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

Abstract

The air passage of the flow path forming plate extends in a first direction along the gas path surface and the first end surface. The air passage has a gas path defining surface in a back-to-back relationship with the gas path surface and an end defining surface in a back-to-back relationship with the first end surface. The gas path defining surface has a plurality of first spoilers formed separately in the first direction. The end defining surface has a plurality of second spoilers formed so as to be separated from each other in the first direction. The first spoiler and the second spoiler extend in a direction inclined with respect to the first direction.

Description

Technical Field

[0001] The present invention relates to a flow path forming plate for defining a combustion gas flow path, a blade having the flow path forming plate, and a gas turbine having the blade.

[0002] This application claims priority based on Japanese Patent Application No. 2023-163936, filed on September 26, 2023, the contents of which are incorporated herein by reference. Background Technology

[0003] A gas turbine includes: a compressor for compressing air to generate compressed air; a combustor for burning fuel in the compressed air to generate combustion gases; and a turbine driven by the combustion gases. The turbine includes a rotor rotating about an axis and a turbine housing covering the rotor. The rotor includes: a rotor shaft extending in the axial direction about the axis; and multiple rows of rotating blades mounted on the rotor shaft. The multiple rows of rotating blades are arranged at intervals between each other in the axial direction. Each row of rotating blades has multiple rotating blades arranged circumferentially relative to the axis. Multiple rows of fixed blades are provided inside the turbine housing. The multiple rows of fixed blades are arranged at intervals between each other in the axial direction. Each row of fixed blades has multiple fixed blades arranged circumferentially relative to the axis.

[0004] A rotating blade has: a blade body extending radially relative to an axis; and a platform disposed radially inside the blade body. The blade body of the rotating blade is positioned within a combustion gas flow path through which combustion gases pass. The platform defines the radially inner edge of the combustion gas flow path. A stationary blade has: a blade body extending radially relative to an axis; an inner shroud disposed radially inside the blade body; and an outer shroud disposed radially outside the blade body. The blade body of the stationary blade is positioned within a combustion gas flow path through which combustion gases pass. 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. A plurality of segmented rings are provided on the turbine housing. The plurality of segmented rings are positioned radially opposite the rotating blade relative to the axis. The segmented rings define the outer edge of the combustion gas flow path.

[0005] The platform for rotating blades, the outer and inner shrouds for fixing the blades, and the dividing ring all form flow path forming plates that define the combustion gas flow path. These flow path forming plates are exposed to the high-temperature combustion gases. Therefore, they are typically cooled by air or the like.

[0006] For example, Patent Document 1 discloses a shroud with fixed blades as a type of flow path forming plate. This shroud has: a gas path surface defining a portion of the combustion gas flow path; multiple end faces connected to the periphery of the gas path surface; and an end-side air passage through which cooling air can flow. The end-side air passage extends along the gas path surface and a first end face among the multiple end faces, and in a first direction parallel to the gas path surface and the first end face. The end-side air passage is defined by multiple channel defining surfaces. On two adjacent channel defining surfaces among the multiple channel defining surfaces, alternating convex and concave baffles are formed, repeating in the first direction. These baffles create a turbulent boundary layer for the cooling air along the channel defining surfaces, thereby improving the heat transfer rate between the cooling air and the portion of the shroud adjacent to the end-side air passage.

[0007] Existing technical documents

[0008] Patent documents

[0009] Patent Document 1: Japanese Patent Application Publication No. 2018-141393 Summary of the Invention

[0010] The problem that the invention aims to solve

[0011] In the flow path forming plate, due to its configuration and other factors, sometimes a portion of the gas path surface and any one of the end faces, such as the corner, is easily heated by the combustion gas.

[0012] Therefore, the object of the present invention is to provide a flow path forming plate that can effectively cool the gas path surface and end face, a blade having the flow path forming plate, and a gas turbine having the blade.

[0013] Methods for solving problems

[0014] A flow path forming plate, as an embodiment of the invention for achieving the stated purpose, comprises: a gas path surface, defining a portion of a combustion gas flow path; a first end face, connected to the periphery of the gas path surface; and an air passage, defined by a plurality of defining surfaces and having an inlet into which cooling air can flow, the air passage extending in a first direction along the gas path surface and the first end face, the plurality of defining surfaces comprising: a gas path defining surface extending in the first direction and positioned back-to-back with the gas path surface; and an end defining surface extending in the first direction and positioned back-to-back with the first end face, the end defining surface and the gas path defining surface being connected via a first corner, the gas path defining surface having a plurality of first baffles formed separately in the first direction protruding toward the interior of the air passage, the end defining surface having a plurality of second baffles formed separately in the first direction protruding toward the interior of the air passage, the plurality of first baffles and the plurality of second baffles extending in a direction inclined relative to the first direction.

[0015] One aspect of the invention for achieving the stated purpose includes a blade comprising: a flow path forming plate; and a blade body having a blade-shaped cross-section and extending in a blade height direction having a directional component perpendicular to the cross-section. The flow path forming plate is disposed at one end of the blade body on one side in the blade height direction and extends in a direction perpendicular to the blade height direction.

[0016] A gas turbine, as an embodiment of the invention for achieving the aforementioned objective, comprises: a compressor capable of compressing air to generate compressed air; a combustor capable of burning fuel in the compressed air to generate combustion gases; and a turbine capable of being driven by the combustion gases. The turbine has a flow path forming plate that defines a portion of a combustion gas flow path that delineates the flow path of the combustion gases.

[0017] Invention Effects

[0018] According to one aspect of the present invention, the gas path surface and end face in the flow path forming plate can be effectively cooled. Attached Figure Description

[0019] Figure 1 This is a schematic cross-sectional view of a gas turbine in one embodiment of the present invention.

[0020] Figure 2 This is a cross-sectional view of the main part of the gas turbine in one embodiment of the present invention.

[0021] Figure 3 This is a perspective view of a fixed blade in one embodiment of the present invention.

[0022] Figure 4 It is a cross-sectional view of a section taken along the arc of the fixed blade in one embodiment of the present invention.

[0023] Figure 5 This is a cross-sectional view of the main part of the fixed blade in one embodiment of the present invention.

[0024] Figure 6 It is along Figure 4 A sectional view cut along line VI-VI.

[0025] Figure 7 It is along Figure 4 A sectional view cut along line VII-VII.

[0026] Figure 8 This is a perspective view of the main part of the protective cover involved in this invention.

[0027] Figure 9 This is a top view showing a cut of the main part of the rear end of the outer protective cover body involved in this invention.

[0028] Figure 10 This is an explanatory diagram illustrating the surface shape of the second gas path demarcation surface and the second end demarcation surface in the rear end channel of the outer shield involved in the present invention.

[0029] Figure 11 This is a slanted cut view of the main part of the rear end of the inner protective cover body involved in this invention.

[0030] Figure 12 This is an explanatory diagram illustrating the surface shape of the gas path demarcation surface and the end demarcation surface in the rear channel of the inner shield involved in the present invention.

[0031] Figure 13 This is a top view showing a cutaway section of the main rear portion of the inner protective cover body in a modified example of the present invention.

[0032] Figure 14 This is an explanatory diagram illustrating the surface shape of the gas path demarcation surface and the end demarcation surface in the rear channel of the inner shield of the modified example of the present invention. Detailed Implementation

[0033] Hereinafter, with reference to the accompanying drawings, an embodiment and variations thereof will be described in detail.

[0034] "Implementation Methods of Gas Turbines"

[0035] refer to Figure 1 and Figure 2 The implementation method of the gas turbine is described.

[0036] like Figure 1 As shown, the gas turbine in this embodiment includes: a compressor 10 that compresses external air A to generate compressed air ACOM; a combustor 20 that burns fuel F from a fuel supply source in the compressed air ACOM to generate combustion gas G; and a turbine 30 that can be driven by the combustion gas G.

[0037] The compressor 10 has a compressor rotor 11 that rotates around an axis AR, a compressor housing 18 covering the compressor rotor 11, and multiple fixed blade rows 15. The turbine 30 has a turbine rotor 31 that rotates around an axis AR, a turbine housing 38 covering the turbine rotor 31, and multiple fixed blade rows 35. Hereinafter, the direction in which the axis AR extends is designated as the axial direction DA, the circumferential direction centered on the axis AR is simply referred to as the circumferential direction DC, and the direction perpendicular to the axis AR is designated as the radial direction DR. Furthermore, one side of the axial direction DA is designated as the upstream side DAU, and the opposite side is designated as the downstream side DAD. Also, the side of the radial direction DR closest to the axis AR is designated as the inner side DRI, and the opposite side is designated as the outer side DRO.

[0038] The compressor 10 is positioned on the upstream DAU relative to the turbine 30.

[0039] The compressor rotor 11 and the turbine rotor 31 are located on the same axis AR and are connected to each other to form the gas turbine rotor 1. For example, a generator rotor GEN is connected to this gas turbine rotor 1. The gas turbine further includes an intermediate housing 6. This intermediate housing 6 is disposed between the compressor housing 18 and the turbine housing 38 in the axial direction DA. The compressor housing 18, the intermediate housing 6, and the turbine housing 38 are interconnected to form the gas turbine housing 8.

[0040] like Figure 1 and Figure 2 As shown, the compressor rotor 11 has a rotor shaft 12 extending along the axial direction DA with the axis AR as its center, and a plurality of rotating blade rows 13 mounted on the rotor shaft 12. The plurality of rotating blade rows 13 are arranged in the axial direction DA. Each rotating blade row 13 is composed of a plurality of rotating blades arranged in the circumferential direction DC. One of a plurality of fixed blade rows 15 is disposed on the downstream side DAD of each of the plurality of rotating blade rows 13. Each fixed blade row 15 is disposed inside the compressor housing 18. Each fixed blade row 15 is composed of a plurality of fixed blades arranged in the circumferential direction DC.

[0041] The turbine rotor 31 includes: a rotor shaft 32 extending in the axial direction DA with axis AR as its center; and a plurality of rotating blade rows 33 mounted on the rotor shaft 32. The plurality of rotating blade rows 33 are arranged in the axial direction DA. Each rotating blade row 33 is composed of a plurality of rotating blades 34 arranged in the circumferential direction DC. One of a plurality of fixed blade rows 35 is disposed on each upstream side DAU of the plurality of rotating blade rows 33. Each fixed blade row 35 is disposed inside the turbine housing 38. Each fixed blade row 35 is composed of a plurality of fixed blades 36 arranged in the circumferential direction DC.

[0042] An annular space between the outer periphery of the rotor shaft 32 and the inner periphery of the turbine housing 38, and arranged along the axial direction DA, forms a combustion gas flow path 39 for the combustion gas G from the combustor 20. This combustion gas flow path 39 is annular about the axis AR and extends along the axial direction DA.

[0043] The rotating blade 34 has a blade body 34B extending radially in the direction of extension (DR) and a platform 34P connected to the end of the inner side (DRI) of the blade body 34B. The cross-section of the blade body 34B perpendicular to the direction of extension of the blade body 34B is blade-shaped. The platform 34P extends in a direction perpendicular to the direction of extension of the blade body 34B. The platform 34P defines a portion of the edge of the inner side (DRI) of the combustion gas flow path 39. Therefore, the platform 34P is a flow path forming plate defining a portion of the combustion gas flow path 39.

[0044] The fixed blade 36 has a blade body 36B extending radially in the direction of extension (DR), an outer shield 36O connected to the outer end of the blade body 36B (DRO), and an inner shield 36I connected to the inner end of the blade body 36B (DRI). The cross-section of the blade body 36B perpendicular to the direction of extension of the blade body 36B is blade-shaped. Both the outer shield 36O and the inner shield 36I extend in a direction perpendicular to the direction of extension of the blade body 36B.

[0045] The outer shroud 36O of the fixed blade 36 defines a portion of the edge of the outer DRO of the combustion gas flow path 39. The inner shroud 36I of the fixed blade 36 defines a portion of the edge of the inner DRI of the combustion gas flow path 39. Therefore, 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.

[0046] In addition to multiple fixed blades 36, multiple dividing rings 37 are provided on the inner side of the turbine housing 38. These dividing rings 37 are located at positions where rotating blade rows 33 exist in the axial direction DA and are situated outside the rotating blade rows 33 (DRO). Therefore, the dividing rings 37 are located between the multiple fixed blade rows 35 arranged in the axial direction DA. The dividing rings 37 define a portion of the edge of the outer DRO of the combustion gas flow path 39. Therefore, the dividing rings 37 also serve as flow path forming plates defining a portion of the combustion gas flow path 39.

[0047] The burner 20 is mounted on the intermediate housing 6. For example... Figure 2 As shown, the burner 20 has a tail tube (or combustion tube) 22 in which fuel F is burned internally and a plurality of combustion furnaces 21 into which fuel is injected.

[0048] In the gas turbine of this embodiment, a cooling device 40 is connected. This cooling device 40 includes an extraction pipe 41, a cooler 42, a booster compressor 43, and a cooling air pipe 44. One end of the extraction pipe 41 is connected to the intermediate housing 6, and the other end is connected to the intake port of the booster compressor 43. The extraction pipe 41 extracts compressed air from the intermediate housing 6 to the outside of the gas turbine housing 8. The cooler 42 is disposed in the extraction pipe 41 and cools the compressed air flowing in the extraction pipe 41. The booster compressor 43 pressurizes the compressed air cooled by the cooler 42. The cooling air pipe 44 has one end and multiple other ends. One end of the cooling air pipe 44 is connected to the outlet of the booster compressor 43. The multiple other ends of the cooling air pipe 44 are connected to any one of multiple high-temperature components, such as the fixed blades 36 exposed to the combustion gas G. The cooling air duct 44 can guide compressed air from the booster compressor 43 as cooling air ACL to high-temperature components.

[0049] As described above, the platform 34P of the rotating blade 34, the outer and inner protective covers 36O and the dividing ring 36I of the fixed blade 36 are all flow path forming plates. Therefore, the following describes an embodiment of a fixed blade having a flow path forming plate.

[0050] "Implementation Method of Fixed Blades"

[0051] refer to Figures 3 to 12 The embodiments of the fixed blades will be described below. Furthermore, the fixed blades described below are all specific examples of the fixed blade 36 described in the "Embodiments of the Gas Turbine" section above.

[0052] like Figure 3As shown, the fixed blade 50 of this embodiment has a blade body 51, an inner shield 60I, and an outer shield 60O. The blade body 51 has a blade-shaped cross-section and extends in the blade height direction, which has a directional component perpendicular to the cross-section. Furthermore, as... Figure 2 As shown, when the fixed blade 50 (36) is mounted on the turbine housing 38, the blade height direction becomes radial DR. The blade body 51 (36B) is positioned in the combustion gas flow path 39 of the combustion gas G flow path (reference). Figure 2 The inner shield 60I is provided radially (DR) at the end of the inner DRI of the blade body 51. In other words, the inner shield 60I is provided at the end of one side of the blade body 51 in the blade height direction. The inner shield 60I extends in a direction perpendicular to the blade height direction. The inner shield 60I defines the edge of the inner DRI of the annular combustion gas flow path 39 in the radial DR. The outer shield 60O is provided radially (DR) at the end of the outer DRO of the blade body 51. In other words, the outer shield 60O is provided at the end of the blade body 51 on the other side in the blade height direction. The outer shield 60O also extends in a direction perpendicular to the blade height direction. The outer shield 60O defines the edge of the outer DRO of the annular combustion gas flow path 39 in the radial DR. Therefore, as described in the above "Embodiment of Gas Turbine", both the inner shield 60I and the outer shield 60O are flow path forming plates that define a part of the combustion gas flow path 39.

[0053] like Figures 3-7 As shown, the leading edge 52 is formed at the end of the upstream side DAU of the blade body 51, and the trailing edge 53 is formed at the end of the downstream side DAD. On the surface of the blade body 51, the convex surface facing the circumferential direction DC forms the dorsal surface 55 (=negative pressure surface), and the concave surface forms the ventral surface 54 (=positive pressure surface). Furthermore, for ease of explanation below, the side of the ventral surface 55 facing the circumferential direction DC of the blade body 51 is designated as the first side DC1, and the side of the dorsal surface 54 facing the circumferential direction DC of the blade body 51 is designated as the second side DC2.

[0054] like Figure 3 , Figure 4 and Figure 7 As shown, the inner shield 60I, which serves as the flow path forming plate, has an inner shield body 61I and a peripheral wall 65I. The inner shield body 61I has a gas path surface 64P facing outward DRO, a gas path opposite surface 64A facing inward DRI, an end face 62F (front end face) of the upstream DAU, an end face 62B (rear end face) of the downstream DAD, an end face 63P (ventral end face) of the first circumferential side DC1, and an end face 63N (back end face) of the second side DC2. The front end face 62F is substantially parallel to the rear end face 62B. Furthermore, the ventral end face 63P is substantially parallel to the back end face 63N. Therefore, as Figure 7As shown, when viewed from the radial DR position, the inner protective cover body 61I has a parallelogram shape.

[0055] A peripheral wall 65I protrudes inward from the gas path opposite side 64A of the inner shield body 61I towards the inner DRI (flow path opposite side). This peripheral wall 65I is disposed along the end face of the inner shield body 61I. The peripheral wall 65I has a front wall 65F and a rear wall 65B facing each other in the axial direction DA, and a ventral side wall 65P and a dorsal side wall 65N facing each other in the circumferential direction DC. The front wall 65F is disposed along the front end face 62F of the inner shield body 61I. The rear wall 65B is disposed along the rear end face 62B of the inner shield body 61I. The ventral side wall 65P is disposed along the ventral end face 63P of the inner shield body 61I. The dorsal side wall 65N is disposed along the dorsal end face 63N of the inner shield body 61I. On the inner shield 60I, a recess 66 is formed by the inner shield body 61I and the peripheral wall 65I, recessed towards the outer DRO. Furthermore, the surface of the first side DC1 of the ventral wall 65P is coplanar with the ventral end face 63P of the inner shield body 61I. Also, the surface of the second side DC2 of the dorsal wall 65N is coplanar with the dorsal end face 63N of the inner shield body 61I. Although the rear wall 65B is formed along the rear end face 62B of the inner shield body 61I, it is formed on the upstream side DAU, which is further upstream than the rear end face 62B. Therefore, in the gas path opposite surface 64A of the shield body 61I, with the rear wall 65B as a reference, the surface of the upstream side DAU forms the bottom surface of the aforementioned recess 66. Furthermore, in the gas path opposite surface 64A of the shield body 61I, with the rear wall 65B as a reference, the surface of the downstream side DAU does not form the bottom surface of the aforementioned recess 66 but forms the outer gas path opposite surface 64AO. The outer gas path opposite surface 64AO of the inner shield 60I is formed to gradually approach the gas path surface 64P as it moves towards the downstream side DAD.

[0056] like Figure 4 As shown, in the composition Figure 2 A retainer 69 is provided on the fixed blade 50 of any of the fixed blade rows 35 shown, protruding from the ventral sidewall 65P and the back sidewall 65N of the inner shroud 60I toward the inward DRI. This retainer 69 is located between the front wall 65F and the rear wall 65B in the axial direction DA, and extends from the ventral end face 63P to the back end face 63N. This retainer 69 contacts the outer DRO end of the inner shroud 7 fixed to the gas turbine housing 8 and serves to support a portion of the inner DRI of the fixed blade 50 on the end of the outer DRO of the inner shroud 7. A retainer channel 69P extending through the axial direction DA is formed on this retainer 69.

[0057] like Figure 3 , Figure 4 and Figure 6 As shown, the outer shield 60O, which serves as the flow path forming plate, has an outer shield body 61O and a peripheral wall 65O. Similar to the inner shield body 61I, the outer shield body 61O also has a gas path surface 64P, a gas path opposite surface 64A, a front end surface 62F, a rear end surface 620B, a ventral end surface 63P, and a dorsal end surface 63N. Like the inner shield body 61I, the outer shield body 61O also has a parallelogram shape when viewed radially (DR). Furthermore, the gas path surface 64P of the inner shield body 61I faces outward (DRO), but the gas path surface 64P of the outer shield body 61O faces inward (DRI).

[0058] A peripheral wall 65O protrudes outward from the opposite side 64A of the gas path of the outer shield body 61O towards the DRO (opposite flow path). This peripheral wall 65O is disposed along the end face of the outer shield body 61O. Similar to the peripheral wall 65I of the inner shield 60I, the peripheral wall 65O of ​​the outer shield 60O also has a front wall 65F, a rear wall 65B, a ventral wall 65P, and a dorsal wall 65N. The front wall 65F is located along the front end face 62F of the outer shield body 61O. The rear wall 65B is located along the rear end face 620B of the outer shield body 61O. The ventral wall 65P is located along the ventral end face 63P of the outer shield body 61O. The dorsal wall 65N is located along the dorsal end face 63N of the outer shield body 61O. On the outer protective cover 60O, a recess 66 is formed by the outer protective cover body 61O and the peripheral wall 65O, recessed towards the inward DRI. Furthermore, the surface of the first side DC1 of the ventral side wall 65P is coplanar with the ventral end face 63P of the outer protective cover body 61O. And the surface of the second side DC2 of the dorsal side wall 65N is coplanar with the dorsal end face 63N of the outer protective cover body 61O.

[0059] like Figure 3 and Figure 4As shown, the blade body 51 has a first blade channel 71, a second blade channel 72, a third blade channel 73, a fourth blade channel 74, a plurality of leading edge injection channels 75, and a plurality of trailing edge injection channels 76. The first blade channel 71, the second blade channel 72, the third blade channel 73, and the fourth blade channel 74 are arranged in this order along the arc CL of the blade body 51 from one side of the leading edge 52 toward one side of the trailing edge 53. The first blade channel 71, the second blade channel 72, the third blade channel 73, and the fourth blade channel 74 all extend in the radial direction DR. The ends of the outer DRO of the first blade channel 71, the second blade channel 72, the third blade channel 73, and the fourth blade channel 74 are all opened at a position further outward than the gas path opposite to the outer shield body 61O on the opposite side 64A. The ends of the inner DRI of the first blade channel 71 and the fourth blade channel 74 are closed by the inner shield body 61I. The ends of the inner DRI of the second blade passage 72 and the inner DRI of the third blade passage 73 open at positions further inward than the gas path opposite to the inner shroud body 61I. Multiple leading-edge injection channels 75 extend from the inner circumferential surface of the first blade passage 71 to a surface near the leading edge 52 on the outer surface of the blade body 51, penetrating the leading edge portion of the blade body 51, so that a portion of the cooling air ACL flowing in 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. Multiple trailing-edge injection channels 76 extend from the inner circumferential surface of the fourth blade passage 74 to a surface near the trailing edge 53 on the outer surface of the blade body 51, penetrating the trailing edge portion of the blade body 51, so that a portion of the cooling air ACL flowing in 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.

[0060] like Figure 5 As shown, 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 shield body 61I, 61O, and the end face of each shield body 61I, 61O. This thermal barrier coating 56 has a ceramic layer formed from ZrO2-based ceramics. The thermal barrier coating 56 is also applied to the outer gas path opposite surface 64AO of the inner shield body 61I and the surface facing downstream of the retainer 69 (DAD).

[0061] like Figure 4 As shown, in this embodiment, the outer protective cover 60O is provided with a blade air passage cover 57, a sealing plate 58, and an impact plate 59. Furthermore, in this embodiment, the inner protective cover 60I is also provided with a blade air passage cover 57, a sealing plate 58, and an impact plate 59.

[0062] The blade air passage cover 57, located on the outer shroud 60O, is connected to the opposite side 64A of the gas path of the outer shroud body 61O in such a way that it covers the openings at the ends of the outer DROs of the first blade passage 71, the second blade passage 72, the third blade passage 73, and the fourth blade passage 74. A blade air passage cover 57 is connected to the blade air passage cover 57. Figure 2 The cooling air duct 44 is shown. Therefore, a portion of the cooling air ACL from the cooling unit 40 flows into the first blade passage 71, the second blade passage 72, the third blade passage 73, and the fourth blade passage 74 after entering the blade air passage shroud 57. (As shown...) Figure 4 and Figure 8 As shown, the sealing plate 58 divides the space within the recess 66 of the outer shield 60O into an external space of the outer DRO (opposite flow path side) and a cooling air space 67 of the inner DRI (flow path side). The impact plate 59 divides the cooling air space 67 into a first space 67A of the outer DRO (opposite flow path side) and a second space 67B of the inner DRI (flow path side). A plurality of through holes 59A are formed on the impact plate 59, penetrating radially in the DR direction. Cooling air ACL in the first space 67A flows into the second space 67B through the plurality of through holes 59A of the impact plate 59. At this time, the cooling air ACL through the plurality of through holes 59A of the impact plate 59 impacts and cools the gas path opposite side 64A of the outer shield body 61O. A cooling air exhaust pipe 45 is connected to the impact plate 59. The cooling air exhaust pipe 45 extends from the impact plate 59 to the outer DRO and passes through the sealing plate 58. Cooling air ACL, which flows into the second space 67B and impacts the gas path opposite to the outer shield body 61O, is guided, for example, into the intermediate housing 6 via the cooling air exhaust pipe 45. Additionally, the cooling air ACL can be guided via the cooling air exhaust pipe 45 to the tailpipe 22 of the burner 20 for cooling the tailpipe 22.

[0063] The blade air passage cover 57, located in the inner shroud 60I, is connected to the opposite side 64A of the gas path of the inner shroud body 61I in such a way that it covers the openings at the ends of the inner DRIs of the second blade passage 72 and the third blade passage 73. Figure 4 , Figure 5 and Figure 8As shown, the sealing plate 58 divides the space within the recess 66 of the inner shield 60I into an outer space of the inner DRI (opposite flow path side) and a cooling air space 67 of the outer DRO (flow path side). The impact plate 59 divides the cooling air space 67 into a first space 67A of the inner DRI (opposite flow path side) and a second space 67B of the outer DRO (flow path side). A plurality of through holes 59A are formed on the impact plate 59, penetrating radially in the DR direction. The cooling air ACL in the first space 67A flows into the second space 67B through the plurality of through holes 59A of the impact plate 59. At this time, the cooling air ACL through the plurality of through holes 59A of the impact plate 59 impacts and cools the gas path opposite side 64A of the inner shield body 61I. A cooling air exhaust pipe 45 is connected to the impact plate 59. The cooling air exhaust pipe 45 extends from the impact plate 59 to the inner DRI and passes through the sealing plate 58. Cooling air ACL, which flows into the second space 67B and impacts the opposite side 64A of the gas path of the outer shield body 61O, is guided to the intermediate housing 6 via the cooling air exhaust pipe 45.

[0064] like Figure 4 and Figure 6 As shown, the outer shield body 61O has multiple internal channels 80, a front inlet channel 85, a rear inlet channel 86, a first outlet channel 87A, a third outlet channel 88A, a second outlet channel 87B, a fourth outlet channel 88B, and an angle spray channel 89. The multiple internal channels 80 are formed along any one of the multiple end faces of the outer shield body 61O. The multiple internal channels 80 include a front end channel 81, a first transverse channel 82A, a second transverse channel 82B, a rear end channel 83O, a third transverse channel 84A, and a fourth transverse channel 84B.

[0065] The front-end channel 81 extends along the gas path surface 64P and the front-end surface 62F of the outer shield body 61O, and in the circumferential direction DC, extending in the direction of the gas path surface 64P and the direction of the front-end surface 62F. The front-end channel 81 extends in the circumferential direction DC from a position near the ventral end face 63P of the outer shield body 61O to a position near the dorsal end face 63N of the outer shield body 61O. The front-end channel 81 has a front inlet (second inlet) 81E located approximately at the middle position in the direction in which it extends, capable of guiding cooling air ACL within the front-end channel 81. In this front-end channel 81, a portion on one side of the ventral end face 63P, based on the front inlet 81E, forms the front-end first channel 81A, and a portion on one side of the dorsal end face 63N, based on the front inlet 81E, forms the front-end second channel 81B.

[0066] The front inlet passage 85 connects the front end passage 81 to the first blade passage 71. The front inlet passage 85 has the aforementioned front inlet 81E that opens onto the second demarcated surface of the front end passage 81. Therefore, a portion of the cooling air ACL in the first blade passage 71 can flow into the front end passage 81 via the front inlet passage 85.

[0067] The first transverse channel 82A extends along the gas path surface 64P and the ventral end face 63P of the outer shield body 61O, and extends in the direction of the gas path surface 64P and the ventral end face 63P. The first transverse channel 82A connects to the end of the front first channel 81A on the ventral end face 63P side. The connection portion of the first transverse channel 82A with the front first channel 81A forms the inlet of the first transverse channel 82A. The first transverse channel 82A extends from the connection portion with the front first channel 81A to approximately the middle position of the outer shield body 61O. The first outlet channel 87A connects to the downstream end of the first transverse channel 82A, such as... Figure 8 As shown, the first transverse channel 82A is connected to the first space 67A of the outer shield 60O. Therefore, the cooling air ACL in the front first channel 81A, after flowing into the first transverse channel 82A, can flow into the first space 67A through the first outlet channel 87A.

[0068] The second transverse channel 82B extends along the gas path surface 64P and the back end face 63N of the outer shield body 61O, and extends in the direction of expansion of the gas path surface 64P and the direction of expansion of the back end face 63N. This second transverse channel 82B connects to the end of the front second channel 81B on the back end face 63N side. The connection portion in the second transverse channel 82B with the front second channel 81B forms the inlet of the second transverse channel 82B. This second transverse channel 82B extends from the connection portion with the front second channel 81B to approximately the middle position in the axial direction DA of the outer shield body 61O. Figure 8 As shown, the second outlet channel 87B is connected to the downstream end of the second transverse channel 82B, thereby connecting the second transverse channel 82B with the first space 67A of the outer shroud 60O. Therefore, the cooling air ACL in the front end second channel 81B, after flowing into the second transverse channel 82B, can flow into the first space 67A via the second outlet channel 87B.

[0069] The rear end channel 83O extends along the gas path surface 64P and the rear end face 620B of the outer shield body 61O, and in the circumferential direction DC, in the direction of expansion of the gas path surface 64P and the direction of expansion of the rear end face 620B. The rear end channel 83O extends in the circumferential direction DC from a position near the ventral end face 63P of the outer shield body 61O to a position near the dorsal end face 63N of the outer shield body 61O.

[0070] Furthermore, the rear-end channel 83O is formed as a different channel from the air channel described later, and is a separate channel for the flow of cooling air inside. That is, the rear-end channel 83O is formed independently of the air channel. For example, when viewed from the circumferential DC direction, the rear-end channel 83O is formed away from the rear-end channel 83I described later.

[0071] The rear end channel 83O has a rear inlet (second inlet) 830E located approximately at the center of its extension direction, capable of guiding cooling air ACL within the rear end channel 83O. In the rear end channel 83O, a portion of one side of the ventral end face 63P, based on the rear inlet 830E, forms the rear end first channel 83A, and a portion of one side of the dorsal end face 63N, also based on the rear inlet 830E, forms the rear end second channel 83B. The rear end first channel 83A extends from the rear inlet 830E toward a first side DC1 on both sides in the circumferential direction DC. The rear end second channel 83B extends in the circumferential direction DC from the rear inlet 830E toward a second side DC2 on the side opposite to the first side DC1.

[0072] The rear inlet passage 86 connects the rear end passage 83O to the fourth blade passage 74. The rear inlet passage 86 has the aforementioned rear inlet 830E, which opens onto the second demarcation surface of the rear end passage 83O. Therefore, a portion of the cooling air ACL within the fourth blade passage 74 can flow into the rear end passage 83O via the rear inlet passage 86.

[0073] The third transverse channel 84A extends along the gas path surface 64P and the ventral end face 63P of the outer shield body 61O, and extends in the direction of the gas path surface 64P and the ventral end face 63P. The third transverse channel 84A connects to the end of the rear first channel 83A on the ventral end face 63P side. The connection portion of the third transverse channel 84A with the rear first channel 83A forms the inlet of the third transverse channel 84A. The third transverse channel 84A extends from the connection portion with the rear first channel 83A to approximately the middle position in the axial direction DA of the outer shield body 61O. The third outlet channel 88A connects to the end of the upstream side DAU of the third transverse channel 84A, as shown below. Figure 8 As shown, the third transverse channel 84A is connected to the first space 67A of the outer shield 60O. Therefore, the cooling air ACL in the rear first channel 83A, after flowing into the third transverse channel 84A, can flow into the first space 67A through the third outlet channel 88A.

[0074] Angle injection channel 89 extends from the end of the ventral end face 63P side of the rear first channel 83A to the angle between the rear end face 620B and the ventral end face 63P of the outer shield 60O, and passes through the angle between the rear end face 620B and the ventral end face 63P of the outer shield 60O, so that a portion of the cooling air ACL flowing from the end of the ventral end face 63P side of the rear first channel 83A is injected from the angle between the rear end face 620B and the ventral end face 63P of the outer shield 60O into the combustion gas flow path.

[0075] The fourth transverse channel 84B extends along the gas path surface 64P and the back end face 63N of the outer shield body 61O, and extends in the direction of expansion of the gas path surface 64P and the direction of expansion of the back end face 63N. This fourth transverse channel 84B connects to the end of the rear second channel 83B on the back end face 63N side. The connection portion of the fourth transverse channel 84B with the rear second channel 83B forms the inlet of the fourth transverse channel 84B. This fourth transverse channel 84B extends from the connection portion with the rear second channel 83B to approximately the middle position in the axial direction DA of the outer shield body 61O. The fourth outlet channel 88B connects to the end of the upstream side DAU of the third transverse channel 84A, as shown below. Figure 8 As shown, the fourth transverse channel 84B is connected to the first space 67A of the outer shield 60O. Therefore, the cooling air ACL in the rear second channel 83B, after flowing into the fourth transverse channel 84B, can flow into the first space 67A through the fourth outlet channel 88B.

[0076] like Figure 9As shown, the rear channel 83O is defined by a plurality of second defining surfaces. All of the second defining surfaces extend in the circumferential direction DC. Each of the second defining surfaces has a second gas path defining surface 91O, a second end defining surface 92O, a gas path defining opposite 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 shield body 61O. The gas path defining opposite surface 93 separates from the second gas path defining surface 91O outwards DRO and is opposite to 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 shield body 61O. One edge of the gas path surface 64P in the second end defining surface 92O, i.e., the gas path side edge, is connected to one edge of the rear end surface 620B in the second gas path defining surface 91O, i.e., the end side edge, via a second corner 950. One edge of the gas path opposite surface 64A on the second end defining surface 92O is connected to one edge of the rear end surface 620B on the gas path opposite surface 93. The inner defining surface 94 separates from the second end defining surface 92O upstream of the second end defining surface 92O and is opposite to the second end defining surface 92O. The aforementioned rear inlet 830E is formed on this inner defining surface 94. The rear inlet 830E is formed on the inner defining surface 94 so that the cooling air flowing into the rear end channel 83O from the rear inlet 830E collides with the second end defining surface 92O. The side edge of the gas path surface 64P in the inner defining surface 94 is connected to the second gas path defining surface 91O, and the side edge of the gas path opposite surface 64A in the inner defining surface 94 is connected to the gas path opposite surface 93.

[0077] The angle between the second end defining surface 92O and the second gas path defining surface 91O is approximately a right angle. That is, the second corner 950 is formed at approximately a right angle. The angle between the opposite gas path defining surface 93 and the second end defining surface 92O is approximately a right angle. The angle between the inner defining surface 94 and the opposite gas path defining surface 93 is approximately a right angle. The angle between the second gas path defining surface 91O and the inner defining surface 94 is approximately a right angle. Therefore, the cross-sectional shape of the rear end channel 83O is approximately rectangular.

[0078] like Figure 9 and Figure 10As shown, the second gas path defining surface 91O is a series of alternating concave and convex surfaces in the circumferential direction DC, consisting of a second gas path bottom surface 91AO and a second gas path protruding surface 91BO located on the side of the second gas path bottom surface 91AO that is farther from the gas path surface 64P. That is, the second gas path defining surface 91O forms a first vertical spoiler 917. Therefore, the first vertical spoiler 917 is formed to protrude towards the interior of the rear end channel 83O. Furthermore, multiple first vertical spoilers 917 are formed separately in the circumferential direction DC. The multiple first vertical spoilers 917 extend vertically relative to the circumferential direction DC. The first vertical spoiler 917 is formed by the second gas path bottom surface 91AO, the second gas path protruding surface 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 the second gas path connecting surface 91CO. The bottom surface 91AO of the second gas path, the protruding surface 91BO of the second gas path, and the connecting surface 91CO of the second gas path all extend in a direction perpendicular to the circumferential DC.

[0079] The first vertical spoiler 917 is shaped like a long, thin guide rail that traverses the bottom surface 91AO of the second gas path and protrudes from the bottom surface 91AO. The cross-section of the first vertical spoiler 917 is rectangular. Furthermore, the width (width in the circumferential direction DC) of the upper surface of the convex portion of the first vertical spoiler 917 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 protrusion surface 91BO. And the bottom surface of the concave portion is the second gas path bottom surface 91AO sandwiched between the two second gas path protrusion surfaces 91BO. Preferably, the width of the upper surface of the convex portion, i.e., the second gas path protrusion surface 91BO, is less than 1 / 2 of the width of the bottom surface of the concave portion, i.e., the second gas path bottom surface 91AO. Moreover, the width of the second gas path protrusion surface 91BO is more preferably less than 1 / 3 of the width of the second gas path bottom surface 91AO.

[0080] The second end defining surface 92O is a series of alternating concave and convex surfaces, consisting of a second end bottom surface 92AO and a second end protruding surface 92BO located on the side of the second end bottom surface 92AO away from the rear end surface 620B, in the circumferential direction DC. That is, the second end defining surface 92O forms a second vertical spoiler 927. Therefore, the second vertical spoiler 927 is formed to protrude towards the interior of the rear end channel 83O. Furthermore, multiple second vertical spoilers 927 are formed separately in the circumferential direction DC. The multiple second vertical spoilers 927 extend vertically relative to the circumferential direction DC. The second vertical spoiler 927 is formed by the second end bottom surface 92AO, the second end protruding surface 92BO, and the second end connecting surface 92CO. The second end bottom surface 92AO and the second end protruding surface 92BO are connected by the second end connecting surface 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 the virtual plane VP1 containing 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 virtual plane VP1.

[0081] The second vertical spoiler 927 is shaped like a long, thin guide rail that traverses the second end bottom surface 92AO and protrudes from it. The cross-section of the second vertical spoiler 927 is rectangular. Furthermore, the width (circumferential DC width) of the upper surface of the convex portion of the second vertical spoiler 927 is narrower than the width of the bottom surface of the concave portion. Specifically, the upper surface of the convex portion is the second end protrusion surface 92BO. The bottom surface of the concave portion is the second end bottom surface 92AO, which is sandwiched between the two second end protrusion surfaces 92BO. The width of the upper surface of the convex portion, i.e., the second end protrusion surface 92BO, is preferably less than 1 / 2 the width of the bottom surface of the concave portion, i.e., the second end bottom surface 92AO. More preferably, the width of the second end protrusion surface 92BO is less than 1 / 3 the width of the second end bottom surface 92AO.

[0082] The circumferential DC position of the gas path side edge on the second end protrusion 92BO is different from the circumferential DC position of the end side edge on the second gas path protrusion 91BO. Therefore, the circumferential DC positions of the first vertical spoiler 925 and the second vertical spoiler 927 facing the second corner 950 are different from each other. The ends of the second corner 950 facing the first vertical spoiler 925 and the second vertical spoiler 927 are separated from each other in the circumferential DC. That is, the first vertical spoiler 925 and the second vertical spoiler 927 are not arranged in the same position in the circumferential DC. They are staggered in such a way that the protrusion of a second vertical spoiler 927 is arranged between the adjacent protrusions of the two first vertical spoilers 925 in the circumferential DC. Therefore, the first vertical spoiler 925 and the second vertical spoiler 927 are staggered in the circumferential DC such that the second vertical spoiler 927 is arranged between the two adjacent first vertical spoilers 925 in the circumferential DC.

[0083] Furthermore, similar to the rear end channel 830 in the outer shield body 610, the front end channel 81, the first transverse channel 82A, the second transverse channel 82B, the third transverse channel 84A, and the fourth transverse channel 84B in the outer shield body 610 are defined by a second gas path defining surface, a second end defining surface, a gas path defining opposite surface, and an inner defining surface. That is, the front end channel 81, the first transverse channel 82A, the second transverse channel 82B, the third transverse channel 84A, and the fourth transverse channel 84B in the outer shield body 610 form separate channels. Also similar to the second gas path defining surface 91O and the second end defining surface 92O of the rear end channel 830 in the outer shield body 610, the second gas path defining surface and the second end defining surface of these separate channels also form multiple first vertical baffles 917 and multiple second vertical baffles 927.

[0084] like Figure 4 and Figure 7 As shown, similar to the outer shield body 61O, the inner shield body 61I has multiple internal channels 80, a front inlet channel 85, a rear inlet channel 86, a first outlet channel 87A, a third outlet channel 88A, a fourth outlet channel 88B, and an angle spray channel 89. The multiple internal channels 80 are formed along any one of the multiple end faces of the inner shield body 61I. Similar to the multiple internal channels 80 of the outer shield body 61O, the multiple internal channels 80 have a front end channel 81, a first transverse channel 82A, a second transverse channel 82B, a rear end channel 83I, a third transverse channel 84A, and a fourth transverse channel 84B.

[0085] The front-end channel 81 extends along the gas path surface 64P and the front-end surface 62F of the inner shield body 61I, and in the circumferential direction DC, extending in the direction of the gas path surface 64P and the direction of the front-end surface 62F. The front-end channel 81 extends in the circumferential direction DC from a position near the ventral end face 63P of the inner shield body 61I to a position near the dorsal end face 63N of the inner shield body 61I. The front-end channel 81 has a front inlet 81E located approximately at the middle position in the direction of its extension, which guides cooling air ACL within the front-end channel 81. In this front-end channel 81, a portion of one side of the ventral end face 63P, based on the front inlet 81E, forms the first front-end channel 81A, and a portion of one side of the dorsal end face 63N, based on the front inlet 81E, forms the second front-end channel 81B.

[0086] The front inlet passage 85 connects the front end passage 81 with the second blade passage 72. The front inlet passage 85 has the aforementioned front inlet 81E that opens onto the second demarcated surface of the front end passage 81. Therefore, a portion of the cooling air ACL in the second blade passage 72 can flow into the front end passage 81 via the front inlet passage 85.

[0087] The first transverse channel 82A extends along the gas path surface 64P and the ventral end face 63P of the inner shield body 61I, and extends in the direction of the gas path surface 64P and the ventral end face 63P. The first transverse channel 82A connects to the end of the front first channel 81A on the ventral end face 63P side. The connection portion of the first transverse channel 82A with the front first channel 81A forms the inlet of the first transverse channel 82A. The first transverse channel 82A extends from the connection portion with the front first channel 81A to approximately the middle position in the axial direction DA of the inner shield body 61I. The first outlet channel 87A connects to the downstream end of the first transverse channel 82A on the DAD side, as shown below. Figure 8 As shown, the first transverse channel 82A is connected to the first space 67A of the inner shroud 60I. Therefore, the cooling air ACL in the front first channel 81A, after flowing into the first transverse channel 82A, can flow into the first space 67A through the first outlet channel 87A.

[0088] The second transverse channel 82B extends along the gas path surface 64P and the back end face 63N of the inner shield body 61I, and extends in the direction of expansion of the gas path surface 64P and the back end face 63N. This second transverse channel 82B connects to the end of the front second channel 81B on the back end face 63N side. The connection portion in the second transverse channel 82B with the front second channel 81B forms the inlet of the second transverse channel 82B. This second transverse channel 82B extends from the connection portion with the front second channel 81B to approximately the middle position in the axial direction DA of the inner shield body 61I. Figure 8As shown, the second outlet channel 87B is connected to the downstream end of the second transverse channel 82B, thereby connecting the second transverse channel 82B with the first space 67A of the inner shroud 60I. Therefore, the cooling air ACL in the front second channel 81B, after flowing into the second transverse channel 82B, can flow into the first space 67A via the second outlet channel 87B.

[0089] Similar to the rear end channel 830 in the aforementioned outer shield body 61O, the front end channel 81, the first transverse channel 82A, the second transverse channel 82B, the third transverse channel 84A, and the fourth transverse channel 84B in the inner shield body 61I are defined by a second gas path defining surface, a second end defining surface, a gas path defining opposite surface, and an inner defining surface. That is, in this embodiment, the front end channel 81, the first transverse channel 82A, the second transverse channel 82B, the third transverse channel 84A, and the fourth transverse channel 84B in the inner shield body 61I are formed as separate channels. Furthermore, similar to the second gas path defining surface 91O and the second end defining surface 92O of the aforementioned rear end channel 83O in the outer shield body 61O, the second gas path defining surface and the second end defining surface of these separate channels also form a plurality of first vertical baffles 917 and a plurality of second vertical baffles 927.

[0090] The rear end channel 83I extends along the gas path surface 64P and the rear end surface 62B of the inner shield body 61I, and in the circumferential direction DC, in the direction of the gas path surface 64P and the direction of the rear end surface 62B. The rear end channel 83I extends in the circumferential direction DC from a position near the ventral end surface 63P of the inner shield body 61I to a position near the dorsal end surface 63N of the inner shield body 61I.

[0091] Furthermore, the rear-end channel 83I is formed as a channel different from the separation channel, and is an internal air channel for the flow of cooling air. That is, the rear-end channel 83I is an internal channel 80, i.e., an air channel, formed independently of the separation channel. For example, when viewed from the circumferential DC direction, the rear-end channel 83I is formed away from the front-end channel 81.

[0092] The rear end channel 83I has a rear inlet (inlet) 83E located approximately at the middle of its extending direction, which guides cooling air ACL within the rear end channel 83I. In this embodiment, only the rear inlet 83E of the rear end channel 83I of the inner shield body 61I is an inlet. In this rear end channel 83I, a portion of one side of the ventral end face 63P, based on the rear inlet 83E, forms the rear end first channel 83A, and a portion of one side of the dorsal end face 63N, based on the rear inlet 83E, forms the rear end second channel 83B. In this embodiment, only the rear end first channel 83A of the inner shield body 61I is a first air channel, and only the rear end second channel 83B of the inner shield body 61I is a second air channel.

[0093] The rear inlet channel 86 connects the rear end channel 83I to the third blade channel 73. The rear inlet channel 86 extends from the third blade channel 73 toward the downstream side DAD, which is perpendicular to the circumferential direction DC (first direction). This rear inlet channel 86 has the aforementioned rear inlet 83E, which opens onto the defined surface of the rear end channel 83I. Therefore, a portion of the cooling air ACL within the third blade channel 73 can flow into the rear end channel 83I via this rear inlet channel 86. In this embodiment, the rear inlet channel 86 of the inner shroud body 61I serves as the inlet channel.

[0094] The third transverse channel 84A extends along the gas path surface 64P and the ventral end face 63P of the inner shield body 61I, and extends in the direction of the gas path surface 64P and the ventral end face 63P. This third transverse channel 84A connects to the end of the rear first channel 83A on the ventral end face 63P side. The connection portion of the third transverse channel 84A with the rear first channel 83A forms the inlet of the third transverse channel 84A. The third transverse channel 84A extends from the connection portion with the rear first channel 83A to approximately the middle position in the axial direction DA of the inner shield body 61I. The third outlet channel 88A connects to the end of the upstream side DAU of the third transverse channel 84A, as shown below. Figure 8 As shown, the third transverse channel 84A is connected to the first space 67A of the inner shield 60I. Therefore, the cooling air ACL in the rear first channel 83A, after flowing into the third transverse channel 84A, can flow into the first space 67A through the third outlet channel 88A.

[0095] Angle injection channel 89 extends from the end of the ventral end face 63P side of the rear first channel 83A to the angle between the rear end face 62B and the ventral end face 63P of the outer shield, and passes through the angle between the rear end face 62B and the ventral end face 63P of the inner shield 60I, so that a portion of the cooling air ACL flowing from the end of the ventral end face 63P side of the rear first channel 83A is injected from the angle between the rear end face 62B and the ventral end face 63P of the inner shield 60I into the combustion gas flow path.

[0096] The fourth transverse channel 84B extends along the gas path surface 64P and the back end face 63N of the inner shield body 61I, and extends in the direction of the gas path surface 64P and the direction of the back end face 63N. This fourth transverse channel 84B connects to the end of the rear second channel 83B on the side of the back end face 63N. The connection portion of the fourth transverse channel 84B with the rear second channel 83B forms the inlet of the fourth transverse channel 84B. This fourth transverse channel 84B extends from the connection portion with the rear second channel 83B to approximately the middle position in the axial direction DA of the inner shield body 61I. The fourth outlet channel 88B connects to the end of the upstream side DAU of the third transverse channel 84A, as shown below. Figure 8 As shown, the fourth transverse channel 84B is connected to the first space 67A of the inner shield 60I. Therefore, the cooling air ACL in the rear second channel 83B, after flowing into the fourth transverse channel 84B, can flow into the first space 67A through the fourth outlet channel 88B.

[0097] like Figure 5 and Figure 11 As shown, the rear channel 83I is defined by multiple defining surfaces. These multiple defining surfaces all extend in the circumferential direction (DC). Each defining surface has a gas path defining surface 91I, an end defining surface 92I, a gas path defining opposite surface 93, and an inner defining surface 94. The gas path defining surface 91I is back-to-back with the gas path surface 64P of the inner shield body 61I. The gas path defining opposite surface 93 separates from the gas path defining surface 91I towards the inner DC and is opposite to the gas path defining surface 91I. The end defining surface 92I is back-to-back with the rear end surface 62B of the inner shield body 61I. One edge of the gas path surface 64P in the end defining surface 92I, i.e., the gas path side edge, is connected via a first corner 95 to one edge of the rear end surface 62B in the gas path defining surface 91I, i.e., the end side edge. One edge of the gas path opposite surface 64A in the end defining surface 92I is connected to one edge of the rear end surface 62B in the gas path opposite surface 93. The inner defining surface 94 separates from the end defining surface 92I upstream and is opposite to the end defining surface 92I. The aforementioned rear inlet 83E is formed on the inner defining surface 94. The rear inlet 83E is formed on the inner defining surface 94 so that the cooling air flowing into the rear end channel 83I from the rear inlet 83E collides with the end defining surface 92I. The side edge of the gas path surface 64P in the inner defining surface 94 is connected to the gas path defining surface 91I, and the side edge of the gas path opposite surface 64A in the inner defining surface 94 is connected to the gas path opposite surface 93.

[0098] The end-demarcation surface 92I is approximately parallel to the outer gas path opposite surface 64A of the inner shield body 61I (reference). Figure 5Therefore, the angle of the end defining surface 92I relative to the gas path defining surface 91I is an acute angle. That is, the first corner 95 is formed at an acute angle. Therefore, when viewed from the circumferential DC direction, the second corner 950 is formed at an angle greater than that of the first corner 95. The angle of the opposite gas path defining surface 93 relative to the end defining surface 92I is an obtuse angle. The angle of the inner defining surface 94 relative to the opposite gas path defining surface 93 is approximately a right angle. The angle of the gas path defining surface 91I relative to the inner defining surface 94 is approximately a right angle. Therefore, the cross-sectional shape of the rear channel 83I is approximately a frustum shape.

[0099] like Figure 11 and Figure 12 As shown, the gas path defining surface 91I of the rear first channel 83A and the gas path defining surface 91I of the rear second channel 83B are both gas path bottom surface 91AI and gas path protruding surface 91BI located on the side of the gas path bottom surface 91AI away from the gas path surface 64P, which are alternating concave and convex surfaces repeated in the circumferential direction DC. That is, the gas path defining surface 91I is formed with a first baffle 915. Therefore, the first baffle 915 is formed to protrude toward the interior of the rear channel 83I. Furthermore, multiple first baffles 915 are formed separately in the circumferential direction DC. The multiple first baffles 915 extend in an inclined direction in a manner that intersects the circumferential direction DC. The first baffle 915 is formed by the gas path bottom surface 91AI, the gas path protruding surface 91BI, and the gas path connecting surface 91CI. The gas path bottom surface 91AI and the gas path protruding surface 91BI are connected in the gas path connecting surface 91CI. The bottom surface 91AI, the protruding surface 91BI, and the connecting surface 91CI of the gas path all extend in a direction intersecting the circumferential DC. However, the bottom surface 91AI, the protruding surface 91BI, and the connecting surface 91CI of the gas path all extend in a direction inclined relative to the circumferential DC (first direction) as they move away from the rear end face 62B (first end face) of the inner shield body 61I, towards the circumferential downstream side DCD (downstream side of the first direction) away from the rear inlet 83E in the circumferential DC (first direction). The direction in which the bottom surface 91AI, the protruding surface 91BI, and the connecting surface 91CI of the gas path extend is at an angle Θ of 45° to 75°, for example, 60°, relative to the circumferential DC (first direction). In addition, the circumferential downstream side DCD (downstream side of the first direction) in the rear first channel 83A is the first side DC1, and the circumferential downstream side DCD (downstream side of the first direction) in the rear second channel 83B is the second side DC2. Therefore, the plurality of first spoilers 915 gradually extend in a direction inclined relative to the circumferential direction as they move away from the first corner 95 away from the rear inlet 83E in the circumferential DC direction.

[0100] The first spoiler 915 is a long and thin guide rail that obliquely traverses the bottom surface 91AI of the gas path, protruding from the bottom surface 91AI. The cross-section of the first spoiler 915 is rectangular. Furthermore, the width (circumferential DC width) of the upper surface of the convex portion of the first spoiler 915 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 protrusion surface 91BI. And the bottom surface of the concave portion is the gas path bottom surface 91AI sandwiched between the two gas path protrusion surfaces 91BI. The width of the gas path protrusion surface 91BI, which is the upper surface of the convex portion, is preferably less than 1 / 2 of the width of the second gas path bottom surface 91AI of the bottom surface of the concave portion. Moreover, the width of the gas path protrusion surface 91BI is more preferably less than 1 / 3 of the width of the gas path bottom surface 91AI.

[0101] Both the end-marking surface 92I of the first rear channel 83A and the end-marking surface 92I of the second rear channel 83B are alternating concave and convex surfaces in the circumferential direction DC, consisting of an end bottom surface 92AI and an end protruding surface 92BI located on the side of the end bottom surface 92AI away from the gas path surface 64P. That is, the end-marking surface 92I forms a second spoiler 925. Therefore, the second spoiler 925 is formed to protrude towards the interior of the rear channel 83I. Furthermore, multiple second spoilers 925 are formed separately in the circumferential direction DC. The multiple second spoilers 925 extend in an inclined direction, intersecting the circumferential direction DC. The second spoiler 925 is formed by the end bottom surface 92AI, the end protruding surface 92BI, and the end connecting surface 92CI. The end bottom surface 92AI and the end protruding surface 92BI are connected on the end connecting surface 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 gradually extend away from the gas path surface 64P of the inner shield body 61I in a direction inclined relative to the circumferential DC (first direction), moving towards the circumferential downstream side DCD (downstream side of the first direction) away from the rear inlet 83E in the circumferential DC (first direction). The direction in which the end bottom surface 92AI, the end protruding surface 92BI, and the end connecting surface 92CI extend is at an angle Θ of 45° to 75° relative to the circumferential DC (first direction), for example, at an angle of 60°. Therefore, the plurality of second spoilers 925 gradually extend away from the first corner 95 in a direction inclined relative to the circumferential DC, moving away from the rear inlet 83E in the circumferential DC.

[0102] The second spoiler 925 is a long and thin guide rail that traverses the end bottom surface 92AI and protrudes from the end bottom surface 92AI. The cross-section of the second spoiler 925 is rectangular. Furthermore, the width (circumferential DC width) of the upper surface of the convex portion of the second spoiler 925 is narrower than the width of the bottom surface of the concave portion. Specifically, the upper surface of the convex portion is the end protrusion surface 92BI. And the bottom surface of the concave portion is the end bottom surface 92AI sandwiched between the two end protrusion surfaces 92BI. The width of the upper surface of the convex portion, i.e., the end protrusion surface 92BI, is preferably less than 1 / 2 of the width of the bottom surface of the concave portion, i.e., the end bottom surface 92AI. Moreover, the width of the end protrusion surface 92BI is more preferably less than 1 / 3 of the width of the end bottom surface 92AI.

[0103] The circumferential DC position of the gas path side edge on the end protrusion surface 92BI is different from the circumferential DC position of the end side edge on the gas path protrusion surface 91BI. Therefore, the circumferential DC positions of the first spoiler 915 and the second spoiler 925 facing the first corner 95 are different from each other. The ends of the first spoiler 915 and the second spoiler 925 facing the first corner 95 are separated from each other in the circumferential DC. That is, the first spoiler 915 and the second spoiler 925 are not arranged in the same position in the circumferential DC. They are staggered in such a way that a protrusion of a second spoiler 925 is arranged between adjacent protrusions of two first spoilers 915 in the circumferential DC. Therefore, the first spoilers 915 and the second spoiler 925 are staggered in the circumferential DC so that a second spoiler 925 is arranged between two adjacent first spoilers 915 in the circumferential DC.

[0104] The surface shape of the gas path defining surface 91I of the rear second channel 83B is symmetrical to the surface shape of the gas path defining surface 91I of the rear first channel 83A, based on the virtual plane VP2 perpendicular to the circumferential direction DC (first direction) via the rear inlet 83E. Furthermore, the surface shape of the end defining surface 92I of the rear second channel 83B is symmetrical to the surface shape of the end defining surface 92I of the rear first channel 83A, based on the virtual plane VP2. Therefore, the rear first channel 83A and the rear second channel 83B are formed into a linearly symmetrical shape based on the virtual plane perpendicular to the circumferential direction DC (a virtual plane extending in the axial direction DA and radial direction DR) via the rear inlet 83E.

[0105] Next, the function and effect of the fixed blades described above will be explained.

[0106] like Figure 4 As shown, the cooling air ACL from the cooling air pipe 44 of the cooling device 40 flows into the blade air passage cover 57 of the outer cover 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.

[0107] Cooling air ACL flowing into the first blade passage 71 flows towards the inner side of the inner shroud 60I, i.e., the inner DRI, within the first blade passage 71. During its flow through the first blade passage 71, the cooling air ACL convectively cools the portion surrounding the first blade passage 71 within the blade body 51. A portion of the cooling air ACL flowing 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. Furthermore, another portion of the cooling air ACL flowing into the first blade passage 71 flows into multiple leading edge injection passages 75. The cooling air ACL flowing into the leading edge injection passages 75 convectively cools the portion surrounding 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 that is injected from near the leading edge of the blade body 51 to the outside of the blade body 51.

[0108] Cooling air ACL flowing into the fourth blade passage 74 flows towards the inner side of the inner shroud 60I, i.e., the inner DRI, within the fourth blade passage 74. During its flow through the fourth blade passage 74, the cooling air ACL provides convective cooling to the portion surrounding the fourth blade passage 74 within the blade body 51. A portion of the cooling air ACL flowing into the fourth blade passage 74 flows into the rear end passage 83O of the outer shroud body 61O via the rear inlet passage 86. Furthermore, another portion of the cooling air ACL flowing into the fourth blade passage 74 flows into multiple trailing edge injection passages 76. The cooling air ACL flowing into the trailing edge injection passages 76 provides convective cooling to the portion surrounding 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 from the trailing edge of the blade body 51 to the outside of the blade body 51.

[0109] like Figure 6As shown, a portion of the cooling air ACL flowing from the front inlet channel 85 of the outer shield body 61O into the front end channel 81 of the outer shield body 61O flows toward the first side DC1 within the front first channel 81A. During its flow within the front first channel 81A, the cooling air ACL provides convective cooling to the portion surrounding the front first channel 81A within the outer shield body 61O. This cooling air ACL flows from the front first channel 81A into the first transverse channel 82A and flows toward the downstream side DAD within the first transverse channel 82A. During its flow within the first transverse channel 82A, the cooling air ACL provides convective cooling to the portion surrounding the first transverse channel 82A within the outer shield body 61O. In this embodiment, the second gas path demarcation surface and the second end demarcation surface of the front first channel 81A, together with the second gas path demarcation surface and the second end demarcation surface of the first transverse channel 82A, form a first vertical baffle 917 and a second vertical baffle 927. Therefore, a turbulent boundary layer of cooling air ACL is formed along these surfaces, improving the heat transfer rate between the cooling air ACL and the portions forming these surfaces. Consequently, the cooling performance near the portions forming these surfaces is improved. The cooling air ACL flows from the first transverse channel 82A into the first outlet channel 87A.

[0110] Another portion of the cooling air ACL flowing from the front inlet channel 85 of the outer shield body 61O into the front end channel 81 of the outer shield body 61O flows toward the second side DC2 within the front end second channel 81B. During its flow within the front end second channel 81B, the cooling air ACL convectively cools the portion surrounding the front end second channel 81B within the outer shield body 61O. This cooling air ACL flows from the front end second channel 81B into the second transverse channel 82B and flows toward the downstream side DAD within the second transverse channel 82B. During its flow within the second transverse channel 82B, the cooling air ACL convectively cools the portion surrounding the second transverse channel 82B within the outer shield body 61O. In this embodiment, the second gas path demarcation surface and the second end demarcation surface of the front end second channel 81B, together with the second gas path demarcation surface and the second end demarcation surface of the second transverse channel 82B, form a first vertical baffle 917 and a second vertical baffle 927. Therefore, a turbulent boundary layer of cooling air ACL is formed along these surfaces, improving the heat transfer rate between the cooling air ACL and the portions forming these surfaces. Consequently, the cooling performance near the portions forming these surfaces is improved. The cooling air ACL flows from the second transverse channel 82B into the second outlet channel 87B.

[0111] A portion of the cooling air ACL flowing from the rear inlet channel 86 of the outer shield body 61O into the rear end channel 83O of the outer shield body 61O flows toward the first side DC1 within the rear first channel 83A. During its flow within the rear first channel 83A, the cooling air ACL provides convective cooling to the portion surrounding the rear first channel 83A in the outer shield body 61O. This cooling air ACL flows from the rear first channel 83A into the third transverse channel 84A and flows toward the upstream side DAU within the third transverse channel 84A. During its flow within the third transverse channel 84A, the cooling air ACL provides convective cooling to the portion surrounding the third transverse channel 84A in the outer shield body 61O. In this embodiment, the second gas path demarcation surface 91O and the second end demarcation surface 92O of the rear first channel 83A, together with the second gas path demarcation surface and the second end demarcation surface of the third transverse channel 84A, form a first vertical baffle 917 and a second vertical baffle 927. Therefore, a turbulent boundary layer of cooling air ACL is formed along these surfaces, improving the heat transfer rate between the cooling air ACL and the portions forming these surfaces. Consequently, the cooling performance near the portions forming these surfaces is improved. This cooling air ACL flows from the third transverse channel 84A into the third outlet channel 88A.

[0112] Another portion of the cooling air ACL flowing from the rear inlet channel 86 of the outer shield body 61O into the rear end channel 83O of the outer shield body 61O flows toward the second side DC2 within the rear second channel 83B. During its flow within the rear second channel 83B, the cooling air ACL convectively cools the portion surrounding the rear second channel 83B within the outer shield body 61O. This cooling air ACL flows from the rear second channel 83B into the fourth transverse channel 84B and flows toward the upstream side DAU within the fourth transverse channel 84B. During its flow within the fourth transverse channel 84B, the cooling air ACL convectively cools the portion surrounding the fourth transverse channel 84B within the outer shield body 61O. In this embodiment, the second gas path demarcation surface 91O and the second end demarcation surface 92O of the rear second channel 83B, together with the second gas path demarcation surface and the second end demarcation surface of the fourth transverse channel 84B, form a first vertical baffle 917 and a second vertical baffle 927. Therefore, a turbulent boundary layer of cooling air ACL is formed along these surfaces, improving the heat transfer rate between the cooling air ACL and the portions forming these surfaces. Consequently, the cooling performance near the portions forming these surfaces is improved. This cooling air ACL flows from the fourth transverse channel 84B into the fourth outlet channel 88B.

[0113] like Figure 8As shown, cooling air ACL flowing into the first outlet channel 87A, the second outlet channel 87B, the third outlet channel 88A, and the fourth outlet channel 88B flows into the first space 67A within the recess 66 of the outer casing 60O. The cooling air ACL in the first space 67A flows into the second space 67B through the multiple through holes 59A of the impact plate 59. At this time, the cooling air ACL flowing through the multiple through holes 59A of the impact plate 59 impacts and cools the opposite side 64A of the gas path of the outer casing body 61O. The cooling air ACL that has cooled the opposite side 64A of the gas path of the outer casing body 61O is guided, for example, into the intermediate housing 6 via the cooling air exhaust pipe 45.

[0114] like Figure 4 As shown, the cooling air ACL flowing into the second blade channel 72 flows towards the inner shroud 60I, i.e., the inner DRI, within the second blade channel 72. During its flow through the second blade channel 72, the cooling air ACL provides convective cooling to the portion surrounding the second blade channel 72 within the blade body 51. The cooling air ACL flowing into the second blade channel 72 then flows into the front end channel 81 of the inner shroud body 61I via the front inlet channel 85.

[0115] The cooling air ACL flowing into the third blade passage 73 flows towards the inner shroud 60I, i.e., the inner DRI, within the third blade passage 73. During its flow through the third blade passage 73, the cooling air ACL provides convective cooling to the portion surrounding the third blade passage 73 within the blade body 51. A portion of the cooling air ACL flowing into the third blade passage 73 flows into the rear end passage 83I of the inner shroud body 61I via the rear inlet passage 86.

[0116] like Figure 7As shown, a portion of the cooling air ACL flowing into the front end channel 81 of the inner shield body 61I flows toward the first side DC1 within the front end first channel 81A. During its flow within the front end first channel 81A, the cooling air ACL convectively cools the portion surrounding the front end first channel 81A within the inner shield body 61I. This cooling air ACL flows from the front end first channel 81A into the first transverse channel 82A and flows toward the downstream side DAD within the first transverse channel 82A. During its flow within the first transverse channel 82A, the cooling air ACL convectively cools the portion surrounding the first transverse channel 82A within the inner shield body 61I. In this embodiment, the second gas path demarcation surface and the second end demarcation surface of the front end first channel 81A, together with the second gas path demarcation surface and the second end demarcation surface of the first transverse channel 82A, form a first vertical baffle 917 and a second vertical baffle 927. Therefore, a turbulent boundary layer of cooling air ACL is formed along these surfaces, improving the heat transfer rate between the cooling air ACL and the portions forming these surfaces. Therefore, the cooling performance near the portions forming these surfaces is improved. The cooling air ACL flows from the first transverse channel 82A into the first outlet channel 87A.

[0117] Another portion of the cooling air ACL flowing into the front end channel 81 of the inner shield body 61I flows towards the second side DC2 within the front end second channel 81B. During its flow within the front end second channel 81B, the cooling air ACL convectively cools the portion surrounding the front end second channel 81B within the inner shield body 61I. This cooling air ACL flows from the front end second channel 81B into the second transverse channel 82B and flows towards the downstream side DAD within the second transverse channel 82B. During its flow within the second transverse channel 82B, the cooling air ACL convectively cools the portion surrounding the second transverse channel 82B within the inner shield body 61I. In this embodiment, the second gas path demarcation surface and the second end demarcation surface of the front end second channel 81B, together with the second gas path demarcation surface and the second end demarcation surface of the second transverse channel 82B, form a first vertical baffle 917 and a second vertical baffle 927. Therefore, a turbulent boundary layer of cooling air ACL is formed along these surfaces, improving the heat transfer rate between the cooling air ACL and the portions forming these surfaces. Therefore, the cooling performance near the portions forming these surfaces is improved. The cooling air ACL flows from the second transverse channel 82B into the second outlet channel 87B.

[0118] As mentioned above, the cooling air ACL flowing into the third blade passage 73 flows into the rear end passage 83I of the inner shroud body 61I via the rear inlet passage 86, and collides with the end marking surface 92I that defines the rear end passage 83I. The rear inlet passage 86 extends in the axial direction DA perpendicular to the circumferential direction DC (first direction) extending from the rear end passage 83I. Therefore, the cooling air ACL flowing into the rear end passage 83I of the inner shroud body 61I is approximately evenly distributed to the rear end first passage 83A of the first side DC1 and the rear end second passage 83B of the second side DC2, with reference to the rear inlet 83E.

[0119] Cooling air ACL flows from the rear inlet channel 86 of the inner shield body 61I into the rear first channel 83A and flows towards the first side DC1 within the rear first channel 83A. During its flow within the rear first channel 83A, the cooling air ACL provides convective cooling to the portion surrounding the rear first channel 83A within the inner shield body 61I. This cooling air ACL flows from the rear first channel 83A into the third transverse channel 84A and flows towards the upstream side DAU within the third transverse channel 84A. During its flow within the third transverse channel 84A, the cooling air ACL provides convective cooling to the portion surrounding the third transverse channel 84A within the inner shield body 61I. In this embodiment, a first baffle 915 and a second baffle 925 are formed on the gas path defining surface 91I and the end defining surface 92I of the rear first channel 83A. Furthermore, a first vertical baffle 917 and a second vertical baffle 927 are formed on the second gas path defining surface and the second end defining surface of the third transverse channel 84A. Therefore, a turbulent boundary layer of cooling air ACL is formed along these surfaces, improving the heat transfer rate between the cooling air ACL and the portions forming these surfaces. Consequently, the cooling performance near the portions forming these surfaces is improved. This cooling air ACL flows from the third transverse channel 84A into the third outlet channel 88A.

[0120] Cooling air ACL flows from the rear inlet channel 86 of the inner shield body 61I into the rear second channel 83B and flows towards the second side DC2 within the rear second channel 83B. During its flow within the rear second channel 83B, the cooling air ACL provides convective cooling to the portion surrounding the rear second channel 83B within the inner shield body 61I. This cooling air ACL then flows from the rear second channel 83B into the fourth transverse channel 84B and flows towards the upstream side DAU within the fourth transverse channel 84B. During its flow within the fourth transverse channel 84B, the cooling air ACL provides convective cooling to the portion surrounding the fourth transverse channel 84B within the inner shield body 61I. In this embodiment, the gas path defining surface 91I and the end defining surface 92I of the rear second channel 83B form a first baffle 915 and a second baffle 925. Furthermore, the second gas path defining surface and the second side defining surface of the fourth transverse channel 84B form a first vertical baffle 917 and a second vertical baffle 927. Therefore, a turbulent boundary layer of cooling air ACL is formed along these surfaces, improving the heat transfer rate between the cooling air ACL and the portions forming these surfaces. Consequently, the cooling performance near the portions forming these surfaces is improved. This cooling air ACL flows from the fourth transverse channel 84B into the fourth outlet channel 88B.

[0121] like Figure 8 As shown, cooling air ACL flowing into the first outlet channel 87A, the second outlet channel 87B, the third outlet channel 88A, and the fourth outlet channel 88B flows into the first space 67A within the recess 66 of the inner shroud 60I. The cooling air ACL in the first space 67A flows into the second space 67B through the multiple through holes 59A of the impact plate 59. At this time, the cooling air ACL flowing through the multiple through holes 59A of the impact plate 59 impacts and cools the gas path opposite surface 64A of the inner shroud body 61I. The cooling air ACL that has cooled the gas path opposite surface 64A of the inner shroud body 61I is guided, for example, into the intermediate housing 6 via the cooling air exhaust pipe 45.

[0122] Thus, a first spoiler 915 and a second spoiler 925 are formed on the defining surface of the rear end channel 83I extending in the circumferential direction DC, and a first vertical spoiler 917 and a second vertical spoiler 927 are formed on the second defining surface of the rear end channel 83O. When the protrusions and recesses formed by the first spoiler 915 and the second spoiler 925, or the first vertical spoiler 917 and the second vertical spoiler 927, extend in an intersecting direction that intersects with the first direction, the cooling air ACL flows in a direction perpendicular to that intersecting direction.

[0123] Furthermore, the first spoiler 915 and the second spoiler 925 have rectangular cross-sections, thereby generating turbulence in the flow of cooling air ACL as it crosses the rectangles. Similarly, the first vertical spoiler 917 and the second vertical spoiler 927 have rectangular cross-sections, thereby generating turbulence in the flow of cooling air ACL as it crosses the rectangles. Therefore, the cooling performance near the portions forming these surfaces is further improved.

[0124] In particular, in this embodiment, a plurality of first baffles 915 and a plurality of second baffles 925 extend in a direction inclined relative to the circumferential DC. Therefore, the cooling air ACL flowing along the rear end channel 83I in the circumferential DC changes direction as it passes through the first baffles 915 and the second baffles 925. Thus, any portion of the rear end channel 83I can be effectively cooled, and the gas path surface 64P and the rear end surface 62B can be effectively cooled.

[0125] In this embodiment, the concave and convex portions of the gas path defining surface 91I in the rear end channel 83I of the inner shield body 61I gradually extend in a direction inclined relative to the circumferential DC (first direction) as they move away from the rear end face 62B of the inner shield body 61I. That is, the plurality of first baffles 915 and the plurality of second baffles 925 gradually extend in a direction inclined relative to the circumferential DC as they move away from the first corner 95, as they move away from the rear inlet 83E in the circumferential DC. Therefore, the cooling air ACL flowing along the gas path defining surface 91I is directed towards the circumferential downstream side DCD (first direction), but also towards the side closer to the rear end face 62B (first end face), i.e., towards the first corner 95. Furthermore, in this embodiment, the recess and protrusion of the end-defining surface 92I in the rear end channel 83I of the inner shield body 61I gradually extend in a direction inclined relative to the circumferential DC (first direction) as they move away from the gas path surface 64P of the inner shield body 61I. Therefore, the cooling air ACL flowing along the end-defining surface 92I is directed toward the circumferential downstream side DCD (first direction), but also toward the side closer to the gas path surface 64P, i.e., toward the first corner 95.

[0126] As described above, in this embodiment, the cooling air ACL flowing along the gas path demarcation surface 91I and the cooling air ACL flowing along the end demarcation surface 92I both face the circumferential downstream side DCD (the downstream side in the first direction), but also face the side of the first corner 95. Therefore, the flow of the cooling air ACL near the first corner 95 is concentratedly disturbed, and the heat transfer rate between the cooling air ACL and the first corner 95 is improved. Therefore, in this embodiment, the cooling performance of the angle formed by the gas path surface 64P and the rear end surface 62B of the inner shield body 61I near the first corner 95 of the rear end channel 83I is further improved.

[0127] Furthermore, in this embodiment, the circumferential DC positions of the ends of the first spoiler 915 and the second spoiler 925 facing the first corner 95 are different from each other. Specifically, the position of the circumferential DC (first direction) near the edge of the first corner 95 in the end protrusion surface 92BI is different from the position of the circumferential DC (first direction) near the edge of the first corner 95 in the gas path protrusion surface 91BI. Therefore, in this embodiment, the cooling performance near the first corner 95 of the rear end channel 83I is further improved.

[0128] Therefore, in this embodiment, the gas path surface 64P and the first corner of the rear end surface 62B of the inner shield body 61I can be effectively cooled.

[0129] "Variations"

[0130] Next, the first baffle 9150 and the second baffle 9250 of the flow path forming plate according to the modified example of the present invention will be described. Furthermore, in the modified examples described below, structures common to the above embodiments are marked with the same symbols in the figures and their descriptions are omitted. In the modified examples, the tilting directions of the first baffle 9150 and the second baffle 9250 are different from those in the embodiments.

[0131] like Figure 13 and Figure 14 As shown, similarly to the embodiment, the flow path forming plate in the modified example comprises a platform 34P for rotating blade 34, an outer shield 36O and an inner shield 36I for fixing blade 36, a dividing ring 37, and an inner shield 60I and an outer shield 60O for fixing blade 50. In this modified example, taking the inner shield body 61I as an example, the first baffle 9150 and the second baffle 9250 will be described. Similar to the embodiment, the first baffle 9150 and the second baffle 9250 are formed in the rear end channel 83I of the inner shield body 61I.

[0132] Multiple first baffles 9150 are formed on the gas path defining surface 910I. Each first baffle 9150 is 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, as they approach the rear end face 62B (first end face) of the inner shield body 61I, they gradually extend in a direction inclined relative to the circumferential direction DC (first direction) towards the circumferential downstream side DCD (downstream side of the first direction) as they move away from the rear inlet 83E in the circumferential direction DC (first direction). The directions in which the gas path bottom surface 910AI, the gas path protruding surface 910BI, and the gas path connecting surface 910CI extend form an obtuse angle relative to the circumferential direction DC (first direction). Therefore, the plurality of first spoilers 9150 gradually extend in a direction inclined relative to the circumferential direction as they approach the first corner 95, away from the rear inlet 83E in the circumferential DC direction.

[0133] Multiple second spoilers 9250 are formed on the end defining surface 920I. Each second spoiler 9250 is 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 DC. However, the end bottom surface 920AI, the end protruding surface 920BI, and the end connecting surface 920CI all gradually extend in a direction inclined relative to the circumferential DC (first direction) toward the circumferential downstream side DCD (downstream side of the first direction) away from the rear inlet 83E, as they approach the gas path surface 64P of the inner shield body 61I. The directions in which the end bottom surface 920AI, the end protruding surface 920BI, and the end connecting surface 920CI extend form an obtuse angle relative to the circumferential DC (first direction). Therefore, the multiple second spoilers 9250 gradually extend in a direction inclined relative to the circumferential direction as they approach the first corner 95, away from the rear inlet 83E in the circumferential DC direction.

[0134] Even in the modified examples described above, the protrusions and recesses extend in the intersecting direction that intersects the first direction. Therefore, the cooling air ACL flowing along the gas path demarcation surface 910I moves towards the circumferential downstream side DCD (downstream side of the first direction), but moves away from the first corner 95 on the side away from the rear end face 62B (first end face). Furthermore, the cooling air ACL flowing along the end demarcation surface 920I moves towards the circumferential downstream side DCD (downstream side of the first direction), but moves away from the first corner 95 on the side away from the gas path surface 64P. Therefore, the cooling air ACL does not concentrate at the first corner 95 but flows uniformly in the rear end channel 83I. Thus, the cooling performance in the rear end channel 83I can be improved in a near-uniform state.

[0135] Other variations

[0136] The second gas path defining surfaces and second end defining surfaces of the front end channel 81, the first transverse channel 82A, the second transverse channel 82B, the rear end channel 83O, the third transverse channel 84A, and the fourth transverse channel 84B in the outer shield body 61O can be formed in the same way as the gas path defining surface 91I and the end defining surface 92I of the rear end channel 83I in the inner shield body 61I described above. That is, in the outer shield body 61O, the first baffle 915 and the second baffle 925 can be formed instead of the first vertical baffle 917 and the second vertical baffle 927, forming the front end channel 81, the first transverse channel 82A, the second transverse channel 82B, the rear end channel 83O, the third transverse channel 84A, and the fourth transverse channel 84B. Therefore, for example, when the rear end channel 83O is formed as an air channel, the rear end first channel 83A of the outer shield body 61O becomes the first air channel, and the rear end second channel 83B of the outer shield body 61O becomes the second air channel.

[0137] Furthermore, the second gas path defining surfaces and second end defining surfaces of the front end channel 81, the first horizontal channel 82A, the second horizontal channel 82B, the third horizontal channel 84A, and the fourth horizontal channel 84B in the inner shield body 61I can also be formed in the same way as the gas path defining surface 91I and the end defining surface 92I of the rear end channel 83I in the inner shield body 61I described above. That is, in the front end channel 81, the first horizontal channel 82A, the second horizontal channel 82B, the third horizontal channel 84A, and the fourth horizontal channel 84B in the inner shield body 61I, the first baffle 915 and the second baffle 925 can be formed, instead of the first vertical baffle 917 and the second vertical baffle 927. Therefore, for example, when the front end channel 81 is formed as an air channel, the front end first channel 81A of the inner shield body 61I becomes the first air channel, and the front end second channel 81B of the inner shield body 61I becomes the second air channel.

[0138] Furthermore, in the above embodiment, the flow path forming plate is the inner shroud 60I of the fixed blade 50. However, the platform 34P of the rotating blade 34 and the dividing ring 37 are also flow path forming plates. Therefore, when an air channel is formed on the platform 34P and the dividing ring 37 of the rotating blade 34, the gas path defining surface and the end defining surface in the air channel can be formed in the same way as the gas path defining surface 91I and the end defining surface 92I of the rear end channel 83I in the inner shroud body 61I described above.

[0139] Furthermore, the first corner 95 is preferably formed as an acute angle, but is not limited to being formed as an acute angle. The first corner 95 may be formed as a substantially right angle, as in the second corner 950 of this embodiment.

[0140] Furthermore, the second corner 950 is not limited to being formed as a right angle. The second corner 950 can be formed in any size as long as the angle is greater than that of the first corner 95.

[0141] Furthermore, in this embodiment and its variations, the cross-sections of the first spoiler 915, the second spoiler 925, the first spoiler 9150, the second spoiler 9250, the first vertical spoiler 917, and the second vertical spoiler 927 are rectangular, but are not limited to this shape. The first spoiler 915, the second spoiler 925, the first spoiler 9150, the second spoiler 9250, the first vertical spoiler 917, and the second vertical spoiler 927 can be of any shape as long as they protrude from the surface forming the flow path. Therefore, the cross-sections of the first spoiler 915, the second spoiler 925, the first spoiler 9150, the second spoiler 9250, the first vertical spoiler 917, and the second vertical spoiler 927 can be triangular (a shape where the upper surface of the protrusion does not exist).

[0142] Furthermore, the present invention is not limited to the embodiment and variations described above. Various additions, modifications, substitutions, partial deletions, etc., can be made without departing from the content specified in the technical solution and the conceptual idea and spirit of the present invention derived from its equivalents.

[0143] Postscript

[0144] The flow path forming plate in the above implementation methods and variations is as follows.

[0145] (1) The flow path forming plate in the first embodiment includes: a gas path surface 64P, which defines a portion of the combustion gas flow path 39 through which the combustion gas G flows; a first end face 62B, which is connected to the periphery of the gas path surface 64P; and an air passage 83I, which is defined by a plurality of defining surfaces and has an inlet 83E into which cooling air ACL can flow. The air passage 83I extends in the direction in which the gas path surface 64P and the first end face 62B extend, i.e., a first direction DC. The plurality of defining surfaces include: a gas path defining surface 91I, which extends in the first direction DC and is in a back-to-back relationship with the gas path surface 64P; and an end defining surface 92I, which extends in the first direction DC and is opposite to the first end face 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 has a plurality of first baffles 915 formed to protrude toward the interior of the air passage 83I and away from the first direction DC. The end-defining surface 92I has a plurality of second spoilers 925 formed to protrude toward the interior of the air passage 83I and away from the first direction DC. The plurality of first spoilers 915 and the plurality of second spoilers 925 extend in a direction inclined relative to the first direction DC.

[0146] As a result, the cooling air ACL flowing along the air passage 83I in the first direction DC changes direction after passing through the first baffle 915 and the second baffle 925. Therefore, any part in the air passage 83I can be effectively cooled, and the gas path 64P surface and the first end face 62B can be effectively cooled.

[0147] (2) In the flow path forming plate of the second method, in the flow path forming plate of (1), a plurality of first baffles 915 and a plurality of second baffles 925 gradually extend in a direction inclined relative to the first direction DC as they move away from the first corner 95 away from the inlet 83E in the first direction DC.

[0148] (3) In the flow path forming plate of the third method, the gas path side edge is connected to the edge of one side of the first end face 62B in the gas path defining surface 91I via the first corner 95, i.e., the end side edge. The gas path side edge is the edge of one side of the gas path surface 64P in the end defining surface 92I. The gas path defining surface 91I is a concave-convex surface that alternately repeats in the first direction DC between the gas path bottom surface 91AI and the gas path protrusion surface 91BI located on the side of the gas path bottom surface 91AI away from the gas path surface 64P. The end defining surface 92I is a concave-convex surface that alternately repeats in the first direction DC between the end bottom surface 92AI and the end protrusion surface 92BI located on the side of the end bottom surface 92AI away from the first end face 62B. The bottom surface 91AI and the protruding surface 91BI of the gas path gradually extend away from the first end face 62B in a direction inclined relative to the first direction DC, toward the downstream side DCD in the first direction DC, away from the inlet 83E. The bottom surface 92AI and the protruding surface 92BI gradually extend away from the gas path surface 64P in a direction inclined relative to the first direction DC, toward the downstream side DCD in the first direction.

[0149] In this embodiment, among the multiple demarcation surfaces of the air passage 83I, the gas path demarcation surface 91I and the end demarcation surface 92I are both alternating concave and convex surfaces that repeat in the first direction DC extending from the air passage 83I. In other words, the gas path demarcation surface 91I and the end demarcation surface 92I form a first baffle 915 and a second baffle 925. Therefore, a turbulent boundary layer of cooling air ACL is formed along these surfaces, and the heat transfer rate between the cooling air ACL and the portions forming these surfaces is improved. Therefore, in this embodiment, the cooling performance near the portions of these surfaces forming the flow path forming plate, namely the gas path surface 64P and the first end surface 62B of the flow path forming plate, is improved.

[0150] When a first spoiler 915 and a second spoiler 925 are formed on a defined surface extending in the first direction DC, and the protrusions and recesses of the first spoiler 915 and the second spoiler 925 extend in an intersecting direction relative to the first direction DC, the cooling air ACL flows in a direction perpendicular to the intersecting direction.

[0151] In this configuration, the concave and convex portions of the gas path defining surface 91I gradually extend in a direction inclined relative to the first direction DC, moving away from the first end face 62B and towards the downstream side DC of the first direction. Therefore, the cooling air ACL flowing along the gas path defining surface 91I moves towards the downstream side DC of the first direction, but also towards the side closer to the first end face 62B, i.e., towards the corner 95. Furthermore, in this configuration, the concave and convex portions of the end defining surface 92I gradually extend in a direction inclined relative to the first direction DC, moving away from the gas path surface 64P and towards the downstream side DC of the first direction. Therefore, the cooling air ACL flowing along the end defining surface 92I moves towards the downstream side DC of the first direction, but also towards the side closer to the gas path surface 64P, i.e., towards the first corner 95.

[0152] As described above, in this embodiment, the cooling air ACL flowing along the gas path demarcation surface 91I and the cooling air ACL flowing along the end demarcation surface 92I both face the downstream side DCD in the first direction, but also face the side of the first corner 95. Therefore, the flow of the cooling air ACL near the first corner 95 is concentratedly disturbed, and the heat transfer rate between the cooling air ACL and the first corner 95 is improved. Therefore, in this embodiment, the cooling performance near the first corner 95 of the air passage 83I, i.e., the angle formed by the gas path surface 64P of the flow path forming plate and the first end face 62B, is further improved.

[0153] (4) In any of the flow path forming plates in (1) to (3), the positions of the first direction DC of the first baffle 915 and the second baffle 925 facing the first corner 95 are different from each other.

[0154] Therefore, the cooling performance near the first corner 95 of the air passage 83I is further improved.

[0155] (5) In the flow path forming plate of the fifth method, the first baffle and the second baffle are staggered in the first direction so that a second baffle is disposed between two adjacent first baffles in the first direction.

[0156] (6) In any of the flow path forming plates in (1) to (5) of the sixth method, when viewed from the first direction DC, the first corner 95 of the air channel 83I is formed as an acute angle.

[0157] (7) In any of (1) to (6) of the flow path forming plate in the seventh embodiment, the plurality of defining surfaces have an inner defining surface 94 opposite to the end defining surface 92I. The inlet 83E is formed on the inner defining surface 94 so that the cooling air ACL flowing into the air passage 83I from the inlet 83E collides with the end defining surface 92I.

[0158] (8) In the flow path forming plate of the eighth embodiment (7), the air passage 83I has: a first air passage 83A extending from the inlet 83E toward a first side DC1 on both sides of the first direction DC; and a second air passage 83B extending from the inlet 83E toward a second side DC2 on the side opposite to the first side DC1 in the first direction DC. The first baffle 915 and the second baffle 925 are inclined in the first air passage 83A and the second air passage 83B, with reference to the first corner 95, in a direction different from the first direction DC.

[0159] (9) In the flow path forming plate of the ninth embodiment, 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 a concave-convex surface that alternately repeats in the first direction DC between the gas path bottom surface 91AI and the gas path protrusion surface 91BI located on the side of the gas path bottom surface 91AI away from the gas path surface 64P. The end defining surface 92I is a concave-convex surface that alternately repeats in the first direction DC between the end bottom surface 92AI and the end protrusion surface 92BI located on the side of the end bottom surface 92AI away from the first end surface 62B. 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 concave-convex surfaces that alternately repeat the gas path bottom surface 91AI and the gas path protruding surface 91BI 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 concave-convex surfaces that alternately repeat the end bottom surface 92AI and the end protruding surface 92BI in the first direction DC. The gas path bottom surface 91AI and the gas path protruding surface 91BI of the first air passage 83A and the gas path bottom surface 91AI and the gas path protruding surface 91BI of the second air passage 83B gradually extend in a direction inclined relative to the first direction DC as they move away from the first end face 62B, towards the downstream side DCD in the first direction. The end bottom surface 92AI and the end protruding surface 92BI of the first air passage 83A, and the end bottom surface 92AI and the end protruding surface 92BI of the second air passage 83B, gradually extend away from the gas path surface 64P in a direction inclined relative to the first direction DC, towards the downstream side DCD in the first direction. 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.

[0160] (10) In the flow path forming plate of the tenth method, the first air passage 83A and the second air passage 83B are formed in a linearly symmetrical shape with reference to the virtual plane perpendicular to the first direction DC, passing through the inlet 83E.

[0161] (11) In any one of the flow path forming plates in (7) to (10) of the eleventh embodiment, the flow path forming plate includes: an inlet channel 86 connected to the air channel 83I at the inlet 83E. The inlet channel 86 extends in a direction perpendicular to the first direction DC.

[0162] In this configuration, the inlet channel 86 extends in a direction perpendicular to the first direction DC of the air channel 83I. Therefore, the cooling air ACL flowing into the air channel 83I is distributed approximately evenly to the first side DC1 and the second side DC2 of the first direction, with reference to the inlet 83E.

[0163] (12) In any of the flow path forming plates in (1) to (11), the flow path forming plate in the twelfth embodiment further comprises: a separation channel 83O, formed independently of the air channel 83I, and having a second inlet 830E into which the cooling air ACL can flow. The separation channel 83O extends in the first direction DC and is defined by a plurality of second defining surfaces. The plurality of second defining surfaces have a second gas path defining surface 91O extending in the first direction DC and in a back-to-back relationship with 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 has a plurality of first vertical baffles 917 formed to protrude into the interior of the separation channel 83O and are formed separately in the first direction DC. The second end demarcation surface 92O has a plurality of second vertical spoilers 927 formed to protrude into the interior of the separation channel 83O and are spaced apart in the first direction DC. The plurality of first vertical spoilers 917 and the plurality of second vertical spoilers 927 extend perpendicularly to the first direction DC.

[0164] (13) In the flow path forming plate of the thirteenth method, when viewed from the first direction DC, the second corner 950 in the separation channel 83O is formed at an angle larger than the first corner 95.

[0165] The blades in the above embodiments and variations are as follows.

[0166] (14) The blade in the fourteenth embodiment includes any one of (1) to (13) flow path forming plates; and a blade body 51 having a blade-shaped cross-section and extending in a blade height direction having a directional component perpendicular to the cross-section. The flow path forming plate is disposed at one end of the blade body 51 on one side in the blade height direction and extends in a direction perpendicular to the blade height direction.

[0167] (15) In the blade of the fifteenth embodiment (14), the blade body 51 has a leading edge 52 and a trailing edge 53 separated from the leading edge 52. The first end face 62B is located on the downstream side DAD, which is further from the trailing edge 53 relative to the leading edge 52 than the blade body 51, and is the rear end face 62B facing the downstream side DAD.

[0168] The gas turbines in the above-described embodiments and variations can be understood as follows.

[0169] (16) The gas turbine in the sixteenth embodiment comprises: a compressor 10 that compresses air to generate compressed air ACOM; a combustor 20 that burns fuel F in the compressed air ACOM to generate combustion gas G; and a turbine 30 that can be driven by the combustion gas G. The turbine 30 has a flow path forming plate of any one of (1) to (13) that defines a portion of a combustion gas flow path 39 that defines the flow of the combustion gas G.

[0170] Industrial availability

[0171] According to one aspect of the present invention, the gas path surface and end face in the flow path forming plate can be effectively cooled.

[0172] Symbol Explanation

[0173] 1-Gas turbine rotor, 6-Intermediate casing, 7-Inner shroud, 8-Gas turbine casing, 10-Compressor, 11-Compressor rotor, 12-Rotor shaft, 13-Rotating blade row, 15-Fixed blade row, 18-Compressor casing, 20-Burner, 21-Combustion furnace, 22-Tail stack (or combustion chamber), 30-Turbine, 31-Turbine rotor, 32-Rotor shaft, 33-Rotating blade row, 34-Rotating blade, 34B-Blade body, 34P-Platform, 35-Fixed blade row, 36-Fixed blade, 36B-Blade body, 36I-Inner shroud, 36O-Outer shroud, 37-Divider ring, 38-Turbine casing, 39-Combustion gas flow path, 40-Cooling device, 41-Extraction pipe, 42- Cooler, 43-Boost compressor, 44-Cooling air pipe, 45-Cooling air exhaust pipe, 50-Fixed blade, 51-Blade body, 52-Leading edge, 53-Leading edge, 54-Negative pressure surface, 55-Positive pressure surface, 56-Heat insulation coating, 57-Blade air passage cover, 58-Sealing plate, 59-Impact plate, 59A-Through hole, 60I-Inner protective cover, 60O-Outer protective cover, 61I-Inner protective cover body, 61O-Outer protective cover body, 62F-Front end face (second end face), 62B-Rear end face (first end face), 620B-Rear end face (second end face), 63N-Back side end face, 63P-Ventral side end face, 64A-Opposite surface of gas path, 64AO-Opposite surface of outer gas path, 64P- Gas path surface, 65I, 65O - peripheral wall, 65F - front wall, 65B - rear wall, 65N - back side wall, 65P - ventral side wall, 66 - recess, 67 - cooling air space, 67A - first space, 67B - second space, 68F - front hook, 68R - rear hook, 69 - retainer, 69P - retainer channel, 71 - first blade channel, 72 - second blade channel, 73 - third blade channel, 74 - fourth blade channel, 75 - leading edge injection channel, 76 - trailing edge injection channel, 80 - internal channel, 81 - front end channel (or, simply referred to as separation channel), 81E - front inlet (or, simply referred to as second inlet), 81A - front end first channel, 81B - front end second channel, 82A - ... 82B - Second Horizontal Channel, 83I - Rear End Channel (or, simply called Air Channel), 83O - Rear End Channel (or, simply called Separation Channel), 83E - Rear Inlet (or, simply called Inlet), 830E - Rear Inlet (or, simply called Second Inlet), 83A - Rear End First Channel (or, simply called First Air Channel), 83B - Rear End Second Channel (or, simply called Second Air Channel), 84A - Third Horizontal Channel, 84B - Fourth Horizontal Channel, 85 - Front Inlet Channel, 86 - Rear Inlet Channel (or, simply called Inlet Channel), 87A - First Outlet Channel, 87B - Second Outlet Channel, 88A - Third Outlet Channel, 88B - Fourth Outlet Channel, 89 - Angle Injection Channel.91I, 910I - Gas path demarcation surface, 91O - Second gas path demarcation surface, 915, 9150 - First baffle, 917 - First vertical baffle, 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 demarcation surface, 92O - Second end demarcation surface, 925, 9250 - Second baffle, 927 - Second vertical baffle, 92AI, 920AI - End bottom surface, 92AO - Second end bottom surface, 92BI, 920BI - End protruding surface, 92BO - Second end protruding surface, 92CI, 920CI - End connection surface, 92CO - Second end connection surface, 93 - Gas path side demarcation opposite surface, 94 - Inner side demarcation surface, 95 - First corner, 950 - Second corner, A - External air, ACOM - Compressed air, ACL - Cooling air, G - Combustion gas, F - Fuel, CL - Arc, VP1, VP2 - Virtual plane, DA - Axial direction, DAU - Upstream side, DAD - Downstream side, DC - Circumferential (or, first direction), DC1 - First side (or, first side of the first direction), DC2 - Second side (or, second side of the first direction), DCD - Circumferential downstream side (or, downstream side of the first direction), DR - Radial, DRI - Inner side, DRO - Outer side.

Claims

1. A flow path forming plate, comprising: Gas path surface, which defines a portion of the combustion gas flow path; The first end face is connected to the periphery of the gas path surface; and The air passage is defined by multiple demarcation surfaces and has inlets through which cooling air can flow in. The air passage extends in a first direction along the gas path surface and the first end face. The plurality of demarcation surfaces include: a gas path demarcation surface extending in the first direction and positioned back-to-back with the gas path surface; and an end demarcation surface extending in the first direction and positioned back-to-back with the first end surface. The end demarcation surface and the gas path demarcation surface are connected via a first corner. The gas path delineation surface has a projection protruding toward the interior of the air channel, and a plurality of first baffles are formed separately in the first direction. The end-defined surface has a projection toward the interior of the air passage, and a plurality of second spoilers are formed separately in the first direction. The plurality of first spoilers and the plurality of second spoilers extend in a direction inclined relative to the first direction.

2. The flow path forming plate according to claim 1, wherein, The plurality of first spoilers and the plurality of second spoilers gradually extend in a direction inclined relative to the first direction away from the first corner, in a manner that moves away from the inlet in the first direction.

3. The flow path forming plate according to claim 2, wherein, The edge of one side of the gas path surface in the end-defining surface, i.e., the gas path side edge, is connected to the edge of one side of the first end face in the gas path defining surface, i.e., the end side edge, via the first corner. The gas path defining surface is a series of alternating concave and convex surfaces in the first direction, consisting of a gas path bottom surface and a gas path protrusion surface located on the side of the gas path away from the gas path surface relative to the gas path bottom surface. The end defining surface is an alternating concave-convex surface in the first direction of an end bottom surface and an end protrusion surface located on the side of the end bottom surface away from the first end surface. The bottom surface of the gas path and the protruding surface of the gas path gradually extend in a direction inclined relative to the first direction as they move away from the first end face, toward the downstream side of the first direction away from the inlet in the first direction. The bottom surface and the protruding surface of the end gradually extend in a direction inclined relative to the first direction, toward the downstream side of the first direction, as they move away from the gas path surface.

4. The flow path forming plate according to any one of claims 1 to 3, wherein, The first spoiler and the second spoiler facing the first corner are positioned differently in the first direction.

5. The flow path forming plate according to claim 4, wherein, The first spoiler and the second spoiler are staggered in the first direction, such that a second spoiler is disposed between two adjacent first spoilers in the first direction.

6. The flow path forming plate according to any one of claims 1 to 5, wherein, When viewed from the first direction, the first corner of the air passage forms an acute angle.

7. The flow path forming plate according to any one of claims 1 to 6, wherein, The plurality of demarcation surfaces have an inner demarcation surface opposite to the end demarcation surface. The inlet is formed on the inner defined surface so that the cooling air flowing into the air passage from the inlet collides with the end defined surface.

8. The flow path forming plate according to claim 7, wherein, The air passage has: a first air passage extending from the inlet toward a first side of two sides in the first direction; and a second air passage extending from the inlet toward a second side in the first direction opposite to the first side. The first and second spoilers are tilted in the first and second air channels, respectively, with the first corner as a reference, in an orientation different from the first direction.

9. The flow path forming plate according to claim 8, wherein, Both the first air passage and the second air passage are 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 is a series of alternating concave and convex surfaces in the first direction, consisting of a gas path bottom surface and a gas path protrusion surface located on the side of the gas path away from the gas path surface relative to the gas path bottom surface. The end defining surface is an alternating concave-convex surface in the first direction, consisting of an end bottom surface and an end protrusion surface located on the side of the end that is away from the first end surface relative to the end bottom surface. The gas path defining surface of the first air channel and the gas path defining surface of the second air channel are both concave and convex surfaces that alternately repeat the bottom surface and the protruding surface of the gas path in the first direction. The end defining surfaces of the first air channel and the second air channel are both concave and convex surfaces that alternately repeat the end bottom surface and the end protruding surface in the first direction. The bottom surface and protruding surface of the gas path in the first air channel, and the bottom surface and protruding surface of the gas path in the second air channel, gradually extend in a direction inclined relative to the first direction as they move away from the first end face, towards the downstream side of the first direction. The bottom surface and the protruding surface of the first air passage, and the bottom surface and the protruding surface of the second air passage, gradually extend in a direction inclined relative to the first direction, toward the downstream side of the first direction, as they move away from the gas path surface. The downstream side of the first direction in the first air passage is the first side. The downstream side of the second air passage in the first direction is the second side.

10. The flow path forming plate according to claim 8 or 9, wherein, The first air passage and the second air passage are formed in a linearly symmetrical shape with reference to a virtual plane passing through the inlet and perpendicular to the first direction.

11. The flow path forming plate according to any one of claims 7 to 10, comprising: An entrance passage, which connects to the air passage at the entrance. The entrance channel extends in a direction perpendicular to the first direction.

12. The flow path forming plate according to any one of claims 1 to 11, further comprising: A separation channel, formed independently of the air channel, has a second inlet into which the cooling air can flow. The separation channel extends in the first direction and is defined by a plurality of second delineated surfaces. The plurality of second delineation surfaces include: a second gas path delineation surface extending in the first direction and having a back-to-back relationship with the gas path surface; and a second end delineation surface extending in the first direction and connected to the second gas path delineation surface. The second end demarcation surface and the second gas path demarcation surface are connected via the second corner portion. The second gas path delineation surface has multiple first vertical baffles formed protruding toward the interior of the separation channel and spaced apart in the first direction. The second end demarcation surface has multiple second vertical baffles formed protruding toward the interior of the separation channel and spaced apart in the first direction. The plurality of first vertical spoilers and the plurality of second vertical spoilers extend perpendicularly to the first direction.

13. The flow path forming plate according to claim 12, wherein, When viewed from the first direction, the second corner is formed in the separation channel at an angle greater than that of the first corner.

14. A leaf having: The flow path forming plate according to any one of claims 1 to 13; and The blade body has a blade-shaped cross-section and extends in the blade height direction having a directional component perpendicular to the cross-section. The flow path forming plate is disposed at one end of the blade body on one side of the blade height direction and extends in a direction perpendicular to the blade height direction.

15. The blade according to claim 14, wherein, The blade body has a leading edge and a trailing edge separate from the leading edge. The first end face is formed relative to the leading edge at a position closer to the trailing edge than the blade body, and is a rear end face facing the trailing edge.

16. A gas turbine comprising: A compressor is a device that compresses air to produce compressed air. A burner that enables fuel to burn in the compressed air to generate combustion gases; and A turbine, capable of being driven by the combustion gases, The turbine has a flow path forming plate as described in any one of claims 1 to 13, which defines a portion of the combustion gas flow path.

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