Insert support body, stationary blade, gas turbine with this stationary blade, and method for manufacturing stationary blade

Abstract

To appropriately manage the impingement cooling performance of passage-defining surfaces that define a blade air passage.SOLUTION: A blade air passage of a stationary blade is defined by multiple passage-defining surfaces including a first passage-defining surface and a second passage-defining surface, which is connected to the first passage-defining surface and extends in a direction intersecting the first passage-defining surface. A cylindrical body of an impingement tube in which multiple impingement holes penetrating from an inner peripheral side to an outer peripheral side are formed is disposed in the blade air passage. This insert support body includes: a support plate; a position-regulating protrusion piece capable of facing an inner peripheral surface of a second-side end part in the cylindrical body; a first pressing part that is positioned closer to the first passage-defining surface than the position-regulating protrusion piece in a direction perpendicular to the blade height direction, and has a first contact surface capable of contacting the first passage-defining surface; and a second pressing part that is positioned closer to the second passage-defining surface than the position-regulating protrusion piece in the direction perpendicular to the blade height direction, and has a second contact surface capable of contacting the second passage-defining surface.SELECTED DRAWING: Figure 10

Description

Technical Field

[0001] The present disclosure relates to an insert support capable of supporting an insert cylinder disposed in a blade cooling air passage, a stator blade, a gas turbine including the stator blade, a method for manufacturing the stator blade, and a gas turbine including the same.

Background Art

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

[0003] Patent Document 1 below discloses a stationary blade of a gas turbine. This stationary blade has a blade body extending in the radial direction with respect to the axis, an outer shroud provided on the radially outer side of the blade body, an inner shroud provided on the radially inner side of the blade body, and a blade air passage. The blade body of the stationary blade is disposed in a combustion gas flow path through which combustion gas passes. The outer shroud has an outer shroud body that extends in a direction perpendicular to the radial direction in which the blade body extends and defines the radially outer edge of the combustion gas flow path. The inner shroud also has an inner shroud body that extends in a direction perpendicular to the radial direction in which the blade body extends and defines the radially inner edge of the combustion gas flow path. The blade air passage penetrates the outer shroud body, the blade body, and the inner shroud body in the radial direction. This stationary blade further has an insert (or insert cylinder) disposed in the blade air passage and a holding member (or insert support) that supports this insert. The insert has a cylindrical body that extends in the radial direction and forms a cylindrical shape. A plurality of impingement holes penetrating from the inner peripheral side to the outer peripheral side are formed in this cylindrical body. The holding member extends in a direction perpendicular to the direction in which the cylindrical body extends, and has a support plate fixed to the outer shroud body and a positioning portion (protruding piece) that protrudes radially outward from the support plate and faces the inner peripheral surface of the cylindrical body. By this positioning portion, the relative position of the insert in the direction perpendicular to the radial direction with respect to the holding member is regulated. On the other hand, the radially inner end of the insert is movable in the radial direction with respect to the holding member in order to allow for the difference in thermal expansion in the radial direction between the insert and the blade body. The cooling air present on the inner peripheral side of the insert collides with the passage defining surface that defines the blade air passage through the plurality of impingement holes of the insert. Therefore, this passage defining surface is impingement cooled by the cooling air that has passed through the plurality of impingement holes of the insert.

Prior Art Documents

Patent Documents

[0004]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0005] When an insert cylinder is arranged in the blade air passage like the stator blade described in Patent Document 2, it is desirable to appropriately manage the impingement cooling performance of the passage defining surface that defines this blade air passage.

[0006] Therefore, an object of the present disclosure is to provide an insert support, a stator blade, a gas turbine including this stator blade, and a method for manufacturing a stator blade that can appropriately manage the impingement cooling performance of the passage defining surface that defines the blade air passage.

Means for Solving the Problems

[0007] An insert support as an aspect of the invention for achieving the above object is a blade body having a cross section forming an airfoil shape and extending in the blade height direction having a direction component perpendicular to the cross section, a blade air passage extending in the blade height direction inside the blade body through which cooling air can flow, a first shroud provided at an end on the first side of the blade height in the blade height direction of the blade body, a second shroud provided at an end on the second side of the blade height opposite to the first side of the blade height of the blade body, and an insert cylinder arranged in the blade air passage. It is an insert support of a stator blade. The first shroud has a first shroud body that extends in a direction perpendicular to the blade height direction from the end on the first side of the blade height of the blade body. The second shroud has a second shroud body that extends in a direction perpendicular to the blade height direction from the end on the second side of the blade height of the blade body. The blade air passage penetrates the first shroud body, the blade body, and the second shroud body in the blade height direction. 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 spreading in a direction intersecting the first passage defining surface. The insert cylinder has a cylindrical body that extends in the blade height direction and forms a cylindrical shape, and a plurality of impinge holes are formed that penetrate from the inner peripheral side to the outer peripheral side. The insert support has a support plate that extends in a direction perpendicular to the blade height direction, a cylindrical portion that protrudes from the support plate to the first side of the blade height and forms a cylindrical shape, and a position regulating protrusion piece that can face the inner peripheral surface or the outer peripheral surface of the second side end portion including the end on the second side of the blade height in the cylindrical body. The insert support further has a first pressing portion that protrudes from the support plate to the first side of the blade height, is located on the side of the first passage defining surface rather than the position regulating protrusion piece in a direction perpendicular to the blade height direction, and has a first contact surface that can contact the first passage defining surface. The insert support also has a second pressing portion that protrudes from the support plate to the first side of the blade height, is located on the side of the second passage defining surface rather than the position regulating protrusion piece in a direction perpendicular to the blade height direction, and has a second contact surface that can contact the second passage defining surface. The support plate can be joined to the second shroud body at the outer peripheral edge of the support plate.

[0008] In this embodiment, the relative position of the insert cylinder in the direction perpendicular to the blade height direction with respect to the insert support can be regulated by the position regulating protrusion piece of the insert support. Also, in this embodiment, by bringing the first contact surface of the insert support into contact with the first passage defining surface and bringing the second contact surface of the insert support into contact with the second passage defining surface, the relative position of the insert support in the direction perpendicular to the blade height direction with respect to the blade air passage can be accurately determined. Therefore, in this embodiment, the distance from the cylindrical body of the insert cylinder to a plurality of passage defining surfaces including the first passage defining surface and the second passage defining surface can be accurately set to the target distance. Thus, in this embodiment, the impingement cooling performance of the plurality of passage defining surfaces by the cooling air ejected from the plurality of impinge holes of the cylindrical body can be appropriately managed.

[0009] As one aspect of the invention for achieving the above object, a stator vane is An insert support as the one aspect, the blade, the blade air passage, the first shroud, the second shroud, and the insert cylinder are provided. The first contact surface is in contact with the first passage defining surface. The second contact surface is in contact with the second passage defining surface. The outer peripheral edge of the support plate is joined to the second shroud body.

[0010] As one aspect of the invention for achieving the above object, a gas turbine includes a stator blade as the one aspect, a rotor rotatable about an axis, and a turbine casing covering the rotor. The stator blade body is attached inside the turbine casing such that the blade height direction is the radial direction with respect to the axis.

[0011] As one aspect of the invention for achieving the above object, a method for manufacturing a stator blade A preparation step of preparing a stationary vane body, an insert cylinder, and an insert support; a support fixing step of fixing the insert support to the stationary vane body; and a cylinder arranging step of arranging the insert cylinder are executed. The stationary vane body has an airfoil-shaped cross-section and includes a blade body extending in a blade height direction having a direction component perpendicular to the cross-section, a blade air passage extending in the blade height direction inside the blade body through which cooling air can flow, a first shroud provided at an end on a first side in the blade height direction of the blade body, and a second shroud provided at an end on a second side in the blade height direction opposite to the first side in the blade height direction of the blade body. The first shroud has a first shroud body that extends in a direction perpendicular to the blade height direction from the end on the first side in the blade height direction of the blade body. The second shroud has a second shroud body that extends in a direction perpendicular to the blade height direction from the end on the second side in the blade height direction of the blade body. The blade air passage penetrates the first shroud body, the blade body, and the second shroud body in the blade height direction. The passage defining surface that defines the blade air passage has 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 spreading in a direction intersecting the first passage defining surface. The insert cylinder has a cylindrical body extending in the blade height direction and having a plurality of impingement holes formed to penetrate from the inner peripheral side to the outer peripheral side. The insert support has a support plate extending in a direction perpendicular to the blade height direction, a position regulating protruding piece protruding from the support plate to the first side in the blade height direction and capable of facing the inner peripheral surface or the outer peripheral surface of the cylindrical body, a first pressing portion protruding from the support plate to the first side in the blade height direction, located on the side of the first passage defining surface rather than the position regulating protruding piece in a direction perpendicular to the blade height direction, and having a first contact surface capable of contacting the first passage defining surface, and a second pressing portion protruding from the support plate to the first side in the blade height direction, located on the side of the second passage defining surface rather than the position regulating protruding piece in a direction perpendicular to the blade height direction, and having a second contact surface capable of contacting the second passage defining surface. The support plate is joinable to the second shroud body at the outer peripheral edge of the support plate.The support fixing step includes a pressing step of bringing the first contact surface into contact with the first passage defining surface and the second contact surface into contact with the second passage defining surface, and a joining step of joining the outer peripheral edge of the support plate to the second shroud body in a state where the first contact surface is in contact with the first passage defining surface and the second contact surface is in contact with the second passage defining surface. In the cylinder arrangement step, the insert cylinder is arranged such that the inner peripheral surface or the outer peripheral surface of the cylinder body of the insert cylinder faces the position regulating protrusion piece of the insert support.

Advantages of the Invention

[0012] According to one aspect of the present disclosure, the impingement cooling performance of the passage defining surface that defines the vane air passage can be appropriately managed.

Brief Description of the Drawings

[0013]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

Figure 7

Figure 8

Figure 9

Figure 10

Figure 11

Figure 12

Figure 13

Figure 14

Figure 15

Figure 16

Embodiments for Carrying Out the Invention

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

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

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

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

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

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

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

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

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

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

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

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

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

[0027] As shown in FIGS. 3 to 5, the stator vane 50 of this embodiment includes 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.

[0028] The blade body 51 has an airfoil cross-section and extends in the blade height direction Dr having a direction component perpendicular to the cross-section. As shown in FIG. 2, when the stationary blade 50 is attached to the turbine casing 38, the blade height direction Dr becomes the radial direction Dr. This blade body 51 (36b) is disposed in the 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 the second blade height side Dri of both sides in the blade height direction Dr of the blade body 51. In other words, the inner shroud 60i is provided at the end of the radially inner side Dri of the blade body 51. The inner shroud 60i defines the radially inner edge Dri of the annular combustion gas flow path 39. The outer shroud 60o is provided at the end of the first blade height side Dro of both sides in the blade height direction Dr of the blade body 51. 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 radially outer edge Dro of the annular combustion gas flow path 39. Hereinafter, the blade height direction Dr is referred to as the radial direction Dr. Also, the first blade height side Dro is referred to as the radially outer side Dro, and the second blade height side Dri is referred to as the radially inner side Dri.

[0029] 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 relationship opposite to 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 upstream side Dau of the axis in the blade body 51. The trailing edge is the end of the downstream side Dad of the axis in the blade body 51. 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.

[0030] The inner shroud (second shroud) 60i has an inner shroud body (second shroud body) 61i and a peripheral wall 65i, as shown in FIGS. 4 and 5. The inner shroud body 61i extends in a direction perpendicular to the radial direction Dr from the end of the radial inner side Dri of the blade body 51. This inner shroud body 61i has a gas path surface 64p facing the radial outer side Dro, a counter gas path surface 64a facing the radial inner side Dri, a front end surface 62f which is the end surface on the upstream side Dau of the axis, a rear end surface 62b which is the end surface on the downstream side Dad of the axis, a positive pressure side end surface 63p which is the end surface on the circumferential positive pressure side Dcp, and a negative pressure side end surface 63n which is the end surface on the circumferential negative pressure side Dcn. The front end surface 62f and the rear end surface 62b are substantially parallel. Also, the positive pressure side end surface 63p and the negative pressure side end surface 63n are substantially parallel. Therefore, when viewed from the radial direction Dr, the inner shroud body 61i forms a parallelogram shape.

[0031] The peripheral wall 65i protrudes radially inward Dri from the counter gas path surface 64a of the inner shroud body 61i. This peripheral wall 65i is provided along the end surface of the inner shroud body 61i. The peripheral wall 65i has a front wall 65f and a rear wall 65b facing each other in the axial direction Da, and a positive pressure side wall 65p and a negative pressure side wall 65n facing each other in the circumferential direction Dc. The front wall 65f is provided at a position along the front end surface 62f of the inner shroud body 61i. The rear wall 65b is provided at a position along the rear end surface 62b of the inner shroud body 61i. The positive pressure side wall 65p is provided at a position along the positive pressure side end surface 63p of the inner shroud body 61i. The negative pressure side wall 65n is provided at a position along the negative pressure side end surface 63n of the inner shroud body 61i. In the inner shroud 60i, a recess 66 that is recessed toward the radial outer side Dro is formed by the inner shroud body 61i and the peripheral wall 65i. Note that the surface of the positive pressure side wall 65p on the circumferential positive pressure side Dcp and the positive pressure side end surface 63p of the inner shroud body 61i are flush. Also, the surface of the negative pressure side wall 65n on the circumferential negative pressure side Dcn and the negative pressure side end surface 63n of the inner shroud body 61i are flush. Although the rear wall 65b is formed along the rear end surface 62b of the inner shroud body 61i, it is formed on the upstream side Dau of the axis rather than the rear end surface 62b.

[0032] Of the plurality of stator blade rows 35 shown in FIG. 2, the stator blades constituting any one of the stator blade rows 35 are provided with retainers 69 protruding radially inward Dri from the positive pressure side wall 65p and the negative pressure side wall 65n of the inner shroud 60i. This retainer 69 is located between the front wall 65f and the rear wall 65b in the axial direction Da, and is formed from the positive pressure side end face 63p to the negative pressure side end face 63n. This retainer 69 is in contact with the radially outer Dro end of the inner cover 7 fixed to the gas turbine casing 8, and serves to support the radially inner Dri portion of the stator blade 50 at the radially outer Dro end of the inner cover 7.

[0033] As shown in FIGS. 3 and 5, the outer shroud (first shroud) 60o has an outer shroud body (first shroud body) 61o, a peripheral wall 65o, a front hook 68f, and a rear hook 68b. The outer shroud body 61o extends in a direction perpendicular to the radial direction Dr from the radially outer Dro end of the blade body 51. The outer shroud body 61o also has a gas path surface 64p, a counter gas path surface 64a, a front end face 62f, a rear end face 62b, a positive pressure side end face 63p, and a negative pressure side end face 63n, similar to the inner shroud body 61i. The outer shroud body 61o also forms a parallelogram shape when viewed from the radial direction Dr, similar to the inner shroud body 61i. Note that the gas path surface 64p of the inner shroud body 61i faces the radially outer Dro, while the gas path surface 64p of the outer shroud body 61o faces the radially inner Dri.

[0034] The peripheral wall 65o protrudes radially outward to Dro from the gas path opposite surface 64a of the outer shroud main body 61o. This peripheral wall 65o is provided along the end face of the outer shroud main body 61o. The peripheral wall 65o of the outer shroud 60o also has a front wall 65f, a rear wall 65b, a positive pressure side wall 65p, and a negative pressure side wall 65n, similar to the peripheral wall 65i of the inner shroud 60i. The front wall 65f is provided at a position along the front end face 62f of the outer shroud main body 61o. The rear wall 65b is provided at a position along the rear end face 62b of the outer shroud main body 61o. The positive pressure side wall 65p is provided at a position along the positive pressure side end face 63p of the outer shroud main body 61o. The negative pressure side wall 65n is provided at a position along the negative pressure side end face 63n of the outer shroud main body 61o. In the outer shroud 60o, a recess 66 that is recessed radially inward to Dri is formed by the outer shroud main body 61o and the peripheral wall 65o. Note that the surface of the positive pressure side Dcp in the circumferential direction of the positive pressure side wall 65p and the positive pressure side end face 63p of the outer shroud main body 61o are flush. Also, the surface of the negative pressure side Dcn in the circumferential direction of the negative pressure side wall 65n and the negative pressure side end face 63n of the outer shroud main body 61o are flush.

[0035] The front hook 68f is formed so as to protrude radially outward to Dro from the front wall 65f. Also, the rear hook 68b is formed so as to protrude radially outward to Dro 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.

[0036] As shown in FIGS. 3 and 5, the plurality of 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 arranged in this order along the camber line CL of the blade body 51 from the side of the leading edge 52 of the blade body 51 toward the side of the trailing edge 53. 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 is open 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 that is the opening at the radially outer end Dro and an inner opening 56ai that is the opening at the radially inner end Dri. The radially inner end Dri of the second blade air passage 56b is open 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 that is the opening at the radially inner end Dri. The radially outer end Dro of the second blade air passage 56b is closed by the outer shroud body 61o. The radially inner end Dri of the third blade air passage 56c is closed by the inner shroud body 61i, and the radially outer end Dro of the third blade air passage 56c is closed by the outer shroud body 61o. The radially outer portion Dro of the second blade air passage 56b communicates with the radially outer portion Dro of the third blade air passage 56c.

[0037] The first wing air passage 56a, the second wing air passage 56b, and the third wing air passage 56c are all defined by a plurality of passage defining surfaces. A part of the cooling air Acl flowing through the first wing air passage 56a is injected into the combustion gas flow path 39 (see FIG. 2) outside the airfoil 51 from the vicinity of the leading edge of the airfoil 51 through the passage defining surface of the first wing air passage 56a so that a plurality of leading edge injection passages 59f penetrate the leading edge portion of the airfoil 51. A part of the cooling air Acl flowing through the third wing air passage 56c is injected into the combustion gas flow path 39 outside the airfoil 51 from the trailing edge 53 of the airfoil 51 through the passage defining surface of the third wing air passage 56c so that a plurality of trailing edge injection passages 59b penetrate the trailing edge portion of the airfoil 51.

[0038] As shown in FIG. 5, the stator vane 50 of the present embodiment further includes an outer impingement plate 95o, an inner impingement plate 95i, an insert cylinder 70, an insert support 80, and a blocking plate 90.

[0039] As shown in FIGS. 3 and 5, the outer impingement plate 95o is fixed to the outer shroud 60o. This outer impingement plate 95o is disposed in the recess 66 of the outer shroud 60o and partitions the recess 66 of the outer shroud 60o into a radially outer space Dro and a radially inner space Dri. A plurality of impingement holes 95h penetrating in the radial direction Dr are formed in the outer impingement plate 95o. Cooling air Acl from the cooling device 40 described with reference to FIG. 2 flows into the space in the recess 66 of the outer shroud 60o that is radially outer Dro than the outer impingement plate 95o. This cooling air Acl passes through the plurality of impingement holes 95h of the outer impingement plate 95o and impingement-cools the anti-gas path surface 64a of the outer shroud body 61o. The cooling air Acl that has impingement-cooled the anti-gas path surface 64a is injected outside the outer shroud body 61o from, for example, the front end surface 62f and / or the rear end surface 62b of the outer shroud body 61o. The outer opening 56ao of the first wing air passage 56a described above is located radially outer Dro than the outer impingement plate 95o. Therefore, a part of the cooling air Acl from the cooling device 40 flows into the first wing air passage 56a through this outer opening 56ao.

[0040] The plugging plate 90 is fixed to the inner shroud 60i. This plugging plate 90 is arranged at a radial inner side Dri with a space from the inner shroud main body 61i, and partitions the cooling air space in the recess 66 of the inner shroud 60i and the space at the radial inner side Dri than the cooling air space. The plugging plate 90 has a front plugging plate 90f arranged at the upstream side Dau of the axis from the retainer 69 and a rear plugging plate 90b arranged at the downstream side Dad of the axis from the retainer 69.

[0041] The inner impingement plate 95i is arranged in the recess 66 of the inner shroud 60i, and partitions the aforementioned cooling air space into a first space S1 at the radial outer side Dro and a second space S2 at the radial inner side Dri. A plurality of impingement holes 95h penetrating from the second space S2 to the first space S1 are formed in the inner impingement plate 95i.

[0042] The insert cylinder 70 is cylindrical and is arranged in the first blade air passage 56a. The insert support 80 is fixed to the inner shroud main body 61i so as to support the insert cylinder 70.

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

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

[0045] As shown in FIGS. 6 to 8, the insert support 80 has a support plate 81 that extends in a direction perpendicular to the radial direction Dr and is fixed to the anti-gas path surface 64a of the inner shroud body 61i, a position regulating protruding piece 82 provided on the support plate 81, and a first pressing portion 83a and a second pressing portion 83b also provided on the support plate 81.

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

[0047] The end on the radially outer side Dro of the insert cylinder 70 is connected to the edge of the outer opening 56ao of the first wing air passage 56a (see FIG. 5). On the other hand, the radially inner end portion 72 of the insert cylinder 70 is restricted from moving in the direction perpendicular to the radial direction Dr by the annular position regulating protruding piece 82 in the insert support 80, but is allowed to move in the radial direction Dr with respect to the insert support 80. For this reason, in the present embodiment, while the movement of the insert cylinder 70 in the direction perpendicular to the radial direction Dr can be restricted, the difference in thermal expansion in the radial direction Dr between the insert cylinder 70 and the wing body 51 can be tolerated.

[0048] As shown in FIG. 8, the plurality of passage defining surfaces that define the first wing 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 spreads in a direction intersecting the first passage defining surface 57a. The first passage defining surface 57a faces the circumferential positive pressure side Dcp and is a surface that defines the edge on the circumferential negative pressure side Dcn of the first wing air passage 56a. The second passage defining surface 57b faces the axial upstream side Dau and is a surface that defines the edge on the axial downstream side Dad of the first wing air passage 56a.

[0049] As shown in FIGS. 6 to 8, the first pressing portion 83a protrudes radially outward Dro from the support plate 81, is located on the side of the first passage defining surface 57a rather than the position regulating protrusion 82 in the direction perpendicular to the radial direction Dr, and has a first contact surface 84a that contacts the first passage defining surface 57a. The second pressing portion 83b protrudes radially outward Dro from the support plate 81, is located on the side of the second passage defining surface 57b rather than the position regulating protrusion 82 in the direction perpendicular to the radial direction Dr, and has a second contact surface 84b that contacts the second passage defining surface 57b.

[0050] As shown in FIGS. 4 to 6, the front plugging plate 90f has a passage facing portion 91 that faces the first vane air passage 56a in the radial direction Dr, a transition portion 92 connected around the passage facing portion 91, and an outer peripheral portion 93 connected around the transition portion 92 and at least a part of which is connected to the peripheral wall of the inner shroud 60i. The passage facing portion 91 is located radially inward Dri of the outer peripheral portion 93. The transition portion 92 is formed to gradually go toward the radially inner Dri as it approaches the passage facing portion 91 from the outer peripheral portion 93. The outer peripheral portion 93 has a curved portion 93a that gradually goes toward the radially inner Dri as it moves away from the passage facing portion 91 in the direction perpendicular to the radial direction Dr. The edge of this curved portion 93a is connected to the retainer 69.

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

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

[0053] The stator vane body is an integrated structure of the outer shroud 60o, the vane body 51, and the inner shroud 60i. This stator vane body is formed by, for example, casting or the like.

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

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

[0056] Next, the outer impinge plate 95o is joined to the outer shroud 60o, and the inner impinge plate 95i is joined to the inner shroud 60i (impinge plate arrangement step S13).

[0057] Next, the closing plate 90 is joined to the inner shroud 60i (closing plate arrangement step S14).

[0058] Thus, the stator vane 50 in the present embodiment is completed. Note that the timing of arranging the insert cylinder 70 so that the position regulating protrusion 82 of the insert support 80 enters the protrusion insertion groove 76 of the insert cylinder 70, that is, the execution timing of the arrangement step S12a, may be after the cylinder arrangement step S11 or before the cylinder arrangement step S11.

[0059] Referring to FIGS. 5 and 6, the flow of cooling air within the stator vane 50 will be described.

[0060] Within the recess 66 of the outer shroud 60o, in a space radially outside Dro from the outer impingement plate 95o, the cooling air Acl from the cooling device 40 described with reference to FIG. 2 flows in. A part of this cooling air Acl passes through a plurality of impingement holes 95h of the outer impingement plate 95o and impingement-cools the anti-gas-passage surface 64a of the outer shroud main body 61o. The cooling air Acl that has impingement-cooled the anti-gas-passage surface 64a is jetted outside the outer shroud main body 61o from, for example, the front end surface 62f and / or the rear end surface 62b of the outer shroud main body 61o. Also, another part of the cooling air Acl flows into the cylinder body 71 of the insert cylinder 70 disposed within the first vane air passage 56a.

[0061] The cooling air Acl that has flowed into the cylinder body 71 of the insert cylinder 70 flows radially inward Dri within the cylinder body 71. In this process, a part of the cooling air Acl passes through a plurality of impingement holes 71h of the cylinder body 71. The remaining cooling air Acl flows through the annular groove side wall portion 74 fixed to the cylinder body 71 and into the second space S2 between the plugging plate 90 and the inner impingement plate 95i within the recess 66 of the inner shroud 60i. Thus, the annular groove side wall portion 74 fixed to the cylinder body 71 forms a guide cylinder portion that guides the cooling air Acl flowing into the cylinder body 71 into the second space S2.

[0062] The cooling air Acl that has passed through the plurality of impingement holes 71h of the cylinder body 71 impingement-cools the passage defining surface that defines the first vane air passage 56a. The cooling air Acl that has impingement-cooled the passage defining surface flows into a plurality of leading edge jet passages 59f. The portion near the leading edge of the vane body 51 is convectively cooled by the cooling air Acl flowing through the plurality of leading edge jet passages 59f. This cooling air Acl is jetted from the vicinity of the leading edge of the vane body 51 into the combustion gas flow path 39 outside the vane body 51.

[0063] The cooling air Acl that has flowed into the second space S2 within the recess 66 of the inner shroud 60i passes through the plurality of impinge holes 95h of the inner impinge plate 95i and impinges-cools the anti-gas-passage surface 64a of the inner shroud body 61i. The cooling air Acl that has impinged-cooled the anti-gas-passage surface 64a of the inner shroud body 61i flows into the second blade air passage 56b and flows in the second blade air passage 56b toward the radially outer side Dro. As the cooling air Acl flows in the second blade air passage 56b, it convectively cools around the second blade air passage 56b within the blade body 51.

[0064] Thereafter, the cooling air Acl flows into the third blade air passage 56c and flows in the third blade air passage 56c toward the radially inner side Dri. As the cooling air Acl flows in the third blade air passage 56c, it convectively cools around the third blade air passage 56c within the blade body 51. Further, the cooling air Acl flows into the plurality of trailing-edge injection passages 59b. The portion near the trailing edge of the blade body 51 is convectively cooled by the cooling air Acl flowing through the plurality of trailing-edge injection passages 59b. This cooling air Acl is injected from the vicinity of the trailing edge of the blade body 51 into the combustion gas flow path 39 outside the blade body 51.

[0065] In the present embodiment, as described above, the insert cylinder 70 is not joined to the insert support 80 so as to allow for the thermal expansion difference in the radial direction Dr between the insert cylinder 70 and the blade body 51. For this reason, a part of the cooling air Acl that has flowed into the space radially inner Dri than the inner shroud body 61i may leak through the gap between the insert support 80 and the insert cylinder 70 into the space on the outer peripheral side of the cylinder body 71 within the first blade air passage 56a. If the flow rate of the cooling air Acl that leaks through the gap between the insert support 80 and the insert cylinder 70 into the space on the outer peripheral side of the cylinder body 71 within the first blade air passage 56a increases, the pressure difference between the space on the inner peripheral side of the cylinder body 71 and the space on the outer peripheral side of the cylinder body 71 decreases. For this reason, the speed at which the cooling air Acl on the inner peripheral side of the cylinder body 71 passes through the plurality of impinge holes 71h of the cylinder body 71 decreases, and the impinge cooling effect on the passage defining surface that defines the first blade air passage 56a deteriorates.

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

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

[0068] As described above, in this embodiment, the resistance of the cooling air Acl flowing through the flow path formed by the gap between the insert support 80 and the insert cylinder 70 increases, and the pressure of the cooling air Acl flowing into the gap between the insert support 80 and the insert cylinder 70 decreases. Therefore, the flow rate of the cooling air Acl leaking into the space on the outer peripheral side of the cylinder body 71 within the first blade air passage 56a can be reduced. Thus, in this embodiment, it is possible to suppress a decrease in the impingement cooling effect with respect to the passage defining surface that defines the first blade air passage 56a.

[0069] In this embodiment, as described above, the position regulating protrusion piece 82 of the insert support 80 can regulate the relative position in the direction perpendicular to the radial direction Dr of the insert cylinder 70 with respect to the insert support 80. Further, in this embodiment, since the first contact surface 84a of the insert support 80 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, the relative position in the direction perpendicular to the radial direction Dr of the insert support 80 with respect to the first wing air passage 56a can be accurately determined. For this reason, in this embodiment, the distances from the outer peripheral surface of the cylindrical body 71 of the insert cylinder 70 to a plurality of passage defining surfaces including the first passage defining surface 57a and the second passage defining surface 57b can be accurately set to the target distances. Thus, in this embodiment, the impingement cooling performance of the plurality of passage defining surfaces by the cooling air Acl ejected from the plurality of impingement holes 71h of the cylindrical body 71 can be appropriately managed.

[0070] The outer shroud 60o, the blade 51, and the inner shroud 60i are exposed to the high-temperature combustion gas G. On the other hand, the plugging plate 90 joined to the inner shroud 60i is in contact with the cooling air Acl and is not exposed to the combustion gas G. For this reason, a thermal expansion difference occurs between the inner shroud 60i and the plugging plate 90. In this embodiment, even if a thermal expansion difference occurs between the inner shroud 60i and the plugging plate 90, the connection portion between the passage facing portion 91 and the transition portion 92 and the connection portion between the transition portion 92 and the outer peripheral portion 93 are deformed, and the plugging plate 90 can accept this thermal expansion difference without difficulty. Thus, in this embodiment, damage to the joint portion between the inner shroud 60i and the plugging plate 90 and the plugging plate 90 can be suppressed. Further, even if a thermal expansion difference occurs between the inner shroud 60i and the plugging plate 90, damage at the joint portion between the curved portion 93a in the outer peripheral portion 93 and the retainer 69 can be suppressed by the deformation of the curved portion 93a in the outer peripheral portion 93.

[0071] Further, in the present embodiment, the distance between the passage facing portion 91 and the inner shroud main body 61i is larger than at least the distance between the connection portion with the transition portion 92 in the outer peripheral portion 93 and the inner shroud main body 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 adjusted to match the distance between the connection portion with the transition portion 92 in the outer peripheral portion 93 and the inner shroud main body 61i. Therefore, in the present embodiment, it is possible to suppress a pressure drop of the cooling air Acl due to the cooling air Acl colliding with the passage facing portion 91 of the blocking plate 90 after passing through the first blade air passage 56a. Thus, in the present embodiment, the cooling air Acl that has passed through the insert cylinder 70 in the first blade air passage 56a and has flowed into the recess 66 of the inner shroud 60i can be effectively used for cooling the inner shroud 60i and the like. Further, in the present embodiment, it is possible to avoid the blocking plate 90 interfering with the inner end in the radial direction Dri of the groove side wall portion (guide cylinder portion) 74 due to thermal expansion of a part of the stator vane 50.

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

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

[0074] Therefore, in this modification, the flow rate of the cooling air Acl flowing into the gap between the insert support 80a and the insert cylinder 70 can be reduced in the space Dri radially inside the inner shroud body 61i. Thus, in the present embodiment, the flow rate of the cooling air Acl leaking into the space on the outer peripheral side of the cylinder body 71 within the first blade air passage 56a can be reduced.

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

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

[0077] In this modification, the radially inner end Dri of the cylindrical body 71b is located radially inward Dri of the inner impingement plate 95i and radially inward Dri of the plugging plate 90. Similar to the cylindrical body 71 in the above-described embodiment, the radially outer end Dro and the radially inner end Dri of this cylindrical body 71b are open. Therefore, the cooling air Acl flowing into the cylindrical body 71b from the opening on the radially outer side Dro of the cylindrical body 71b can flow through the inside of this cylindrical body 71b and into the second space S2 between the plugging plate 90 and the inner impingement plate 95i in the recess 66 of the inner shroud 60i. Thus, this cylindrical body 71b forms a guide cylinder portion that guides the cooling air Acl flowing into the cylindrical body 71b into the second space S2. A plurality of impingement holes 71h penetrating from the inner peripheral side toward the outer peripheral side are also formed in this cylindrical body 71b. The flange portion 73b is annular. The outer peripheral edge of the annular flange portion 73b is joined to the inner peripheral surface of the cylindrical body 71b. This flange portion 73b protrudes toward the inner peripheral side of the cylindrical body 71b from a position closer to the radially inner side Dri of the cylindrical body 71b among the inner peripheral surfaces of the cylindrical body 71b. Therefore, the air passage inside the cylindrical body 71b is narrowed by this flange portion 73b. The groove bottom portion 75b is annular. The outer peripheral edge of the annular groove bottom portion 75b is joined to the outer peripheral surface of the cylindrical body 71b. This groove bottom portion 75b protrudes toward the outer peripheral side of the cylindrical body 71b from a position closer to the radially inner side Dri of the cylindrical body 71b among the outer peripheral surfaces of the cylindrical body 71b. The groove side wall portion 74b is cylindrical, joined to the outer peripheral edge of the annular groove bottom portion 75b, and extends radially inward Dri. The inner peripheral surface of the annular groove side wall portion 74b faces the outer peripheral surface of the annular cylindrical body 71b with a gap therebetween. Therefore, an annular protruding piece insertion groove 76b is formed between the annular groove side wall portion 74b and the annular cylindrical body 71b. This protruding piece insertion groove 76b is recessed radially outward Dro. The annular position regulating protruding piece 82 of the insert support 80 fits into this annular protruding piece insertion groove 76b.

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

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

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

[0081] As described above, also in this modified example, similar to the above-described embodiment, the resistance of the cooling air Acl flowing through the flow path formed by the gap between the insert support 80 and the insert cylinder 70b increases, and the pressure of the cooling air Acl flowing into the gap between the insert support 80 and the insert cylinder 70b decreases. For this reason, the flow rate of the cooling air Acl leaking into the space on the outer peripheral side of the cylinder body 71b within the first blade air passage 56a can be reduced. Thus, also in this modified example, a decrease in the impingement cooling effect with respect to the passage defining surface that defines the first blade air passage 56a can be suppressed.

[0082] Also in this modified example, the end on the radially inner side Dri of the cylinder body 71b that forms the guide cylinder portion is located on the radially outer side Dro of the blocking plate 90 rather than on the radially inner side Dri of the inner impingement plate 95i. However, the passage facing portion 91 of the blocking plate 90 is located on the radially inner side Dri of the outer peripheral portion 93 of this blocking plate 90. For this reason, it is possible to avoid the blocking plate 90 interfering with the end on the radially inner side Dri of the cylinder body 71b that forms the guide cylinder portion due to thermal expansion of a part of the stationary blade 50.

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

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

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

[0086] The insert support 80c in this modification example has, similar to the insert support 80 in the above embodiment, a support plate 81 that spreads 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 regulating protruding piece 82c, a first pressing portion 83a, a second pressing portion 83b, a groove side wall portion 87, and a guide cylinder portion 88. The position regulating protruding piece 82c, the first pressing portion 83a, the second pressing portion 83b, the groove side wall portion 87, and the guide cylinder portion 88 are all provided on the support plate 81.

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

[0088] The first pressing portion 83a projects radially outward Dro from the support plate 81 and is located on the side of the first passage defining surface 57a (see FIG. 8) rather than the inner position regulating projection piece 82c and the outer position regulating projection piece 87 in the direction perpendicular to the radial direction Dr, and has a first contact surface 84a (see FIG. 8) that contacts the first passage defining surface 57a. The second pressing portion 83b projects radially outward Dro from the support plate 81 and is located on the side of the second passage defining surface 57b (see FIG. 8) rather than the inner position regulating projection piece 82c and the outer position regulating projection piece 87 in the direction perpendicular to the radial direction Dr, and has a second contact surface 84b (see FIG. 8) that contacts the second passage defining surface 57b.

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

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

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

[0092] As described above, also in this modification, similar to the said embodiment and the said second modification, the resistance of the cooling air Acl flowing through the flow path formed by the gap between the insert support 80c and the insert cylinder 70c increases, and the pressure of the cooling air Acl flowing into the gap between the insert support 80c and the insert cylinder 70c becomes smaller. Therefore, the flow rate of the cooling air Acl leaking into the space on the outer peripheral side of the cylinder body 71 within the first wing air passage 56a can be reduced. Thus, also in this modification, a decrease in the impingement cooling effect with respect to the passage defining surface that defines the first wing air passage 56a can be suppressed.

[0093] Also in this modification example, the radially inner end Dri of the guide cylinder portion 88 is located radially inside Dri of the inner impinge plate 95i and radially outside Dro of the blocking plate 90. However, the passage facing portion 91 of the blocking plate 90 is located radially inside Dri of the outer peripheral portion 93 of this blocking plate 90. Therefore, it is possible to avoid the blocking plate 90 interfering with the radially inner end Dri of the guide cylinder portion 88 due to thermal expansion of a part of the stationary vane 50.

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

[0095] As shown in FIGS. 14 and 15, the insert support 80d in this modification example, similar to the insert support 80 in the above-described 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 regulating projection piece 82 provided on the support plate 81, and a first pressing portion 83da and a second pressing portion 83db also provided on the support plate 81.

[0096] The first pressing portion 83da in this modification example also projects radially outward Dro from the support plate 81, is located on the side of the first passage defining surface 57a rather than the position regulating projection piece 82 in a direction perpendicular to the radial direction Dr, and has a first contact surface 84a that contacts the first passage defining surface 57a, similar to the first pressing portion 83a in the above-described embodiment. Also, the second pressing portion 83db in this modification example also projects radially outward Dro from the support plate 81, is located on the side of the second passage defining surface 57b rather than the position regulating projection piece 82 in a direction perpendicular to the radial direction Dr, and has a second contact surface 84b that contacts the second passage defining surface 57b, similar to the first pressing portion 83a in the above-described embodiment.

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

[0098] In this modified example, even if the insert support 80d has the first pressing portion 83da and the second pressing portion 83db, the end 71i on 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 on the radially inner side Dri of the cylindrical body 71 can be brought closer to the position of the anti-gas path surface 64a of the inner shroud main body 61i. For this reason, in this modified example, while maintaining the overlap amount in the radial direction Dr between the cylindrical body 71 and the position regulating protrusion 82, the position of the impinge hole 71h formed at the most radially inner side Dri in the cylindrical body 71 can be brought closer to the position of the anti-gas path surface 64a of the inner shroud main body 61i.

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

[0100] As shown in FIG. 16, the insert support 80e in this modified example has, similar to the insert support 80d in the fourth modified example, 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 regulating protrusion 82 provided on the support plate 81, and a first pressing portion 83ea and a second pressing portion 83eb also provided on the support plate 81.

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

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

[0103] "Modified Example" The stationary vane 50 in the above embodiments and each modified example has three vane air passages 56. However, the stationary vane 50 may have four or more vane air passages 56.

[0104] In the stationary vane 50 in the above embodiments and each modified example, among the plurality of vane air passages 56, the insert cylinders 70, 70b, 70c are arranged in the most axially upstream first vane air passage 56a. However, the insert cylinders 70, 70b, 70c may be arranged in the vane air passage 56 on the axially downstream side Dad from the most axially upstream first vane air passage 56a.

[0105] In the above-described embodiments and each modification example, the first passage defining surface 57a that defines the blade air passage 56 of the stator blade 50 faces the circumferential direction positive pressure side Dcp and is a surface that defines the edge of the circumferential direction negative pressure side Dcn of the first blade air passage 56a. Alternatively, the second passage defining surface 57b faces the axial upstream side Dau and is a surface that defines the edge of the axial downstream side Dad of the first blade air passage 56a. However, 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 only needs to be connected to the first passage defining surface 57a and expand in a direction intersecting the first passage defining surface 57a. For example, assume that the first passage defining surface 57a faces the circumferential direction positive pressure side Dcp and is a surface that defines the edge of the circumferential direction negative pressure side Dcn of the blade air passage 56. In this case, if 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 expands in a direction intersecting the first passage defining surface 57a, this passage defining surface may be used as the second passage defining surface 57b.

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

[0107] "Supplementary Note" The insert supports 80, 80a, 80c, 80d, 80e in the above-described embodiments and modification examples are understood as follows, for example. (1) The insert support in the first aspect is An airfoil 51 having a cross-section forming an airfoil shape and extending in a blade height direction Dr having a direction component perpendicular to the cross-section, an airfoil air passage 56a extending through the airfoil 51 in the blade height direction Dr through which cooling air Acl can flow, a first shroud 60o provided at an end of the airfoil 51 on a first blade height side Dro in the blade height direction Dr, a second shroud 60i provided at an end of the airfoil 51 on a second blade height side Dri opposite to the first blade height side Dro, and insert cylinders 70, 70b, 70c at least partially disposed in the airfoil air passage 56a. The insert supports 80, 80a, 80c, 80d, 80e of the stationary blade 50. The first shroud 60o has a first shroud body 61o that extends in a direction perpendicular to the blade height direction Dr from the end of the airfoil 51 on the first blade height side Dro. The second shroud 60i has a second shroud body 61i that extends in a direction perpendicular to the blade height direction Dr from the end of the airfoil 51 on the second blade height side Dri. The airfoil air passage 56a passes through the first shroud body 61o, the airfoil 51, and the second shroud body 61i in the blade height direction Dr. The airfoil 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 and extending in the blade height direction Dr while expanding in a direction intersecting the first passage defining surface 57a. The insert cylinders 70, 70b, 70c extend in the blade height direction Dr and form a cylindrical shape, and have cylindrical bodies 71, 71b in which a plurality of impinge holes 71h penetrating from the inner peripheral side to the outer peripheral side are formed.The insert supports 80, 80a, 80c, 80d, 80e include a support plate 81 extending in a direction perpendicular to the wing height direction Dr, a cylindrical protrusion from the support plate 81 to the first side Dro of the wing height, and position regulating protrusion pieces 82, 82c that can face the inner peripheral surface or the outer peripheral surface of the second side end portion 72 including the end of the second side Dri in the cylinders 71, 71b. The first pressing portions 83a, 83da, 83ea protrude from the support plate 81 to the first side Dro of the wing height, are located on the side of the first passage defining surface 57a in a direction perpendicular to the wing height direction Dr and closer to the first passage defining surface 57a than the position regulating protrusion pieces 82, 82c, and have a first contact surface 84a capable of contacting the first passage defining surface 57a. The second pressing portions 83b, 83db, 83eb protrude from the support plate 81 to the first side Dro of the wing height, are located on the side of the second passage defining surface 57b in a direction perpendicular to the wing height direction Dr and closer to the second passage defining surface 57b than the position regulating protrusion pieces 82, 82c, and have a second contact surface 84b capable of contacting the second passage defining surface 57b. The outer peripheral edge of the support plate 81 can be joined to the second shroud body 61i.

[0108] In this aspect, the relative position in the direction perpendicular to the blade height direction Dr of the insert cylinders 70, 70b, 70c with respect to the insert supports 80, 80a, 80c, 80d, 80e can be restricted by the position restricting protruding pieces 82, 82c of the insert supports 80, 80a, 80c, 80d, 80e. Further, in this aspect, by bringing the first contact surface 84a of the insert supports 80, 80a, 80c, 80d, 80e into contact with the first passage defining surface 57a and bringing the second contact surface 84b of the insert supports 80, 80a, 80c, 80d, 80e into contact with the second passage defining surface 57b, the relative position in the direction perpendicular to the blade height direction Dr of the insert supports 80, 80a, 80c, 80d, 80e with respect to the blade air passage 56a can be accurately determined. Therefore, in this aspect, the distance from the cylinder bodies 71, 71b of the insert cylinders 70, 70b, 70c to a plurality of passage defining surfaces including the first passage defining surface 57a and the second passage defining surface 57b can be accurately set to the target distance. Thus, in this aspect, the impingement cooling performance of the plurality of passage defining surfaces by the cooling air Acl ejected from the plurality of impingement holes 71h of the cylinder bodies 71, 71b can be appropriately controlled.

[0109] (2) The insert support in the second aspect is In the insert supports 80, 80a, 80c, 80d, 80e in the first aspect, the support plate 81 has a support plate opening 81o that penetrates in the blade height direction Dr in a portion facing the inner peripheral side region of the cylinder bodies 71, 71b in the blade height direction Dr. The position restricting protruding pieces 82, 82c project from the support plate 81 toward the first blade height side Dro in a cylindrical shape over the entire circumference of the opening edge of the support plate opening 81o.

[0110] (3) The insert support in the third aspect is In the insert supports 80d and 80e in the first aspect or the second aspect, the position regulating protruding piece 82 is located on the inner peripheral side of the cylindrical body 71 and can face the inner peripheral surface of the cylindrical body 71. A first groove 86a is formed between the position regulating protruding piece 82 and the first pressing portions 83da and 83ea, being recessed on the second wing height side Dri such that the end of the second wing height side Dri of the cylindrical body 71 can enter. A second groove 86b is formed between the position regulating protruding piece 82 and the second pressing portions 83db and 83eb, being recessed on the second wing height side Dri such that the end of the second wing height side Dri of the cylindrical body 71 can enter.

[0111] In this aspect, even if the insert supports 80d and 80e have the first pressing portions 83da and 83ea and the second pressing portions 83db and 83eb, by having the ends of the second wing height side Dri of the cylindrical body 71 enter the first groove 86a and the second groove 86b, the position of the end of the second wing height side Dri of the cylindrical body 71 can be brought closer to the position of the anti-gas path surface 64a of the second shroud body 61i. Therefore, in this aspect, while maintaining the overlap amount in the wing height direction Dr between the cylindrical body 71 and the position regulating protruding piece 82, the position of the impinge hole 71h formed at the most second wing height side Dri in the cylindrical body 71 can be brought closer to the position of the anti-gas path surface 64a of the second shroud body 61i.

[0112] (4) The insert support in the fourth aspect is In the insert support 80e in the third aspect, the second pressing portion 83eb is separated from the first pressing portion 83ea.

[0113] In this aspect, the first groove 86a and the second groove 86b can be easily machined.

[0114] The stationary vane 50 in the above embodiments and modified examples can be understood as follows, for example. (5) The stationary vane in the fifth aspect is In any one of the first to fourth aspects, an insert support 80, 80a, 80c, 80d, 80e, a wing body 51, a wing air passage 56a, a first shroud 60o, a second shroud 60i, and insert cylinders 70, 70b, 70c are provided. The first contact surface 84a is in contact with the first passage defining surface 57a. The second contact surface 84b is in contact with the second passage defining surface 57b. The outer peripheral edge of the support plate 81 is joined to the second shroud body 61i.

[0115] The gas turbines in the above embodiments and modifications are understood, for example, as follows. (6) The gas turbine in the sixth aspect is provided with the stationary blade 50 in the fifth aspect, a rotor 31 rotatable about an axis Ar, and a turbine casing 38 covering the rotor 31. The stationary blade 50 is attached inside the turbine casing 38 such that the blade height direction Dr becomes the radial direction Dr with respect to the axis Ar.

[0116] The manufacturing method of the stationary blade in the above embodiments and modifications is understood, for example, as follows. (7) The manufacturing method of the stationary blade in the seventh aspect is A preparation step S10 of preparing a stationary vane body, insert cylinders 70, 70b, 70c, and insert supports 80, 80a, 80c, 80d, 80e; a cylinder arrangement step S11 of arranging the insert cylinders 70, 70b, 70c; and a support fixing step S12 of fixing the insert supports 80, 80a, 80c, 80d, 80e to the stationary vane body are executed. The stationary vane body includes a vane body 51 having an airfoil-shaped cross-section and extending in a vane height direction Dr having a direction component perpendicular to the cross-section; a vane air passage 56a extending in the vane height direction Dr inside the vane body 51 and through which cooling air Acl can flow; a first shroud 60o provided at an end of the vane body 51 on a first vane height side Dro in the vane height direction Dr; and a second shroud 60i provided at an end of the vane body 51 on a second vane height side Dri opposite to the first vane height side Dro. The first shroud 60o has a first shroud body 61o that extends in a direction perpendicular to the vane height direction Dr from the end of the vane body 51 on the first vane height side Dro. The second shroud 60i has a second shroud body 61i that extends in a direction perpendicular to the vane height direction Dr from the end of the vane body 51 on the second vane height side Dri. The vane air passage 56a penetrates the first shroud body 61o, the vane body 51, and the second shroud body 61i in the vane height direction Dr. The passage defining surface that defines the vane air passage 56a has a first passage defining surface 57a extending in the vane height direction Dr and a second passage defining surface 57b connected to the first passage defining surface 57a, extending in the vane height direction Dr, and spreading in a direction intersecting the first passage defining surface 57a. The insert cylinders 70, 70b, 70c are cylindrical bodies 71, 71b that extend in the vane height direction Dr and have a plurality of impingement holes 71h formed therethrough from the inner peripheral side to the outer peripheral side.The insert supports 80, 80a, 80c, 80d, 80e include a support plate 81 that extends in a direction perpendicular to the blade height direction Dr, position regulating protrusions 82, 82c that protrude from the support plate 81 toward the first blade height side Dro and can face the inner peripheral surface or the outer peripheral surface of the cylinders 71, 71b, first pressing portions 83a, 83da, 83ea that protrude from the support plate 81 toward the first blade height side Dro, are located on the side of the first passage defining surface 57a rather than the position regulating protrusions 82, 82c in a direction perpendicular to the blade height direction Dr, and have first contact surfaces 84a that can contact 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 located on the side of the second passage defining surface 57b rather than the position regulating protrusions 82, 82c in a direction perpendicular to the blade height direction Dr, and have second contact surfaces 84b that can contact the second passage defining surface 57b. The support plate 81 can be joined to the second shroud body 61i at the outer peripheral edge of the support plate 81. In the cylinder arrangement step S11, the insert cylinders 70, 70b, 70c are arranged such that the inner peripheral surface or the outer peripheral surface of the cylinders 71, 71b of the insert cylinders 70, 70b, 70c faces the position regulating protrusions 82, 82c of the insert supports 80, 80a, 80c, 80d, 80e. The support fixing step S12 includes a pressing step S12b of bringing the first contact surface 84a into contact with the first passage defining surface 57a and bringing the second contact surface 84b into contact with the second passage defining surface 57b, and a joining step S12c of joining the outer peripheral edge of the support plate 81 to the second shroud body 61i in a state where 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.

Explanation of Signs

[0117] 1: Gas turbine rotor 6: Intermediate casing 7: Inner cover 8: Gas turbine casing 10: Compressor 11: Compressor rotor 12: Rotor shaft 13: Blade row 15: Stator blade body row 18: Compressor casing 20: Combustor 21: Burner 22: Tail pipe (or combustion tube) 30: Turbine 31: Turbine rotor 32: Rotor shaft 33: Rotor blade row 35: Stator blade row 37: Split ring 38: Turbine casing 39: Combustion gas flow path 40: Cooling device 41: Bleed line 42: Cooler 43: Boost compressor 44: Cooling air line 45: Cooling air exhaust line 50: Stator blade body 51: Blade body 52: Leading edge 53: Trailing edge 54: Suction surface 55: Pressure surface 56: Blade air passage 56a: First blade air passage (or simply blade air passage) 56ai: Inner opening 56ao: Outer opening 56b: Second blade air passage 56bi: Inner opening 56c: Third blade air passage 57a: First passage defining surface 57b: Second passage defining surface 59f: Leading edge injection passage 59b: Trailing edge injection passage 60i: Inner shroud (or second shroud) 60o: Outer shroud (or first shroud) 61i: Inner shroud body (or second shroud body) 61o: Outer shroud body (or first shroud body) 62f: Front end face 62b: Rear end face 63n: Suction side end face 63p: Positive pressure side end face 64p: Gas path surface 64a: Reverse gas path surface 65i, 65o: Peripheral wall 65f: Front wall 65b: Rear wall 65n: Negative pressure side wall 65p: Positive pressure side wall 66: Recess 68f: Front hook 68b: Rear hook 69: Retainer 70, 70b, 70c: Insert cylinder 71: Cylindrical body 71b: Cylindrical body (or guide cylinder part) 71h: Impinge hole 72: Radial inner end (or second side end) 73: Flange part (or groove bottom) 73b, 73c: Flange part 74: Groove side wall part (or guide cylinder part) 74b: Groove side wall part 75b: Groove bottom 76, 76b: Projection insertion groove 80: Insert support 81: Support plate 81c: Groove bottom 81o: Support plate opening 82: Position regulating projection 82c: Position regulating projection (or inner position regulating projection) 83a, 83da: First pressing part 83b, 83db: Second pressing part 84a: First contact surface 84b: Second contact surface 85: Throttle ring 85o: Throttle opening 86a: First groove 86b: Second groove 87: Groove side wall part (or outer position regulating projection) 88: Guide cylinder part 89: Cylindrical body insertion groove 90: Plugging plate 90f: Front plugging plate 90b: Rear plugging plate 91: Passage facing part 92: Migration part 93: Peripheral part 93a: Bending part 95i: Inner impinge plate (or simply impinge plate) 95o: Outer impinge plate 95h: Impinge hole A: Outside air Acom: Compressed air Acl: Cooling air G: Combustion gas F: Fuel CL: Camber line S1: First space S2: Second space Ar: Axis Da: Axial direction Dau: Upstream side of the axis Dad: Downstream side of the axis Dc: Circumferential direction Dcn: Negative pressure side in the circumferential direction Dcp: Positive pressure side Dcp in the circumferential direction Dr: Radial direction (or blade height direction) Dri: Inner side in the radial direction (or second side of the blade height) Dro: Outer side in the radial direction (or first side of the blade height)

Claims

1. An airfoil-shaped cross-section and a blade body extending in the blade height direction having a direction component perpendicular to the cross-section, A blade air passage extending in the blade height direction inside the blade body and through which cooling air can flow, A first shroud provided at an end on the first side of the blade height of the blade body, A second shroud provided at an end on the second side of the blade height, which is opposite to the first side of the blade height of the blade body, An insert cylinder at least partially disposed within the blade air passage, Comprising, The first shroud has a first shroud body that extends in a direction perpendicular to the blade height direction from the end on the first side of the blade height of the blade body, The second shroud has a second shroud body that extends in a direction perpendicular to the blade height direction from the end on the second side of the blade height of the blade body, The blade air passage penetrates the first shroud body, the blade body, and the second shroud body in the blade height direction, 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 spreading in a direction intersecting the first passage defining surface, The insert cylinder has a cylindrical body extending in the blade height direction and having a plurality of impingement holes penetrating from the inner peripheral side to the outer peripheral side, In the insert support of the stator vane, A support plate extending in a direction perpendicular to the blade height direction, A position regulating projection protruding from the support plate to the first side of the blade height and having a cylindrical shape, and capable of facing the inner peripheral surface or the outer peripheral surface of the second side end portion including the end on the second side of the blade height in the cylindrical body, A first pressing portion protruding from the support plate to the first side of the blade height, located on the side of the first passage defining surface rather than the position regulating projection in a direction perpendicular to the blade height direction, and having a first contact surface capable of contacting the first passage defining surface, A second pressing portion protruding from the support plate to the first side of the blade height, located on the side of the second passage defining surface rather than the position regulating projection in a direction perpendicular to the blade height direction, and having a second contact surface capable of contacting the second passage defining surface, Having, The support plate is joinable to the second shroud body at the outer peripheral edge of the support plate, Insert support.

2. In the insert support according to claim 1, The support plate has a support plate opening penetrating in the blade height direction at a portion facing the inner peripheral side region of the cylindrical body in the blade height direction, The position regulating protruding piece protrudes from the support plate toward the first side of the vane height in a cylindrical shape over the entire circumference of the opening edge of the support plate opening. Insert support.

3. In the insert support according to claim 1, the position regulating protruding piece is located on the inner peripheral side of the cylindrical body and can face the inner peripheral surface of the cylindrical body. A first groove is formed between the position regulating protruding piece and the first pressing portion, recessed toward the second side of the vane height, into which the end of the cylindrical body on the second side of the vane height can enter. A second groove is formed between the position regulating protruding piece and the second pressing portion, recessed toward the second side of the vane height, into which the end of the cylindrical body on the second side of the vane height can enter. Insert support.

4. In the insert support according to claim 3, the second pressing portion is separated from the first pressing portion. Insert support.

5. The insert support according to any one of claims 1 to 4, the vane, the vane air passage, the first shroud, the second shroud, the insert cylinder, are provided, the first contact surface contacts the first passage defining surface, the second contact surface contacts the second passage defining surface, the outer peripheral edge of the support plate is joined to the second shroud body. Stationary vane.

6. The stationary vane according to claim 5, a rotor rotatable about an axis, a turbine casing covering the rotor, are provided, the stationary vane is attached inside the turbine casing such that the vane height direction is the radial direction with respect to the axis. Gas turbine.

7. A preparation step of preparing a stationary vane body, an insert cylinder, and an insert support, a cylinder arrangement step of arranging the insert cylinder, a support fixing step of fixing the insert support to the stationary vane body, are executed, the stationary vane body has a vane body whose cross section forms an airfoil shape and extends in the vane height direction having a direction component perpendicular to the cross section, a vane air passage extending in the vane height direction inside the vane body through which cooling air can flow, a first shroud provided at the end of the vane body on the first side of the vane height in the vane height direction, a second shroud provided at the end of the vane body on the second side of the vane height, which is opposite to the first side of the vane height, and has, the first shroud has a first shroud body that extends in a direction perpendicular to the vane height direction from the end of the vane body on the first side of the vane height. The second shroud has a second shroud body that extends in a direction perpendicular to the wing height direction from an end on the second side of the wing height of the airfoil body. The wing air passage penetrates the first shroud body, the airfoil body, and the second shroud body in the wing height direction. The passage defining surface that defines the wing air passage has a first passage defining surface that extends in the wing height direction, and a second passage defining surface that is connected to the first passage defining surface, extends in the wing height direction, and spreads in a direction intersecting the first passage defining surface. The insert cylinder has a cylindrical body that extends in the wing height direction and has a plurality of impinge holes formed to penetrate from the inner peripheral side to the outer peripheral side. The insert support has a support plate that spreads in a direction perpendicular to the wing height direction, a position regulating protrusion that protrudes from the support plate to the first side of the wing height and can face the inner peripheral surface or the outer peripheral surface of the cylindrical body, a first pressing portion that protrudes from the support plate to the first side of the wing height, is located on the side of the first passage defining surface rather than the position regulating protrusion in a direction perpendicular to the wing height direction, and has a first contact surface that can contact the first passage defining surface, a second pressing portion that protrudes from the support plate to the first side of the wing height, is located on the side of the second passage defining surface rather than the position regulating protrusion in a direction perpendicular to the wing height direction, and has a second contact surface that can contact the second passage defining surface, and has The support plate can be joined to the second shroud body at the outer peripheral edge of the support plate. In the cylinder arranging step, the insert cylinder is arranged so that the inner peripheral surface or the outer peripheral surface of the cylindrical body of the insert cylinder faces the position regulating protrusion of the insert support. The support fixing step includes a pressing step of bringing the first contact surface into contact with the first passage defining surface and bringing the second contact surface into contact with the second passage defining surface, and a joining step of joining the outer peripheral edge of the support plate to the second shroud body in a state where the first contact surface is in contact with the first passage defining surface and the second contact surface is in contact with the second passage defining surface. including A method for manufacturing a stator vane.

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