Turbine stator blade shroud

Abstract

A shroud according to the present disclosure is equipped with a shroud body, a shroud end section and an impingement box. The shroud body is equipped with a first wall which has: a gas path surface which faces a high-temperature gas channel of the turbine; and a cooling surface which faces toward the side opposite the high-temperature gas channel. The shroud end section is equipped with a shroud end section channel in the interior thereof and is positioned in the periphery around the shroud body so as to surround the shroud body. The impingement box is provided at a distance from the cooling surface so as to face the cooling surface of the first wall. The impingement box is equipped with a cooling air introduction port for introducing cooling air from the shroud end section channel into the interior of the impingement box, and an impingement cooling hole for cooling the cooling surface of the first wall by injecting the introduced cooling air at the cooling surface of the first wall.

Description

[Technical Field]

[0001] This disclosure is, Turbine stator blade shroud Regarding. [Background technology]

[0002] The stator vanes and rotor blades of a gas turbine are exposed to high-temperature combustion gases. Therefore, the stator vanes and rotor blades need to be cooled by cooling air. For example, Patent Document 1 below describes an impingement plate that sequentially impinges-cools the stator vanes. Figure 5 of Patent Document 1 illustrates that a series of individual impingement cavities 12, 13, and 21 are sequentially impinged-cooled. [Prior art documents] [Patent Documents]

[0003] [Patent Document 1] U.S. Patent No. 9,638,047 [Overview of the Initiative] [Problems that the invention aims to solve]

[0004] In recent years, gas turbine inlet temperatures have risen, and therefore, further cooling of the first-stage stator vanes is desired. One approach to address the above problem is to supply the first-stage stator vanes with cooling air at a higher pressure and lower temperature (compared to conventional techniques). According to the inventors' considerations, if cooling air at a higher pressure and lower temperature is used to cool the first-stage stator vanes, it may be possible to reuse the cooling air to cool other components of the first-stage stator vanes even after it has been used to cool the airfoil or shroud ends. However, conventional techniques have limited the efficiency of cooling air utilization.

[0005] It is possible to improve the efficiency of using cooling air. Turbine stator blade shroud It is desirable to provide this. [Means for solving the problem]

[0006] A first aspect of the present disclosure provides a shroud for a turbine stator blade. The shroud comprises a shroud body having a first wall having a gas path surface facing the high-temperature gas flow path of the turbine and a cooling surface facing the opposite side of the high-temperature gas flow path; a shroud end provided around the shroud body so as to surround the shroud body and having a shroud end flow path inside; and an impingement box provided spaced apart from the cooling surface of the first wall so as to face the cooling surface of the first wall. The impingement box includes a cooling air intake for introducing cooling air from the shroud end flow path into the interior of the impingement box, and an impingement cooling hole for injecting the introduced cooling air onto the cooling surface of the first wall to cool the cooling surface of the first wall. a flow path that guides the cooling air injected onto the cooling surface of the first wall to the outer space located on the opposite side of the first wall as viewed from the impingement box, It is equipped with.

[0007] The features described above allow the shroud to incorporate such an impingement box, making it possible to provide a turbine stator vane shroud that is easy to manufacture and assemble, while improving cooling efficiency by suppressing cooling air leakage.

[0008] According to another aspect of the present disclosure, the shroud of a turbine stator blade comprises a shroud body having a parallelogram shape and a first wall having a gas path surface facing the high-temperature gas passage of the turbine and a cooling surface facing the opposite side of the high-temperature gas passage, and a shroud end provided around the shroud body so as to surround the shroud body and having a shroud end passage inside, The shroud end passage is provided along the side of the parallelogram shape, and the impingement box includes a cooling air intake for introducing cooling air from the shroud end passage into the interior of the impingement box, and an impingement cooling hole for injecting the introduced cooling air onto the cooling surface of the first wall to cool the cooling surface of the first wall. 。 BookAccording to another aspect of the disclosure, the shroud of a turbine stator blade comprises a shroud body having a first wall having a gas path surface facing the hot gas passage of the turbine and a cooling surface facing the opposite side of the hot gas passage; a shroud end provided around the shroud body so as to surround the shroud body and having a shroud end passage inside; and an impingement box provided spaced apart from the cooling surface of the first wall so as to face the cooling surface of the first wall, wherein the impingement box is the shroud The impingement box includes a cooling air intake for introducing cooling air from an end passage into the interior of the impingement box, and an impingement cooling hole for injecting the introduced cooling air onto the cooling surface of the first wall to cool the cooling surface of the first wall, the periphery of the impingement box includes a mounting portion fixed to the end of the shroud, the impingement box has a rear wall facing the cooling surface of the first wall, the rear wall has a thickened portion around the mounting portion, and the thickened portion has a greater thickness than the rest of the rear wall. According to another aspect of the present disclosure, the shroud of a turbine stator blade comprises a shroud body having a first wall having a gas path surface facing the high-temperature gas passage of the turbine and a cooling surface facing the opposite side of the high-temperature gas passage; a shroud end provided around the shroud body so as to surround the shroud body and having a shroud end passage inside; and an impingement box provided spaced apart from the cooling surface of the first wall so as to be opposite to the cooling surface of the first wall, wherein the impingement box is provided with respect to the shroud end passage and the impingement box The impingement box comprises a cooling air intake for introducing cooling air into the interior, and an impingement cooling hole for injecting the introduced cooling air onto the cooling surface of the first wall to cool the cooling surface of the first wall, the periphery of the impingement box is provided with a mounting portion fixed to the end of the shroud, the impingement box comprises a rear wall facing the cooling surface of the first wall, and a front wall located on the opposite side of the rear wall and having a void between it and the rear wall, and the impingement box further comprises a support structure in which one end is fixed to the front wall and the other end is fixed to the rear wall.

[0010] The significant advantages of this disclosure will become apparent from the following drawings and detailed description. [Brief explanation of the drawing]

[0011] [Figure 1] This is a schematic cross-sectional view of a gas turbine in an embodiment relating to this disclosure. [Figure 2] This is a perspective view of the stator vane in the first embodiment. [Figure 3] This is a cross-sectional view along line III-III in Figure 2. [Figure 4] This is a close-up view of a section of the stator wing. [Figure 5] This is a partial perspective view of a stator vane according to the first embodiment. [Figure 6] This is a partial perspective view of a stator vane according to another embodiment. [Figure 7] This is a flowchart illustrating the cooling method for the stator vanes in the first embodiment. [Figure 8] This is a flowchart illustrating the cooling method for the stator vanes in the second embodiment. [Figure 9] This figure schematically illustrates the cooling process of the second embodiment. [Figure 10] This is a flowchart illustrating the cooling method for the stator vanes in the third embodiment. [Figure 11] This is a schematic cross-sectional view of a stator vane according to the fourth embodiment. [Figure 12A] This is a schematic cross-sectional view of a stator vane according to the fifth embodiment. [Figure 12B] This is a schematic cross-sectional view of a stator vane according to the fifth embodiment. [Figure 13A] This is a schematic cross-sectional view of a stator vane according to the sixth embodiment. [Figure 13B] This is a schematic cross-sectional view of a stator vane according to the sixth embodiment. [Figure 14] This is a perspective view of the seventh embodiment. [Figure 15] This is a schematic diagram of the seventh embodiment. [Figure 16A] This is a perspective view of the stator vane in the seventh embodiment. [Figure 16B] This is a perspective view of a modified example of the seventh embodiment. [Figure 17] This is a flowchart explaining the manufacturing method for turbine stator blade shrouds. [Figure 18] This is a perspective view of a stator wing according to the eighth embodiment. [Figure 19] This is a schematic cross-sectional view of a stator vane according to the eighth embodiment. [Figure 20] This is a magnified view of a portion of Figure 19. [Figure 21] This is a close-up view of a portion of the impingement box. [Figure 22] This is a cross-sectional view along the line XXII-XXII in Figure 20. [Figure 23A] This is a schematic cross-sectional view of a stator vane according to the eighth embodiment. [Figure 23B] This is a schematic cross-sectional view of a stator vane according to the eighth embodiment. [Figure 24] This is a flowchart explaining the manufacturing method for turbine stator blade shrouds. [Figure 25] This is a schematic cross-sectional view of a stator vane according to the eighth embodiment. [Figure 26] This is a schematic cross-sectional view of a stator vane illustrating the principle of the eighth embodiment. [Figure 27] This is a schematic cross-sectional view of the ninth embodiment. [Figure 28] This is a schematic bottom view of the ninth embodiment. [Figure 29] This is a schematic cross-sectional view of a modified example of the ninth embodiment. [Modes for carrying out the invention]

[0012] Embodiments of the present disclosure will be described in detail below with reference to the drawings. Figure 1 is a schematic cross-sectional view of a gas turbine according to an embodiment of the present disclosure. As shown in Figure 1, the gas turbine 10 of this embodiment includes a turbine 20 driven by combustion gas generated by a combustor 30. The turbine 20 comprises a rotor shaft 24, a turbine rotor 26 that rotates around axis Ar, a turbine casing 22 that covers the turbine rotor 26, and a plurality of stator vanes 28.

[0013] Figure 2 schematically illustrates a stator blade of a gas turbine according to an embodiment of the present disclosure. Figure 2 is a perspective view of a stator blade in the first embodiment. Figure 3 is a cross-sectional view along line III-III in Figure 2. Figure 4 is a partially enlarged view of the stator blade. As shown in Figure 2, the stator blade 50 includes a stator blade body (airfoil) 51 extending radially from the gas turbine, an inner shroud 60 positioned radially inside the stator blade body 51, and an outer shroud 70 positioned radially outside the stator blade body 51. The stator blade body 51 is positioned in a combustion gas flow path (high-temperature gas flow path) through which combustion gases pass. Generally, an annular combustion gas flow path is defined radially inside by the inner shroud 60 and radially outside by the outer shroud 70. The inner shroud 60 and the outer shroud 70 are plate-like members that define a portion of the combustion gas flow path.

[0014] As shown in Figure 2, the upstream end of the stator vane body 51 has a leading edge 52, and the downstream end of the stator vane body 51 has a trailing edge 53. Of the surfaces of the stator vane body 51, the convex surface is the dorsal surface 54 (negative pressure surface), and the concave surface is the ventral surface 55 (positive pressure surface). For convenience, in the following description, the ventral side (positive pressure surface side) and the dorsal side (negative pressure surface side) of the stator vane body 51 will be referred to as the ventral side and the dorsal side, respectively.

[0015] The inner shroud 60 and the outer shroud 70 have essentially the same structure. Therefore, the following description will mainly focus on the outer shroud 70.

[0016] As shown in FIGS. 2 and 3, the outer shroud 70 is a plate-shaped shroud member, and includes a shroud body 72, a shroud end portion 74 disposed on the outer periphery of the shroud body 72, and a peripheral wall 76 extending along the shroud end portion 74. The peripheral wall 76 protrudes radially outward from the shroud body 72 toward the gas turbine.

[0017] The outer shroud 70 has a front end face which is an upstream end face, a rear end face which is a downstream end face, a ventral end face which is a ventral side end face, and a dorsal end face which is a ventral side end face. The outer shroud 70 has a gas passage surface 78 facing radially inward and facing the high-temperature gas flow path. The front end face and the rear end face are substantially parallel to each other, and the ventral end face and the dorsal end face are substantially parallel to each other. Therefore, when viewed from the radial direction, the outer shroud 70 has a substantially parallelogram shape as shown in FIG. 3.

[0018] The shroud end portion 74 is a flange-like or edge-like structure protruding from the shroud body 72. The shroud end portion 74 includes a front shroud end portion 74 disposed on the upstream side of the outer shroud 70 L and a rear shroud end portion 74 disposed on the downstream side of the outer shroud 70 T and a dorsal shroud end portion 74 disposed on the dorsal side of the outer shroud 70 N and a ventral shroud end portion 74 disposed on the ventral side of the outer shroud 70 P and the like. For example, as shown in FIG. 3, the front shroud end portion 74 L、 the rear shroud end portion 74 T、 the dorsal shroud end portion 74 N and the ventral shroud end portion 74 P are disposed on the outer periphery of the shroud body 72 and surround the entire shroud body 72.

[0019] The front shroud end portion ...... L includes a front shroud end portion flow path 75 inside thereof L The rear shroud end portion 74 T includes a rear shroud end portion flow path 75 inside thereof T The dorsal shroud end portion 74 NThe dorsal shroud end channel 75 is located inside it. N Includes. Ventral shroud end 74 P The ventral shroud end channel 75 is located inside it. P Includes.

[0020] In this embodiment, the front shroud end channel 75 L At one end, the dorsal shroud end channel 75 N It is connected to the ventral shroud end channel 75 at the other end. P It is connected to the rear shroud end channel 75. T At one end, the dorsal shroud end channel 75 N It is connected to the ventral shroud end channel 75 at the other end. P It is connected to the front shroud end channel 75. As shown in Figures 2, 3 and 4, L It has a shroud end channel inlet 171. Rear shroud end channel 75 T It has a shroud end channel outlet 172. The front shroud end channel 75 passes through the shroud end channel inlet 171. L A portion of the cooling air flowing into the rear shroud end channel 75 N and ventral shroud end channel 75 P It passes through, and then the rear shroud end channel 75 T It flows through and exits from the shroud end channel outlet 172. As shown in Figure 3, the shroud end channel 75 L , 75 T , 75 P , 75 N The system includes a turbulator 175. The turbulator 175 may be a rib positioned on the inner surface of the shroud end flow path. To enhance cooling of the shroud end, the turbulator 175 may be positioned on the bottom surface of the flow path that defines the radial inner surface of the flow path. Here, the bottom surface of the flow path may extend substantially parallel to the radial inner wall 81. The turbulator 175 may also be positioned on the side surface of the flow path that defines the circumferential side wall or the axial wall of the flow path.

[0021] In this embodiment, the shroud end channel inlet 171 is the front shroud end channel 75L The shroud end channel outlet 172 is located at the rear shroud end channel 75 T It is provided in the following location. However, the structure of the stator vane is not limited to this embodiment. The shroud end channel inlet 171 is located in the dorsal shroud end channel 75 N ventral shroud end channel 75 P , or rear shroud end channel 75 T It may also be provided in other shroud end channels such as the one shown. The shroud end channel outlet 172 is located in the dorsal shroud end channel 75 N ventral shroud end channel 75 P , or front shroud end channel 75 L They may also be provided in other shroud end channel inlets such as the following. In another form, multiple shroud end channel inlets 171 may be provided in one or more shroud end channel inlets 75 L , 75 T , 75 N , 75 P They may also be provided in one or more shroud end channel outlets 172. L、 75 T , 75 N , 75 P It may be provided in [location].

[0022] The shroud body 72 comprises a radial inner wall 81 and a radial outer wall 82 located on the opposite side. The shroud body 72 includes a hollow space S between the radial inner wall 81 and the radial outer wall 82. The radial inner surface of the inner wall 81 constitutes the gas path surface 78 of the outer shroud 70. This radial inner wall 81 constitutes a part of the shroud body 72. This radial inner wall 81 may extend continuously in the circumferential or axial direction of the gas turbine to constitute a part of the shroud end 74. Figure 2 shows, as an example, the radial inner wall 81 continuously extends in the axial direction of the gas turbine to form the rear shroud end 74. T This describes an example of a part of the structure. The shroud body 72 includes an impingement plate 73 that divides the space S of the outer shroud 70 into an outer region radially outward and an inner region (cavity) radially inward. In the outer region, a portion of the cooling air flows through the rear shroud end passage 75. TIt is connected to the shroud end flow outlet 172 so that it flows into the outer region. The inner region is defined between the radial inner wall 81 of the outer shroud 70 and the impingement plate 73.

[0023] In the impingement plate 73, a plurality of impingement cooling holes 79 are provided so as to penetrate the impingement plate 73 radially. A portion of the cooling air present in the outer region flows into the inner region through the impingement cooling holes 79 of the impingement plate 73. This cooling air is injected toward the radial outer surface of the radial inner wall 81, impingement cooling the radial outer surface of the radial inner wall 81, and then discharged to the outside through the outer wall 82. For example, the cooling air injected from the impingement cooling holes 79 toward the radial outer surface of the radial inner wall 81 to impingement cool the radial outer surface of the radial inner wall 81 is discharged through a passage connecting the inner region of the hollow space (S) and the outer space located on the opposite side (outside) of the hollow space (S) of the outer wall 82. Such a passage may be isolated from the outer region of the hollow space (S). More specifically, in this embodiment, the cooling air is discharged through a hole in the discharge pipe 83. The discharge pipe 83 is provided so as to penetrate the radial outer wall 82 and the impingement plate 73 in a manner that connects the inner region and the outer space.

[0024] The stator vane body 51 is provided with a plurality of air channels 141, 142, 143. More specifically, the interior of the stator vane body 51 is provided with a radially extending partition wall 51 PThis divides the air into multiple air channels 141, 142, and 143. Multiple inserts 151, 152, and 153 are inserted into each of the air channels 141, 142, and 143. Each of the inserts 151, 152, and 153 includes radially extending inner air channels 161, 162, and 163, extending radially from the outer shroud 70 through the stator vane body 51 toward the inner shroud 60. Each insert 151, 152, and 153 is formed continuously from the outer shroud 70 through the stator vane body 51 toward the inner shroud 60. Each inner air channel 161, 162, and 163 has an air intake 58 that opens into the inside of the intake manifold 56.

[0025] Each insert 151, 152, and 153 has multiple holes (through-holes) 59 that communicate with the internal air channels 161, 162, and 163, respectively. A portion of the cooling air supplied to the internal air channels 161, 162, and 163 of the inserts 151, 152, and 153 is injected from the multiple holes 59 toward the inner surface of the stator vane body 51 to impinge cooling the inner surface of the airfoil 51. Each of the multiple air channels 141, 142, and 143 has an external air channel defined between the inserts 151, 152, and 153 and the inner surface of the stator vane body 51. A portion of the cooling air injected through the holes 59 is guided by the external air channel and flows through the external air channel toward the radially outward, radially inward, or radially outward and inward. As an example, Figure 3 shows an external air channel 57 provided between the side of insert 151 and the inner surface of the front end of the stator vane body 51.

[0026] The intake manifold 56 and exhaust pipe 83 are connected to a forced air cooling system in which cooling air drawn from inside the combustor casing is cooled by an external cooler (not shown) and then compressed by an external compressor (not shown). The compressed air is used for cooling and then returned to the inside of the combustor casing. The above description illustrates an example in which an air cooling system is applied to this embodiment. However, the stator vanes are not limited to such embodiments. The disclosure may be applied to other types of cooling systems. For example, the intake manifold 56 and exhaust pipe 83 may be connected to a closed-loop steam cooling system or a closed-loop air cooling system. The compressed air used for cooling is supplied to the intake manifold and first supplied directly to the air intake 58 without passing through the shroud body 72 or the shroud end 74. That is, the cooling air is first used to cool the airfoil 51 before it is used to cool the shroud body 72 or the shroud end 74.

[0027] In this embodiment, the air channel 141 is a front end air channel located at the upstream end of the stator vane body 51. For example, in the insert 151, which is a front end insert, a portion of the cooling air supplied to the inner air channel 161 through the air intake 58 is injected through the hole 59 toward the inner surface of the front end of the airfoil 51, and then flows radially outward through the outer air channel 57. The outer air channel 57, which is the space between the inner surface of the front end of the stator vane body 51 and the insert 151, is the front shroud end passage 75 L It communicates with the shroud end channel inlet 171. A portion of the cooling air injected toward the inner surface of the front end of the airfoil 51 passes through the outer air channel 57 connected to the shroud end channel inlet 171 to the front shroud end channel 75. L It flows into the shroud end channel inlet 171.

[0028] Figure 5 is a partial perspective view of a stator vane in the first embodiment. In this embodiment, the air channel 142 is located downstream of the front air channel 141 and is an intermediate air channel located between the front air channel 141 and the rear air channel 143 (described in detail below). For example, in the intermediate insert insert 152, a portion of the cooling air supplied to the inner air channel 162 through the air intake 58 is injected through the hole 59 toward the inner surface of the central part of the airfoil 51, then flows radially inward through the outer air channel toward the inner shroud 60, and then flows into the shroud end flow channel inlet 181 of the inner shroud 60 (located on the rear shroud end), as shown in Figure 5. Next, the cooling air passes through the shroud end passage 65 of the inner shroud 60, cooling the shroud end 64 of the inner shroud 60, and then flows into the shroud body 62 of the shroud 60 via the shroud end passage outlet 182 (located in the front shroud end passage) of the inner shroud 60. Similar to the outer shroud 70, the cooling air is injected from the impingement cooling holes of the impingement plate 63, cooling the radial outer wall of the inner shroud 60, which has a gas path surface facing radially outward and facing the hot gas passage.

[0029] In this embodiment, a portion of the cooling air injected from the front inner air channel 161 toward the inner surface of the front end of the airfoil 51 flows radially outward through the outer air channel 57 toward the outer shroud 70. Also, a portion of the cooling air injected from the intermediate inner air channel 162 toward the inner surface of the central part of the airfoil 51 flows radially inward through the outer air channel 57 toward the inner shroud 60. However, the structure of the stator vanes is not limited to this embodiment. A portion of the cooling air injected from the front inner air channel 161 toward the inner surface of the front end of the airfoil 51 may be configured to flow radially inward through the outer air channel 57 toward the inner shroud 60. Alternatively, a portion of the cooling air injected from the intermediate inner air channel 162 toward the inner surface of the central part of the airfoil 51 may be configured to flow radially outward through the outer air channel 57 toward the outer shroud 70. Such modifications are described in detail below as other embodiments.

[0030] In some embodiments of this disclosure, as shown in Figure 2, the air channel 143 is a rear-end air channel located at the downstream end of the stator vane body 51. The rear-end air channel 143 includes an airfoil cooling structure 154 downstream of the insert 153. The airfoil cooling structure 154 includes a passage in which a plurality of pin fins 164 are arranged inside. For example, in the insert 153, which is a rear-end insert, a portion of the cooling air supplied to the inner air channel (rear-end inner air channel) 163 via the air intake 58 is injected through the hole 59 onto the inner surface of the rear end of the airfoil 51 and then led to the airfoil cooling structure 154. The cooling air passes through the passage with the pin fins 164 and is then discharged into a hot gas passage at the trailing edge 53 of the airfoil 51.

[0031] Figure 6 is a partial perspective view of a stator vane in another embodiment. As shown in Figure 6, in this embodiment, the shroud end channel inlet 181 of the inner shroud 60 is located at the front shroud end 64 L It is positioned on top. Also, the shroud end flow outlet 182 of the inner shroud 60 is located at the rear shroud end 64T It is positioned on top. In this embodiment, the shroud end channel inlet 171 of the outer shroud 70 is located at the rear shroud end 74 T It is positioned on top. Furthermore, the shroud end flow outlet 172 of the outer shroud 70 is located at the front shroud end 74 L It is positioned above. In this embodiment, in the front end insert insert 151, a portion of the cooling air supplied to the inner air channel 161 through the air intake 58 is injected through the hole 59 toward the inner surface of the front end of the airfoil 51, and then guided radially inward through the outer air channel 57 toward the inner shroud 60, and as shown in Figure 6, the shroud end flow channel inlet 181 (front shroud end 64) of the inner shroud 60. L It flows into (located above). The cooling air then passes through the shroud end passage 65 of the inner shroud 60, cooling the shroud end 64 of the inner shroud 60, and then flows out the shroud end passage outlet 182 (rear shroud end 64) of the inner shroud 60. T It flows into the shroud body 62 of the inner shroud 60 via the (located at) the insert 152, which is an intermediate insert, and a portion of the cooling air supplied to the inner air channel 162 through the air intake 58 is injected through the hole 59 toward the inner surface of the central part of the airfoil 51, then guided radially outward through the outer air channel 57 toward the outer shroud 70, and then flows through the shroud end flow channel inlet 171 (rear shroud end 74) of the outer shroud 70. T It flows into (located above). The cooling air then passes through the shroud end passage 75 of the outer shroud 70, cooling the shroud end 74 of the outer shroud 70, and then flows out the shroud end passage outlet 172 (front shroud end 74) of the outer shroud 70. L It flows into the shroud body 72 of the outer shroud 70 via (which is located at).

[0032] Next, the cooling method for the stator vane of the first embodiment will be described. Figure 7 is a flowchart illustrating the cooling method for the stator vane of the first embodiment. As shown in Figure 7, in step S102, a portion of the cooling air flows into the front end air channel 141 to cool the front end air channel 141. The cooling air passes through the hole 59 of the insert 151 and is injected from the front end inner air channel 161 toward the inner surface of the front end of the airfoil 51, and then passes through the outer air channel 57 and is guided radially outward or radially inward toward either the outer shroud 70 or the inner shroud 60, thereby cooling the outer shroud 70 or the inner shroud 60.

[0033] In step S104, a portion of the cooling air flows into the intermediate air channel 142 to cool it. The cooling air is injected through the hole 59 of the insert 151, from the intermediate inner air channel 162 toward the inner surface of the central part of the airfoil 51, and then guided radially outward or radially inward through the outer air channel 57 toward the other of the outer shroud 70 or the inner shroud 60, to cool the other of the outer shroud 70 or the inner shroud 60.

[0034] Next, a method for cooling the stator vane according to a second embodiment will be described. Figure 8 is a flowchart illustrating the method for cooling the stator vane according to a second embodiment. This method will be illustrated using an air channel 141 and an outer shroud 70 as an example. Figure 9 schematically illustrates the cooling process of the second embodiment. As shown in Figures 8 and 9(a), in step S202, a portion of the cooling air flows through the air intake 58 into the inner air channel 161 of the insert 151. The cooling air is then injected through the hole 59 toward the inner surface of the front end of the airfoil 51 to cool the airfoil 51 and flows radially outward through the outer air channel 57. In some embodiments, the cooling air flowing into the inner air channel may be introduced from a forced air cooling system.

[0035] As shown in Figure 9(b), in step S204, cooling air flows into the shroud end channel 75 through the shroud end channel inlet 171. The cooling air flows along the shroud end channel 75 and cools the shroud end 74.

[0036] As shown in Figure 9(c), in step S206, cooling air flows into the outer region of the shroud body 72 and is injected through the impingement cooling holes 79 toward the radial outer surface of the radial inner wall 81, thereby impinging and cooling the radial outer surface of the radial inner wall 81 and cooling the shroud body 72.

[0037] Next, a cooling method for the stator vane according to a third embodiment will be described. Figure 10 is a flowchart illustrating the cooling method for the stator vane according to the third embodiment. As shown in Figure 10, in step S302, in at least one air channel, a portion of the cooling air flows through the air intake into the inner air channel of the insert. The cooling air is then injected through the hole toward the inner surface of the front end of the airfoil to cool the airfoil and flows radially outward through the outer air channel. In one embodiment, the cooling air flowing into the inner air channel may be introduced from a forced air cooling system.

[0038] In step S304, cooling air flows into the outer region of the shroud body and is injected through the impingement cooling holes toward the radial outer surface of the radial inner wall, cooling the radial outer surface of the radial inner wall and thus cooling the shroud body.

[0039] In step S306, cooling air flows into the shroud end channel through the shroud end channel inlet. The cooling air flows along the shroud end channel, cooling the shroud end. In one embodiment, the cooling air is returned to the forced air cooling system through the shroud end channel outlet.

[0040] Next, a fourth embodiment of the present application will be described below. Figure 11 is a schematic cross-sectional view of a stator vane according to the fourth embodiment. As shown in Figure 11, in the fourth embodiment, a plurality of airfoils 51 (two in this embodiment) are connected to the shroud end flow path 75 L , 75 T , 75 N , 75 P It is surrounded by. Unlike the first embodiment (Figure 3), the two shroud end channel inlets 171 are located in the front shroud end channel 75 L It is located at [location].

[0041] Each outer air channel, which is the space between the inner surface of the front end of the two airfoils 51 and each insert 151, flows through the front shroud end flow path 75 via an air passage provided at the outer end of the outer air channel of each airfoil 51. L The shroud end channel inlet 171 is connected to the front shroud end channel 75. Cooling air passes through each shroud end channel inlet 171 to the front shroud end channel 75. L It flows into the dorsal shroud end channel 75 N , or ventral shroud end channel 75 P The fluid flows through the shroud end channel outlet 172 and into the outer region of the shroud body 72.

[0042] In the above embodiment, the stator vane body (airfoil) included three air channels 141, 142, and 143. However, the number of air channels included in the stator vane body (airfoil) is not limited to three. The stator vane body (airfoil) may include a different number of air channels, such as two, four, five, or more. In such modified embodiments, each air channel may be connected to an outer shroud or an inner shroud.

[0043] For example, a fifth embodiment of the present application is described below. Figures 12A and 12B are schematic cross-sectional views of a stator vane according to the fifth embodiment, respectively. As shown in Figures 12A and 12B, in the fifth embodiment, the stator vane body (airfoil) includes air channels 191, 192, 193, 194, and 195 arranged in this order from the upstream end to the downstream end of the hot gas flow in the turbine. Each of the air channels 191, 192, 193, 194, and 195 includes an insert and an inner air channel (not shown). As shown in Figure 12A, the first air channel 191 and the second air channel 192 are located at the front shroud end 74 L The outer shroud 70 is located at the rear shroud end, and the air channel inlet 171 is connected to it. Also, as shown in Figure 12B, the third air channel 193 and the fourth air channel 194 are connected at the rear shroud end 64 T It communicates with the shroud end channel inlet 181 of the inner shroud 60 located there.

[0044] In this embodiment, a portion of the cooling air introduced into the first air channel 191 flows through the interior of the first air channel 191, is injected from the first inner air channel through the hole 59 of the first insert toward the inner surface of the front end of the airfoil 51, and is then guided to flow radially outward through the outer air channel 57 toward the outer shroud 70. Similarly, a portion of the cooling air injected from the second inner air channel of the second air channel 192 through the hole 59 of the second insert toward the inner surface of the central part of the airfoil 51 is guided to flow radially outward through its own outer air channel 57 toward the outer shroud 70. The cooling air is then guided to the shroud end flow channel inlet 171 of the outer shroud 70.

[0045] In this embodiment, a portion of the cooling air injected from the third inner air channel of the third air channel 193 through the hole 59 of the third insert toward the inner surface of the central part of the airfoil 51 is guided to flow radially inward toward the inner shroud 60 through its outer air channel 57. Similarly, a portion of the cooling air injected from the fourth inner air channel of the fourth air channel 194 through the hole 59 of the fourth insert toward the inner surface of the central part of the airfoil 51 is guided to flow radially inward toward the inner shroud 60 through its outer air channel 57. The cooling air is then guided to the shroud end flow channel inlet 181 of the inner shroud 60.

[0046] The fifth air channel 195 is a rear-end air channel located at the downstream end of the stator vane body 51. As described above, in the fifth air channel 195, a portion of the cooling air supplied to the fifth inner air channel through the air intake 58 is injected through the holes 59 toward the inner surface of the rear end of the airfoil 51 and is then guided to flow into the airfoil cooling structure 154. A portion of the cooling air flows through a passage equipped with pin fins 164 and is then discharged into a hot gas passage at the trailing edge 53 of the airfoil 51.

[0047] The structure of the stator vanes is not limited to this embodiment. In an alternative embodiment, the shroud end flow channel inlet 171 of the outer shroud 70 is located at the rear shroud end 74 T The outer shroud 70 may be positioned at the front shroud end 74 L They may be arranged as follows. Also, the shroud end channel inlet 181 of the inner shroud 60 is the front shroud end 64 L The inner shroud 60 may be positioned at the rear shroud end 64 T They may be arranged at the front shroud end 64. In this embodiment, the first air channel 191 and the second air channel 192 are located at the front shroud end 64 LIt communicates with the shroud end channel inlet 181 of the inner shroud 60 disposed therein. Further, the third air channel 193 and the fourth air channel 194 communicate with the shroud end channel inlet 171 of the outer shroud 70 disposed at the rear shroud end 74 T It communicates with the shroud end channel inlet 171 of the outer shroud 70 disposed therein.

[0048] Next, a sixth embodiment of the present application will be described below. FIGS. 13A and 13B are schematic cross-sectional views of the stator blades according to the sixth embodiment. In this embodiment, the outer shroud 70 has two shroud end channel inlets (the front shroud end channel inlet 171 L and the rear shroud end channel inlet 171 T ) and two shroud end channel outlets (the ventral shroud end channel outlet 172P and the dorsal shroud end channel outlet 172 N ). The front shroud end channel inlet 171 L is provided at the front shroud end 74 L . The rear shroud end channel inlet 171 T is provided at the rear shroud end 74 T . The ventral shroud end channel outlet 172 P is provided at the ventral shroud end 74 P . The dorsal shroud end channel outlet 172 N is provided at the dorsal shroud end 74 N . The air channels 191, 192, 193, 194 and 195 each include an insert and an inner air channel (not shown).

[0049] In this embodiment, the inner shroud 60 has two shroud end channel inlets (the front shroud end channel inlet 181 L and the rear shroud end channel inlet 181<C T ) and two shroud end channel outlets (the ventral shroud end channel outlet 182<C P and the dorsal shroud end channel outlet 182<C N ). The front shroud end channel inlet 181 L is provided at the front shroud end 64 Lis provided at the rear shroud end flow path inlet 181 T is provided at the rear shroud end 64 T The ventral shroud end flow path outlet 182 P is provided at the ventral shroud end 64 P The dorsal shroud end flow path outlet 182 N is provided at the dorsal shroud end 64 N is provided at.

[0050] As shown in FIG. 13A, the first air channel 191 is connected to the shroud end flow path inlet 171 of the outer shroud 70 disposed at the front shroud end 74 L and is in communication. Also, the fourth air channel 194 is connected to the shroud end flow path inlet 171 of the outer shroud 70 disposed at the rear shroud end 74 L and is in communication. As shown in FIG. 13B, the second air channel 192 is connected to the shroud end flow path inlet 181 of the inner shroud 60 disposed at the front shroud end 64 T and is in communication. The third air flow path 193 is connected to the shroud end flow path inlet 181 of the inner shroud 60 disposed at the rear shroud end 64 T and is in communication. L and is in communication. L and is in communication. The third air flow path 193 is connected to the shroud end flow path inlet 181 of the inner shroud 60 disposed at the rear shroud end 64 T and is in communication. T and is in communication.

[0051] In this embodiment, for example, a part of the cooling air supplied to the first air channel 191 is jetted from the first inner air channel through the hole portion 59 of the first insert toward the inner surface of the front end portion of the airfoil 51, and then is guided to flow radially outward through its outer air channel 57 toward the outer shroud 70. Then, as shown in FIG. 13A, it flows into the front shroud end flow path inlet 171 L . The cooling air then flows along the front shroud end flow path 7'5 L . Then, the cooling air flows along the ventral shroud end flow path 75 P , then flows out from the ventral shroud end flow path outlet 172 P , or the dorsal shroud end flow path 75N It flows along the back shroud end channel outlet 172 N It flows out from there. In this embodiment, for example, a portion of the cooling air supplied to the fourth air channel 194 is injected from the fourth inner air channel through the hole 59 of the fourth insert toward the inner surface of the central part of the airfoil 51, and is then guided to flow radially outward through its own outer air channel 57 toward the outer shroud 70. Then, as shown in Figure 13A, the rear shroud end flow channel inlet 171 T The cooling air then flows into the rear shroud end passage 75. T It flows along the following path. Next, the cooling air flows through the ventral shroud end channel 75 P It flows along the ventral shroud end channel outlet 172 P Outflow from, or from the dorsal shroud end channel 75 N It flows along the back shroud end channel outlet 172 N It leaks from there.

[0052] In this embodiment, for example, a portion of the cooling air supplied to the second air channel 192 is injected from the second inner air channel through the hole 59 of the second insert toward the inner surface of the central part of the airfoil 51, and then guided to flow radially inward through its outer air channel 57 toward the inner shroud 60. Then, as shown in Figure 13B, the front shroud end flow channel inlet 181 L The cooling air then flows into the front shroud end passage 65. L It flows along the following path. Next, the cooling air flows through the ventral shroud end channel 65 P It flows along the ventral shroud end channel outlet 182 P Outflow from, or from the dorsal shroud end channel 65 N It flows along the back shroud end channel outlet 182 NIt flows out from there. In this embodiment, for example, a portion of the cooling air supplied to the third air channel 193 is injected from the third inner air channel through the hole 59 of the third insert toward the inner surface of the central part of the airfoil 51, and is then guided to flow radially inward through its outer air channel 57 toward the inner shroud 60. Then, as shown in Figure 13B, the rear shroud end flow channel inlet 181 T The cooling air then flows into the rear shroud end passage 65. T It flows along the following path. Next, the cooling air flows through the ventral shroud end channel 65 P It flows along the ventral shroud end channel outlet 182 P Outflow from, or from the dorsal shroud end channel 65 N It flows along the back shroud end channel outlet 182 N It leaks from there.

[0053] The fifth air channel 195 is a rear-end air channel located at the downstream end of the stator vane body 51. As described above, in the fifth air channel 195, a portion of the cooling air supplied to the fifth inner air channel through the air intake 58 is injected through the holes 59 toward the inner surface of the rear end of the airfoil 51 and is then guided to flow into the airfoil cooling structure 154. A portion of the cooling air flows through a passage equipped with pin fins 164 and is then discharged into a hot gas passage at the trailing edge 53 of the airfoil 51.

[0054] The stator vane structure is not limited to this embodiment. In an alternative embodiment, the first air channel 191 is located at the front shroud end 64 L The inner shroud 60 is positioned at the shroud end channel inlet 181. L It may also be connected to the rear shroud end 64. T The inner shroud 60 is positioned at the shroud end channel inlet 181. T It may also be connected to the front shroud end 74. L Outer shroud 70 is located at the shroud end channel inlet 171L It may also be connected to the rear shroud end 74. T Outer shroud 70 is located at the shroud end channel inlet 171 T It may be connected to this.

[0055] Next, a seventh embodiment of the present application will be described below. Figure 14 is a perspective view of the seventh embodiment. Figure 15 is a schematic diagram of the seventh embodiment. Figure 16A is a perspective view of the stator vane in the seventh embodiment. This embodiment will be described using the outer shroud 70 as an example. As shown in Figure 16A, the outer shroud body 72 includes an impingement box 300. As shown in Figure 15, the impingement box 300 is inserted into a gap CA formed in the shroud body 72. The gap CA is a space enclosed by the shroud end 74 and the radial inner wall 81. One or more spacers 320 are provided inside the gap CA.

[0056] As shown in Figure 14, the impingement box 300 is a box-shaped structure with an internal space. The impingement box 300 comprises a front wall 302, a rear wall 304, and a perimeter side wall 306. The impingement box 300 also includes a box air intake 308 in the perimeter side wall 306. The box air intake 308 is connected to the shroud end flow outlet 172 to introduce cooling air into the internal space. After being fixed to the shroud body 72, the front wall 302 constitutes the radial outer wall 82, and the rear wall 304 constitutes the impingement plate 73. Thus, the rear wall 304 comprises a plurality of cooling holes 79.

[0057] The front wall 302, the rear wall 304, and the surrounding side walls 306 are connected to each other to provide an airtight chamber inside the impingement box 300, except for the box air intake 308 and the cooling holes 79.

[0058] Figure 16A illustrates the impingement box 300 being inserted and mounted into the outer shroud 70. The impingement box 300 is fixed to the shroud end 74, for example, by welding or brazing. In Figure 16A, the dashed line indicates the welded portion between the impingement box 300 and the shroud end 74. As an example, the impingement box 300 is attached to the rear shroud end 74 N It is welded to the front shroud end 74. L , rear shroud end 74 T , or ventral shroud end 74 P Other parts of the shroud end 74 may be welded to it. Furthermore, the impingement box 300 may be welded to the airfoil 51.

[0059] For example, Figure 16B is a perspective view of a modified example of the seventh embodiment. In Figure 16B, the peripheral end of the front wall 302 is the rear shroud end 74 N , front shroud end 74 L , rear shroud end 74 T and welded to the side of the airfoil 51. The peripheral end of the front wall 302 is welded to the rear shroud end 74. N , front shroud end 74 L , rear shroud end 74 T An airtight structure is provided around the front wall 302 by welding to the side of the airfoil 51. As shown in Figure 16B, a discharge pipe 83 may be provided that penetrates the front wall and the impingement plate (rear wall) to connect the inner region with the outer space.

[0060] Next, a method for manufacturing the turbine stator blade shroud will be described. Figure 17 is a flowchart illustrating the method for manufacturing the turbine stator blade shroud. As shown in Figure 17, in step S402, the impingement box 300 is prepared. Next, in step S404, the impingement box 300 is inserted into the gap CA of the shroud body 72 such that the rear wall 304 faces the radially outer surface of the radially inner wall 81. Next, the impingement box 300 is welded to the side of the shroud end 74 and / or airfoil 51 to provide sealing around the front wall 302.

[0061] In these steps, a spacer 320 may be provided to support the rear wall 304. As shown in Figure 15, the shroud body 72 may have a spacer 320 on the surface of the radial inner wall 81. The spacer 320 provides support to the rear wall 304 and facilitates the positioning of the impingement box 300 and the maintenance of space between the radial inner wall 81 of the shroud body 72 and the rear wall 304.

[0062] According to this embodiment, the impingement box 300 is inserted into and welded to the outer shroud 70, thereby forming the inner and outer regions of the space S of the shroud body 72. Sealing is provided along the perimeter of the front wall 302 so that the impingement box 300 can be attached to the rear shroud end 74 N , front shroud end 74 L , rear shroud end 74 T Furthermore, by welding to the side of the airfoil 51, the inner and outer regions of the space S of the shroud body 72 can be easily sealed. In addition, the exhaust pipe 83 can collect and discharge cooling air from the airtight space after impingement cooling.

[0063] Although the above embodiment was described using the outer shroud 70 as an example, this embodiment can be similarly applied to the inner shroud 60. Although the above embodiment was described using an impingement box 300 installed on the dorsal side of the shroud body 72 as an example, the shroud body 72 may also have other impingement boxes 300 installed on the ventral side. Since the other impingement boxes 300 have a similar structure, a detailed explanation will be omitted.

[0064] Next, an eighth embodiment of the present application will be described. Figure 18 is a perspective view of a stator vane according to the eighth embodiment. This embodiment will be described using the outer shroud 70 as an example. As shown in Figure 18, the outer shroud body 72 comprises an impingement box 400. Similar to the impingement box 300, the impingement box 400 comprises a front wall 402, a rear wall 404, and a periphery side wall 406. The rear wall 404 comprises a plurality of cooling holes 79. The impingement box 400 also comprises a box air intake 408 (see Figures 21 and 22). The front wall 402, the rear wall 404, and the periphery side wall 406 are connected to each other to provide an airtight chamber inside the impingement box 400, except for the portions of the box air intake 408 and the cooling holes 79.

[0065] Figure 19 is a schematic cross-sectional view of a stator vane according to the eighth embodiment. Figure 20 is a partially enlarged view of Figure 19. As shown in Figure 18, the impingement box 400 includes a mounting portion 410 fixed to the shroud end. The impingement box 400 is connected to and fixed to the shroud end 74 only at the mounting portion 410. The rest of the impingement box 400 is not connected to the shroud end 74 or the side wall of the airfoil 51, and the rest of the impingement box 400, excluding the mounting portion 410, is spaced apart from the shroud end 74 and the side wall of the airfoil 51. For example, the surrounding side wall 406, excluding the mounting portion 410, is spaced apart from the shroud end 74, creating a gap between it and the shroud end 74. Also, the surrounding side wall 406 is spaced apart from the side wall of the airfoil 51, creating a gap between it and the side wall of the airfoil 51.

[0066] As shown in Figure 19, the lateral shroud 70 comprises a dorsal impingement box 400N and a ventral impingement box 400P. N The dorsal shroud end channel outlet 172 N It is connected to the ventral impingement box 400. P The ventral shroud end channel outlet 172 P It is connected to the dorsal impingement box 400. N Let's explain using this as an example. Ventral impingement box 400 P Since it has a similar structure, a detailed explanation will be omitted. Figure 20 shows the dorsal impingement box 400. N (i) dorsal shroud end 74 N (ii) Front shroud end 74 L (iii) The gap GA between the side wall of the airfoil 51 and (iii) the dorsal impingement box 400. N and dorsal shroud end 74 N The gap GA between the mounting portion 410 and the dorsal impingement box 400 is provided on both sides of the mounting portion 410. NIt is provided to surround it. As shown in Figure 19, the gap GA is also the dorsal impingement box 400 N and rear shroud end 74 T It is provided between the two. The gap GA is also the dorsal impingement box 400 N and shroud end channel inlet 171 T It is provided between them. The cover plate 430 is provided so as to cover the mounting portion 410.

[0067] The structure and arrangement of the gap GA are not limited to this embodiment. The mounting portion 410 can be attached to other parts of the impingement box 400, for example, the front shroud end 74 L It may be moved to a portion corresponding to another shroud end, such as the modified mounting portion 410. In such a modification, a gap GA is provided so as to surround the impingement box 400 other than this modified mounting portion 410. Alternatively, multiple mounting portions may be provided on the impingement box 400 and fixed to the shroud end 74 or airfoil 51. In such a structure, multiple gaps would be provided between adjacent mounting portions.

[0068] Figure 21 is a magnified view of a portion of the impingement box. Figure 21 illustrates the portion of the impingement box 400 around the mounting portion 410. The impingement box 400 includes a box air intake 408. The impingement box 400 further includes a U-shaped attachment 412 surrounding the box air intake 408. The attachment 412 protrudes from the surrounding side wall 406.

[0069] Figure 22 is a cross-sectional view along the line XXII-XXII in Figure 20. As shown in Figure 22, the end face of attachment 412 is the dorsal shroud end 74 N It is abutted against the inner side surface. Attachment 412 is at the dorsal shroud end 74 N It is fixed to the inner side surface, for example, by welding. The connection between the impingement box 400 and the shroud end 74 is between the attachment 412 and the rear shroud end 74N It is limited to the connection between the two. With this structure, the impingement box 400 is cantilevered by this connection. Spacers 420 are provided on the outer surface of the radial inner wall 81 to provide support to the rear wall 404 of the impingement box 400, facilitating the positioning of the impingement box 400 and maintaining the space between the radial inner wall 81 and the rear wall 404 of the shroud body 72. Multiple spacers 420 may be provided on the radial inner wall 81.

[0070] As shown in Figure 22, the box air intake 408 is connected to the rear shroud end flow channel outlet 172 N It is connected to the dorsal shroud end channel 75 N Cooling air flowing inside is directed to the rear shroud end flow outlet 172 N It is then discharged into the box air intake 408.

[0071] Figures 23A and 23B are schematic cross-sectional views of the stator vane according to the eighth embodiment, respectively. As shown in Figure 23A, the end face of the attachment 412 is connected to the dorsal shroud end 74 N For example, after being attached and fixed by welding, the rear shroud end flow channel outlet 172 N This opens up. Therefore, as shown in Figure 23B, the cover plate 430 is moved to the rear shroud end flow channel outlet 172 N A connection is provided between the box air intake 408 and the rear shroud end flow channel outlet 172 N The cover plate 430 provides an airtight structure, airtight chamber, or airtight passage extending between the box air intake 408 and the rear shroud end 74 N The attachment is attached, for example, by welding, to the surface (top surface and inclined surface) of the attachment 412 and the surface of the front wall 402.

[0072] Next, the manufacturing method for the turbine stator blade shroud will be described. Figure 24 is a flowchart illustrating the manufacturing method for the turbine stator blade shroud. As shown in Figure 24, in step S502, the impingement box 400 is prepared. Next, in step S504, the impingement box 400 is inserted into the gap CA of the shroud body 72 such that the rear wall 404 faces the radially outer surface of the radially inner wall 81. Next, in step S506, the impingement box 400 is welded to the shroud end 74 at the mounting portion 410, and the rest of the impingement box 400 is spaced apart from the shroud end 74 and the side wall of the airfoil 51, providing a cantilever structure in which the gap GA surrounds the impingement box 400 other than the mounting portion 410. More specifically, the attachment 412 is attached to the rear shroud end 74 N It is welded to it. In these steps, the rear wall 404 may be supported by the spacer 420. Next, in step S508, the cover plate 430 is attached to the rear shroud end flow outlet 172 N It covers the flow path from the box air intake 408.

[0073] Figure 25 is a schematic cross-sectional view of a stator vane according to the eighth embodiment. Figure 25 shows the dorsal shroud end flow channel outlet 172 N The flow of cooling air from the impingement box 400 into the impingement box 400 and to the outside of the impingement box 400 is described. As shown in Figure 25, the rear shroud end channel 75 N Cooling air flowing inside passes through the box air intake 408 to the rear shroud end flow outlet 172 NThe air flows from there into the impingement box 400. Next, the cooling air is injected from the cooling holes 79 toward the radial outer surface of the radial inner wall 81, impingement cooling the radial outer surface of the radial inner wall 81, and then discharged to the outside through the gap GA and returned to the inside of the combustor casing. The gap GA connects the inner region (cavity) of space S to the outer space located opposite the front wall 402 as seen from space S. In Figure 25, the gap GA is shown, for example, between the surrounding side wall 406 and the side wall of the airfoil 51.

[0074] According to this embodiment, the impingement box 400 is inserted into the gap in the shroud body 72 and the impingement box 400 is welded at the mounting portion, thereby forming an inner region and an outer region of the space S in the shroud body 72. Therefore, by supporting the impingement box at the end of the shroud, it becomes possible to easily provide a shroud with a cooling structure having an effectively sealed void. Furthermore, after impingement cooling of the radial inner wall 81, the cooling air is discharged and collected through the gap GA. Therefore, it becomes possible to eliminate the need to provide a separate structure (flow channel) for discharging and collecting the cooling air after impingement cooling.

[0075] According to the inventor's research, during turbine operation, a temperature difference occurs between the shroud end 74 and the impingement box 400, which can generate thermal stress at the connection between the two components. In this embodiment, the impingement box 400 is supported in a cantilever structure, and the gap GA surrounds the impingement box 400, so the gap GA can absorb the thermal expansion effect and reduce thermal stress.

[0076] Figure 26 is a schematic cross-sectional view of a stator vane illustrating the principle of the eighth embodiment. As shown in Figure 26, the shroud end flow path 75 N It is connected to the inside of the impingement box 400. Shroud end channel 75 facing the impingement box 400 NAssuming an example where the outlet of the shroud end channel is provided in this section, the flow of cooling air toward the impingement box 400 causes the shroud end channel 75 N A low-velocity airflow region (LFVA) occurs where the flow velocity of the internal cooling air is reduced. On the other hand, in this embodiment, as shown in Figure 22, the rear shroud end 74 N It extends diagonally, and the shroud end channel 75 N and the dorsal shroud end channel outlet 172 N Shroud end outlet channel 75 connecting to OP It includes, more specifically, the dorsal shroud end 74 N This is the shroud end 74 facing the high-temperature gas flow path of the turbine. N The opposite side wall 74 is located on the opposite side of the surface (indicated by reference numeral 81 in Figure 22). OSW and the inner side wall 74 facing the impingement box 400 ISW It is equipped with the opposite side wall 74 OSW and inner side wall 74 ISW This refers to the shroud end channel 75 N Define it internally.

[0077] Shroud end outlet channel 75 OP The shroud end channel 75 N The inlet end is connected to the rear shroud end channel outlet 172 N It comprises an outlet end connected to the shroud end outlet channel 75. OP The opposite side wall 74 OSW It is provided in the shroud end outlet channel 75. More specifically, the shroud end outlet channel 75 OP The entrance end is on the opposite side wall 74 OSW It is provided at the shroud end outlet channel 75 OP The inlet end is the shroud end outlet channel 75 OP It is provided near the virtual low velocity region (LFVA) so as to communicate with the virtual low velocity region (LFVA). Shroud end outlet channel 75 OP This structure, in which the inlet end is located near a virtual low velocity region (LFVA), can suppress the generation of a virtual low velocity region (LFVA) in the shroud end flow path.

[0078] The structure of the stator vane is not limited to this embodiment. For example, the shroud end outlet channel 75 OP The exit end is on the inner side wall 74 ISW It may be provided in [location].

[0079] Next, a ninth embodiment will be described. Figure 27 is a schematic cross-sectional view of the ninth embodiment. Figure 27 illustrates a portion of the shroud corresponding to Figure 22. Figure 28 is a schematic bottom view of the ninth embodiment. Figure 28 schematically illustrates the bottom view of the rear wall 404 of the impingement box 400. As shown in Figure 27, the impingement box 400 includes a rear wall 404 facing the cooling surface of the radial inner wall 81. As shown in Figures 27 and 28, the rear wall 404 includes a thickened portion 440 around the mounting portion 410. The thickened portion 440 has a thickness T1 that is greater than the thickness T2 of the rest of the rear wall 404. This structure with the thickened portion 440 suppresses thermal stress and thermal deformation in the mounting portion 410 and prevents low-cycle fatigue.

[0080] The thickened portion 440 of the rear wall 404 is provided with cooling holes 79. The cooling holes 79 provided in the thickened portion 440 may have a larger diameter than the cooling holes 79 provided in other parts of the rear wall 404. For example, the diameter of the cooling holes 79 may be set in advance so that the ratio of thickness T to diameter D is constant.

[0081] As shown in Figure 27, the impingement box 400 includes a support structure 450 inside, such as a support pin. The impingement box 400 has a space between the front wall 402 and the rear wall 404. The support pin 450 is a columnar structure fixed at one end to the front wall 402 and at the other end to the rear wall 404. Multiple support pins 450 may be provided inside the impingement box 400, or multiple support pins 450 may be provided at regular intervals.

[0082] According to the inventor's research, a pressure difference occurs inside and outside the impingement box 400 during turbine operation, which can cause the impingement box 400 to expand. By providing support pins 450 that connect and hold the front wall 402 to the rear wall 404, it becomes possible to suppress the expansion of the impingement box 400 that separates the front wall 402 from the rear wall 404.

[0083] The structure of the stator vanes is not limited to this embodiment. For example, Figure 29 is a schematic cross-sectional view of a modified example of the ninth embodiment. In this embodiment, the impingement box 400 includes a support structure 460 which also functions similarly to the discharge pipe 83. The support pin 460 is a columnar structure fixed at one end to the front wall 402 and at the other end to the rear wall 404. The support pin 460 has a hollow passage inside which it penetrates the front wall 402 and the impingement plate (rear wall 404), connecting the inner region and the outer space to collect and discharge the cooling air after impingement cooling.

[0084] Although the above embodiment has been described using the outer shroud 70 as an example, this embodiment is also applicable to the inner shroud 60. This disclosure is not limited to the above embodiment and can be implemented in various embodiments. For better understanding, specific embodiments have been described with reference to the drawings, but the above description is presented as an example and does not limit the scope of the invention as defined by the accompanying claims. The scope of the invention should be determined by the accompanying claims. Those skilled in the art can make various modifications without departing from the scope of the invention, and the accompanying claims cover such modifications. [Explanation of Symbols]

[0085] 10 Gas Turbines 20 Turbines 22 Turbine Casing 24 Rotor Shaft 26 Turbine rotor Ar axis 30 Combustors 50 Stationary Wings 51. Stator wing body (airfoil) 51 P bulkhead 52 Front edge 53 Trailing edge 54 Dorsal aspect 55 Ventral aspect 56 Intake Manifold 57 Outside air channel 58 Air intake 59 Hole 141, 142, 143 Air Channels 151, 152, 153 Inserts 161, 162, 163 Internal air channels 191, 192, 193, 194, 195 Air channels 154 Airfoil Cooling Structure 164 Pinfin 60 Inner Shroud 70 Outer shroud 62, 72 Shroud body 63, 73 Impingement Plates 64, 74 Shroud ends 65, 75 Shroud end channel S hollow space 171 Shroud end channel inlet 172 Shroud end flow outlet 175 Turbulator 76 Peripheral wall 78 Gas Pass Surface 79 Impingement cooling holes 81 Radial inner wall 82 Radial exterior wall 83 Discharge pipe 181 Shroud end channel inlet 182 Shroud end channel outlet 300, 400 impingement boxes 302, 402 front wall 304, 404 rear wall 306, 406 Surrounding side walls 308, 408 Box Air Intake 320, 420 spacers 410 Mounting part 412 Attachments 430 Cover Plate 440 Thick part 450, 460 support pins

Claims

1. It is a shroud for a turbine stator blade, A shroud body having a first wall having a gas path surface facing the high-temperature gas flow path of the turbine and a cooling surface facing the opposite side of the high-temperature gas flow path, A shroud end is provided around the shroud body so as to surround the shroud body and has a shroud end flow path inside, The system comprises an impingement box provided at a distance from the cooling surface of the first wall so as to be opposite to the cooling surface of the first wall, The impingement box includes a cooling air intake for introducing cooling air from the shroud end passage into the interior of the impingement box, an impingement cooling hole for injecting the introduced cooling air onto the cooling surface of the first wall to cool the cooling surface of the first wall, and a passage for guiding the cooling air injected onto the cooling surface of the first wall to an outer space located on the opposite side of the first wall as viewed from the impingement box. A shroud for the turbine stator blades, equipped with this feature.

2. The turbine stator blade shroud according to claim 1, wherein the periphery of the impingement box is provided with a mounting portion fixed to the end of the shroud.

3. The shroud for a turbine stator blade according to claim 1, further comprising a cooling air collection channel configured to collect the cooling air injected to cool the cooling surface of the first wall.

4. The turbine stator vane shroud according to claim 2, wherein the area around the impingement box includes a non-mounting portion having a gap between the shroud end and the area around the impingement box.

5. The shroud includes a cooling air collection channel for collecting the cooling air injected to cool the cooling surface of the first wall, The shroud of the turbine stator blade according to claim 4, wherein the gap constitutes the cooling air collection channel.

6. The turbine stator blade shroud according to claim 5, wherein the gap is in communication with the space between the cooling surface of the impingement box and the first wall.

7. The turbine stator blade shroud according to claim 2, wherein the impingement box is cantilevered by the mounting portion fixed to the end of the shroud.

8. The shroud for a turbine stator blade according to claim 1, wherein the shroud body comprises a gap defined by the first wall and the shroud end, and the impingement box is inserted into the gap and partially fixed to the shroud end.

9. It is a shroud for a turbine stator blade, A shroud body having a parallelogram shape and a first wall having a gas path surface facing the high-temperature gas flow path of the turbine and a cooling surface facing the opposite side of the high-temperature gas flow path, A shroud end is provided around the shroud body so as to surround the shroud body and has a shroud end flow path inside, The system comprises an impingement box provided at a distance from the cooling surface of the first wall so as to be opposite to the cooling surface of the first wall, The shroud end channel is provided along the side of the parallelogram shape, The impingement box is a shroud for a turbine stator blade, comprising a cooling air intake for introducing cooling air from the shroud end passage into the interior of the impingement box, and an impingement cooling hole for injecting the introduced cooling air onto the cooling surface of the first wall to cool the cooling surface of the first wall.

10. The shroud body has a gap defined by the first wall and the shroud end, and the impingement box is inserted into the gap. The shroud end is, A side wall, the opposite side wall located on the side of the shroud end facing the high-temperature gas flow path of the turbine, The inner side wall facing the impingement box, wherein the opposite side wall and the inner side wall define the shroud end flow path, The shroud end channel is connected to the cooling air intake of the impingement box, and the shroud end outlet channel is configured to introduce the cooling air flowing inside the shroud end channel into the cooling air intake of the impingement box, The shroud end outlet passage is provided within the opposite side wall of the shroud end, according to claim 9, for the shroud of a turbine stator blade.

11. The shroud for a turbine stator blade according to claim 10, wherein the shroud end outlet passage includes an inlet end connected to the shroud end passage, and the inlet end of the shroud end outlet passage is provided within the opposite side wall of the shroud end.

12. The shroud for a turbine stator blade according to claim 9, wherein the mounting portion comprises an attachment configured to protrude from the side of the impingement box, and the attachment is fixed to the end of the shroud.

13. The shroud for a turbine stator blade according to claim 12, wherein the attachment is configured to surround the cooling air intake.

14. The turbine stator vane shroud according to claim 9, wherein the impingement box comprises a cover that covers the opening of the cooling air intake.

15. The shroud end channel is provided along two adjacent sides of the parallelogram shape, as described in claim 9 for the turbine stator blade shroud.

16. It is a shroud for a turbine stator blade, A shroud body having a first wall having a gas path surface facing the high-temperature gas flow path of the turbine and a cooling surface facing the opposite side of the high-temperature gas flow path, A shroud end is provided around the shroud body so as to surround the shroud body and has a shroud end flow path inside, The system comprises an impingement box provided at a distance from the cooling surface of the first wall so as to be opposite to the cooling surface of the first wall, The impingement box includes a cooling air intake for introducing cooling air from the shroud end passage into the interior of the impingement box, and an impingement cooling hole for injecting the introduced cooling air onto the cooling surface of the first wall to cool the cooling surface of the first wall. The area around the impingement box is provided with mounting portions fixed to the ends of the shroud, The impingement box includes a rear wall facing the cooling surface of the first wall, The rear wall is a shroud for a turbine stator blade, having a thickened portion around the mounting portion, the thickened portion having a greater thickness than the rest of the rear wall.

17. It is a shroud for a turbine stator blade, A shroud body having a first wall having a gas path surface facing the high-temperature gas flow path of the turbine and a cooling surface facing the opposite side of the high-temperature gas flow path, A shroud end is provided around the shroud body so as to surround the shroud body and has a shroud end flow path inside, The system comprises an impingement box provided at a distance from the cooling surface of the first wall so as to be opposite to the cooling surface of the first wall, The impingement box includes a cooling air intake for introducing cooling air from the shroud end passage into the interior of the impingement box, and an impingement cooling hole for injecting the introduced cooling air onto the cooling surface of the first wall to cool the cooling surface of the first wall. The area around the impingement box is provided with mounting portions fixed to the ends of the shroud, The impingement box comprises a rear wall facing the cooling surface of the first wall, and a front wall located on the opposite side of the rear wall and having a void between it and the rear wall. The impingement box further comprises a shroud for a turbine stator blade, with one end fixed to the front wall and the other end fixed to the rear wall.

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