Stator vane assembly of gas turbine, stationary member segment, and method for manufacturing stator vane assembly of gas turbine

Abstract

A stationary vane assembly of a gas turbine includes a stationary member formed in a ring shape, and a plurality of stationary vane segments each provided with a shroud and a blade body, disposed along a circumferential direction of the stationary member at a radially inner side of the stationary member, a cavity being provided between the shroud and the stationary member, and the shrouds being adjacent to each other in the circumferential direction of the stationary member, the stationary member being provided with a hole passing through from a radially outer side to a radially inner side of the stationary member, a central axis of the hole being arranged toward a circumferential end portion of the shroud.

Description

Technical Field

[0001] This disclosure relates to a stationary blade assembly for a gas turbine, a stationary component segment, and a method for manufacturing the stationary blade assembly for a gas turbine.

[0002] This application asserts priority based on Japan Patent Application No. 2021-048341 filed with the Japan Patent Office on March 23, 2021, the contents of which are incorporated herein by reference. Background Technology

[0003] Patent Document 1 discloses a cooling air passage that extends radially from the outer side to the inner side of the turbine housing. The cooling air passing through this cooling air passage is used to cool the stator blade stage located inside the turbine housing.

[0004] Prior art literature

[0005] Patent documents

[0006] Patent Document 1: International Publication No. 2016 / 152573 Summary of the Invention

[0007] The problem that the invention aims to solve

[0008] However, the stator stage disclosed in Patent Document 1 is composed of multiple stator blades arranged circumferentially, thus resulting in double-sided heating where the inner circumferential surfaces of the multiple stator blades (shrouds) and the adjacent end faces (circumferential end faces) of the multiple stator blades (shrouds) are simultaneously heated by the combustion gas flowing in the combustion gas flow path. The part heated on both sides thus experiences a higher temperature and requires more cooling compared to other parts.

[0009] However, in the structure disclosed in Patent Document 1, since the cooling air is not diffused primarily to the part heated on both sides, the part heated on both sides cannot be cooled effectively compared to other parts.

[0010] This disclosure was made in view of the aforementioned problems, and its object is to provide a gas turbine stator assembly, a stationary component segment, and a method for manufacturing the gas turbine stator assembly, which can effectively cool the part heated by the combustion gas on both sides.

[0011] Solution for solving the problem

[0012] To achieve the above objectives, the stator assembly of the gas turbine disclosed herein comprises:

[0013] A stationary component, which is formed in a ring shape; and

[0014] Multiple stationary blade segments, each equipped with a protective cover and a blade body, are arranged radially inside the stationary member along its circumference. A cavity is formed between the protective cover and the stationary member, and the protective covers are adjacent to each other in the circumferential direction of the stationary member.

[0015] The stationary member is provided with a hole extending from the radially outer side to the radially inner side of the stationary member, the central axis of the hole being arranged toward the circumferential end of the shield.

[0016] Furthermore, the stationary component segment of the gas turbine disclosed herein is divided into multiple segments circumferentially in the stationary component, which is formed as a ring, to constitute the stationary component, wherein,

[0017] Multiple holes extending radially from the outer side to the inner side of the stationary component are provided circumferentially on the stationary component segment.

[0018] The plurality of holes include a first hole and a second hole with different radial angles relative to the stationary member.

[0019] The second hole is inclined toward the radially inner side of the stationary member toward the segmental surface of the stationary member.

[0020] Furthermore, in the method for manufacturing the stator assembly of the gas turbine disclosed herein, the stator assembly of the gas turbine comprises:

[0021] A stationary component, which is formed in a ring shape; and

[0022] Multiple stationary blade segments, each equipped with a protective cover and a blade body, are arranged radially inside the stationary member along its circumference. A cavity is formed between the protective cover and the stationary member, and the protective covers are adjacent to each other in the circumferential direction of the stationary member.

[0023] in,

[0024] The stationary blade segment is configured such that the central axis of the hole provided in the stationary member, which extends from the radially outer side to the radially inner side of the stationary member, is oriented toward the circumferential end of the shroud.

[0025] Invention Effects

[0026] According to at least one embodiment of the present disclosure, the circumferential end of the shield can be effectively cooled. Attached Figure Description

[0027] Figure 1 This is a diagram of a gas turbine that briefly illustrates the stator assembly of a gas turbine employing an embodiment.

[0028] Figure 2This is a front view that briefly illustrates the stator assembly of a gas turbine according to an embodiment.

[0029] Figure 3 It is shown Figure 2 A three-dimensional diagram of the segment shown.

[0030] Figure 4 It is Figure 2 The enlarged longitudinal sectional view of the main part of the stationary blade assembly of the gas turbine shown.

[0031] Figure 5 It is Figure 4 The enlarged cross-sectional view of the main part of the stationary blade assembly of the gas turbine shown.

[0032] Figure 6 It is Figure 5 The diagram shows an enlarged unfolded view of the main parts of the gas turbine stator assembly.

[0033] Figure 7 It is Figure 5 The diagram shows an enlarged unfolded view of the main parts of the gas turbine stator assembly.

[0034] Figure 8 It is Figure 2 The enlarged cross-sectional view of the main part of the stationary blade assembly of the gas turbine shown.

[0035] Figure 9 This is an enlarged cross-sectional view of the main part of the stator assembly of the gas turbine in the embodiment.

[0036] Figure 10 This is a schematic diagram illustrating one example (Example 1) of a segment that can be used in the stator assembly of a gas turbine in an embodiment.

[0037] Figure 11 This is a schematic diagram illustrating one example (Example 2) of a segment that can be used in the stator assembly of a gas turbine in an embodiment.

[0038] Figure 12 This is a schematic diagram illustrating one example (Example 3) of a segment that can be used in the stator assembly of a gas turbine in an embodiment. Detailed Implementation

[0039] Hereinafter, the stator assembly, stationary component segment, and manufacturing method of the gas turbine stator assembly according to the embodiments will be described with reference to the accompanying drawings. The dimensions, materials, shapes, and relative arrangements of the constituent components described in the embodiments or shown in the drawings are not intended to limit the scope of the invention, but are merely illustrative examples.

[0040] like Figure 1 As shown, the gas turbine 10 of the gas turbine stator assembly 1 of the embodiment includes a compressor 13, multiple burners 15, and a turbine 17. The gas turbine 10 has a rotor shaft 12 that serves as the rotation axis and is arranged through the compressor 13 and the turbine 17. The multiple burners 15 are arranged around the rotor shaft 12. The compressor 13, the multiple burners 15, and the turbine 17 are arranged sequentially from upstream to downstream along the axis C of the rotor shaft 12 in the direction of air flow.

[0041] It should be noted that, in the following description, the axial direction of the rotor shaft 12 is referred to as the rotor axial direction, the circumferential direction centered on the axis of the rotor shaft 12 is referred to as the rotor circumferential direction, and the direction orthogonal to the axis of the rotor shaft 12 is referred to as the rotor radial direction.

[0042] The compressor 13 generates compressed air by rotating the rotor shaft 12. The compressor 13 has a compressor housing 131, multi-stage compressor stationary vanes 133, and multi-stage compressor moving vanes 135. The compressor housing 131 is cylindrical, with the rotor shaft 12 penetrating its interior, and has a cylindrical space (chamber) inside to accommodate the compressor stationary vanes 133 and compressor moving vanes 135. Furthermore, the compressor housing 131 has an intake 137 upstream in the airflow direction and an outlet 139 downstream in the airflow direction. The intake 137 allows air to be drawn into the compressor housing 131 from upstream in the airflow direction. The outlet 139 is formed in an annular shape centered on the rotor shaft 12, allowing the compressed air generated by the compressor 13 to be discharged.

[0043] The compressor stationary vanes 133 are fixed to the inner circumference of the compressor housing 131 in a state where they are neatly arranged along the rotor axial and circumferential directions with the axis of the rotor shaft 12 as the center. The compressor moving vanes 135 are fixed to the outer circumference of the rotor shaft 12 in a state where they alternate with the compressor stationary vanes 133 in the rotor axial direction and are neatly arranged along the rotor axial and circumferential directions with the axis of the rotor shaft 12 as the center.

[0044] Multiple burners 15 are each capable of generating combustion gases using compressed air generated by compressor 13. Fuel and compressed air can be supplied to the burners 15 together, and combustion gases are generated through fuel combustion. Multiple burners 15 are disposed inside a burner housing 151. The burner housing 151 is formed in a cylindrical shape, its interior is penetrated by a rotor shaft 12, and it has a cylindrical space (chamber) inside that accommodates multiple burners 15.

[0045] Multiple burners 15 are arranged circumferentially on the rotor. For example, the multiple burners 15 consist of 16 burners 15, arranged at equal intervals circumferentially on the rotor.

[0046] Multiple burners 15 each have a combustion chamber 153 and a tail tube 155. Fuel, along with compressed air generated by the compressor 13, is supplied to the combustion chamber 153 to generate combustion gases through fuel combustion. The combustion chamber 153 is cylindrical, with its axis aligned along the rotor axis. One end of the combustion chamber 153 is opened as an air inlet 157, which is positioned toward the outlet 1139 of the compressor 13. The tail tube 155 allows the combustion gases generated by the combustion chamber 153 to be discharged from the combustion chamber 153 to the turbine 17.

[0047] In the aforementioned burner 15, if high-temperature and high-pressure compressed air flows into the interior of the combustion cylinder 153 from the air supply port 157, the compressed air mixes with the fuel injected from the main combustion burner to generate a swirling flow of premixed gas.

[0048] The turbine 17 is capable of generating rotational power for the rotor shaft 12 using combustion gases. The turbine 17 includes a turbine housing 171, a multi-stage stator assembly 1, and multi-stage turbine moving blades 175. The turbine housing 171 is cylindrical in shape, penetrated by the rotor shaft 12, and has a cylindrical space (chamber) inside to accommodate the stator assembly 1 and the turbine moving blades 175. Furthermore, the turbine housing 171 has an exhaust chamber 177 downstream in the airflow direction. The exhaust chamber 177 has an exhaust diffuser 179, capable of discharging the exhaust gases generated from the rotational power of the rotor shaft 12. The multi-stage stator assembly 1 is fixed to the inner side of the turbine housing 171 in a state where it is neatly arranged along the rotor axial and circumferential directions with the axis of the rotor shaft 12 as the center. The multi-stage turbine moving blades 175 are fixed to the outer circumference of the rotor shaft in a state where they alternate with the stator assembly 1 in the rotor axial direction, and are neatly arranged along the rotor axial and circumferential directions with the axis of the rotor shaft 12 as the center.

[0049] The compressor-side end of the rotor shaft 12 is supported by bearing portion 121, and the exhaust chamber-side end is supported by bearing portion 123. Thus, the rotor shaft 12 can rotate freely about its axis. Furthermore, although not explicitly shown in the figures, a generator drive shaft is connected to the compressor-side end of the rotor shaft 12.

[0050] The gas turbine 10 draws in air from the inlet of the compressor 13, which is compressed by passing through multi-stage compressor stator vanes 133 and multi-stage compressor moving vanes 135. Thus, the air passing through the compressor 13 becomes high-temperature, high-pressure compressed air. This high-temperature, high-pressure compressed air, along with fuel, is supplied to the combustor 15, where fuel combustion generates high-temperature, high-pressure combustion gas. This combustion gas generates rotational power for the rotor shaft 12 by passing through the multi-stage stator vane assembly 1 and multi-stage turbine moving vanes 175 of the turbine 17, driving the rotor shaft 12 to rotate. Furthermore, this rotational power is applied to a generator connected to the rotor shaft 12 to generate electricity. On the other hand, the exhaust gas from driving the rotor shaft 12 to rotate is discharged into the atmosphere as exhaust gas through the exhaust diffuser in the exhaust chamber.

[0051] The stator assembly 1 of the gas turbine 10 in this embodiment is at least one of the multi-stage stator assemblies 1 described above. Here, the stator assembly 1 of the third stage from the upstream side in the direction of combustion gas flow will be used as an example for explanation, but the stator assembly 1 of the gas turbine 10 according to the present invention is not limited to the stator assembly 1 of the third stage from the upstream side in the direction of combustion gas flow.

[0052] like Figure 2 As shown, the stationary blade assembly 1 of the gas turbine 10 in this embodiment includes a stationary member 3 formed in an annular shape and a protective cover 6 respectively provided thereon (see reference). Figure 3 ) and multiple static leaf segments 5 of the leaf body 7.

[0053] The stationary member 3 is used to house multiple stator blade segments 5 (blade bodies 7) on the inner side of the turbine housing 171, and is therefore also called a blade ring. The stationary member 3 is formed, for example, in an annular shape and is located on the inner side of the turbine housing 171. The stationary member 3 is composed of at least two constituent members (stationary member segments) divided by a dividing surface 3ab extending radially along the stationary member 3, but it can also be further divided into multiple constituent members in the circumferential direction.

[0054] exist Figure 2 In the example shown, the dividing surface 3ab is disposed on a horizontal plane HZ extending radially along the stationary member 3, and the aforementioned at least two constituent members are composed of a lower half 3A and an upper half 3B divided by the dividing surface 3ab. Figure 2 In the example shown, flanges 3A1 and 3B1 are respectively provided on the opening edge (circumferential end of the lower half 3A) and the opening edge (circumferential end of the upper half 3B) of the upper half 3B. A through hole 3B12 is provided on the flange 3B1 of the upper half 3B, and a threaded hole 3A12 is provided on the flange 3A1 of the lower half 3A (see reference). Figure 5Furthermore, by inserting a bolt BT into the through hole 3B12 of the flange 3B1 in the upper half 3B and engaging it with the threaded hole 3A12 of the flange 3A1 in the lower half 3A, the upper half 3B and the lower half 3A are joined. It should be noted that in Figure 2 In the example shown, in order to balance the amount of deformation caused by thermal elongation with the flanges 3A1 and 3B1 respectively provided in the lower half 3A and the upper half 3B, dummy flanges 3A2 and 3B2 are respectively provided at the circumferential center of the lower half 3A and the circumferential center of the upper half 3B.

[0055] like Figure 2 As shown, multiple stationary blade segments 5 are arranged radially inside the stationary member 3 along the circumference of the stationary member 3, and a cavity CV is provided between the protective cover 6 and the stationary member 3 (see reference). Figure 4 In the circumferential direction of the stationary component 3, the protective covers 6 are adjacent to each other (see reference). Figure 5 ).

[0056] like Figure 3 As shown, each of the multiple stationary blade segments 5 has one blade body 7 provided in a shroud 6, but more than two blade bodies 7 may also be provided in a shroud 6. The shroud 6 is a partition wall provided along the radially inner side of the stationary member 3, and the blade body 7 is a stationary blade extending from the shroud 6 towards the radially inner side of the stationary member 3. An inner shroud 8 with a smaller diameter than the shroud 6 (hereinafter referred to as "outer shroud 6") is provided at the front end of the blade body 7 (the radially inner end of the stationary member 3). Thus, in each of the multiple stationary blade segments 5, a blade body 7 is provided between the outer shroud 6 and the inner shroud 8.

[0057] exist Figure 3 In the example shown, two adjacent stator blade segments 5A and 5B of the outer outer cover 6 of the stationary member 3 are fastened together as a group, and are arranged radially inward along the circumference of the stationary member 3. For the outer outer cover 6 of the two stator blade segments 5A and 5B that are fastened together as a group, the circumferential end 61 on the fastening surface side of the outer cover 6 is a fastening end 611, and the circumferential end 61 on the side opposite to the fastening surface of the outer cover 6 is a sealing end 612. Furthermore, a fastening part 63 is provided at the fastening end 611 of the outer cover 6, and a protruding end 64 is provided at the sealing end of the outer cover.

[0058] The fastening portions 63 of the outer outer covers 6, which are respectively provided on each other, are fastened to each other by fastening members 65, and the sealing ends 612 of the adjacent outer outer covers 6 are fastened to each other by sealing members 66 (see reference). Figure 6 and Figure 7They are interconnected. Fastening member 65 is, for example, made of bolts and nuts, but is not limited thereto. Sealing member 66 is, for example, a sealing plate, embedded in a groove provided in sealing end 612, but is not limited thereto.

[0059] In addition, the outer cover 6 of each stationary blade segment 5 has a front end mounting portion 621 and a rear end mounting portion 622. The front end mounting portion 621 is provided on the radially outer side of the front end of the outer cover 6 (on the side opposite to the radially inner side of the stationary member 3), and the rear end mounting portion 622 is provided on the radially outer side of the rear end.

[0060] like Figure 4 As shown, the front-end mounting portion 621 is a portion mounted on the front end of the stationary member 3, and is provided along the front end of the outer protective cover 6, isolating the annular cavity CV provided between the stationary member 3 and the outer protective cover 6 from the combustion gases. The rear-end mounting portion 622 is a portion mounted on the axial middle of the stationary member 3, and is provided along the rear end of the outer protective cover 6, isolating the cavity CV from the combustion gases.

[0061] The cavity CV is an annular shape extending circumferentially along the axis C of the rotor shaft of the gas turbine 10, and passes through the hole 31 of the stationary member 3 (described later) and is disposed between the stationary member 3 and the turbine housing 171 (see reference). Figure 1 The space X between the compressor 13 and the stationary member 3 is connected. Thus, the air drawn from the compressor 13 and supplied to the space X is supplied to the cavity CV through the hole 31 that passes through the stationary member 3.

[0062] Additionally, the outer shield 6 has an impact plate mounting step 68 (see reference). Figure 6 and Figure 7 The impact plate mounting step 68 is a step portion for mounting the impact plate 69 on the surface of the outer cover 6 facing the cavity CV (becoming the radially outer side of the outer cover 6), and is configured as a frame edge on the inner side of the front end mounting portion 621, the rear end mounting portion 622, the fastening portion 63 and the protruding end 64.

[0063] like Figures 5 to 7As shown, in the stator vane assembly 1 of the gas turbine 10 of this embodiment, a hole 31 is provided in the stationary member 3, extending from the radially outer side of the stationary member 3 to the inner side. The hole 31 is not limited to a hole with a straight central axis CN; it can also be a hole with a bent or curved central axis CN. The central axis CN of the hole 31 is arranged such that it extends from the radially outer side of the stationary member 3 toward the circumferential end 61 of the outer shield 6. As described above, when the central axis CN of the hole 31 is bent or curved, any hole that extends from the inner circumference of the stationary member 3 toward the circumferential end 61 of the outer shield 6 is included in the category of holes arranged from the radially outer side of the stationary member 3 toward the circumferential end 61 of the outer shield 6. Furthermore, the hole 31 is not limited to a hole with a circular cross-section; it can also be non-circular, such as elliptical, rectangular, or polygonal, and can also be an asymmetrical shape. Moreover, when the hole 31 has the above-described shape, the central axis CN passes through the centroid of that shape. Furthermore, the cross-sectional shape of the hole 31 does not need to be the same in the extension direction of the hole 31, and the cross-sectional shape can also be different in the extension direction of the hole 31. For example, the hole 31 can be a shape with a larger and gradually expanding cross-sectional shape at one end (inlet) compared to the other end (outlet) (conical shape), or it can be a shape with a smaller and gradually narrowing cross-sectional shape at one end compared to the other end (conical shape). The hole 31 is a hole for ejecting the air (compressed air) drawn from the compressor 13 toward the circumferential end 61 of the outer cover 6, and is also called an air hole or FH (Feed Hole) hole.

[0064] In the stator assembly 1 of the gas turbine 10 described above, the inner circumferential surface of the outer shroud 6 and the adjacent end faces of the multiple outer shrouds 6 in the circumferential direction are heated simultaneously. Therefore, the circumferential end 61 of the outer shroud 6 is heated on both sides, and its temperature rises more easily than other parts, and it requires more cooling than other parts. According to the stator assembly 1 of the gas turbine 10 of this embodiment, the central axis CN of the hole 31 is arranged from the radially outer side of the stationary member 3 toward the circumferential end 61 of the outer shroud 6. Therefore, if air (compressed air) drawn from the compressor 13 is supplied to the space X radially outer side of the stationary member 3, the air is ejected toward the circumferential end 61 of the outer shroud 6 through the hole 31 that extends from the radially outer side of the stationary member 3 to the radially inner side. As a result, the circumferential end 61 of the outer shroud 6, which is heated on both sides, is cooled preferentially compared to other parts, and the circumferential end 61 of the outer shroud 6, which is heated on both sides, can be cooled efficiently.

[0065] like Figures 5 to 7 As shown, in the stator blade assembly 1 of the gas turbine 10 in this embodiment, the circumferential end 61 of the outer shield 6 includes a fastening end 611, which is fastened to the outer shield 6 of other stator blade segments 5 adjacent to the outer shield 6 by fastening member 65.

[0066] In the stationary blade assembly 1 of the gas turbine 10 described above, as mentioned above, the circumferential end 61 of the outer shield 6 is heated on both sides and requires more cooling than other parts. However, the fastening end 611, which is fastened by the fastening member 65, especially requires cooling. In the stationary blade assembly 1 of the gas turbine 10 of this embodiment, the holes 31B, 31D, 31E, and 31F extending from the radially outer side of the stationary member 3 to the inner side face the fastening end 611. Therefore, if air (compressed air) drawn from the compressor 13 is supplied to the radially outer side of the stationary member 3, the air is ejected through the holes 31B, 31D, 31E, and 31F extending from the radially outer side of the stationary member 3 to the inner side toward the fastening end 611 of the outer shield 6. Thus, the fastening end 611 of the outer shield 6, which especially needs cooling, can be cooled efficiently.

[0067] like Figures 5 to 7 As shown, in the stator blade assembly 1 of the gas turbine 10 in this embodiment, the circumferential end 61 of the outer shield 6 includes a sealing end 612, which is connected to the outer shield 6 of other stator blade segments 5 adjacent to the outer shield 6 via a sealing member 66.

[0068] In the stationary blade assembly 1 of the gas turbine 10 described above, as mentioned above, the circumferential end 61 of the outer shield 6 is heated on both sides and requires more cooling than other parts, but the sealing end 612 connected by the sealing member 66 also needs cooling. In the stationary blade assembly 1 of the gas turbine 10 of this embodiment, the holes 31A, 31C, and 31G extending from the radially outer side of the stationary member 3 to the inner side face the sealing end 612. Therefore, if air (compressed air) drawn from the compressor 13 is supplied to the radially outer side of the stationary member 3, the air is ejected towards the sealing end 612 of the outer shield 6 through the holes 31A, 31C, and 31G extending from the radially outer side of the stationary member 3 to the inner side, thus efficiently cooling the sealing end 612 of the outer shield 6 that needs cooling.

[0069] like Figures 5 to 7 As shown, in the stator vane assembly 1 of the gas turbine 10 of this embodiment, the circumferential end 61 of the outer shield 6 includes a protruding end 64 that protrudes toward the stationary member side. The protruding end 64 is, for example, a fastening part 63 provided on the outer shield 6 or a protruding end provided on the sealing end 612, but is not limited thereto.

[0070] In the stationary blade assembly 1 of the gas turbine 10 described above, as mentioned above, the circumferential end 61 of the outer shield 6 is heated on both sides and requires more cooling than other parts. In addition, the protruding end 64 protruding towards the stationary member also needs cooling. In the stationary blade assembly 1 of the gas turbine 10 of this embodiment, the hole extending from the radially outer side to the inner side of the stationary member 3 faces the protruding end 64 of the outer shield 6. Therefore, if air (compressed air) drawn from the compressor 13 is supplied to the radially outer side of the stationary member 3, the air is ejected through the hole 31 extending from the radially outer side to the inner side of the stationary member 3 toward the protruding end 64 of the outer shield 6, thus efficiently cooling the protruding end 64 of the outer shield 6 that needs cooling.

[0071] like Figures 5 to 7 As shown, in the stationary blade assembly 1 of the gas turbine 10 of this embodiment, when viewed radially from the stationary member 3, the inner openings of the holes 31A to 31D, 31F, and 31G that extend from the radially outer side to the radially inner side of the stationary member 3 overlap with the circumferential end 61 of the outer shield 6 in the circumferential direction of the stationary member 3.

[0072] According to the gas turbine 10 stator assembly 1 of the above embodiment, the air drawn from the compressor 13 is ejected from the inner opening of the holes 31A to 31D, 31F, and 31G that penetrate the stationary member 3 from the radial outside to the inside toward the circumferential end 61 of the outer cover 6, so that the circumferential end 61 of the outer cover 6 heated by the combustion gas can be cooled efficiently.

[0073] like Figure 5 As shown, when the stationary member 3 is composed of a lower half 3A and an upper half 3B divided by a dividing surface 3ab located on a horizontal plane HZ extending radially along the stationary member 3, flanges 3A1 and 3B1 are respectively provided at the opening edge of the lower half 3A and the opening edge of the upper half 3B. A through hole 3B12 is provided in the flange 3B1 of the upper half 3B, and a threaded hole 3A12 is provided in the flange 3A1 of the lower half 3A. Furthermore, by inserting a bolt BT into the through hole 3B12 of the flange 3B1 of the upper half 3B and engaging with the threaded hole 3A12 of the flange 3A1 of the lower half 3A, the upper half 3B and the lower half 3A are joined. Therefore, it is not possible to provide a hole that extends radially from the outer side to the inner side of the stationary member 3 in the flange 3A1 of the lower half 3A and the flange 3B1 of the upper half 3B.

[0074] In the stationary blade assembly 1 of the gas turbine 10 of this embodiment, when the stationary member 3 is divided into multiple parts in the circumferential direction of the stationary member 3, the central axis CN of the hole 31E that passes through the hole 31 of the stationary member 3 and is adjacent to the dividing surface 3ab of the stationary member 3 is inclined toward the dividing surface 3ab of the stationary member 3 in the radial inward direction of the stationary member 3.

[0075] For example, such as Figure 5 As shown, when the stationary member 3 is composed of at least two constituent members divided by a dividing surface 3ab extending radially along the stationary member 3, the central axis CN of the hole 31E that passes through the stationary member 3 and is adjacent to the dividing surface 3ab in the circumferential direction of the stationary member 3 is inclined towards the dividing surface 3ab of the stationary member 3 in the radially inward direction.

[0076] According to the stationary blade assembly 1 of the gas turbine 10 described above, air drawn from the compressor 13 is ejected through a hole 31E adjacent to the dividing surface 3ab in the circumferential direction of the stationary member 3 and toward the circumferential end 61 of the outer shield 6 provided on the radially inner side of the dividing surface 3ab. Therefore, the circumferential end 61 of the outer shield 6 provided on the radially inner side of the dividing surface 3ab in the circumferential direction of the stationary member 3 can be effectively cooled.

[0077] exist Figures 5 to 7 In the example shown, such as Figure 7 As shown, the stator segment 5 is configured such that the sealing end 612 of the outer shield 6 is transversely cut across the dividing surface 3ab, as... Figure 5 As shown, the hole 31E of the fastening end 611 of the outer cover 6 closest to the dividing surface 3ab is provided in a manner that is radially inclined θ relative to the stationary member 3. Therefore, if air (compressed air) drawn from the compressor 13 is supplied to the radially outward side of the stationary member 3, the air is ejected through the hole 31E toward the fastening end 611 of the outer cover 6 closest to the dividing surface 3ab, thus enabling efficient cooling of the fastening end 611 of the outer cover 6 closest to the dividing surface 3ab.

[0078] like Figure 5 As shown, in the stator blade assembly 1 of the gas turbine 10 of this embodiment, the holes 31 penetrating the stationary member 3 are a plurality of holes 31 arranged along the circumference of the stationary member 3. The plurality of holes 31 include holes (first holes) 31A to 31D, 31F to 31G arranged radially along the central axis CN of the hole 31 along the stationary member 3, and holes (second holes) 31E in which the central axis CN of the hole 31 is inclined radially relative to the stationary member 3 and inclined radially inward toward the dividing surface 3ab of the stationary member 3 toward the stationary member 3.

[0079] According to the above-described embodiment, the air drawn from the compressor 13 in the stationary blade assembly 1 of the gas turbine 10 is ejected through the first holes 31A-31D, 31F-31G and the second hole 31E, thus effectively cooling the circumferential end 61 of the outer shroud 6 located on the radially inner side of the dividing surface 3ab of the stationary component segment (lower half 3A, upper half 3B).

[0080] like Figure 5 As shown, in this embodiment, the stationary component segments (lower half 3A, upper half 3B) of the gas turbine 10 are divided into multiple segments in the circumferential direction of the annular stationary component 3, thus constituting the stationary component 3. In each stationary component segment (lower half 3A, upper half 3B), multiple holes 31 extending from the radially outer side to the radially inner side of the stationary component segment (lower half 3A, upper half 3B) are provided along the circumferential direction of the stationary component segment (lower half 3A, upper half 3B). The plurality of holes 31 include holes (first holes) 31A to 31D, 31F to 31G arranged radially along the central axis CN of the hole 31 along the stationary member segment (lower half 3A, upper half 3B), and holes (second holes) 31E inclined radially relative to the stationary member segment (lower half 3A, upper half 3B) and inclined radially inward toward the dividing surface 3ab of the stationary member segment (lower half 3A, upper half 3B).

[0081] According to the above-described embodiment, the air drawn from the compressor 13 in the stationary component segment (lower half 3A, upper half 3B) is ejected through the first holes 31A-31D, 31F-31G and the second hole 31E, thus effectively cooling the circumferential end 61 of the outer cover 6 located on the radially inner side of the dividing surface 3ab of the stationary component segment (lower half 3A, upper half 3B).

[0082] like Figure 2 As shown, in the stator blade assembly 1 of the gas turbine 10 of this embodiment, the stationary member 3 has multiple stationary member segments (lower half 3A, upper half 3B) that are divided into multiple segments in the circumferential direction. The stationary member segments (lower half 3A, upper half 3B) have dummy flanges 3A2 and 3B2 that protrude radially outward from the outer circumferential surface (outer circumferential surface). It should be noted that the stationary member 3 may be a member in which each of the stationary member segments (lower half 3A, upper half 3B) has a dummy flange 3A2 and 3B2, but it may also be a member in which at least one stationary member segment (upper half 3B (lower half 3A)) has a dummy flange (3A3B).

[0083] like Figure 8 As shown, the central axis CN of the holes 31P and 31Q set in the dummy flange 3B2 (3A2) is inclined radially relative to the stationary member 3.

[0084] According to the gas turbine stator assembly 1 of the present embodiment described above, air drawn from the compressor 13 is ejected through holes 31P and 31Q that are radially inclined relative to the stationary member 3 and provided on the dummy flange 3B2 (3A2). Therefore, the circumferential end 61 of the outer shroud 6 provided on the radially inner side of the dummy flange 3B2 (3A2) can be effectively cooled.

[0085] exist Figure 8 In the example shown, a hole 31P provided in the dummy flange 3B2 (3A2) of the stationary member 3 faces the fastening end 611 of the outer cover 6 and is arranged parallel to a vertical plane (a plane orthogonal to the horizontal plane HZ) extending radially along the stationary member 3. Therefore, if air (compressed air) drawn from the compressor 13 is supplied to the space X radially outward of the stationary member 3, the air is ejected through a hole 31P toward the fastening end 611 of the outer cover 6, which is located radially inward of the dummy flange 3B2 (3A2), thus effectively cooling the fastening end 611 of the outer cover 6, which is located inside the dummy flange 3B2 (3A2). Furthermore, in Figure 8 In the example shown, another hole 31Q provided on the dummy flange 3B2 (3A2) of the stationary member 3 faces the sealing end 612 of the outer cover 6 and is provided parallel to the vertical plane (the plane orthogonal to the horizontal plane HZ) extending radially along the stationary member 3. Therefore, if air (compressed air) drawn from the compressor 13 is supplied to the radially outer side of the stationary member 3, the air is ejected through the other hole 31Q toward the sealing end 612 of the outer cover 6 provided on the radially inner side of the dummy flange 3B2 (3A2), thus effectively cooling the sealing end 612 of the outer cover 6 provided on the inner side of the dummy flange 3B2 (3A2).

[0086] like Figure 9 As shown, in a stationary member 3 with a hole 31 provided at a position offset from the dummy flange 3B2 (3A2), the central axis CN of the holes 31P and 31r adjacent to the dummy flange 3B2 (3A2) is inclined toward the dummy flange 3B2 (3A2) side on the radial inner side of the stationary member 3.

[0087] According to this structure, the air drawn from the compressor 13 is ejected through the holes 31P and 31r adjacent to the dummy flange 3B2 (3A2), and the central axis CN of the holes 31P and 31r is inclined toward the dummy flange 3B2 (3A2) on the radially inner side of the stationary member 3. Therefore, the circumferential end 61 of the outer cover 6 located on the radially inner side of the dummy flange 3B2 (3A2) can be effectively cooled.

[0088] exist Figure 9In the example shown, the holes 31P and 31r, located offset from the dummy flange 3B2 (3A2), are arranged toward the fastening end 611 of the outer cover 6 and inclined relative to the vertical plane (the plane orthogonal to the horizontal plane HZ) extending radially along the stationary member 3. Therefore, if air (compressed air) drawn from the compressor 13 is supplied to the space X radially outward of the stationary member 3, the air is ejected through the holes 31P and 31r toward the fastening end 611 of the outer cover 6, which is located radially inward of the dummy flange 3B2 (3A2), thus effectively cooling the fastening end 611 of the outer cover 6, which is located inside the dummy flange 3B2 (3A2). Furthermore, in Figure 9 In the example shown, the hole 31q of the stationary member 3 located in the dummy flange 3B2 (3A2) faces the sealing end 612 of the outer cover 6 and is arranged parallel to the vertical plane (the plane orthogonal to the horizontal plane HZ) extending radially along the stationary member 3. Therefore, if air (compressed air) drawn from the compressor 13 is supplied to the space X radially outward of the stationary member 3, the air is ejected through a hole 31q toward the sealing end 612 of the outer cover 6 located radially inward of the dummy flange 3B2 (3A2), thus effectively cooling the sealing end 612 of the outer cover 6 located inside the dummy flange 3B2 (3A2).

[0089] The method for manufacturing the stator blade assembly 1 of the gas turbine 10 according to this embodiment is the same as the method described above. The stator blade segment 5 is arranged such that the central axis CN of the hole 31 extending radially from the outer side to the inner side of the stationary member 3 faces the circumferential end 61 of the outer shroud 6. Thus, the stator blade segment 5 is provided on the stationary member 3 such that the circumferential end of the outer shroud 6 is located on the extension line of the hole 31 of the stationary member 3.

[0090] According to the manufacturing method of the stator blade assembly 1 of the gas turbine 10 described above, the stator blade segment 5 is arranged such that the central axis CN of the hole 31 extending radially from the outer side to the inner side of the stationary member 3 faces the circumferential end 61 of the outer shroud 6. Therefore, air drawn from the compressor 13 is ejected through the hole 31 extending radially from the outer side to the inner side of the stationary member 3 toward the circumferential end 61 of the outer shroud 6. As a result, the circumferential end 61 of the outer shroud 6, which is heated by the combustion gas, can be effectively cooled.

[0091] Figures 10 to 12 This is a developed view showing the stator blade segments 5X, 5Y, and 5Z that can be used in the stator blade assemblies 1A, 1B, and 1C of the gas turbine 10 in the embodiments. It should be noted that... Figures 10 to 12 In the middle, for convenience, the outer protective covers 6A, 6B, and 6C are represented as straight lines, but they are formed as arcs along the inner circumference of the stationary member 3.

[0092] Figure 10 The stationary blade segment 5X shown is a stationary blade segment with a fastening part 63A on one side of the circumferential end 61A of the outer protective cover 6A and a protruding end 64A on the other side. An impact plate mounting step 68A for mounting an impact plate 69A is provided inside the fastening part 63A.

[0093] Although not specifically illustrated, in the stationary blade assembly 1A of the gas turbine 10 employing this stationary blade segment 5X, the stationary member has a hole extending radially outward from the stationary member toward the fastening end 611A and through the stationary member to the radially inward. In this stationary blade assembly 1A of the gas turbine 10, air drawn from the compressor 13 is ejected toward the fastening end 611A of the outer shroud 6A, thus efficiently cooling the fastening end 611A of the outer shroud 6A, which particularly requires cooling. Furthermore, although not specifically illustrated, in the stationary blade assembly 1A of the gas turbine 10, the stationary member may also have a hole extending radially outward from the stationary member toward the protruding end 64A and through the stationary member to the radially inward. In the stator assembly 1A of the gas turbine 10, the air drawn from the compressor 13 is sprayed toward the fastening end 611A of the outer casing 6A and the protruding end 64A, so that in addition to the fastening end 611A of the outer casing 6A which particularly needs to be cooled, the protruding end 64A which needs to be cooled can also be cooled efficiently.

[0094] Figure 11 The stationary blade segment 5Y shown is a stationary blade segment with a protruding end 64B provided at the sealing end 612B of the outer protective cover 6B, and an impact plate 69A is mounted on the protruding end 64B.

[0095] Although not specifically illustrated, the stator assembly 1B of the gas turbine 10 employing this stator segment 5Y has a hole extending radially outward from the stationary member toward the protruding end 64B and penetrating radially inward from the stationary member. In this stator assembly 1B of the gas turbine 10, air drawn from the compressor 13 is ejected toward the protruding end 64B of the outer shroud 6B, thus efficiently cooling the protruding end 64B of the outer shroud 6B that requires cooling.

[0096] exist Figure 12 In the stationary blade segment 5Z shown, the sealing end 612C of the outer shield 6C has the same thickness as the other parts (not a protruding end protruding towards the stationary member). In this stationary blade segment 5Z, an impact plate 69C formed in a box shape is provided in a concealed state.

[0097] Although not specifically illustrated, in the stationary blade assembly 1C of the gas turbine 10 employing this stationary blade segment 5Z, the stationary member has a hole extending radially outward from the stationary member toward the sealing end 612C and penetrating radially inward from the stationary member. In this stationary blade assembly 1C of the gas turbine 10, air drawn from the compressor 13 is ejected toward the sealing end 612C of the outer shroud 6C, thus efficiently cooling the sealing end 612C of the outer shroud 6C that requires cooling.

[0098] The present invention is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations thereof.

[0099] For example, the stationary blade segment 5 is not limited to a component with one blade body 7 in a protective cover 6, but can also have two or more blade bodies 7 in the circumferential direction of a protective cover 6, as in a compound leaf.

[0100] The contents described in the above embodiments are as follows.

[0101] The stator assembly (1) of the gas turbine (10) of scheme [1] has the following features:

[0102] The stationary component (3) is formed in a ring shape; and

[0103] Multiple stationary blade segments (5), each equipped with a protective cover (6) and a blade body (7), are arranged radially inside the stationary member (3) along the circumference of the stationary member (3). A cavity (CV) is provided between the protective cover (6) and the stationary member (3), and the protective covers (6) are adjacent to each other in the circumference of the stationary member (3).

[0104] The stationary member (3) is provided with a hole (31) extending from the radially outer side to the radially inner side of the stationary member (3), and the central axis (CN) of the hole (31) is arranged toward the circumferential end (61) of the cover (6).

[0105] According to the stationary blade assembly (1) of the gas turbine (10) disclosed herein, air drawn from the compressor (13) is ejected through a hole (31) extending from the radially outer side to the radially inner side of the stationary member (3) to the circumferential end (61) of the shield (6), thereby effectively cooling the part heated by the combustion gas on both sides, namely the circumferential end (61) of the shield (6).

[0106] [2] The stator assembly (1) of the gas turbine (10) of another embodiment is based on the stator assembly (1) of the gas turbine (10) described in [1].

[0107] The circumferential end (61) of the shield (6) includes a fastening end (611) which is fastened to other shields (6) adjacent to the shield (6) by means of a fastening member (65).

[0108] According to this structure, the air drawn from the compressor (13) is ejected toward the fastening end (611) of the shield (6) through holes (31B, 31D, 31E, 31F) that extend from the radially outer side to the radially inner side of the stationary member (3), thus effectively cooling the fastening end (611) of the shield (6) which is heated on both sides by the combustion gas.

[0109] [3] The stator assembly (1) of the gas turbine (10) of another embodiment is based on the stator assembly (1) of the gas turbine (10) described in [1] or [2].

[0110] The circumferential end (61) of the shield (6) is connected via a sealing member (66) to the sealing end (612) of another shield (6) adjacent to the shield (6).

[0111] According to this structure, the air drawn from the compressor (13) is ejected toward the sealed end (612) of the shield (6) through holes (31A, 31C, 31G) that extend from the radially outer side to the radially inner side of the stationary member (3), thus effectively cooling the sealed end (612) of the shield (6) which is heated on both sides by the combustion gas.

[0112] [4] The stator assembly (1) of the gas turbine (10) of another embodiment is based on the stator assembly (1) of the gas turbine (10) described in any one of [1] to [3].

[0113] The circumferential end (61) of the shield (6) includes a protruding end (64) that protrudes toward the stationary member.

[0114] According to this structure, the air drawn from the compressor (13) is ejected toward the protruding end (64) of the shield (6) through a hole (31) that extends from the radially outer side to the radially inner side of the stationary member (3), thus effectively cooling the protruding end (64) of the shield (6) which is heated by the combustion gas.

[0115] [5] The stator assembly (1) of the gas turbine (10) of another embodiment is based on the stator assembly (1) of the gas turbine (10) described in any one of [1] to [4].

[0116] When viewed radially from the stationary member (3), the openings on the radially inner side of the holes (31A-31D, 31F, 31G) overlap with the circumferential end (61) of the shield (6) in the circumferential direction.

[0117] According to this structure, the air drawn from the compressor (13) is ejected from the opening on the radially inner side of the hole (31A~31D, 31F, 31G) that passes through the stationary member (3) from the radially outer side to the radially inner side toward the circumferential end (61) of the shield (6), thus effectively cooling the circumferential end (61) of the shield (6) which is heated by the combustion gas on both sides.

[0118] [6] The stator assembly (1) of the gas turbine (10) of another embodiment is based on the stator assembly (1) of the gas turbine (10) described in any one of [1] to [5].

[0119] The stationary component (3) is divided into multiple parts in the circumferential direction.

[0120] The hole (31) is a hole (31E) adjacent to the dividing surface of the stationary member (3), and the central axis (CN) of the hole (31E) is inclined toward the dividing surface (3ab) of the stationary member (3) on the radially inner side.

[0121] According to this structure, the air drawn from the compressor (13) is ejected through the hole (31E) adjacent to the dividing surface of the stationary member (3) toward the circumferential end (61) of the shield (6) which is arranged radially inside the dividing surface (3ab) in the circumferential direction of the stationary member (3), thus effectively cooling the circumferential end (61) of the shield (6) which is arranged radially inside the dividing surface (3ab) in the circumferential direction of the stationary member (3).

[0122] [7] Another embodiment of the gas turbine (10) stator assembly (1) of any one of [1] to [5],

[0123] The holes are a plurality of holes arranged circumferentially along the stationary member.

[0124] The plurality of holes include:

[0125] The central axis (CN) of the hole is radially arranged along the first hole (31A-31D, 31F-31G) of the stationary member; and

[0126] The central axis (CN) of the hole is inclined radially relative to the stationary member, and the second hole (31E) is inclined radially inward toward the segmented surface of the stationary member.

[0127] According to this structure, the air drawn from the compressor (13) is ejected through the first hole (31A~31D, 31F~31G) and the second hole (31E), thus effectively cooling the circumferential end (61) of the cover (6) located on the radially inner side of the dividing surface (3ab) of the stationary component segment (lower half 3A, upper half 3B).

[0128] [8] The stator assembly (1) of the gas turbine (10) of another embodiment is based on the stator assembly (1) of the gas turbine (10) described in any one of [1] to [5].

[0129] The stationary component has multiple stationary component segments (lower half 3A, upper half 3B) that are divided circumferentially.

[0130] At least one of the stationary component segments (lower half 3A, upper half 3B) has a central protrusion (dummy flange 3B2 (3A2)) projecting radially outward from the central portion in the circumferential direction.

[0131] The hole is adjacent to the central protrusion (dummy flange 3B2 (3A2)), and the central axis (CN) of the hole is inclined toward the central protrusion (dummy flange 3B2 (3A2)) on the radially inward side of the stationary member.

[0132] According to this structure, the air drawn from the compressor (13) is ejected through the holes (31r, 31p) adjacent to the central protrusion (dummy flange 3B2 (3A2)), that is, the holes (31r, 31p) with the central axis (CN) of the holes inclined toward the central protrusion (dummy flange 3B2 (3A2)) on the radially inner side of the stationary member, so that the circumferential end of the cover (6) provided on the radially inner side of the central protrusion (dummy flange 3B2 (3A2)) can be effectively cooled.

[0133] In the scheme of [9], the stationary component segments (lower half 3A, upper half 3B) are divided into multiple segments in the circumferential direction of the stationary component (3) which is formed into a ring, thus constituting the stationary component (3).

[0134] Multiple holes (31) extending radially from the outer side to the inner side of the stationary component segments (lower half 3A, upper half 3B) are provided circumferentially on the stationary component segments (lower half 3A, upper half 3B).

[0135] The plurality of holes (31) include a first hole (31A-31D, 31F-31G) and a second hole (31E) arranged radially on the stationary member (3).

[0136] The second hole (31D) is inclined toward the radially inner side of the stationary member (3) toward the dividing surface (3ab) of the stationary member segment (lower half 3A, upper half 3B).

[0137] According to this structure, the air drawn from the compressor (13) is ejected through the first hole (31A~31D, 31F~31G) and the second hole (31E), thus effectively cooling the circumferential end (61) of the cover (6) located on the radially inner side of the dividing surface (3ab) of the stationary component segment (lower half 3A, upper half 3B).

[0138] The method for manufacturing the stator assembly 1 of the gas turbine (10) according to scheme

[10] comprises:

[0139] The stationary component (3) is formed in a ring shape; and

[0140] Multiple stationary blade segments (5) are provided with protective covers (6) and blade bodies (7) respectively. They are arranged along the circumference of the stationary member (3) on the radial inner side of the stationary member (3). A cavity (CV) is provided between the protective covers (6) and the stationary member (3). The protective covers (6) are adjacent to each other in the circumference of the stationary member (3).

[0141] in,

[0142] The stationary blade segment (5) is arranged such that the central axis (CN) of the hole (31) provided in the stationary member (3) extending from the radially outer side to the radially inner side of the stationary member (3) is oriented toward the circumferential end (61) of the cover (6).

[0143] According to this manufacturing method, the stator blade segment (5) is arranged such that the central axis (CN) of the hole (31) extending from the radially outer side to the radially inner side of the stationary member (3) is directed toward the circumferential end (61) of the shroud (6). Therefore, air drawn from the compressor (13) is ejected toward the circumferential end (61) of the shroud (6) through the hole (31) extending from the radially outer side to the radially inner side of the stationary member (3). As a result, the part heated by the combustion gas on both sides, namely the circumferential end (61) of the shroud (6), can be effectively cooled.

[0144] Explanation of reference numerals in the attached figures:

[0145] 1, 1A, 1B, 1C...Stationary blade assembly of gas turbine;

[0146] 3...static components;

[0147] 3ab... divides the surface;

[0148] 3A... lower half;

[0149] 3A1...Flange;

[0150] 3A12... Threaded hole;

[0151] 3A2...Dummy flange (central protrusion);

[0152] 3B... Upper half;

[0153] 3B1...Flange;

[0154] 3B12...through hole;

[0155] 3B2...Dummy flange (central protrusion);

[0156] Holes 31, 31A~31G, 31P, 31Q, 31p, 31q, 31r...

[0157] 5, 5A, 5B, 5X, 5Y, 5Z... static leaf segments;

[0158] 6, 6A, 6B, 6C... outer protective cover (protective cover);

[0159] 61... Circumferential end;

[0160] 611, 611A... Fastening end;

[0161] 612, 612B, 612C... Sealed end;

[0162] 621...Front-end mounting section;

[0163] 622... Rear-end mounting section;

[0164] 63, 63A... Fastening parts;

[0165] 64, 64A, 64B... protruding ends;

[0166] 65...fastening components;

[0167] 66...sealing components;

[0168] 68...Impact plate installation step section;

[0169] Impact plates: 69, 69A, 69B, 69C...

[0170] 7...blade body;

[0171] 8...Inner protective cover;

[0172] 10... Gas turbine;

[0173] 12...rotor shaft;

[0174] 121, 123... Bearing sections;

[0175] 13...compressor;

[0176] 131...compressor housing;

[0177] 133... Compressor stator vanes;

[0178] 135...compressor moving blades;

[0179] 137...Entrance;

[0180] 139...discharge outlet;

[0181] 15...burner;

[0182] 151...burner housing;

[0183] 153...combustion tube;

[0184] 155...tailstock;

[0185] 157...Gas supply port;

[0186] 17... Turbine;

[0187] 171... Turbine casing;

[0188] 175... Turbine motor blades;

[0189] 177...exhaust chamber;

[0190] 179... Diffuser.

Claims

1. A stator blade assembly for a gas turbine, wherein, The gas turbine stator assembly includes: A stationary component, which is formed in a ring shape; and Multiple stationary blade segments, each equipped with a protective cover and a blade body, are arranged radially inside the stationary member along its circumference. A cavity is formed between the protective cover and the stationary member, and the protective covers are adjacent to each other in the circumferential direction of the stationary member. The stationary component is provided with a hole extending from the radially outer side to the radially inner side of the stationary component, and the central axis of the hole is arranged toward the circumferential end of the shield in such a way that air passing through the hole directly collides with the circumferential end of the shield.

2. The gas turbine stator assembly according to claim 1, wherein, The circumferential end of the shield includes a fastening end, which is fastened to other shields adjacent to the shield by fastening members.

3. The stator blade assembly of a gas turbine according to claim 1 or 2, wherein, The circumferential end of the shield includes a sealing end, which is connected to other shields adjacent to the shield via a sealing member.

4. The stator blade assembly of a gas turbine according to claim 1 or 2, wherein, The circumferential end of the shield includes a protruding end that projects toward the stationary member.

5. The stator blade assembly of a gas turbine according to claim 1 or 2, wherein, When viewed radially from the stationary member, the opening on the radially inner side of the hole overlaps with the circumferential end of the shield in the circumferential direction.

6. The stator blade assembly of a gas turbine according to claim 1 or 2, wherein, The stationary component is divided into multiple parts in the circumferential direction. The hole is adjacent to the dividing surface of the stationary member, and the central axis of the hole is inclined toward the dividing surface of the stationary member on the radially inward side.

7. The stator blade assembly of a gas turbine according to claim 1 or 2, wherein, The stationary component is divided into multiple parts in the circumferential direction. The holes are a plurality of holes arranged circumferentially along the stationary member. The plurality of holes include: The first hole, whose central axis is arranged radially along the stationary member; and The second hole has its central axis inclined radially relative to the stationary member and is inclined radially inward toward the segmented surface of the stationary member.

8. The stator blade assembly of a gas turbine according to claim 1 or 2, wherein, The stationary component has multiple stationary component segments that are divided into multiple segments in the circumferential direction. At least one of the stationary component segments has a central protrusion that projects radially outward from the radially outer surface of the central portion in the circumferential direction. The hole is adjacent to the central protrusion, and the central axis of the hole is inclined radially inward toward the central protrusion side of the stationary member.

9. A stationary component segment for a gas turbine, wherein the stationary component, which is mounted on the shroud of each stator blade segment of the gas turbine and formed in an annular shape, is divided into a plurality of segments in the circumference of the stationary component, constituting the stationary component, wherein, Multiple holes extending radially from the outer side to the inner side of the stationary component are provided circumferentially on the stationary component segment. The plurality of holes include a first hole and a second hole with different radial angles relative to the stationary member. The first hole is arranged radially along the stationary member such that air passing through it directly collides with the circumferential end of the shield. The second hole is tilted radially relative to the stationary member and towards the segmental surface of the stationary member in such a way that air passes through the second hole and directly collides with the circumferential end of the shield.

10. A method for manufacturing a stator assembly for a gas turbine, the stator assembly comprising: A stationary component, which is formed in a ring shape; and Multiple stationary blade segments, each equipped with a protective cover and a blade body, are arranged radially inside the stationary member along its circumference. A cavity is formed between the protective cover and the stationary member, and the protective covers are adjacent to each other in the circumferential direction of the stationary member. in, The stationary blade segment is configured such that the central axis of the hole extending radially outward to radially inward from the stationary member is positioned such that air passes through the hole and directly collides with the circumferential end of the shield.

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