Turbine stator blades, turbine stator blade assemblies, and gas turbines

Abstract

To provide turbine stator blades that are easy to manufacture and offer effective cooling. [Solution] The shroud portion includes a cavity capable of receiving cooling fluid from the space opposite to the blade portion, sandwiching the shroud portion in the blade height direction; a peripheral wall portion provided so as to surround the cavity when viewed from the blade height direction and having a surface that forms the inner wall surface of the cavity; and a flange portion for connecting the turbine stator blade and the turbine stator blade adjacent to the turbine stator blade. The peripheral wall portion includes a ventral peripheral wall portion and a dorsal peripheral wall portion. The flange portion is provided so as to protrude from one of the ventral peripheral wall portion or the dorsal peripheral wall portion in the blade height direction, and includes an introduction hole having an opening on the side of the ventral peripheral wall portion or the dorsal peripheral wall portion that faces the opposite side of the gas pass surface in the blade height direction; and a first cooling hole having an opening on the front end surface, rear end surface or the gas pass surface of the shroud portion and communicating with the introduction hole.

Description

Technical Field

[0001] The present disclosure relates to a turbine stator blade, a turbine stator blade assembly, and a gas turbine.

Background Art

[0002] In a gas turbine, a stator blade assembly in which a pair of circumferentially arranged turbine stator blades are bolted together may be used. A shroud provided at the end of the stator blade in the radial direction of the gas turbine usually has a cooling structure such as an impingement cooling hole or a trailing edge cooling hole to cool the shroud. However, since the end face on the bolt connection side of the shroud is in close contact with the end face of the shroud of the other turbine stator blade configuring the stator blade assembly, and since this end face is far from the above-described cooling structure, the region near this end face is difficult to be cooled and tends to become high temperature. Therefore, a configuration for cooling the region near the end face on the bolt connection side of the turbine stator blade shroud has been proposed.

[0003] For example, Patent Document 1 describes providing cooling holes that incline so as to approach the end face of the shroud of the other turbine stator blade toward the rear (downstream side) in the vicinity of the end face on the bolt connection side at the rear end of the shroud of a pair of turbine stator blades.

[0004] Also, for example, Patent Document 2 describes providing long cooling holes (passages) that extend along the end face over most of the region in the front-rear direction (turbine axis direction) of the shroud in the vicinity of the end face on the bolt connection side of the shroud of a pair of turbine stator blades.

Prior Art Documents

Patent Documents

[0005]

Patent Document 1

Patent Document 2

Summary of the Invention

[0006] However, even when cooling holes are provided at the rear end of the shroud, as described in Patent Document 1, that are inclined to approach the end face of the shroud of the other turbine stator blade as they move towards the rear (downstream), the area near the end face of the bolted connection side of the shroud may not be sufficiently cooled. Furthermore, machining long cooling holes that extend along the front-to-back direction of the shroud, as described in Patent Document 2, is not easy and can lead to increased manufacturing costs and lead times.

[0007] In view of the above circumstances, at least one embodiment of the present invention aims to provide a turbine stator blade, a turbine stator blade assembly, and a gas turbine that are easy to manufacture and capable of effective cooling. [Means for solving the problem]

[0008] A turbine stator blade according to at least one embodiment of the present invention is A wing portion having ventral and dorsal surfaces that extend along the wing height direction and between the leading and trailing edges, A shroud portion connected to the blade portion and having a gas path surface facing the combustion gas passage, A turbine stator blade equipped with, The aforementioned shroud portion is, A cavity capable of receiving cooling fluid from the space opposite to the blade portion, sandwiching the shroud portion in the blade height direction, A peripheral wall portion is provided so as to surround the cavity when viewed from the wing height direction and has a surface that forms the inner wall surface of the cavity, The turbine stator blade and a flange portion having bolt holes through which bolts for connecting the turbine stator blade to an adjacent turbine stator blade are inserted, The aforementioned peripheral wall portion is A ventral peripheral wall portion located on the ventral end side of the shroud portion and extending along the chord direction of the wing portion, A rear peripheral wall portion located on the rear end side of the shroud portion and extending along the direction of the cord, Includes, The flange portion is provided so as to protrude from either the ventral circumferential wall portion or the dorsal circumferential wall portion in the direction of the wing height. An introduction hole having an opening on the side of the ventral or dorsal circumferential wall that faces away from the gas pass surface in the wing height direction, The first cooling hole has an opening on the front end surface, rear end surface, or gas pass surface of the shroud portion and communicates with the introduction hole, It is equipped with.

[0009] Furthermore, a turbine stator blade assembly according to at least one embodiment of the present invention is The turbine comprises a ventral stator vane and a dorsal stator vane, which are arranged adjacent to each other in the circumferential direction of the turbine and are connected to each other by bolts. At least one of the ventral stator vane and the dorsal stator vane is the turbine stator vane described above.

[0010] Furthermore, a gas turbine according to at least one embodiment of the present invention is A compressor for compressing air, A combustor for burning fuel using compressed air from the aforementioned compressor, A turbine configured to be driven by combustion gas from the aforementioned combustor, Equipped with, The turbine includes the turbine stator blade assembly described above. [Effects of the Invention]

[0011] According to at least one embodiment of the present invention, turbine stator blades, turbine stator blade assemblies, and gas turbines are provided that are easy to manufacture and capable of effective cooling. [Brief explanation of the drawing]

[0012] [Figure 1] This is a schematic diagram of a gas turbine according to one embodiment. [Figure 2]It is a schematic diagram showing an enlarged part of the gas turbine 1 shown in FIG. 1. [Figure 3] It is a schematic perspective view showing a stator blade (turbine stator blade) and a turbine stator blade assembly according to an embodiment. [Figure 4] It is a schematic cross-sectional view of a part of the outer shroud of a turbine stator blade assembly according to an embodiment. [Figure 5] It is a cross-sectional view taken along line A-A of the stator blade shown in FIG. 4. [Figure 6] It is a cross-sectional view taken along line B-B of the stator blade shown in FIG. 4. [Figure 7] It is a schematic cross-sectional view of a part of the outer shroud of a turbine stator blade assembly according to an embodiment. [Figure 8] It is a schematic cross-sectional view of a part of the outer shroud of a turbine stator blade assembly according to an embodiment.

Mode for Carrying Out the Invention

[0013] Hereinafter, some embodiments of the present invention will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of the components described as embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0014] (Configuration of Gas Turbine) FIG. 1 is a schematic configuration diagram of a gas turbine to which a turbine stator blade and a turbine stator blade assembly according to an embodiment are applied. FIG. 2 is a schematic diagram showing an enlarged part of the gas turbine 1 shown in FIG. 1.

[0015] As shown in FIG. 1, the gas turbine 1 includes a compressor 2 for generating compressed air, a combustor 4 for generating combustion gas using the compressed air and fuel, and a turbine 6 configured to be rotationally driven by the combustion gas. In the case of the gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6.

[0016] The compressor 2 includes a plurality of stationary vanes 16 fixed to the compressor casing 10 side, and a plurality of rotor blades 18 mounted on the rotor 8 so as to be alternately arranged with respect to the stationary vanes 16. Air taken in from the air intake 12 is supplied to the compressor 2, and this air is compressed by passing through the plurality of stationary vanes 16 and the plurality of rotor blades 18 to become high-temperature, high-pressure compressed air.

[0017] The combustor 4 is supplied with fuel and compressed air generated by the compressor 2. In the combustor 4, the fuel and compressed air are mixed and burned to produce combustion gas, which is the working fluid for the turbine 6. As shown in Figure 1, multiple combustors 4 may be arranged in the combustor casing 20 along the circumferential direction with the rotor as the center.

[0018] As shown in Figures 1 and 2, the turbine 6 has a combustion gas passage 28 formed within the turbine casing 22, and includes a plurality of stator blades 24 (turbine stator blades) and rotor blades 26 provided in the combustion gas passage 28. The stator blades 24 are fixed to the turbine casing 22 side, and a plurality of stator blades 24 arranged along the circumferential direction of the rotor 8 constitute a stator blade row. The rotor blades 26 are mounted on the rotor 8, and a plurality of rotor blades 26 arranged along the circumferential direction of the rotor 8 constitute a rotor blade row. The stator blade row and the rotor blade row are arranged alternately in the axial direction of the rotor 8.

[0019] In the turbine 6, the combustion gas G (see Figure 2) from the combustor 4 flows into the combustion gas passage 28 and passes through multiple stationary blades 24 and multiple rotor blades 26, thereby driving the rotor 8 to rotate. This drives a generator connected to the rotor 8, generating electricity. After driving the turbine 6, the combustion gas is discharged to the outside through the exhaust chamber 30.

[0020] (Configuration of turbine stator blades and turbine stator blade assembly) Figure 3 is a schematic perspective view showing a stator blade 24 (turbine stator blade) and turbine stator blade assembly 100 according to one embodiment.

[0021] In some embodiments, as shown in Figure 3, the turbine 6 includes a stator vane assembly 100 in which a pair of adjacent stator vanes 24 in the circumferential direction of the turbine 6 are joined by bolts 96. The pair of adjacent stator vanes 24 in the circumferential direction includes a dorsal stator vane 24A located on the dorsal side (i.e., the side facing the dorsal surface 44 of the blade portion 40, described later) and a ventral stator vane 24B located on the ventral side (i.e., the side facing the ventral surface 43 of the blade portion 40, described later). The stator vane row of the turbine 6 may consist of a plurality of stator vane assemblies 100 arranged along the circumferential direction.

[0022] As shown in Figures 2 and 3, each of the stator blades 24 constituting the stator blade assembly 100 comprises a blade portion 40 extending along the blade height direction, and an inner shroud 50 and an outer shroud 60 connected to the ends of the blade portion 40 in the blade height direction. Here, the blade height direction of the stator blade 24 corresponds to the radial direction of the turbine rotor on which the stator blade 24 is installed.

[0023] The wing section 40 has a leading edge 41 and a trailing edge 42 extending along the wing height direction, and a ventral surface (pressure surface) 43 and a dorsal surface (negative pressure surface) 44 extending between the leading edge 41 and the trailing edge 42. The ventral surface 43 and the dorsal surface 44 are connected to each other at the leading edge 41 and the trailing edge 42. Typically, in a cross section perpendicular to the wing height direction, the ventral surface 43 is concave overall, and the dorsal surface 44 is convex overall. A cooling passage 45 may be provided inside the wing section 40 to which a cooling fluid is supplied. As shown in Figure 3, the cooling passage 45 may form a meandering passage (serpentine passage). A cooling fluid A (e.g., air) may be supplied to the cooling passage 45 through an inlet opening 46.

[0024] The inner shroud 50 is connected to the inner end of the blade portion 40 in the radial direction of the turbine 6 and has a gas path surface 52 facing the combustion gas passage 28 of the turbine 6. On the side of the inner shroud 50 opposite to the blade portion 40 in the blade height direction, a seal ring retaining ring 51 (see Figure 2) for holding a seal ring (not shown) is provided. The inner shroud 50 may have engaging portions 94, 95 that engage with the seal ring retaining ring 51. On the side of the inner shroud 50 opposite to the blade portion 40 in the blade height direction, an inner space 32 (see Figure 2) is formed. The inner space 32 may be at least partially defined by the inner shroud 50 and the seal ring retaining ring 51. The inner space 32 may be supplied with a cooling fluid for cooling the stator blade 24, or a sealing fluid for suppressing the intrusion of combustion gas from the combustion gas passage 28 into the inner space 32.

[0025] The outer shroud 60 is connected to the outer end of the blade 40 in the radial direction of the turbine 6 and has a gas path surface 61 facing the combustion gas passage 28 of the turbine 6. The outer shroud 60 may be supported by the turbine casing 22 via a heat shield ring 23, together with a segmented ring 27 provided radially outward of the rotor blade 26 adjacent to the stator blade 24. The outer shroud 60 may have engaging portions 92, 93 that engage with the heat shield ring 23. An outer space 34 (see Figure 2) is formed on the side of the outer shroud 60 opposite to the blade 40 in the blade height direction. The outer space 34 may be at least partially defined by the outer shroud 60. Cooling fluid for cooling the stator blade 24 may be supplied to the outer space 34.

[0026] Furthermore, the outer space 34 and the inner space 32 described above may be in communication with each other via a tube or the like that extends along the wing height direction so as to penetrate the wing portion 40, and the cooling fluid supplied to the outer space 34 may be supplied to the inner space 32 via the tube or the like and function as a cooling fluid or sealing fluid.

[0027] Figure 4 is a schematic cross-sectional view of a portion of the outer shroud 60 of a turbine stator blade assembly 100 according to one embodiment. Figure 5 is a cross-sectional view of the stator blade 24 shown in Figure 4 along line AA, and Figure 6 is a cross-sectional view of the stator blade 24 shown in Figure 4 along line BB. Figures 7 and 8 are schematic cross-sectional views of a portion of the outer shroud 60 of a turbine stator blade assembly 100 according to one embodiment (an embodiment different from that in Figure 4), respectively.

[0028] In the following description, the configuration of the outer shroud 60 will be explained, but in some embodiments of the stator vane 24, the inner shroud 50 may have the configuration described below, or both the outer shroud 60 and the inner shroud 50 may have the configuration described below.

[0029] As shown in Figures 3, 4, 7, and 8, the outer shroud 60 (shroud portion) of the stationary blade 24 (24A, 24B) according to some embodiments has a shape that is generally rectangular or parallelogram when viewed from the radial direction, and has a front end surface 62 and a rear end surface 64 which are the axial ends of the turbine 6 (or the chord direction of the blade portion 40), and a ventral end surface 66 and a dorsal end surface 68 which are the circumferential ends of the turbine 6.

[0030] As shown in Figures 3 to 8, in some embodiments, the outer shroud 60 includes a cavity 70 capable of receiving cooling fluid A from the space on the opposite side of the blade portion 40 (the outer space 34 in the case of the outer shroud 60) in the blade height direction, and a peripheral wall portion 74 provided so as to surround the cavity 70 when viewed from the blade height direction.

[0031] In the illustrated embodiment, the outer shroud 60 is recessed from the surface opposite to the gas path surface 61 of the outer shroud 60 and includes a recess having a bottom surface 71 and inner wall surfaces 72f, 72p, 72r, and 72s. The cavity 70 is defined by this recess and an impingement plate 90 covering the recess. The impingement plate 90 has a plurality of impingement holes 91, and the outer shroud 60 is cooled when the cooling fluid supplied to the outer space 34 collides with the bottom surface 71 of the cavity 70 through the impingement holes 91. The cavity 70 may be provided to extend along a plane including the axial and circumferential directions of the turbine 6.

[0032] The inner wall surfaces 72f, 72p, 72r, and 72s of the cavity 70 may be formed by the circumferential wall portion 74. In the illustrated embodiment, the circumferential wall portion 74 includes a ventral circumferential wall portion 74p located on the ventral end side of the outer shroud 60 and extending along the cord direction, and a dorsal circumferential wall portion 74s located on the dorsal end side of the outer shroud 60 and extending along the cord direction. In the illustrated embodiment, the circumferential wall portion 74 also includes a front circumferential wall portion 74f and a rear circumferential wall portion 74r located on the front and rear ends of the outer shroud 60, respectively, and extending along the circumferential direction of the turbine 6. The ventral circumferential wall portion 74p, the dorsal circumferential wall portion 74s, the front circumferential wall portion 74f, and the rear circumferential wall portion 74r each have surfaces that form the inner wall surfaces 72p, 72s, 72f, and 72r.

[0033] In the illustrated embodiment, the outer shroud 60 includes flange portions 78p and 78s that protrude in the wing height direction from the ventral circumferential wall portion 74p and the dorsal circumferential wall portion 74s. The flange portions 78p and 78s extend only to a portion of the area of ​​the outer shroud 60 in the chord direction. It may be provided.

[0034] Of the flange portions 78p and 78s, the one closer to the adjacent stator blade 24 constituting the turbine stator blade assembly 100 is provided with a bolt hole 79 through which a bolt 96 (see Figure 2) for connecting these stator blades 24 is inserted. Specifically, bolt holes 79 are provided in the flange portion 78p that protrudes in the blade height direction from the ventral peripheral wall portion 74p of the dorsal stator blade 24A, and in the flange portion 78s that protrudes in the blade height direction from the dorsal peripheral wall portion 74s of the ventral stator blade 24B. The dorsal stator blade 24A and the ventral stator blade 24B are connected to each other by screwing the bolt 96 and nut 97 through these bolt holes 79. Note that the straight line L1 in Figures 4, 7, and 8 represents the central axis of the bolt 96.

[0035] In some embodiments, the stator vane 24 includes an inlet 84 and a first cooling hole 86 provided in the outer shroud 60. The inlet 84 has an opening 85 on the side of the bolt-connected portion of either the ventral circumferential wall portion 74p or the dorsal circumferential wall portion 74s (i.e., the ventral circumferential wall portion 74p of the dorsal stator vane 24A, or the dorsal circumferential wall portion 74s of the ventral stator vane 24B) that faces away from the gas pass surface 61 in the vane height direction. The first cooling hole 86 has an opening 87 on the front end surface 62, the rear end surface 64, or the gas pass surface 61 of the outer shroud 60.

[0036] The inlet holes 84 may extend along the blade height direction. Furthermore, the inlet holes 84 do not penetrate to the gas path surface 61, but extend over a portion of the outer shroud 60 in the blade height direction. The first cooling holes 86 may extend along the cord direction.

[0037] In the exemplary embodiment shown in Figure 4, the introduction hole 84 has an opening 85 on the ventral peripheral wall portion 74p of the dorsal stator vane 24A, on the surface 75 facing away from the gas pass surface 61 in the vane height direction. The first cooling hole 86 has an opening 87 on the rear end surface 64 of the outer shroud 60.

[0038] In the exemplary embodiment shown in Figure 7, the introduction hole 84 has an opening 85 on the ventral peripheral wall portion 74p of the dorsal stator vane 24A, on the surface 75 facing away from the gas pass surface 61 in the vane height direction. The first cooling hole 86 has an opening 87 on the front end surface 62 of the outer shroud 60.

[0039] In the exemplary embodiment shown in Figure 8, the inlet holes 84 are provided on both the dorsal stator vane 24A and the ventral stator vane 24B. The inlet hole 84 provided on the dorsal stator vane 24A has an opening 85 on the ventral peripheral wall portion 74p of the dorsal stator vane 24A, on the surface 75 facing away from the gas pass surface 61 in the wing height direction, and the first cooling hole 86 has an opening 87 on the front end surface 62 of the outer shroud 60. The inlet hole 84 provided on the ventral stator vane 24B has an opening 85 on the ventral peripheral wall portion 74s of the ventral stator vane 24B, on the surface 75 facing away from the gas pass surface 61 in the wing height direction, and the first cooling hole 86 has an opening 87 on the rear end surface 64 of the outer shroud 60.

[0040] In some embodiments, the introduction holes 84 and the first cooling holes 86 may be provided only on the ventral stator vane 24B of the dorsal stator vane 24A and the ventral stator vane 24B.

[0041] In the above embodiment, an introduction hole 84 is provided in the outer shroud 60 (shroud portion), which has an opening 85 on the surface 75 facing away from the gas pass surface 61, located at the end on the bolt-connection side of the ventral circumferential wall portion 74p or the dorsal circumferential wall portion 74s, and a first cooling hole 86 is provided which communicates with the introduction hole 84 and has an opening 87 on the front end surface 62, the rear end surface 64, or the gas pass surface 61 of the shroud portion. Therefore, the cooling fluid in the outer space 34 on the opposite side of the wing portion 40 across the outer shroud 60 can be supplied to the first cooling hole 86 via the introduction hole 84 without going through the cavity 70 for impingement cooling. That is, since a relatively low-temperature cooling fluid that is not used for impingement cooling is supplied to the first cooling hole 86, the area of ​​the outer shroud 60 near the end surface on the bolt-connection side (the ventral end surface 66 of the dorsal stator vane 24A in Figure 4), which tends to become hot, can be effectively cooled. Furthermore, since the introduction holes 84 and the first cooling holes 86 are shorter than long cooling holes that extend over most of the front-rear direction (or the chord direction of the blade portion 40) (see, for example, Patent Document 2), they can be easily machined, for example, by electrical discharge machining. Therefore, according to the above embodiment, the stator vane 24 is easy to manufacture and can be effectively cooled.

[0042] As shown in Figures 4 to 8, in some embodiments, the stator vane 24 is provided with a second cooling hole 80 that communicates with the cavity 70 and has an opening in the front end face 62 or rear end face 64 of the outer shroud 60 (shroud portion). Typically, a plurality of such second cooling holes 80 are provided.

[0043] In the exemplary embodiments shown in Figures 4 and 8, each of the plurality of second cooling holes 80 has an opening 81 provided in the inner wall surface 72r of the cavity 70 and an opening 82 provided in the rear end surface 64 of the outer shroud 60.

[0044] In the exemplary embodiment shown in Figure 7, each of the plurality of second cooling holes 80 has an opening 81 provided in the inner wall surface 72f of the cavity 70 and an opening 82 provided in the front end surface 62 of the outer shroud 60.

[0045] According to the above-described embodiment, a second cooling hole 80 is provided that communicates with the cavity 70 and has an opening 82 on the front end surface 62 or rear end surface 64 of the outer shroud 60 (shroud portion). As a result, the cooling fluid in the cavity 70 is supplied to the second cooling hole 80. Therefore, the outer shroud 60 can be cooled more effectively by the cooling fluid flowing through the first cooling hole 86 and the second cooling hole 80.

[0046] As shown in Figures 4 to 8, the rear end surface 64 of the outer shroud 60 may be provided with a projection 88 that protrudes rearward. By providing this projection 88, contact between the rear end surface 64 of the outer shroud 60 and the adjacent divided ring 27 (see Figure 2) is suppressed, and the cooling fluid from the second cooling hole 80 is smoothly discharged through the opening 81.

[0047] In some embodiments, as shown in Figure 6, for example, at least a portion of the first cooling holes 86 is located closer to the gas path surface 61 than the second cooling holes 80 in the blade height direction. That is, in the case of the first cooling holes 86 provided in the outer shroud 60, in some embodiments, at least a portion of the first cooling holes 86 is located radially inward than the second cooling holes 80.

[0048] In some embodiments, as shown in Figure 6, for example, within the extension region of the second cooling hole 80 in the code direction (or axial direction), the first cooling hole 86 is located closer to the gas path surface 61 than the second cooling hole 80 in the blade height direction.

[0049] In the outer shroud 60 (shroud portion) of the stator vane 24, the area near the gas path surface 61 facing the combustion gas passage 28 tends to become hotter. In this regard, according to the above embodiment, the first cooling hole 86 provided at the bolt-connected end of the outer shroud 60 is positioned relatively close to the gas path surface 61, so that the area of ​​the outer shroud 60 that becomes particularly hot can be cooled more effectively.

[0050] In some embodiments, as shown in Figures 3 to 7, for example, the opening 85 of the introduction hole 84 and the opening 87 of the first cooling hole 86 are provided on the same side with respect to the flange portion 78p or 78s in the cord direction (or axial direction).

[0051] For example, in the dorsal stator vane 24A shown in Figure 4, the opening 85 of the introduction hole 84 and the opening 87 of the first cooling hole 86 are located behind the flange portion 78p (towards the rear end surface 64) in the cord direction.

[0052] Furthermore, in the dorsal stator vane 24A shown in Figure 7 and the dorsal stator vane 24A shown in Figure 8, for example, the opening 85 of the introduction hole 84 and the opening 87 of the first cooling hole 86 are located in front of the flange portion 78p (towards the front end surface 62) in the cord direction.

[0053] Furthermore, in the ventral stator vane 24B shown in Figure 8, for example, the opening 85 of the introduction hole 84 and the opening 87 of the first cooling hole 86 are located behind the flange portion 78s (towards the rear end surface 64) in the cord direction.

[0054] In some embodiments, the opening 85 of the introduction hole 84 and the opening 87 of the first cooling hole 86 may be provided in front of the flange portion 78s (towards the front end surface 62) in the cord direction of the ventral stator vane 24B.

[0055] In the above embodiment, since the opening 85 of the introduction hole 84 and the opening 87 of the first cooling hole 86 are located on the same side with respect to the flange portions 78s and 78p in the cord direction, the distance between the opening 85 of the introduction hole 84 and the opening 87 of the first cooling hole 86 in the cord direction is relatively short. As a result, the first cooling hole 86 does not need to be very long, making it easy to process. Thus, the manufacturing of the stator vane 24 is easy, and effective cooling of the stator vane 24 is possible.

[0056] Although not specifically shown in the figures, in some embodiments, the opening 85 of the introduction hole 84 and the opening 87 of the first cooling hole 86 may be located on both sides of the flange portion 78p or 78s in the cord direction (or axial direction). That is, the first cooling hole 86 may be provided so as to pass through the flange portion 78p or 78s in the cord direction.

[0057] In some embodiments, the opening 85 of the introduction hole 84 is located in the code direction (or axial direction) between the flange portion 78p or 78s and the front wall surface (inner wall surface 72f) or rear wall surface (inner wall surface 72r) of the cavity 70.

[0058] For example, in the dorsal stator vane 24A shown in Figure 4, the opening 85 of the introduction hole 84 is located between the flange portion 78p and the rear wall surface (inner wall surface 72r) of the cavity 70 in the cord direction.

[0059] Furthermore, in the case of the dorsal stator vane 24A shown in Figure 7 and the dorsal stator vane 24A shown in Figure 8, for example, the opening 85 of the introduction hole 84 is located between the flange portion 78p and the front wall surface (inner wall surface 72f) of the cavity 70 in the cord direction.

[0060] Furthermore, in the ventral stator vane 24B shown in Figure 8, for example, the opening 85 of the introduction hole 84 is located between the flange portion 78p and the rear side wall surface (inner wall surface 72r) of the cavity 70 in the direction of the cord.

[0061] According to the above embodiment, the opening 85 of the introduction hole 84 is located between the flange portion 78p or 78s and the front wall surface (inner wall surface 72f) or rear wall surface (inner wall surface 72r) of the cavity 70 in the cord direction. That is, since the opening 85 of the introduction hole 84 is located relatively close to the flange portion 78p or 78s in the cord direction, the length of the first cooling hole 86 can be made somewhat longer. Therefore, the manufacturing of the stator vane 24 is made easier, and more effective cooling of the stator vane 24 is possible.

[0062] In some embodiments, the diameter of the inlet hole 84 is larger than the diameter of the first cooling hole 86. Alternatively, in some embodiments, the equivalent diameter of the inlet hole 84 is larger than the equivalent diameter of the first cooling hole 86.

[0063] In the above-described embodiment, the diameter of the inlet hole 84 is larger than the diameter of the first cooling hole 86. Therefore, when machining the first cooling hole 86 in the outer shroud 60 (shroud portion) in which the inlet hole 84 is formed, it is easy to reliably connect the first cooling hole 86 to the inlet hole 84. In addition, since the pressure loss in the first cooling hole 86 is relatively small, it is easy to supply the cooling fluid to the first cooling hole 86 through the inlet hole 84. Thus, the manufacturing of the stator vane 24 is easy, and more effective cooling of the stator vane 24 is possible.

[0064] The contents described in each of the above embodiments can be understood, for example, as follows:

[0065] [1] A turbine stator blade (24) according to at least one embodiment of the present invention is A wing portion (40) having ventral surfaces (43) and dorsal surfaces (44) that extend along the wing height direction and between the leading edge (41) and trailing edge (42), A shroud portion (outer shroud 60 or inner shroud 50) is connected to the wing portion and has a gas path surface (61) facing the combustion gas passage (28), A turbine stator blade equipped with, The aforementioned shroud portion is, A cavity (70) is provided in the wing height direction, sandwiching the shroud portion, which is capable of receiving cooling fluid from the space on the opposite side of the wing portion. A peripheral wall portion (74) is provided so as to surround the cavity when viewed from the wing height direction and has a surface that forms the inner wall surface of the cavity, The turbine includes a flange portion (78p or 78s) having a bolt hole (79) through which a bolt (96) is inserted for connecting the turbine stator blade (e.g., dorsal stator blade 24A) to an adjacent turbine stator blade (e.g., ventral stator blade 24B), The aforementioned peripheral wall portion is A ventral peripheral wall portion (64p) located on the ventral end side of the shroud portion and extending along the chord direction of the wing portion, A rear peripheral wall portion (74s) located on the rear end side of the shroud portion and extending along the direction of the cord, Includes, The flange portion is provided so as to protrude from either the ventral circumferential wall portion or the dorsal circumferential wall portion in the direction of the wing height. An introduction hole (84) having an opening (85) on the side (75) of the ventral or dorsal circumferential wall portion that faces the opposite side from the gas pass surface in the wing height direction, The first cooling hole (86) has an opening (87) on the front end surface (62), rear end surface (64), or gas pass surface of the shroud portion and communicates with the introduction hole, It is equipped with.

[0066] In the configuration described in [1] above, an introduction hole is provided on the side of the ventral or dorsal circumferential wall portion of the shroud portion where a flange for connecting bolts to adjacent turbine stator blades is provided (i.e., the bolt connection side), with an opening on the side facing away from the gas pass surface, and a first cooling hole is provided which communicates with the introduction hole and has an opening on the front end surface, rear end surface, or gas pass surface of the shroud portion. Therefore, cooling fluid from the outer space on the side of the outer shroud opposite to the blade portion can be supplied to the first cooling hole via the introduction hole without going through a cavity. In other words, since a relatively low-temperature cooling fluid that is not used for cooling using a cavity is supplied to the first cooling hole, the area of ​​the outer shroud near the bolt connection end surface, which tends to become hot, can be effectively cooled. Furthermore, since the introduction hole and the first cooling hole are shorter than long cooling holes that extend over most of the front-rear direction (or the chord direction of the blade portion) (see, for example, Patent Document 2), they can be easily manufactured. Therefore, according to the configuration described in [1] above, the turbine stator blades can be easily manufactured and the turbine stator blades can be effectively cooled.

[0067] [2] In some embodiments, in the configuration of [1] above, The turbine stator blades are The shroud portion is provided with a second cooling hole (80) that communicates with the cavity and has an opening (82) on the front end surface or the rear end surface.

[0068] According to the configuration described in [2] above, a second cooling hole is provided that communicates with the cavity and has an opening on the front or rear end surface of the shroud portion, so that the cooling fluid in the cavity is supplied to the second cooling hole. Therefore, the shroud portion can be cooled more effectively by the cooling fluid flowing through the first and second cooling holes.

[0069] [3] In some embodiments, in the configuration of [2] above, At least a portion of the first cooling hole is located closer to the gas path surface than the second cooling hole in the direction of the blade height.

[0070] In the shroud portion of the turbine stator blade, the region near the gas path surface facing the combustion gas flow path tends to be hotter. With the configuration described in [3] above, the first cooling hole provided at the bolted end of the shroud portion is positioned relatively close to the gas path surface, so that the particularly hot region of the shroud portion can be cooled more effectively.

[0071] [4] In some embodiments, in any of the configurations described in [1] to [3] above, The opening of the introduction hole and the opening of the first cooling hole are provided on the same side with respect to the flange portion in the cord direction.

[0072] According to the configuration described in [4] above, the opening of the inlet hole and the opening of the first cooling hole are located on the same side with respect to the flange portion in the cord direction, so the distance between the opening of the inlet hole and the opening of the first cooling hole in the cord direction is relatively short. As a result, the first cooling hole does not need to be very long, making it easy to process. Thus, the turbine stator blades can be manufactured easily and the turbine stator blades can be cooled effectively.

[0073] [5] In some embodiments, in the configuration of [4] above, The opening of the introduction hole is located in the direction of the code between the flange portion and the front wall surface (inner wall surface 72f) or rear wall surface (inner wall surface 72r) of the cavity.

[0074] According to the configuration described in [5] above, the opening of the inlet hole is located between the flange portion and the front or rear wall surface of the cavity in the direction of the cord. That is, since the opening of the inlet hole is located relatively close to the flange portion in the direction of the cord, the length of the first cooling hole can be secured to a certain extent. Therefore, the manufacturing of the turbine stator blades is made easier, and more effective cooling of the turbine stator blades is possible.

[0075] [6] In some embodiments, in any of the configurations described in [1] to [5] above, The diameter of the introduction hole is larger than the diameter of the first cooling hole.

[0076] In the configuration described in [6] above, the diameter of the inlet hole is larger than the diameter of the first cooling hole. Therefore, when machining the first cooling hole in the shroud portion where the inlet hole is formed, it is easier to ensure that the first cooling hole is reliably connected to the inlet hole. In addition, because the pressure loss in the first cooling hole is relatively small, it is easy to supply the cooling fluid to the first cooling hole through the inlet hole. Thus, the manufacturing of the turbine stator blades is easier, and more effective cooling of the turbine stator blades is possible.

[0077] [7] In some embodiments, in any of the configurations described in [1] to [6] above, The shroud portion includes an outer shroud (60) provided on the outside of the blade portion in the radial direction of the turbine (6).

[0078] In some types of gas turbines, the end region on the bolted-on side, particularly in the outer shroud, tends to become hot. In this regard, according to the configuration described in [7] above, since the above-mentioned inlet holes and first cooling holes are provided in the outer shroud, the outer shroud can be effectively cooled. Therefore, the manufacturing of the turbine stator blades is made easier, and more effective cooling of the turbine stator blades is possible.

[0079] [8] A turbine stator blade assembly (100) according to at least one embodiment of the present invention is The turbine (6) is provided with ventral stator vanes (24B) and dorsal stator vanes (24A) that are arranged adjacent to each other in the circumferential direction and connected to each other by bolts (96). At least one of the ventral stator vane and the dorsal stator vane is a turbine stator vane as described in any one of the above items [1] to [7].

[0080] In the configuration described in [8] above, an introduction hole is provided on the side of the ventral or dorsal circumferential wall portion of the shroud portion where a flange through which bolts for connecting to adjacent turbine stator blades are inserted is provided (i.e., the bolt connection side), with an opening on the side facing away from the gas pass surface, and a first cooling hole is provided which communicates with the introduction hole and has an opening on the front end surface, rear end surface, or gas pass surface of the shroud portion. Therefore, cooling fluid from the outer space on the opposite side of the blade portion across the outer shroud can be supplied to the first cooling hole via the introduction hole without going through a cavity. In other words, since a relatively low-temperature cooling fluid that is not used for cooling using a cavity is supplied to the first cooling hole, the area of ​​the outer shroud near the bolt connection end surface, which tends to become hot, can be effectively cooled. Furthermore, since the introduction hole and the first cooling hole are shorter than long cooling holes that extend over most of the front-rear direction (or the chord direction of the blade portion) (see, for example, Patent Document 2), they can be easily manufactured. Therefore, according to the configuration described in [8] above, the turbine stator blades can be easily manufactured and the turbine stator blades can be effectively cooled.

[0081] [9] A gas turbine (1) according to at least one embodiment of the present invention is A compressor (2) for compressing air, A combustor (4) for burning fuel using compressed air from the aforementioned compressor, A turbine (6) configured to be driven by combustion gas from the aforementioned combustor, Equipped with, The turbine includes the turbine stator blade assembly (100) described in [8] above.

[0082] In the configuration described in [9] above, an introduction hole is provided on the ventral or dorsal circumferential wall portion of the shroud portion, located at the end of the shroud portion where a flange for connecting bolts to adjacent turbine stator blades is provided (i.e., the bolt connection side), with an opening on the side facing away from the gas pass surface, and a first cooling hole is provided that communicates with the introduction hole and has an opening on the front end surface, rear end surface, or gas pass surface of the shroud portion. Therefore, cooling fluid from the outer space on the opposite side of the blade portion across the outer shroud can be supplied to the first cooling hole via the introduction hole without going through a cavity. In other words, since a relatively low-temperature cooling fluid that is not used for cooling using a cavity is supplied to the first cooling hole, the area of ​​the outer shroud near the bolt connection end surface, which tends to become hot, can be effectively cooled. Furthermore, since the introduction hole and the first cooling hole are shorter than long cooling holes that extend over most of the front-rear direction (or the chord direction of the blade portion) (see, for example, Patent Document 2), they can be easily manufactured. Therefore, according to the configuration described in [9] above, the turbine stator blades can be easily manufactured and the turbine stator blades can be effectively cooled.

[0083] Although embodiments of the present invention have been described above, the present invention is not limited to the embodiments described above, and also includes modified forms of the embodiments described above, as well as forms that combine these forms as appropriate.

[0084] In this specification, expressions describing relative or absolute arrangements such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" shall not only describe such arrangements strictly, but also describe states of relative displacement with tolerances or angles or distances that allow for the same function to be achieved. For example, expressions such as "identical," "equal," and "homogeneous" that describe things being in an equal state not only describe a state of being strictly equal, but also describe a state in which there is a tolerance or a difference that is sufficient to achieve the same function. Furthermore, in this specification, expressions describing shapes such as quadrilaterals and cylindrical shapes shall not only represent geometrically precise quadrilaterals and cylindrical shapes, but also shapes that include uneven surfaces, chamfered surfaces, etc., to the extent that the same effect can be achieved. Furthermore, in this specification, the expressions “equipment,” “includes,” or “possess” of a component are not exclusive expressions that exclude the existence of other components. [Explanation of symbols]

[0085] 1 Gas Turbine 2 Compressor 4 Combustor 6 Turbines 8 rotors 10 Compressor compartment 12 Air intake 16 Static Wings 18 Moving blade 20 Combustion chamber 22 Turbine casing 23 Heat-shielding ring 24 Static Wing 24A Dorsal vane 24B Ventral stator wing 26 Moving blade 27 split ring 28 Combustion gas flow path 30 Exhaust chamber 32 Interior space 34 Outside space 40 Wings 41 Leading edge 42 Trailing edge 43 Ventral aspect 44 Dorsal aspect 45 Cooling passage 46 Entrance opening 50 Inner Shroud 51 Seal ring retaining ring 52 Gas path surface 60 Outer shroud 61 Gas Pass Surface 62 Front end surface 64 Rear end surface 66 Ventral end surface 68 Dorsal end face 70 Cavity 71 Bottom 72f Interior wall surface 72p Interior wall surface 72r interior wall surface 72s Interior wall surface 74 Peripheral wall section 74f Front peripheral wall 74p Ventral peripheral wall 74r Rear peripheral wall 74s Dorsal peripheral wall 75 sides 78p Flange section 78s flange section 79 bolt holes 80 2nd cooling hole 81 Aperture 82 Aperture 84 Inlet holes 85 Aperture 86 1st cooling hole 87 Aperture 88 Protrusion 90 Impingement Plate 91 Impingement holes 92 Engaging part 93 Engaging part 94 Engaging part 95 Engaging part 96 volts 97 Nut 100 Turbine Stator Blade Assembly A cooling fluid G Combustion gas

Claims

1. A wing portion having ventral and dorsal surfaces that extend along the wing height direction and between the leading and trailing edges, A shroud portion connected to the blade portion and having a gas path surface facing the combustion gas passage, A turbine stator blade equipped with, The aforementioned shroud portion is, A cavity capable of receiving cooling fluid from the space opposite to the blade portion, sandwiching the shroud portion in the blade height direction, A peripheral wall portion is provided so as to surround the cavity when viewed from the wing height direction and has a surface that forms the inner wall surface of the cavity, The turbine stator blade and a flange portion having bolt holes through which bolts for connecting the turbine stator blade to an adjacent turbine stator blade are inserted, The aforementioned peripheral wall portion is A ventral peripheral wall portion located on the ventral end side of the shroud portion and extending along the chord direction of the wing portion, A rear peripheral wall portion located on the rear end side of the shroud portion and extending along the direction of the cord, Includes, The flange portion is provided so as to protrude from either the ventral circumferential wall portion or the dorsal circumferential wall portion in the direction of the wing height. An introduction hole having an opening on the side of the ventral or dorsal circumferential wall that faces away from the gas pass surface in the wing height direction, The first cooling hole has an opening on the front end surface, rear end surface, or gas pass surface of the shroud portion and communicates with the introduction hole, Equipped with Turbine stator blades.

2. It comprises a second cooling hole that communicates with the cavity and has an opening on the front end surface or the rear end surface of the shroud portion. The turbine stator blade according to claim 1.

3. At least a portion of the first cooling hole is located closer to the gas path surface than the second cooling hole in the direction of the blade height. The turbine stator blade according to claim 2.

4. The opening of the introduction hole and the opening of the first cooling hole are provided on the same side with respect to the flange portion in the cord direction. A turbine stator blade according to any one of claims 1 to 3.

5. The opening of the introduction hole is located between the flange portion and the front or rear wall surface of the cavity in the direction of the code. The turbine stator blade according to claim 4.

6. The diameter of the introduction hole is larger than the diameter of the first cooling hole. A turbine stator blade according to any one of claims 1 to 3.

7. The shroud portion includes an outer shroud provided on the outside of the blade portion in the radial direction of the turbine. A turbine stator blade according to any one of claims 1 to 3.

8. The turbine comprises a ventral stator vane and a dorsal stator vane, which are arranged adjacent to each other in the circumferential direction of the turbine and are connected to each other by bolts. At least one of the ventral stator vane and the dorsal stator vane is a turbine stator vane according to any one of claims 1 to 3. Turbine stator blade assembly.

9. A compressor for compressing air, A combustor for burning fuel using compressed air from the aforementioned compressor, A turbine configured to be driven by combustion gas from the aforementioned combustor, Equipped with, The turbine includes the turbine stator blade assembly described in claim 8. Gas turbine.

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