Gas turbine guide vane, gas turbine equipped with such a guide vane and method for manufacturing a gas turbine guide vane

Abstract

Gas turbine guide vane, featuring: a leaf body (51) which forms a leaf profile and extends in a leaf height direction (Dh) to a first side (Dh1) and a second side (Dh2) which are opposite each other; a cover band (60°) which is provided on the first side (Dh1) of the leaf body (51); and a baffle plate (81), wherein the cover band (60o) has a recess (66) which has an opening on the first side (Dh1) and is recessed from the opening towards the second side (Dh2), wherein the impact plate (81) is provided in the opening of the recess (66) to form a cavity (64i) within the recess (66), wherein a plurality of through holes (88) are formed in the baffle plate (81), which penetrate the baffle plate (81) in the blade height direction (Dh) and through which an external space (64o), which is a space on the first side (Dh1), and the cavity (64i) communicate with each other with the baffle plate (81) as a reference, characterized by the fact that a communication hole (89) is formed in the impact plate (81) and the cover strip (60o), which penetrates the impact plate (81) and the cover strip (60o) in the blade height direction (Dh) and through which an interior space (49), which is a space on the second side (Dh2), and the exterior space (64o) communicate with each other using the cover strip (60o) as a reference, wherein a first area (91) in which an opening ratio, which is an opening area of ​​the plurality of through holes (88) per unit area, is low, and a second area (92) in which the opening ratio is higher than that in the first area (91) are present in an area of ​​the baffle plate (81), and wherein in the impact plate (81) the second area (92) is formed on a circumference of an opening of the communication hole (89) in the impact plate (81).

Description

[Technical field]

[0001] The present invention relates to a gas turbine guide vane, a gas turbine equipped with such a guide vane and a method for manufacturing a gas turbine guide vane. [Technical background]

[0002] A gas turbine has a rotor that rotates around an axis and a casing that covers the rotor. The rotor has a rotor shaft and a multitude of rotor blades attached to the rotor shaft. Additionally, a multitude of guide vanes are provided within the casing.

[0003] The guide vane has a blade body which extends in a radial direction with respect to the axis to form a blade profile, an inner deck band which is provided on a radial inside of the blade body, and an outer deck band which is provided on a radial outside of the blade body.

[0004] The guide vane of the gas turbine is exposed to hot combustion gas. Therefore, the guide vane is generally cooled by air or similar means.

[0005] For example, a guide vane described in the following patent reference 1 features a cooling system for a guide vane, which is applied to a gas turbine. Specifically, a flow path is formed in a blade body of the guide vane through which a coolant flows. Furthermore, the outer shroud has a recessed section that is cut out towards a radial inner side and opens towards a radial outer side. A baffle plate is provided to cover the recessed section, and a cavity is formed between the baffle plate and the recessed section. A through-hole, through which the coolant flows, is provided in a surface of the baffle plate. The outer shroud also has a tubular projection that extends from a bottom surface of the recessed section.A through-hole is formed in the tubular projection, penetrating it radially. A probe for testing is inserted into this through-hole.

[0006] In this guide vane, the tubular projection is designed as part of the outer cover strip to improve the sealing performance of the coolant flowing through the cavity. [List of oppositions][Patent literature]

[0007] [Patent literature 1] JP 2003-120207A. This document discloses features that fall under the preamble of claims 1 and 4. JP 2009-243429A is further prior art. [Brief description of the invention][Technical problem]

[0008] In the guide vane of the gas turbine, it is desirable to improve durability while simultaneously enabling testing with a probe or similar device.

[0009] One object of the present invention is to provide a turbine guide vane in which it is possible to improve durability and at the same time to enable testing with a test probe or the like, a gas turbine equipped with this, and a method for manufacturing a gas turbine guide vane. [Solution to the problem] The invention is defined by the independent claims.

[0010] A gas turbine guide vane of an aspect according to the invention for fulfilling the aforementioned problem comprises a blade body forming a blade profile, a shroud strip provided on a first side and a second side of the blade body in a blade height direction, and a baffle plate forming a cavity with the shroud strip. The shroud strip has a recess extending towards the second side, and the first side of the recess opens. The baffle plate is positioned in an opening of the recess to form the cavity within the recess. A plurality of through-holes are formed in the baffle plate, penetrating it in the blade height direction and through which an external space, which is a space on the first side, and the cavity communicate with each other, using the baffle plate as a reference.A communication hole is formed in the impact plate and the cover strip. This hole penetrates the impact plate and the cover strip in the direction of the sheet height, allowing communication between an interior space (located on the second side) and the exterior space (with the cover strip as a reference). A first area, where the openness ratio (the number of openings per unit area) is low, and a second area, where the openness ratio is high, are present on one surface of the impact plate. The second area is formed around the perimeter of the communication hole opening in the impact plate.

[0011] According to the present aspect, even if the communication hole is provided for the introduction of a test device such as a probe in the impact plate, it is possible to prevent a reduction in the cooling efficiency of the cover strip by providing the second area with a high opening ratio due to the through holes.

[0012] Furthermore, according to the present aspect, by providing the second area at the circumference of the opening in which the communication hole for the introduction of the test device is provided, it is possible to efficiently cool the circumference of the communication hole.

[0013] In the gas turbine guide vane, according to any of the above-mentioned aspects, the number of through holes contained in the second area per unit area can be higher than the number of multiple through holes contained in the first area per unit area.

[0014] According to the present aspect, the number of through holes per unit area in the second area is greater than in the first area, and thus the opening ratio in the second area is higher than the opening ratio in the first area, and it is possible to prevent a reduction in the cooling efficiency of the cover strip.

[0015] In the gas turbine guide vane, according to any of the above-mentioned aspects, the inner diameters of the plurality of through holes contained in the second area can be larger than the inner diameters of the plurality of through holes contained in the first area.

[0016] According to the present aspect, since the inner diameters of the through holes contained in the second area are designed to be larger than the inner diameters of the through holes contained in the first area, in a case where the number of through holes to be arranged is limited, it is possible to prevent a reduction in the cooling efficiency of the cover strip without increasing the number of through holes.

[0017] A gas turbine guide vane of a further aspect of the invention for fulfilling the aforementioned problem comprises a blade body forming a blade profile, a shroud provided on a first side and a second side of the blade body in a blade height direction, and a baffle plate forming a cavity with the shroud plate. The shroud plate has a recess extending towards the second side, and the first side of the recess opens. The baffle plate is positioned in an opening of the recess to form the cavity within the recess. A plurality of through-holes are formed in the baffle plate, penetrating it in the blade height direction and through which an external space, which is a space on the first side, and the cavity communicate with each other, using the baffle plate as a reference.A communication hole is formed in the impact plate and the cover strip. This hole penetrates the impact plate and the cover strip in the sheet height direction, allowing communication between an interior space (located on the second side) and the exterior space (using the cover strip as a reference). A first area, where the open area ratio (the number of openings of multiple through holes per unit area) is low, and a second area, where the open area ratio is higher than in the first area, are present on one surface of the impact plate. The inner diameters of the multiple through holes in the second area are larger than the inner diameters of the multiple through holes in the first area.The distance between the centers of two adjacent through holes in the first area is the same as the distance between the centers of two adjacent through holes in the second area.

[0018] According to the present aspect, since the distance between the centers of the openings of the two adjacent through holes in the first area is made the same as the distance between the centers of the openings of the two adjacent through holes in the second area, instructions for sending processing instructions are simplified and processability can be improved.

[0019] In the gas turbine guide vane, according to any of the above-mentioned aspects, the cover strip can have a tubular section extending from a bottom surface of the recess towards the first side, an end of the tubular section on the first side is connected to the baffle plate, and an inner space of the tubular section can form part of an inner space of the communication hole.

[0020] A gas turbine of one aspect according to the invention for fulfilling the above-mentioned problem comprises the gas turbine guide vanes according to each of the above-mentioned aspects, a rotor which is configured to rotate about an axis, a casing which covers an outer circumferential side of the rotor, and a combustion chamber which is configured to burn fuel to produce a combustion gas and to direct the combustion gas to the casing. The gas turbine guide vane is attached to the casing such that the blade height direction points radially with respect to the axis and the first side is a radial outer side with respect to the axis.

[0021] A gas turbine of a further aspect according to the invention for fulfilling the aforementioned problem comprises a plurality of gas turbine guide vanes, a rotor configured to rotate about an axis, a casing covering an outer circumferential side of the rotor, and a combustion chamber configured to burn fuel to produce a combustion gas and to direct the combustion gas to the casing. Each of the plurality of gas turbine guide vanes comprises a blade body forming a blade profile, a shroud provided on a first side and a second side of the blade body in a blade height direction, and a baffle plate forming a cavity with the shroud.The multiple gas turbine guide vanes are arranged circumferentially with respect to the axis, and each of the multiple gas turbine guide vanes is attached to the casing such that the blade height direction points radially with respect to the axis, and the first side is a radial outside with respect to the axis. Of any two adjacent gas turbine guide vanes circumferentially, a first gas turbine guide vane, which is a gas turbine guide vane, is the gas turbine guide vane according to each of the aspects mentioned above. Of the two gas turbine guide vanes, a second cover strip, which is the cover strip of a second gas turbine guide vane, has a second recess that is cut out radially inward with respect to the axis, and a radial outside of the second recess opens with respect to the axis.A second baffle plate, which is the baffle plate of the second gas turbine guide vane, is provided in an opening of the second recess to form a second cavity, which is the cavity within the second recess. A multitude of through-holes are formed in the second baffle plate, penetrating it in the blade height direction. These through-holes allow communication between an external space (a space on the first side) and the second cavity, with the second baffle plate serving as a reference. The communication hole of the first gas turbine guide vane is not formed in the second baffle plate or the second cover strip.

[0022] A gas turbine, in addition to another aspect of the invention for fulfilling the aforementioned problem, comprises a plurality of gas turbine guide vanes, a rotor configured to rotate about an axis, a casing covering an outer circumferential side of the rotor, and a combustion chamber configured to burn fuel to produce a combustion gas and to direct the combustion gas to the casing. Each plurality of gas turbine guide vanes comprises a blade body forming a blade profile, a shroud provided on a first side and a second side of the blade body in a blade height direction, and a baffle plate forming a cavity with the shroud. The plurality of gas turbine guide vanes are arranged circumferentially with respect to the axis. Each plurality of gas turbine guide vanes is attached to the casing within the casing such thatthat the blade height direction with respect to the axis points in a radial direction and the first side with respect to the axis is a radial outside. Of two adjacent gas turbine guide vanes in the circumferential direction, a first gas turbine guide vane, which is a gas turbine guide vane, in which a first cover strip, which is the cover strip, has a first recess which is recessed in the direction of the second side, and the first side of the first recess opens, a first baffle plate, which is the baffle plate, is provided in an opening of the first recess to form the cavity within the first recess, in the first baffle plate a plurality of through holes are formed which penetrate the first baffle plate in the blade height direction and through which an outside space, which is a space on the first side,and the cavity communicate with each other using the first baffle plate as a reference, a communication hole is formed in the first baffle plate and the first cover strip, which penetrates the first baffle plate and the first cover strip in the blade height direction and through which an interior space, which is a space on the second side, and the exterior space communicate with each other using the first cover strip as a reference, and a first area in which an opening ratio, which is an opening area of ​​the multitude of through holes per unit area, is low, and a second area in which the opening ratio is higher than that in the first area, are present in an area of ​​the first baffle plate. Of the two gas turbine guide vanes, a second gas turbine guide vane, which is the other gas turbine guide vane, is a gas turbine guide vane in which the second cover strip, which is the cover strip of the second gas turbine guide vane,in the circumferential direction adjacent to the first cover strip, a second cover strip has a second recess which is recessed in the direction of a radial inside with respect to the axis, a radial outside of the second recess opens with respect to the axis, and the second recess, which is adjacent to the first recess in the circumferential direction, is a second baffle plate, which is the baffle plate of the second gas turbine guide vane, provided in an opening of the second recess to form a second cavity, which is the cavity within the second recess, a plurality of through holes are formed in the second baffle plate, which penetrate the second baffle plate in the blade height direction and through which an outside space, which is a space on the first side, and the second cavity communicate with each other with the second baffle plate as a reference,The communication hole of the first gas turbine guide vane is not formed in the second baffle plate and the second cover strip, and there is no area in the second baffle plate corresponding to the second area in the first gas turbine guide vane.

[0023] In a method for manufacturing a gas turbine guide vane of an aspect according to the invention to fulfill the above-mentioned problem, a blade body construction step of constructing a blade body which has a blade body which forms a blade profile and a cover strip which is provided on a first side by the first side and a second side of the blade body in a blade height direction, a baffle plate construction step of constructing a baffle plate which forms a cavity with the cover strip, a manufacturing step of manufacturing the blade body constructed in the blade body construction step and the baffle plate constructed in the baffle plate construction step and an assembly step of mounting the baffle plate on the blade body which are manufactured in the manufacturing step are carried out.The cover strip constructed in the main blade body construction step has a recess that extends towards the second side, and the first side of the recess opens. The impact plate constructed in the baffle plate construction step is positioned in an opening of the recess to form the cavity within the recess.The impact plate construction step comprises a first arrangement determination step of determining the arrangement of a plurality of through holes which penetrate the impact plate in the sheet height direction and through which an external space, which is a space on the first side, and the cavity communicate with each other with the impact plate as a reference, and a second arrangement determination step of determining the arrangement of a communication hole which penetrates the impact plate and the cover strip in the sheet height direction and through which an internal space, which is a space on the second side, and the external space with the cover strip as a reference communicate with each other.In the first arrangement determination step, an arrangement of a plurality of first through holes is determined, which are the plurality of through holes contained in a first region in a surface of the impact plate; an arrangement of a plurality of second through holes is determined, which are the plurality of through holes contained in a second region in the surface of the impact plate other than the first region, such that the number of the plurality of second through holes per unit area is greater than the number of the plurality of first through holes per unit area; and a perimeter of an opening of the communication hole in the impact plate is defined as the second region.

[0024] Furthermore, in a method for manufacturing a gas turbine guide vane, a further aspect of the invention is used to fulfill the aforementioned problem: a blade body construction step of constructing a blade body, which has a blade body forming a blade profile and a cover strip provided on a first side and a second side of the blade body in a blade height direction; a baffle plate construction step of constructing a baffle plate forming a cavity with the cover strip; a manufacturing step of manufacturing the blade body constructed in the blade body construction step and the baffle plate constructed in the baffle plate construction step; and an assembly step of mounting the baffle plate to the blade body, which are manufactured in the manufacturing step.executed. The cover strip constructed in the main blade body construction step has a recess which is cut out towards the second side, and the first side of the recess opens. The baffle plate constructed in the impact plate construction step is provided in an opening of the recess to form the cavity within the recess. The impact plate construction step comprises a first arrangement determination step of determining the arrangement of a plurality of through holes which penetrate the baffle plate in the blade height direction and through which an exterior space, which is a space on the first side, and the cavity communicate with each other with the baffle plate as a reference; a second arrangement determination step of determining the arrangement of a communication hole which penetrates the baffle plate and the cover strip in the blade height direction and through which an interior space,which is a space on the second side, and the outer space communicate with each other using the cover strip as a reference, and an inner diameter determination step of determining the inner diameters of a plurality of first through holes, which are the plurality of through holes contained in a first area in a surface of the baffle plate, and of determining the inner diameters of a plurality of second through holes, which are the plurality of through holes contained in a second area in the surface of the baffle plate other than the first area, such that the inner diameters of the plurality of second through holes are larger than the inner diameters of the plurality of first through holes. In the first arrangement determination step, the second area is formed on a circumference of an opening of the communication hole in the baffle plate.

[0025] Furthermore, in a method for manufacturing a gas turbine guide vane, a further aspect according to the invention is incorporated to fulfill the aforementioned problem: a blade body construction step of constructing a blade body, which has a blade body forming a blade profile and a cover strip provided on a first side and a second side of the blade body in a blade height direction; a baffle plate construction step of constructing a baffle plate forming a cavity with the cover strip; a manufacturing step of manufacturing the blade body constructed in the blade body construction step and the baffle plate constructed in the baffle plate construction step; and an assembly step of mounting the baffle plate to the blade body, which are manufactured in the manufacturing step.executed. The cover strip constructed in the main blade body construction step has a recess which is cut out towards the second side, and the first side of the recess opens. The baffle plate constructed in the impact plate construction step is provided in an opening of the recess to form the cavity within the recess. The impact plate construction step comprises a first arrangement determination step of determining the arrangement of a plurality of through holes which penetrate the baffle plate in the blade height direction and through which an exterior space, which is a space on the first side, and the cavity communicate with each other with the baffle plate as a reference; a second arrangement determination step of determining the arrangement of a communication hole which penetrates the baffle plate and the cover strip in the blade height direction and through which an interior space,which is a space on the second side, and the outer space communicate with each other using the cover strip as a reference, and an inner diameter determination step of determining inner diameters of a plurality of first through holes, which are the plurality of through holes contained in a first area in a surface of the baffle plate, and of determining inner diameters of a plurality of second through holes, which are the plurality of through holes contained in a second area in the surface of the baffle plate except the first area, such thatthat the inner diameters of the plurality of second through holes are larger than the inner diameters of the plurality of first through holes. In the first arrangement determination step, the distance between the centers of openings of two adjacent through holes in the first region is made the same as the distance between the centers of openings of two adjacent through holes in the second region. [Advantageous effects of the invention]

[0026] According to the aspects of the present invention, it is possible to cool the turbine guide vane appropriately, and it is possible to improve the durability of the turbine guide vane. [Brief description of the drawings] Fig. Figure 1 is a schematic cross-sectional view of a gas turbine according to an embodiment of the present invention. Fig. Figure 2 is a perspective view of a gas turbine guide vane according to a first embodiment of the present invention. Fig. 3 is a cross-sectional view along line III-III in Fig. 2. Fig. 4 is a cross-sectional view along line IV-IV in Fig. 3. Fig. 5 is a view when viewed in one direction from arrow V in Fig. 2. Fig. Figure 6 is a view of part of a guide vane ring according to the first embodiment of the present invention when viewed from a radial outside. Fig. Figure 7 is a cross-sectional view of a gas turbine guide vane with a probe inserted therein in the first embodiment of the present invention. Fig. Figure 8 is a vertical cross-sectional view of a gas turbine guide vane with a plug attached to it in the first embodiment of the present invention. Fig. Figure 9 is a flowchart illustrating a method for manufacturing a gas turbine guide vane according to the first embodiment of the present invention. Fig. Figure 10 is a flowchart illustrating details of a baffle plate construction step according to the first embodiment of the present invention. Fig. Figure 11 is a view of a gas turbine guide vane according to a second embodiment of the present invention when viewed from the radial outside. Fig. Figure 12 is a flowchart illustrating details of a baffle plate construction step according to the second embodiment of the present invention. Fig. Figure 13 is a view of a gas turbine guide vane according to a third embodiment of the present invention when viewed from the radial outside. [Description of embodiments][Design of the gas turbine]

[0027] In the following, an embodiment of a gas turbine according to the present invention is described with reference to Fig. 1 described.

[0028] As in Fig. Figure 1 shows a gas turbine 10 of the present embodiment comprising a compressor 20 which compresses air A, a combustion chamber 30 which burns fuel F in the air compressed by the compressor 20 to produce a combustion gas G, and a turbine 40 which is driven by the combustion gas G.

[0029] The compressor 20 comprises a compressor rotor 21, which rotates about an axis Ar, a compressor casing 25, which covers the compressor rotor 21, and a plurality of compressor guide vane assemblies 26. The turbine 40 comprises a turbine rotor 41, which rotates about the axis Ar, a turbine casing 45, which covers the turbine rotor 41, and a plurality of turbine guide vane assemblies 46.

[0030] The compressor rotor 21 and the turbine rotor 41 are located on the same axis and are connected to form a gas turbine rotor 11. For example, a generator rotor GEN is connected to the gas turbine rotor 11. Furthermore, the compressor casing 25 and the turbine casing 45 are connected to form a gas turbine casing 15. Hereinafter, a direction in which the axis Ar extends is referred to as the axial direction Da, a circumferential direction around the axis Ar is simply referred to as the circumferential direction Dc, and a direction perpendicular to the axis Ar is referred to as the radial direction Dr. Furthermore, in the axial direction Da, with the turbine 40 as a reference, the side of the compressor 20 is referred to as the axially upstream side Dau, and the opposite side is referred to as the axially downstream side Dad.Furthermore, in the radial direction Dr, a side closer to the axis Ar is called the radial inside Dri, and a side opposite this is called the radial outside Dro.

[0031] The compressor rotor 21 comprises a compressor rotor shaft 22, which extends in the axial direction Da centered on the axis Ar, and a plurality of compressor rotor blade assemblies 23, which are attached to the compressor rotor shaft 22. The plurality of compressor rotor blade assemblies 23 are arranged in the axial direction Da. Each of the compressor rotor blade assemblies 23 is formed by a plurality of compressor rotor blades 23a, which are arranged in the circumferential direction Dc. The compressor guide vane assembly 26 is arranged on the axially downstream side Dad of each of the plurality of compressor rotor blade assemblies 23. Each of the compressor guide vane assemblies 26 is provided within the compressor casing 25. Each of the compressor guide vane assemblies 26 is formed by a plurality of compressor guide vanes 26a, which are arranged in the circumferential direction Dc.

[0032] The turbine rotor 41 comprises a turbine rotor shaft 42, which extends in the axial direction Da centered on the axis Ar, and a plurality of turbine rotor blade assemblies 43, which are attached to the turbine rotor shaft 42. The plurality of turbine rotor blade assemblies 43 are arranged in the axial direction Da. Each of the turbine rotor blade assemblies 43 is formed by a plurality of turbine rotor blades 43a, which are arranged in the circumferential direction Dc. The turbine guide vane assembly 46 is arranged on the axially upstream side Dau of each of the plurality of turbine rotor blade assemblies 43. Each of the turbine guide vane assemblies 46 is provided within the turbine casing 45. Each of the turbine guide vane assemblies 46 is formed by a plurality of turbine guide vanes 46a, which are arranged in the circumferential direction Dc. In the following, the turbine guide vane will simply be referred to as the guide vane.

[0033] A space between an outer circumferential side of the turbine rotor shaft 42 and an inner circumferential side of the turbine housing 45, in which the guide vanes 46a and the rotor blades 43a are arranged in the axial direction Da, forms a combustion gas flow path 49 through which the combustion gas G flows from the combustion chamber 30. This combustion gas flow path 49 forms a ring shape centered on the axis Ar and is long in the axial direction Da.

[0034] Compressor 20 compresses air A to produce compressed air. This compressed air flows into combustion chamber 30. Fuel F is supplied to combustion chamber 30. In combustion chamber 30, the fuel F is burned in the compressed air to produce combustion gas G at a high temperature and high pressure. This combustion gas G is directed from combustion chamber 30 to combustion gas flow path 49 in turbine 40. As it flows through combustion gas flow path 49, the combustion gas G rotates the turbine rotor 41 in the axially downstream direction. This rotation of the turbine rotor 41 also rotates the generator rotor GEN, which is connected to the gas turbine rotor 11.

[0035] The following describes various embodiments of the guide vane 46a of the gas turbine 10. [Design of the guide vane]

[0036] In the following, a first embodiment of a guide vane according to the present invention is described with reference to the Fig. 2 to 10 described.

[0037] As in Fig. Figure 2 shows a guide vane 50 of the present embodiment comprising a blade body 51, which forms a blade profile and extends in a blade height direction Dh, an inner cover band 60i, which is formed at one end on a second side Dh2 of a first side Dh1 and the second side Dh2 of the blade body 51 in the blade height direction Dh, and an outer cover band 60o, which is formed at one end of the blade body 51 on the first side Dh1. When the guide vane 50 is attached to the turbine housing 45, the radial direction Dr and the blade height direction Dh coincide, and thus the blade height direction Dh is hereinafter referred to as the radial direction Dr. When the guide vane 50 is attached to the turbine housing 45, the blade body 51 is arranged in the combustion gas flow path 49 through which the combustion gas G passes.The inner cover band 60i defines a position of the annular combustion gas flow path 49 on the radial inner side Dri. Furthermore, the outer cover band 60o defines a position of the annular combustion gas flow path 49 on the radial outer side Dro.

[0038] When the guide vane 50 is attached to the turbine casing 45, a section which is an end of the blade body 51 on the axially upstream side Dau forms a leading edge section 52, and a section which is an end of the blade body 51 on the axially downstream side Dad forms a trailing edge section 53. On a surface of the blade body 51, a convex side forms an intake side 54 of the blade (= an intake side), and a concave side forms a pressure side 55 of the blade (= a pressure side). For the simplicity of the following description, the circumferential direction Dc can be referred to as the lateral direction Dc.Furthermore, a side on which the pressure side 55 of the blade is located relative to the suction side 54 of the blade in the circumferential direction Dc is referred to as the circumferential pressure side Dcp of the blade, and a side on which the suction side 54 of the blade is located relative to the pressure side 55 of the blade in the circumferential direction Dc is referred to as the circumferential suction side Dcn of the blade. Furthermore, the axially upstream side Dau in the axial direction Da can be referred to as the front side, and the axially downstream side Dad in the axial direction Da can be referred to as the back side.

[0039] The following describes the structure of the outer deck tape 60°. As in the Fig. Figures 2 to 5 show that the outer cover band 60o has a plate-shaped outer cover band main body 61, which extends in the axial direction Da and the circumferential direction Dc, and a circumferential wall 65o, which projects along an outer circumferential edge of the outer cover band main body 61 from the outer cover band main body 61 in the direction of the radial outer side Dro.

[0040] The outer deck band main body 61A comprises a front end surface 62f, which is an end surface on the axially upstream side Dau in the axial direction, a rear end surface 62b, which is an end surface on the axially downstream side Dad, a pressure-side end surface 63p of the blade, which is an end surface of the circumferential pressure side Dcp of the blade, an intake-side end surface 63n of the blade, which is an end surface on the circumferential intake side Dcn of the blade, and a gas path surface 64p in the direction of the radial inner side Dri. The front end surface 62f and the rear end surface 62b are substantially parallel to each other. Furthermore, the pressure-side end surface 63p of the blade and the intake-side end surface 63n of the blade are substantially parallel to each other. Therefore, the outer deck band main body 61A has, as in Fig. Figure 5 shows a parallelogram shape when viewed in the radial direction Dr.

[0041] The circumferential wall 65o comprises a front circumferential wall 65f and a rear circumferential wall 65b, which face each other in the axial direction Da, and a pair of lateral circumferential walls 65p and 65n, which face each other in the circumferential direction Dc. Both the front circumferential wall 65f and the rear circumferential wall 65b project further than the pair of lateral circumferential walls 65p and 65n from the outer cover band main body 61 towards the radial outer side Dro to form a hook section. The front circumferential wall 65f and the rear circumferential wall 65b, which form the hook section, serve to attach the guide vane 50 to an inner circumferential side of the turbine casing 45 (see Fig. 1) In the outer cover strip 60o, a recess 66 is formed in the direction of the radial inner side Dri by the outer cover strip main body 61 and the circumferential wall 65o.

[0042] The guide vane 50 further comprises a deflector plate 81, which divides a space within the recess 66 of the outer deck strip 60o into an outer space 64o on the radial outside Dro and a cavity 64i on the radial inside Dri. As in Fig. Figure 5 shows that a plurality of through holes 88 are formed in the baffle plate 81, which penetrate the baffle plate 81 in the radial direction Dr. A portion of cooling air Ac, which is present on the radial outer surface Dro of the baffle plate 81, flows through the plurality of through holes 88 provided in the baffle plate 81 into the cavity 64i.

[0043] As in the Fig. 2 and Fig. Figure 3 shows a communication hole 89 formed in the outer cover strip 60o and the baffle plate 81. This communication hole 89 penetrates the outer cover strip 60o and the baffle plate 81 in the blade height direction Dh (Dr) and allows the outer space 64o on the radial outer side Dro of the baffle plate 81 and the aforementioned combustion gas flow path (an interior space) 49 to communicate with each other, using the outer cover strip 60o as a reference. The outer cover strip 60o has a tubular section 67 that extends from a bottom surface of the recess 66 towards the radial outer side Dro. One end of the tubular section 67 on the radial outer side Dro is connected to the baffle plate 81, and an interior space of the tubular section 67 forms part of an interior space of the communication hole 89.

[0044] Here, in one area of ​​the baffle plate 81, a region around the perimeter of the communication hole 89 is designated as the second region 92, and the other region is designated as the first region 91. The inner diameters of the plurality of through holes 88 in the first region 91 and the second region 92 are essentially uniform. Furthermore, the plurality of through holes 88 in the first region 91 and the second region 92 are regularly arranged. However, the distance between the centers of the openings of the plurality of through holes 88 in the second region 92 is narrower than the distance between the centers of the openings of the plurality of through holes 88 in the first region 91. Consequently, the opening density in the second region 92 is higher than the opening density in the first region 91. Opening density is the number of through holes 88 per unit area in the surface of the baffle plate 81.Therefore, the opening ratio in the second area 92 is higher than the opening ratio in the first area 91. An opening ratio is a ratio of the opening area through the plurality of through holes 88 to the total area of ​​each area.

[0045] As in Fig. Figure 3 shows a plurality of leaf air passages 75 formed in the leaf body 51, the outer cover band 60o, and the inner cover band 60i, extending in the radial direction Dr. Each leaf air passage 75 extends continuously from the outer cover band 60o to the inner cover band 60i by means of the leaf body 51. The plurality of leaf air passages 75 are arranged along a curvature line of the leaf body 51. Some of the adjacent leaf air passages 75 communicate with each other at a section on the radial outer side Dro or a section on the radial inner side Dri. The outer cover band 60o has a tubular leaf air passage 77, which extends from the base of the recess 66 towards the radial outer side Dro. An inner space of the tubular leaf air passage 77 forms part of an inner space of the leaf air passage 75.The tubular leaf air section 77 penetrates the baffle plate 81 and opens at one end on the radial outer side Dro. In the leading edge section 52 and the trailing edge section 53 of the leaf body 51, a plurality of leaf surface ejection passages 76 are formed, which penetrate the leaf body 51 from the leaf air passage 75 to the combustion gas flow path 49.

[0046] As in Fig. Figure 4 shows that a pressure-side passage 73p of the sheet is formed in the lateral circumferential wall 65p on the pressure side Dcp of the sheet (a pressure-side circumferential wall of the sheet). This passage extends along the pressure-side end surface 63p of the sheet with a component in the axial direction Da. Furthermore, an intake-side passage 73n of the sheet is formed in the lateral circumferential wall 65n on the suction side Dcn of the sheet (a suction-side circumferential wall of the sheet). This intake-side passage 73n of the sheet extends along the suction-side end surface 63n of the sheet with a component in the axial direction Da. Both the pressure-side passage 73p and the intake-side passage 73n of the sheet communicate with the cavity 64i at their upstream ends.Furthermore, the pressure-side passage 73p of the blade and the suction-side passage 73n of the blade are connected to each other by means of a connecting passage 72, which is formed parallel to one direction of the rear end surface 62b. Furthermore, a plurality of rear end passages 71 are formed in the outer deck band main body 61, which are located on the axially downstream side Dad with the cavity 64i as a reference, and upstream ends of the plurality of rear end passages 71 are connected to the connecting passage 72. The plurality of rear end passages 71 open at the rear end surface 62b of the outer deck band main body 61. The plurality of rear end passages 71 are arranged parallel to the circumferential direction (the lateral direction) Dc.

[0047] The combustion gas G flows between the outer deck band 60o and the inner deck band 60i of the guide vane 50. Therefore, the blade body 51, located between the outer deck band 60o and the inner deck band 60i, is heated by the combustion gas G. Consequently, cooling air Ac flows through the blade air passage 75 to cool the blade body 51. Furthermore, the cooling air Ac, which has flowed into the blade air passage 75, flows from the blade surface ejection passage 76 into the combustion gas flow path 49. Therefore, the leading edge section 52 and the trailing edge section 53 of the blade body 51 are cooled by the cooling air Ac as it flows out of the blade surface ejection passage 76. Furthermore, part of the cooling air Ac, which has flowed from the leaf surface ejection passage 76 into the combustion gas flow path 49, partially covers the surface of the leaf body 51 and also serves as layer air.

[0048] As in Fig. Figure 6 shows that, in a case where part of the turbine guide vane assembly 46 is viewed from the radial outer side Dro, a guide vane forming the turbine guide vane assembly 46 is a first guide vane 50 as described above, and a guide vane adjacent to the first guide vane assembly in the circumferential direction Dc is a second guide vane 50a. The second guide vane 50a has a second blade body 51a, a second inner deck band (not shown), and a second outer deck band 60oa. The second blade body 51a is essentially the same as the blade body 51 in the first guide vane 50. The second inner deck band is essentially the same as the inner deck band 60i in the first guide vane 50. The second outer deck band 60oa is essentially the same as the outer deck band 60o in the first guide vane 50.The second outer deck band 60oa has a second recess 66a, which is recessed towards the radial inner side Dri, and the radial outer side Dro of the second recess 66a opens. The second recess 66a corresponds to the recess 66 in the first guide vane 50. A second baffle plate 81a, corresponding to the baffle plate 81 of the first guide vane 50, is provided in an opening of the second recess 66a to form a second cavity 64ia within the second recess 66a. In the second baffle plate 81a, a plurality of second through-holes 88a are formed, which penetrate the second baffle plate 81a in the radial direction Dr and through which a second outer space 64oa, which is a space on the radial outer side Dro, and the second cavity 64ia communicate with each other with the second baffle plate 81a as a reference.In the second baffle plate 81a and the second outer deck band 60oa, the communication hole 89 in the first guide vane 50 is not formed. Furthermore, the second through holes 88a are regularly arranged and there is no area corresponding to the second area 92 in the first guide vane 50.

[0049] Next, a method for manufacturing the guide vane 50 is described with reference to the Fig. 9 and Fig. 10 described. As in Fig. Figure 9 shows that the production of the guide vane 50 involves a blade main body construction step (S1), a deflector plate construction step (S2), a manufacturing step (S3) and an assembly step (S4).

[0050] In the leaf body construction step (S1), a leaf body is constructed, which is formed by the leaf body 51, the outer cover band 60o and the inner cover band 60i. The outer cover band 60o constructed in the leaf body construction step (S1) has the recess 66, which is cut out in the direction of the second side Dh2, and the first side Dh1 of the recess 66 opens.

[0051] In the impact plate construction step (S2), the impact plate 81 is constructed, which forms the cavity 64i with the outer cover strip 60o. The impact plate constructed in the impact plate construction step (S2) is positioned in an opening of the recess 66 to form the cavity 64i within the recess 66. This includes, as in Fig. Figure 10 shows the impact plate construction step (S2) comprising a first arrangement determination step (S21) and a second arrangement determination step (S22). In the first arrangement determination step (S21), the arrangement of the plurality of through holes 88 is determined, which penetrate the impact plate 81 in the sheet height direction Dh and through which the external space 64o, which is a space on the first side Dh1, and the cavity 64i communicate with each other, using the impact plate 81 as a reference. At this point, the arrangement of the plurality of through holes 88 contained in the first region 91 in the surface of the impact plate 81 is determined. Furthermore, the arrangement of the plurality of through holes 88 in the second region 92 is determined such that the opening ratio of the second region 92 in the surface of the impact plate 81 is higher than the opening ratio of the first region 91 in the surface of the impact plate 81.Specifically, the arrangement of the multitude of through-holes 88 is determined such that the opening density in the second area 92 is higher than the opening density in the first area 91. In the second arrangement determination step (S22), the arrangement of the communication hole 89 is determined, which penetrates the baffle plate 81 and the outer cover strip 60° in the blade height direction Dh and through which the combustion gas flow path (the interior) 49, which is a space on the second side Dh2, and the exterior space 64° communicate with each other using the outer cover strip 60° as a reference.

[0052] In manufacturing step (S3), the main blade body constructed in the main blade body construction step S1 and the baffle plate 81 constructed in the baffle plate construction step S2 are manufactured. In this manufacturing step (S3), the main blade body is manufactured, for example, by casting. Furthermore, in this manufacturing step (S3), holes are made in a metal plate using a tool such as a drill to manufacture the baffle plate 81. In assembly step (S4), the baffle plate 81 is mounted onto the main blade body, which was manufactured in manufacturing step S3. Specifically, the baffle plate 81 is welded to the opening of the recess 66 of the outer cover strip 60°. The baffle plate 81 is also welded to the tubular section 67 and the tubular leaf air section 77 of the outer cover strip 60°.

[0053] Since the gas path area 64p of the outer deck strip 60o and a gas path area of ​​the inner deck strip 60i are heated by the combustion gas G, they must be cooled. A method for cooling the inner deck strip 60i is omitted here, but a method for cooling the outer deck strip 60o is described.

[0054] The cooling air Ac, which is present on the radial outer surface Dro of the outer cover strip 60o, flows through the plurality of through-holes 88 of the baffle plate 81 into the cavity 64i. The cooling air Ac expelled from the plurality of through-holes 88 of the baffle plate 81 impacts the bottom surface of the recess 66 of the outer cover strip 60o, and the bottom surface is cooled by impact. Consequently, an area corresponding to the bottom surface of the recess 66 is cooled in the gas path area 64p of the outer cover strip 60o.

[0055] A portion of the cooling air Ac, which has flowed into the cavity 64i of the outer cover strip 60o, flows into the pressure-side passage 73p of the blade, flows from the connecting passage 72 to the rear end passage 71, and flows out of the opening of the rear end surface 62b. In the gas path area 64p of the outer cover strip 60o, a region along the pressure-side end surface 63p of the blade is cooled by the cooling air Ac during the process of the cooling air Ac flowing through the pressure-side passage 73p of the blade. Another portion of the cooling air Ac, which has flowed into the cavity 64i of the outer cover strip 60o, flows into the intake-side passage 73n of the blade, flows from the connecting passage 72 to the rear end passage 71, and flows out of the opening of the rear end surface 62b.In the gas path area 64p of the outer cover strip 60o, an area along the intake-side end surface 63n of the blade is cooled during the process of the cooling air Ac flowing through the intake-side passage 73n of the blade.

[0056] In the gas path area 64p of the outer cover strip 60o, a region along the trailing end surface 62b of the blade is cooled by the cooling air Ac flowing through the trailing end passage 71. In the gas path area 64p of the outer cover strip 60o, a region along the intake end surface 63n of the blade and the trailing end surface 62b is cooled by the cooling air Ac flowing through the intake passage 73n of the blade. Furthermore, in the gas path area 64p of the outer cover strip 60o, a region along the pressure end surface 63p of the blade and the trailing end surface 62b is cooled by the cooling air Ac flowing through the pressure passage 73p of the blade.

[0057] Incidentally, as in the Fig. 2 and Fig. Figure 7 illustrates a case in which the baffle plate 81 is provided with the communication hole 89 through which a probe 100 is inserted to test the guide vane 50. The through-hole 88 is not formed in a region of the baffle plate 81 where the communication hole 89 is present. Therefore, it is difficult to cool the circumference of the communication hole 89. The communication hole 89 is used in the operation of the gas turbine 10 using a Fig. The plug 101 shown in section 8 is closed. On the other hand, at the time of a periodic inspection, the plug 101 is removed and, as shown in section 8, is closed. Fig. Figure 7 shows that the probe 100 is inserted from the radial outer side Dro of the guide vane 50 to check for damage to the guide vane 50.

[0058] The baffle plate 81 according to the outer cover strip 60o of the present embodiment has, as described above, the plurality of through holes 88 together with the communication holes 89, and the second area 92, whose opening density is higher than that of the first area 91, is present on the surface of the baffle plate 81. Therefore, in the present embodiment, the amount of cooling air Ac flowing into the cavity 64i is greater than in a case where the entire area of ​​the baffle plate 81 is designated as the first area 91, and the entire outer cover strip 60o can be adequately cooled. Furthermore, because the second area is arranged at the circumference of the communication hole 89, which is difficult to cool, the amount of cooling air Ac flowing into the area at the circumference of the communication hole 89 in the bottom surface of the recess 66 is increased, and the circumference of the communication hole 89 can be effectively cooled.Consequently, expansion of the circumference of communication hole 89 due to thermal stress can be prevented.

[0059] As described above, in the present embodiment, by arranging the second area 92 at the circumference of the communication hole 89, which is difficult to cool, it is possible to increase the cooling capacity. Therefore, according to the present embodiment, the durability of the guide vane 50 can be improved even in a case where the communication hole 89 is provided for the insertion of the test probe.

[0060] The baffle plate 81 of the present embodiment is provided with the second area 92 to increase the cooling capacity in the second area 92. Furthermore, in the present embodiment, it is possible to make the inner diameters of the plurality of through holes 88 the same size. Therefore, the type of drill used for drilling is limited to one, and it is not necessary to change the drill to form a plurality of through holes 88, and the drilling operation can be carried out simply. [Second embodiment of the guide vane]

[0061] In the following, a second embodiment of a guide vane according to the present invention is described with reference to Fig. 11 described.

[0062] In a guide vane 50x of the second embodiment, the size of a portion of the plurality of through holes 88 in the baffle plate 81 of the first embodiment is changed, and other features are the same as those of the guide vane 50 of the first embodiment. Therefore, a detailed description of the same design elements as those in the first embodiment is omitted in the present embodiment.

[0063] In a baffle plate 81x of the present embodiment, the inner diameters of a plurality of through holes 88x are formed in a second area 92x on the baffle plate 81x (a area defined by a dotted line in Fig. 11 marked area) are included, larger than the inner diameters of the plurality of through holes 88, which are included in a first area 91x.

[0064] Furthermore, the distance between the centers of the openings of the two adjacent through holes 88 in the first region 91x is equal to the distance between the centers of the openings of the two adjacent through holes 88x in the second region 92x. Therefore, the number of openings in the first region 91x is the same as the number of openings in the second region 92x. Thus, the opening ratio of the second region 92x is higher than the opening ratio of the first region 91x. The through hole 88x with a large inner diameter in the second region 92x is designed so as not to overlap the communication hole 89.

[0065] As in Fig. Figure 12 shows a method for manufacturing the guide vane 50x according to the second embodiment that differs from the method for manufacturing the guide vane 50 according to the first embodiment with respect to the baffle plate construction step. A baffle plate construction step (S2a) according to the second embodiment comprises a first arrangement determination step (S21a), a second arrangement determination step (S22a), and an inner diameter determination step (S23). In the first arrangement determination step (S21a), the arrangement of the plurality of through holes 88 and 88x is determined, which penetrate the baffle plate 81x in the blade height direction Dh and through which an outer space 64ox, which is a space on the first side Dh1, and a cavity 64ix communicate with each other with the baffle plate 81x as a reference, while the first area 91x and the second area 92x are not distinguished from each other.In the second arrangement determination step (S22a), the arrangement of the communication hole 89 is determined. This hole penetrates the baffle plate 81x and an outer cover strip 60ox in the blade height direction Dh, and through which the combustion gas flow path 49 (the interior), which is a space on the second side Dh2, and the outer space 64ox communicate with each other, using the outer cover strip 60ox as a reference. In the inner diameter determination step (S23), the inner diameters of the plurality of through holes 88 contained in the first region 91x in the surface of the baffle plate 81x are determined, as are the inner diameters of the plurality of through holes 88 contained in the second region 92x in the surface of the baffle plate 81x.At this point, the inner diameters of the multitude of through holes contained in a second area 92x are made 88x larger than the inner diameters of the multitude of through holes contained in the first area 91x.

[0066] After the impact plate construction step (S2a) is carried out, the guide vane 50x of the present embodiment is completed by carrying out the manufacturing step (S3) and the assembly step (S4) as in the first embodiment.

[0067] According to the embodiment of the present design, the opening ratio of the second area 92x is higher than the opening ratio of the first area 91x, and thus the amount of cooling air Ac flowing into the cavity 64ix is ​​greater than in a case where the entire area of ​​the baffle plate 81x is designated as the first area 91x, and the entire outer cover strip 60ox can be adequately cooled. Furthermore, because the second area 92x is arranged at the circumference of the communication hole 89, which is difficult to cool, the amount of cooling air Ac flowing into the area at the circumference of the communication hole 89 in a base surface of a recess 66x is increased, and the circumference of the communication hole 89 can be effectively cooled. Consequently, expansion of the circumference of the communication hole 89 due to thermal stress can be prevented.

[0068] Furthermore, since the distance between the centers of the multiple adjacent through holes 88x in the second area is 92x and the distance between the centers of the multiple adjacent through holes 88 in the first area is 91x designed to be the same, it is possible to increase the cooling capacity at the perimeter of the communication hole 89 without increasing the number of through holes 88 and 88x.

[0069] Furthermore, in a case where drilling is carried out using a machine such as a machining center, the arrangement of the plurality of through holes 88 in the first area 91x and the arrangement of the plurality of through holes 88x in the second area 92x are the same, and thus a tool is simply positioned and the determination of machining conditions can be simplified. [Third embodiment of the guide vane]

[0070] In the following, a third embodiment of a guide vane according to the present invention is described with reference to Fig. 13 described.

[0071] In a guide vane 50y of the present embodiment, the position of the second area 92 in the guide vane 50 of the first embodiment is changed.

[0072] As in Fig. Figure 13 shows a second area 92y (a section defined by a dotted line in the guide vane 50y of the present embodiment). Fig. 13 surrounded area) is provided at a corner formed by a print-side side 82 of the sheet and a front-side side 83 of the sheet of a baffle plate 81y. The aperture density in the second area 92y is, as in the first embodiment, higher than the aperture density in a first area 91y.

[0073] In the present embodiment, as in the first embodiment, the amount of cooling air Ac flowing into the cavity 64iy increases due to the provision of the second area 92y. Therefore, by providing the second area 92y on the baffle plate 81y, it is possible to cool the entire outer cover strip 60oy effectively. That is to say, the position of the second area is not limited to the circumference of the communication hole 89, and the second area can be arranged at any position on the baffle plate. However, as in the first and second embodiments, it is preferred to arrange the second area 92y at the circumference of the communication hole 89y.

[0074] As described in the second embodiment, the second region 92y can be configured such that the opening ratio is higher than that of the first region 91y, with an increased inner diameter of the through-hole 88. Furthermore, the second region 92y can be located at a position remote from the communication hole 89 and at the circumference of the communication hole 89. In this case, the entire outer cover strip 60oy can be suitably cooled, and the cooling capacity at the circumference of the communication hole 89 can be improved.

[0075] Although the embodiments of the present invention have been described in detail with reference to the drawings, the specific configuration of the implementation according to the present invention is not limited to these embodiments and also includes a modification of a design or the like. For example, the through-holes can be provided in two or more different sizes, and the shape of the opening of the through-holes is not limited to a circle and can, for example, be a square. [Commercial Applicability]

[0076] According to the aspects of the present invention, it is possible to cool the turbine guide vane appropriately, and it is possible to improve the durability of the turbine guide vane. [List of reference symbols] 10 Gas turbine 11 Gas turbine rotor 15 gas turbine casings 20 compressors 21 Compressor rotor 22 Compressor rotor shaft 23 compressor rotor blade ring 23a Compressor rotor blade 25 compressor housings 26 Compressor guide vane ring 26a Compressor guide vane 30 combustion chamber 40 Turbine 41 Turbine rotor 42 Turbine rotor shaft 43 Turbine rotor blade ring 43a Turbine rotor blade 45 turbine housings 46 Turbine guide vane ring 46a Turbine guide vane 49 Combustion gas flow path 50, 50x, 50y guide vane 50a Second guide vane 51 leaf bodies 51a Second leaf body 52 Leading edge section 53 Trailing edge section 54 Intake side of the leaf 55 Printable area of ​​the sheet 60i inner cover tape 60o, 60ox, 60oy outer cover tape 60oa Second outer deck tape 61 Outer deck band main body 62f Front end surface 62b Rear end surface 63n Intake-side end surface of the blade 63p Print-side end surface of the sheet 64i, 64ix, 64iy cavity 64ia Second cavity 64o, 64ox outdoor area 64oa Second outdoor room 64p gas path area 65° perimeter wall 65f Front perimeter wall 65b Rear perimeter wall 65n Intake-side circumferential wall of the leaf 65p Print-side perimeter wall of the sheet 66 recess 66a Second recess 67 Tubular section 71 Rear End 72 Connecting passage 73n Intake-side passage of the leaf 73p Print-side pass of the sheet 75 leaf air passage 76 leaf area ejection passes 77 Tubular leaf air section 81, 81x, 81y impact plate 81a Second impact plate 82 Printed side of the sheet 83 Front side of the sheet 88, 88x through hole 88a Second through hole 89 Communication gap 91, 91x, 91y First range 92, 92x, 92y Second range 100 probes 101 plugs A air AC cooling air Ar axis Fuel G Combustion gas GEN Generator DC circumferential direction (lateral direction) DCP perimeter print side of the sheet Dcn Circumferential suction side of the leaf Since the axial direction Dau Axial upstream side Dad Axial downstream side Dr. Radiale direction Dri Radiale inside Dro Radiale Outer Dh blade height direction Dh1 First page Dh2 Second Page

Claims

[1] Gas turbine guide vane, comprising: a leaf body (51) which forms a leaf profile and extends in a leaf height direction (Dh) to a first side (Dh1) and a second side (Dh2) which are opposite each other; a cover band (60°) which is provided on the first side (Dh1) of the leaf body (51); and a baffle plate (81), wherein the cover band (60o) has a recess (66) which has an opening on the first side (Dh1) and is recessed from the opening towards the second side (Dh2), wherein the impact plate (81) is provided in the opening of the recess (66) to form a cavity (64i) within the recess (66), wherein a plurality of through holes (88) are formed in the baffle plate (81), which penetrate the baffle plate (81) in the blade height direction (Dh) and through which an external space (64o), which is a space on the first side (Dh1), and the cavity (64i) communicate with each other with the baffle plate (81) as a reference, characterized by , that a communication hole (89) is formed in the impact plate (81) and the cover strip (60o), which penetrates the impact plate (81) and the cover strip (60o) in the blade height direction (Dh) and through which an interior space (49), which is a space on the second side (Dh2), and the exterior space (64o) communicate with each other using the cover strip (60o) as a reference, wherein a first area (91) in which an opening ratio, which is an opening area of ​​the plurality of through holes (88) per unit area, is low, and a second area (92) in which the opening ratio is higher than that in the first area (91) are present in an area of ​​the baffle plate (81), and wherein in the impact plate (81) the second area (92) is formed on a circumference of an opening of the communication hole (89) in the impact plate (81). [2] Gas turbine guide vane according to claim 1, wherein the number of multiple through holes (88) contained in the second area (92) per unit area is greater than the number of multiple through holes (88) contained in the first area (91) per unit area. [3] Gas turbine guide vane according to claim 1, wherein the inner diameter of the plurality of through holes (88) contained in the second region (92) is larger than the inner diameter of the plurality of through holes (88) contained in the first region (91). [4] Gas turbine guide vane, comprising: a leaf body (51) which forms a leaf profile and extends in a leaf height direction (Dh) to a first side (Dh1) and a second side (Dh2) which are opposite each other; a cover band (60°) which is provided on the first side (Dh1) of the leaf body (51); and a baffle plate (81), wherein the cover band (60o) has a recess (66) which has an opening on the first side (Dh1) and is recessed from the opening towards the second side (Dh2), wherein the impact plate (81) is provided in the opening of the recess (66) to form a cavity (64i) within the recess (66), wherein a plurality of through holes (88) are formed in the baffle plate (81), which penetrate the baffle plate (81) in the blade height direction (Dh) and through which an external space (64o), which is a space on the first side (Dh1), and the cavity (64i) communicate with each other with the baffle plate (81) as a reference, characterized by , that a communication hole (89) is formed in the impact plate (81) and the cover strip (60o), which penetrates the impact plate (81) and the cover strip (60o) in the blade height direction (Dh) and through which an interior space (49), which is a space on the second side (Dh2), and the exterior space (64o) communicate with each other using the cover strip (60o) as a reference, wherein a first area (91) in which an opening ratio, which is an opening area of ​​the plurality of through holes (88) per unit area, is low, and a second area (92) in which the opening ratio is higher than that in the first area (91) are present in an area of ​​the impact plate (81), wherein the inner diameters of the plurality of through holes (88) contained in the second region (92) are larger than the inner diameters of the plurality of through holes (88) contained in the first region (91), and wherein a distance between the centers of openings of two adjacent through holes (88) in the first area (91) is the same as a distance between the centers of openings of two adjacent through holes (88) in the second area (92). [5] Gas turbine guide vane according to any one of claims 1 to 4, wherein the cover band (60o) has a tubular section (67) which extends from a bottom surface of the recess (66) towards the first side (Dh1), wherein one end of the tubular section (67) is connected to the impact plate (81) on the first side (Dh1), and wherein an inner space of the tubular section (67) forms part of an inner space of the communication hole (89). [6] Gas turbine (10), comprising: the gas turbine guide vane according to one of claims 1 to 5; a rotor (11) which is arranged to rotate about an axis (Ar); a housing (15) which covers an outer circumferential side of the rotor (11); and a combustion chamber (30) which is configured to burn fuel (F) to produce a combustion gas (G) and to direct the combustion gas (G) to the housing (15), wherein the gas turbine guide vane is attached to the casing (15) such that the blade height direction (Dh) points in a radial direction (Dr) with respect to the axis (Ar) and the first side (Dh1) is a radial outside with respect to the axis (Ar). [7] Gas turbine (10), comprising: a large number of gas turbine guide vanes; a rotor (11) which is arranged to rotate about an axis (Ar); a housing (15) which covers an outer circumferential side of the rotor (11); and a combustion chamber (30) which is configured to burn fuel (F) to produce a combustion gas (G) and to direct the combustion gas (G) to the housing (15), wherein each of the multiple gas turbine guide vanes has a blade body (51) which forms a blade profile and extends in a blade height direction (Dh) to a first side (Dh1) and a second side (Dh2) which are opposite each other, a cover strip (60o) which is provided on the first side (Dh1) of the blade body (51), and a baffle plate (81), wherein the plurality of gas turbine guide vanes are arranged in a circumferential direction (Dc) with respect to the axis (Ar), wherein each of the plurality of gas turbine guide vanes within the casing (15) is attached to the casing (15) such that the blade height direction (Dh) points in a radial direction (Dr) with respect to the axis (Ar) and the first side (Dh1) is a radial outside with respect to the axis (Ar), wherein of two adjacent gas turbine guide vanes in the circumferential direction (Dc) a first gas turbine guide vane is the gas turbine guide vane according to one of claims 1 to 5, wherein of the two gas turbine guide vanes a second cover band (60oa), which is the cover band of a second gas turbine guide vane, which is the other gas turbine guide vane, has a second recess (66a) which has an opening on a radially outer side with respect to the axis (Ar) and with respect to the axis (Ar) in the direction of a radial inner side of the opening (66a), wherein a second baffle plate (81a), which is the baffle plate of the second gas turbine guide vane, is provided in the opening of the second recess (66a) to form a second cavity (64ia), which is the cavity within the second recess (66a), wherein a plurality of through holes (88a) are formed in the second impact plate (81a), which penetrate the second impact plate (81a) in the blade height direction (Dh) and through which an outer space (64o), which is a space on the first side (Dh1), and the second cavity (64ia) communicate with each other with the second impact plate (81a) as a reference, and wherein the communication hole (89) of the first gas turbine guide vane is not formed in the second baffle plate (81a) and the second cover band (60oa). [8] Gas turbine (10), comprising: a large number of gas turbine guide vanes; a rotor (11) which is arranged to rotate about an axis (Ar); a housing (15) which covers an outer circumferential side of the rotor (11); and a combustion chamber (30) which is configured to burn fuel (F) to produce a combustion gas (G) and to direct the combustion gas (G) to the housing (15), wherein each of the multiple gas turbine guide vanes has a blade body (51) which forms a blade profile and extends in a blade height direction (Dh) to a first side (Dh1) and a second side (Dh2) which are opposite each other, a cover strip (60o) which is provided on the first side (Dh1) of the blade body (51), and a baffle plate (81), wherein the plurality of gas turbine guide vanes are arranged in a circumferential direction (Dc) with respect to the axis (Ar), wherein each of the plurality of gas turbine guide vanes within the casing (15) is attached to the casing (15) such that the blade height direction (Dh) points in a radial direction with respect to the axis (Ar) and the first side (Dh1) is a radial outside with respect to the axis (Ar), wherein of two adjacent gas turbine guide vanes in the circumferential direction a first gas turbine guide vane is a gas turbine guide vane according to one of claims 1 to 5, in which a first cover band, which is the cover band (60o), has a first recess (66) which has an opening on the first side (Dh1) and is recessed from the opening towards the second side (Dh2), a first impact plate (81), which is the impact plate (81), is provided in the opening of the first recess (66) to form a cavity (64i) within the first recess (66), in the first impact plate (81) a plurality of through holes (88) are formed, which penetrate the first impact plate (81) in the blade height direction (Dh) and through which an external space (64o), which is a space on the first side (Dh1), and the cavity (64i) communicate with each other with the first impact plate (81) as a reference, a communication hole (89) is formed in the first impact plate (81) and the first cover strip (60o), which penetrates the first impact plate (81) and the first cover strip (60o) in the blade height direction (Dh) and through which an interior space (49), which is a space on the second side (Dh2), and the exterior space (64o) communicate with each other using the first cover strip (60o) as a reference, and a first area (91) in which an opening ratio, which is an opening area of ​​the plurality of through holes (88) per unit area, is low, and a second area (92) in which the opening ratio is higher than that in the first area (91), are present in an area of ​​the first impact plate (81), and wherein of the two gas turbine guide vanes, a second gas turbine guide vane, which is the other gas turbine guide vane, is a gas turbine guide vane in which a second cover band (60oa), which is the cover band of the second gas turbine guide vane, is adjacent in the circumferential direction to the first cover band (60o), the second cover strip (60oa) has a second recess (66a) which has an opening on a radially outer side with respect to the axis (Ar), is recessed from the opening with respect to the axis (Ar) in the direction of a radial inner side, and is adjacent to the first recess (66) in the circumferential direction, a second baffle plate (81a), which is the baffle plate of the second gas turbine guide vane, is provided in the opening of the second recess (66a) to form a second cavity (64ia), which is the cavity within the second recess (66a), in the second impact plate (81a) a plurality of through holes (88a) are formed, which penetrate the second impact plate in the blade height direction (Dh) and through which an outer space (64o), which is a space on the first side (Dh1), and the second cavity (64ia) communicate with each other with the second impact plate (81a) as a reference, in the second baffle plate (81a) and the second cover strip (60oa) the communication hole (89) of the first gas turbine guide vane is not formed, and in the second baffle plate (81a) there is no area corresponding to the second area (92) in the first gas turbine guide vane. [9] Method for manufacturing a gas turbine guide vane by performing: a leaf body construction step (S 1) of constructing a leaf body which comprises a leaf body (51) which forms a leaf profile and extends in a leaf height direction (Dh) to a first side (Dh1) and a second side (Dh2) which are opposite each other, and has a cover band (60o) which is provided on the first side (Dh1) of the leaf body (51); of a baffle plate construction step (S2) of constructing a baffle plate (81), a manufacturing step (S3) of manufacturing the main leaf body constructed in the main leaf construction step (S1) and the baffle plate constructed in the baffle plate construction step (S2) (81); and of an assembly step (S4) of mounting the baffle plate (81) to the main blade body, which are manufactured in the manufacturing step (S3), wherein the cover band (60o) constructed in the leaf main body construction step (S1) has a recess (66) which has an opening on the first side (Dh1) and is recessed from the opening towards the second side (Dh2), wherein the impact plate (81) constructed in the impact plate construction step (S1) is provided in the opening of the recess (66) to form a cavity (64i) within the recess (66), the impact plate construction step (S2) includes: a first arrangement determination step (S21) of determining the arrangement of a plurality of through holes (88) which penetrate the baffle plate (81) in the blade height direction (Dh) and through which an external space (64o), which is a space on the first side (Dh1), and the cavity (64i) communicate with each other with the baffle plate (81) as a reference, and a second arrangement determination step (S22) of determining the arrangement of a communication hole (89) which penetrates the impact plate (81) and the cover strip (60o) in the blade height direction (Dh) and through which an interior space (49), which is a space on the second side (Dh2), and the exterior space (64o) communicate with each other using the cover strip (60o) as a reference, and wherein in the first arrangement determination step (S21) an arrangement of a plurality of first through holes (88) is determined, which is the plurality of through holes (88) contained in a first region (91) in a surface of the baffle plate (81), an arrangement of a plurality of second through holes, which is the plurality of through holes contained in a second region (92) in the surface of the baffle plate (81) other than the first region (91), is determined such that the number of plurality of second through holes (88a) per unit area is greater than the number of plurality of first through holes (88) per unit area, and a perimeter of an opening of the communication hole (89) in the baffle plate (81) is defined as the second region (92). [10] Method for manufacturing a gas turbine guide vane by performing: a leaf body construction step (S1) of constructing a leaf body which comprises a leaf body (51) which forms a leaf profile and extends in a leaf height direction (Dh) to a first side (Dh1) and a second side (Dh2) which are opposite each other, and has a cover band (60o) which is provided on the first side (Dh1) of the leaf body (51); a baffle plate construction step (S2a) of constructing a baffle plate (81), a manufacturing step (S3) of manufacturing the main leaf body constructed in the main leaf construction step (S1) and the baffle plate constructed in the baffle plate construction step (S2a) (81); and of an assembly step (S4) of mounting the baffle plate (81) to the main blade body, which are manufactured in the manufacturing step (S3), wherein the cover band (60o) constructed in the leaf main body construction step (S1) has a recess (66) which has an opening on the first side (Dh1) and is recessed from the opening towards the second side (Dh2), wherein the impact plate (81) constructed in the impact plate construction step (S2a) is provided in an opening of the recess (66) to form a cavity (64i) within the recess (66), the impact plate construction step (S2a) includes: a first arrangement determination step (S21a) of determining the arrangement of a plurality of through holes (88) which penetrate the baffle plate (81) in the sheet height direction (Dh) and through which an external space (64o), which is a space on the first side (Dh1), and the cavity (64i) communicate with each other with the baffle plate (81) as a reference, a second arrangement determination step (S22a) of determining the arrangement of a communication hole (89) which penetrates the impact plate (81) and the cover strip (60o) in the blade height direction (Dh) and through which an interior space (49), which is a space on the second side (Dh2), and the exterior space (64o) communicate with each other using the cover strip (60o) as a reference, and an inner diameter determination step (S23) of determining the inner diameters of a plurality of first through holes (88), which is the plurality of through holes contained in a first region (91) in a surface of the baffle plate (81), and of determining the inner diameters of a plurality of second through holes, which is the plurality of through holes contained in a second region (92) in the surface of the baffle plate (81) other than the first region (91), such that the inner diameters of the plurality of second through holes are larger than the inner diameters of the plurality of first through holes (88), and wherein in the first arrangement determination step (S21a) the second area (92) is formed on a circumference of an opening of the communication hole (89) in the impact plate (81). [11] Method for manufacturing a gas turbine guide vane by carrying out: a leaf body construction step (S1) of constructing a leaf body which comprises a leaf body (51) which forms a leaf profile and extends in a leaf height direction (Dh) to a first side (Dh1) and a second side (Dh2) which are opposite each other, and has a cover band (60o) which is provided on the first side (Dh1) of the leaf body (51); a baffle plate construction step (S2a) of constructing a baffle plate (81), a manufacturing step (S3) of manufacturing the main leaf body constructed in the main leaf construction step (S1) and the baffle plate constructed in the baffle plate construction step (S2a) (81); and of an assembly step (S3) of mounting the baffle plate (81) to the main blade body, which are manufactured in the manufacturing step (S3), wherein the cover band (60o) constructed in the leaf main body construction step (S1) has a recess (66) which has an opening on the first side (Dh1) and is recessed from the opening towards the second side (Dh2), wherein the impact plate (81) constructed in the impact plate construction step (S1) is provided in the opening of the recess (66) to form a cavity (64i) within the recess (66), the impact plate construction step (S2a) includes: a first arrangement determination step (S21a) of determining the arrangement of a plurality of through holes (88) which penetrate the baffle plate (81) in the sheet height direction (Dh) and through which an external space (64o), which is a space on the first side (Dh1), and the cavity (64i) communicate with each other with the baffle plate (81) as a reference, a second arrangement determination step (S22a) of determining the arrangement of a communication hole (89) which penetrates the impact plate (81) and the cover strip (60o) in the blade height direction (Dh) and through which an interior space (49), which is a space on the second side (Dh2), and the exterior space (64o) communicate with each other using the cover strip (60o) as a reference, and an inner diameter determination step (S23) of determining the inner diameters of a plurality of first through holes (88), which is the plurality of through holes (88) contained in a first region (91) in a surface of the baffle plate (81), and of determining the inner diameters of a plurality of second through holes (88a), which is the plurality of through holes (88) contained in a second region (92) in the surface of the baffle plate (81) other than the first region (91), such that the inner diameters of the plurality of second through holes (88a) are larger than the inner diameters of the plurality of first through holes (88), and wherein in the first arrangement determination step (S21a) a distance between opening centers of two adjacent through holes (88) in the first area (91) is made the same as a distance between opening centers of two adjacent through holes in the second area (92).

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