Flow path forming plate, blade provided with same, and gas turbine provided with same

Abstract

An air passage of a flow path forming plate according to the present disclosure extends in a first direction along a gas path surface and a first end surface. The air passage has a gas path defining surface that is in a back-to-back relationship with the gas path surface, and an end defining surface that is in a back-to-back relationship with the first end surface. The gas path defining surface has a plurality of first turbulators formed apart from each other in the first direction. The end defining surface has a plurality of second turbulators formed apart from each other in the first direction. The first turbulators and the second turbulators extend in a direction inclined with respect to the first direction.

Description

Flow path forming plate, blade equipped with same, and gas turbine equipped with same

[0001] The present disclosure relates to a flow path forming plate that defines a combustion gas flow path through which combustion gas flows, a blade including the same, and a gas turbine including the same. This application claims priority to Japanese Patent Application No. 2023-163936, filed on September 26, 2023, the contents of which are incorporated herein by reference.

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

[0003] The rotor blade has a blade body extending in a radial direction relative to the axis and a platform provided radially inside the blade body. The blade body of the rotor blade is arranged in a combustion gas flow path through which combustion gas passes. The platform defines the radially inner edge of the combustion gas flow path. The stator vane has a blade body extending in a radial direction relative to the axis, an inner shroud provided radially inside the blade body, and an outer shroud provided radially outside the blade body. The blade body of the stator vane is arranged in the combustion gas flow path through which combustion gas passes. The inner shroud defines the radially inner edge of the combustion gas flow path. The outer shroud defines the radially outer edge of the combustion gas flow path. The turbine casing is provided with a plurality of segmented rings. The plurality of segmented rings are arranged in positions facing the rotor blades in the radial direction relative to the axis. The segmented rings define the outer edge of the combustion gas flow path.

[0004] As described above, the platforms of the rotor blades, the outer and inner shrouds of the vanes, and the segmented rings all form flow passage plates that define the combustion gas flow passages. These flow passage plates are exposed to high-temperature combustion gas. For this reason, the flow passage plates are generally cooled by air or the like.

[0005] For example, Patent Document 1 below discloses a shroud for a stator vane, which is a type of flow path forming plate. The shroud has a gas path surface that defines a portion of a combustion gas flow path, multiple end faces connected to the periphery of the gas path surface, and an end air passage through which cooling air can flow. The end air passage extends along a first end face of the gas path surface and the multiple end faces and in a first direction parallel to the gas path surface and the first end face. The end air passage is defined by multiple passage defining surfaces. Two adjacent passage defining surfaces of the multiple passage defining surfaces are formed with turbulators, in which convex and concave portions are alternately repeated in the first direction. The turbulators form a turbulent boundary layer of the cooling air along the passage defining surfaces, improving the heat transfer coefficient between the cooling air and a portion of the shroud near the end air passage.

[0006] JP 2018-141393 A

[0007] In the flow passage forming plate, a part such as a corner between the gas path surface and one of the end faces may be easily heated by the combustion gas due to its arrangement or the like.

[0008] Therefore, an object of the present disclosure is to provide a flow passage forming plate capable of efficiently cooling the gas path surface and the end surface, a blade including the same, and a gas turbine including the same.

[0009] A flow path forming plate according to one aspect of the invention for achieving the above object includes a gas path surface that defines a part of a combustion gas flow path through which combustion gas flows, a first end surface connected to the periphery of the gas path surface, and an air passage defined by a plurality of defining surfaces and having an inlet through which cooling air can flow, the air passage extending in a first direction that is a direction extending along the gas path surface and the first end surface, and the plurality of defining surfaces are a gas path defining surface that extends in the first direction and is back-to-back with the gas path surface, and a first end surface that extends in the first direction and is back-to-back with the first end surface. and an end defining surface in a relative relationship, the end defining surface and the gas path defining surface being connected via a first corner portion, the gas path defining surface being formed to protrude toward the inside of the air passage and having a plurality of first turbulators formed spaced apart in the first direction, the end defining surface being formed to protrude toward the inside of the air passage and having a plurality of second turbulators formed spaced apart in the first direction, the plurality of first turbulators and the plurality of second turbulators extending in a direction inclined with respect to the first direction.

[0010] The blade according to one aspect of the invention for achieving the above object comprises the flow passage forming plate and a blade body having an airfoil-shaped cross section and extending in a blade height direction having a directional component perpendicular to the cross section. The flow passage forming plate is provided at one end of the blade body in the blade height direction and extends in a direction perpendicular to the blade height direction.

[0011] To achieve the above object, one aspect of the invention provides a gas turbine comprising: a compressor capable of compressing air to generate compressed air; a combustor capable of burning fuel in the compressed air to generate combustion gas; and a turbine capable of being driven by the combustion gas. The turbine has the flow path forming plate that defines a portion of a combustion gas flow path through which the combustion gas flows.

[0012] According to one aspect of the present disclosure, the gas path surface and the end surface of the flow path forming plate can be effectively cooled.

[0013] FIG. 4 is a schematic cross-sectional view of a gas turbine according to an embodiment of the present disclosure. FIG. 4 is a cross-sectional view of a main portion of a gas turbine according to an embodiment of the present disclosure. FIG. 4 is a perspective view of a stator vane according to an embodiment of the present disclosure. FIG. 4 is a cross-sectional view taken along a camber line of a stator vane according to an embodiment of the present disclosure. FIG. 4 is a cross-sectional view taken along line VI-VI in FIG. 4. FIG. 4 is a cross-sectional view taken along line VII-VII in FIG. 4. FIG. 4 is a cutaway perspective view of a main portion of a shroud according to the present disclosure. FIG. 4 is a cutaway perspective view of a main portion of an aft end portion of an outer shroud body according to the present disclosure. FIG. 4 is an explanatory view for explaining the surface shapes of a second gas path defining surface and a second end defining surface in an aft end passage of an outer shroud according to the present disclosure. FIG. 4 is a cutaway perspective view of a main portion of an aft end portion of an inner shroud body according to the present disclosure. FIG. 4 is an explanatory view for explaining the surface shapes of a gas path defining surface and an end defining surface in an aft end air passage of an inner shroud according to the present disclosure. 10A and 10B are explanatory views for explaining the surface shapes of a gas path defining surface and an end defining surface in a rear end passage of an inner shroud of a modified example according to the present disclosure.

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

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

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

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

[0018] The compressor 10 is disposed upstream Dau of the turbine 30 .

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

[0020] As shown in Figures 1 and 2, the compressor rotor 11 has a rotor shaft 12 extending in an axial direction Da about an axis Ar, and a plurality of rotor blade rows 13 attached to the rotor shaft 12. The plurality of rotor blade rows 13 are aligned in the axial direction Da. Each rotor blade row 13 is made up of a plurality of rotor blades aligned in a circumferential direction Dc. One of a plurality of stator blade rows 15 is arranged on the downstream side Dad of each of the plurality of rotor blade rows 13. Each stator blade row 15 is provided inside a compressor casing 18. Each stator blade row 15 is made up of a plurality of stator blades aligned in the circumferential direction Dc.

[0021] The turbine rotor 31 has a rotor shaft 32 extending in the axial direction Da centered on the axis Ar, and a plurality of rotor blade rows 33 attached to the rotor shaft 32. The plurality of rotor blade rows 33 are aligned in the axial direction Da. Each rotor blade row 33 is composed of a plurality of rotor blades 34 aligned in the circumferential direction Dc. One of a plurality of stator blade rows 35 is arranged on the upstream side Dau of each of the plurality of rotor blade rows 33. Each stator blade row 35 is provided inside a turbine casing 38. Each stator blade row 35 is composed of a plurality of stator blades 36 aligned in the circumferential direction Dc.

[0022] The annular space between the outer circumferential side of the rotor shaft 32 and the inner circumferential side of the turbine casing 38, in which the rotor blade row 33 and the stator blade row 35 are arranged in the axial direction Da, forms a combustion gas flow path 39 through which the combustion gas G from the combustor 20 flows. This combustion gas flow path 39 forms an annular shape centered on the axis Ar and extends in the axial direction Da.

[0023] The rotor blade 34 has a blade body 34b extending in the radial direction Dr and a platform 34p connected to the end of the inner Dri of the blade body 34b. The blade body 34b has an airfoil-shaped cross section perpendicular to the direction in which the blade body 34b extends. The platform 34p extends in a direction perpendicular to the direction in which the blade body 34b extends. The platform 34p defines a portion of the edge of the inner Dri of the combustion gas flow path 39. Therefore, the platform 34p is a flow path forming plate that defines a portion of the combustion gas flow path 39.

[0024] The stator vane 36 has a blade body 36b extending in the radial direction Dr, an outer shroud 36o connected to an end of the outer side Dr of the blade body 36b, and an inner shroud 36i connected to an end of the inner side Dr of the blade body 36b. The blade body 36b has an airfoil-shaped cross section perpendicular to the direction in which the blade body 36b extends. Both the outer shroud 36o and the inner shroud 36i extend in a direction perpendicular to the direction in which the blade body 36b extends.

[0025] The outer shroud 36o of the stator vane 36 defines a portion of the edge of the outer side Dro of the combustion gas flow path 39. The inner shroud 36i of the stator vane 36 defines a portion of the edge of the inner side Dri of the combustion gas flow path 39. Thus, both the outer shroud 36o and the inner shroud 36i are flow path forming plates that define a portion of the combustion gas flow path 39.

[0026] In addition to the plurality of stator vanes 36, a plurality of ring segments 37 are provided inside the turbine casing 38. The ring segments 37 are located at positions where the rotor blade rows 33 are present in the axial direction Da, on the outside Dro of the rotor blade rows 33. Therefore, the ring segments 37 are located between the plurality of stator blade rows 35 lined up in the axial direction Da. The ring segments 37 define part of the edge of the outside Dro of the combustion gas flow path 39. Therefore, the ring segments 37 are also flow path forming plates that define part of the combustion gas flow path 39.

[0027] The combustor 20 is attached to the intermediate casing 6. As shown in FIG. 2 , the combustor 20 has a transition piece (or combustion piece) 22 in which fuel F is burned, and a plurality of burners 21 that inject fuel into the transition piece 22.

[0028] A cooling device 40 is connected to the gas turbine of this embodiment. The cooling device 40 has an extraction line 41, a cooler 42, a boost compressor 43, and a cooling air line 44. One end of the extraction line 41 is connected to the intermediate casing 6, and the other end of the extraction line 41 is connected to an inlet of the boost compressor 43. The extraction line 41 is capable of extracting compressed air in the intermediate casing 6 to the outside of the gas turbine casing 8. The cooler 42 is provided in the extraction line 41 and is capable of cooling the compressed air flowing through the extraction line 41. The boost compressor 43 is capable of increasing the pressure of the compressed air cooled by the cooler 42. The cooling air line 44 has one end and multiple other ends. One end of the cooling air line 44 is connected to a discharge port of the boost compressor 43. The multiple other ends of the cooling air line 44 are connected to any of multiple high-temperature components, such as the stator vanes 36, that are exposed to the combustion gas G. This cooling air line 44 can guide compressed air from the boost compressor 43 as cooling air Ac1 to the high-temperature components.

[0029] As described above, the platform 34p of the rotor blade 34, the outer shroud 36o and the inner shroud 36i of the stator vane 36, and the ring segment 37 are all flow passage forming plates. Therefore, hereinafter, an embodiment of a stator vane having a flow passage forming plate will be described.

[0030] "Embodiments of Stator Vanes" Embodiments of the stator vanes will be described with reference to Figures 3 to 12. Note that the stator vanes described below are all specific examples of the stator vanes 36 described above in the "Embodiments of Gas Turbines."

[0031] As shown in FIG. 3 , the stator vane 50 of this embodiment includes a blade body 51, an inner shroud 60i, and an outer shroud 60o. The blade body 51 has an airfoil-shaped cross section and extends in a blade height direction having a component perpendicular to the cross section. As shown in FIG. 2 , when the stator vane 50 (36) is attached to the turbine casing 38, the blade height direction corresponds to the radial direction Dr. The blade body 51 (36b) is disposed in a combustion gas flow path 39 (see FIG. 2 ) through which the combustion gas G flows. The inner shroud 60i is provided at an end of the inner side Dri of the blade body 51 in the radial direction Dr. In other words, the inner shroud 60i is provided at one end of the blade body 51 in the blade height direction. The inner shroud 60i extends in a direction perpendicular to the blade height direction. The inner shroud 60i defines the edge of the inner side Dri of the annular combustion gas flow path 39 in the radial direction Dr. The outer shroud 60o is provided at the end of the outer side Dro of the blade body 51 in the radial direction Dr. In other words, the outer shroud 60o is provided at the other end of the blade body 51 in the blade height direction. This outer shroud 60o also extends in a direction perpendicular to the blade height direction. The outer shroud 60o defines the edge of the outer side Dro of the annular combustion gas flow path 39 in the radial direction Dr. Therefore, both the inner shroud 60i and the outer shroud 60o are flow path forming plates that define part of the combustion gas flow path 39, as described above in the "Embodiment of a Gas Turbine" section.

[0032] 3 to 7, the blade body 51 has an upstream end Dau that forms a leading edge 52 and a downstream end Dad that forms a trailing edge 53. Of the surfaces of this blade body 51 facing the circumferential direction Dc, the convex surface forms a suction side surface 54 (= negative pressure surface) and the concave surface forms a ventral side surface 55 (= positive pressure surface). For convenience of the following explanation, the side toward which the ventral side surface 55 of the blade body 51 faces in the circumferential direction Dc is referred to as a first side Dc1, and the side toward which the suction side surface 54 of the blade body 51 faces in the circumferential direction Dc is referred to as a second side Dc2.

[0033] As shown in FIGS. 3, 4, and 7, the inner shroud 60i, which is a flow passage forming plate, includes an inner shroud main body 61i and a peripheral wall 65i. The inner shroud main body 61i includes a gas path surface 64p facing the outer side Dro, a counter-gas path surface 64a facing the inner side Dri, a front end face 62f that is an end face on the upstream side Dau, a rear end face 62b that is an end face on the downstream side Dad, a pressure side end face 63p that is an end face on the circumferential pressure first side Dc1, and a suction side end face 63n that is an end face on the second side Dc2. The front end face 62f and the rear end face 62b are substantially parallel. The pressure side end face 63p and the suction side end face 63n are also substantially parallel. Therefore, when viewed from the radial direction Dr, the inner shroud main body 61i has a parallelogram shape, as shown in FIG. 7.

[0034] The peripheral wall 65i protrudes from the anti-gas path surface 64a of the inner shroud main body 61i toward the inner side Dri (opposite the flow path side). The peripheral wall 65i is provided along the end face of the inner shroud main body 61i. The peripheral wall 65i has a front wall 65f and a rear wall 65b that face each other in the axial direction Da, and a pressure side wall 65p and a suction side wall 65n that face each other in the circumferential direction Dc. The front wall 65f is provided along a front end surface 62f of the inner shroud main body 61i. The rear wall 65b is provided along a rear end surface 62b of the inner shroud main body 61i. The pressure side wall 65p is provided along a pressure side end surface 63p of the inner shroud main body 61i. The suction side wall 65n is provided along a suction side end surface 63n of the inner shroud main body 61i. The inner shroud 60i has a recess 66 formed by the inner shroud main body 61i and the peripheral wall 65i, the recess 66 being recessed toward the outer side Dro. The first side Dc1 surface of the ventral side wall 65p is flush with the ventral side end surface 63p of the inner shroud main body 61i. The second side Dc2 surface of the suction side wall 65n is flush with the suction side end surface 63n of the inner shroud main body 61i. The rear wall 65b is formed along the rear end surface 62b of the inner shroud main body 61i, but is formed upstream Dau of the rear end surface 62b. Therefore, the surface of the anti-gas path surface 64a of the shroud main body 61i that is upstream Dau with respect to the rear wall 65b forms the bottom surface of the recess 66. Furthermore, of the anti-gas path surface 64a of the shroud body 61i, the surface on the downstream side Dad with respect to the rear wall 65b does not form the bottom surface of the recess 66, but forms an outer anti-gas path surface 64ao. The outer anti-gas path surface 64ao of the inner shroud 60i is formed so as to gradually approach the gas path surface 64p as it moves toward the downstream side Dad.

[0035] As shown in Fig. 4, a stator vane 50 constituting one of the plurality of stator vane rows 35 shown in Fig. 2 is provided with a retainer 69 that protrudes from the pressure side wall 65p and the suction side wall 65n of the inner shroud 60i to the inner Dri. The retainer 69 is located between the front wall 65f and the rear wall 65b in the axial direction Da, and is formed from the pressure side end face 63p to the suction side end face 63n. The retainer 69 contacts the outer Dro end of the inner cover 7 fixed to the gas turbine casing 8, and serves to support the inner Dri portion of the stator vane 50 on the outer Dro end of the inner cover 7. A retainer passage 69p that penetrates the retainer 69 in the axial direction Da is formed.

[0036] As shown in Figures 3, 4, and 6, the outer shroud 60o, which is a flow path forming plate, has an outer shroud main body 61o and a peripheral wall 65o. Like the inner shroud main body 61i, the outer shroud main body 61o also has a gas path surface 64p, an anti-gas path surface 64a, a front end surface 62f, a rear end surface 620b, a ventral end surface 63p, and a suction side end surface 63n. Like the inner shroud main body 61i, the outer shroud main body 61o also has a parallelogram shape when viewed from the radial direction Dr. Note that the gas path surface 64p of the inner shroud main body 61i faces the outer side Dro, while the gas path surface 64p of the outer shroud main body 61o faces the inner side Dri.

[0037] The peripheral wall 65o protrudes from the anti-gas path surface 64a of the outer shroud body 61o toward the outer side Dro (opposite the flow path side). The peripheral wall 65o is provided along the end face of the outer shroud body 61o. Like the peripheral wall 65i of the inner shroud 60i, the peripheral wall 65o of the outer shroud 60o also has a front wall 65f, a rear wall 65b, a pressure side wall 65p, and a suction side wall 65n. The front wall 65f is provided along a front end face 62f of the outer shroud body 61o. The rear wall 65b is provided along a rear end face 620b of the outer shroud body 61o. The pressure side wall 65p is provided along a pressure side end face 63p of the outer shroud body 61o. The suction side wall 65n is provided along a suction side end face 63n of the outer shroud body 61o. In the outer shroud 60o, a recess 66 recessed toward the inner side Dri is formed by the outer shroud main body 61o and the peripheral wall 65o. The surface of the first side Dc1 of the pressure side wall 65p and the pressure side end surface 63p of the outer shroud main body 61o are flush with each other. The surface of the second side Dc2 of the suction side wall 65n and the suction side end surface 63n of the outer shroud main body 61o are flush with each other.

[0038] 3 and 4, the blade body 51 has a first blade passage 71, a second blade passage 72, a third blade passage 73, a fourth blade passage 74, a plurality of leading edge injection passages 75, and a plurality of trailing edge injection passages 76. The first blade passage 71, the second blade passage 72, the third blade passage 73, and the fourth blade passage 74 are aligned in this order along the camber line CL of the blade body 51 from the leading edge 52 side to the trailing edge 53 side of the blade body 51. The first blade passage 71, the second blade passage 72, the third blade passage 73, and the fourth blade passage 74 all extend in the radial direction Dr. The ends of the outer Dro of the first blade passage 71, the second blade passage 72, the third blade passage 73, and the fourth blade passage 74 all open at positions outer than the opposite gas path surface 64a of the outer shroud main body 61o. The ends of the inner Dri of the first blade passage 71 and the fourth blade passage 74 are closed by the inner shroud body 61i. The ends of the inner Dri of the second blade passage 72 and the third blade passage 73 open at positions inner Dri than the anti-gas path surface 64a of the inner shroud body 61i. The multiple leading edge injection passages 75 penetrate the leading edge portion of the blade body 51 from the inner peripheral surface of the first blade passage 71 to the surface of the outer surface of the blade body 51 near the leading edge 52 so that a portion of the cooling air Ac1 flowing through the first blade passage 71 is injected from near the leading edge of the blade body 51 into the combustion gas flow path outside the blade body 51. The multiple trailing edge injection passages 76 penetrate the trailing edge portion of the blade body 51 from the inner surface of the fourth blade passage 74 to the surface of the outer surface of the blade body 51 near the trailing edge 53 so that a portion of the cooling air Ac1 flowing through the fourth blade passage 74 is injected from the trailing edge 53 of the blade body 51 into the combustion gas flow path outside the blade body 51.

[0039] As shown in Fig. 5, a thermal barrier coating (TBC) layer 56 is applied to the outer surface of the blade body 51, the gas path surface 64p of each shroud body 61i, 61o, and the end surface of each shroud body 61i, 61o. This thermal barrier coating layer 56 is made of ZrO ２ The thermal barrier coating layer 56 is also applied to an outer anti-gas path surface 64ao of the inner shroud body 61i and a surface of the retainer 69 facing the downstream side Dad.

[0040] 4, the outer shroud 60o of the present embodiment is provided with a blade air passage cover 57, a sealing plate 58, and an impingement plate 59. The inner shroud 60i of the present embodiment is also provided with a blade air passage cover 57, a sealing plate 58, and an impingement plate 59.

[0041] The blade air passage cover 57 provided on the outer shroud 60o is connected to the opposite gas path surface 64a of the outer shroud body 61o so as to collectively cover the openings at the ends of the outer Dro of the first blade passage 71, the second blade passage 72, the third blade passage 73, and the fourth blade passage 74. The cooling air line 44 shown in FIG. 2 is connected to this blade air passage cover 57. Therefore, a portion of the cooling air Ac1 from the cooling device 40 flows into the blade air passage cover 57 and then into the first blade passage 71, the second blade passage 72, the third blade passage 73, and the fourth blade passage 74. As shown in FIGS. 4 and 8 , the sealing plate 58 divides the space within the recess 66 of the outer shroud 60o into an outer space on the opposite gas path side to the outer Dro and a cooling air space 67 on the inner gas path side. The impingement plate 59 divides the cooling air space 67 into a first space 67a on the outer side Dro (opposite the flow path side) and a second space 67b on the inner side Dri (flow path side). The impingement plate 59 has a plurality of through holes 59a formed therethrough in the radial direction Dr. The cooling air Ac1 in the first space 67a passes through the plurality of through holes 59a of the impingement plate 59 and flows into the second space 67b. At this time, the cooling air Ac1 that has passed through the plurality of through holes 59a of the impingement plate 59 impinges and cools the anti-gas path surface 64a of the outer shroud body 61o. A cooling air exhaust line 45 is connected to the impingement plate 59. This cooling air exhaust line 45 extends from the impingement plate 59 to the outer side Dro and penetrates the sealing plate 58. The cooling air Ac1 that has flowed into the second space 67b and impingement-cooled the anti-gas path surface 64a of the outer shroud body 61o is guided through this cooling air exhaust line 45 into, for example, the intermediate casing 6. Note that this cooling air Ac1 may also be guided through this cooling air exhaust line 45 to the transition piece 22 of the combustor 20 and used to cool the transition piece 22.

[0042] The blade air passage cover 57 provided on the inner shroud 60i is connected to the opposite gas path surface 64a of the inner shroud body 61i so as to collectively cover the openings at the ends of the inner Dri of the second blade passage 72 and the inner Dri of the third blade passage 73. As shown in FIGS. 4, 5, and 8, the sealing plate 58 divides the space within the recess 66 of the inner shroud 60i into an outer space (opposite the flow path side) of the inner Dri and a cooling air space 67 on the outer Dro (flow path side). The impingement plate 59 divides this cooling air space 67 into a first space 67a on the inner Dri (opposite the flow path side) and a second space 67b on the outer Dro (flow path side). The impingement plate 59 has a plurality of through holes 59a formed therethrough in the radial direction Dr. The cooling air Ac1 in the first space 67a flows into the second space 67b through the plurality of through holes 59a of the impingement plate 59. At this time, the cooling air Ac1 that has passed through the multiple through holes 59a of the impingement plate 59 impinge-cools the anti-gas path surface 64a of the inner shroud body 61i. A cooling air exhaust line 45 is connected to the impingement plate 59. This cooling air exhaust line 45 extends from the impingement plate 59 to the inner side Dri and penetrates the sealing plate 58. The cooling air Ac1 that has flowed into the second space 67b and impinge-cooled the anti-gas path surface 64a of the outer shroud body 61o is guided via this cooling air exhaust line 45 into, for example, the intermediate casing 6.

[0043] 4 and 6 , the outer shroud body 61o has a plurality of internal passages 80, a front inlet passage 85, a rear inlet passage 86, a first outlet passage 87a, a third outlet passage 88a, a second outlet passage 87b, a fourth outlet passage 88b, and a square injection passage 89. Each of the plurality of internal passages 80 is formed along one of the plurality of end faces of the outer shroud body 61o. The plurality of internal passages 80 includes a front end passage 81, a first lateral passage 82a, a second lateral passage 82b, a rear end passage 83o, a third lateral passage 84a, and a fourth lateral passage 84b.

[0044] The front end passage 81 extends along the gas path surface 64p and the front end face 62f of the outer shroud body 61o in the circumferential direction Dc, which is the direction in which the gas path surface 64p and the front end face 62f widen. The front end passage 81 extends in the circumferential direction Dc from a position near the pressure side end face 63p of the outer shroud body 61o to a position near the suction side end face 63n of the outer shroud body 61o. The front end passage 81 has a front inlet (second inlet) 81e, located approximately midway in the direction in which the front end passage 81 extends, that can introduce cooling air Ac1 into the front end passage 81. A portion of the front end passage 81 closer to the pressure side end face 63p than the front inlet 81e forms a front end first passage 81a, and a portion closer to the suction side end face 63n than the front inlet 81e forms a front end second passage 81b.

[0045] The front inlet passage 85 connects the front end passage 81 and the first blade passage 71. The front inlet passage 85 has the aforementioned front inlet 81e that opens at the second defining plane of the front end passage 81. Therefore, a portion of the cooling air Ac1 in the first blade passage 71 can flow into the front end passage 81 through this front inlet passage 85.

[0046] The first transverse passage 82a extends along the gas path surface 64p and the ventral end face 63p of the outer shroud body 61o, in the direction in which the gas path surface 64p widens and the ventral end face 63p widens. The first transverse passage 82a is connected to the end of the front end first passage 81a on the ventral end face 63p side. The connection portion of the first transverse passage 82a with the front end first passage 81a forms an inlet of the first transverse passage 82a. The first transverse passage 82a extends from the connection portion with the front end first passage 81a to approximately the middle position of the outer shroud body 61o. The first outlet passage 87a is connected to the downstream end Dad of the first transverse passage 82a, and as shown in FIG. 8 , connects the first transverse passage 82a with the first space 67a of the outer shroud 60o. Therefore, the cooling air Ac1 in the front end first passage 81a can flow into the first lateral passage 82a and then into the first space 67a via the first outlet passage 87a.

[0047] The second transverse passage 82b extends along the gas path surface 64p and the suction side end face 63n of the outer shroud body 61o, in the direction in which the gas path surface 64p and the suction side end face 63n widen. The second transverse passage 82b is connected to the end of the front end second passage 81b on the suction side end face 63n side. The connection portion of the second transverse passage 82b with the front end second passage 81b forms an inlet of the second transverse passage 82b. The second transverse passage 82b extends from the connection portion with the front end second passage 81b to approximately the middle position in the axial direction Da of the outer shroud body 61o. The second outlet passage 87b is connected to the downstream end Dad of the second transverse passage 82b, and as shown in FIG. 8 , connects the second transverse passage 82b with the first space 67a of the outer shroud 60o. Therefore, the cooling air Ac1 in the front end second passage 81b can flow into the second transverse passage 82b, and then into the first space 67a via the second outlet passage 87b.

[0048] The rear end passage 83o extends along the gas path surface 64p and the rear end face 620b of the outer shroud body 61o in the circumferential direction Dc, which is the direction in which the gas path surface 64p and the rear end face 620b widen. The rear end passage 83o extends in the circumferential direction Dc from a position near the ventral end face 63p of the outer shroud body 61o to a position near the suction end face 63n of the outer shroud body 61o.

[0049] The rear end passage 83o is a passage separate from the air passage described below and is formed as a separate passage through which cooling air flows. That is, the rear end passage 83o is formed independently of the air passage. For example, the rear end passage 83o is formed apart from the rear end passage 83i described below when viewed from the circumferential direction Dc.

[0050] The rear end passage 83o has a rear inlet (second inlet) 830e at a substantially midpoint in the direction in which the rear end passage 83o extends, through which cooling air Ac1 can be introduced into the rear end passage 83o. A portion of the rear end passage 83o closer to the ventral end face 63p than the rear inlet 830e forms a rear end first passage 83a, while a portion closer to the suction end face 63n than the rear inlet 830e forms a rear end second passage 83b. The rear end first passage 83a extends from the rear inlet 830e toward a first side Dc1 of both sides in the circumferential direction Dc. The rear end second passage 83b extends from the rear inlet 830e toward a second side Dc2 opposite the first side Dc1 in the circumferential direction Dc.

[0051] The rear inlet passage 86 connects the rear end passage 83o and the fourth blade passage 74. The rear inlet passage 86 has the aforementioned rear inlet 830e that opens at the second boundary plane of the rear end passage 83o. Therefore, a portion of the cooling air Ac1 in the fourth blade passage 74 can flow into the rear end passage 83o via this rear inlet passage 86.

[0052] The third transverse passage 84a extends along the gas path surface 64p and the ventral end face 63p of the outer shroud body 61o, in the direction in which the gas path surface 64p and the ventral end face 63p widen. The third transverse passage 84a is connected to the end of the rear first passage 83a on the ventral end face 63p side. A connection portion of the third transverse passage 84a with the rear first passage 83a forms an inlet of the third transverse passage 84a. The third transverse passage 84a extends from the connection portion with the rear first passage 83a to approximately the middle position in the axial direction Da of the outer shroud body 61o. The third outlet passage 88a is connected to an upstream end Dau of the third transverse passage 84a, and as shown in FIG. 8 , connects the third transverse passage 84a with the first space 67a of the outer shroud 60o. Therefore, the cooling air Ac1 in the rear end first passage 83a can flow into the third transverse passage 84a and then into the first space 67a via the third outlet passage 88a.

[0053] The angular injection passage 89 penetrates from the end of the rear end first passage 83a on the ventral side end face 63p side to the corner between the rear end face 620b and the ventral side end face 63p of the outer shroud 60o, and through the corner between the rear end face 620b and the ventral side end face 63p of the outer shroud 60o, so that a portion of the cooling air Ac1 flowing through the end of the rear end first passage 83a on the ventral side end face 63p side is injected into the combustion gas flow path from the corner between the rear end face 620b and the ventral side end face 63p of the outer shroud 60o.

[0054] The fourth transverse passage 84b extends along the gas path surface 64p and the suction side end face 63n of the outer shroud body 61o, in the direction in which the gas path surface 64p and the suction side end face 63n widen. The fourth transverse passage 84b is connected to the end of the rear end second passage 83b on the suction side end face 63n side. The connection portion of the fourth transverse passage 84b with the rear end second passage 83b forms an inlet of the fourth transverse passage 84b. The fourth transverse passage 84b extends from the connection portion with the rear end second passage 83b to approximately the middle position in the axial direction Da of the outer shroud body 61o. The fourth outlet passage 88b is connected to the upstream end Dau end of the third transverse passage 84a, and as shown in FIG. 8 , connects the fourth transverse passage 84b with the first space 67a of the outer shroud 60o. Therefore, the cooling air Ac1 in the rear end second passage 83b can flow into the fourth transverse passage 84b, and then into the first space 67a via the fourth outlet passage 88b.

[0055] As shown in FIG. 9 , the rear end passage 83o is defined by a plurality of second defining surfaces. All of the second defining surfaces extend in the circumferential direction Dc. The second defining surfaces include a second gas path defining surface 91o, a second end defining surface 92o, a counter-gas path defining surface 93, and an inner defining surface 94. The second gas path defining surface 91o is back-to-back with the gas path surface 64p of the outer shroud body 61o. The counter-gas path defining surface 93 is spaced outwardly Dro from the second gas path defining surface 91o and faces the second gas path defining surface 91o. The second end defining surface 92o is back-to-back with the rear end surface 620b of the outer shroud body 61o. A gas path side edge of the second end defining surface 92o, which is the edge on the gas path surface 64p side, is connected to an end side edge of the second gas path defining surface 91o, which is the edge on the rear end surface 620b side, via a second corner 950. An edge of the second end defining surface 92o on the side opposite to the gas path surface 64a is connected to an edge of the opposite gas path defining surface 93 on the side opposite to the rear end surface 620b. The inner defining surface 94 is spaced upstream Dau from the second end defining surface 92o and faces the second end defining surface 92o. The aforementioned rear inlet 830e is formed in this inner defining surface 94. The rear inlet 830e is formed in the inner defining surface 94 so that the cooling air flowing into the rear end passage 83o from the rear inlet 830e collides with the second end defining surface 92o. The edge of this inner defining surface 94 on the gas path surface 64p side is connected to the second gas path defining surface 91o, and the edge of this inner defining surface 94 on the opposite gas path surface 64a side is connected to the opposite gas path defining surface 93.

[0056] The angle of the second end defining surface 92o relative to the second gas path defining surface 91o is approximately a right angle. That is, the second corner portion 950 is formed at approximately a right angle. The angle of the anti-gas path defining surface 93 relative to the second end defining surface 92o is approximately a right angle. The angle of the inner defining surface 94 relative to the anti-gas path defining surface 93 is approximately a right angle. The angle of the second gas path defining surface 91o relative to the inner defining surface 94 is approximately a right angle. Therefore, the cross-sectional shape of the rear end passage 83o is approximately rectangular.

[0057] As shown in FIGS. 9 and 10 , the second gas path defining surface 91o is an uneven surface in which second gas path bottom surfaces 91ao and second gas path protruding surfaces 91bo located on the side of the second gas path bottom surface 91ao away from the gas path surface 64p are alternately arranged in the circumferential direction Dc. That is, the second gas path defining surface 91o forms first vertical turbulators 917. Accordingly, the first vertical turbulators 917 are formed so as to protrude toward the interior of the rear end passage 83o. Furthermore, a plurality of first vertical turbulators 917 are formed spaced apart in the circumferential direction Dc. The plurality of first vertical turbulators 917 extend perpendicular to the circumferential direction Dc. The first vertical turbulators 917 are formed by the second gas path bottom surface 91ao, the second gas path protruding surfaces 91bo, and the second gas path connecting surface 91co. The second gas path bottom surface 91ao and the second gas path protruding surface 91bo are connected by a second gas path connecting surface 91co. The second gas path bottom surface 91ao, the second gas path protruding surface 91bo, and the second gas path connecting surface 91co all extend in a direction perpendicular to the circumferential direction Dc.

[0058] The first vertical turbulators 917 have a long, narrow rail-like shape that crosses the second gas path bottom surface 91ao and protrudes from the second gas path bottom surface 91ao. The first vertical turbulators 917 have a rectangular cross section. Furthermore, the width of the upper surface of the convex portion of the first vertical turbulators 917 (width in the circumferential direction Dc) is narrower than the width of the bottom surface of the concave portion. Specifically, the upper surface of the convex portion is the second gas path protruding surface 91bo. Furthermore, the bottom surface of the concave portion is the second gas path bottom surface 91ao sandwiched between two second gas path protruding surfaces 91bo. The width of the second gas path protruding surface 91bo, which is the upper surface of the convex portion, is preferably ½ or less of the width of the second gas path bottom surface 91ao, which is the bottom surface of the concave portion. Furthermore, the width of the second gas path protruding surface 91bo is more preferably ⅓ or less of the width of the second gas path bottom surface 91ao.

[0059] The second end defining surface 92o is an uneven surface in which second end bottom surfaces 92ao and second end protruding surfaces 92bo located away from the rear end surface 620b relative to the second end bottom surfaces 92ao are alternately arranged in the circumferential direction Dc. That is, the second end defining surface 92o forms second vertical turbulators 927. Therefore, the second vertical turbulators 927 are formed to protrude toward the interior of the rear end passage 83o. Furthermore, multiple second vertical turbulators 927 are formed spaced apart in the circumferential direction Dc. The multiple second vertical turbulators 927 extend perpendicular to the circumferential direction Dc. The second vertical turbulators 927 are formed by the second end bottom surfaces 92ao, the second end protruding surfaces 92bo, and the second end connecting surfaces 92co. The second end bottom surfaces 92ao and the second end protruding surfaces 92bo are connected by the second end connecting surfaces 92co. The second end bottom surface 92ao, the second end protruding surface 92bo, and the second end connecting surface 92co all extend in a direction perpendicular to the circumferential direction Dc and parallel to an imaginary plane VP1 that includes the gas path connecting surface 91ci. That is, the second gas path bottom surface 91ao, the second gas path protruding surface 91bo, the second gas path connecting surface 91co, the second end bottom surface 92ao, the second end protruding surface 92bo, and the second end connecting surface 92co all extend in a direction parallel to the imaginary plane VP1.

[0060] The second vertical turbulators 927 are shaped like long, narrow rails that cross the second end bottom surface 92ao and protrude from the second end bottom surface 92ao. The second vertical turbulators 927 have a rectangular cross section. Furthermore, the width of the top surface of the convex portion of the second vertical turbulators 927 (the width in the circumferential direction Dc) is narrower than the width of the bottom surface of the concave portion. Specifically, the top surface of the convex portion is the second end protruding surface 92bo. The bottom surface of the concave portion is the second end bottom surface 92ao, which is sandwiched between the two second end protruding surfaces 92bo. The width of the second end protruding surface 92bo, which is the top surface of the convex portion, is preferably no more than half the width of the second end bottom surface 92ao, which is the bottom surface of the concave portion. Furthermore, the width of the second end protruding surface 92bo is more preferably no more than one-third the width of the second end bottom surface 92ao.

[0061] The position in the circumferential direction Dc of the gas path side edge of the second end protruding surface 92bo is different from the position in the circumferential direction Dc of the end side edge of the second gas path protruding surface 91bo. Therefore, the positions in the circumferential direction Dc of the first vertical turbulator 925 and the second vertical turbulator 927 facing the second corner portion 950 are different from each other. The ends of the first vertical turbulator 925 and the second vertical turbulator 927 facing the second corner portion 950 are arranged apart from each other in the circumferential direction Dc. In other words, the first vertical turbulator 925 and the second vertical turbulator 927 are not arranged at the same position in the circumferential direction Dc. The first vertical turbulator 925 and the second vertical turbulator 927 are arranged alternately in the circumferential direction Dc so that a convex portion of one second vertical turbulator 927 is arranged between adjacent convex portions of two first vertical turbulators 925. Therefore, the first vertical turbulators 925 and the second vertical turbulators 927 are arranged alternately in the circumferential direction Dc so that one second vertical turbulator 927 is arranged between two adjacent first vertical turbulators 925 in the circumferential direction Dc.

[0062] The front end passage 81, the first lateral passage 82a, the second lateral passage 82b, the third lateral passage 84a, and the fourth lateral passage 84b in the outer shroud body 61o are defined by a second gas path defining surface, a second end defining surface, a counter-gas path defining surface, and an inner defining surface, similar to the aft end passage 83o in the outer shroud body 61o. That is, the front end passage 81, the first lateral passage 82a, the second lateral passage 82b, the third lateral passage 84a, and the fourth lateral passage 84b in the outer shroud body 61o are formed as separated passages. The second gas path defining surface and the second end defining surface of these separated passages also form a plurality of first vertical turbulators 917 and a plurality of second vertical turbulators 927, similar to the second gas path defining surface 91o and the second end defining surface 92o of the aft end passage 83o in the outer shroud body 61o.

[0063] 4 and 7 , the inner shroud body 61i, like the outer shroud body 61o, has multiple internal passages 80, a front inlet passage 85, a rear inlet passage 86, a first outlet passage 87a, a third outlet passage 88a, a fourth outlet passage 88b, and a square injection passage 89. Each of the multiple internal passages 80 is formed along one of the multiple end faces of the inner shroud body 61i. Like the multiple internal passages 80 of the outer shroud body 61o, the multiple internal passages 80 have a front end passage 81, a first lateral passage 82a, a second lateral passage 82b, a rear end passage 83i, a third lateral passage 84a, and a fourth lateral passage 84b.

[0064] The front end passage 81 extends along the gas path surface 64p and the front end face 62f of the inner shroud body 61i in the circumferential direction Dc, which is the direction in which the gas path surface 64p and the front end face 62f widen. The front end passage 81 extends in the circumferential direction Dc from a position near the pressure side end face 63p of the inner shroud body 61i to a position near the suction side end face 63n of the inner shroud body 61i. The front end passage 81 has a front inlet 81e, which can introduce cooling air Ac1 into the front end passage 81, at a substantially midpoint in the direction in which the front end passage 81 extends. A portion of the front end passage 81 closer to the pressure side end face 63p than the front inlet 81e forms a front end first passage 81a, and a portion closer to the suction side end face 63n than the front inlet 81e forms a front end second passage 81b.

[0065] The front inlet passage 85 communicates the front end passage 81 with the second blade passage 72. The front inlet passage 85 has the aforementioned front inlet 81e that opens at the second defining plane of the front end passage 81. Therefore, a portion of the cooling air Ac1 in the second blade passage 72 can flow into the front end passage 81 through this front inlet passage 85.

[0066] The first transverse passage 82a extends along the gas path surface 64p and the ventral end face 63p of the inner shroud body 61i, in the direction in which the gas path surface 64p widens and the ventral end face 63p widens. The first transverse passage 82a is connected to the end of the front end first passage 81a on the ventral end face 63p side. A connection portion of the first transverse passage 82a with the front end first passage 81a forms an inlet of the first transverse passage 82a. The first transverse passage 82a extends from the connection portion with the front end first passage 81a to approximately the middle position in the axial direction Da of the inner shroud body 61i. The first outlet passage 87a is connected to the downstream end Dad of the first transverse passage 82a, and as shown in FIG. 8 , connects the first transverse passage 82a with the first space 67a of the inner shroud 60i. Therefore, the cooling air Ac1 in the front end first passage 81a can flow into the first lateral passage 82a and then into the first space 67a via the first outlet passage 87a.

[0067] The second transverse passage 82b extends along the gas path surface 64p and the suction side end face 63n of the inner shroud body 61i, in the direction in which the gas path surface 64p and the suction side end face 63n widen. The second transverse passage 82b is connected to the end of the front end second passage 81b on the suction side end face 63n side. The connection portion of the second transverse passage 82b with the front end second passage 81b forms an inlet of the second transverse passage 82b. The second transverse passage 82b extends from the connection portion with the front end second passage 81b to approximately the middle position in the axial direction Da of the inner shroud body 61i. The second outlet passage 87b is connected to the downstream end Dad of the second transverse passage 82b, and as shown in FIG. 8 , connects the second transverse passage 82b with the first space 67a of the inner shroud 60i. Therefore, the cooling air Ac1 in the front end second passage 81b can flow into the second transverse passage 82b, and then into the first space 67a via the second outlet passage 87b.

[0068] The front end passage 81, the first lateral passage 82a, the second lateral passage 82b, the third lateral passage 84a, and the fourth lateral passage 84b in the inner shroud body 61i are defined by a second gas path defining surface, a second end defining surface, a counter-gas path defining surface, and an inner defining surface, similar to the aft end passage 83o in the outer shroud body 61o. That is, in the present embodiment, the front end passage 81, the first lateral passage 82a, the second lateral passage 82b, the third lateral passage 84a, and the fourth lateral passage 84b in the inner shroud body 61i are formed as separated passages. Furthermore, the second gas path defining surface and the second end defining surface of these separated passages also form a plurality of first vertical turbulators 917 and a plurality of second vertical turbulators 927, similar to the second gas path defining surface 91o and the second end defining surface 92o of the aft end passage 83o in the outer shroud body 61o.

[0069] The rear end passage 83i extends along the gas path surface 64p and the rear end face 62b of the inner shroud body 61i in the circumferential direction Dc, which is the direction in which the gas path surface 64p and the rear end face 62b widen. The rear end passage 83i extends in the circumferential direction Dc from a position near the ventral end face 63p of the inner shroud body 61i to a position near the suction end face 63n of the inner shroud body 61i.

[0070] The rear end passage 83i is a passage separate from the separated passage and is formed as an air passage through which cooling air flows. That is, the rear end passage 83i is an air passage that is an internal passage 80 formed independently of the separated passage. For example, the rear end passage 83i is formed apart from the front end passage 81 when viewed from the circumferential direction Dc.

[0071] The rear end passage 83i has a rear inlet (inlet) 83e at approximately the middle in the direction in which the rear end passage 83i extends, through which cooling air AcI can be introduced into the rear end passage 83i. In the present embodiment, only the rear inlet 83e of the rear end passage 83i of the inner shroud main body 61i is an inlet. Of the rear end passage 83i, a portion closer to the ventral end face 63p with respect to the rear inlet 83e forms a rear end first passage 83a, and a portion closer to the suction end face 63n with respect to the rear inlet 83e forms a rear end second passage 83b. In the present embodiment, only the rear end first passage 83a of the inner shroud main body 61i is the first air passage, and only the rear end second passage 83b of the inner shroud main body 61i is the second air passage.

[0072] The rear inlet passage 86 connects the rear end passage 83i and the third blade passage 73. The rear inlet passage 86 extends from the third blade passage 73 toward the downstream side Dad perpendicular to the circumferential direction Dc (first direction). This rear inlet passage 86 has the aforementioned rear inlet 83e that opens at a boundary plane of the rear end passage 83i. Therefore, a portion of the cooling air Ac1 in the third blade passage 73 can flow into the rear end passage 83i via this rear inlet passage 86. In the present embodiment, the rear inlet passage 86 of the inner shroud body 61i is the inlet passage.

[0073] The third transverse passage 84a extends along the gas path surface 64p and the ventral end face 63p of the inner shroud body 61i, in the direction in which the gas path surface 64p and the ventral end face 63p widen. The third transverse passage 84a is connected to the end of the rear first passage 83a on the ventral end face 63p side. A connection portion of the third transverse passage 84a with the rear first passage 83a forms an inlet of the third transverse passage 84a. The third transverse passage 84a extends from the connection portion with the rear first passage 83a to approximately the middle position in the axial direction Da of the inner shroud body 61i. The third outlet passage 88a is connected to an end on the upstream side Dau of the third transverse passage 84a, and as shown in FIG. 8 , connects the third transverse passage 84a with the first space 67a of the inner shroud 60i. Therefore, the cooling air Ac1 in the rear end first passage 83a can flow into the third transverse passage 84a and then into the first space 67a via the third outlet passage 88a.

[0074] The angular injection passage 89 penetrates from the end of the rear first passage 83a on the ventral side end face 63p side to the corner between the rear end face 62b and the ventral side end face 63p of the outer shroud and through the corner between the rear end face 62b and the ventral side end face 63p of the inner shroud 60i so that a portion of the cooling air Ac1 flowing through the end of the rear first passage 83a on the ventral side end face 63p side is injected into the combustion gas flow path from the corner between the rear end face 62b and the ventral side end face 63p of the inner shroud 60i.

[0075] The fourth transverse passage 84b extends along the gas path surface 64p and the suction side end face 63n of the inner shroud body 61i and in the direction in which the gas path surface 64p and the suction side end face 63n widen. The fourth transverse passage 84b is connected to the end of the rear end second passage 83b on the suction side end face 63n side. A connection portion of the fourth transverse passage 84b with the rear end second passage 83b forms an inlet of the fourth transverse passage 84b. The fourth transverse passage 84b extends from the connection portion with the rear end second passage 83b to approximately the middle position in the axial direction Da of the inner shroud body 61i. The fourth outlet passage 88b is connected to the upstream end Dau end of the third transverse passage 84a and, as shown in FIG. 8 , connects the fourth transverse passage 84b with the first space 67a of the inner shroud 60i. Therefore, the cooling air Ac1 in the rear end second passage 83b can flow into the fourth transverse passage 84b, and then into the first space 67a via the fourth outlet passage 88b.

[0076] As shown in FIGS. 5 and 11 , the rear end passage 83i is defined by a plurality of defining surfaces. All of the defining surfaces extend in the circumferential direction Dc. The defining surfaces include a gas path defining surface 91i, an end defining surface 92i, a counter-gas path defining surface 93, and an inner defining surface 94. The gas path defining surface 91i is in a back-to-back relationship with the gas path surface 64p of the inner shroud body 61i. The counter-gas path defining surface 93 is spaced inwardly Dri from the gas path defining surface 91i and faces the gas path defining surface 91i. The end defining surface 92i is in a back-to-back relationship with the rear end surface 62b of the inner shroud body 61i. A gas path side edge of the end defining surface 92i, which is the edge on the gas path surface 64p side, is connected to an end side edge of the gas path defining surface 91i, which is the edge on the rear end surface 62b side, via a first corner 95. An edge of the end defining surface 92i on the side opposite to the gas path surface 64a is connected to an edge of the opposite to the gas path defining surface 93 on the side opposite to the rear end surface 62b. The inner defining surface 94 is spaced upstream Dau from the end defining surface 92i and faces the end defining surface 92i. The aforementioned rear inlet 83e is formed in this inner defining surface 94. The rear inlet 83e is formed in the inner defining surface 94 so that the cooling air flowing into the rear end passage 83i from the rear inlet 83e collides with the end defining surface 92i. The edge of this inner defining surface 94 on the gas path surface 64p side is connected to the gas path defining surface 91i, and the edge of this inner defining surface 94 on the opposite gas path surface 64a side is connected to the opposite gas path defining surface 93.

[0077] The end defining surface 92i is substantially parallel to the outer anti-gas path surface 64a of the inner shroud body 61i (see FIG. 5). Therefore, the angle of the end defining surface 92i with respect to the gas path defining surface 91i is an acute angle. That is, the first corner portion 95 is formed at an acute angle. Therefore, when viewed from the circumferential direction Dc, the second corner portion 950 is formed at an angle larger than that of the first corner portion 95. The angle of the anti-gas path defining surface 93 with respect to the end defining surface 92i is an obtuse angle. The angle of the inner defining surface 94 with respect to the anti-gas path defining surface 93 is substantially a right angle. The angle of the gas path defining surface 91i with respect to the inner defining surface 94 is substantially a right angle. Therefore, the cross-sectional shape of the rear end passage 83i is substantially trapezoidal.

[0078] As shown in FIGS. 11 and 12 , the gas path defining surface 91i of the rear end first passage 83a and the gas path defining surface 91i of the rear end second passage 83b are both uneven surfaces in which gas path bottom surfaces 91ai and gas path protruding surfaces 91bi located on the side of the gas path bottom surface 91ai that is farther from the gas path surface 64p are alternately arranged in the circumferential direction Dc. That is, the gas path defining surface 91i forms first turbulators 915. Therefore, the first turbulators 915 are formed so as to protrude toward the interior of the rear end passage 83i. Furthermore, multiple first turbulators 915 are formed spaced apart in the circumferential direction Dc. The multiple first turbulators 915 extend in an inclined direction so as to intersect with the circumferential direction Dc. The first turbulators 915 are formed by the gas path bottom surface 91ai, the gas path protruding surfaces 91bi, and the gas path connecting surfaces 91ci. The gas path bottom surface 91ai and the gas path protruding surface 91bi are connected by a gas path connecting surface 91ci. The gas path bottom surface 91ai, the gas path protruding surface 91bi, and the gas path connecting surface 91ci all extend in a direction intersecting the circumferential direction Dc. However, the gas path bottom surface 91ai, the gas path protruding surface 91bi, and the gas path connecting surface 91ci all extend in a direction inclined with respect to the circumferential direction Dc (first direction) so as to gradually move toward a circumferential downstream side Dcd (downstream side in the first direction) that moves away from the rear inlet 83e in the circumferential direction Dc (first direction) with increasing distance from the rear end surface 62b (first end surface) of the inner shroud main body 61i. The gas path bottom surface 91ai, the gas path protruding surface 91bi, and the gas path connecting surface 91ci extend at an angle θ of 45° to 75°, for example, 60°, with respect to the circumferential direction Dc (first direction). The circumferential downstream side Dcd (downstream side in the first direction) of the rear end first passage 83a is the first side Dc1, and the circumferential downstream side Dcd (downstream side in the first direction) of the rear end second passage 83b is the second side Dc2. Therefore, the multiple first turbulators 915 extend in a direction inclined with respect to the circumferential direction so as to gradually move away from the rear inlet 83e in the circumferential direction Dc with increasing distance from the first corner portion 95.

[0079] The first turbulators 915 have a long, narrow rail-like shape that diagonally crosses the gas path bottom surface 91ai and protrudes from the gas path bottom surface 91ai. The first turbulators 915 have a rectangular cross section. Furthermore, the width of the upper surface of the convex portion of the first turbulator 915 (width in the circumferential direction Dc) is narrower than the width of the bottom surface of the concave portion. Specifically, the upper surface of the convex portion is the gas path protruding surface 91bi. Furthermore, the bottom surface of the concave portion is the gas path bottom surface 91ai sandwiched between the two gas path protruding surfaces 91bi. The width of the gas path protruding surface 91bi, which is the upper surface of the convex portion, is preferably ½ or less of the width of the second gas path bottom surface 91ai, which is the bottom surface of the concave portion. Furthermore, the width of the gas path protruding surface 91bi is more preferably ⅓ or less of the width of the gas path bottom surface 91ai.

[0080] The end defining surfaces 92i of the rear end first passage 83a and the rear end second passage 83b are both uneven surfaces in which end bottom surfaces 92ai and end protruding surfaces 92bi located on the side away from the gas path surface 64p relative to the end bottom surfaces 92ai are alternately arranged in the circumferential direction Dc. That is, the end defining surfaces 92i form second turbulators 925. Accordingly, the second turbulators 925 are formed so as to protrude toward the interior of the rear end passage 83i. Furthermore, multiple second turbulators 925 are formed spaced apart in the circumferential direction Dc. The multiple second turbulators 925 extend in an inclined direction so as to intersect with the circumferential direction Dc. The second turbulators 925 are formed by end bottom surfaces 92ai, end protruding surfaces 92bi, and end connecting surfaces 92ci. The end bottom surfaces 92ai and the end protruding surfaces 92bi are connected by the end connecting surfaces 92ci. The end bottom surface 92ai, the end protruding surface 92bi, and the end connecting surface 92ci all extend in a direction intersecting the circumferential direction Dc. However, the end bottom surface 92ai, the end protruding surface 92bi, and the end connecting surface 92ci all extend in a direction inclined with respect to the circumferential direction Dc (first direction) so as to gradually move toward a circumferential downstream side Dcd (downstream side in the first direction) that moves away from the rear inlet 83e in the circumferential direction Dc (first direction) as they move away from the gas path surface 64p of the inner shroud body 61i. The extending direction of the end bottom surface 92ai, the end protruding surface 92bi, and the end connecting surface 92ci forms an angle θ of 45° to 75°, for example, an angle of 60°, with respect to the circumferential direction Dc (first direction). Therefore, the multiple second turbulators 925 extend in a direction inclined relative to the circumferential direction so as to gradually move away from the rear entrance 83e in the circumferential direction Dc as they move away from the first corner portion 95.

[0081] The second turbulators 925 are formed in the shape of long, thin rails that cross the end bottom surface 92ai and protrude from the end bottom surface 92ai. The second turbulators 925 have a rectangular cross section. Furthermore, the width of the upper surface of the convex portion of the second turbulator 925 (width in the circumferential direction Dc) is narrower than the width of the bottom surface of the recess. Specifically, the upper surface of the convex portion is the end protruding surface 92bi. Furthermore, the bottom surface of the recess is the end bottom surface 92ai sandwiched between the two end protruding surfaces 92bi. The width of the end protruding surface 92bi, which is the upper surface of the convex portion, is preferably ½ or less of the width of the end bottom surface 92ai, which is the bottom surface of the recess. Furthermore, the width of the end protruding surface 92bi is more preferably ⅓ or less of the width of the end bottom surface 92ai.

[0082] The position in the circumferential direction Dc of the gas path side edge of the end protruding surface 92bi is different from the position in the circumferential direction Dc of the end side edge of the gas path protruding surface 91bi. Therefore, the positions in the circumferential direction Dc of the first turbulators 915 and the second turbulators 925 facing the first corner portion 95 are different from each other. The ends of the first turbulators 915 and the second turbulators 925 facing the first corner portion 95 are arranged apart from each other in the circumferential direction Dc. In other words, the first turbulators 915 and the second turbulators 925 are not arranged at the same position in the circumferential direction Dc. The first turbulators 915 and the second turbulators 925 are arranged alternately in the circumferential direction Dc, such that a convex portion of one second turbulator 925 is arranged between adjacent convex portions of two first turbulators 915. Therefore, the first turbulators 915 and the second turbulators 925 are arranged alternately in the circumferential direction Dc so that one second turbulator 925 is arranged between two first turbulators 915 adjacent to each other in the circumferential direction Dc.

[0083] The surface shape of the gas path defining surface 91i of the rear end second passage 83b is symmetrical to the surface shape of the gas path defining surface 91i of the rear end first passage 83a with respect to an imaginary plane VP2 that passes through the rear inlet 83e and is perpendicular to the circumferential direction Dc (first direction). Furthermore, the surface shape of the end defining surface 92i of the rear end second passage 83b is symmetrical to the surface shape of the end defining surface 92i of the rear end first passage 83a with respect to the imaginary plane VP2. Therefore, the rear end first passage 83a and the rear end second passage 83b are formed in shapes that are line-symmetrical with respect to an imaginary plane (an imaginary plane extending in the axial direction Da and the radial direction Dr) that passes through the rear inlet 83e and is perpendicular to the circumferential direction Dc.

[0084] Next, the operation and effect of the stationary blades described above will be explained.

[0085] As shown in FIG. 4 , the cooling air Ac1 from the cooling air line 44 of the cooling device 40 flows into the blade air passage cover 57 of the outer shroud 60o, and then flows into the first blade passage 71, the second blade passage 72, the third blade passage 73, and the fourth blade passage 74.

[0086] The cooling air Acl that has flowed into the first blade passage 71 flows through this first blade passage 71 toward the inner shroud 60i, i.e., toward the inner Dr. As the cooling air Acl flows through the first blade passage 71, it convectively cools the area around the first blade passage 71 within the blade body 51. A portion of the cooling air Acl that has flowed into the first blade passage 71 flows into the front end passage 81 of the outer shroud body 61o via the front inlet passage 85 of the outer shroud body 61o. Another portion of the cooling air Acl that has flowed into the first blade passage 71 flows into the multiple leading edge injection passages 75. The cooling air Acl that has flowed into the leading edge injection passages 75 flows through these leading edge injection passages 75 and convectively cools the area around the leading edge injection passages 75 within the blade body 51. This cooling air Acl is injected from the leading edge injection passages 75 into the combustion gas flow path outside the blade body 51 from near the leading edge of the blade body 51.

[0087] The cooling air Acl that has flowed into the fourth blade passage 74 flows through this fourth blade passage 74 toward the inner shroud 60i, i.e., the inner Dr. As the cooling air Acl flows through the fourth blade passage 74, it convectively cools the area around the fourth blade passage 74 within the blade body 51. A portion of the cooling air Acl that has flowed into the fourth blade passage 74 flows into the aft end passage 83o of the outer shroud body 61o via the rear inlet passage 86 of the outer shroud body 61o. Another portion of the cooling air Acl that has flowed into the fourth blade passage 74 flows into the multiple trailing edge injection passages 76. The cooling air Acl that has flowed into the trailing edge injection passages 76 flows through these trailing edge injection passages 76 and convectively cools the area around the trailing edge injection passages 76 within the blade body 51. This cooling air Acl is injected from the trailing edge injection passages 76 into the combustion gas flow path outside the blade body 51 from the trailing edge of the blade body 51.

[0088] As shown in FIG. 6 , a portion of the cooling air Acl that flows from the front inlet passage 85 into the front end passages 81 of the outer shroud body 61o flows through the front end first passages 81a toward the first side Dc1. As the cooling air Acl flows through the front end first passages 81a, it convectively cools the portion of the outer shroud body 61o around the front end first passages 81a. This cooling air Acl flows from the front end first passages 81a into the first transverse passages 82a and flows through this first transverse passage 82a toward the downstream side Dad. As the cooling air Acl flows through the first transverse passages 82a, it convectively cools the portion of the outer shroud body 61o around the first transverse passages 82a. In this embodiment, the second gas path defining surface and the second end defining surface of the front-end first passage 81a and the second gas path defining surface and the second end defining surface of the first transverse passage 82a form first vertical turbulators 917 and second vertical turbulators 927. Therefore, a turbulent boundary layer of the cooling air Ac1 is formed along these surfaces, improving the heat transfer coefficient between the cooling air Ac1 and the portions forming these surfaces. This improves the cooling performance in the vicinity of the portions forming these surfaces. This cooling air Ac1 flows from the first transverse passage 82a into the first outlet passage 87a.

[0089] Another portion of the cooling air Acl that flows from the front inlet passage 85 into the front end passage 81 of the outer shroud body 61o flows through the front end second passage 81b toward the second side Dc2. As the cooling air Acl flows through the front end second passage 81b, it convectively cools the portion of the outer shroud body 61o around the front end second passage 81b. This cooling air Acl flows from the front end second passage 81b into the second transverse passage 82b and flows through this second transverse passage 82b toward the downstream side Dad. As the cooling air Acl flows through the second transverse passage 82b, it convectively cools the portion of the outer shroud body 61o around the second transverse passage 82b. In this embodiment, the second gas path defining surface and the second end defining surface of the front-end second passage 81b and the second gas path defining surface and the second end defining surface of the second transverse passage 82b form the first vertical turbulator 917 and the second vertical turbulator 927. Therefore, a turbulent boundary layer of the cooling air Ac1 is formed along these surfaces, improving the heat transfer coefficient between the cooling air Ac1 and the portions forming these surfaces. This improves the cooling performance in the vicinity of the portions forming these surfaces. This cooling air Ac1 flows from the second transverse passage 82b into the second outlet passage 87b.

[0090] A portion of the cooling air Acl that flows from the rear inlet passage 86 into the rear end passage 83o of the outer shroud body 61o flows through the rear end first passage 83a toward the first side Dc1. As the cooling air Acl flows through the rear end first passage 83a, it convectively cools the portion of the outer shroud body 61o around the rear end first passage 83a. This cooling air Acl flows from the rear end first passage 83a into the third transverse passage 84a and flows through this third transverse passage 84a toward the upstream side Dau. As the cooling air Acl flows through the third transverse passage 84a, it convectively cools the portion of the outer shroud body 61o around the third transverse passage 84a. In this embodiment, the second gas path defining surface 91o and the second end defining surface 92o of the rear end first passage 83a and the second gas path defining surface and the second end defining surface of the third transverse passage 84a form first vertical turbulators 917 and second vertical turbulators 927. Therefore, a turbulent boundary layer of the cooling air Ac1 is formed along these surfaces, improving the heat transfer coefficient between the cooling air Ac1 and the portions forming these surfaces. This improves the cooling performance in the vicinity of the portions forming these surfaces. This cooling air Ac1 flows from the third transverse passage 84a into the third outlet passage 88a.

[0091] Another portion of the cooling air Acl that flows from the rear inlet passage 86 into the rear end passage 83o of the outer shroud body 61o flows through the rear end second passage 83b toward the second side Dc2. As the cooling air Acl flows through the rear end second passage 83b, it convectively cools the portion of the outer shroud body 61o around the rear end second passage 83b. This cooling air Acl flows from the rear end second passage 83b into the fourth transverse passage 84b and flows through this fourth transverse passage 84b toward the upstream side Dau. As the cooling air Acl flows through the fourth transverse passage 84b, it convectively cools the portion of the outer shroud body 61o around the fourth transverse passage 84b. In this embodiment, the second gas path defining surface 91o and the second end defining surface 92o of the rear end second passage 83b and the second gas path defining surface and the second end defining surface of the fourth transverse passage 84b form first vertical turbulators 917 and second vertical turbulators 927. Therefore, a turbulent boundary layer of the cooling air Ac1 is formed along these surfaces, improving the heat transfer coefficient between the cooling air Ac1 and the portions forming these surfaces. This improves the cooling performance in the vicinity of the portions forming these surfaces. This cooling air Ac1 flows from the fourth transverse passage 84b into the fourth outlet passage 88b.

[0092] As shown in FIG. 8 , the cooling air Ac1 that has flowed into the first outlet passage 87a, the second outlet passage 87b, the third outlet passage 88a, and the fourth outlet passage 88b flows into a first space 67a in the recess 66 of the outer shroud 60o. The cooling air Ac1 in the first space 67a passes through the plurality of through holes 59a in the impingement plate 59 and flows into the second space 67b. At this time, the cooling air Ac1 that has passed through the plurality of through holes 59a in the impingement plate 59 impinge-cools the anti-gas path surface 64a of the outer shroud body 61o. The cooling air Ac1 that has impinge-cooled the anti-gas path surface 64a of the outer shroud body 61o is guided into, for example, the intermediate casing 6 via the cooling air exhaust line 45.

[0093] 4, the cooling air Ac1 that has flowed into the second blade passage 72 flows inside the second blade passage 72 toward the inner shroud 60i, i.e., toward the inner Dr. While flowing through the second blade passage 72, the cooling air Ac1 convectively cools the portion of the blade body 51 around the second blade passage 72. The cooling air Ac1 that has flowed into the second blade passage 72 flows into the front end passage 81 of the inner shroud body 61i via the front inlet passage 85 of the inner shroud body 61i.

[0094] The cooling air Ac1 that has flowed into the third blade passage 73 flows toward the inner shroud 60i, i.e., toward the inner Dr, inside the third blade passage 73. The cooling air Ac1 convectively cools the portion of the blade body 51 around the third blade passage 73 while flowing through the third blade passage 73. A portion of the cooling air Ac1 that has flowed into the third blade passage 73 flows into the rear end passage 83i of the inner shroud main body 61i via the rear inlet passage 86 of the inner shroud main body 61i.

[0095] As shown in FIG. 7 , a portion of the cooling air Ac1 that has flowed into the front end passage 81 of the inner shroud body 61i flows through the front end first passage 81a toward the first side Dc1. As the cooling air Ac1 flows through the front end first passage 81a, it convectively cools a portion of the inner shroud body 61i around the front end first passage 81a. This cooling air Ac1 flows from the front end first passage 81a into the first transverse passage 82a and flows through this first transverse passage 82a toward the downstream side Dad. As the cooling air Ac1 flows through the first transverse passage 82a, it convectively cools a portion of the inner shroud body 61i around the first transverse passage 82a. In the present embodiment, the second gas path defining surface and the second end defining surface of the front end first passage 81a and the second gas path defining surface and the second end defining surface of the first transverse passage 82a form first vertical turbulators 917 and second vertical turbulators 927. Therefore, a turbulent boundary layer of the cooling air Ac1 is formed along these surfaces, improving the heat transfer coefficient between the cooling air Ac1 and the portions forming these surfaces. This improves the cooling performance in the vicinity of the portions forming these surfaces. This cooling air Ac1 flows from the first transverse passage 82a into the first outlet passage 87a.

[0096] Another portion of the cooling air Acl that has flowed into the front end passage 81 of the inner shroud body 61i flows through the front end second passage 81b toward the second side Dc2. As the cooling air Acl flows through the front end second passage 81b, it convectively cools a portion of the inner shroud body 61i around the front end second passage 81b. This cooling air Acl flows from the front end second passage 81b into the second transverse passage 82b and flows through this second transverse passage 82b toward the downstream side Dad. As the cooling air Acl flows through the second transverse passage 82b, it convectively cools a portion of the inner shroud body 61i around the second transverse passage 82b. In the present embodiment, the second gas path defining surface and the second end defining surface of the front end second passage 81b and the second gas path defining surface and the second end defining surface of the second transverse passage 82b form first vertical turbulators 917 and second vertical turbulators 927. Therefore, a turbulent boundary layer of the cooling air Ac1 is formed along these surfaces, improving the heat transfer coefficient between the cooling air Ac1 and the portions forming these surfaces. This improves the cooling performance in the vicinity of the portions forming these surfaces. This cooling air Ac1 flows from the second transverse passage 82b into the second outlet passage 87b.

[0097] As described above, the cooling air Ac1 that has flowed into the third blade passage 73 flows through the rear inlet passage 86 of the inner shroud body 61 i into the rear end passage 83 i of the inner shroud body 61 i and collides with the end defining surface 92 i that defines the rear end passage 83 i. The rear inlet passage 86 extends in the axial direction Da that is perpendicular to the circumferential direction Dc (first direction) in which the rear end passage 83 i extends. For this reason, the cooling air Ac1 that has flowed into the rear end passage 83 i of the inner shroud body 61 i is divided approximately equally into the rear end first passage 83 a of the first side Dc1 and the rear end second passage 83 b of the second side Dc2, with the rear inlet 83 e as the reference.

[0098] The cooling air Ac1 that flows from the rear inlet passage 86 of the inner shroud body 61i into the rear end first passage 83a flows through the rear end first passage 83a toward the first side Dc1. As the cooling air Ac1 flows through the rear end first passage 83a, it convectively cools a portion of the inner shroud body 61i around the rear end first passage 83a. This cooling air Ac1 flows from the rear end first passage 83a into the third transverse passage 84a and flows through this third transverse passage 84a toward the upstream side Dau. As the cooling air Ac1 flows through the third transverse passage 84a, it convectively cools a portion of the inner shroud body 61i around the third transverse passage 84a. In the present embodiment, the gas path defining surface 91i and the end defining surface 92i of the rear end first passage 83a form first turbulators 915 and second turbulators 925. Furthermore, the second gas path defining surface and the second end defining surface of the third lateral passage 84a form first vertical turbulators 917 and second vertical turbulators 927. Therefore, a turbulent boundary layer of the cooling air Ac1 is formed along these surfaces, improving the heat transfer coefficient between the cooling air Ac1 and the portions forming these surfaces. This improves the cooling performance in the vicinity of the portions forming these surfaces. This cooling air Ac1 flows from the third lateral passage 84a into the third outlet passage 88a.

[0099] The cooling air Ac1 that flows from the rear inlet passage 86 of the inner shroud body 61i into the rear end second passage 83b flows through the rear end second passage 83b toward the second side Dc2. As the cooling air Ac1 flows through the rear end second passage 83b, it convectively cools a portion of the inner shroud body 61i around the rear end second passage 83b. This cooling air Ac1 flows from the rear end second passage 83b into the fourth transverse passage 84b and flows through this fourth transverse passage 84b toward the upstream side Dau. As the cooling air Ac1 flows through the fourth transverse passage 84b, it convectively cools a portion of the inner shroud body 61i around the fourth transverse passage 84b. In the present embodiment, the gas path defining surface 91i and the end defining surface 92i of the rear end second passage 83b form first turbulators 915 and second turbulators 925. Furthermore, the second gas path defining surface and the second side defining surface of the fourth transverse passage 84b form first vertical turbulators 917 and second vertical turbulators 927. Therefore, a turbulent boundary layer of the cooling air Ac1 is formed along these surfaces, improving the heat transfer coefficient between the cooling air Ac1 and the portions forming these surfaces. This improves the cooling performance in the vicinity of the portions forming these surfaces. This cooling air Ac1 flows from the fourth transverse passage 84b into the fourth outlet passage 88b.

[0100] As shown in FIG. 8 , the cooling air Ac1 that has flowed into the first outlet passage 87a, the second outlet passage 87b, the third outlet passage 88a, and the fourth outlet passage 88b flows into a first space 67a in the recess 66 of the inner shroud 60i. The cooling air Ac1 in the first space 67a passes through the plurality of through holes 59a of the impingement plate 59 and flows into the second space 67b. At this time, the cooling air Ac1 that has passed through the plurality of through holes 59a of the impingement plate 59 impingement-cools the anti-gas path surface 64a of the inner shroud main body 61i. The cooling air Ac1 that has impingement-cooled the anti-gas path surface 64a of the inner shroud main body 61i is guided into, for example, the intermediate casing 6 via the cooling air exhaust line 45.

[0101] Incidentally, the boundary surface of the rear end passage 83i extending in the circumferential direction Dc forms the first turbulator 915 and the second turbulator 925, and the second boundary surface of the rear end passage 83o forms the first vertical turbulator 917 and the second vertical turbulator 927. When the convex portions and concave portions formed by the first turbulator 915 and the second turbulator 925 and the first vertical turbulator 917 and the second vertical turbulator 927 extend in an intersecting direction that intersects the first direction, the cooling air Ac1 flows in a direction perpendicular to this intersecting direction.

[0102] Furthermore, because the cross sections of the first turbulators 915 and the second turbulators 925 are rectangular, turbulence occurs when the flow of cooling air Ac1 passes over the rectangular shapes. Similarly, because the cross sections of the first vertical turbulators 917 and the second vertical turbulators 927 are rectangular, turbulence occurs when the flow of cooling air Ac1 passes over the rectangular shapes. This further improves the cooling performance in the vicinity of the portions forming these surfaces.

[0103] In particular, in this embodiment, the multiple first turbulators 915 and the multiple second turbulators 925 extend in a direction inclined with respect to the circumferential direction Dc. Therefore, the flow direction of the cooling air Ac1 flowing in the circumferential direction Dc along the rear end passage 83i is changed by the first turbulators 915 and the second turbulators 925. Therefore, any location in the rear end passage 83i can be effectively cooled, and the gas path surface 64p and the rear end surface 62b can be efficiently cooled.

[0104] In the present embodiment, the concave and convex portions of the gas path defining surface 91i in the rear end passage 83i of the inner shroud body 61i extend in a direction inclined with respect to the circumferential direction Dc (first direction) so as to gradually move toward the circumferential downstream side Dcd (downstream side in the first direction) as they move away from the rear end surface 62b of the inner shroud body 61i. In other words, the multiple first turbulators 915 and the multiple second turbulators 925 extend in a direction inclined with respect to the circumferential direction Dc so as to gradually move away from the rear inlet 83e in the circumferential direction Dc as they move away from the first corner 95. For this reason, the cooling air Ac1 flowing along the gas path defining surface 91i moves toward the side approaching the rear end surface 62b (first end surface), that is, toward the first corner 95, while moving toward the circumferential downstream side Dcd (downstream side in the first direction). In the present embodiment, the recessed and protruding portions of the end defining surface 92i in the rear end passage 83i of the inner shroud body 61i extend in a direction inclined with respect to the circumferential direction Dc (first direction) so as to gradually move toward the circumferential downstream side Dcd (downstream side in the first direction) as they move away from the gas path surface 64p of the inner shroud body 61i. For this reason, the cooling air Ac1 flowing along the end defining surface 92i moves toward the side approaching the gas path surface 64p, i.e., toward the first corner portion 95, while moving toward the circumferential downstream side Dcd (downstream side in the first direction).

[0105] As described above, in the present embodiment, both the cooling air Acl flowing along the gas path defining surface 91i and the cooling air Acl flowing along the end defining surface 92i head toward the circumferential downstream side Dcd (downstream side in the first direction), but also toward the first corner 95. For this reason, the flow of the cooling air Acl near the first corner 95 is intensively disturbed, improving the heat transfer coefficient between the cooling air Acl and the first corner 95. Therefore, in the present embodiment, the cooling performance is further improved near the first corner 95 of the rear end passage 83i, that is, at the corner formed by the gas path surface 64p and the rear end face 62b of the inner shroud main body 61i.

[0106] Furthermore, in the present embodiment, the positions in the circumferential direction Dc of the end of the first turbulator 915 and the end of the second turbulator 925 that face the first corner 95 are different from each other. Specifically, the position in the circumferential direction Dc (first direction) of the edge of the end protruding surface 92bi that is close to the first corner 95 is different from the position in the circumferential direction Dc (first direction) of the edge of the gas path protruding surface 91bi that is close to the first corner 95. Therefore, in the present embodiment, the cooling performance in the vicinity of the first corner 95 of the rear end passage 83i is further improved.

[0107] Therefore, in this embodiment, the first corner portion between the gas path surface 64p and the rear end surface 62b of the inner shroud body 61i can be efficiently cooled.

[0108] "Modification" Next, the first turbulators 9150 and second turbulators 9250 of a flow path forming plate according to a modification of the present disclosure will be described. Note that in the modification described below, components common to the above embodiment will be denoted by the same reference numerals in the drawings and description thereof will be omitted. In the modification, the inclination direction of the first turbulators 9150 and second turbulators 9250 differs from that of the embodiment.

[0109] 13 and 14 , the flow passage forming plates of the modified example are, similarly to the embodiment, the platform 34p of the rotor blade 34, the outer shroud 36o and inner shroud 36i of the stator vane 36, and further the ring segments 37, and the inner shroud 60i and outer shroud 60o of the stator vane 50. In this modified example, the first turbulator 9150 and the second turbulator 9250 will be described using the inner shroud main body 61i as an example. The first turbulator 9150 and the second turbulator 9250 are formed in the aft end passage 83i of the inner shroud main body 61i, similarly to the embodiment.

[0110] A plurality of first turbulators 9150 are formed on the gas path defining surface 910i. The plurality of first turbulators 9150 are formed by a gas path bottom surface 910ai, a gas path protruding surface 910bi, and a gas path connecting surface 910ci. The gas path bottom surface 910ai, the gas path protruding surface 910bi, and the gas path connecting surface 910ci all extend in a direction intersecting the circumferential direction Dc. However, the gas path bottom surface 910ai, the gas path protruding surface 910bi, and the gas path connecting surface 910ci all extend in a direction inclined with respect to the circumferential direction Dc (first direction) so as to gradually move toward a circumferential downstream side Dcd (downstream side in the first direction) that moves away from the rear inlet 83e in the circumferential direction Dc (first direction) as they approach the rear end surface 62b (first end surface) of the inner shroud body 61i. The extending directions of the gas path bottom surface 910ai, the gas path protruding surface 910bi, and the gas path connecting surface 910ci form an obtuse angle with respect to the circumferential direction Dc (first direction). Therefore, the first turbulators 9150 extend in a direction inclined with respect to the circumferential direction so as to gradually move away from the rear inlet 83e in the circumferential direction Dc as they approach the first corner portion 95.

[0111] The plurality of second turbulators 9250 are formed on the end defining surface 920i. The plurality of second turbulators 9250 are formed by an end bottom surface 920ai, an end protruding surface 920bi, and an end connecting surface 920ci. The end bottom surface 920ai, the end protruding surface 920bi, and the end connecting surface 920ci all extend in a direction intersecting the circumferential direction Dc. However, the end bottom surface 920ai, the end protruding surface 920bi, and the end connecting surface 920ci all extend in a direction inclined with respect to the circumferential direction Dc (first direction) so as to gradually move toward a circumferential downstream side Dcd (downstream side in the first direction) that moves away from the rear inlet 83e in the circumferential direction Dc (first direction) as they approach the gas path surface 64p of the inner shroud body 61i. The extending directions of the end bottom surface 920ai, the end protruding surface 920bi, and the end connecting surface 920ci form an obtuse angle with respect to the circumferential direction Dc (first direction). Therefore, the second turbulators 9250 extend in a direction inclined with respect to the circumferential direction so as to gradually move away from the rear inlet 83e in the circumferential direction Dc as they approach the first corner portion 95.

[0112] Even in the first turbulator 9150 and the second turbulator 9250 of the modified example described above, the convex portions and concave portions extend in a direction intersecting the first direction. Therefore, the cooling air Ac1 flowing along the gas path defining surface 910i flows toward the circumferential downstream side Dcd (downstream side in the first direction) while also flowing away from the rear end surface 62b (first end surface), i.e., away from the first corner 95. Furthermore, the cooling air Ac1 flowing along the end defining surface 920i flows toward the circumferential downstream side Dcd (downstream side in the first direction) while also flowing away from the gas path surface 64p, i.e., away from the first corner 95. Therefore, the cooling air Ac1 flows uniformly through the rear end passage 83i without concentrating at the first corner 95. This allows for improved cooling performance in the rear end passage 83i in a nearly uniform manner.

[0113] "Other Modifications"

[0114] In the outer shroud body 61o, the second gas path defining surfaces and the second end defining surfaces of the front end passage 81, the first transverse passage 82a, the second transverse passage 82b, the aft end passage 83o, the third transverse passage 84a, and the fourth transverse passage 84b may be formed similarly to the gas path defining surfaces 91i and the end defining surfaces 92i of the aft end passage 83i in the inner shroud body 61i described above. That is, in the outer shroud body 61o, the front end passage 81, the first transverse passage 82a, the second transverse passage 82b, the aft end passage 83o, the third transverse passage 84a, and the fourth transverse passage 84b may be formed with the first turbulators 915 and the second turbulators 925, rather than the first vertical turbulators 917 and the second vertical turbulators 927. Therefore, for example, when the rear end passage 83o is formed as an air passage, the rear end first passage 83a of the outer shroud body 61o becomes the first air passage, and the rear end second passage 83b of the outer shroud body 61o becomes the second air passage.

[0115] Furthermore, the second gas path defining surfaces and second end defining surfaces of the front end passage 81, the first lateral passage 82a, the second lateral passage 82b, the third lateral passage 84a, and the fourth lateral passage 84b in the inner shroud body 61i may be formed similarly to the gas path defining surfaces 91i and the end defining surfaces 92i of the rear end passage 83i in the inner shroud body 61i described above. That is, instead of the first vertical turbulators 917 and the second vertical turbulators 927, the front end passage 81, the first lateral passage 82a, the second lateral passage 82b, the third lateral passage 84a, and the fourth lateral passage 84b in the inner shroud body 61i may be formed with the first turbulators 915 and the second turbulators 925. Therefore, for example, when the front end passage 81 is formed as an air passage, the front end first passage 81a of the inner shroud body 61i becomes the first air passage, and the front end second passage 81b of the inner shroud body 61i becomes the second air passage.

[0116] Furthermore, the passage-forming plate in the above embodiment is the inner shroud 60i of the stator vane 50. However, the platform 34p of the rotor blade 34 and the ring segment 37 are also passage-forming plates. Therefore, when an air passage is formed in the platform 34p of the rotor blade 34 or the ring segment 37, the gas path defining surface and the end defining surface in this air passage may be formed in the same manner as the gas path defining surface 91i and the end defining surface 92i of the aft end passage 83i in the inner shroud main body 61i described above.

[0117] The first corner 95 is preferably formed at an acute angle, but is not limited to this. The first corner 95 may be formed at a substantially right angle, like the second corner 950 of this embodiment.

[0118] Furthermore, the second corner 950 is not limited to being formed at a right angle, and may be formed at any angle as long as the angle is larger than that of the first corner 95.

[0119] Furthermore, in this embodiment and the modified examples, the first turbulators 915, the second turbulators 925, the first turbulators 9150, the second turbulators 9250, the first vertical turbulators 917, and the second vertical turbulators 927 have rectangular cross sections, but are not limited to such shapes. The first turbulators 915, the second turbulators 925, the first turbulators 9150, the second turbulators 9250, the first vertical turbulators 917, and the second vertical turbulators 927 may have any shape as long as they protrude from the surface forming the flow path. Therefore, the first turbulators 915, the second turbulators 925, the first turbulators 9150, the second turbulators 9250, the first vertical turbulators 917, and the second vertical turbulators 927 may have triangular cross sections (shapes in which the upper surfaces of the convex portions do not exist).

[0120] Furthermore, the present disclosure is not limited to the embodiment and modifications described above, and various additions, modifications, substitutions, partial deletions, etc. are possible within the scope of the conceptual idea and spirit of the present invention derived from the content defined in the claims and their equivalents.

[0121] "Additional Notes" The flow path forming plates in the above embodiments and modified examples can be understood, for example, as follows. (1) In a first aspect, the flow path forming plate includes a gas path surface 64p that defines a portion of the combustion gas flow path 39 through which the combustion gas G flows, a first end surface 62b connected to the periphery of the gas path surface 64p, and an air passage 83i defined by a plurality of defining surfaces and having an inlet 83e through which cooling air Ac1 can flow. The air passage 83i extends in a first direction Dc, which is a direction extending along the gas path surface 64p and the first end surface 62b. The plurality of defining surfaces include a gas path defining surface 91i that extends in the first direction Dc and is back-to-back with the gas path surface 64p, and an end defining surface 92i that extends in the first direction Dc and is back-to-back with the first end surface 62b. The end defining surface 92i and the gas path defining surface 91i are connected via a first corner 95. The gas path defining surface 91i is formed to protrude toward the inside of the air passage 83i and has a plurality of first turbulators 915 spaced apart in the first direction Dc. The end defining surface 92i is formed to protrude toward the inside of the air passage 83i and has a plurality of second turbulators 925 spaced apart in the first direction Dc. The first turbulators 915 and the second turbulators 925 extend in a direction inclined with respect to the first direction Dc.

[0122] As a result, the flow direction of the cooling air Ac1 that had been flowing in the first direction Dc along the air passage 83i is changed by the first turbulators 915 and the second turbulators 925. Therefore, any desired location in the air passage 83i can be effectively cooled, and the gas path surface 64p and the first end surface 62b can be efficiently cooled.

[0123] (2) In the second aspect, the flow path forming plate in (1) is such that the plurality of first turbulators 915 and the plurality of second turbulators 925 extend in a direction inclined with respect to the first direction Dc so as to gradually move away from the inlet 83e in the first direction Dc as they move away from the first corner portion 95.

[0124] (3) A flow path forming plate in a third aspect is the flow path forming plate in (2), wherein a gas path side edge, which is an edge of the end defining surface 92i on the side of the gas path surface 64p, is connected to an end side edge, which is an edge of the gas path defining surface 91i on the side of the first end surface 62b, via the first corner 95. The gas path defining surface 91i is an uneven surface in which a gas path bottom surface 91ai and a gas path protruding surface 91bi located on the side away from the gas path surface 64p with respect to the gas path bottom surface 91ai are alternately repeated in the first direction Dc. The end defining surface 92i is an uneven surface in which an end bottom surface 92ai and an end protruding surface 92bi located on the side away from the first end surface 62b with respect to the end bottom surface 92ai are alternately repeated in the first direction Dc. The gas path bottom surface 91ai and the gas path protruding surface 91bi extend in a direction inclined with respect to the first direction Dc so as to gradually move toward the downstream side Dcd in the first direction Dc, which is away from the inlet 83e, as the gas path bottom surface 91ai and the gas path protruding surface 91bi move away from the first end surface 62b. The end bottom surface 92ai and the end protruding surface 92bi extend in a direction inclined with respect to the first direction Dc so as to gradually move toward the downstream side Dcd in the first direction as the gas path surface 64p moves away.

[0125] Among the multiple defining surfaces that define the air passage 83i in this embodiment, the gas path defining surface 91i and the end defining surface 92i are both uneven surfaces with alternating concave and convex portions in the first direction Dc along which the air passage 83i extends. In other words, the gas path defining surface 91i and the end defining surface 92i form first turbulators 915 and second turbulators 925. Therefore, a turbulent boundary layer of the cooling air Ac1 is formed along these surfaces, improving the heat transfer coefficient between the cooling air Ac1 and the portions that form these surfaces. Therefore, in this embodiment, the cooling performance of the flow passage forming plate in the vicinity of the portions that form these surfaces, i.e., the gas path surface 64p and the first end surface 62b of the flow passage forming plate, is improved.

[0126] When a defining surface extending in a first direction Dc forms a first turbulator 915 and a second turbulator 925, and the convex portions and concave portions of the first turbulator 915 and the second turbulator 925 extend in a cross direction that intersects with the first direction Dc, the cooling air Ac1 flows in a direction perpendicular to this cross direction.

[0127] In this embodiment, the recesses and protrusions of the gas path defining surface 91i extend in a direction inclined with respect to the first direction Dc so as to gradually move toward the downstream side Dcd in the first direction as they move away from the first end face 62b. Therefore, the cooling air Ac1 flowing along the gas path defining surface 91i flows toward the side approaching the first end face 62b, i.e., the corner 95 side, while flowing toward the downstream side Dcd in the first direction. Also, in this embodiment, the recesses and protrusions of the end defining surface 92i extend in a direction inclined with respect to the first direction Dc so as to gradually move toward the downstream side Dcd in the first direction as they move away from the gas path surface 64p. Therefore, the cooling air Ac1 flowing along the end defining surface 92i flows toward the downstream side Dcd in the first direction, while flowing toward the side approaching the gas path surface 64p, i.e., the first corner 95 side.

[0128] As described above, in this embodiment, both the cooling air Ac1 flowing along the gas path defining surface 91i and the cooling air Ac1 flowing along the end defining surface 92i flow toward the first corner 95 while heading toward the downstream side Dcd in the first direction. This causes concentrated turbulence in the flow of the cooling air Ac1 near the first corner 95, improving the heat transfer coefficient between the cooling air Ac1 and the first corner 95. Therefore, in this embodiment, the cooling performance is further improved near the first corner 95 of the air passage 83i, that is, at the corner formed by the gas path surface 64p and the first end face 62b of the flow path forming plate.

[0129] (4) In the fourth aspect, in the flow path forming plate of any one of (1) to (3), the positions of the first direction Dc of the first turbulator 915 and the second turbulator 925 facing the first corner portion 95 are different from each other.

[0130] This further improves the cooling performance in the vicinity of the first corner portion 95 of the air passage 83i.

[0131] (5) In the fifth aspect, the flow path forming plate is the flow path forming plate of (4), in which the first turbulators and the second turbulators are arranged alternately in the first direction so that one second turbulator is arranged between two first turbulators adjacent to each other in the first direction.

[0132] (6) In the sixth aspect, the flow path forming plate is any one of the flow path forming plates (1) to (5), and the first corner portion 95 of the air passage 83i is formed at an acute angle when viewed from the first direction Dc.

[0133] (7) In a seventh aspect, the flow path forming plate is any one of the flow path forming plates of (1) to (6), wherein the plurality of defining surfaces have an inner defining surface 94 that faces the end defining surface 92 i. The inlet 83 e is formed on the inner defining surface 94 so that the cooling air Ac1 that flows into the air passage 83 i from the inlet 83 e collides with the end defining surface 92 i.

[0134] (8) In an eighth aspect, the flow path forming plate of (7) is configured such that the air passage 83i has a first air passage 83a extending from the inlet 83e toward a first side Dc1 of both sides in the first direction Dc, and a second air passage 83b extending from the inlet 83e toward a second side Dc2 opposite to the first side Dc1 in the first direction Dc. The first turbulators 915 and the second turbulators 925 are inclined in different directions with respect to the first direction Dc, with the first corner portion 95 as a reference, in the first air passage 83a and the second air passage 83b.

[0135] (9) A ninth aspect of the flow path forming plate is the flow path forming plate of (8), wherein the first air passage 83a and the second air passage 83b are both defined by the plurality of defining surfaces, including the gas path defining surface 91i, the end defining surface 92i, and the inner defining surface 94. The gas path defining surface 91i is an uneven surface in which a gas path bottom surface 91ai and a gas path protruding surface 91bi located on the side away from the gas path surface 64p with respect to the gas path bottom surface 91ai are alternately repeated in the first direction Dc. The end defining surface 92i is an uneven surface in which an end bottom surface 92ai and an end protruding surface 92bi located on the side away from the first end surface 62b with respect to the end bottom surface 92ai are alternately repeated in the first direction Dc. The gas path defining surface 91i of the first air passage 83a and the gas path defining surface 91i of the second air passage 83b are both uneven surfaces in which the gas path bottom surfaces 91ai and the gas path protruding surfaces 91bi are alternately repeated in the first direction Dc. The end defining surface 92i of the first air passage 83a and the end defining surface 92i of the second air passage 83b are both uneven surfaces in which the end bottom surfaces 92ai and the end protruding surfaces 92bi are alternately repeated in the first direction Dc. The gas path bottom surfaces 91ai and the gas path protruding surfaces 91bi of the first air passage 83a and the gas path bottom surfaces 91ai and the gas path protruding surfaces 91bi of the second air passage 83b extend in a direction inclined with respect to the first direction Dc so as to gradually move toward the downstream side Dcd in the first direction with increasing distance from the first end surface 62b. The bottom end surface 92ai and the protruding end surface 92bi of the first air passage 83a and the bottom end surface 92ai and the protruding end surface 92bi of the second air passage 83b extend in a direction inclined with respect to the first direction Dc so as to gradually move toward the downstream side Dcd in the first direction with increasing distance from the gas path surface 64p. The downstream side Dcd in the first direction of the first air passage 83a is the first side Dc1. The downstream side Dcd in the first direction of the second air passage 83b is the second side Dc2.

[0136] (10) In the tenth aspect, the flow path forming plate is the flow path forming plate of (8) or (9), in which the first air passage 83a and the second air passage 83b are formed in an axisymmetric shape with respect to an imaginary plane that passes through the inlet 83e and is perpendicular to the first direction Dc.

[0137] (11) In an eleventh aspect, the flow path forming plate is the flow path forming plate of any one of (7) to (10), further including an inlet passage 86 connected to the air passage 83i at the inlet 83e. The inlet passage 86 extends in a direction perpendicular to the first direction Dc.

[0138] In this embodiment, the inlet passage 86 extends in a direction perpendicular to the first direction Dc in which the air passage 83i extends. Therefore, the cooling air Ac1 that has flowed into the air passage 83i is divided approximately evenly into a first side Dc1 in the first direction and a second side Dc2 in the first direction with respect to the inlet 83e.

[0139] (12) A twelfth aspect of the flow path forming plate is the flow path forming plate of any one of (1) to (11), further including a separated passage (83o) formed independently of the air passage (83i) and having a second inlet (830e) through which the cooling air Ac1 can flow. The separated passage (83o) extends in the first direction (Dc) and is defined by a plurality of second defining surfaces. The second defining surfaces include a second gas path defining surface (91o) extending in the first direction (Dc) and facing the gas path surface (64p), and a second end defining surface (92o) extending in the first direction (Dc) and connected to the second gas path defining surface (91o). The second end defining surface (92o) and the second gas path defining surface (91o) are connected via a second corner (950). The second gas path defining surface (91o) is formed to protrude toward the interior of the separated passage (83o) and includes a plurality of first vertical turbulators (917) spaced apart in the first direction (Dc). The second end defining surface 92o is formed to protrude toward the inside of the separated passage 83o and has a plurality of second vertical turbulators 927 formed spaced apart in the first direction Dc. The plurality of first vertical turbulators 917 and the plurality of second vertical turbulators 927 extend perpendicular to the first direction Dc.

[0140] (13) In the thirteenth aspect, the flow path forming plate is the flow path forming plate of (12), in which, in the separation passage 83o, the second corner portion 950 is formed at a larger angle than the first corner portion 95 when viewed from the first direction Dc.

[0141] The blades in the above embodiments and modifications can be understood, for example, as follows: (14) A blade in a fourteenth aspect comprises a flow passage forming plate according to any one of (1) to (13) and a blade body 51 having an airfoil-shaped cross section and extending in a blade height direction having a directional component perpendicular to the cross section. The flow passage forming plate is provided at one end of the blade body 51 in the blade height direction and extends in a direction perpendicular to the blade height direction.

[0142] (15) In a fifteenth aspect, the blade of (14) is such that the blade body 51 has a leading edge 52 and a trailing edge 53 spaced apart from the leading edge 52. The first end surface 62b is located downstream (Dad), which is the side of the blade body 51 where the trailing edge 53 is located relative to the leading edge 52, and is a trailing end surface 62b facing the downstream side (Dad).

[0143] The gas turbines in the above embodiments and modifications can be understood, for example, as follows: (16) A gas turbine in a sixteenth aspect includes a compressor 10 capable of compressing air to generate compressed air Acom, a combustor 20 capable of burning fuel F in the compressed air Acom to generate combustion gas G, and a turbine 30 capable of being driven by the combustion gas G. The turbine 30 has any one of flow path forming plates (1) to (13) that define a portion of a combustion gas flow path 39 through which the combustion gas G flows.

[0144] According to one aspect of the present disclosure, the gas path surface and the end surface of the flow path forming plate can be effectively cooled.

[0145] 1: Gas turbine rotor 6: Intermediate casing 7: Inner cover 8: Gas turbine casing 10: Compressor 11: Compressor rotor 12: Rotor shaft 13: Row of moving blades 15: Row of stator blades 18: Compressor casing 20: Combustor 21: Burner 22: Transition piece (or combustion duct) 30: Turbine 31: Turbine rotor 32: Rotor shaft 33: Row of moving blades 34: Row of moving blades 34b: Blade body 34p: Platform 35: Row of stator blades 36: Stator blades 36b: Blade body 36i: Inner shroud 36o: Outer shroud 37: Ring segment 38: Turbine casing 39: Combustion gas flow path 40: Cooling device 41: Extraction line 42: Cooler 43: Boost compressor 44: Cooling air line 45: Cooling air exhaust line 50: Stator blades 51: Blade body 52: Leading edge 53: Trailing edge 54: Suction surface 55: Pressure surface 56: Thermal barrier coating layer 57: Blade air passage cover 58: Sealing plate 59: Impingement plate 59a: Through hole 60i: Inner shroud 60o: Outer shroud 61i: Inner shroud body 61o: Outer shroud body 62f: Front end surface (second end surface) 62b: Aft end surface (first end surface) 620b: Aft end surface (second end surface) 63n: Suction side end surface 63p: Pressure side end surface 64a: Counter-gas path surface 64ao: Outer counter-gas path surface 64p: Gas path surface 65i,65o: Peripheral wall 65f: Front wall 65b: Rear wall 65n: Suction side wall 65p: Pressure side wall 66: Recess 67: Cooling air space 67a: First space 67b: Second space 68f: Front hook 68r: Rear hook 69: Retainer 69p: Retainer passage 71: First blade passage 72: Second blade passage 73: Third blade passage 74: Fourth blade passage 75: Leading edge injection passage 76: Trailing edge injection passage 80: Internal passage 81: Front end passage (or simply separated passage) 81e: Front inlet (or simply second inlet) 81a: Front end first passage 81b: Front end second passage 82a: First lateral passage 82b: Second lateral passage 83i: Rear end passage (or simply air passage) 83o: Rear end passage (or simply separated passage) 83e: Rear inlet (or simply inlet) 830e: Rear inlet (or simply second inlet) 83a: Rear end first passage (or simply first air passage) 83b: Rear end second passage (or simply second air passage) 84a: Third lateral passage 84b: Fourth lateral passage 85: Front inlet passage 86: Rear inlet passage (or simply inlet passage) 87a: First outlet passage 87b: Second outlet passage 88a: Third outlet passage 88b: Fourth outlet passage 89: Corner injection passage 91i, 910i: Gas path defining surface 91o: Second gas path defining surface 915, 9150: First turbulator 917: First vertical turbulator 91ai, 910ai: Gas path bottom surface 91ao: Second gas path bottom surface 91bi, 910bi: Gas path protruding surface 91bo: Second gas path protruding surface 91ci, 910ci: Gas path connection surface 91co: Second gas path connection surface 92i, 920i: End defining surface 92o: Second end defining surface 925, 9250: Second turbulator 927: Second vertical turbulator 92ai, 920ai: End bottom surface 92ao: Second end bottom surface 92bi, 920bi: End protruding surface 92bo: Second end protruding surface 92ci, 920ci: End connecting surface 92co: Second end connecting surface 93: Anti-gas path side defining surface 94: Inner defining surface 95: First corner portion 950: Second corner portion A: Outside air Acom: Compressed air Ac1: Cooling air G: Combustion gas F: Fuel CL: Camber line VP1,VP2: Virtual plane Da: Axial direction Dau: Upstream side Dad: Downstream side Dc: Circumferential direction (or first direction) Dc1: First side (or first side in the first direction) Dc2: Second side (or second side in the first direction) Dcd: Circumferential downstream side (or downstream side in the first direction) Dr: Radial direction Dri: Inner side Dro: Outer side

Claims

1. A flow passage forming plate comprising: a gas path surface defining a portion of a combustion gas flow passage through which combustion gas flows; a first end surface connected to a periphery of the gas path surface; and an air passage defined by a plurality of defining surfaces and having an inlet through which cooling air can flow, wherein the air passage extends in a first direction which is a direction extending along the gas path surface and the first end surface, the plurality of defining surfaces including a gas path defining surface extending in the first direction and in a back-to-back relationship with the gas path surface, and an end defining surface extending in the first direction and in a back-to-back relationship with the first end surface, the end defining surface and the gas path defining surface are connected through a first corner, the gas path defining surface is formed to protrude toward the inside of the air passage and has a plurality of first turbulators formed and spaced apart in the first direction, the end defining surface is formed to protrude toward the inside of the air passage and has a plurality of second turbulators formed and spaced apart in the first direction, and the plurality of first turbulators and the plurality of second turbulators extend in a direction inclined with respect to the first direction.

2. A flow path forming plate as described in claim 1, wherein the first turbulators and the second turbulators extend in a direction inclined with respect to the first direction so as to gradually move away from the inlet in the first direction with increasing distance from the first corner portion.

3. A flow path forming plate as described in claim 2, wherein a gas path side edge which is an edge of the end defining surface on the side of the gas path surface is connected to an end side edge which is an edge of the gas path defining surface on the side of the first end face via the first corner portion, the gas path defining surface is an uneven surface in which a gas path bottom surface and a gas path protruding surface located on a side of the gas path bottom surface that moves away from the gas path surface are alternately repeated in the first direction, the end defining surface is an uneven surface in which an end bottom surface and an end protruding surface located on a side of the end bottom surface that moves away from the first end face are alternately repeated in the first direction, the gas path bottom surface and the gas path protruding surface extend in a direction inclined with respect to the first direction so as to gradually move away from the first end face in the first direction toward a downstream side in the first direction that moves away from the inlet, the end bottom surface and the end protruding surface extend in a direction inclined with respect to the first direction so as to gradually move toward a downstream side in the first direction with increasing distance from the gas path surface.

4. A flow passage forming plate according to any one of claims 1 to 3, wherein the positions of the first turbulator and the second turbulator facing the first corner portion in the first direction are different from each other.

5. A flow path forming plate as described in claim 4, wherein the first turbulators and the second turbulators are arranged alternately in the first direction such that one second turbulator is arranged between two first turbulators adjacent to each other in the first direction.

6. A flow path forming plate according to any one of claims 1 to 5, wherein the first corner of the air passage is formed at an acute angle when viewed from the first direction.

7. A flow passage forming plate as claimed in any one of claims 1 to 6, wherein the plurality of defining surfaces have an inner defining surface opposed to the end defining surface, and the inlet is formed on the inner defining surface so that the cooling air flowing into the air passage from the inlet collides with the end defining surface.

8. A flow path forming plate as described in claim 7, wherein the air passage has a first air passage extending from the inlet toward a first side of both sides in the first direction, and a second air passage extending from the inlet toward a second side opposite the first side in the first direction, and the first turbulators and the second turbulators are inclined in different directions with respect to the first direction, with the first corner portion as a reference, in the first air passage and the second air passage.

9. A flow path forming plate according to claim 8, wherein the first air passage and the second air passage are both defined by the plurality of defining surfaces including the gas path defining surface, the end defining surface and the inner defining surface, the gas path defining surface being an uneven surface in which a gas path bottom surface and a gas path protruding surface located on a side of the gas path bottom surface that is away from the gas path surface are alternately repeated in the first direction, the end defining surface being an uneven surface in which an end bottom surface and an end protruding surface located on a side of the end bottom surface that is away from the first end surface are alternately repeated in the first direction, and the gas path defining surface of the first air passage and the gas path defining surface of the second air passage are both uneven surfaces in which the gas path bottom surface and the gas path protruding surface are alternately repeated in the first direction, a flow path forming plate, wherein the end defining surface of the first air passage and the end defining surface of the second air passage are both uneven surfaces in which the end bottom surfaces and the end protruding surfaces are alternately repeated in the first direction, the gas path bottom surface and the gas path protruding surface of the first air passage and the gas path bottom surface and the gas path protruding surface of the second air passage extend in a direction inclined with respect to the first direction so as to gradually move toward the downstream side in the first direction as they move away from the first end face, the end bottom surface and the end protruding surface of the first air passage and the end bottom surface and the end protruding surface of the second air passage extend in a direction inclined with respect to the first direction so as to gradually move toward the downstream side in the first direction as they move away from the gas path surface, the downstream side of the first air passage in the first direction is the first side, and the downstream side of the second air passage in the first direction is the second side.

10. A flow path forming plate according to claim 8 or 9, wherein the first air passage and the second air passage are formed in a shape that is linearly symmetrical with respect to an imaginary plane that passes through the inlet and is perpendicular to the first direction.

11. A flow path forming plate according to any one of claims 7 to 10, comprising an inlet passage connected to the air passage at the inlet, the inlet passage extending in a direction perpendicular to the first direction.

12. A flow passage forming plate according to any one of claims 1 to 11, further comprising a separated passage formed independently of the air passage and having a second inlet through which the cooling air can flow, the separated passage extending in the first direction and defined by a plurality of second defining surfaces, the plurality of second defining surfaces including a second gas path defining surface extending in the first direction and in a back-to-back relationship with the gas path surface, and a second end defining surface extending in the first direction and connected to the second gas path defining surface, the second end defining surface and the second gas path defining surface being connected via a second corner portion, the second gas path defining surface having a first vertical turbulator formed so as to protrude toward the inside of the separated passage and a plurality of second vertical turbulators formed so as to protrude toward the inside of the separated passage and a plurality of second vertical turbulators formed so as to be spaced apart in the first direction, the plurality of first vertical turbulators and the plurality of second vertical turbulators extending perpendicular to the first direction.

13. A flow path forming plate according to claim 12, wherein in the separation passage, the second corner portion is formed at an angle larger than that of the first corner portion when viewed from the first direction.

14. A wing comprising: a flow passage forming plate as claimed in any one of claims 1 to 13; and a wing body having an aerofoil-shaped cross section and extending in a wing height direction having a directional component perpendicular to the cross section, wherein the flow passage forming plate is provided at one end of the wing body in the wing height direction and extends in a direction perpendicular to the wing height direction.

15. A wing as claimed in claim 14, wherein the wing body has a leading edge and a trailing edge spaced apart from the leading edge, and the first end surface is a trailing end surface formed at a position closer to the trailing edge than the wing body is to the leading edge and facing the trailing edge.

16. A gas turbine comprising: a compressor capable of compressing air to generate compressed air; a combustor capable of burning fuel in the compressed air to generate combustion gas; and a turbine capable of being driven by the combustion gas, wherein the turbine has a flow path forming plate according to any one of claims 1 to 13 that defines a portion of a combustion gas flow path through which the combustion gas flows.

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