Turbine stator blades and gas turbines

Abstract

The present invention provides a turbine stator blade and a gas turbine capable of effectively cooling the turbine stator blade, including the shroud portion which is impingement cooled. [Solution] The turbine stator blade comprises a blade portion extending along the blade height direction and having a ventral surface and a dorsal surface extending between a leading edge and a trailing edge, and a shroud portion connected to the blade portion and forming a combustion gas passage, wherein the shroud portion includes a shroud body extending along a plane perpendicular to the blade height direction and connected to the blade portion, a peripheral wall portion located on the opposite side of the blade portion from the shroud body in the blade height direction and extending from the shroud body along the blade height direction, an impingement plate forming a cooling cavity together with the shroud body and the peripheral wall portion, a base portion protruding from the inner wall surface of the peripheral wall portion and for mounting the impingement plate, and at least one cooling passage having a first end connected to the cooling cavity and a second end opening to the surface of the shroud portion, and penetrating the base portion.

Description

Technical Field

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[0001] The present disclosure relates to turbine stator blades and gas turbines.

Background Art

[0002] As a cooling method for the shroud of a turbine stator blade, impingement cooling may be performed. In the impingement cooling of the shroud, cooling air is made to collide with the wall surface of the shroud through a large number of through holes of an impingement plate attached to the shroud, thereby cooling the shroud.

[0003] Patent Document 1 describes a turbine stator blade in which an impingement plate is supported on a shelf (pedestal portion) provided on the surface opposite to the gas path surface of a shroud bottom plate that forms a gas path surface facing the combustion gas flow path.

Prior Art Documents

Patent Documents

[0004] ​​​​​​​​​​​​​​​​​​​​​​​​ 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 aforementioned blade portion and forming a combustion gas passage, Equipped with, The aforementioned shroud portion is, A shroud body extending along a plane perpendicular to the wing height direction and connected to the wing portion, A peripheral wall portion located on the opposite side of the wing portion from the shroud body in the wing height direction, and extending from the shroud body along the wing height direction, An impingement plate that forms a cooling cavity together with the shroud body and the peripheral wall portion, A base portion protruding from the inner wall surface of the peripheral wall portion for installing the impingement plate, It includes at least one cooling passage that penetrates the base portion, each having a first end connected to the cooling cavity and a second end opening to the surface of the shroud portion.

[0008] 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 blades described above. [Effects of the Invention]

[0009] According to at least one embodiment of the present invention, a turbine stator blade and a gas turbine are provided that can effectively cool a turbine stator blade including a shroud portion that is impingement cooled. [Brief explanation of the drawing]

[0010] [Figure 1] This is a schematic diagram of a gas turbine to which a turbine stator blade according to one embodiment is applied. [Figure 2]It is a schematic diagram showing an enlarged part of the gas turbine shown in FIG. 1. [Figure 3] It is a schematic perspective view showing a stator blade (turbine stator blade) according to an embodiment. [Figure 4] It is a schematic cross-sectional view of a part of the outer shroud of a stator blade (turbine stator blade) 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. [[ID=I4]]

Mode for Carrying Out the Invention

[0011] 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.

[0012] (Configuration of Gas Turbine) FIG. 1 is a schematic configuration diagram of a gas turbine to which a turbine stator blade according to an embodiment is applied. FIG. 2 is a schematic diagram showing an enlarged part of the gas turbine 1 shown in FIG. 1.

[0013] 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.

[0014] The compressor 2 includes a plurality of stator blades 16 fixed to the compressor casing 10 side, and a plurality of rotor blades 18 implanted in the rotor 8 so as to be alternately arranged with respect to the stator blades 16. Air taken in from the air intake 12 is sent to the compressor 2, and this air is compressed by passing through the plurality of stator blades 16 and the plurality of rotor blades 18 to become high-temperature and high-pressure compressed air.

[0015] The combustor 4 is configured to be supplied with fuel and the compressed air generated by the compressor 2. In the combustor 4, the fuel and the compressed air are mixed and burned to generate combustion gas, which is the working fluid of the turbine 6. As shown in FIG. 1, a plurality of combustors 4 may be arranged circumferentially around the rotor 8 in the combustor compartment 20.

[0016] As shown in FIGS. 1 and 2, the turbine 6 has a combustion gas flow path 28 formed in the turbine compartment 22, and includes a plurality of stationary blades 24 (turbine stationary blades) and moving blades 26 provided in the combustion gas flow path 28. The stationary blades 24 are fixed to the turbine compartment 22 side, and a plurality of stationary blades 24 arranged along the circumferential direction of the rotor 8 constitute a stationary blade row. The moving blades 26 are implanted in the rotor 8, and a plurality of moving blades 26 arranged along the circumferential direction of the rotor 8 constitute a moving blade row. The stationary blade row and the moving blade row are alternately arranged in the axial direction of the rotor 8.

[0017] In the turbine 6, the combustion gas G (see FIG. 2) from the combustor 4 flowing into the combustion gas flow path 28 passes through the plurality of stationary blades 24 and the plurality of moving blades 26, thereby rotationally driving the rotor 8. As a result, the generator connected to the rotor 8 is driven to generate electric power. The combustion gas after driving the turbine 6 is discharged to the outside through the exhaust chamber 30.

[0018] (Turbine stationary blade) FIG. 3 is a schematic perspective view showing the stationary blade 24 (turbine stationary blade) according to an embodiment.

[0019] As shown in FIGS. 2 and 3, the stationary blade 24 includes 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 stationary blade 24 corresponds to the radial direction of the turbine rotor on which the stationary blade 24 is installed.

[0020] 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 to which a cooling fluid is supplied may be provided inside the wing section 40. Although not specifically shown, the cooling passage 45 may form a serpentine flow path. A cooling fluid A (e.g., air) may be supplied to the cooling passage 45 through an inlet opening 46.

[0021] 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.

[0022] 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.

[0023] 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.

[0024] Figure 4 is a schematic cross-sectional view of the outer shroud 60 portion of the stator blade 24 (turbine stator blade) 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.

[0025] 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.

[0026] As shown in Figures 3 to 6, the outer shroud 60 (shroud portion) of the stator blade 24 according to some embodiments includes a plate-shaped shroud body 60a that extends along a plane perpendicular to the blade height direction and is connected to the blade portion 40. The shroud body 60a has the gas path surface 61 described above. The shroud body 60a 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 both end surfaces in the axial direction of the turbine 6 (or the chord direction of the blade portion 40 or the first direction described later), and a ventral end surface 66 and a dorsal end surface 68 which are both end surfaces in the circumferential direction of the turbine 6. As shown in Figures 5 and 6, the outer shroud 60 may extend along a plane perpendicular to the blade height direction and be inclined radially outward as it approaches the rear. Alternatively, the outer shroud 60 may extend along a plane perpendicular to the blade height direction and be inclined radially inward as it approaches the rear.

[0027] As shown in Figures 3 to 6, in some embodiments, the outer shroud 60 includes a cavity 70 (cooling cavity) capable of receiving cooling fluid A from the space on the opposite side of the blade portion 40 (outer space 34 in the case of the outer shroud 60) on either side 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. The peripheral wall portion 74 is located on the opposite side of the blade portion 40 on either side of the shroud body 60a in the blade height direction, and is provided so as to extend from the shroud body 60a along the blade height direction.

[0028] In the illustrated embodiment, the outer shroud 60 includes a recess having a bottom surface 71 and inner wall surfaces 72f, 72p, 72r, and 72s, which are the surfaces opposite to the gas path surface 61 of the shroud body 60a. The cavity 70 is defined by this recess and an impingement plate 90 that covers the recess. That is, the cavity 70 is formed by the shroud body 60a, the peripheral wall portion 74, and the impingement plate 90. The impingement plate 90 has a plurality of impingement holes 91 (through holes), and the cooling fluid supplied to the outer space 34 is cooled by impacting 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.

[0029] 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 front circumferential wall portion 74f and a rear circumferential wall portion 74r, which are located on the front and rear ends of the outer shroud 60, respectively, and extend along the circumferential direction of the turbine 6. The circumferential wall portion 74 also includes a pair of lateral circumferential wall portions (ventral circumferential wall portion 74p and dorsal circumferential wall portion 74s) that connect the ends of the front circumferential wall portion 74f and the ends of the rear circumferential wall portion 74r, respectively, and extend along a first direction (see Figure 4) that intersects the circumferential direction when viewed from the blade height direction. The ventral circumferential wall portion 74p is located on the ventral end side of the outer shroud 60 and extends along the first direction. The dorsal circumferential wall portion 74s is located on the dorsal end side of the outer shroud 60 and extends along the first direction. The first direction described above may be a direction along the chord direction of the blade portion 40, or a direction along the axial direction of the rotor. 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, respectively.

[0030] As shown in Figures 3 to 6, in some embodiments, the outer shroud 60 protrudes from the inner wall surfaces 72 (72p, 72s, 72f and / or 72r) of the peripheral wall portion 74 in the direction of each inner wall surface 72 and includes a base portion 78 for mounting the impingement plate 90.

[0031] The base portion 78 is provided between the bottom surface 71 of the shroud body 50a and the impingement plate 90 in the wing height direction. The base portion 78 serves as a base when attaching the impingement plate 90 to the outer shroud 60. With the impingement plate 90 resting on the base portion 78, the impingement plate 90 is attached to the outer shroud 60 by welding or other means. The base portion 78 plays a role in positioning the impingement plate 90 in the wing height direction.

[0032] As shown in Figure 4, the base portion 78 includes at least one of the following: a front base portion 78f protruding from the inner wall surface 72f of the front circumferential wall portion 74f; a rear base portion 78r protruding from the inner wall surface 72r of the rear circumferential wall portion 74r; a ventral base portion 78p (lateral base portion) protruding from the inner wall surface 72p of the ventral circumferential wall portion 74p (lateral circumferential wall portion); or a dorsal base portion 78s (lateral base portion) protruding from the inner wall surface 72s of the dorsal circumferential wall portion 74s (lateral circumferential wall portion).

[0033] In the exemplary embodiment shown in Figure 4, the outer shroud 60 includes a front base portion 78f and a rear base portion 78r that extend circumferentially when viewed from the wing height direction. The outer shroud 60 also includes a ventral base portion 78p and a dorsal base portion 78s connected to both ends of the front base portion 78f and extending in a first direction when viewed from the wing height direction. The outer shroud 60 also includes a ventral base portion 78p and a dorsal base portion 78s connected to both ends of the rear base portion 78r and extending in a first direction when viewed from the wing height direction.

[0034] As shown in the figure, the ventral base portion 78p and the dorsal base portion 78s may be provided over a portion of the first-direction extending region of the cavity 70, or over the entire region of the first-direction extending region of the cavity 70. As shown in the figure, the front base portion 78f and the rear base portion 78r may be provided over the entire region of the circumferential-direction extending region of the cavity 70, or over a portion of the circumferential-direction extending region of the cavity 70.

[0035] As shown in Figure 4, the front base portion 78f, the rear base portion 78r, the ventral base portion 78p, or the dorsal base portion 78s may have an axial surface 79 that faces the cavity 70 and extends along the circumferential direction when viewed from the wing height direction. In the exemplary embodiment shown in Figure 4, each of the front base portion 78f, the rear base portion 78r, the ventral base portion 78p, and the dorsal base portion 78s has the aforementioned axial surface 79.

[0036] As shown in Figure 4, at least one of the pair of lateral base portions (i.e., the ventral base portion 78p and the dorsal base portion 78s) has a circumferential surface 80 that faces the cavity 70 and is opposite to the other lateral base portion. The circumferential surface 80 may extend along the first direction described above when viewed from the wing height direction. In the exemplary embodiment shown in Figure 4, the ventral base portion 78p has a circumferential surface 80 that faces the cavity 70 and is opposite to the dorsal base portion 78s. The dorsal base portion 78s also has a circumferential surface 80 that faces the cavity 70 and is opposite to the ventral base portion 78p.

[0037] As shown in Figures 4 to 6, in some embodiments, the cooling passage 82 has a first end 83 connected to the cavity 70 and a second end 84 opening to the surface of the outer shroud 60 (shroud portion) (e.g., the front end surface 62, the rear end surface 64, or the gas pass surface 61), and includes at least one cooling passage 82 that penetrates the base portion 78 (front base portion 78f, rear base portion 78r, ventral base portion 78p, or dorsal base portion 78s). As shown in Figure 4, the at least one cooling passage 82 may include a plurality of cooling passages 82 arranged along the circumferential direction.

[0038] In the illustrated embodiment, the stator vane 24 has a first end 83 connected to the cavity 70 and a second end 84 opening to the rear end surface 64 of the outer shroud 60, and includes a plurality of cooling passages 82 that penetrate either the rear base portion 78r, the ventral base portion 78p, or the dorsal base portion 78s. As shown in the illustration, each cooling passage 82 may be provided to extend along the first direction described above (or the chord direction of the vane portion 40). As shown in the illustration, the first end 83 of the plurality of cooling passages 82 may open to the axial surface 79 of the rear base portion 78r, the ventral base portion 78p, or the dorsal base portion 78s.

[0039] In some embodiments, the stator vane 24 may have the first end 83 and second end 84 described above and may include at least one cooling passage 82 that penetrates the front base portion 78f. The second end 84 of such a cooling passage 82 may open to the front end surface 62 of the outer shroud 60.

[0040] According to the above configuration, at least one cooling passage 82 is provided that penetrates the base portion 78 for installing the impingement plate 90 and has a first end 83 connected to the cavity 70 (cooling cavity) and a second end 84 opening to the surface of the outer shroud 60 (shroud portion). As a result, the cooling fluid supplied to the cavity 70 can pass through the cooling passage 82, through the base portion 78, and then be discharged outside the outer shroud 60. Therefore, the base portion 78, which is normally difficult to cool, can be effectively cooled. Thus, the stator vane 24, including the shroud portion that is impinged and cooled, can be effectively cooled.

[0041] In some embodiments, as shown in Figure 4, for example, at least one cooling passage 82 includes a first passage 86 passing through a lateral base portion (ventral base portion 78p or dorsal base portion 78s). In the exemplary embodiment shown in Figure 4, a first passage 86 passing through the ventral base portion 78p and a first passage 86 passing through the dorsal base portion 78s are provided. As shown in Figure 4, these first passages 86 may be located at both ends of a plurality of cooling passages 82 arranged in the circumferential direction.

[0042] Of the base portion 78, the lateral base portion (ventral base portion 78p or dorsal base portion 78s) provided on the lateral circumferential wall portion (ventral circumferential wall portion 74p or dorsal circumferential wall portion 74s) is usually longer in the first direction than the front base portion 78f provided on the front circumferential wall portion 74f or the rear base portion 78r provided on the rear circumferential wall portion 74r. In this respect, according to the above embodiment, since at least one cooling passage 82 includes a first passage 86 that passes through the lateral base portion, the first passage 86 can be formed as a relatively long cooling passage 82. Therefore, the base portion 78 can be cooled more effectively. Therefore, the stator vane 24, including the shroud portion that is impinged and cooled, can be cooled more effectively.

[0043] In some embodiments, as shown in Figure 4, for example, the centerline C1 of the first passage 86 is inclined with respect to the inner wall surface 72 of the corresponding lateral circumferential wall, so as it approaches the first end 83 (see Figure 5) from the second end 84 (see Figure 5) (i.e., as it approaches forward in the first direction or axial direction), it moves away from the inner wall surface 72 of the corresponding lateral circumferential wall.

[0044] In the exemplary embodiment shown in Figure 4, the centerline C1 of the first passage 86 that penetrates the dorsal base portion 78s is inclined with respect to the inner wall surface 72s of the dorsal circumferential wall portion 74s, so that it moves away from the inner wall surface 72s of the dorsal circumferential wall portion 74s as it approaches the first end 83 from the second end 84. Similarly, the centerline C1 of the first passage 86 that penetrates the ventral base portion 78p is inclined with respect to the inner wall surface 72p of the ventral circumferential wall portion 74p, so that it moves away from the inner wall surface 72p of the ventral circumferential wall portion 74p as it approaches the first end 83 from the second end 84.

[0045] According to the above embodiment, when viewed from the wing height direction, the center line C1 of the first passage 86, which is provided to penetrate the lateral base portion, is inclined with respect to the inner wall surface 72 of the lateral circumferential wall portion such that it moves away from the inner wall surface 72 of the lateral circumferential wall portion as it approaches the first end 83 from the second end 84. Therefore, interference between the drilling tool and the lateral circumferential wall portion can be suppressed when drilling holes in the first passage 86. Thus, it becomes easier to manufacture the above-described stationary vane 24.

[0046] In some embodiments, as shown in Figure 4, for example, the center line C1 of the first passage 86 is inclined with respect to the circumferential surface 80 such that, when viewed from the wing height direction, it approaches the circumferential surface 80 of the corresponding base portion 78 as it approaches the first end 83 from the second end 84 (i.e., as it approaches forward in the first direction or axial direction).

[0047] In the exemplary embodiment shown in Figure 4, the center line C1 of the first passage 86 that penetrates the dorsal base portion 78s is inclined with respect to the circumferential surface 80 of the dorsal base portion 78s as it approaches the first end 83 from the second end 84. Similarly, the center line C1 of the first passage 86 that penetrates the ventral base portion 78p is inclined with respect to the circumferential surface 80 of the ventral base portion 78p as it approaches the first end 83 from the second end 84.

[0048] According to the above embodiment, when viewed from the wing height direction, the center line C1 of the first passage 86, which is provided to penetrate the lateral base portion, is inclined with respect to the circumferential surface 80 of the lateral base portion (dorsal base portion 78s or ventral base portion 78p) so as it approaches the first end 83 from the second end 84. Therefore, interference between the drilling tool and the lateral circumferential wall portion can be suppressed when drilling holes in the first passage 86. Thus, the above-described stationary vane 24 is easier to manufacture.

[0049] In some embodiments, as shown in Figure 4, for example, at least one cooling passage 82 includes, in addition to the first passage 86 described above, at least one second passage 88 that penetrates the rear peripheral wall portion 74r. Furthermore, the second ends 84 of each of the first passage 86 and the second passage 88 (see Figures 5 and 6) open to the surface of the outer shroud 60 at the rear end of the outer shroud 60 (such as the rear end surface 64 or the gas pass surface 61). As shown in Figure 4, the second passage 88 may be provided so as to penetrate the rear base portion 78r and the rear peripheral wall portion 74r. In some embodiments, for example, when the rear base portion 78r is absent, or when the rear base portion 78r is provided only in a portion of the area between a pair of lateral base portions in the circumferential direction, the second passage 88 may be provided so as to penetrate the rear peripheral wall portion 74r without penetrating the rear base portion 78r.

[0050] In the exemplary embodiment shown in Figure 4, at least one cooling passage 82 includes the first passage 86 described above and a plurality of second passages 88 that penetrate the rear base portion 78r. The second ends 84 of each of the first passage 86 and the second passages 88 open to the rear end surface 64 of the outer shroud 60.

[0051] According to the above embodiment, in addition to the first passage 86 that penetrates the lateral base portion, a second passage 88 that penetrates the rear base portion 78r is provided, and the second ends 84 of the first passage 86 and the second passage 88 open to the rear end of the outer shroud 60 (shroud portion), so that the base portion on the rear end can be cooled more effectively. Therefore, the stator vane 24, including the shroud portion that is impinged and cooled, can be cooled more effectively.

[0052] In some embodiments, as shown in Figure 4 for example, when viewed from the wing height direction, the centerline C1 of the first passage 86 and the centerline C2n of the second passage 88n that is adjacent to the first passage 86 in the circumferential direction are inclined toward each other so as they move away from the second end 84 toward the first end 83 (i.e., toward the front).

[0053] According to the above embodiment, the center line C1 of the first passage 86 and the center line C2n of the second passage 88n adjacent to the first passage 86 in the circumferential direction are inclined to move away from each other as they move from the second end 84 toward the first end 83. Therefore, interference between the drilling tool and the lateral base portion (i.e., interference with the circumferential surface 80 of the dorsal base portion 78s or the ventral base portion 78p) can be suppressed when drilling holes in the second passage 88n adjacent to the first passage 86. Thus, the above-described stationary vane 24 becomes easier to manufacture.

[0054] In some embodiments, as shown in Figure 4, for example, at least one cooling passage 82 includes a plurality of second passages 88 in addition to the first passage 86. The plurality of second passages 88 include a first group of plurality of second passages 88A and a second group of plurality of second passages 88B, as described below. Here, the first group of plurality of second passages 88A have a constant (common) angle of the centerline C2 with respect to the first direction when viewed from the wing height direction. The second group of plurality of second passages 88B are arranged in the circumferential direction between the first group of plurality of second passages 88A and the first passage 86, and the angle of the centerline C2 with respect to the first direction when viewed from the wing height direction changes gradually.

[0055] According to the embodiment described above, the plurality of second passages 88 include a first group of plurality of second passages 88A whose angle with respect to the first direction of the centerline C2 when viewed from the wing height direction is constant, and a second group of plurality of second passages 88B which are arranged in the circumferential direction between the first group of plurality of second passages 88A and the first passage 86, and whose angle with respect to the first direction of the centerline when viewed from the wing height direction gradually changes. As a result, even though the first passage 86 is given a special angle as described above, it becomes easier to make the pitch (the distance in the circumferential direction between the centerlines of adjacent cooling passages) at the second ends 84 of the plurality of cooling passages 82 (first passage 86 and plurality of second passages 88) equal. Thus, by providing a first passage 86 that is inclined with respect to the first direction, manufacturing is made easier, while uniform cooling in the circumferential direction becomes easier.

[0056] As shown in Figure 4, the angle of the center line C2 with respect to the first direction may gradually change so that the multiple second passages 88B of the second group move away from each other as they move from the first end 83 to the second end 84. In this case, the center line C1 of the first passage 86 and the center line C2 of the second passage 88B located adjacent to the first passage 86 in the circumferential direction tend to tilt away from each other as they move from the second end 84 to the first end 83. Therefore, interference between the drilling tool and the lateral base portion is suppressed when drilling holes in the aforementioned second passages 88B adjacent to the first passage 86.

[0057] Alternatively, the angle of the center line C2 with respect to the first direction may gradually change such that the multiple second passages 88B of the second group approach each other as they move from the first end 83 to the second end 84.

[0058] The contents described in each of the above embodiments can be understood, for example, as follows:

[0059] [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 and trailing edge, A shroud portion (for example, an outer shroud 60 or an inner shroud 50) is connected to the blade portion and forms a combustion gas passage, Equipped with, The aforementioned shroud portion is, A shroud body (60a) extending along a plane perpendicular to the wing height direction and connected to the wing portion, A peripheral wall portion (74) is located on the opposite side of the wing portion from the shroud body in the wing height direction, and extends from the shroud body along the wing height direction, An impingement plate (90) that together with the shroud body and the peripheral wall portion forms a cooling cavity (cavity 70), A base portion (78) protrudes from the inner wall surface of the peripheral wall portion and is used to install the impingement plate, It includes at least one cooling passage (86) that penetrates the base portion, having a first end (83) connected to the cooling cavity and a second end (84) that opens to the surface of the shroud portion.

[0060] According to the configuration described in [1] above, at least one cooling passage is provided that penetrates the base portion for installing the impingement plate and has a first end connected to the cooling cavity and a second end opening to the surface of the shroud portion. As a result, the cooling fluid supplied to the cooling cavity can pass through the cooling passage to the base portion and then be discharged outside the shroud portion. Therefore, the base portion, which is normally difficult to cool, can be effectively cooled. Thus, the turbine stator blades, including the shroud portion that is impingement cooled, can be effectively cooled.

[0061] [2] In some embodiments, in the configuration of [1] above, The aforementioned peripheral wall portion is The front circumferential wall portion (74f) is located on the front end side of the shroud portion and extends along the circumferential direction of the turbine, A rear circumferential wall portion (74r) located at the rear end of the shroud portion and extending along the circumferential direction, The ends of the front circumferential wall and the ends of the rear circumferential wall are connected, respectively, and a pair of lateral circumferential wall portions (ventral circumferential wall portion 74p and dorsal circumferential wall portion 74s) extend along a first direction that intersects the circumferential direction when viewed from the wing height direction, Includes, The base portion includes a lateral base portion (ventral base portion 78p or dorsal base portion 78s) that protrudes from the inner wall surface of one of the pair of lateral periphery portions. The at least one cooling passage includes a first passage (86) that passes through the lateral base portion.

[0062] Of the base portions, the lateral base portion provided on the lateral circumferential wall is usually longer in the first direction (generally along the code direction) than the front base portion provided on the front circumferential wall or the rear base portion provided on the rear circumferential wall. According to the configuration described in [2] above, at least one cooling passage includes a first passage that passes through the lateral base portion, so the first passage can be formed as a relatively long cooling passage. Therefore, the base portion can be cooled more effectively. Therefore, the turbine stator blades, including the shroud portion that is impingement cooled, can be cooled more effectively.

[0063] [3] In some embodiments, in the configuration of [2] above, Viewed from the wing height direction, the centerline (C1) of the first passage is inclined with respect to the inner wall surface of the one lateral circumferential wall such that it moves away from the inner wall surface of the one lateral circumferential wall as it approaches the first end from the second end.

[0064] According to the configuration described in [3] above, the centerline of the first passage, which is provided to penetrate the lateral base portion when viewed from the wing height direction, is inclined with respect to the inner wall surface of the lateral circumferential wall portion such that it moves away from the inner wall surface of the lateral circumferential wall portion as it approaches the first end from the second end. Therefore, interference between the drilling tool and the lateral circumferential wall portion can be suppressed when drilling holes in the first passage. Thus, it becomes easier to manufacture turbine stator blades having the configuration described in [1] above.

[0065] [4] In some embodiments, in the configuration of [2] above, The lateral base portion has a circumferential surface (80) facing the other lateral circumferential wall portion of the pair of lateral circumferential wall portions, Viewed from the wing height direction, the centerline of the first passage is inclined with respect to the circumferential surface such that it approaches the circumferential surface as it moves from the second end towards the first end.

[0066] According to the configuration described in [4] above, the center line of the first passage, which is provided to penetrate the lateral base portion when viewed from the wing height direction, is inclined with respect to the circumferential surface of the lateral base portion such that it approaches the circumferential surface of the lateral base portion as it approaches the circumferential surface of the lateral base portion from the second end towards the first end. Therefore, interference between the drilling tool and the lateral circumferential wall portion can be suppressed when drilling holes in the first passage. Thus, it becomes easier to manufacture turbine stator blades having the configuration described in [1] above.

[0067] [5] In some embodiments, in any of the configurations described in [2] to [4] above, The aforementioned at least one cooling passage includes at least one second passage (88) that penetrates the rear peripheral wall portion, The second end of each of the first passage and the second passage opens to the surface of the shroud portion at the rear end of the shroud portion (for example, the rear end surface 64, etc.).

[0068] According to the configuration described in [5] above, in addition to the first passage that penetrates the lateral base portion, a second passage that penetrates the rear peripheral wall portion is provided, and the second ends of the first and second passages open to the rear end of the shroud portion, so that the rear portion of the turbine stator blade can be effectively cooled. Therefore, the turbine stator blade, including the shroud portion that is impinged and cooled, can be cooled more effectively.

[0069] [6] In some embodiments, in the configuration of [5] above, The base portion includes a rear base portion (78r) that protrudes from the inner wall surface of the rear peripheral wall portion. The at least one second passage penetrates the rear base portion and the rear peripheral wall portion.

[0070] According to the configuration described in [6] above, in addition to the first passage that penetrates the lateral base portion, a second passage that penetrates the rear base portion is provided, and the second ends of the first and second passages open to the rear end of the shroud portion, so that the base portion on the rear end can be cooled more effectively. Therefore, the turbine stator blades, including the shroud portion that is impinged and cooled, can be cooled more effectively.

[0071] [7] In some embodiments, in the configuration of [5] or [6] above, Viewed from the wing height direction, the centerline of the first passage and the centerline (C2n) of the second passage (88n) adjacent to the first passage in the circumferential direction among the at least one second passage are inclined to move away from each other as they move from the second end toward the first end.

[0072] According to the configuration described in [7] above, the centerline of the first passage and the centerline of the second passage adjacent to the first passage in the circumferential direction are inclined to move away from each other as they move from the second end toward the first end. Therefore, interference between the drilling tool and the lateral base can be suppressed when drilling the aforementioned second passage adjacent to the first passage. Thus, it becomes easier to manufacture turbine stator blades having the configuration described in [1] above.

[0073] [8] In some embodiments, in any of the configurations described in [5] to [7] above, The at least one cooling passage includes a plurality of the second passages arranged along the circumferential direction, The aforementioned multiple second passages are, A group of second passages (88A) in the first group, where the angle of the center line (C2) with respect to the first direction is constant when viewed from the wing height direction, A plurality of second passages (88B) of the second group are arranged between the first group of second passages in the circumferential direction, and the angle of the center line (C1) with respect to the first direction when viewed from the wing height direction gradually changes. Includes.

[0074] According to the configuration described in [8] above, the multiple second passages include a first group of multiple second passages whose angle with respect to the first direction is constant when viewed from the wing height direction, and a second group of multiple second passages arranged between the first group of multiple second passages and the first passage in the circumferential direction, the angle with respect to the first direction when viewed from the wing height direction gradually changes. Therefore, even when the first passage is given a special angle as described above, it becomes easier to make the pitch (the distance in the circumferential direction between the centerlines of adjacent cooling passages) at the second ends of the multiple cooling passages (first passage and multiple second passages) uniform. Thus, by providing a first passage that is inclined with respect to the first direction, manufacturing is made easier, while uniform cooling in the circumferential direction becomes easier.

[0075] [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 a turbine stator blade (24) as described in any one of the above items [1] to [8].

[0076] According to the configuration described in [9] above, at least one cooling passage is provided that penetrates the base portion for installing the impingement plate and has a first end connected to the cooling cavity and a second end opening to the surface of the shroud portion. This allows the cooling fluid supplied to the cooling cavity to pass through the cooling passage to the base portion and then be discharged outside the shroud portion. Therefore, the base portion, which is normally difficult to cool, can be effectively cooled. Thus, the turbine stator blades, including the shroud portion that is impingement cooled, can be effectively cooled.

[0077] 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.

[0078] 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]

[0079] 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 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 50a Shroud Body 51 Seal ring retaining ring 52 Gas path surface 60 Outer shroud 60a Shroud Body 61 Gas Pass Surface 62 Front end surface 64 Rear end surface 66 Ventral end surface 68 Dorsal end face 70 Cavity 71 Bottom 72 Interior wall surface 72f Interior wall surface 72p Interior wall surface 72r interior wall surface 72s Interior wall surface 74 Peripheral wall part 74f Front peripheral wall 74p Ventral peripheral wall 74r Rear peripheral wall 74s Dorsal peripheral wall 78 Base 78f Front base section 78p Ventral base 78r Rear base section 78s Rear base 79 Axial surface 80 Circumferential surface 82 Cooling passage 83 1st end 84 2nd end 86 1st aisle 88 2nd aisle 88A 2nd aisle 88B 2nd aisle 88n Second aisle 90 Impingement Plate 91 Impingement holes 92 Engaging part 93 Engaging part 94 Engaging part 95 Engaging part A cooling fluid C1 center line C2 center line C2n center line 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 aforementioned blade portion and forming a combustion gas passage, Equipped with, The aforementioned shroud portion is, A shroud body extending along a plane perpendicular to the wing height direction and connected to the wing portion, A peripheral wall portion located on the opposite side of the wing portion from the shroud body in the wing height direction, and extending from the shroud body along the wing height direction, An impingement plate that forms a cooling cavity together with the shroud body and the peripheral wall portion, A base portion protruding from the inner wall surface of the peripheral wall portion for installing the impingement plate, It includes at least one cooling passage having a first end connected to the cooling cavity and a second end opening to the surface of the shroud portion, and passing through the base portion, The aforementioned peripheral wall portion is The front circumferential wall portion is located on the front end side of the shroud portion and extends along the circumferential direction of the turbine, A rear circumferential wall portion located at the rear end of the shroud portion and extending along the circumferential direction, The ends of the front circumferential wall and the ends of the rear circumferential wall are connected, and a pair of lateral circumferential wall portions extend along a first direction that intersects the circumferential direction when viewed from the wing height direction, Includes, The base portion includes a lateral base portion that protrudes from the inner wall surface of one of the pair of lateral periphery portions. The at least one cooling passage includes a first passage passing through the lateral base portion, The lateral base portion faces the cooling cavity and extends circumferentially when viewed from the wing height direction, and has an axial surface located forward of the inner wall surface of the rear circumferential wall portion in the first direction. The first end of the first passage opens to the axial surface of the lateral base portion. Turbine stator blades.

2. The base portion includes a rear base portion that protrudes from the inner wall surface of the rear peripheral wall portion, The rear base portion faces the cooling cavity and has an axial surface that extends circumferentially when viewed from the wing height direction, The axial surface of the lateral base portion is located in front of the axial surface of the rear base portion in the first direction. The turbine stator blade according to claim 1.

3. Viewed from the wing height direction, the centerline of the first passage is inclined with respect to the inner wall surface of the one lateral circumferential wall such that it moves away from the inner wall surface of the one lateral circumferential wall as it approaches the first end from the second end. The turbine stator blade according to claim 1 or 2.

4. The lateral base portion has a circumferential surface facing the other lateral circumferential wall portion of the pair of lateral circumferential wall portions, Viewed from the wing height direction, the centerline of the first passage is inclined with respect to the circumferential surface such that it approaches the circumferential surface as it moves from the second end towards the first end. The turbine stator blade according to claim 1 or 2.

5. The aforementioned at least one cooling passage includes at least one second passage that penetrates the rear peripheral wall portion, The second end of each of the first and second passages opens to the surface of the shroud portion at the rear end of the shroud portion. The turbine stator blade according to claim 1 or 2.

6. The base portion includes a rear base portion that protrudes from the inner wall surface of the rear peripheral wall portion. The at least one second passage penetrates the rear base portion and the rear peripheral wall portion. The turbine stator blade according to claim 5.

7. A wing portion having a ventral surface and a dorsal surface that extend along the wing height direction and between the leading edge and the trailing edge, A shroud portion connected to the aforementioned blade portion and forming a combustion gas passage, Equipped with, The aforementioned shroud portion is, A shroud body extending along a plane perpendicular to the wing height direction and connected to the wing portion, A peripheral wall portion located on the opposite side of the wing portion from the shroud body in the wing height direction, and extending from the shroud body along the wing height direction, An impingement plate that forms a cooling cavity together with the shroud body and the peripheral wall portion, A base portion protruding from the inner wall surface of the peripheral wall portion for installing the impingement plate, It includes at least one cooling passage having a first end connected to the cooling cavity and a second end opening to the surface of the shroud portion, and passing through the base portion, The aforementioned peripheral wall portion is The front circumferential wall portion is located on the front end side of the shroud portion and extends along the circumferential direction of the turbine, A rear circumferential wall portion located at the rear end of the shroud portion and extending along the circumferential direction, The ends of the front circumferential wall and the ends of the rear circumferential wall are connected, and a pair of lateral circumferential wall portions extend along a first direction that intersects the circumferential direction when viewed from the wing height direction, Includes, The base portion includes a lateral base portion that protrudes from the inner wall surface of one of the pair of lateral periphery portions. The at least one cooling passage is The first passage passing through the aforementioned lateral base portion, At least one second passage penetrating the rear peripheral wall portion, Includes, The second end of each of the first passage and the second passage opens to the surface of the shroud portion at the rear end of the shroud portion, Viewed from the wing height direction, the centerline of the first passage and the centerline of the second passage (of which at least one second passage is adjacent to the first passage in the circumferential direction) are inclined to move away from each other as they move from the second end toward the first end. Turbine stator blades.

8. A wing portion having a ventral surface and a dorsal surface that extend along the wing height direction and between the leading edge and the trailing edge, A shroud portion connected to the aforementioned blade portion and forming a combustion gas passage, Equipped with, The aforementioned shroud portion is, A shroud body extending along a plane perpendicular to the wing height direction and connected to the wing portion, A peripheral wall portion located on the opposite side of the wing portion from the shroud body in the wing height direction, and extending from the shroud body along the wing height direction, An impingement plate that forms a cooling cavity together with the shroud body and the peripheral wall portion, A base portion protruding from the inner wall surface of the peripheral wall portion for installing the impingement plate, It includes at least one cooling passage having a first end connected to the cooling cavity and a second end opening to the surface of the shroud portion, and passing through the base portion, The aforementioned peripheral wall portion is The front circumferential wall portion is located on the front end side of the shroud portion and extends along the circumferential direction of the turbine, A rear circumferential wall portion located at the rear end of the shroud portion and extending along the circumferential direction, The ends of the front circumferential wall and the ends of the rear circumferential wall are connected, and a pair of lateral circumferential wall portions extend along a first direction that intersects the circumferential direction when viewed from the wing height direction, Includes, The base portion includes a lateral base portion that protrudes from the inner wall surface of one of the pair of lateral periphery portions. The at least one cooling passage is The first passage passing through the aforementioned lateral base portion, At least one second passage penetrating the rear peripheral wall portion, Includes, The second end of each of the first passage and the second passage opens to the surface of the shroud portion at the rear end of the shroud portion, The at least one second passage includes a plurality of the second passages arranged along the circumferential direction, The aforementioned plurality of second passages are, A plurality of second passages in a first group, the angle of the centerline with respect to the first direction when viewed from the wing height direction is constant, A plurality of second passages of the second group are arranged in the circumferential direction between the first group of second passages and the first passage, and the angle of the centerline with respect to the first direction when viewed from the wing height direction changes gradually. including Turbine stator blades.

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 blades described in claim 1, 7, or 8. Gas turbine.

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