d, 80e. The support plate 81 is joined to the second shroud body at the outer peripheral edge of the support plate 81. The insert cylinder is engaged with the insert support so as to be relatively movable.

[0115] In this aspect, the insert cylinders 70, 70b, 70c are engaged so as to be relatively movable with respect to the insert supports 80, 80a, 80c, 80d, 80e. In this aspect, the position regulating protrusions 82, 82c of the insert supports 80, 80a, 80c, 80d, 80e fixed to the second shroud main body face the inner peripheral surface or the outer peripheral surface of the cylindrical bodies 71, 71b of the insert cylinders 70, 70b, 70c. For this reason, in this aspect, while the movement of the insert cylinders 70, 70b, 70c in the direction perpendicular to the blade height direction Dr can be regulated, the end of the blade height second side Dri of the insert cylinders 70, 70b, 70c is movable in the blade height direction Dr with respect to the blade body. Therefore, in this aspect, the difference in thermal expansion in the blade height direction Dr between the insert cylinders 70, 70b, 70c and the blade body can be tolerated.

[0116] In this aspect, the cooling air Acl present on the blade height first side Dro rather than the first shroud main body flows into the cylindrical bodies 71, 71b of the insert cylinders 70, 70b, 70c arranged in the blade air passage. The cooling air Acl that has flowed into the cylindrical bodies 71, 71b flows through the cylindrical bodies 71, 71b toward the blade height second side Dri. In this process, a part of the cooling air Acl passes through the plurality of impingement holes 71h of the cylindrical bodies 71, 71b. The remaining cooling air Acl flows into the space on the blade height second side Dri rather than the second shroud main body through the support plate opening 81o. The cooling air Acl that has passed through the plurality of impingement holes 71h of the cylindrical bodies 71, 71b impingement-cools the passage defining surface that defines the blade air passage.

[0117] (5) The stator blade in the fifth aspect is In the stator vane 50 in the fourth aspect, the blade air passage is defined by a plurality of passage defining surfaces including a first passage defining surface 57a extending in the blade height direction Dr, and a second passage defining surface 57b connected to the first passage defining surface 57a, extending in the blade height direction Dr and spreading in a direction intersecting the first passage defining surface 57a. The insert supports 80, 80a, 80c, 80d, 80e project from the support plate 81 to the first blade height side Dro, are located on the side of the first passage defining surface 57a rather than the position regulating projecting pieces 82, 82c in a direction perpendicular to the blade height direction Dr, and have first pressing portions 83a, 83da, 83ea having a first contact surface 84a in contact with the first passage defining surface 57a, and second pressing portions 83b, 83db, 83eb projecting from the support plate 81 to the first blade height side Dro, located on the side of the second passage defining surface 57b rather than the position regulating projecting pieces 82, 82c in a direction perpendicular to the blade height direction Dr, and having a second contact surface 84b in contact with the second passage defining surface 57b.

[0118] In this aspect, the position regulating projecting pieces 82, 82c of the insert supports 80, 80a, 80c, 80d, 80e can regulate the relative position of the insert cylinders 70, 70b, 70c with respect to the insert supports 80, 80a, 80c, 80d, 80e in a direction perpendicular to the blade height direction Dr. Also, in this aspect, since the first contact surface 84a of the insert supports 80, 80a, 80c, 80d, 80e is in contact with the first passage defining surface 57a and the second contact surface 84b of the insert supports 80, 80a, 80c, 80d, 80e is in contact with the second passage defining surface 57b, the relative position of the insert supports 80, 80a, 80c, 80d, 80e with respect to the blade air passage in a direction perpendicular to the blade height direction Dr can be accurately determined. Therefore, in this aspect, the distance from the cylinder bodies 71, 71b of the insert cylinders 70, 70b, 70c to a plurality of passage defining surfaces including the first passage defining surface 57a and the second passage defining surface 57b can be accurately set to the target distance. Thus, in this aspect, the impingement cooling performance of the plurality of passage defining surfaces by the cooling air Acl ejected from the plurality of impingement holes 71h of the cylinder bodies 71, 71b can be appropriately managed.

[0119] (6) In the stator vane according to the sixth aspect, In the stator vane 50 in the fifth aspect, the position regulating protruding piece 82 is located on the inner peripheral side of the cylindrical body 71 and faces the inner peripheral surface of the cylindrical body 71. A first groove 86a that is recessed on the second vane height side Dri and into which the end of the cylindrical body 71 on the second vane height side Dri enters is formed between the position regulating protruding piece 82 and the first pressing portions 83da, 83ea. A second groove 86b that is recessed on the second vane height side Dri and into which the end of the cylindrical body 71 on the second vane height side Dri enters is formed between the position regulating protruding piece 82 and the second pressing portions 83db, 83eb.

[0120] In this aspect, even if the insert supports 80d, 80e have the first pressing portions 83da, 83ea and the second pressing portions 83db, 83eb, by the end of the cylindrical body 71 on the second vane height side Dri entering the first groove 86a and the second groove 86b, the position of the end of the cylindrical body 71 on the second vane height side Dri can be brought closer to the position of the anti-gas path surface of the second shroud body. For this reason, in this aspect, while maintaining the overlap amount in the vane height direction Dr between the cylindrical body 71 and the position regulating protruding piece 82, the position of the impinge hole 71h formed on the most second vane height side Dri in the cylindrical body 71 can be brought closer to the position of the anti-gas path surface of the second shroud body.

[0121] (7) In the stator vane according to the seventh aspect, In the stator vane 50 in the sixth aspect, the second pressing portion 83eb is separated from the first pressing portion 83ea.

[0122] In this aspect, the first groove 86a and the second groove 86b can be easily machined.

[0123] (8) In the stator vane according to the eighth aspect, In the stator vane 50 according to any one of the fourth aspect to the seventh aspect, the cooling air space in the recess is partitioned into a first space S1 on the first side Dro of the blade height and a second space S2 on the second side Dri of the blade height, and an impingement plate 95i is provided with a plurality of impingement holes 95h penetrating from the second space S2 to the first space S1. Among the insert cylinders 70, 70b, 70c and the insert supports 80, 80a, 80c, 80d, 80e, either one has guide cylinder portions 71b, 74, 88 that can guide the cooling air Acl flowing into the cylinder bodies 71, 71b into the second space S2. The guide cylinder portions 71b, 74, 88 extend in the blade height direction Dr, and the end on the second side Dri of the blade height is located in the second space S2.

[0124] In this aspect, the blocking plate 90 can be prevented from interfering with the end on the second side Dri of the blade height of the guide cylinder portions 71b, 74, 88 due to thermal expansion of a part of the stator vane.

[0125] The gas turbine in the above embodiments and modifications can be understood as follows, for example. (9) The gas turbine in the ninth aspect includes the stator vane 50 according to any one of the first aspect to the eighth aspect, a rotor 31 rotatable about an axis Ar, and a turbine casing 38 covering the rotor 31. The stator vane is attached inside the turbine casing 38 such that the blade height direction Dr becomes the radial direction Dr with respect to the axis Ar.

Explanation of reference numerals

[0126] 1: Gas turbine rotor 6: Intermediate casing 7: Inner cover 8: Gas turbine casing 10: Compressor 11: Compressor rotor 12: Rotor shaft 13: Moving blade row 15: Stator vane row 18: Compressor casing 20: Combustor 21: Burner 22: Tail pipe (or combustion chamber) 30: Turbine 31: Turbine rotor 32: Rotor shaft 33: Moving blade row 35: Stationary blade row 37: Split ring 38: Turbine casing 39: Combustion gas flow path 40: Cooling device 41: Extraction line 42: Cooler 43: Boost compressor 44: Cooling air line 45: Cooling air exhaust line 50: Stationary blade 51: Blade body 52: Leading edge 53: Trailing edge 54: Suction surface 55: Pressure surface 56: Blade air passage 56a: First blade air passage (or simply blade air passage) 56ai: Inner opening 56ao: Outer opening 56b: Second blade air passage 56bi: Inner opening 56c: Third blade air passage 57a: First passage defining surface 57b: Second passage defining surface 59f: Leading edge injection passage 59b: Trailing edge injection passage 60i: Inner shroud (or second shroud) 60o: Outer shroud (or first shroud) 61i: Inner shroud body (or second shroud body) 61o: Outer shroud body (or first shroud body) 62f: Front end face 62b: Rear end face 63n: Suction side end face 63p: Pressure side end face 64p: Gas path surface 64a: Anti-gas path surface 65i, 65o: Peripheral wall 65f: Front wall 65b: Rear wall 65n: Negative pressure side wall 65p: Positive pressure side wall 66: Recess 68f: Front hook 68b: Rear hook 69: Retainer 70, 70b, 70c: Insert cylinder 71: Cylindrical body 71b: Cylindrical body (or guide cylinder part) 71h: Impinge hole 72: Radial inner end (or second side end) 73: Flange part (or groove bottom) 73b, 73c: Flange part 74: Groove side wall part (or guide cylinder part) 74b: Groove side wall part 75b: Groove bottom 76, 76b: Projection insertion groove 80: Insert support 81: Support plate 81c: Groove bottom 81o: Support plate opening 82: Position regulating projection 82c: Position regulating projection (or inner position regulating projection) 83a, 83da: First pressing part 83b, 83db: Second pressing part 84a: First contact surface 84b: Second contact surface 85: Throttle ring 85o: Throttle opening 86a: First groove 86b: Second groove 87: Groove side wall part (or outer position regulating projection) 88: Guide cylinder part 89: Cylindrical body insertion groove 90: Plugging plate 90f: Front plugging plate 90b: Rear plugging plate 91: Passage facing part 92: Transition part 93: Outer peripheral part 93a: Curved part 95i: Inner impinge plate (or simply impinge plate) 95o: Outer impinge plate 95h: Impinge hole A: Ambient air Acom: Compressed air Acl: Cooling air G: Combustion gas F: Fuel CL: Camber line S1: First space S2: Second space Ar: Axis Da: Axial direction Dau: Upstream side of the axis Dad: Downstream side of the axis Dc: Circumferential direction Dcn: Negative pressure side in the circumferential direction Dcp: Positive pressure side in the circumferential direction Dr: Radial direction (or blade height direction) Dri: Inner side in the radial direction (or second side of the blade height) Dro: Outer side in the radial direction (or first side of the blade height)

Claims

1. A blade body having an airfoil-shaped cross-section and extending in a blade height direction having a direction component perpendicular to the cross-section, A blade air passage extending in the blade height direction inside the blade body and through which cooling air can flow, A first shroud provided at an end on the first side of the blade height of the blade body, A second shroud provided at an end on the second side of the blade height, which is opposite to the first side of the blade height of the blade body, A blocking plate fixed to the second shroud, Comprising: The first shroud has a first shroud body that extends in a direction perpendicular to the blade height direction from the end on the first side of the blade height of the blade body, The second shroud has a second shroud body that extends in a direction perpendicular to the blade height direction from the end on the second side of the blade height of the blade body, and a peripheral wall that protrudes from the outer peripheral edge of the second shroud body toward the second side of the blade height, The second shroud body and the peripheral wall jointly form a concave portion that is recessed toward the first side of the blade height on the second side of the blade height of the second shroud body, The blade air passage penetrates the first shroud body, the blade body, and the second shroud body in the blade height direction, The blocking plate is disposed at a distance from the second shroud body toward the second side of the blade height, and partitions the cooling air space in the concave portion and the space on the second side of the blade height from the cooling air space, The blocking plate has a passage facing portion that faces the blade air passage in the blade height direction, a transition portion connected around the passage facing portion, and an outer peripheral portion connected around the transition portion and at least a part of which is joined to the peripheral wall, The passage facing portion is located on the second side of the blade height relative to the connection portion with the transition portion in the outer peripheral portion, The transition portion is formed to gradually face the second side of the blade height as it approaches the passage facing portion from the outer peripheral portion, A stator blade.

2. The stator blade according to Claim 1, The outer peripheral portion has a curved portion that gradually faces the second side of the blade height in a direction perpendicular to the blade height direction as it moves away from the passage facing portion, A stator blade.

3. The stator blade according to Claim 2, The blade body has a leading edge, a trailing edge, a positive pressure surface connecting the leading edge and the trailing edge, and a negative pressure surface connecting the leading edge and the trailing edge in a back-to-back relationship with the positive pressure surface, The second shroud has a retainer connected to the peripheral wall, The peripheral wall of the second shroud has a positive pressure side wall that exists on the positive pressure side where the positive pressure surface exists with respect to the negative pressure surface based on the airfoil, and a negative pressure side wall that exists on the negative pressure side opposite to the positive pressure side based on the airfoil. The retainer is connected to the positive pressure side wall and the negative pressure side wall. The curved portion is joined to the retainer. Stationary vane.

4. In the stationary vane according to any one of Claims 1 to 3, an insert cylinder at least a part of which is disposed in the air passage of the airfoil; an insert support for supporting the insert cylinder; comprising The insert cylinder extends in the airfoil height direction to form a cylindrical shape, and has a cylindrical body that is open at each of the end on the first side of the airfoil height and the end on the second side of the airfoil height, and in which a plurality of impinge holes penetrating from the inner peripheral side to the outer peripheral side are formed. The insert support has a support plate that extends in a direction perpendicular to the airfoil height direction, and a position regulating projection that protrudes from the support plate to the first side of the airfoil height. having The support plate has a support plate opening that penetrates in the airfoil height direction at a portion facing the inner peripheral side region of the cylindrical body in the airfoil height direction. The position regulating projection protrudes from the support plate to the first side of the airfoil height over the entire circumference of the opening edge of the support plate opening, faces the inner peripheral surface or the outer peripheral surface of the cylindrical body, and regulates the relative position of the insert cylinder with respect to the insert support in a direction perpendicular to the airfoil height direction. The support plate is joined to the second shroud body at the outer peripheral edge of the support plate. The insert cylinder is engaged with the insert support so as to be relatively movable. Stationary vane.

5. In the stationary vane according to Claim 4, the air passage of the airfoil is defined by a plurality of passage defining surfaces including a first passage defining surface that extends in the airfoil height direction and a second passage defining surface that is connected to the first passage defining surface, extends in the airfoil height direction, and extends in a direction intersecting the first passage defining surface. The insert support has a first pressing portion that protrudes from the support plate to the first side of the airfoil height, is located on the side of the first passage defining surface rather than the position regulating projection in a direction perpendicular to the airfoil height direction, and has a first contact surface that contacts the first passage defining surface. A second pressing portion that protrudes from the support plate toward the first side of the blade height, is located on the side of the second passage defining surface closer to the second passage defining surface than the position regulating protrusion piece in a direction perpendicular to the blade height direction, and has a second contact surface that contacts the second passage defining surface. having stator vane.

6. In the stator vane according to claim 5, The position regulating protrusion piece is located on the inner peripheral side of the cylindrical body and faces the inner peripheral surface of the cylindrical body. A first groove that is recessed toward the second side of the blade height and into which the end of the cylindrical body on the second side of the blade height has entered is formed between the position regulating protrusion piece and the first pressing portion. A second groove that is recessed toward the second side of the blade height and into which the end of the cylindrical body on the second side of the blade height has entered is formed between the position regulating protrusion piece and the second pressing portion. stator vane.

7. In the stator vane according to claim 6, The second pressing portion is separated from the first pressing portion. stator vane.

8. In the stator vane according to claim 4, An impingement plate that partitions the cooling air space in the recess into a first space on the first side of the blade height and a second space on the second side of the blade height, and has a plurality of impingement holes penetrating from the second space to the first space is provided. Among the insert cylinder and the insert support, either one has a guide cylinder portion that guides the cooling air flowing into the cylindrical body into the second space. The guide cylinder portion extends in the blade height direction, and the end on the second side of the blade height is located in the second space. stator vane.

9. The stator vane according to any one of claims 1 to 3, a rotor rotatable about an axis, a turbine casing covering the rotor, comprising The stator vane is attached inside the turbine casing such that the blade height direction is the radial direction with respect to the axis. gas turbine.

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