Stator blade and gas turbine provided with same

Abstract

This stator blade comprises: an insert cylinder that is disposed in a blade air passage that passes through a first shroud body, a blade body, and a second shroud body; and an insert support body that supports the insert cylinder. The insert cylinder has: a cylindrical body that has a cylindrical shape and in which a plurality of impingement holes penetrating from an inner peripheral side toward an outer peripheral side is formed; and a flange part that protrudes from the inner peripheral surface of the cylindrical body toward the inner peripheral side of the cylindrical body. The insert support body has a support plate fixed to the second shroud body, and a position restricting protruding piece protruding from the support plate. A protruding piece insertion groove into which the position restricting protruding piece enters is formed in the insert cylinder.

Description

Stationary blade and gas turbine equipped with same

[0001] This application claims priority to Japanese Patent Application No. 2023-198160, 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] Patent Document 2 below also discloses a gas turbine stator vane. Like the stator vane disclosed in Patent Document 1, this stator vane also has 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 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 has an outer shroud body extending in a direction perpendicular to the radial direction of the blade body and defining the radially outer edge of the combustion gas flow path. The inner shroud also has an inner shroud body extending in a direction perpendicular to the radial direction of the blade body and defining the radially inner edge of the combustion gas flow path. The blade air passage radially penetrates the outer shroud body, the blade body, and the inner shroud body. This stator vane also has an insert (or an insert tube) disposed in the blade air passage and a retaining member (or an insert support) that supports the insert. The insert has a cylindrical body extending radially. A plurality of impingement holes are formed in the cylindrical body, penetrating from the inner periphery to the outer periphery. The retaining member extends in a direction perpendicular to the direction of extension of the cylindrical body. The retaining member has a support plate fixed to the outer shroud body and a positioning portion (protrusion) protruding radially outward from the support plate and facing the inner periphery of the cylindrical body. The positioning portion regulates the relative position of the insert in a direction perpendicular to the radial direction with respect to the retaining member. Meanwhile, the radially inner end of the insert is movable radially relative to the retaining member to allow for differential thermal expansion between the insert and the blade body in the radial direction. Cooling air present on the inner periphery of the insert collides with a passage defining surface defining the blade air passage through the plurality of impingement holes in the insert. Therefore, the passage defining surface is impingement-cooled by the cooling air passing through the plurality of impingement holes in the insert.

[0006] In this vane, the support plate does not have an opening in the portion facing the inner peripheral region of the cylinder, so that the cooling air that flows into the cylinder from the radially outer side does not reach the radially inner side of the inner shroud body.

[0007] JP 2013-019348 A JP 2017-150333 A

[0008] Even in the case of the vane described in Patent Document 1, where cooling air flows from the recess of the outer shroud into the recess of the inner shroud via the insert tube in the blade air passage, it is necessary to restrict movement of the insert tube in a direction perpendicular to the radial direction while allowing for differential thermal expansion between the insert tube and the blade body in the radial direction. Therefore, in this case, by adopting the structure of the retaining member (or insert support) in the vane described in Patent Document 2, it is possible to restrict movement of the insert tube in a direction perpendicular to the radial direction (blade height direction) while allowing for differential thermal expansion between the insert tube and the blade body in the radial direction. In this case, it is necessary to provide an opening in the support plate of the retaining member (or insert support) in a portion facing the inner peripheral region of the insert tube.

[0009] When cooling air flows from the recess of the outer shroud into the recess of the inner shroud through the insert tube in the blade air passage, if the retaining member (or insert support) structure for the stator vane described in Patent Document 2 is adopted, some of the cooling air inside the insert tube leaks outward from the gap between the inner circumferential surface of the insert tube and the protruding piece of the insert support. If some of the cooling air inside the insert tube leaks outward from the portion excluding the impingement holes, the pressure difference between the inner circumferential side and the outer circumferential side of the insert tube becomes smaller. As a result, the speed of the cooling air on the inner circumferential side of the insert tube decreases as it passes through the multiple impingement holes in the insert tube, reducing the impingement cooling effect on the passage defining surface that defines the blade air passage.

[0010] Therefore, an object of the present disclosure is to provide a stator vane that can restrict the movement of the insert tube in a direction perpendicular to the blade height direction, while allowing for a thermal expansion difference between the insert and the blade body in the blade height direction, and can suppress a decrease in the impingement cooling effect on the passage defining surface that defines the blade air passage, and a gas turbine equipped with the same.

[0011] 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; an insert tube at least a portion of which is disposed within the blade air passage; and an insert support for supporting the insert tube. The first shroud has a first shroud body extending from the end of the blade body on the first blade height side in a direction perpendicular to the blade height direction. The second shroud has a second shroud body extending from the end of the blade body on the second blade height side in a direction perpendicular to the blade height direction. The blade air passage penetrates the first shroud body, the blade body, and the second shroud body in the blade height direction. The insert tube has a cylindrical shape extending in the blade height direction, a cylindrical body having openings at each of the first blade height end and the second blade height end, and a plurality of impingement holes formed therein that penetrate from the inner periphery to the outer periphery, and a flange portion that protrudes toward the inner periphery of the cylindrical body from a position on the inner periphery of the cylindrical body closer to the second blade height side to narrow the air passage within the cylindrical body. The insert support member has a support plate that extends in a direction perpendicular to the blade height direction and is fixed to the second shroud body, and a position-limiting protrusion that protrudes from the support plate toward the first blade height side. The support plate has a support plate opening that penetrates in the blade height direction in a portion facing the inner periphery of the cylindrical body in the blade height direction. The position-regulating protrusion has a cylindrical shape, protruding from the support plate toward the first blade height side around the entire circumference of the opening edge of the support plate opening, and faces the inner or outer circumferential surface of a second side end portion including the end on the second blade height side of the cylindrical body, and regulates the relative position of the insert tube in a direction perpendicular to the blade height direction with respect to the insert support body. One of the insert tube and the insert support body has a groove bottom portion that extends in a direction perpendicular to the blade height direction, and a groove side wall portion that protrudes in the blade height direction from the groove bottom portion.When the one of the insert tubes is the insert tube, the groove side wall portion is cylindrically shaped so as to face the second side end of the tube at a distance from the second side end of the tube along the entire circumference of the tube, and the groove bottom portion connects the tube and the groove side wall portion along the entire circumference of the tube, so that the tube, the groove side wall portion, and the groove bottom form an annular protrusion insertion groove into which the position restricting protrusion fits. When the one of the insert support bodies is the insert support, the groove side wall portion is cylindrically shaped so as to face the position restricting protrusion at a distance from the second side end of the tube along the entire circumference of the tube, and the groove bottom portion connects the position restricting protrusion and the groove side wall portion along the entire circumference of the tube, so that the position restricting protrusion, the groove side wall portion, and the groove bottom form an annular tube insertion groove into which the second side end of the tube fits. The insert tube is engaged with the insert support body so as to be able to move relatively to the insert support body.

[0012] In this aspect, the insert tube is engaged with the insert support body so as to be relatively movable. In this aspect, the annular position-limiting protrusion of the insert support body, which is fixed to the second shroud body, faces the inner or outer circumferential surface of the insert tube's body. Therefore, in this aspect, movement of the insert tube in a direction perpendicular to the blade height direction can be restricted, while the second side end of the insert tube can move in the blade height direction relative to the blade body. Therefore, in this aspect, thermal expansion differences in the blade height direction between the insert tube and the blade body can be tolerated.

[0013] In this aspect, cooling air present on the first blade height side of the first shroud body flows into the tube of the insert tube arranged in the blade air passage. The cooling air that flows into the tube flows inside the tube toward the second blade height side. In this process, part of the cooling air passes through multiple impingement holes in the tube. The remaining cooling air flows through the support plate opening into the space on the second blade height side of the second shroud body. The cooling air that passes through the multiple impingement holes in the tube impingement cools the passage defining surface that defines the blade air passage.

[0014] In this aspect, the insert tube is not joined to the insert support member to allow for differential thermal expansion between the insert tube and the blade body in the blade height direction. Therefore, some of the cooling air that flows into the space on the second blade height side of the second shroud body through the support plate opening may leak into the space on the outer circumferential side of the tube through the gap between the insert support member and the insert tube. If the flow rate of the cooling air leaking into the space on the outer circumferential side of the tube through the gap between the insert support member and the insert tube increases, the pressure difference between the space on the inner circumferential side of the tube and the space on the outer circumferential side of the tube decreases. Therefore, the speed of the cooling air on the inner circumferential side of the tube decreases as it passes through the multiple impingement holes in the tube, reducing the impingement cooling effect on the passage defining surface that defines the blade air passage.

[0015] In this aspect, when the one of the two is an insert tube, the gap between the insert support and the insert tube is the gap between the protrusion insertion groove and the position-limiting protrusion inserted into this groove. Therefore, the cooling air flow path formed by this gap is a flow path that undulates and bends in the blade height direction. Also, in this aspect, when the one of the two is an insert support, the gap is the gap between the cylinder insertion groove and the second end of the cylinder inserted into this groove. Therefore, the cooling air flow path formed by this gap is also a flow path that undulates and bends in the blade height direction. Therefore, in this aspect, the resistance of the cooling air flowing through the flow path formed by the gap between the insert support and the insert tube is large. The resistance of the cooling air is particularly large at the corners of this flow path.

[0016] In addition, in this aspect, the flange that narrows the air passage within the cylinder is provided inside the cylinder, so the pressure of the cooling air that passes through the flange inside the cylinder can be reduced, and therefore, in this aspect, the pressure of the cooling air that flows out of the cylinder and into the gap between the insert support body and the insert cylinder can be reduced.

[0017] As described above, in this aspect, the resistance of the cooling air flowing through the flow path formed by the gap between the insert support body and the insert cylinder is increased, and the pressure of the cooling air flowing into the gap between the insert support body and the insert cylinder is reduced. This reduces the flow rate of cooling air leaking into the space on the outer periphery of the cylinder within the blade air passage. Therefore, in this aspect, it is possible to suppress a decrease in the impingement cooling effect on the passage defining surface that defines the blade air passage.

[0018] 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.

[0019] According to one aspect of the present disclosure, it is possible to restrict the movement of the insert tube in a direction perpendicular to the blade height direction, while allowing the thermal expansion difference between the insert and the blade body in the blade height direction, and suppress a decrease in the impingement cooling effect on the passage defining surface that defines the blade air passage.

[0020] 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 cross-sectional view of a main portion of a stator vane according to a fourth modified example according to the present disclosure; FIG. 14 is a perspective view of an insert support 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;

[0021] Hereinafter, an embodiment of the present disclosure and its modified examples will be described in detail with reference to the drawings.

[0022] Gas Turbine Embodiment An embodiment of a gas turbine will be described with reference to FIGS. 1 and 2. FIG.

[0023] 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.

[0024] 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.

[0025] The compressor 10 is disposed on the axial upstream side Dau relative to the turbine 30 .

[0026] 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.

[0027] 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.

[0028] 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.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] 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.

[0033] "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.

[0034] As shown in Figures 3 to 5, the stator vane 50 of this embodiment has a blade body 51, 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.

[0035] The blade body 51 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 50 is attached to the turbine casing 38, the blade height direction Dr becomes the radial direction Dr. The blade body 51 (36b) is disposed in a combustion gas flow path 39 (see FIG. 2 ) through which the combustion gas G flows. The inner shroud 60i is provided at the end of a second blade height side Dr, one of both sides of the blade body 51 in the blade height direction Dr. In other words, the inner shroud 60i is provided at the end of the radially inner side Dr of the blade body 51. The inner shroud 60i defines the edge of the radially inner side Dr of the annular combustion gas flow path 39. The outer shroud 60o is provided at the end of a first blade height side Dr, one of both sides of the blade body 51 in the blade height direction Dr. In other words, the outer shroud 60o is provided at the end of the radially outer side Dro of the blade body 51. The outer shroud 60o defines the edge of the radially outer side Dro of the annular combustion gas flow path 39. Note that, hereinafter, the blade height direction Dr will be referred to as the radial direction Dr. Also, 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.

[0036] The blade body 51 has a leading edge 52, a trailing edge 53, a pressure surface 55 connecting the leading edge 52 and the trailing edge 53, and a suction surface 54 connecting the leading edge 52 and the trailing edge 53 in a back-to-back relationship with the pressure surface 55. The leading edge 52, the trailing edge 53, the pressure surface 55, and the suction surface 54 all extend in the radial direction Dr. The leading edge is the end of the blade body 51 on the axial upstream side Dau. The trailing edge is the end of the blade body 51 on the axial downstream side Dad. The pressure surface 55 is a concave surface, and the suction surface 54 is a convex surface. The pressure surface 55 faces the circumferential pressure side Dcp, which is one side in the circumferential direction Dc. The suction surface 54 faces the circumferential suction side Dcn, which is the other side in the circumferential direction Dc.

[0037] As shown in Figures 4 and 5, the inner shroud (second shroud) 60i has an inner shroud main body (second shroud main body) 61i and a peripheral wall 65i. The inner shroud main body 61i extends in a direction perpendicular to the radial direction Dr from an end of the radially inner side Dri of the blade body 51. The inner shroud main body 61i has a gas path surface 64p facing the radially outer side Dro, a counter-gas path surface 64a facing the radially inner side Dri, a front end face 62f which is an end face on the axial upstream side Dau, a rear end face 62b which is an end face on the axial downstream side Dad, a pressure side end face 63p which is an end face on the circumferential pressure side Dcp, and a suction side end face 63n which is an end face on the circumferential suction side Dcn. The front end face 62f and the rear end face 62b are substantially parallel to each other. The positive pressure side end face 63p and the negative pressure side end face 63n are substantially parallel to each other. Therefore, the inner shroud body 61i has a parallelogram shape when viewed from the radial direction Dr.

[0038] The peripheral wall 65i protrudes radially inwardly Dri from the anti-gas path surface 64a of the inner shroud body 61i. The peripheral wall 65i is provided along the end face of the inner shroud body 61i. The peripheral wall 65i 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 61i. The rear wall 65b is provided along a rear end surface 62b of the inner shroud body 61i. The pressure side wall 65p is provided along a pressure side end surface 63p of the inner shroud body 61i. The suction side wall 65n is provided along a suction side end surface 63n of the inner shroud body 61i. The inner shroud 60i has a recess 66 formed by the inner shroud main body 61i and the peripheral wall 65i, the recess 66 being recessed toward the radially outer side Dro. The surface of the circumferential pressure side Dcp of the pressure side wall 65p is flush with the pressure side end face 63p of the inner shroud main body 61i. The surface of the circumferential suction side Dcn of the suction side wall 65n is flush with the suction side end face 63n of the inner shroud main body 61i. The rear wall 65b is formed along the rear end face 62b of the inner shroud main body 61i, but is located axially upstream Dau of the rear end face 62b.

[0039] 2 , a stator vane constituting one of the stator vane rows 35 is provided with a retainer 69 that protrudes radially inwardly Dri from the pressure side wall 65 p and the suction side wall 65 n of the inner shroud 60 i. This retainer 69 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 69 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 50 on the end of the radially outer side Dro of the inner cover 7.

[0040] 3 and 5, the outer shroud (first shroud) 60o has an outer shroud body (first shroud body) 61o, a peripheral wall 65o, front hooks 68f, and rear hooks 68b. The outer shroud body 61o extends in a direction perpendicular to the radial direction Dr from the end of the radially outer side Dro of the blade body 51. Like the inner shroud body 61i, the outer shroud body 61o also has a gas path surface 64p, an opposite gas path surface 64a, a front end surface 62f, a rear end surface 62b, a pressure side end surface 63p, and a suction side end surface 63n. Like the inner shroud body 61i, the outer shroud body 61o also has a parallelogram shape when viewed from the radial direction Dr. The gas path surface 64p of the inner shroud body 61i faces the radially outer side Dro, whereas the gas path surface 64p of the outer shroud body 61o faces the radially inner side Dri.

[0041] The peripheral wall 65o protrudes radially outward from the counter-gas path surface 64a of the outer shroud body 61o. The peripheral wall 65o is provided along the end face of the outer shroud body 61o. Like the peripheral wall 65i of the inner shroud 60i, the peripheral wall 65o of the outer shroud 60o 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 61o. The rear wall 65b is provided along a rear end face 62b of the outer shroud body 61o. The pressure side wall 65p is provided along a pressure side end face 63p of the outer shroud body 61o. The suction side wall 65n is provided along a suction side end face 63n of the outer shroud body 61o. In the outer shroud 60o, a recess 66 recessed toward the radially inward direction Dri is formed by the outer shroud main body 61o 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 face 63p of the outer shroud main body 61o. The surface of the circumferential suction side Dcn of the suction side wall 65n is flush with the suction side end face 63n of the outer shroud main body 61o.

[0042] 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 50 to the turbine casing 38.

[0043] As shown in Figures 3 and 5, the multiple blade air passages 56 include a first blade air passage 56a, a second blade air passage 56b, and a third blade air passage 56c. The first blade air passage 56a, 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 51 from the leading edge 52 side to the trailing edge 53 side of the blade body 51. The first blade air passage 56a, 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 56a penetrates the outer shroud body 61o, the blade body 51, and the inner shroud body 61i in the radial direction Dr. Therefore, the first blade air passage 56a opens at the radially outer end Dro and the radially inner end Dri. That is, the first blade air passage 56a has an outer opening 56ao, which is an opening at the end of the radially outer Dro, and an inner opening 56ai, which is an opening at the end of the radially inner Dri. The radially inner Dri end of the second blade air passage 56b opens at the anti-gas path surface 64a of the inner shroud body 61i. That is, the second blade air passage 56b has an inner opening 56bi, which is an opening at the end of the radially inner Dri. The radially outer Dro end of this second blade air passage 56b is closed by the outer shroud body 61o. The radially inner Dri end of the third blade air passage 56c is closed by the inner shroud body 61i, and the radially outer Dro end of this third blade air passage 56c is closed by the outer shroud body 61o. The radially outer Dro portion of the second blade air passage 56b and the radially outer Dro portion of the third blade air passage 56c are in communication with each other.

[0044] The first blade air passage 56a, the second blade air passage 56b, and the third blade air passage 56c are each defined by a plurality of passage defining surfaces. The plurality of leading-edge injection passages 59f penetrate from the passage defining surface of the first blade air passage 56a through the leading edge portion of the blade body 51 so that a portion of the cooling air AcI flowing through the first blade air passage 56a is injected from near the leading edge of the blade body 51 into the combustion gas flow path 39 (see FIG. 2) outside the blade body 51. The plurality of trailing-edge injection passages 59b penetrate from the passage defining surface of the third blade air passage 56c through the trailing edge portion of the blade body 51 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 body 51 into the combustion gas flow path 39 outside the blade body 51.

[0045] As shown in FIG. 5 , the stator vane 50 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 .

[0046] As shown in Figures 3 and 5, the outer impingement plate 95o is fixed to the outer shroud 60o. This outer impingement plate 95o is disposed in the recessed portion 66 of the outer shroud 60o and divides the recessed portion 66 of the outer shroud 60o 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 recessed portion 66 of the outer shroud 60o 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 counter-gas path surface 64a of the outer shroud main body 61o. The cooling air Ac1 that has impingement-cooled the anti-gas path surface 64a is injected to the outside of the outer shroud body 61o, for example, from the leading end surface 62f and / or the trailing end surface 62b of the outer shroud body 61o. The outer opening 56ao of the first blade air passage 56a is located radially outwardly 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 56a from this outer opening 56ao.

[0047] The blocking plates 90 are fixed to the inner shroud 60i. The blocking plates 90 are arranged at a distance radially inward Dri from the inner shroud main body 61i to separate the cooling air space in the recess 66 of the inner shroud 60i from a space radially inward Dri of the cooling air space. The blocking plates 90 include a front blocking plate 90f arranged on the axial upstream side Dau of the retainer 69 and a rear blocking plate 90b arranged on the axial downstream side Dad of the retainer 69.

[0048] The inner impingement plate 95i is disposed in the recess 66 of the inner shroud 60i 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.

[0049] The insert cylinder 70 has a cylindrical shape and is disposed in the first blade air passage 56a. The insert support 80 is fixed to the inner shroud body 61i so as to support the insert cylinder 70.

[0050] 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.

[0051] 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.

[0052] 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 64a of the inner shroud main body 61i, 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.

[0053] 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.

[0054] 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 56a (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 a thermal expansion difference in the radial direction Dr between the insert tube 70 and the blade body 51 can be tolerated.

[0055] 8 , the multiple passage-defining surfaces that define the first blade air passage 56a include a first passage-defining surface 57a that extends in the radial direction Dr, and a second passage-defining surface 57b that is connected to the first passage-defining surface 57a, extends in the radial direction Dr, and widens in a direction intersecting the first passage-defining surface 57a. The first passage-defining surface 57a faces the circumferential pressure side Dcp and defines the edge of the circumferential suction side Dcn of the first blade air passage 56a. The second passage-defining surface 57b faces the axial upstream side Dau and defines the edge of the axial downstream side Dad of the first blade air passage 56a.

[0056] 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 57a 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 57a. The second pressing portion 83b protrudes radially outward Dro from the support plate 81, is positioned closer to the second passage defining surface 57b 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 57b.

[0057] As shown in FIGS. 4 to 6 , the front blocking plate 90f has a passage facing portion 91 facing the first blade air passage 56a 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 60i. 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 69.

[0058] Next, the method for manufacturing the vane described above will be described with reference to the flowchart shown in FIG.

[0059] 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).

[0060] The vane body is formed by integrating the outer shroud 60o, the blade body 51, and the inner shroud 60i. This vane body is formed by, for example, casting.

[0061] 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 insert cylinder 70 on the radially outer side Dro is joined to the outer shroud body 61o by welding or the like.

[0062] 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.

[0063] Next, the outer impingement plate 95o is joined to the outer shroud 60o, and the inner impingement plate 95i is joined to the inner shroud 60i (impingement plate arrangement step S13).

[0064] Next, the blocking plate 90 is joined to the inner shroud 60i (blocking plate placement step S14).

[0065] This completes the production of the stator vane 50 in this embodiment. Note that the timing of placing the insert support body 80 so that the position restricting protrusion piece 82 of the insert support body 80 enters the protrusion piece insertion groove 76 of the insert tube 70, i.e., the timing of performing the placing step S12a, may be after the tube placing step S11 or before the tube placing step S11.

[0066] The flow of cooling air within the vane 50 will be described with reference to FIGS.

[0067] Cooling air Ac1 from the cooling device 40 described with reference to FIG. 2 flows into a space Dro radially outward of the outer impingement plate 95o within the recess 66 of the outer shroud 60o. 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 64a of the outer shroud main body 61o. The cooling air Ac1 that has impingement-cooled the anti-gas path surface 64a is ejected to the outside of the outer shroud main body 61o, for example, from the front end surface 62f and / or the rear end surface 62b of the outer shroud main body 61o. 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 56a.

[0068] 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 blocking plate 90 and the inner impingement plate 95i in the recess 66 of the inner shroud 60i. 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.

[0069] The cooling air Ac1 that has passed through the multiple impingement holes 71h of the cylindrical body 71 impingement cools the passage defining surface that defines the first blade air passage 56a. 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 51 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 51 into the combustion gas flow path 39 outside the blade body 51.

[0070] The cooling air Ac1 that has flowed into the second space S2 in the recess 66 of the inner shroud 60i passes through the multiple impingement holes 95h of the inner impingement plate 95i and impingement-cools the anti-gas path surface 64a of the inner shroud body 61i. The cooling air Ac1 that has impingement-cooled the anti-gas path surface 64a of the inner shroud body 61i 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 51.

[0071] The cooling air Ac1 then flows into the third blade air passage 56c and flows through the third blade air passage 56c toward the radially inward direction Dri. As the cooling air Ac1 flows through the third blade air passage 56c, it convectively cools the area around the third blade air passage 56c within the blade body 51. The cooling air Ac1 also flows into the multiple trailing edge injection passages 59b. The portion of the blade body 51 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 51 into the combustion gas flow path 39 outside the blade body 51.

[0072] In the present embodiment, as described above, the insert cylinder 70 is not joined to the insert support 80 so as to allow for the difference in thermal expansion between the insert cylinder 70 and the blade body 51 in the radial direction Dr. Therefore, a portion of the cooling air Ac1 that flows into the space radially inwardly Dri of the inner shroud body 61i may pass through the gap between the insert support 80 and the insert cylinder 70 and leak into the space on the outer circumferential side of the cylinder body 71 within the first blade air passage 56a. If the flow rate of the cooling air Ac1 that passes through the gap between the insert support 80 and the insert cylinder 70 and leaks into the space on the outer circumferential side of the cylinder body 71 within the first blade air passage 56a increases, the pressure difference between the space on the inner circumferential side of the cylinder body 71 and the space on the outer circumferential side of the cylinder body 71 decreases. Therefore, the speed of the cooling air Ac1 on the inner circumferential side of the cylinder body 71 when passing through the multiple impingement holes 71h in the cylinder body 71 decreases, and the impingement cooling effect on the passage defining surface that defines the first blade air passage 56a decreases.

[0073] 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.

[0074] 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.

[0075] 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 is increased, and the pressure of the cooling air Ac1 flowing into the gap between the insert support body 80 and the insert cylinder 70 is reduced. This makes it possible to reduce the flow rate of the cooling air Ac1 leaking into the space inside the first blade air passage 56a on the outer circumferential side of the cylinder body 71. 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 56a.

[0076] As described above, in the present embodiment, 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 57a, and the second contact surface 84b of the insert support 80 contacts the second passage-defining surface 57b. This allows the relative position of the insert support 80 with respect to the first blade air passage 56a 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 57a and the second passage-defining surface 57b, 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.

[0077] The outer shroud 60o, the blade body 51, and the inner shroud 60i are exposed to high-temperature combustion gas G. On the other hand, the blocking plate 90 joined to the inner shroud 60i 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 60i and the blocking plate 90. In this embodiment, even if a thermal expansion difference occurs between the inner shroud 60i 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 60i 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 60i and the blocking plate 90, the curved portion 93a in the outer circumferential portion 93 deforms, thereby reducing damage to the joint between the curved portion 93a in the outer circumferential portion 93 and the retainer 69.

[0078] Furthermore, in the present embodiment, the distance between the passage facing portion 91 and the inner shroud main body 61i is larger than the distance between at least a connecting portion with the transition portion 92 in the outer circumferential portion 93 and the inner shroud main body 61i. In the present embodiment, the distance between the passage facing portion 91 and the inner shroud main body 61i can be made larger than when the distance between the passage facing portion 91 and the inner shroud main body 61i is set to the distance between a connecting portion with the transition portion 92 in the outer circumferential portion 93 and the inner shroud main body 61i. Therefore, in the present embodiment, a pressure drop of the cooling air Ac1 that occurs when the cooling air Ac1 passes through the first blade air passage 56a and collides with the passage facing portion 91 of the blocking plate 90 can be suppressed. Therefore, in the present embodiment, the cooling air Ac1 that passes through the insert tube 70 in the first blade air passage 56a and flows into the recess 66 of the inner shroud 60i can be effectively used for cooling the inner shroud 60i, for example. Furthermore, in this embodiment, it is possible to prevent the blocking plate 90 from interfering with the end of the radially inner side Dri of the groove side wall portion (guide tube portion) 74 due to thermal expansion of a portion of the stator blade 50 .

[0079] 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.

[0080] 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.

[0081] 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 61i 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 71 within the first blade air passage 56a.

[0082] 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.

[0083] 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.

[0084] 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 66 of the inner shroud 60i. 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.

[0085] 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.

[0086] 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.

[0087] 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.

[0088] 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 inside the first blade air passage 56a on the outer circumferential side of the cylinder 71b. 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 56a.

[0089] In this modified example, too, the end of the radially inner Dri of the cylindrical body 71b that forms 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 end of the radially inner Dri of the cylindrical body 71b that forms the guide cylindrical portion due to thermal expansion of a portion of the stator blade 50.

[0090] 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.

[0091] 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.

[0092] 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.

[0093] 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 anti-gas path surface 64a of the inner shroud body 61i, 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.

[0094] 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.

[0095] The first pressing portion 83a protrudes radially outward from the support plate 81 Dro, is positioned closer to the first passage defining surface 57a (see FIG. 8) than the inner position limiting protrusion 82c and the outer position limiting protrusion 87 in the 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 57a. The second pressing portion 83b protrudes radially outward from the support plate 81 Dro, is positioned closer to the second passage defining surface 57b (see FIG. 8) than the inner position limiting protrusion 82c and the outer position limiting protrusion 87 in the 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 57b.

[0096] 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.

[0097] 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.

[0098] 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.

[0099] 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 reduces the flow rate of the cooling air Ac1 leaking into the space inside the first blade air passage 56a on the outer circumferential side of the cylinder body 71. 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 56a.

[0100] 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 50.

[0101] 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.

[0102] 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 64a of the inner shroud main body 61i, 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.

[0103] 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 57a 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 57a. 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 57b 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 57b.

[0104] 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.

[0105] In this modified example, even if the insert support body 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 64a of the inner shroud main body 61i. Therefore, in this modified example, the overlap amount between the cylindrical body 71 and the position limiting protrusion 82 in the radial direction Dri can be 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 64a of the inner shroud main body 61i.

[0106] 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.

[0107] 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 64a of the inner shroud main body 61i, 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.

[0108] 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.

[0109] 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.

[0110] Other Modifications The stator vane 50 in the above-described embodiment and each modification has three blade air passages 56. However, the stator vane 50 may have four or more blade air passages 56.

[0111] In the stator vane 50 in the above embodiment and each modified example, the insert tubes 70, 70b, 70c are arranged in the first blade air passage 56a, which is located on the most axially upstream side Dau, among 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 56a, which is located on the most axially upstream side Dau.

[0112] In the above-described embodiment and each modified example, the first passage-defining surface 57a defining the blade air passage 56 of the stator vane 50 faces the circumferential pressure side Dcp and defines the edge of the circumferential suction side Dcn of the first blade air passage 56a. Alternatively, the second passage-defining surface 57b faces the axial upstream side Dau and defines the edge of the axial downstream side Dad of the first blade air passage 56a. However, it is sufficient that both the first passage-defining surface 57a and the second passage-defining surface 57b extend in the radial direction Dr, and the second passage-defining surface 57b is connected to the first passage-defining surface 57a and extends in a direction intersecting the first passage-defining surface 57a. For example, suppose the first passage-defining surface 57a 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 57a and extends in a direction intersecting the first passage defining surface 57a, this passage defining surface may be the second passage defining surface 57b.

[0113] 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.

[0114] "Additional Notes" The stator vane 50 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 51 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 56a extending in the blade height direction Dr within the blade body 51 and allowing cooling air Ac1 to flow, a first shroud 60o provided at an end of a first blade height side Dro of the blade body 51 in the blade height direction Dr, a second shroud 60i provided at an end of a second blade height side Dri of the blade body 51 opposite to the first blade height side Dro, insert tubes 70, 70b, 70c at least partially disposed within the blade air passage 56a, and insert supports 80, 80a, 80c, 80d, 80e supporting the insert tubes 70, 70b, 70c. The first shroud 60o has a first shroud body 61o that extends in a direction perpendicular to the blade height direction Dr from an end of the blade height first side Dro of the blade body 51. The second shroud 60i has a second shroud body 61i that extends in a direction perpendicular to the blade height direction Dr from an end of the blade height second side Dri of the blade body 51. The blade air passage 56a penetrates the first shroud body 61o, the blade body 51, and the second shroud body 61i in the blade height direction Dr. The insert tubes 70, 70b, 70c each have a cylindrical shape extending in the blade height direction Dr, and include a cylindrical body 71, 71b that opens at an end of the blade height first side Dro and an end of the blade height second side Dri and has a plurality of impingement holes 71h that penetrate from the inner periphery to the outer periphery, and a flange portion 73, 73b, 73c that protrudes from an inner periphery of the cylindrical body 71, 71b toward the inner periphery of the cylindrical body 71, 71b from a position close to the blade height second side Dri on the inner periphery of the cylindrical body 71, 71b to narrow the air passage within the cylindrical body 71, 71b. The insert supports 80, 80a, 80c, 80d, 80e each have a support plate 81 that extends in a direction perpendicular to the blade height direction Dr and is fixed to the second shroud body 61i, and a position limiting protrusion 82, 82c that protrudes from the support plate 81 toward the blade height first side Dro. The support plate 81 has a support plate opening 81o that penetrates in the blade height direction Dr at a portion facing the inner peripheral side region of the cylindrical bodies 71, 71b in the blade height direction Dr.The position-limiting protrusions 82, 82c form a cylindrical shape protruding from the support plate 81 toward the blade height first side Dro around the entire opening edge of the support plate opening 81o, and face the inner or outer circumferential surface of the second side end portion 72 including the end of the blade height second side Dri in the cylindrical body 71, 71b, and regulate the relative position of the insert tubes 70, 70b, 70c in a direction perpendicular to the blade height direction Dr with respect to the insert supports 80, 80a, 80c, 80d, 80e. One of the insert tubes 70, 70b, 70c and the insert supports 80, 80a, 80c, 80d, 80e has groove bottoms 73, 75b, 81c that extend in a direction perpendicular to the blade height direction Dr, and groove side walls 74, 74b, 87 that protrude from the groove bottoms 73, 75b, 81c in the blade height direction Dr. When one of them is the insert tube 70, 70b, the groove side wall portion 74, 74b is cylindrical so as to face the second side end portion 72 of the cylindrical body 71, 71b at a distance around the entire circumference of the cylindrical body 71, 71b, and the groove bottom portion 73, 75b connects the cylindrical body 71, 71b and the groove side wall portion 74, 74b around the entire circumference of the cylindrical body 71, 71b, and the cylindrical body 71, 71b, the groove side wall portion 74, 74b and the groove bottom portion 73, 75b form annular protrusion insertion grooves 76, 76b into which the position regulating protrusion piece 82 is inserted. When the one of them is the insert support body 80c, the groove side wall portion 87 is cylindrical so as to face the position restricting protrusion piece 82c at an interval along the entire circumference of the cylindrical body 71, and the groove bottom portion 81c connects the position restricting protrusion piece 82c and the groove side wall portion 87 along the entire circumference of the cylindrical body 71, and the position restricting protrusion piece 82c, the groove side wall portion 87, and the groove bottom portion 81c form an annular cylindrical body insertion groove 89 into which the second side end portion 72 of the cylindrical body 71 is inserted. The insert cylinders 70, 70b, 70c are engaged with the insert supports 80, 80a, 80c, 80d, 80e so as to be relatively movable.

[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 annular position-limiting protrusions 82, 82c of the insert supports 80, 80a, 80c, 80d, 80e fixed to the second shroud body 61i face the inner or outer circumferential surfaces of the cylindrical bodies 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 second side end portions 72 of the insert tubes 70, 70b, 70c can move in the blade height direction Dr relative to the blade body 51. Therefore, in this embodiment, a thermal expansion difference between the insert tubes 70, 70b, 70c and the blade body 51 in the blade height direction Dr can be tolerated.

[0116] In this embodiment, the cooling air Ac1 present on the blade height first side Dro relative to the first shroud body 61o flows into the cylinders 71, 71b of the insert cylinders 70, 70b, 70c arranged in the blade air passage 56a. The cooling air Ac1 that has flowed into the cylinders 71, 71b flows within the cylinders 71, 71b toward the blade height second 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 blade height second side Dri relative to the second shroud body 61i. The cooling air Ac1 that has passed through the multiple impingement holes 71h in the cylinders 71, 71b impingement cools the passage defining surfaces that define the blade air passage 56a.

[0117] In this embodiment, the insert tubes 70, 70b, 70c are engaged with the insert supports 80, 80a, 80c, 80d, 80e so as to be able to move relatively to each other so as to allow for the difference in thermal expansion between the insert tubes 70, 70b, 70c and the blade body 51 in the blade height direction Dr. As a result, there is a possibility that part of the cooling air Ac1 that flows into the space on the second blade height side Dri of the second shroud body 61i through the support plate opening 81o may leak out into the space inside the blade air passage 56a on the outer periphery of the cylinder bodies 71, 71b through the gap between the insert supports 80, 80a, 80c, 80d, 80e and the insert tubes 70, 70b, 70c. If the flow rate of the cooling air Ac1 leaking into the space on the outer periphery of the cylinder 71, 71 b within the blade air passage 56 a through the gaps between the insert supports 80, 80 a, 80 c, 80 d, 80 e and the insert cylinders 70, 70 b, 70 c increases, the pressure difference between the space on the inner periphery of the cylinder 71, 71 b and the space on the outer periphery of the cylinder 71, 71 b decreases. As a result, the speed of the cooling air Ac1 on the inner periphery of the cylinder 71, 71 b when passing through the multiple impingement holes 71 h in the cylinder 71, 71 b decreases, and the impingement cooling effect on the passage defining surfaces that define the blade air passage 56 a decreases.

[0118] In this embodiment, when one of the two is the insert tube 70, 70b, the gap between the insert support 80, 80a, 80d, 80e and the insert tube 70, 70b is the gap between the protrusion insertion groove 76, 76b and the position limiting protrusion 82 inserted into this groove 76, 76b. Therefore, the flow path of the cooling air Ac1 formed by this gap is a flow path that undulates and bends in the blade height direction Dr. Also, in this embodiment, when the other is the insert support 80c, the gap is the gap between the cylinder body insertion groove 89 and the second side end 72 of the cylinder 71 inserted into this groove 89. Therefore, the flow path of the cooling air Ac1 formed by this gap is also a flow path that undulates and bends in the blade height 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 80, 80a, 80c, 80d, 80e and the insert tube 70, 70b, 70c is large. In particular, the resistance of the cooling air Ac1 increases at the corners of this flow path.

[0119] In addition, in this aspect, the flanges 73, 73b, and 73c that narrow the air passages in the cylindrical bodies 71 and 71b are provided in the cylindrical bodies 71 and 71b, so that the pressure of the cooling air Ac1 that passes through the flanges 73, 73b, and 73c in the cylindrical bodies 71 and 71b can be reduced. Therefore, in this aspect, the pressure of the cooling air Ac1 that flows out of the cylindrical bodies 71 and 71b and into the gaps between the insert supports 80, 80a, 80c, 80d, and 80e and the insert cylinders 70, 70b, and 70c can be reduced.

[0120] As described above, in this embodiment, the resistance of the cooling air Ac1 flowing through the flow passage formed by the gaps between the insert supports 80, 80a, 80c, 80d, 80e and the insert cylinders 70, 70b, 70c is increased, and the pressure of the cooling air Ac1 flowing into the gaps between the insert supports 80, 80a, 80c, 80d, 80e and the insert cylinders 70, 70b, 70c is reduced. This reduces the flow rate of the cooling air Ac1 leaking into the space outside the cylinders 71, 71b within the blade air passage 56a. Therefore, in this embodiment, it is possible to suppress a decrease in the impingement cooling effect on the passage defining surfaces that define the blade air passage 56a.

[0121] (2) A stator vane according to a second aspect is the stator vane 50 according to the first aspect, wherein the one of the two is the insert cylinder 70. The position restricting protrusion 82 of the insert support body 80, 80a, 80d, 80e is located on the inner circumferential side of the cylindrical body 71 and faces the inner circumferential surface of the cylindrical body 71. The flange 73 of the insert cylinder 70 forms the groove bottom. The groove side wall 74 extends from the inner circumferential edge of the flange 73 forming the groove bottom to the second blade height side Dri so that the position restricting protrusion 82 is located between the cylindrical body 71 and the flange 73. The cylindrical body 71, the groove side wall 74, and the flange 73 forming the groove bottom form a protrusion insertion groove 76.

[0122] In this embodiment, in which the insert tube 70 has the groove side wall portion 74 and the groove bottom portion 73, the gap between the insert supports 80, 80a, 80c, 80d, 80e and the insert tube 70 is the gap between the protrusion insertion groove 76 and the position regulating protrusion 82 inserted in 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 blade height direction Dr. Therefore, in this embodiment as well, the resistance of the cooling air Ac1 flowing through the flow path formed by the gap between the insert supports 80, 80a, 80c, 80d, 80e and the insert tube 70 is large.

[0123] (3) In the third aspect, the stator vane is such that, in the stator vane 50 in the second aspect, the end of the groove side wall portion 74 on the second blade height side Dri is positioned closer to the second blade height side Dri than the support plate 81.

[0124] The cooling air Ac1 that has flowed into the cylindrical body 71 of the insert cylinder 70 passes through the inner peripheral side of a cylindrical groove side wall portion 74 that is arranged on the inner peripheral side of the cylindrical body 71. Therefore, when the end of the groove side wall portion 74 on the second blade height side Dri is located on the second blade height side Dri higher than the support plate 81, the pressure of the cooling air Ac1 that has passed through the inner peripheral side of the cylindrical groove side wall portion 74 can be reduced.

[0125] (4) A stator vane according to a fourth aspect includes, in the stator vane 50 according to the second aspect, a blocking plate 90 and an impingement plate 95i fixed to the second shroud 60i. The second shroud 60i has a peripheral wall 65i protruding from an outer circumferential edge of the second shroud body 61i toward the blade height second side Dri. The second shroud body 61i and the peripheral wall 65i cooperate to form a recess 66 on the blade height second side Dri of the second shroud body 61i that is recessed toward the blade height first side Dro. The blocking plate 90 is disposed at a distance from the second shroud body 61i on the blade height second side Dri, and separates the cooling air space within the recess 66 from a space on the blade height second side Dri beyond the cooling air space. The impingement plate 95i divides the cooling air space 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 has a plurality of impingement holes 95h formed therein that penetrate from the second space S2 to the first space S1. An end of the groove side wall portion 74 on the blade height second side Dri is positioned closer to the blade height second side Dro than the impingement plate 95i and closer to the blade height first side Dro than the blocking plate 90.

[0126] In this aspect, a portion of the cooling air Ac1 that flows into the inner peripheral side of the cylindrical body 71 of the insert cylinder 70 passes through the inner peripheral side of the cylindrical groove side wall portion 74 that is disposed on the inner peripheral side of the cylindrical body 71 and flows into the second space S2 in the recess 66 of the second shroud 60i. The cooling air Ac1 that flows into the second space S2 passes through the multiple impingement holes 95h of the impingement plate 95i and impingement-cools the second shroud body 61i. Thus, in this aspect, the second shroud body 61i can be cooled by a portion of the cooling air Ac1 that was present on the first blade height side Dro of the first shroud body 61o.

[0127] (5) A stator vane according to a fifth aspect is the stator vane 50 according to the third or fourth aspect, wherein the insert support 80a has a throttle opening 85o through which the annular groove side wall portion 74 is inserted, and has a throttle ring 85 fixed to a surface of the support plate 81 facing the second blade height side Dri. An average distance d2 between the throttle opening 85o and the annular groove side wall portion 74 is narrower than an 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.

[0128] In this aspect, because the average distance d2 is narrower than the average distance d1, resistance to the cooling air Ac1 increases, and it is possible to reduce the flow rate of the cooling air Ac1 in the space on the second blade height side Dri relative to the second shroud body 61i that flows into the gap between the insert support body 80a and the insert cylinder 70. Therefore, in this aspect, 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 71 within the blade air passage 56a.

[0129] (6) A stator vane according to a sixth aspect is the stator vane 50 according to the first aspect, wherein the one of the two is the insert cylinder 70b. The position restricting protrusion 82 of the insert support 80 is located on the outer circumferential side of the cylindrical body 71b and faces the outer circumferential surface of the cylindrical body 71b. The groove bottom 75b extends outer circumferentially from the outer circumferential surface of the cylindrical body 71b. The groove side wall 74b extends from the outer circumferential edge of the groove bottom 75b toward the second blade height side Dri so that the position restricting protrusion 82 is located between the cylindrical body 71b and the groove side wall 74b. The cylindrical body 71b, the groove side wall 74b, and the groove bottom 75b form the protrusion insertion groove 76b.

[0130] In this embodiment, in which the insert tube 70b has the groove side wall portion 74b and the groove bottom portion 75b, 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 portion 82 inserted in this groove 76b. Therefore, the flow path of the cooling air Ac1 formed by this gap is a flow path that undulates and bends in the blade height direction Dr. Therefore, in this embodiment as well, 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. In particular, the resistance of the cooling air Ac1 is large at the corners of this flow path.

[0131] (7) A seventh aspect of the stator vane is the stator vane 50 of the first aspect, wherein the one of the two is the insert support body 80c. The position limiting protrusion 82c of the insert support body 80c is located on the inner circumferential side of the cylindrical body 71 and forms an inner position limiting protrusion 82c facing the inner circumferential surface of the cylindrical body 71. The groove side wall portion 87 protrudes from the support plate 81 toward the blade height first side Dro around the entire circumference of the opening edge of the support plate opening 81o and forms an outer position limiting protrusion 87 located on the outer circumferential side of the cylindrical body 71 and facing the outer circumferential surface of the cylindrical body 71. The groove bottom portion 81c is a portion of the support plate 81 that is located between the inner position limiting protrusion 82c and the outer position limiting protrusion 87. The inner position limiting protrusion 82c, the outer position limiting protrusion 87, and the groove bottom portion 81c form an annular cylindrical body insertion groove 89.

[0132] In this embodiment, in which the insert support 80c has the groove side wall portion 87 and the groove bottom portion 81c, the gap between the insert support 80c and the insert cylinder 70c becomes the gap between the cylinder insertion groove 89 and 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 blade height direction Dr. Therefore, in this embodiment as well, the resistance of the cooling air Ac1 flowing through the flow path formed by the gap between the insert support 80c and the insert cylinder 70c becomes large.

[0133] (8) The stator vane in an eighth aspect is the stator vane 50 in any one of the first to seventh aspects, wherein the projected area of ​​the flange portion 73 in the blade height direction Dr is equal to or greater than half of the area of ​​the air flow path in the cylindrical body 71 in a direction perpendicular to the blade height direction Dr.

[0134] In this embodiment, the pressure of the cooling air Ac1 that has passed through the flanges 73, 73b, and 73c inside the cylindrical bodies 71 and 71b can be reduced. Therefore, in this embodiment, the pressure of the cooling air Ac1 that flows out of the cylindrical bodies 71 and 71b and into the gaps between the insert supports 80, 80a, 80c, 80d, and 80e and the insert cylinders 70, 70b, and 70c can be reduced. Therefore, in this embodiment, the flow rate of the cooling air Ac1 that leaks from these gaps can be reduced.

[0135] (9) A stator vane in a ninth aspect is a stator vane 50 in any one of the first to eighth aspects, wherein the blade air passage 56a is defined by a plurality of passage defining surfaces including a first passage defining surface 57a extending in the blade height direction Dr and a second passage defining surface 57b connected to the first passage defining surface 57a, extending in the blade height direction Dr, and widening in a direction intersecting the first passage defining surface 57a. The insert supports 80, 80a, 80c, 80d, 80e include first pressing portions 83a, 83da, 83ea that protrude from the support plate 81 toward the first blade height side Dro, are positioned closer to the first passage defining surface 57a than the position limiting 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 first blade height side Dro, are positioned closer to the second passage defining surface 57b than the position limiting 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. The support plate 81 is joined to the second shroud body 61i at its outer circumferential edge.

[0136] In this aspect, the position limiting protrusions 82, 82c of the insert supports 80, 80a, 80c, 80d, 80e can limit 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 position of the insert supports 80, 80a, 80c, 80d, 80e with respect to the blade air passage 56a in a direction perpendicular to the blade height direction Dr can be accurately determined. Therefore, in this aspect, the distance from the outer peripheral surface of the cylindrical body 71, 71 b of the insert cylinder 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 passage defining surfaces that define the blade air passage 56 a by the cooling air Ac1 ejected from the plurality of impingement holes 71 h of the cylindrical body 71, 71 b can be appropriately managed.

[0137] (10) A stator vane according to a tenth aspect is a stator vane 50 according to any one of the first to fifth, seventh and eighth aspects, wherein the blade air passage 56a is defined by a plurality of passage defining surfaces including a first passage defining surface 57a extending in the blade height direction Dr and a second passage defining surface 57b connected to the first passage defining surface 57a, extending in the blade height direction Dr and widening in a direction intersecting with the first passage defining surface 57a. The insert supports 80d, 80e include first pressing portions 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 limiting protrusion 82 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 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 limiting protrusion 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. The support plate 81 is joined to the second shroud body 61i at its outer peripheral edge. The position limiting protrusion 82 is positioned 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 restricting protrusion 82 and the first pressing portions 83da, 83ea, recessed toward the second blade height side Dri and into which an end of the second blade height side Dri of the cylindrical body 71 fits. A second groove 86b is formed between the position restricting protrusion 82 and the second pressing portions 83db, 83eb, recessed toward the second blade height side Dri and into which an end of the second blade height side Dri of the cylindrical body 71 fits.

[0138] In this aspect, similar to the stator vane 50 in the eighth aspect, it is possible to accurately set the distance from the outer peripheral surface of the cylindrical body 71 to the plurality of passage defining surfaces, including the first passage defining surface 57 a and the second passage defining surface 57 b, to a target distance. Therefore, in this aspect, it is possible to appropriately manage 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 body 71.

[0139] Furthermore, 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 position of the end of the blade height second side Dri of the cylindrical body 71 can be brought closer to the position of the opposite gas path surface 64a of the second shroud main body 61i by inserting the end of the blade height second side Dri of the cylindrical body 71 into the first groove 86a and the second groove 86b. Therefore, in this aspect, the position of the impingement hole 71h formed closest to the blade height second side Dri in the cylindrical body 71 can be brought closer to the position of the opposite gas path surface 64a of the second shroud main body 61i while maintaining the amount of overlap between the cylindrical body 71 and the position limiting protrusion 82 in the blade height direction Dr.

[0140] (11) A stator vane according to an eleventh aspect is the stator vane 50 according to the tenth aspect, wherein the second pressing portion 83 eb is spaced apart from the first pressing portion 83 ea.

[0141] In this embodiment, the first groove 86a and the second groove 86b can be easily formed.

[0142] (12) A twelfth aspect of the present invention relates to the stator vane 50 of any one of the first to third aspects and the sixth to eighth aspects, and further includes a blocking plate 90 fixed to the second shroud 60i. The second shroud 60i has a peripheral wall 65i protruding from an outer circumferential edge of the second shroud body 61i toward the blade height second side Dri. The second shroud body 61i and the peripheral wall 65i cooperate to form a recess 66 recessed toward the blade height first side Dro on the blade height second side Dri of the second shroud body 61i. The blocking plate 90 is disposed at a distance from the second shroud body 61i on the blade height second side Dri, and separates a cooling air space within the recess 66 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 56a 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 65i. The passage opposing portion 91 is located on the second blade height side Dri with respect to a connection portion between the passage opposing portion 91 and 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.

[0143] The first shroud 60o, the blade body 51, and the second shroud 60i are exposed to high-temperature combustion gas. On the other hand, the blocking plate 90 joined to the second shroud 60i 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 60i and the blocking plate 90. In this embodiment, even if a thermal expansion difference occurs between the second shroud 60i and the blocking plate 90, the connecting portion between the passage opposing portion 91 and the transition portion 92 and the connecting portion between the transition portion 92 and the outer peripheral portion 93 deforms, allowing the blocking plate 90 to easily accommodate this thermal expansion difference. Therefore, in this embodiment, damage to the connecting portion between the second shroud 60i and the blocking plate 90 and to the blocking plate 90 can be suppressed.

[0144] Furthermore, in this aspect, the distance between the passage facing portion 91 and the second shroud body 61i is larger than the distance between at least a connecting portion with the transition portion 92 in the outer circumferential portion 93 and the second shroud body 61i. In this aspect, the distance between the passage facing portion 91 and the second shroud body 61i can be made larger than when the distance between the passage facing portion 91 and the second shroud body 61i is adjusted to the distance between a connecting portion with the transition portion 92 in the outer circumferential portion 93 and the second shroud body 61i. Therefore, in this aspect, a pressure drop of the cooling air Ac1 passing through the blade air passage 56a due to collision with the passage facing portion 91 of the blocking plate 90 can be suppressed. Therefore, in this aspect, the cooling air Ac1 passing through the blade air passage 56a and flowing into the recess 66 of the second shroud 60i can be effectively used for cooling the second shroud 60i, etc. Furthermore, in this embodiment, when the end of the second blade height side Dri of the groove side wall portion 74 is positioned on the second blade height side Dri higher than the impingement plate 95i, even if a difference in thermal expansion occurs in the blade height direction Dr between the insert tubes 70, 70b and the blade body 51, contact between the groove side wall portion 74 and the blocking plate 90 can be avoided.

[0145] (13) A stator vane according to a thirteenth aspect is the stator vane 50 according to the twelfth aspect, wherein the outer peripheral 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.

[0146] In this aspect, even if a thermal expansion difference occurs between the second shroud 60i and the blocking plate 90, the connecting portion between the passage opposing 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 60i and the blocking plate 90 and to the blocking plate 90 can be suppressed.

[0147] (14) A fourteenth aspect of the stator vane is the stator vane 50 of the thirteenth aspect, wherein the blade body 51 has a leading edge 52, a trailing edge 53, a pressure surface 55 connecting the leading edge 52 and the trailing edge 53, and a suction surface 54 connecting the leading edge 52 and the trailing edge 53 in a back-to-back relationship with the pressure surface 55. The second shroud 60i has a retainer 69 connected to the peripheral wall 65i. The peripheral wall 65i of the second shroud 60i has a pressure side wall 65p located on a pressure side Dcp where the pressure surface 55 is located relative to the suction surface 54, with respect to the blade body 51, and a suction side wall 65n located on a suction side Dcn opposite the pressure side Dcp, with respect to the blade body 51. The retainer 69 is connected to the pressure side wall 65p and the suction side wall 65n. The curved portion 93 a is joined to the retainer 69 .

[0148] In this embodiment, the deformation of the curved portion 93 a can prevent damage to the joint portion between the curved portion 93 a in the outer circumferential portion 93 and the retainer 69 .

[0149] The gas turbines in the above embodiments and modified examples can be understood, for example, as follows: (15) A gas turbine in a fifteenth aspect includes the stator vane 50 in any one of the first to fourteenth aspects, a rotor 31 rotatable about an axis Ar, and a turbine casing 38 covering the rotor 31. The stator vane 50 is attached to the inside of the turbine casing 38 so that the blade height direction Dr is the radial direction Dr relative to the axis Ar.

[0150] According to one aspect of the present disclosure, it is possible to restrict the movement of the insert tube in a direction perpendicular to the blade height direction, while allowing the thermal expansion difference between the insert and the blade body in the blade height direction, and suppress a decrease in the impingement cooling effect on the passage defining surface that defines the blade air passage.

[0151] 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 cylinder 71: Cylinder 71b: Cylinder (or guide cylinder portion) 71h: Impingement hole 72: Radially inner end portion (or second side end portion) 73: Flange portion (or groove bottom portion) 73b, 73c: Flange portion 74: Groove side wall portion (or guide cylinder portion) 74b: Groove side wall portion 75b: Groove bottom portion 76, 76b: Projection piece insertion groove 80, 80a, 80c, 80d, 80e: 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 body in the blade height direction 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; an insert tube at least a part of which is disposed within the blade air passage; and an insert support for supporting the insert tube, wherein the first shroud has a first shroud body extending from the end of the blade body on the first blade height side in a direction perpendicular to the blade height direction, and the second shroud has a second shroud body extending from the end of the blade body on the second blade height side in a direction perpendicular to the blade height direction, and the blade air passage penetrates the first shroud body, the blade body, and the second shroud body in the blade height direction, The insert tube has a cylindrical shape extending in the blade height direction, an opening at each of the blade height first end and the blade height second end, and a plurality of impingement holes penetrating from the inner peripheral side to the outer peripheral side, and a flange portion protruding from a position on the inner peripheral surface of the cylinder closer to the blade height second side toward the inner peripheral side of the cylinder to narrow the air passage within the cylinder, the insert support body has a support plate extending in a direction perpendicular to the blade height direction and fixed to the second shroud main body, and a position regulating protruding piece protruding from the support plate to the blade height first side, the support plate has a support plate opening penetrating in the blade height direction at a portion facing the inner peripheral region of the cylinder in the blade height direction, The position regulating protrusion piece protrudes from the support plate toward the first wing height side around the entire opening edge of the support plate opening, forms a cylindrical shape, faces the inner or outer circumferential surface of a second side end portion including the end on the second wing height side in the cylindrical body, and regulates the relative position of the insert tube in a direction perpendicular to the wing height direction with respect to the insert support body; one of the insert tube and the insert support body has a groove bottom portion extending in a direction perpendicular to the wing height direction, and a groove side wall portion protruding in the wing height direction from the groove bottom portion;when the one of them is the insert tube, the groove side wall portion is tubular so as to face the second side end of the cylinder with a gap over the entire circumference of the cylinder, and the groove bottom portion connects the cylinder and the groove side wall portion over the entire circumference of the cylinder, so that the cylinder, the groove side wall portion and the groove bottom form an annular protrusion insertion groove into which the position regulating protrusion piece is inserted; when the one of them is the insert support body, the groove side wall portion is tubular so as to face the position regulating protrusion piece with a gap over the entire circumference of the cylinder, and the groove bottom portion connects the position regulating protrusion piece and the groove side wall portion over the entire circumference of the cylinder, so that the position regulating protrusion piece, the groove side wall portion and the groove bottom form an annular cylinder insertion groove into which the second side end of the cylinder is inserted; and the insert tube is engaged with the insert support body so as to be movable relatively to the insert support body.

2. A vane according to claim 1, wherein the one of the two is the insert tube, the position regulating protrusion of the insert support is located on the inner periphery of the cylindrical body and faces the inner periphery of the cylindrical body, the flange of the insert tube forms the groove bottom, and the groove side wall extends from the inner periphery edge of the flange forming the groove bottom to the second blade height side so that the position regulating protrusion is located between the cylindrical body and the groove side wall, and a protrusion insertion groove is formed by the cylindrical body, the groove side wall and the flange forming the groove bottom.

3. A stator vane according to claim 2, wherein an end of said groove side wall portion on said second blade height side is located on said second blade height side relative to said support plate.

4. A vane according to claim 2, comprising a blocking plate and an impingement plate fixed to the second shroud, the second shroud having 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 jointly forming a recess on the second blade height side of the second shroud body that is recessed toward the first blade height side, the blocking plate being disposed at a distance on the second blade height side relative to the second shroud body and separating a cooling air space within the recess from a space on the second blade height side of the cooling air space, the impingement plate separating the cooling air space into a first space on the first blade height side and a second space on the second blade height side, and a plurality of impingement holes penetrating from the second space to the first space are formed, and an end on the second blade height side of the groove side wall portion is located on the second blade height side of the impingement plate and on the first blade height side of the blocking plate.

5. A vane as described in claim 3, wherein the insert support has a throttle opening through which the annular groove side wall portion is inserted, and has a throttle ring fixed to a surface of the support plate facing the second blade height side, and the average distance between the throttle opening and the annular groove side wall portion is narrower than the average distance between the annular position regulating protrusion of the insert support and the annular groove side wall portion of the insert tube.

6. A vane according to claim 1, wherein the one of the two is the insert tube, the position regulating protrusion of the insert support is located on the outer periphery of the tube and faces the outer periphery of the tube, the groove bottom extends outer periphery from the outer periphery of the tube, and the groove side wall extends from the outer periphery edge of the groove bottom to the second blade height side so that the position regulating protrusion is located between the tube and the groove side wall, and the tube, the groove side wall and the groove bottom form the protrusion insertion groove.

7. A vane as claimed in claim 1, wherein the one of the vanes is the insert support, the position control protrusion of the insert support is an inner position control protrusion located on the inner peripheral side of the cylinder and facing the inner peripheral surface of the cylinder, the groove side wall protrudes from the support plate towards the first blade height side around the entire circumference of the opening edge of the support plate opening and forms an outer position control protrusion located on the outer peripheral side of the cylinder and facing the outer peripheral surface of the cylinder, the groove bottom is a portion of the support plate located between the inner position control protrusion and the outer position control protrusion, and the inner position control protrusion, the outer position control protrusion and the groove bottom form a ring-shaped cylinder insertion groove.

8. A stator vane as claimed in claim 1, wherein the projected area of ​​said flange portion in the blade height direction is at least half the area of ​​the air flow passage within said tubular body in a direction perpendicular to said blade height direction.

9. A vane according to any one of claims 1 to 8, 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, the insert support comprising: 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 relative to 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 relative to the position restricting protrusion in a direction perpendicular to the blade height direction and having a second contact surface in contact with the second passage defining surface, and the support plate is joined to the second shroud body at an outer circumferential edge of the support plate.

10. A vane according to any one of claims 1 to 5, 7 and 8, 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, the insert support has: 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 relative to 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 relative to the position restricting protrusion in a direction perpendicular to the blade height direction, and having a second contact surface in contact with the second passage defining surface, the support plate being joined to the second shroud body at an outer circumferential edge of the support plate, the position limiting 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 limiting 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 limiting 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.

11. A vane according to claim 10, wherein the second pressing portion is spaced apart from the first pressing portion.

12. A vane according to any one of claims 1 to 3 and 6 to 8, further comprising a blocking plate fixed to the second shroud, the second shroud having 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 together form a recess recessed toward the first blade height side on the second blade height side of the second shroud body, the blocking plate is disposed at a distance from the second blade height side relative to the second shroud body 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 having a passage opposing portion opposing the blade air passage in the blade height direction, a transition portion connected around the passage opposing portion, and an outer periphery portion connected around the transition portion and at least a portion of which is joined to the peripheral wall, the passage opposing portion being located on the second blade height side of the outer periphery portion relative to a connection portion with the transition 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 circumferential portion.

13. A vane according to claim 12, wherein the outer circumferential portion has a curved portion that gradually approaches the second blade height side as it moves away from the passage opposing portion in a direction perpendicular to the blade height direction.

14. A vane as claimed in claim 13, 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.

15. A gas turbine comprising: a stator vane according to any one of claims 1 to 8; a rotor rotatable about an axis; and a turbine casing covering the rotor, wherein the stator vane is attached to the inside of the turbine casing such that the blade height direction is radial to the axis.

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