Turbine stator blades and gas turbines

Abstract

To provide a turbine stationary blade which can effectively and efficiently cool a turbine stationary blade while suppressing the complication of a structure, and a gas turbine.SOLUTION: A turbine stationary blade comprises a cooling passage extending along a blade height direction in a blade main body, an outside shroud connected to the blade main body, an inside shroud connected to the blade main body, and an internal flow passage forming part extending along the blade height direction. The internal flow passage forming part forms an outside space at a side opposite to the blade main body with the outside shroud sandwiched therebetween, and forms an inside space at a side opposite to the blade main body with the inside shroud sandwiched therebetween, and the internal flow passage forming part has a first portion and a second portion which is located while being shifted to the outside rather than the first portion in the blade height direction. An area surrounded by an outer edge of the second portion in a second cross section orthogonal to the blade height direction is larger than an area surrounded by an outer edge of the first portion in a first cross section orthogonal to the blade height direction.SELECTED DRAWING: Figure 3

Description

Technical Field

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

Background Art

[0002] It has been proposed to efficiently cool a turbine blade having a cooling passage provided inside a blade body.

[0003] For example, Patent Document 1 discloses a turbine blade including a blade body having a base portion and an end portion, and a structure provided in a base portion side portion of the blade body of cooling passages extending in the blade height direction inside the blade body. By providing the structure on the base side where the flow passage area of the cooling passage is relatively large, the flow velocity of the cooling fluid is increased on the base side to increase the heat transfer rate, so that the turbine blade can be efficiently cooled.

Prior Art Documents

Patent Documents

[0004]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0005] The turbine blade disclosed in Patent Document 1 has a relatively complex structure because a new structure is provided in the cooling passage formed inside the blade body for efficient cooling of the turbine blade.

[0006] In view of the above circumstances, at least one embodiment of the present invention aims to provide a turbine stator blade and a gas turbine capable of effectively and efficiently cooling the turbine stator blade while suppressing complication of the structure.

Means for Solving the Problems

[0007] The turbine stator blade according to at least one embodiment of the present invention is A wing body having an outer end and an inner end in the wing height direction, A cooling passage extending along the height direction of the wing body is provided inside the wing body, An outer shroud connected to the wing body at the outer end of the wing body in the wing height direction, An inner shroud connected to the wing body at the inner end side of the wing body in the wing height direction, The cooling passage includes an internal flow path forming section that extends along the blade height direction, Equipped with, The internal flow channel forming section forms internal flow channels that communicate with the outer space on the opposite side of the wing body, across the outer shroud, and with the inner space on the opposite side of the wing body, across the inner shroud. The internal flow channel forming portion has a first portion and a second portion located closer to the outer end than the first portion in the wing height direction, The area enclosed by the outer edge of the second portion within a second cross-section perpendicular to the wing height direction is larger than the area enclosed by the outer edge of the first portion within a first cross-section perpendicular to the wing height direction.

[0008] Furthermore, a gas turbine according to at least one embodiment of the present invention is The turbine including the turbine stator blades described above, A combustor for generating combustion gas that flows through a combustion gas passage on which the turbine stator blades are provided, It is equipped with. [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 enable effective and efficient cooling of the turbine stator blade while suppressing structural complexity. [Brief explanation of the drawing]

[0010] [Figure 1] This is a schematic diagram of a gas turbine according to one embodiment. [Figure 2]It is a partial schematic view of a turbine including stator blades according to an embodiment. [Figure 3] It is a schematic partial cross-sectional view along the blade height direction of the stator blade shown in FIG. 2. [Figure 4A] It is a view showing the cross section A-A of FIG. 3. [Figure 4B] It is a view showing the cross section B-B of FIG. 3. [Figure 4C] It is a view showing the cross section C-C of FIG. 3. [Figure 5] It is a schematic view showing the leading edge side and radially outer portion of the stator blade according to an embodiment. [Figure 6] It is a schematic view showing the leading edge side and radially outer portion of the stator blade according to an embodiment. [Figure 7] It is a schematic view showing the leading edge side and radially outer portion of the stator blade according to an embodiment. [Figure 8] It is a schematic view showing the leading edge side and radially outer portion of the stator blade according to an embodiment.

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) First, a gas turbine to which the turbine stator blades according to some embodiments are applied will be described. FIG. 1 is a schematic configuration diagram of a gas turbine to which the turbine blades according to an embodiment are applied. 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.

[0013] The compressor 2 includes a plurality of stationary blades 16 fixed to the side of the compressor compartment 10, and a plurality of moving blades 18 implanted in the rotor 8 so as to be alternately arranged with respect to the stationary blades 16. Air taken in from the air intake 12 is sent to the compressor 2, and this air passes through the plurality of stationary blades 16 and the plurality of moving blades 18 and is compressed to become high-temperature and high-pressure compressed air.

[0014] The combustor 4 is 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 in the combustor compartment 20.

[0015] The turbine 6 has a combustion gas flow path 28 formed in the turbine compartment 22 and includes a plurality of stationary blades 24 and moving blades 26 provided in the combustion gas flow path 28. The stationary blades 24 are fixed to the side of the turbine compartment 22, 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.

[0016] In the turbine 6, the combustion gas 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, whereby the rotor 8 is rotationally driven, and thereby, 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.

[0017] (Configuration of Turbine Stationary Blades) The following describes the stator blades 24 (turbine stator blades) of a turbine 6 according to several embodiments. Figure 2 is a partial schematic diagram of a turbine 6 including a stator blade 24 according to one embodiment, and Figure 3 is a schematic partial cross-sectional view of the stator blade 24 shown in Figure 2 along the blade height direction. Figures 4A to 4C show the AA, BB, and CC cross-sections of Figure 3, respectively. In the figures, "radial direction," "axial direction," and "circumferential direction" refer to the radial, axial, and circumferential directions of the turbine 6 (or turbine rotor), respectively.

[0018] As shown in Figures 2 to 4C, a stator blade 24 according to one embodiment comprises a blade body 40 and an outer shroud 62 and an inner shroud 64 connected to both ends of the blade body 40 in the blade height direction. Here, the blade height direction of the stator blade 24 (i.e., the blade height direction of the blade body 40) corresponds to the radial direction of the turbine rotor on which the stator blade 24 is installed. When the stator blade 24 is installed on the turbine 6, the outer shroud 62 is located radially outward relative to the blade body 40, and the inner shroud 64 is located radially inward relative to the blade body 40.

[0019] The wing body 40 has an outer end 42 and an inner end 44, which are the ends in the wing height direction. The outer end 42 is the radially outer end of the wing body 40, and the inner end 44 is the radially inner end of the wing body 40. The wing body 40 has a leading edge 46 and a trailing edge 48 that extend along the wing height direction from the outer end 42 to the inner end 44. The wing surface of the wing body 40 includes a pressure surface (ventral surface) 50 and a negative pressure surface (back surface) 52 that extend along the wing height direction between the outer end 42 and the inner end 44 (see Figures 4A to 4C). The pressure surface 50 and the negative pressure surface 52 are connected at the leading edge 46 and the trailing edge 48.

[0020] The outer shroud 62 is connected to the blade body 40 at the outer end 42 side of the blade body 40 in the blade height direction. The outer shroud 62 is supported by the turbine casing 22 (see Figure 1), and the stator blades 24 are supported by the turbine casing 22 via the outer shroud 62. An outer space 63 is formed on the opposite side of the outer shroud 62 from the blade body 40. The outer space 63 is at least partially defined by the outer shroud 62.

[0021] The inner shroud 64 is connected to the blade body 40 at the inner end 44 side of the blade body 40 in the blade height direction. On the side of the inner shroud 64 opposite to the blade body 40 in the blade height direction, a seal ring retaining ring 66 is provided for holding a seal ring 68. The seal ring 68 is provided to suppress fluid leakage between the rotor 8 and the stator blades 24. An inner space 65 is formed on the side of the inner shroud 64 opposite to the blade body 40. The inner space 65 is at least partially defined by the inner shroud 64 and the seal ring retaining ring 66.

[0022] A cooling passage 54 is provided inside the wing body 40, extending along the wing height direction. The cooling passage 54 is configured to allow a cooling fluid F1 (e.g., air) to flow through it to cool the stator vane 24.

[0023] In some embodiments, for example, as shown in Figures 2 to 4, a plurality of cooling passages 54 (54A, 54B) may be provided inside the wing body 40 (two in Figures 2 to 4C). As shown in Figures 2 to 4C, a pair of adjacent cooling passages 54 (cooling passage 54A and cooling passage 54B) may be separated by a rib 56 extending along the wing height direction.

[0024] As shown in Figures 2 to 4C, a plurality of cooling passages 54 (54A, 54B) may be connected to each other via folded-back portions 53 located at the ends of the plurality of cooling passages 54 in the blade height direction to form a serpentine flow path (a meandering flow path). In this case, a return flow path is formed at the folded-back portion 53 in which the direction of the cooling fluid flow is reversed in the blade height direction.

[0025] As shown in Figures 2 to 4C, the multiple cooling passages 54 (54A, 54B) may be arranged along the chord direction of the blade body 40 (the direction connecting the leading edge 46 and the trailing edge 48). In the illustrated embodiment, the multiple cooling passages 54A, 54B are arranged in this order from the leading edge 46 to the trailing edge 48 in the chord direction. Of the multiple cooling passages 54, the cooling passage 54 located closest to the leading edge 46 in the chord direction (cooling passage 54A in the illustrated embodiment) is the foremost edge passage.

[0026] The cooling fluid F1 may be introduced into the cooling passage 54 from the outer space 63. The cooling fluid may also be supplied to the outer space 63 via a path not shown. In the illustrated embodiment, the cooling fluid F1 from the outer space 63 is introduced into the cooling passage 54A via a passage 58 provided in the outer shroud 62, flows along the blade height direction in the cooling passage 54A, and flows into the cooling passage 54B via the return section 53. The cooling fluid F1 flowing through the cooling passage 54B may be discharged into the combustion gas passage 28 via a cooling hole 60 provided at the trailing edge of the blade body 40.

[0027] As shown in Figures 2 to 4C, the stator vane 24 includes an internal flow path forming section 70 that extends along the vane height direction within the cooling passage 54. In the illustrated embodiment, the internal flow path forming section 70 is provided to extend within the cooling passage 54A. In the illustrated embodiment, the internal flow path forming section 70 is provided to extend along the vane height direction.

[0028] The internal flow path forming section 70 forms internal flow paths 69 that communicate with the outer space 63 and the inner space 65, respectively. In the illustrated embodiment, the internal flow path forming section 70 has an inlet opening 70a and an outlet opening 70b that open at both ends of the internal flow path forming section 70, and the internal flow path 69 extends between the inlet opening 70a and the outlet opening 70b. The internal flow path 69 communicates with the outer space 63 via the inlet opening 70a and with the inner space 65 via the outlet opening 70b. As a result, fluid F2 from the outer space 63 is guided to the inner space 65 via the internal flow path 69. This fluid F2 may be a sealing fluid to suppress the intrusion of fluid (combustion gas, etc.) from the combustion gas flow path 28 into the inner space 65. Note that the cooling fluid F1 and the fluid F2 may be supplied from the same fluid source. As shown in the illustration, the internal flow path forming section 70 may be provided so as to penetrate the blade body 40.

[0029] The internal flow channel forming portion 70 described above has a first portion 72 and a second portion 74 located closer to the outer end 42 than the first portion 72 in the wing height direction. The area enclosed by the outer edge 71 of the second portion 74 in a cross section perpendicular to the wing height direction (second cross section, for example, AA cross section (see Figure 4A)) is larger than the area enclosed by the outer edge 71 of the first portion 72 in a cross section perpendicular to the wing height direction (first cross section, for example, BB cross section (see Figure 4B)).

[0030] In other words, the internal flow path forming portion 70 has a second portion 74 that is located closer to the outer end 42 in the wing height direction (radially outward) compared to the first portion 72, and has a locally larger area surrounded by the outer edge 71. For example, the area surrounded by the outer edge 71 of the second portion 74 within the second cross-section may be more than twice the area surrounded by the outer edge 71 of the first portion 72 within the first cross-section.

[0031] The first cross-section is the cross-section within the range where the first portion exists in the wing height direction, and the second cross-section is the cross-section within the range where the second portion exists in the wing height direction. The second cross-section is located radially outward from the first cross-section.

[0032] In the above-described embodiment, fluid F2 (seal fluid) can flow from the outer space 63 to the inner space 65 through the internal flow path 69 formed by the internal flow path forming portion 70. That is, the internal flow path forming portion 70 can function as a seal tube. Furthermore, in the above-described embodiment, the area surrounded by the outer edge 71 of the second portion 74 within the cross section perpendicular to the blade height direction (second cross section) is larger than the area surrounded by the outer edge 71 of the first portion 72 within the cross section perpendicular to the blade height direction (first cross section). Therefore, the flow area of ​​the cooling fluid F1 flowing through the cooling passage 54A (effective cross-sectional area of ​​the cooling passage 54A) tends to be relatively large on the outer end 42 side (radially outward) in the blade height direction and relatively small on the inner end 44 side (radially inward). Therefore, the flow velocity of the cooling fluid F1 can be increased at the outer end 42 where the cooling load is relatively high, thereby increasing the heat transfer coefficient between the cooling fluid F1 and the stator vane 24 at the outer end 42, while the increase in the flow velocity of the cooling fluid F1 can be suppressed at the inner end 44 where the cooling load is relatively low, reducing the pressure loss of the cooling fluid F1 and thus reducing the supply pressure (supply amount) of the cooling fluid F1. As a result, the stator vane 24 can be cooled effectively and efficiently. Therefore, according to the above embodiment, by utilizing the internal flow path forming section 70, the stator vane 24 can be cooled effectively and efficiently while suppressing structural complexity.

[0033] Furthermore, the turbine's stator blades 24 tend to get hotter in the radially outer portion, which can lead to increased stress on this portion. In this case, as described above, the cooling load on the radially outer portion of the stator blades 24 (the portion near the outer end 42) becomes higher.

[0034] In some embodiments, the effective cross-sectional area of ​​the cooling passage 54 (a cooling passage in which an internal flow path forming section 70 is provided; in the illustrated example, the cooling passage 54A) within the second cross-section described above is smaller than the effective cross-sectional area of ​​the cooling passage 54 within the first cross-section described above. Here, the effective cross-sectional area of ​​the cooling passage 54(54A) is the flow area of ​​the cooling fluid F1 flowing through the cooling passage 54(54A), and is the difference (Sa-Sb) between the area Sa surrounded by the inner wall surface 55 of the cooling passage 54(54A) (see Figures 4A-4C) and the area Sb surrounded by the outer edge 71 of the internal flow path forming section within a cross-section (first cross-section or second cross-section, etc.) perpendicular to the blade height direction.

[0035] In other words, in the cooling passage 54 (54A) where the internal flow path forming section 70 is provided, there is a region with a locally large effective cross-sectional area, and this region is the area where the second portion 74 of the internal flow path forming section 70 is located in the blade height direction (i.e., a region located relatively radially outward).

[0036] According to the above embodiment, the effective cross-sectional area of ​​the cooling passage 54 in the second cross-section located on the outer end 42 side (radially outward) is smaller than the effective cross-sectional area of ​​the cooling passage 54 in the first cross-section located on the inner end 44 side (radially inward). Therefore, the flow velocity of the cooling fluid F1 can be increased on the outer end 42 side where the cooling load is relatively high, thereby increasing the heat transfer coefficient between the cooling fluid F1 and the stator vane 24 on the outer end 42 side, while suppressing the increase in the flow velocity of the cooling fluid F1 on the inner end 44 side where the cooling load is relatively low, thereby reducing the pressure loss of the cooling fluid F1 and reducing the supply pressure (supply amount) of the cooling fluid F1. Therefore, as described above, the stator vane 24 can be cooled effectively and efficiently while suppressing structural complexity.

[0037] In some embodiments, as shown in Figures 2 to 4C, for example, the internal flow path forming section 70 extends inside the leading edge side passage (cooling passage 54A) which is located furthest towards the leading edge 46 in the cord direction among the multiple cooling passages 54.

[0038] In the stator blades 24 of the turbine 6, the temperature tends to rise near the leading edge 46 during the operation of the turbine 6. In this regard, according to the above embodiment, the internal flow path forming section 70 is provided so as to extend inside the leading edge side passage (cooling passage 54A), which is located closest to the leading edge among the multiple cooling passages 54 provided inside the blade body 40. Therefore, the stator blades 24 can be cooled more effectively.

[0039] Here, the average position Pin of the inner edge 44 in the wing height direction is defined as 0% in the wing height direction, and the average position Pout of the outer edge 42 in the wing height direction is defined as 100% in the wing height direction (see Figure 3). The average position Pin of the inner edge 44 in the wing height direction is the arithmetic mean of the innermost radial position Pin_1 and the outermost radial position Pin_2 of the inner edge 44 (Pin_1 + Pin_2) / 2. The average position Pout of the outer edge 42 in the wing height direction is the arithmetic mean of the innermost radial position Pout_1 and the outermost radial position Pout_2 of the outer edge 42 (Pout_1 + Pout_2) / 2.

[0040] In some embodiments, the first portion 72 of the internal flow channel forming portion 70 extends in the wing height direction within a range that includes the position at 50% of the wing height direction.

[0041] According to the above embodiment, since the first portion 72 of the internal flow path forming portion 70 extends within a range that includes the position at 50% of the blade height in the blade height direction, the second portion 74 is located closer to the outer end 42 where the blade height direction position is greater than 50%. Therefore, the flow velocity of the cooling fluid F1 can be effectively increased on the outer end 42 side where the cooling load is relatively high, thereby effectively increasing the heat transfer coefficient between the cooling fluid F1 and the stator blade 24 on the outer end 42 side, while suppressing the increase in the flow velocity of the cooling fluid F1 in the region on the inner end 44 side where the cooling load is relatively low (the region including the position at 50% of the blade height direction), thereby reducing the pressure loss of the cooling fluid F1 and reducing the supply pressure (supply amount) of the cooling fluid F1.

[0042] In some embodiments, the second portion 74 of the internal flow path forming section 70 is at least partially provided within a position range of 75% to 100% in the wing height direction. In the exemplary embodiment shown in Figure 3, the second portion 74 is partially provided within a position range of 75% to 100% in the wing height direction.

[0043] According to the above-described embodiment, the second portion 74 of the internal flow path forming portion 70 is at least partially provided within a position range of 75% to 100% in the blade height direction. This effectively increases the flow velocity of the cooling fluid F1 on the outer end 42 side where the cooling load is relatively high, thereby effectively increasing the heat transfer coefficient between the cooling fluid F1 and the stator blade 24 on the outer end 42 side, while suppressing the increase in the flow velocity of the cooling fluid F1 on the inner end 44 side where the cooling load is relatively low, thereby reducing the pressure loss of the cooling fluid F1 and reducing the supply pressure (supply amount) of the cooling fluid F1.

[0044] In some embodiments, as shown in Figure 3 for example, the first portion 72 includes a portion of the internal flow path forming portion 70 whose position in the wing height direction is 0% or more and 50% or less.

[0045] According to the embodiment described above, the first portion 72 includes the portion of the internal flow path forming portion 70 whose position in the blade height direction is 0% or more and 50% or less. That is, since the first portion 72 is the majority of the internal flow path forming portion 70 on the inner end 44 side, the increase in the flow velocity of the cooling fluid F1 is suppressed in the majority of the inner end 44 side of the cooling passage 54, thereby reducing the pressure loss of the cooling fluid F1 and effectively reducing the supply pressure (supply amount) of the cooling fluid.

[0046] Figures 5 to 8 are schematic diagrams showing the leading edge and radially outer portion of the stator vane 24 according to one embodiment. Note that the outer shroud 62 is not shown in Figures 5 to 8.

[0047] In the exemplary embodiments shown in Figures 5 and 6, the internal flow channel forming section 70 includes a tubular member 80 extending along the wing height direction between the outer end 42 and the inner end 44 (see Figure 3). The first section 72 and the second section 74 are formed by a single tubular member 80.

[0048] In the exemplary embodiments shown in Figures 7 and 8, the internal flow path forming section 70 includes a tubular member 82 extending along the wing height direction between an outer end 42 and an inner end 44 (see Figure 3), and a cover member 84 covering a portion of the tubular member 82 in the wing height direction from the surroundings. The first section 72 is formed by the tubular member 82. The second section 74 is formed by the tubular member 82 and the cover member 84. That is, the second section 74 includes the cover member 84. The outer edge 71 of the second section 74 (see Figure 4A) is formed by the cover member 84.

[0049] According to the exemplary embodiments shown in Figures 5 to 8, the internal flow path forming portion 70, including the first portion 72 and the second portion 74, can be formed by the tubular member 80, or by the tubular member 82 and the cover member 84. Thus, the stator vane 24 including the above-mentioned internal flow path forming portion 70 can be realized with a simple configuration.

[0050] In some embodiments, as shown in Figures 6 and 8, for example, a connecting portion 76 may be provided between the first portion 72 and the second portion 74, connecting the first portion 72 and the second portion 74. As shown in Figures 6 and 7, the connecting portion 76 may be a portion in which the size of the outer edge 71 (or the area enclosed by the outer edge 71 in a cross section perpendicular to the blade height direction; see Figures 4A to 4C) gradually increases as it approaches the second portion 74 from the first portion 72. In this case, since the effective cross-sectional area of ​​the cooling passage 54 (54A) changes gradually, the flow of the cooling fluid F1 along the internal flow path forming portion 70 in the cooling passage 54 (54A) becomes smoother, and the stator blade 24 can be cooled more efficiently.

[0051] The contents described in each of the above embodiments can be understood, for example, as follows:

[0052] (1) A turbine stator blade (24) according to at least one embodiment of the present invention is A wing body (40) having an outer end (42) and an inner end (44) in the wing height direction, A cooling passage (54) extending along the height direction of the wing body is provided inside the wing body, An outer shroud (62) connected to the wing body at the outer end of the wing body in the wing height direction, An inner shroud (64) connected to the wing body at the inner end side of the wing body in the wing height direction, The cooling passage includes an internal flow path forming portion (70) that extends along the blade height direction, Equipped with, The internal flow channel forming section forms an internal flow channel (69) that communicates with the outer space (63) on the opposite side of the wing body, sandwiching the outer shroud, and with the inner space (65) on the opposite side of the wing body, sandwiching the inner shroud. The internal flow channel forming portion has a first portion (72) and a second portion (74) located closer to the outer end than the first portion in the wing height direction, The area enclosed by the outer edge (71) of the second portion within the second cross-section perpendicular to the wing height direction is larger than the area enclosed by the outer edge (71) of the first portion within the first cross-section perpendicular to the wing height direction.

[0053] In the configuration of (1) above, sealing fluid can flow from the outer space to the inner space through the internal flow path formed by the internal flow path forming section. In other words, the internal flow path forming section can function as a sealing tube. Furthermore, in the configuration of (1) above, the area surrounded by the outer edge of the second part within the second cross section perpendicular to the blade height direction is larger than the area surrounded by the outer edge of the first part within the first cross section. Therefore, the flow area of ​​the cooling fluid flowing through the cooling passage (effective cross-sectional area of ​​the cooling passage) tends to be relatively large on the outer end side (radially outward) in the blade height direction and relatively small on the inner end side (radially inward). Thus, the flow velocity of the cooling fluid can be increased on the outer end side where the cooling load is relatively high, thereby increasing the heat transfer coefficient between the cooling fluid and the turbine stator blades on the outer end side, while the increase in the flow velocity of the cooling fluid can be suppressed on the inner end side where the cooling load is relatively low, reducing the pressure loss of the cooling fluid and thus reducing the supply pressure (supply amount) of the cooling fluid. Thus, the turbine stator blades can be cooled effectively and efficiently. Therefore, according to the configuration of (1) above, the turbine stator blades can be cooled effectively and efficiently while suppressing structural complexity by utilizing the internal flow path forming section.

[0054] (2) In some embodiments, in the configuration of (1) above, The effective cross-sectional area of ​​the cooling passage within the second cross-section is smaller than the effective cross-sectional area of ​​the cooling passage within the first cross-section.

[0055] According to the configuration described in (2) above, the effective cross-sectional area of ​​the cooling passage in the second cross-section located on the outer end side (radially outward) is smaller than the effective cross-sectional area of ​​the cooling passage in the first cross-section located on the inner end side (radially inward). Therefore, the flow velocity of the cooling fluid can be increased on the outer end side where the cooling load is relatively high, thereby increasing the heat transfer coefficient between the cooling fluid and the turbine stator blades on the outer end side, while the increase in the flow velocity of the cooling fluid can be suppressed on the inner end side where the cooling load is relatively low, thereby reducing the pressure loss of the cooling fluid and reducing the supply pressure (supply amount) of the cooling fluid. Therefore, as described in (1) above, the turbine stator blades can be cooled effectively and efficiently while suppressing structural complexity.

[0056] (3) In some embodiments, in the configuration of (1) or (2) above, The turbine stator blades are The wing body is provided with a plurality of cooling passages extending along the wing height direction, The internal flow path forming portion extends inside the leading edge side passage (for example, the cooling passage 54A described above) that is located furthest towards the leading edge (46) in the chord direction of the blade body among the plurality of cooling passages.

[0057] In turbine stator blades, the temperature tends to rise near the leading edge during turbine operation. In this regard, according to the configuration of (3) above, the internal flow path forming section is provided so as to extend within the leading edge passage, which is the closest to the leading edge among the multiple cooling passages provided inside the blade body. Therefore, the turbine stator blades can be cooled more effectively.

[0058] (4) In some embodiments, in any of the configurations (1) to (3) above, When the average position of the inner end in the wing height direction is defined as 0% in the wing height direction, and the average position of the outer end in the wing height direction is defined as 100% in the wing height direction, the first portion extends within a range that includes the position of 50% in the wing height direction.

[0059] According to the configuration of (4) above, the first part of the internal flow path forming section extends within a range that includes the position at 50% of the blade height in the blade height direction, so the second part is located closer to the outer end where the blade height position is greater than 50%. Therefore, the flow velocity of the cooling fluid can be effectively increased at the outer end where the cooling load is relatively high, thereby effectively increasing the heat transfer coefficient between the cooling fluid and the turbine stator blade at the outer end, while the increase in the flow velocity of the cooling fluid can be suppressed in the region at the inner end where the cooling load is relatively low (the region including the position at 50% of the blade height direction), thereby reducing the pressure loss of the cooling fluid and reducing the supply pressure (supply amount) of the cooling fluid. Therefore, as described in (1) above, the turbine stator blade can be cooled effectively and efficiently while suppressing structural complexity.

[0060] (5) In some embodiments, in any of the configurations (1) to (4) above, When the average position of the inner end in the wing height direction is set to 0%, and the average position of the outer end in the wing height direction is set to 100%, the second portion is at least partially provided within a position range of 75% or more and 100% or less in the wing height direction.

[0061] According to the configuration of (5) above, the second portion of the internal flow path forming section is at least partially provided within a position range of 75% to 100% of the blade height direction. This effectively increases the flow velocity of the cooling fluid at the outer end where the cooling load is relatively high, thereby effectively increasing the heat transfer coefficient between the cooling fluid and the turbine stator blades at the outer end. At the same time, it suppresses the increase in the flow velocity of the cooling fluid at the inner end where the cooling load is relatively low, reducing the pressure loss of the cooling fluid and thus reducing the supply pressure (supply amount) of the cooling fluid. Therefore, as described in (1) above, the turbine stator blades can be cooled effectively and efficiently while suppressing structural complexity.

[0062] (6) In some embodiments, in the configuration of (5) above, The first portion includes the portion of the internal flow path forming section whose position in the blade height direction is 0% or more and 50% or less.

[0063] According to the configuration in (6) above, the first part includes the portion of the internal flow path forming section whose position in the blade height direction is 0% or more and 50% or less. In other words, since the first part comprises most of the inner end side of the internal flow path forming section, the increase in the flow velocity of the cooling fluid is suppressed in most of the inner end side of the cooling passage, thereby reducing the pressure loss of the cooling fluid and effectively reducing the supply pressure (supply amount) of the cooling fluid. Therefore, as described in (1) above, the turbine stator blades can be cooled effectively and efficiently while suppressing structural complexity.

[0064] (7) In some embodiments, in any of the configurations (1) to (6) above, The internal flow channel forming section is A tubular member (82) extending along the wing height direction between the outer end and the inner end, A cover member (84) that covers a portion of the tubular member in the wing height direction from the surroundings, Includes, The second portion includes the cover member.

[0065] According to the configuration of (7) above, the tubular member and the cover member can form an internal flow path forming section including the first and second parts. Therefore, the configuration of (1) above can be realized with a simple configuration.

[0066] (8) In some embodiments, in the configuration of (1) to (7) above, The turbine stator blades are The seal ring retaining ring (80) is provided on the side opposite to the wing body, sandwiching the inner shroud in the wing height direction, and together with the inner shroud, forms the inner space. The internal channel forming section is configured to guide the sealing fluid from the outer space into the inner space via the internal channel.

[0067] According to the configuration of (8) above, sealing fluid from the outer space can be guided into the inner space through the internal flow path formed by the internal flow path forming section. In other words, the internal flow path forming section functions as a sealing tube. Therefore, according to the configuration of (8) above, the turbine stator blade having the internal flow path forming section can be cooled effectively and efficiently.

[0068] (9) A gas turbine (1) according to at least one embodiment of the present invention is A turbine (6) including a turbine stator blade (24) as described in any one of the above items (1) to (8), A combustor (4) for generating combustion gas that flows through the combustion gas passage (28) on which the turbine stator blades are provided, It is equipped with.

[0069] In the configuration of (9) above, sealing fluid can flow from the outer space to the inner space through the internal flow path formed by the internal flow path forming section. In other words, the internal flow path forming section can function as a sealing tube. Furthermore, in the configuration of (9) above, the area surrounded by the outer edge of the second part within the second cross section perpendicular to the blade height direction is larger than the area surrounded by the outer edge of the first part within the first cross section. Therefore, the flow area of ​​the cooling fluid flowing through the cooling passage (effective cross-sectional area of ​​the cooling passage) tends to be relatively large on the outer end side (radially outward) in the blade height direction and relatively small on the inner end side (radially inward). Thus, the flow velocity of the cooling fluid can be increased on the outer end side where the cooling load is relatively high, thereby increasing the heat transfer coefficient between the cooling fluid and the turbine stator blades on the outer end side, while the increase in the flow velocity of the cooling fluid can be suppressed on the inner end side where the cooling load is relatively low, reducing the pressure loss of the cooling fluid and thus reducing the supply pressure (supply amount) of the cooling fluid. Thus, the turbine stator blades can be cooled effectively and efficiently. Therefore, according to the configuration of (9) above, the turbine stator blades can be cooled effectively and efficiently while suppressing structural complexity by utilizing the internal flow path forming section.

[0070] 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.

[0071] 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]

[0072] 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 24 Static Wing 26 Moving blade 28 Combustion gas flow path 30 Exhaust chamber 40 Wing body 42 Outer edge 44 Inner edge 46 Leading edge 48 Trailing edge 50 Pressure surface 52 Suction surface 53 Folded section 54,54A,54B Cooling passage 55 Interior wall surface 56 Ribs 58 aisle 60 cooling holes 62 Outer shroud 63 Outside space 64 Inner shroud 65 Interior space 66 Seal ring retaining ring 68 Seal rings 69 Internal flow path 70 Internal flow channel forming section 70a Entrance opening 70b Exit opening 71 Outer edge 72 Part 1 74 Part 2 76 Connection part 80 Tubular member 82 Tubular member 84 Cover component F1 cooling fluid F2 Fluid (Sealing Fluid)

Claims

1. A wing body having an outer end and an inner end in the wing height direction, A cooling passage extending along the height direction of the wing body is provided inside the wing body, An outer shroud connected to the wing body at the outer end of the wing body in the wing height direction, An inner shroud connected to the wing body at the inner end side of the wing body in the wing height direction, The cooling passage includes an internal flow path forming section that extends along the blade height direction, Equipped with, The internal flow channel forming section forms internal flow channels that communicate with the outer space on the opposite side of the wing body, across the outer shroud, and with the inner space on the opposite side of the wing body, across the inner shroud. The internal flow channel forming section is Part 1 and, The wing has a second portion located closer to the outer end than the first portion in the wing height direction, The area enclosed by the outer edge of the second portion within a second cross-section perpendicular to the wing height direction is larger than the area enclosed by the outer edge of the first portion within a first cross-section perpendicular to the wing height direction. The first portion includes the portion of the internal flow path forming section whose position in the blade height direction is 0% or more and 50% or less. Turbine stator blades.

2. The effective cross-sectional area of ​​the cooling passage within the second cross-section is smaller than the effective cross-sectional area of ​​the cooling passage within the first cross-section. The turbine stator blade according to claim 1.

3. The wing body is provided with a plurality of cooling passages extending along the wing height direction, The internal flow path forming portion extends within the leading edge passage, which is located furthest to the leading edge in the chord direction of the blade body, among the plurality of cooling passages. The turbine stator blade according to claim 1 or 2.

4. When the average position of the inner end in the wing height direction is defined as 0% in the wing height direction, and the average position of the outer end in the wing height direction is defined as 100% in the wing height direction, the first portion extends within a range that includes the position of 50% in the wing height direction. The turbine stator blade according to claim 1 or 2.

5. When the average position of the inner end in the wing height direction is set to 0%, and the average position of the outer end in the wing height direction is set to 100%, the second portion is at least partially provided within a position range of 75% or more and 100% or less in the wing height direction. The turbine stator blade according to claim 1 or 2.

6. The second portion extends in the wing height direction to the outer shroud. The turbine stator blade according to claim 1 or 2.

7. The area enclosed by the outer edge of the second portion within the second cross-section is at least twice the area enclosed by the outer edge of the first portion within the first cross-section. The turbine stator blade according to claim 6.

8. The internal flow channel forming section is A tubular member extending along the wing height direction between the outer end and the inner end, A cover member that covers a portion of the tubular member in the wing height direction from the surroundings, Includes, The second portion includes the cover member. The turbine stator blade according to claim 1 or 2.

9. The seal ring retaining ring is provided on the side opposite to the wing body, sandwiching the inner shroud in the wing height direction, and together with the inner shroud, forms the inner space. The internal channel forming section is configured to guide the sealing fluid from the outer space into the inner space via the internal channel. The turbine stator blade according to claim 1 or 2.

10. A turbine including turbine stator blades according to claim 1 or 2, A combustor for generating combustion gas that flows through a combustion gas passage on which the turbine stator blades are provided, A gas turbine characterized by being equipped with

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