Stator blade and gas turbine with same

Abstract

This 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 the 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.

Description

Stationary blade and gas turbine equipped with same

[0001] This application claims priority to Japanese Patent Application No. 2023-198363, filed on November 22, 2023, the contents of which are incorporated herein by reference.

[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 capable of being driven 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 an axial direction about the axis and a plurality of rows of moving blades attached to the rotor shaft. The plurality of rows of moving blades are arranged at intervals from each other in the axial direction. Each of the plurality of rows of moving blades has a plurality of moving blades that are arranged in a circumferential direction about the axis. A plurality of rows of stator blades are provided inside the turbine casing. The plurality of rows of stator blades are arranged at intervals from each other in the axial direction. Each of the plurality of rows of stator blades has a plurality of stator blades that are arranged in the circumferential direction about the axis.

[0003] Patent Document 1 below discloses a gas turbine stator vane. The stator vane includes a blade body extending radially relative to the axis, an outer shroud provided radially outward of the blade body, an inner shroud provided radially inward of the blade body, and a blade cooling air passage. The blade body of the stator vane is disposed in a combustion gas flow path through which combustion gas passes. The outer shroud extends in a direction perpendicular to the radial direction of the blade body and includes an outer shroud body that defines the radially outer edge of the combustion gas flow path, and a peripheral wall that projects radially outward from the outer peripheral edge of the outer shroud body. The outer shroud body and the peripheral wall together form a recess that is recessed radially inward on the radial outer side of the outer shroud body. The inner shroud extends in a direction perpendicular to the radial direction of the blade body and includes an inner shroud body that defines the radially inner edge of the combustion gas flow path, and a peripheral wall that projects radially inward from the outer peripheral edge of the inner shroud body. The inner shroud body and the peripheral wall cooperate to form a recess that is recessed radially outward on the radially inner side of the inner shroud body. The opening of this recess is closed by a blocking plate joined to the edge of the opening. The blade cooling air passages radially penetrate the outer shroud body, the blade body, and the inner shroud body.

[0004] The vane further includes an insert (or insert tube) disposed within the blade air passage. The insert has a cylindrical body extending radially. A plurality of impingement holes are formed in the cylindrical body, penetrating from the inner peripheral side to the outer peripheral side. In this vane, cooling air that has flowed into the recessed portion of the outer shroud flows into the insert within the blade cooling air passage. After passing through the plurality of impingement holes in the insert, the cooling air flows into a recessed portion formed radially inward of the inner shroud body.

[0005] JP 2013-019348 A

[0006] In the technology described in Patent Document 1, the inner shroud is exposed to high-temperature combustion gas, while the blocking plate joined to the inner shroud is in contact with cooling air and is not exposed to the combustion gas, which causes a thermal expansion difference between the inner shroud and the blocking plate, which may damage the joint between the inner shroud and the blocking plate or the blocking plate.

[0007] Therefore, an object of the present disclosure is to provide a vane that can suppress damage to a blocking plate joined to a shroud and to the joint portion between the shroud and the blocking plate, and a gas turbine including the vane.

[0008] To achieve the above object, one aspect of the invention provides a stator vane comprising: a blade body having an airfoil-shaped cross section and extending in a blade height direction having a directional component perpendicular to the cross section; a blade air passage extending in the blade body in the blade height direction and allowing cooling air to flow therethrough; a first shroud provided at an end of the blade body on a first blade height side in the blade height direction; a second shroud provided at an end of the blade body on a second blade height side opposite the first blade height side; and a blocking plate fixed to the second shroud. The first shroud has a first shroud body extending in a direction perpendicular to the blade height direction from the end of the blade body on the first blade height side. The second shroud has a second shroud body extending in a direction perpendicular to the blade height direction from the end of the blade body on the second blade height side, and a peripheral wall protruding from an outer circumferential edge of the second shroud body toward the second blade height side. The second shroud body and the peripheral wall cooperate to form a recess recessed toward the first blade height side on the second blade height side 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 blade height side with respect to the second shroud body and separates the cooling air space in the recess from a space on the second blade height side of the cooling air space. The blocking plate has a passage opposing portion facing the blade air passage in the blade height direction, a transition portion connected around the passage opposing portion, and an outer peripheral portion connected around the transition portion and at least a portion of which is joined to the peripheral wall. The passage opposing portion is located on the second blade height side of the outer peripheral portion. The transition portion is formed so as to gradually move toward the second blade height side as it approaches the passage opposing portion from the outer peripheral portion.

[0009] The first shroud, the blade body, and the second shroud are exposed to high-temperature combustion gas G. On the other hand, the blocking plate joined to the second shroud is in contact with cooling air and is not exposed to the combustion gas G. Therefore, a thermal expansion difference occurs between the second shroud and the blocking plate. In this aspect, even if a thermal expansion difference occurs between the second shroud and the blocking plate, the connection portion between the passage opposing portion and the transition portion and the connection portion between the transition portion and the outer periphery deforms, allowing the blocking plate to reasonably tolerate this thermal expansion difference. Therefore, in this aspect, damage to the joint portion between the second shroud and the blocking plate and to the blocking plate can be suppressed.

[0010] Furthermore, in this aspect, the distance between the passage-facing portion and the second shroud body is larger than the distance between the second shroud body and at least the connecting portion with the transition portion in the outer periphery. This allows the distance between the passage-facing portion and the second shroud body to be larger than if the distance between the passage-facing portion and the second shroud body were equal to the distance between the connecting portion with the transition portion in the outer periphery and the second shroud body. Therefore, in this aspect, a pressure drop in the cooling air that occurs when the cooling air passes through the blade air passage and impinges on the passage-facing portion of the blocking plate can be suppressed. Therefore, in this aspect, the cooling air that passes through the blade air passage and flows into the recessed portion of the second shroud can be effectively used for cooling the second shroud, etc.

[0011] A gas turbine according to one aspect of the invention for achieving the above object includes a stator vane according to the above aspect, a rotor rotatable about an axis, and a turbine casing covering the rotor, wherein the stator vane is attached inside the turbine casing such that the blade height direction is radial to the axis.

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

[0013] 1 is a schematic cross-sectional view of a gas turbine according to an embodiment of the present disclosure; FIG. 1 is a cross-sectional view of a main portion of a gas turbine according to an embodiment of the present disclosure; FIG. 2 is a perspective view of a stator vane according to an embodiment of the present disclosure, viewed from the radially outer side; FIG. 3 is a perspective view of a stator vane according to an embodiment of the present disclosure, viewed from the radially inner side; FIG. 4 is a cross-sectional view of a cross section along a camber line of a stator vane according to an embodiment of the present disclosure; FIG. 5 is a cross-sectional view of a main portion of a stator vane according to an embodiment of the present disclosure; FIG. 6 is a perspective view of an insert support according to an embodiment of the present disclosure; FIG. 7 is a cross-sectional view of a main portion of a blade body according to an embodiment of the present disclosure; FIG. 8 is a flowchart showing a manufacturing procedure of a stator vane according to an embodiment of the present disclosure; FIG. 9 is a cross-sectional view of a main portion of a blade body in a manufacturing process of a stator vane according to an embodiment of the present disclosure; FIG. 10 is a cross-sectional view of an insert tube and an insert support according to a first modified example according to the present disclosure; FIG. 11 is a cross-sectional view of a main portion of a stator vane according to a second modified example according to the present disclosure; FIG. 12 is a cross-sectional view of a main portion of a stator vane according to a third modified example according to the present disclosure; FIG. 13 is a perspective view of an insert support according to a fourth modified example according to the present disclosure; FIG. 14 is a cross-sectional view of a main portion of a stator vane according to a fourth modified example according to the present disclosure; FIG. 15 is a perspective view of an insert support according to a fifth modified example according to the present disclosure;

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

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

[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 capable of being driven by the combustion gas G.

[0017] The compressor 10 includes a compressor rotor 11 that rotates about an axis Ar, a compressor casing 18 that covers the compressor rotor 11, and a plurality of stator vane rows 15. The turbine 30 includes a turbine rotor 31 that rotates about the axis Ar, a turbine casing 38 that covers the turbine rotor 31, and a plurality of stator vane rows 35. In the following, the direction in which the axis Ar extends is referred to as the axial direction Da, the circumferential direction about the axis Ar is simply referred to as the circumferential direction Dc, and the direction perpendicular to the axis Ar is referred to as the radial direction Dr. One side of the axial direction Da is referred to as the axial upstream side Dau, and the opposite side is referred to as the axial downstream side Dad. The side of the radial direction Dr that approaches the axis Ar is referred to as the radially inner side Dri, and the opposite side is referred to as the radially outer side Dro.

[0018] The compressor 10 is disposed on the axial upstream side Dau relative 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. To this gas turbine rotor 1, for example, a rotor of a generator GEN is connected. 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 Figures 1 and 2, the compressor rotor 11 has a rotor shaft 12 extending in an axial direction Da centered on an axis Ar, and a plurality of rotor blade rows 13 attached to the rotor shaft 12. The plurality of rotor blade rows 13 are aligned in the axial direction Da. Each rotor blade row 13 is made up of a plurality of rotor blades aligned in a circumferential direction Dc. One of the plurality of stator blade rows 15 is arranged on the axial downstream side Dad of each of the plurality of rotor blade rows 13. Each stator blade row 15 is provided inside a compressor casing 18. Each stator blade row 15 is made up of a plurality of stator blades aligned in the circumferential direction Dc.

[0021] The turbine rotor 31 has a rotor shaft 32 extending in the axial direction Da centered on the axis Ar, and a plurality of rotor blade rows 33 attached to the rotor shaft 32. The plurality of rotor blade rows 33 are aligned in the axial direction Da. Each rotor blade row 33 is composed of a plurality of rotor blades aligned in the circumferential direction Dc. One of the plurality of stator blade rows 35 is arranged on the axial upstream side Dau of each of the plurality of rotor blade rows 33. Each stator blade row 35 is provided inside a turbine casing 38. Each stator blade row 35 is composed of a plurality of stator blades aligned in the circumferential direction Dc.

[0022] The annular space between the outer circumferential side of the rotor shaft 32 and the inner circumferential side of the turbine casing 38, in which the rotor blade row 33 and the stator 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 forms an annular shape centered on the axis Ar and extends in the axial direction Da.

[0023] In addition to the plurality of stator blade rows 35, a plurality of ring segments 37 are provided inside the turbine casing 38. The plurality of ring segments 37 are located at positions where the rotor blade rows 33 are present in the axial direction Da, on the radially outer side Dro of the rotor blade rows 33. Therefore, the plurality of ring segments 37 are located between the plurality of stator blade rows 35 lined up in the axial direction Da. The ring segments 37 define part of the edge of the combustion gas flow path 39 on the radially outer side Dro.

[0024] The combustor 20 is attached to the intermediate casing 6. As shown in Fig. 2 , the combustor 20 has a transition piece (or combustion piece) 22 in which fuel F is burned, and a plurality of burners 21 that inject fuel into the transition piece 22.

[0025] A cooling device 40 is connected to the gas turbine of this embodiment. The cooling device 40 has an extraction line 41, a cooler 42, a boost compressor 43, and a cooling air line 44. One end of the extraction line 41 is connected to the intermediate casing 6, and the other end of the extraction line 41 is connected to an inlet of the boost compressor 43. The extraction line 41 is capable of extracting compressed air in the intermediate casing 6 to the outside of the gas turbine casing 8. The cooler 42 is provided in the extraction line 41 and is capable of cooling the compressed air flowing through the extraction line 41. The boost compressor 43 is capable of boosting the pressure of the compressed air cooled by the cooler 42. The cooling air line 44 has one end and multiple other ends. One end of the cooling air line 44 is connected to a discharge port of the boost compressor 43. The multiple other ends of the cooling air line 44 are connected to any of multiple high-temperature components, such as stator vanes, that are exposed to the combustion gas G. This cooling air line 44 can guide compressed air from the boost compressor 43 as cooling air Ac1 to the high-temperature components.

[0026] "Embodiments of Stator Vanes" Embodiments of the stator vanes will be described with reference to Figures 3 to 10. Note that the stator vanes described below are all stator vanes that constitute the stator vane row 35 described in the "Embodiments of Gas Turbine" above.

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

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

[0029] 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 connecting the leading edge 52 and the trailing edge 53 in a back-to-back relationship with 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 of the blade body on the axial upstream side Dau. The trailing edge is the end of the blade body on the axial downstream side Dad. 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 one side in the circumferential direction Dc. The suction surface faces the circumferential suction side Dcn, which is the other side in the circumferential direction Dc.

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

[0031] The peripheral wall protrudes radially inwardly 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 pressure side wall 65p and a suction side wall 65n that face each other in the circumferential direction Dc. The front wall 65f is provided along a front end surface 62f of the inner shroud body. The rear wall 65b is provided along a rear end surface 62b of the inner shroud body. The pressure side wall 65p is provided along a pressure side end surface 63p of the inner shroud body. The suction side wall 65n is provided along a suction side end surface 63n of the inner shroud body. A recess recessed toward the radially outwardly Dro is formed in the inner shroud by the inner shroud body and the peripheral wall. The surface of the circumferential pressure side Dcp of the pressure side wall 65p is flush with the pressure side end surface 63p of the inner shroud main body. The surface of the circumferential suction side Dcn of the suction side wall 65n is flush with the suction side end surface 63n of the inner shroud main body. The rear wall 65b is formed along the rear end surface 62b of the inner shroud main body, but is formed on the axial upstream side Dau of the rear end surface 62b.

[0032] 2 , a stator vane constituting one of the stator vane rows 35 is provided with a retainer that protrudes radially inwardly Dri from the pressure side wall 65 p and the suction side wall 65 n of the inner shroud. This retainer is located between the front wall 65 f and the rear wall 65 b in the axial direction Da, and is formed from the pressure side end face 63 p to the suction side end face 63 n. This retainer comes into contact with the end of the radially outer side Dro of the inner cover 7 that is fixed to the gas turbine casing 8, and serves to support the radially inner side Dri of the stator vane on the end of the radially outer side Dro of the inner cover 7.

[0033] As shown in FIGS. 3 and 5 , the outer shroud (first shroud) 60o includes an outer shroud body (first shroud body) 61o, a peripheral wall 65o, a front hook 68f, and an aft hook 68b. The outer shroud body extends in a direction perpendicular to the radial direction Dr from the end of the radially outer side Dro of the blade body. Like the inner shroud body, the outer shroud body also includes a gas path surface, an opposite gas path surface, a front end surface 62f, an aft end surface 62b, a pressure side end surface 63p, and a suction side end surface 63n. Like the inner shroud body, the outer shroud body also has a parallelogram shape when viewed from the radial direction Dr. 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 opposite gas path surface of the outer shroud body. This peripheral wall 65o is provided along the end face of the outer shroud body. Like the peripheral wall of the inner shroud, the peripheral wall 65o of the outer shroud also has a front wall 65f, a rear wall 65b, a pressure side wall 65p, and a suction side wall 65n. The front wall 65f is provided along a front end face 62f of the outer shroud body. The rear wall 65b is provided along a rear end face 62b of the outer shroud body. The pressure side wall 65p is provided along a pressure side end face 63p of the outer shroud body. The suction side wall 65n is provided along a suction side end face 63n of the outer shroud body. A recess recessed toward the radially inward (Dri) is formed in the outer shroud by the outer shroud body and the peripheral wall 65o. The surface of the circumferential pressure side Dcp of the pressure side wall 65p is flush with the pressure side end surface 63p of the outer shroud main body, and the surface of the circumferential suction side Dcn of the suction side wall 65n is flush with the suction side end surface 63n of the outer shroud main body.

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

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

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

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

[0039] As shown in Figures 3 and 5, the outer impingement plate 95o is fixed to the outer shroud. This outer impingement plate 95o is disposed in a recess of the outer shroud and divides the recess of the outer shroud into a space on the radially outer side Dro and a space on the radially inner side Dri. A plurality of impingement holes 95h penetrating in the radial direction Dr are formed in the outer impingement plate 95o. Cooling air AcI from the cooling device 40 described with reference to Figure 2 flows into the space in the recess of the outer shroud that is radially outer than the outer impingement plate 95o. This cooling air AcI passes through the plurality of impingement holes 95h in the outer impingement plate 95o and performs impingement cooling on the anti-gas path surface of the outer shroud main body. The cooling air Ac1 that has impingement-cooled the anti-gas path surface is injected to the outside of the outer shroud body, for example, from the forward end surface 62f and / or the aft end surface 62b of the outer shroud body. The outer opening 56ao of the first blade air passage described above is located radially outward Dro of the outer impingement plate 95o. Therefore, a portion of the cooling air Ac1 from the cooling device 40 flows into the first blade air passage from this outer opening 56ao.

[0040] The blocking plates 90 are fixed to the inner shroud. The blocking plates 90 are arranged at a distance radially inward Dri from the inner shroud body to separate the cooling air space in the recess of the inner shroud from a space radially inward Dri of the cooling air space. The blocking plates 90 include a front blocking plate 90f arranged axially upstream Dau of the retainer and a rear blocking plate 90b arranged axially downstream Dad of the retainer.

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

[0042] The insert tube 70 has a cylindrical shape and is disposed in the first blade air passage. The insert support 80 is fixed to the inner shroud body so as to support the insert tube 70.

[0043] As shown in Figures 5 and 6, the insert tube 70 has a cylindrical body 71 that extends 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 cylindrical body 71 has an open end at the radially outer side Dro and an open end at the radially inner side Dri. A plurality of impingement holes 71h are formed in the cylindrical body 71, penetrating from the inner circumferential side to the outer circumferential side. The flange 73 is annular. The outer circumferential edge of the annular flange 73 is joined to the inner circumferential surface of the cylindrical body 71. The flange 73 protrudes toward the inner circumferential side of the cylindrical body 71 from a position on the inner circumferential surface of the cylindrical body 71 closer to the radially inner side Dri of the cylindrical body 71. Therefore, the flange 73 narrows the air passage within the cylindrical body 71. In this embodiment, the projected area of ​​the flange 73 in the blade height direction Dr is equal to or greater than half the area of ​​the air flow path within the cylindrical body 71 in a direction perpendicular to the blade height direction Dr. The groove side wall portion 74 has a cylindrical shape and is connected to the inner peripheral edge of the flange portion 73 and extends from the flange portion 73 toward the radially inner side Dri. The annular groove side wall portion 74 penetrates the inner impingement plate 95i. Therefore, the radially inner end Dri of the groove side wall portion 74 is located radially inner Dri than the inner impingement plate 95i and radially inner Dri than the blocking plate 90. The outer peripheral surface of the annular groove side wall portion 74 faces, with a gap therebetween, the inner peripheral surface of the radially inner end portion 72 of the annular cylindrical body 71, which includes the end of the radially inner side Dri. The annular groove side wall portion 74 and the annular cylindrical body 71 are connected by the annular flange portion 73. Therefore, an annular protruding piece insertion groove 76 is formed between the annular groove side wall portion 74 and the annular cylindrical body 71, with the annular flange portion 73 serving as the groove bottom. The protruding piece insertion groove 76 is recessed radially outward Dro.

[0045] As shown in Figures 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 control protrusion 82 that is provided on the support plate 81, and a first pressing portion 83a and a second pressing portion 83b that are also provided on the support plate 81.

[0046] The support plate 81 has a support plate opening 81o penetrating in the radial direction Dr in a portion facing the inner peripheral region of the cylindrical body 71. The annular groove side wall portion 74 of the insert tube 70 is inserted into this support plate opening 81o. The position restricting protrusion 82 protrudes radially outward Dro from the support plate 81 around the entire opening edge of the support plate opening 81o, forming a cylindrical shape. The cylindrical position restricting protrusion 82 fits into the annular protrusion insertion groove 76 of the insert tube 70. Therefore, the inner peripheral surface of the cylindrical position restricting protrusion 82 faces the outer peripheral surface of the annular groove side wall portion 74 of the insert tube 70, and the outer peripheral surface of the cylindrical position restricting protrusion 82 faces the inner peripheral surface of the radially inner end portion 72, including the end of the radially inner Dri, of the annular cylindrical body 71 of the insert tube 70. The insert tube 70 is engaged with the insert support 80 so as to be relatively movable.

[0047] The radially outer end Dro of the insert tube 70 is connected to the edge of the outer opening 56ao of the first blade air passage (see FIG. 5). On the other hand, the radially inner end 72 of the insert tube 70 is restricted from moving in a direction perpendicular to the radial direction Dr by an annular position restricting protrusion 82 on the insert support body 80, but is allowed to move in the radial direction Dr relative to the insert support body 80. Therefore, in this embodiment, movement of the insert tube 70 in a direction perpendicular to the radial direction Dr can be restricted while allowing for differential thermal expansion in the radial direction Dr between the insert tube 70 and the blade body.

[0048] 8 , the multiple passage-defining surfaces that define the first blade 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 widens in a direction intersecting the first passage-defining surface. The first passage-defining surface faces the circumferential pressure side Dcp and defines the edge of the circumferential suction side Dcn of the first blade air passage. The second passage-defining surface faces the axial upstream side Dau and defines the edge of the axial downstream side Dad of the first blade air passage.

[0049] 6 to 8, the first pressing portion 83a protrudes radially outward Dro from the support plate 81, is positioned closer to the first passage-defining surface than the position restricting protrusion 82 in a direction perpendicular to the radial direction Dr, and has a first contact surface 84a in contact with the first passage-defining surface. The second pressing portion 83b protrudes radially outward Dro from the support plate 81, is positioned closer to the second passage-defining surface than the position restricting protrusion 82 in a direction perpendicular to the radial direction Dr, and has a second contact surface 84b in contact with the second passage-defining surface.

[0050] As shown in Figures 4 to 6, the front blocking plate 90f has a passage facing portion 91 facing the first blade air passage in the radial direction Dr, a transition portion 92 connected to the periphery of the passage facing portion 91, and an outer peripheral portion 93 connected to the periphery of the transition portion 92 and at least a portion of which is connected to the peripheral wall of the inner shroud. The passage facing portion 91 is located radially inward Dri than the outer peripheral portion 93. The transition portion 92 is formed so as to gradually move toward the 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 moves toward the radially inward Dri as it moves away from the passage facing portion 91 in a direction perpendicular to the radial direction Dr. An edge of this curved portion 93a is connected to the retainer.

[0051] Next, the method for manufacturing the vane described above will be described with reference to the flowchart shown in FIG.

[0052] First, the stator blade body, the outer impingement plate 95o, the inner impingement plate 95i, the blocking plate 90, the insert cylinder 70, and the insert support body 80 are prepared (preparation step S10).

[0053] The vane body is an integral assembly of an outer shroud, a blade body, and an inner shroud, and is formed by, for example, casting.

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

[0055] Next, the insert support 80 is fixed to the vane main 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 restricting protrusion 82 of the insert support 80 is made to face the radially inner end 72 of the cylindrical body 71. Specifically, the insert tube 70 is arranged so that the position restricting protrusion 82 of the insert support 80 enters the protrusion insertion groove 76 between the cylindrical body 71 and the groove side wall portion 74 of the insert tube 70, and the outer peripheral surface of the annular position restricting protrusion 82 faces the inner peripheral surface of the cylindrical body 71. Furthermore, in the arrangement step S12a, as shown in FIG. 10 , the first contact surface 84a of the insert support 80 faces the first passage defining surface 57a of the first blade air passage 56a, and the second contact surface 84b of the insert support 80 faces the second passage defining surface 57b of the first blade air passage 56a. 8, in the pressing step S12b, 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, the outer peripheral edge of the support plate 81 is joined to the anti-gas path surface 64a of the inner shroud body 61i in a state in which the first contact surface 84a is in contact with the first passage-defining surface 57a and the second contact surface 84b is in contact with the second passage-defining surface 57b.

[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 arranging step S13).

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

[0058] The timing of placing the insert tube 70 so that the position restricting protrusion 82 of the insert support 80 fits into the protrusion insertion groove 76 of the insert tube 70, that is, the timing of performing the placing step S12a, may be after the tube placing step S11 or before the tube placing step S11.

[0059] The flow of cooling air within the stationary blade will be described with reference to FIGS.

[0060] Cooling air Ac1 from the cooling device 40 described with reference to FIG. 2 flows into a space within the recess of the outer shroud, radially outward of the outer impingement plate 95o. A portion of this cooling air Ac1 passes through a plurality of impingement holes 95h in the outer impingement plate 95o and impingement-cools the anti-gas path surface of the outer shroud body. The cooling air Ac1 that has impingement-cooled the anti-gas path surface is ejected to the outside 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. Another portion of the cooling air Ac1 flows into the cylinder body 71 of the insert cylinder 70 arranged in the first blade air passage.

[0061] The cooling air Ac1 that has flowed into the cylindrical body 71 of the insert cylinder 70 flows inside the cylindrical body 71 toward the radially inner side Dri. During this process, a portion of the cooling air Ac1 passes through the multiple impingement holes 71h in the cylindrical body 71. The remaining cooling air Ac1 passes through an annular groove side wall portion 74 fixed to the cylindrical body 71 and flows into the second space S2 between the stopper plate 90 and the inner impingement plate 95i in the recessed portion of the inner shroud. Therefore, the annular groove side wall portion 74 fixed to the cylindrical body 71 forms a guide cylindrical portion that guides the cooling air Ac1 that has flowed into the cylindrical body 71 into the second space S2.

[0062] The cooling air Ac1 that passes through the multiple impingement holes 71h in the cylindrical body 71 impingement cools the passage defining surface that defines the first blade air passage. The cooling air Ac1 that has impingement cooled the passage defining surface flows into the multiple leading edge injection passages 59f. The portion of the blade body near the leading edge is convection cooled by the cooling air Ac1 that flows through the multiple leading edge injection passages 59f. This cooling air Ac1 is injected from near the leading edge of the blade body into the combustion gas flow path 39 outside the blade body.

[0063] The cooling air Ac1 that flows into the second space S2 in the recessed portion of the inner shroud passes through the multiple impingement holes 95h of the inner impingement plate 95i and impingement-cools the anti-gas path surface of the inner shroud body. The cooling air Ac1 that has impingement-cooled the anti-gas path surface of the inner shroud body flows into the second blade air passage 56b and flows within this second blade air passage 56b toward the radially outer side Dro. While flowing within this second blade air passage 56b, the cooling air Ac1 convectively cools the periphery of the second blade air passage 56b within the blade body.

[0064] The cooling air Ac1 then flows into the third blade air passage 56c and flows radially inwardly within the third blade air passage 56c toward the radially inward Dri. As the cooling air Ac1 flows through the third blade air passage 56c, it convectively cools the periphery of the third blade air passage 56c within the blade body. The cooling air Ac1 also flows into the multiple trailing edge injection passages 59b. The portion of the blade body near the trailing edge is convectively cooled by the cooling air Ac1 flowing through the multiple trailing edge injection passages 59b. This cooling air Ac1 is injected from near 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 tube 70 is not joined to the insert support 80 so as to allow for the difference in thermal expansion between the insert tube 70 and the blade body in the radial direction Dr. Therefore, a portion of the cooling air Ac1 that flows into the space radially inwardly of the inner shroud body Dri may leak into the space on the outer circumferential side of the cylindrical body 71 within the first blade air passage through the gap between the insert support 80 and the insert tube 70. If the flow rate of the cooling air Ac1 that leaks into the space on the outer circumferential side of the cylindrical body 71 within the first blade air passage through the gap between the insert support 80 and the insert tube 70 increases, the pressure difference between the space on the inner circumferential side of the cylindrical body 71 and the space on the outer circumferential side of the cylindrical body 71 decreases. Therefore, the speed of the cooling air Ac1 on the inner circumferential side of the cylindrical body 71 when passing through the multiple impingement holes 71h in the cylindrical 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 body 80 and the insert tube 70 is the gap between the protrusion insertion groove 76 and the position limiting protrusion 82 inserted into this groove 76. Therefore, the flow path of the cooling air Ac1 formed by this gap is a flow path that undulates and bends in the radial direction Dr. Therefore, in this embodiment, the resistance of the cooling air Ac1 flowing through the flow path formed by the gap between the insert support body 80 and the insert tube 70 is large. In particular, the resistance of the cooling air Ac1 is large at the corners of this flow path.

[0067] Furthermore, in this embodiment, the flange 73 that narrows the air passage inside the cylinder 71 is provided inside the cylinder 71, so it is possible to reduce the pressure of the cooling air Ac1 that has passed through the flange 73 inside the cylinder 71. In particular, in this embodiment, the projected area of ​​the flange 73 in the blade height direction Dr is equal to or greater than half the area of ​​the air flow path inside the cylinder 71 in a direction perpendicular to the blade height direction Dr. Therefore, in this embodiment, it is possible to reduce the pressure of the cooling air Ac1 that flows out of the cylinder 71 and into the gap between the insert support 80 and the insert cylinder 70.

[0068] As described above, in the present embodiment, the resistance of the cooling air Ac1 flowing through the flow path formed by the gap between the insert support body 80 and the insert cylinder 70 increases, and the pressure of the cooling air Ac1 flowing into the gap between the insert support body 80 and the insert cylinder 70 decreases. This reduces the flow rate of the cooling air Ac1 leaking into the space on the outer circumferential side of the cylinder body 71 within the first blade air passage. Therefore, in the present 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 the present embodiment, as described above, the position limiting protrusion 82 of the insert support 80 can limit the relative position of the insert tube 70 with respect to the insert support 80 in a direction perpendicular to the radial direction Dr. Furthermore, in the present embodiment, the first contact surface 84a of the insert support 80 contacts the first passage-defining surface, and the second contact surface 84b of the insert support 80 contacts the second passage-defining surface. This allows the relative position of the insert support 80 with respect to the first blade air passage in a direction perpendicular to the radial direction Dr to be accurately determined. Therefore, in the present embodiment, the distance from the outer peripheral surface of the cylindrical body 71 of the insert tube 70 to the multiple passage-defining surfaces, including the first passage-defining surface and the second passage-defining surface, can be accurately set to the desired distance. Therefore, in the present embodiment, the impingement cooling performance of the multiple passage-defining surfaces by the cooling air Ac1 ejected from the multiple impingement holes 71h of the cylindrical body 71 can be appropriately managed.

[0070] The outer shroud, the blade body, and the inner shroud are exposed to high-temperature combustion gas G. On the other hand, the blocking plate 90 joined to the inner shroud is in contact with the cooling air Ac1 and is not exposed to the combustion gas G. Therefore, a thermal expansion difference occurs between the inner shroud and the blocking plate 90. In this embodiment, even if a thermal expansion difference occurs between the inner shroud and the blocking plate 90, the connection portion between the passage opposing portion 91 and the transition portion 92 and the connection portion between the transition portion 92 and the outer peripheral portion 93 deforms, so that the blocking plate 90 can reasonably tolerate this thermal expansion difference. Therefore, in this embodiment, damage to the joint portion between the inner shroud and the blocking plate 90 and to the blocking plate 90 can be suppressed. Furthermore, even if a thermal expansion difference occurs between the inner shroud and the blocking plate 90, the curved portion 93 a in the outer peripheral portion 93 deforms, so that damage to the joint portion between the curved portion 93 a in the outer peripheral portion 93 and the retainer can be suppressed.

[0071] Furthermore, in the present embodiment, the gap between the passage facing portion 91 and the inner shroud body is larger than the gap between the inner shroud body and at least the connecting portion with the transition portion 92 in the outer circumferential portion 93. In the present embodiment, the gap between the passage facing portion 91 and the inner shroud body can be made larger than when the gap between the passage facing portion 91 and the inner shroud body is equal to the gap between the connecting portion with the transition portion 92 in the outer circumferential portion 93 and the inner shroud body. Therefore, in the present embodiment, a pressure drop of the cooling air Ac1 passing through the first blade air passage due to collision with the passage facing portion 91 of the blocking plate 90 can be suppressed. Therefore, in the present embodiment, the cooling air Ac1 passing through the insert tube 70 in the first blade air passage and flowing into the recess of the inner shroud can be effectively used for cooling the inner shroud, etc. Furthermore, in the present embodiment, it is possible to prevent the blocking plate 90 from interfering with the radially inner end Dri of the groove side wall portion (guide tube portion) 74 due to thermal expansion of a portion of the vane.

[0072] 11, an insert support 80a in this modification is different from the insert support 80 in the above embodiment. On the other hand, an insert cylinder 70 in this modification is the same as the insert cylinder 70 in the above embodiment.

[0073] The insert support 80a in this modified example has a throttle ring 85 in addition to the support plate 81, position limiting protrusion 82, first pressing portion 83a, and second pressing portion 83b that the insert support 80 of the above embodiment has. The throttle ring 85 is fixed to a surface of the support plate 81 facing the radially inner side Dri. The throttle ring 85 has a throttle opening 85o into which the annular groove side wall portion 74 of the insert tube 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 limiting protrusion 82 of the insert support 80a and the annular groove side wall portion 74 of the insert tube 70.

[0074] For this reason, in this modification, it is possible to reduce the flow rate of the cooling air Ac1 in the space radially inward Dri of the inner shroud body that flows into the gap between the insert support body 80a and the insert cylinder 70. Therefore, in the present embodiment, it is possible to reduce the flow rate of the cooling air Ac1 that leaks into the space on the outer circumferential side of the cylinder body 71 within the first blade air passage.

[0075] 12, an insert tube 70b in this modification is different from the insert tube 70 in the above embodiment. On the other hand, an insert support 80 in this modification is the same as the insert support 80 in the above embodiment.

[0076] 12, like the insert tube 70 in the above embodiment, the insert tube 70b in this modification includes a cylindrical body 71b extending in the radial direction Dr, a flange 73b that narrows the air passage in the cylindrical body 71b, and a groove side wall 74b. The insert tube 70b in this modification further includes a groove bottom 75b.

[0077] In this modified example, the end of the radially inner 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. Like the cylindrical body 71 in the above embodiment, the cylindrical body 71b has openings at the end of the radially outer Dro and the end of the radially inner Dri. Therefore, the cooling air Ac1 that flows into the cylindrical body 71b from the opening of the radially outer Dro of the cylindrical body 71b can pass through the cylindrical body 71b and flow into the second space S2 between the blocking plate 90 and the inner impingement plate 95i in the recess of the inner shroud. Therefore, the cylindrical body 71b forms a guide cylindrical portion that guides the cooling air Ac1 that flows into the cylindrical body 71b into the second space S2. The cylindrical body 71b also has multiple impingement holes 71h that penetrate from the inner circumferential side to the outer circumferential side. The flange portion 73b is annular. The outer peripheral edge of the annular flange 73b is joined to the inner peripheral surface of the cylindrical body 71b. The flange 73b protrudes from a position on the inner peripheral surface of the cylindrical body 71b closer to the radially inner side Dri of the cylindrical body 71b toward the inner peripheral side of the cylindrical body 71b. Therefore, the flange 73b narrows the air passage within the cylindrical body 71b. The groove bottom 75b is annular. The outer peripheral edge of the annular groove bottom 75b is joined to the outer peripheral surface of the cylindrical body 71b. The groove bottom 75b protrudes from a position on the outer peripheral surface of the cylindrical body 71b closer to the radially inner side Dri of the cylindrical body 71b toward the outer peripheral side of the cylindrical body 71b. The groove side wall 74b is cylindrical, joined to the outer peripheral edge of the annular groove bottom 75b, and extends toward the radially inner side Dri. The inner peripheral surface of the annular groove side wall 74b faces the outer peripheral surface of the annular cylindrical body 71b with a gap therebetween. Therefore, an annular protrusion insertion groove 76b is formed between the annular groove side wall 74b and the annular cylindrical body 71b. This protrusion insertion groove 76b is recessed radially outward (Dro). The annular position-limiting protrusion 82 of the insert support 80 fits into this annular protrusion insertion groove 76b.

[0078] In the insert tube 70 according to the above embodiment, the protruding piece insertion groove 76 is formed on the inner circumferential side of the cylindrical body 71. On the other hand, in the insert tube 70b according to this modification, the protruding piece insertion groove 76b is formed on the outer circumferential side of the cylindrical body 71b.

[0079] As described above, in this modified example, the gap between the insert support body 80 and the insert tube 70b is the gap between the protrusion insertion groove 76b and the position limiting protrusion 82 inserted into this groove 76b. Therefore, the flow path for the cooling air Ac1 formed by this gap is a flow path that undulates and bends in the radial direction Dr. Therefore, in this modified example, as in the above embodiment, the resistance of the cooling air Ac1 flowing through the flow path formed by the gap between the insert support body 80 and the insert tube 70b is large.

[0080] Also in this modification, the flange 73b that narrows the air passage inside the cylinder 71b is provided inside the cylinder 71b, so that the pressure of the cooling air Ac1 that passes through the flange 73b inside the cylinder 71b can be reduced. Therefore, in this modification, the pressure of the cooling air Ac1 that flows out of the cylinder 71b and into the gap between the insert support 80 and the insert cylinder 70b can be reduced.

[0081] As described above, in this modified example, similar to the above embodiment, the resistance of the cooling air Ac1 flowing through the flow path formed by the gap between the insert support body 80 and the insert cylinder 70b increases, and the pressure of the cooling air Ac1 flowing into the gap between the insert support body 80 and the insert cylinder 70b decreases. This reduces the flow rate of the cooling air Ac1 leaking into the space on the outer circumferential side of the cylinder body 71b within the first blade air passage. Therefore, in this modified example, it is possible to suppress a decrease in the impingement cooling effect on the passage defining surface that defines the first blade air passage.

[0082] In this modified example, too, the radially inner end Dri of the cylindrical body 71b forming the guide cylindrical portion is located radially inward Dri of the inner impingement plate 95i and radially outward Dro of the blocking plate 90. However, the passage facing portion 91 of the blocking plate 90 is located radially inward Dri of the outer peripheral portion 93 of this blocking plate 90. Therefore, it is possible to prevent the blocking plate 90 from interfering with the radially inner end Dri of the cylindrical body 71b forming the guide cylindrical portion due to thermal expansion of part of the stator blade.

[0083] The support plate 81 of the insert support 80 in this modification may be provided with the diaphragm ring 85 described in the first modification.

[0084] 13, an insert tube 70c in this modification is different from the insert tube 70 of the above embodiment. Also, an insert support 80c in this modification is different from the insert support 80 of the above embodiment.

[0085] Similar to the insert tube 70 in the above embodiment, the insert tube 70c in this modification includes a cylindrical body 71 extending in the radial direction Dr and a flange 73c that narrows the air passage within the body 71. However, the insert tube 70c in this modification does not have the groove bottom and groove side wall portions of the insert tube 70 in the above embodiment. Therefore, the insert tube 70c in this modification does not have the protruding piece insertion groove 76 of the insert tube 70 in the above embodiment. Similar to the cylindrical body 71 in the above embodiment, the cylindrical body 71 has an open end at the radially outer side Dro and an open end at the radially inner side Dri. This cylindrical body 71 also has multiple impingement holes 71h that penetrate from the inner periphery to the outer periphery. The flange 73c is annular. The outer peripheral edge of the annular flange 73c is joined to the inner periphery of the cylindrical body 71. The flange 73c protrudes from a position on the inner circumferential surface of the cylindrical body 71 toward the inner circumferential side of the cylindrical body 71, closer to the radially inner side Dri of the cylindrical body 71. Therefore, the air passage inside the cylindrical body 71 is narrowed by the flange 73c.

[0086] Similar to the insert support 80 in the above embodiment, the insert support 80c in this modified example includes a support plate 81 that extends in a direction perpendicular to the radial direction Dr and is fixed to the opposite gas path surface of the inner shroud body, a position restricting protrusion 82c, a first pressing portion 83a, a second pressing portion 83b, a groove side wall portion 87, and a guide tube portion 88. The position restricting protrusion 82c, the first pressing portion 83a, the second pressing portion 83b, the groove side wall portion 87, and the guide tube 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 in a portion facing the inner peripheral region of the cylindrical body 71. The position restricting protrusion 82c is cylindrical and protrudes radially outward Dro around the entire circumference of the opening edge of the support plate opening 81o. This position restricting protrusion 82c is located on the inner peripheral side of the cylindrical body 71 and faces the inner peripheral surface of the radially inner end 72 of the cylindrical body 71. Therefore, this position restricting protrusion 82c constitutes an inner position restricting protrusion. The groove side wall portion 87 is cylindrical and protrudes radially outward Dro from the support plate 81 around 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 of the radially inner end 72 of the cylindrical body 71. Therefore, this groove side wall portion 87 constitutes an outer position restricting protrusion. The portion of the support plate 81 between the position limiting projection 82c and the groove side wall 87, i.e., between the inner position limiting projection 82c and the outer position limiting projection 87, forms the groove bottom 81c. In this insert support 80c, an annular cylinder insertion groove 89 is formed between the inner position limiting projection 82c and the outer position limiting projection 87. This cylinder insertion groove 89 is recessed radially inward Dri. The radially inner end 72 of the cylinder 71 fits into this cylinder insertion groove 89.

[0088] The first pressing portion 83a protrudes radially outward from the support plate 81 Dro, is positioned closer to the first passage defining surface (see FIG. 8) than the inner position limiting protrusion 82c and the outer position limiting protrusion 87 in a direction perpendicular to the radial direction Dr, and has a first contact surface 84a (see FIG. 8) in contact with the first passage defining surface. The second pressing portion 83b protrudes radially outward from the support plate 81 Dro, is positioned closer to the second passage defining surface (see FIG. 8) than the inner position limiting protrusion 82c and the outer position limiting protrusion 87 in a direction perpendicular to the radial direction Dr, and has a second contact surface 84b (see FIG. 8) in contact with the second passage defining surface.

[0089] The guide tube portion 88 is cylindrical and protrudes radially inward Dri around the entire circumference of the edge of the support plate opening 81o. The radially inward end Dri of the guide tube portion 88 is located within the second space S2. Therefore, the guide tube portion 88 can guide the cooling air Ac1 that has flowed into the cylindrical body 71 into the second space S2.

[0090] As described above, in this modification, the gap between the insert support body 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 inserted in this groove 89. Therefore, the flow path of the cooling air Ac1 formed by this gap becomes a flow path that undulates and bends in the radial direction Dr. Therefore, in this modification, as in the above embodiment and the second modification, the resistance of the cooling air Ac1 flowing through the flow path formed by the gap between the insert support body 80c and the insert cylinder 70c becomes large.

[0091] Also in this modification, the flange 73c that narrows the air passage inside the cylindrical body 71 is provided inside the cylindrical body 71, so it is possible to reduce the pressure of the cooling air Ac1 that has passed through the flange 73c inside the cylindrical body 71. Therefore, in this modification, it is possible to reduce the pressure of the cooling air Ac1 that flows out from inside the cylindrical body 71 and into the gap between the insert support body 80c and the insert cylinder 70c.

[0092] As described above, in this modification, as in the above embodiment and the second modification, the resistance of the cooling air Ac1 flowing through the flow path formed by the gap between the insert support body 80c and the insert cylinder 70c increases, and the pressure of the cooling air Ac1 flowing into the gap between the insert support body 80c and the insert cylinder 70c decreases. This makes it possible to reduce the flow rate of the cooling air Ac1 leaking into the space on the outer circumferential side of the cylinder body 71 within the first blade air passage. Therefore, in this modification, it is possible to suppress a decrease in the impingement cooling effect on the passage defining surface that defines the first blade air passage.

[0093] In this modified example, too, the radially inner end Dri of the guide tube portion 88 is located radially inward Dri of the inner impingement plate 95i and radially outward Dro of the blocking plate 90. However, the passage facing portion 91 of the blocking plate 90 is located radially inward Dri of the outer peripheral portion 93 of this blocking plate 90. Therefore, it is possible to prevent the blocking plate 90 from interfering with the radially inner end Dri of the guide tube portion 88 due to thermal expansion of part of the stator blade.

[0094] 14 and 15 , the insert tube 70 in this modification is the same as the insert tube 70 in the above embodiment. On the other hand, the insert support 80d in this modification is different from the insert support 80 in the above embodiment.

[0095] As shown in Figures 14 and 15, the insert support 80d in this modified example, like the insert support 80 in the above embodiment, 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 control protrusion 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] Similar to the first pressing portion 83a in the above embodiment, the first pressing portion 83da in this modified example also protrudes radially outward Dro from the support plate 81, is positioned closer to the first passage defining surface than the position restricting protrusion 82 in the direction perpendicular to the radial direction Dr, and has a first contact surface 84a in contact with the first passage defining surface. Similarly to the first pressing portion 83a in the above embodiment, the second pressing portion 83db in this modified example also protrudes radially outward Dro from the support plate 81, is positioned closer to the second passage defining surface than the position restricting protrusion 82 in the direction perpendicular to the radial direction Dr, and has a second contact surface 84b in contact with the second passage defining surface.

[0097] In this modified example, a first groove 86a is formed between the annular position restricting projection 82 and the first pressing portion 83da, recessed toward the radially inner side Dri, and into which the end 71i of the radially inner side Dri of the cylindrical body 71 is fitted. Furthermore, in this modified example, a second groove 86b is formed between the annular position restricting projection 82 and the second pressing portion 83db, recessed toward the radially inner side Dri, and into which the end 71i of the radially inner side Dri of the cylindrical body 71 is fitted.

[0098] In this modification, even if the insert support 80d has the first pressing portion 83da and the second pressing portion 83db, the end 71i of the radially inner 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 radially inner side Dri of the cylindrical body 71 can be brought closer to the position of the opposite gas path surface of the inner shroud main body. Therefore, in this modification, the overlap amount between the cylindrical body 71 and the position limiting protrusion 82 in the radial direction Dri is maintained, and the position of the impingement hole 71h formed on the radially innermost side Dri in the cylindrical body 71 can be brought closer to the position of the opposite gas path surface of the inner shroud main body.

[0099] Fifth Modification of Insert Cylinder and Insert Support Body This modification differs from the fourth modification only in the insert support body, and the other configurations of this modification are the same as those of the fourth modification.

[0100] As shown in Figure 16, the insert support 80e in this modified example, like the insert support 80d in the fourth modified 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 control protrusion 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] In this modification, as in the fourth modification, a first groove 86a is formed between the annular position restricting projection 82 and the first pressing portion 83ea, recessed toward the radially inner side Dri, into which the end 71i of the radially inner side Dri of the cylindrical body 71 fits. Furthermore, in this modification, a second groove 86b is formed between the annular position restricting projection 82 and the second pressing portion 83eb, recessed toward the radially inner side Dri, into which the end 71i of the radially inner side Dri of the cylindrical body 71 fits.

[0102] However, in this modified example, the second pressing portion 83eb is spaced apart from the first pressing portion 83ea. Therefore, in this modified example, when the machining tool is moved in a direction along the first contact surface 84a to machine the first groove 86a between the first pressing portion 83ea and the position restricting protrusion 82, the machining tool can be moved in a direction along the first contact surface 84a to a position where the second pressing portion 83eb is located. Furthermore, in this modified example, when the machining tool is moved in a direction along the second contact surface 84b to machine the second groove 86b between the second pressing portion 83eb and the position restricting protrusion 82, the machining tool can be moved in a direction along the second contact surface 84b to a position where the first pressing portion 83ea is located. Therefore, in this modified example, the first groove 86a and the second groove 86b can be easily machined.

[0103] Modifications The stator vanes in the above-described embodiment and each modification have three blade air passages 56. However, the stator vanes may have four or more blade air passages 56.

[0104] In the stator vanes in the above-described embodiment and each modified example, the insert tubes 70, 70b, 70c are arranged in the first blade air passage Dau, which is located on the most axially upstream side, of the multiple blade air passages 56. However, the insert tubes 70, 70b, 70c may be arranged in the blade air passage 56, which is located on the axially downstream side Dad of the first blade air passage Dau, which is located on the most axially upstream side.

[0105] In the above-described embodiment and each modified example, the first passage-defining surface that defines the blade air passage 56 of the stator vane faces the circumferential pressure side Dcp and defines the edge of the circumferential suction side Dcn of the first blade air passage. Alternatively, the second passage-defining surface faces the axial upstream side Dau and defines the edge of the axial downstream side Dad of the first blade air passage. However, it is sufficient that both the first passage-defining surface and the second passage-defining surface extend in the radial direction Dr, and the second passage-defining surface is connected to the first passage-defining surface and extends in a direction intersecting the first passage-defining surface. For example, suppose the first passage-defining surface faces the circumferential pressure side Dcp and defines the edge of the circumferential suction side Dcn of the blade air passage 56. In this case, if a 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 the second passage defining surface.

[0106] Furthermore, the present disclosure is not limited to the embodiment and modifications described above, and various additions, modifications, substitutions, partial deletions, etc. are possible within the scope of the conceptual idea and spirit of the present invention derived from the content defined in the claims and their equivalents.

[0107] "Additional Notes" The stator vanes in the above embodiments and modified examples can be understood, for example, as follows. (1) A stator vane in a first aspect comprises: a blade body having an airfoil-shaped cross section and extending in a blade height direction Dr having a directional component perpendicular to the cross section; a blade air passage extending in the blade height direction Dr within the blade body and allowing cooling air Ac1 to 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 the first blade height side Dro; and a blocking plate 90 fixed to the second shroud. The first shroud has a first shroud main body extending from the end of the blade body on the first blade height side Dro in a direction perpendicular to the blade height direction Dr. The second shroud has a second shroud body extending in a direction perpendicular to the blade height direction Dr from an end of the blade height second side Dri of the blade body, and a peripheral wall protruding from an outer circumferential edge of the second shroud body toward the blade height second side Dri. The second shroud body and the peripheral wall cooperate to form a recess on the blade height second side Dri of the second shroud body that is recessed toward the blade height first side Dro. The blade air passage penetrates the first shroud body, the blade body, and the second shroud body in the blade height direction Dr. The blocking plate 90 is disposed at a distance from the second shroud body on the blade height second side Dri and separates the cooling air space within the recess from a space on the blade height second side Dri beyond the cooling air space. The blocking plate 90 has a passage opposing portion 91 opposing the blade air passage in the blade height direction Dr, a transition portion 92 connected to the periphery of the passage opposing portion 91, and an outer circumferential portion 93 connected to the periphery of the transition portion 92 and at least a portion of which is joined to the peripheral wall. The passage opposing portion 91 is located on the second blade height side Dri with respect to a connection portion with the transition portion 92 in the outer circumferential portion 93. The transition portion 92 is formed so as to gradually move toward the second blade height side Dri as it approaches the passage opposing portion 91 from the outer circumferential portion 93.

[0108] The first shroud, the blade body, and the second shroud are exposed to high-temperature combustion gas G. On the other hand, the blocking plate 90 joined to the second shroud is in contact with the cooling air Ac1 and is not exposed to the combustion gas G. Therefore, a thermal expansion difference occurs between the second shroud and the blocking plate 90. In this aspect, even if a thermal expansion difference occurs between the second shroud and the blocking plate 90, the connection portion between the passage opposing portion 91 and the transition portion 92 and the connection portion between the transition portion 92 and the outer peripheral portion 93 deforms, so that the blocking plate 90 can reasonably tolerate this thermal expansion difference. Therefore, in this aspect, damage to the joint portion between the second shroud and the blocking plate 90 and to the blocking plate 90 can be suppressed.

[0109] Furthermore, in this aspect, the gap between the passage facing portion 91 and the second shroud body is larger than the gap between at least a connecting portion of the outer circumferential portion 93 with the transition portion 92 and the second shroud body. This allows the gap between the passage facing portion 91 and the second shroud body to be larger than if the gap between the passage facing portion 91 and the second shroud body were equal to the gap between a connecting portion of the outer circumferential portion 93 with the transition portion 92 and the second shroud body. Therefore, in this aspect, a pressure drop of the cooling air Ac1 that occurs when the cooling air Ac1 passes through the blade air passage and impinges on the passage facing portion 91 of the blocking plate 90 can be suppressed. Therefore, in this aspect, the cooling air Ac1 that passes through the blade air passage and flows into the recessed portion of the second shroud can be effectively used for cooling the second shroud, etc.

[0110] (2) In the second aspect, in the stator vane 50 in the first aspect, the outer circumferential portion 93 has a curved portion 93a that gradually curves toward the second blade height side Dri as it moves away from the passage opposing portion 91 in a direction perpendicular to the blade height direction Dr.

[0111] In this aspect, even if a thermal expansion difference occurs between the second shroud and the blocking plate 90, the connecting portion between the passage facing portion 91 and the transition portion 92, the connecting portion between the transition portion 92 and the outer circumferential portion 93, and the curved portion 93a in the outer circumferential portion 93 deform, so that the blocking plate 90 can reasonably tolerate this thermal expansion difference. Therefore, in this aspect, damage to the connecting portion between the second shroud and the blocking plate 90 and to the blocking plate 90 can be suppressed.

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

[0113] In this embodiment, the deformation of the curved portion 93a can prevent damage to the joint portion between the curved portion 93a and the retainer in the outer circumferential portion 93.

[0114] (4) A stator vane according to a fourth aspect includes the stator vane 50 according to any one of the first to third aspects, and includes insert tubes 70, 70b, 70c at least a portion of which is disposed within the blade air passage, and insert supports 80, 80a, 80c, 80d, 80e that support the insert tubes 70, 70b, 70c. The insert tubes 70, 70b, 70c have cylindrical bodies 71, 71b that extend in the blade height direction Dr and open at an end of the blade height first side Dro and an end of the blade height second side Dri, and in which a plurality of impingement holes 71h are formed, penetrating from the inner circumferential side to the outer circumferential side. The insert supports 80, 80a, 80c, 80d, 80e include a support plate 81 extending in a direction perpendicular to the blade height direction Dr, and position restricting protrusions 82, 82c protruding from the support plate 81 toward the blade height first side Dro. The support plate 81 has a support plate opening 81o penetrating in the blade height direction Dr at a portion facing an inner peripheral region of the cylindrical body 71, 71b in the blade height direction Dr. The position restricting protrusions 82, 82c protrude from the support plate 81 toward the blade height first side Dro around the entire opening edge of the support plate opening 81o, face the inner peripheral surface or outer peripheral surface of the cylindrical body 71, 71b, and restrict the relative position of the insert cylinder 70, 70b, 70c with respect to the insert supports 80, 80a, 80c, 80d, 80e in a direction perpendicular to the blade height direction Dr. The support plate 81 is joined to the second shroud body at an outer peripheral edge of the support plate 81. The insert cylinder is engaged with the insert support member so as to be relatively movable with respect to the insert support member.

[0115] In this embodiment, the insert tubes 70, 70b, 70c are engaged with the insert supports 80, 80a, 80c, 80d, 80e so as to be relatively movable. In this embodiment, the position-limiting protrusions 82, 82c of the insert supports 80, 80a, 80c, 80d, 80e, which are fixed to the second shroud body, face the inner or outer circumferential surface of the cylindrical body 71, 71b of the insert tubes 70, 70b, 70c. Therefore, in this embodiment, movement of the insert tubes 70, 70b, 70c in a direction perpendicular to the blade height direction Dr can be restricted, while the ends of the insert tubes 70, 70b, 70c on the second blade height side Dri can move in the blade height direction Dr relative to the blade body. Therefore, in this embodiment, differential thermal expansion between the insert tubes 70, 70b, 70c and the blade body in the blade height direction Dr can be tolerated.

[0116] In this embodiment, the cooling air Ac1 present on the first blade height side Dro relative to the first shroud body flows into the cylinders 71, 71b of the insert cylinders 70, 70b, 70c arranged in the blade air passage. The cooling air Ac1 that has flowed into the cylinders 71, 71b flows within the cylinders 71, 71b toward the second blade height side Dri. During this process, a portion of the cooling air Ac1 passes through the multiple impingement holes 71h in the cylinders 71, 71b. The remaining cooling air Ac1 flows through the support plate opening 81o into the space on the second blade height side Dri relative to the second shroud body. The cooling air Ac1 that has passed through the multiple impingement holes 71h in the cylinders 71, 71b impinges upon and cools the passage defining surfaces that define the blade air passage.

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

[0118] In this aspect, the position restricting protrusions 82, 82c of the insert supports 80, 80a, 80c, 80d, 80e can restrict the relative position of the insert tubes 70, 70b, 70c with respect to the insert supports 80, 80a, 80c, 80d, 80e in a direction perpendicular to the blade height direction Dr. Furthermore, in this aspect, the first contact surfaces 84a of the insert supports 80, 80a, 80c, 80d, 80e contact the first passage defining surface 57a, and the second contact surfaces 84b of the insert supports 80, 80a, 80c, 80d, 80e contact the second passage defining surface 57b, so that the relative positions 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 cylindrical bodies 71, 71 b of the insert cylinders 70, 70 b, 70 c to the plurality of passage defining surfaces, including the first passage defining surface 57 a and the second passage defining surface 57 b, can be accurately set to a target distance. Therefore, in this aspect, the impingement cooling performance of the plurality of passage defining surfaces by the cooling air Ac1 ejected from the plurality of impingement holes 71 h of the cylindrical bodies 71, 71 b can be appropriately managed.

[0119] (6) A stator vane according to a sixth aspect is the stator vane 50 according to the fifth aspect, wherein the position limiting protrusion 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 is formed between the position limiting protrusion 82 and the first pressing portions 83da, 83ea, recessed toward the blade height second side Dri and into which an end of the cylindrical body 71 on the blade height second side Dri is fitted. A second groove 86b is formed between the position limiting protrusion 82 and the second pressing portions 83db, 83eb, recessed toward the blade height second side Dri and into which an end of the cylindrical body 71 on the blade height second side Dri is fitted.

[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, the end of the cylindrical body 71 on the second blade height side Dri enters the first groove 86a and the second groove 86b, so that the position of the end of the cylindrical body 71 on the second blade height side Dri can be brought closer to the position of the opposite gas path surface of the second shroud main body. Therefore, in this aspect, the overlap amount between the cylindrical body 71 and the position limiting projection 82 in the blade height direction Dr is maintained, and the position of the impingement hole 71h that is formed closest to the second blade height side Dri in the cylindrical body 71 can be brought closer to the position of the opposite gas path surface of the second shroud main body.

[0121] (7) A stator vane according to a seventh aspect is the stator vane 50 according to the sixth aspect, wherein the second pressing portion 83 eb is spaced apart from the first pressing portion 83 ea.

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

[0123] (8) A stator vane according to an eighth aspect is the stator vane 50 according to any one of the fourth to seventh aspects, further comprising an impingement plate 95i that divides the cooling air space within the recess into a first space S1 on the blade height first side Dro and a second space S2 on the blade height second side Dri, and that has a plurality of impingement holes 95h formed therein that penetrate from the second space S2 to the first space S1. Either the insert tube 70, 70b, 70c or the insert support 80, 80a, 80c, 80d, 80e has a guide tube portion 71b, 74, 88 that can guide the cooling air Ac1 that has flowed into the tube body 71, 71b into the second space S2. The guide tube portion 71b, 74, 88 extends in the blade height direction Dr, and an end of the blade height second side Dri is located in the second space S2.

[0124] In this aspect, it is possible to prevent the blocking plate 90 from interfering with the ends of the guide tube portions 71b, 74, and 88 on the second blade height side Dri due to thermal expansion of a portion of the stator blade.

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

[0126] According to one aspect of the present disclosure, damage to the blocking plate joined to the shroud and to the joint portion between the shroud and the blocking plate can be suppressed.

[0127] 1: Gas turbine rotor 6: Intermediate casing 7: Inner cover 8: Gas turbine casing 10: Compressor 11: Compressor rotor 12: Rotor shaft 13: Row of moving blades 15: Row of stator blades 18: Compressor casing 20: Combustor 21: Burner 22: Transition piece (or combustion duct) 30: Turbine 31: Turbine rotor 32: Rotor shaft 33: Row of moving blades 35: Row of stator blades 37: Segment 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: Stator 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 surface 62b: Rear end surface 63n: Suction side end surface 63p: Pressure side end surface 64p: Gas path surface 64a: Anti-gas path surface 65i, 65o: Peripheral wall 65f: Front wall 65b: Rear wall 65n: Suction side wall 65p: Pressure side wall 66: Recess 68f: Front hook 68b: Rear hook 69: Retainer 70, 70b, 70c: Insert tube 71: Cylinder 71b: Cylinder (or guide tube portion) 71h: Impingement hole 72: Radial inner end (or second side end) 73: Flange portion (or groove bottom portion) 73b, 73c: Flange portion 74: Groove side wall portion (or guide tube portion) 74b: Groove side wall portion 75b: Groove bottom portion 76, 76b: Projection piece insertion groove 80: Insert support 81: Support plate 81c: Groove bottom portion 81o: Support plate opening 82: Position restricting projection 82c: Position restricting projection (or inner position restricting projection) 83a, 83da: First pressing portion 83b,83db: Second pressing portion 84a: First contact surface 84b: Second contact surface 85: Throttle ring 85o: Throttle opening 86a: First groove 86b: Second groove 87: Groove side wall portion (or outer position restriction protrusion piece) 88: Guide cylinder portion 89: Cylinder insertion groove 90: Blocking plate 90f: Front blocking plate 90b: Rear blocking plate 91: Passage opposing portion 92: Transition portion 93: Outer periphery 93a: Curved portion 95i: Inner impingement plate (or simply impingement plate) 95o: Outer impingement plate 95h: Impingement hole A: Outside air Acom: Compressed air Ac1: Cooling air G: Combustion gas F: Fuel CL: Camber line S1: First space S2: Second space Ar: Axis Da: Axial direction Dau: Axial upstream side Dad: Axial downstream side Dc: Circumferential direction Dcn: Circumferential negative pressure side Dcp: Circumferential positive pressure side Dr: Radial direction (or blade height direction) Dri: Radial inner side (or blade height second side) Dro: Radial outer side (or blade height first side)

Claims

1. A blade body having an airfoil-shaped cross section and extending in a blade height direction having a directional component perpendicular to the cross section; a blade air passage extending in the blade height direction within the blade body and through which cooling air can flow; a first shroud provided at an end of the blade body on a first blade height side in the blade height direction; a second shroud provided at an end of the blade body on a second blade height side opposite to the first blade height side; and a stopper plate fixed to the second shroud; wherein the first shroud has a first shroud body extending from the end of the blade height first side of the blade body in a direction perpendicular to the blade height direction; the second shroud has a second shroud body extending from the end of the blade height second side of the blade body in a direction perpendicular to the blade height direction and a peripheral wall protruding from an outer circumferential edge of the second shroud body to the second blade height side; and wherein a recess recessed to the first blade height side is formed on the second blade height side of the second shroud body in cooperation with the second shroud body and the peripheral wall; 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 on the second blade height side and separates a cooling air space in the recess from a space on the second blade height side of the cooling air space, the blocking plate has a passage opposing portion facing the blade air passage in the blade height direction, a transition portion connected around the passage opposing portion, and an outer circumferential portion connected around the transition portion and at least a portion of which is joined to the peripheral wall, the passage opposing portion is located on the second blade height side of a connection portion with the transition portion within the outer circumferential portion, and the transition portion is formed to gradually move toward the second blade height side as it approaches the passage opposing portion from the outer circumferential portion.

2. A stator vane according to claim 1, wherein said outer circumferential portion has a curved portion which gradually curves towards said second blade height side as it moves away from said passage opposing portion in a direction perpendicular to said blade height direction.

3. A vane as claimed in claim 2, wherein the blade body has a leading edge, a trailing edge, a pressure surface connecting the leading edge and the trailing edge, and a suction surface connecting the leading edge and the trailing edge in a back-to-back relationship with the pressure surface, the second shroud has a retainer connected to the peripheral wall, the peripheral wall of the second shroud has a pressure side wall located on the pressure side where the pressure surface is located relative to the blade body, and a suction side wall located on the suction side opposite the pressure side relative to the blade body, the retainer is connected to the pressure side wall and the suction side wall, and the curved portion is joined to the retainer.

4. A vane according to any one of claims 1 to 3, comprising: an insert tube at least a portion of which is disposed within the blade air passage; and an insert support body supporting the insert tube, wherein the insert tube has a cylindrical body extending in the blade height direction and opening at each of the first blade height end and the second blade height end, and in which a plurality of impingement holes are formed penetrating from the inner peripheral side to the outer peripheral side, and the insert support body has: a support plate extending in a direction perpendicular to the blade height direction, and a position regulating protruding piece protruding from the support plate to the first blade height side, wherein the support plate has a support plate opening penetrating in the blade height direction in a portion facing the inner peripheral region of the cylinder in the blade height direction, and the position regulating protruding piece protrudes from the support plate to the first blade height side around the entire opening edge of the support plate opening, faces the inner peripheral surface or the outer peripheral surface of the cylinder, and regulates the relative position of the insert tube in the direction perpendicular to the blade height direction with respect to the insert support body, the support plate is joined to the second shroud body at an outer circumferential edge of the support plate, and the insert tube is engaged with the insert support body so as to be relatively movable.

5. A stator vane as claimed in claim 4, wherein the blade air passage is defined by a plurality of passage defining surfaces including a first passage defining surface extending in the blade height direction and a second passage defining surface connected to the first passage defining surface, extending in the blade height direction and widening in a direction intersecting the first passage defining surface, and the insert support comprises: a first pressing portion protruding from the support plate to the first blade height side, located on the side of the first passage defining surface of the position restricting protrusion in a direction perpendicular to the blade height direction and having a first contact surface in contact with the first passage defining surface, and a second pressing portion protruding from the support plate to the first blade height side, located on the side of the second passage defining surface of the position restricting protrusion in the direction perpendicular to the blade height direction and having a second contact surface in contact with the second passage defining surface.

6. A stator vane as described in claim 5, wherein the position control protrusion is located on the inner peripheral side of the cylindrical body and faces the inner peripheral surface of the cylindrical body, a first groove is formed between the position control protrusion and the first pressing portion, the first groove being recessed toward the second blade height side and into which the end of the cylindrical body on the second blade height side is inserted, and a second groove is formed between the position control protrusion and the second pressing portion, the second groove being recessed toward the second blade height side and into which the end of the cylindrical body on the second blade height side is inserted.

7. A stator vane according to claim 6, wherein the second pressing portion is spaced apart from the first pressing portion.

8. A vane as described in claim 4, comprising an impingement plate which divides the cooling air space within the recess into a first space on the first blade height side and a second space on the second blade height side, and in which a plurality of impingement holes are formed which penetrate from the second space to the first space, and one of the insert tube and the insert support has a guide tube portion which can guide the cooling air which has flowed into the tube into the second space, the guide tube portion extending in the blade height direction, and an end of the second blade height side located within the second space.

9. A gas turbine comprising: a stator vane according to any one of claims 1 to 3; a rotor rotatable about an axis; and a turbine casing covering said rotor, wherein said stator vane is attached to the inside of said turbine casing such that said blade height direction is radial to said axis.

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