Turbine blades

Abstract

A turbine rotor blade according to at least one embodiment of the present disclosure comprises a blade root in which a first internal passage extending in a blade height direction is formed and a first opening on one-end side of the first internal passage is formed at the bottom, and an adjustment member attached to the bottom and having formed therein a first through hole overlapping the first opening when viewed from the blade height direction. The first through hole intersects with the first opening when viewed from the blade height direction, and has a first overlapping area that overlaps the first opening and a first non-overlapping area that does not overlap the first opening.

Description

[Technical Field]

[0001] The present disclosure relates to turbine blades. This application claims priority based on Japanese Patent Application No. 2022-006475, filed with the Japan Patent Office on January 19, 2022, the contents of which are incorporated herein by reference. [Background technology]

[0002] In gas turbine systems for aircraft and industrial applications, high-pressure air compressed in a compressor is mixed with fuel in a combustor and combusted to generate high-temperature, high-pressure combustion gases, which are used as a working medium to drive a turbine and convert thermal energy into kinetic energy. Therefore, the surfaces of turbine blades are exposed to the high-temperature working medium. Furthermore, in recent years, combustion temperatures have risen to improve the thermal efficiency of gas turbines, creating increasingly severe temperature environments for the blades. For this reason, convection cooling, film cooling, and other cooling methods are used to prevent high-temperature corrosion of the blade material and a decrease in structural strength (see, for example, Patent Document 1). [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Patent No. 5953136 Summary of the Invention [Problem to be solved by the invention]

[0004] For example, in the turbine rotor blade described in Patent Document 1, the flow rate of cooling air supplied to a cooling flow passage, which is an internal passage inside the blade, can be adjusted by an orifice at the bottom of the blade root. However, because turbine blades are manufactured by casting, misalignment between the internal passage and the orifice opening is relatively likely to occur, which may result in an unintended reduction in the overlap area between the internal passage opening and the orifice opening when viewed from the blade height direction, making it difficult to obtain the desired cooling air flow rate.

[0005] In view of the above circumstances, at least one embodiment of the present disclosure has an object to provide a turbine rotor blade that can supply a desired flow rate of cooling air to the interior of the blade. [Means for solving the problem]

[0006] Book In accordance with at least one embodiment of the disclosure, a turbine blade comprises: a blade root having a first internal passage extending in the blade height direction and a first opening at one end of the first internal passage formed at a bottom thereof; a first through hole attached to the bottom and overlapping with the first opening when viewed from the blade height direction; Plate-shaped An adjustment member; Equipped with When viewed from the blade height direction, the first through hole intersects with the first opening and has a first overlapping region that overlaps with the first opening and a first non-overlapping region that does not overlap with the first opening. death, The first through hole is When viewed from the blade height direction, the opening is larger than the first opening in a first direction, the first non-overlapping region is provided on one side and the other side in the first direction, When viewed from the blade height direction, the first through hole is defined by a first side extending along the first direction, a second side spaced apart from the first side in a second direction intersecting the first direction and parallel to the first side, a first edge portion extending along the second direction, and a second edge portion spaced apart from the first edge portion in the first direction and parallel to the first edge portion, The direction from the opening on one side in the blade height direction of the first through hole to the opening on the other side in the blade height direction coincides with the plate thickness direction of the adjustment member. do. [Effects of the Invention]

[0007] In accordance with at least one embodiment of the present disclosure, a desired flow rate of cooling air can be supplied to the interior of the blade. [Brief explanation of the drawings]

[0008] [Figure 1] 1 is an internal cross-sectional view of an example turbine blade according to some embodiments. [Figure 2] FIG. 2 is an internal cross-sectional view of another example of a turbine blade according to some embodiments. [Figure 3] FIG. 2 is a schematic diagram of an adjustment member according to one embodiment, viewed along the blade height direction from the blade root side toward the blade tip side. [Figure 4A]FIG. 2 is a schematic diagram of a first through hole and a first opening according to one embodiment, viewed along the blade height direction from the blade root side toward the tip side of the blade body. [Figure 4B] FIG. 10 is a schematic diagram of a first through hole and a first opening according to another embodiment, viewed along the blade height direction from the blade root side toward the tip side of the blade body. [Figure 5A] 10 is a diagram for explaining a case where the area of ​​the through hole and the area of ​​the internal passage opening are relatively close to each other. FIG. [Figure 5B] 10 is a diagram for explaining a case where the area of ​​the through hole and the area of ​​the internal passage opening are relatively close to each other. FIG. [Figure 6] 10A and 10B are diagrams showing other examples of through holes and internal passage openings. DETAILED DESCRIPTION OF THE INVENTION

[0009] Hereinafter, several embodiments of the present disclosure will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of components described as embodiments or shown in the drawings are merely illustrative examples and are not intended to limit the scope of the present disclosure. For example, expressions expressing relative or absolute arrangement such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" not only express such an arrangement exactly, but also express a state in which there is a relative displacement with a tolerance or an angle or distance to the extent that the same function is obtained. For example, expressions such as "identical," "equal," and "homogeneous" that indicate that something is in an equal state not only indicate a state of strict equality, but also indicate a state in which there is a tolerance or a difference to the extent that the same function is obtained. For example, expressions representing shapes such as a square shape or a cylindrical shape not only represent shapes such as a square shape or a cylindrical shape in the strict geometric sense, but also represent shapes including uneven portions, chamfered portions, etc., to the extent that the same effect can be obtained. On the other hand, the expressions "comprise," "include," "have," "includes," or "have" of one element are not exclusive expressions that exclude the presence of other elements.

[0010] (Outline of turbine blades) The cooling structure of a turbine rotor blade according to some embodiments of the present disclosure is shown in Figures 1 and 2. Figure 1 is an internal cross-sectional view of one example of a turbine rotor blade according to some embodiments, showing a cross section along the blade height direction. Figure 2 is an internal cross-sectional view of another example of a turbine rotor blade according to some embodiments, showing a cross section along the blade height direction.

[0011] The turbine rotor blade 50 according to some embodiments is a turbine rotor blade for a gas turbine, and includes a blade body 81, a platform 83, and a blade root portion (blade root) 85. The blade root 85 is embedded in a rotor of the gas turbine (not shown), and the turbine rotor blade 50 rotates together with the rotor. The platform 83 is configured integrally with the blade root 85. 1 and 2 , a turbine rotor blade 50 according to some embodiments has a serpentine flow passage (leading-edge-side serpentine flow passage 21) that extends in a serpentine manner from the blade central portion toward the leading edge 51, and a serpentine flow passage (trailing-edge-side serpentine flow passage 22) that extends in a serpentine manner from the blade central portion toward the trailing edge 52. The turbine rotor blade 50 shown in FIG. 1 further has a leading-edge-side flow passage 41 that is provided closer to the leading edge 51 than the leading-edge-side serpentine flow passage 21. In the turbine rotor blade 50 according to some embodiments, the leading-edge-side serpentine flow passage 21, the trailing-edge-side serpentine flow passage 22, and the leading-edge-side flow passage 41 are flow passages independent of one another. In some embodiments of the turbine blade 50, six cooling passages 42 to 47, for example, which are passages that constitute the leading edge side serpentine passage 21 and the trailing edge side serpentine passage 22, are provided in order from the leading edge 51 side, and a cooling passage 48 provided with a large number of pin fins 4 is provided on the trailing edge side.

[0012] 1 has, as a film cooling hole for blowing out film cooling air, a leading edge film cooling hole 1b that opens to a leading edge 51. For example, the leading edge film cooling hole 1b is connected to a leading edge side flow passage 41. 2 has, as film cooling holes for blowing out film cooling air, leading edge film cooling holes 1c that open to a leading edge 51. For example, the leading edge film cooling holes 1c are connected to the cooling flow passages .

[0013] In a turbine rotor blade 50 according to some embodiments, cooling channel 42, cooling channel 43, and cooling channel 44, which are provided in this order from the leading edge side, are sequentially connected to form a serpentine channel (leading-edge-side serpentine channel 21) that extends in a serpentine manner from the blade central portion toward the leading edge 51. In addition, cooling channel 45, cooling channel 46, and cooling channel 47 are sequentially connected to form a serpentine channel (trailing-edge-side serpentine channel 22) that extends toward the trailing edge 52.

[0014] The turbine rotor blade 50 according to some embodiments has a first internal passage 26, a second internal passage 27, and a third internal passage 28 extending from the bottom 85a of the blade root 85 in the blade height direction, i.e., in the radial direction of the rotor of the gas turbine. The first internal passage 26 is an internal passage connected to the cooling passage 45 that constitutes the trailing edge side serpentine passage 22, and a first opening 261, which is an opening on one end side (inlet side), is formed in the bottom 85a of the blade root 85.

[0015] The second internal passage 27 is an internal passage connected to the cooling passage 44 that constitutes the leading edge side serpentine passage 21, and a second opening 271, which is an opening on one end side (inlet side), is formed in the bottom 85a of the blade root 85.

[0016] The third internal passage 28 is an internal passage connected to the leading-edge-side flow passage 41, and a third opening 281, which is an opening on one end side (inlet side), is formed in the bottom portion 85a of the blade root 85.

[0017] Some embodiments of the turbine blade 50 include an adjustment member 100 attached to the bottom 85 a of the root 85 . The adjustment member 100 is a plate-shaped member for adjusting the flow rate of cooling air as a cooling medium flowing into the first internal passage 26, the second internal passage 27, and the third internal passage 28, and is formed with a first through hole 101, a second through hole 102, and a third through hole 103 that penetrate the adjustment member in the thickness direction of the plate, i.e., in the blade height direction.

[0018] 3 is a schematic diagram of the adjustment member 100 attached to the blade root 85 of the turbine rotor blade 50 shown in FIG. 1, viewed along the blade height direction from the blade root 85 toward the tip 81a of the blade body 81. As shown in FIG. 3, the first through hole 101 overlaps with the first opening 261 when viewed from the blade height direction. Similarly, the second through hole 102 overlaps with the second opening 271 when viewed from the blade height direction. The third through hole 103 overlaps with the third opening 281 when viewed from the blade height direction. The turbine rotor blade 50 shown in FIG. 2 is similar to the schematic diagram shown in FIG. 3 except that the third through hole 103 and the third opening 281 in FIG. 3 are not provided, and therefore is not shown.

[0019] The first through hole 101 functions as an orifice for adjusting the flow rate of cooling air flowing into the first internal passage 26. Similarly, the second through hole 102 functions as an orifice for adjusting the flow rate of cooling air flowing into the second internal passage 27. The third through hole 103 functions as an orifice for adjusting the flow rate of cooling air flowing into the third internal passage 28. By conducting a cooling air flow rate test and adjusting the opening area of ​​each of the through holes 101, 102, and 103, it is possible to flow the required flow rate of cooling air through each cooling flow path.

[0020] 1, the leading-edge-side flow passage 41 and the third internal passage 28 extend from the third opening 281, which is the cooling air intake port located at the bottom of the rotor blade, to the blade tip, and do not form a serpentine flow passage, so that the pressure loss in the entire flow passage is small. Therefore, even at the leading edge 51 where the combustion gas pressure is high, cooling air can be supplied from the leading-edge film cooling holes 1b at a pressure that does not cause the combustion gas 30 to flow back.

[0021] In the leading-edge-side serpentine flow passage 21 located behind the leading-edge-side flow passage 41, the cooling air supplied from the second opening 271, which is an intake port for the cooling air, flows from the cooling flow passage 44 through the cooling flow passage 43 toward the cooling flow passage 42, i.e., toward the leading edge 51. The cooling flow passage 43 and the cooling flow passage 42 are wing root On the other hand, in the trailing-edge serpentine channel 22 at the rear of the blade, cooling air supplied from the first opening 261, which is a cooling air intake, flows from cooling channel 45 through cooling channel 46 and cooling channel 47 in this order toward cooling channel 48, i.e., toward the trailing edge 52. This cooling air is blown out as trailing-edge blown air 12 from cooling channel 48, which is provided with a large number of pin fins 4.

[0022] As shown in FIG. 1, the cooling air after flowing through the leading-edge-side serpentine flow passage 21 is discharged to the outside of the blade body 81 from an opening 42 a of a cooling flow passage 42 provided at the tip of the blade body 81 . As shown in FIG. 2, the cooling air that has flowed through the leading-edge-side serpentine flow passage 21 is blown out from film cooling holes 1c provided in the cooling flow passage 42 to cool the blade suction side from the outside.

[0023] (Regarding the relationship between the first through hole 101 and the first opening 261) In the turbine rotor blade 50 according to some embodiments, on the trailing edge 52 side of the maximum blade thickness position, the pressure side wall Face and dorsal wall Face and The distance between the cooling passages 42 and 47 is shortened, resulting in a thinner blade-body 81. Therefore, with regard to the cooling passages formed inside the blade-body 81, the cooling passages on the trailing edge 52 side of the maximum blade thickness position tend to have a narrower passage width in the thickness direction of the blade-body 81 than the cooling passages on the leading edge 51 side. Furthermore, since multiple cooling passages 42 to 47 are provided inside the blade-body 81 from the leading edge 51 side to the trailing edge 52 side, it is difficult to increase the passage width along the camber line of the blade-body 81 for each of the cooling passages 42 to 47.

[0024] In the turbine rotor blade 50 according to some embodiments, the trailing-edge-side serpentine channel 22 formed on the trailing edge 52 side is a serpentine channel, and therefore tends to have a larger pressure loss than a non-serpentine channel (leading-edge-side channel 41). Therefore, for example, in the turbine rotor blade 50 according to some embodiments described above, the trailing-edge-side serpentine channel 22 is less likely to allow cooling air to flow than the other channels (the leading-edge-side channel 41 and the leading-edge-side serpentine channel 21).

[0025] Therefore, in some embodiments of the turbine rotor blade 50, the restriction of cooling air flowing into the first internal passage 26 caused by the first through hole 101 tends to be milder than the restriction of cooling air flowing into the second internal passage 27 caused by the second through hole 102 or the restriction of cooling air flowing into the third internal passage 28 caused by the third through hole 103. That is, in some embodiments of the turbine blade 50, the area of ​​the first through hole 101 when viewed from the blade height direction is closer to the area of ​​the first opening 261 when viewed from the blade height direction, compared to the relationship between the area of ​​the second through hole 102 and the area of ​​the second opening 271 when viewed from the blade height direction, and the relationship between the area of ​​the third through hole 103 and the area of ​​the third opening 281 when viewed from the blade height direction.

[0026] In the following description, when there is no need to particularly distinguish between the first internal passage 26, the second internal passage 27, and the third internal passage 28 or when they are referred to collectively, and when describing the internal passages formed inside the turbine rotor blade, such as the internal passages 26, 27, and 28, they will simply be referred to as the internal passage 29, and the opening on one end side (inlet side) of the internal passage 29 will be referred to as the internal passage opening 291. Similarly, in the following description, when there is no need to particularly distinguish between the first through hole 101, the second through hole 102, and the third through hole 103, or when they are referred to collectively, and when they are described as through holes that serve as orifices for the internal passage 29, similar to the respective through holes 101, 102, and 103, they will simply be referred to as through hole 199. In addition, in the following description, when the first through hole 101, the second through hole 102, the third through hole 103, and the through hole 199 are simply referred to as areas, this refers to the areas when viewed from the wing height direction. Similarly, in the following description, when the first internal passage 26, the second internal passage 27, the third internal passage 28, and the internal passage 29 are simply referred to as areas, this refers to the areas when viewed from the blade height direction.

[0027] Figures 5A and 5B are diagrams for explaining a case where the area of ​​the through hole 199 and the area of ​​the internal passage opening 291 are relatively similar. Figures 5A and 5B are schematic diagrams when viewed along the blade height direction from the blade root 85 side toward the tip 81a side of the blade body 81. Note that Figure 5A shows a case where there is no deviation in the relative positions of the through hole 199 and the internal passage opening 291, and Figure 5B shows an example where there is a deviation in the relative positions of the through hole 199 and the internal passage opening 291.

[0028] The cooling air passes through an overlap region 69 between the through hole 199 and the internal passage opening 291 when viewed from the blade height direction. Therefore, if the through hole 199 unintentionally protrudes outside the internal passage opening 291 when viewed from the blade height direction, the area of ​​the overlap region 69 unintentionally decreases. As shown in Figures 5A and 5B, when the area of ​​the through hole 199 and the area of ​​the internal passage opening 291 are relatively close, even if the deviation in the relative position between the through hole 199 and the internal passage opening 291 is relatively small, the through hole 199 is likely to unintentionally protrude outside the internal passage opening 291 when viewed from the blade height direction. Therefore, when the area of ​​the through hole 199 and the area of ​​the internal passage opening 291 are relatively close, the area of ​​the overlap region 69 is likely to decrease unintentionally even if the deviation in the relative position between the through hole 199 and the internal passage opening 291 is relatively small. Therefore, if the area of ​​the through-hole 199 and the area of ​​the internal passage opening 291 are relatively close to each other, the flow rate of the cooling air is likely to be unintentionally reduced.

[0029] As described above, in some embodiments of the turbine rotor blade 50, the area of ​​the first through hole 101 and the area of ​​the first opening 261 are close to each other, so that the flow rate of cooling air is likely to be unintentionally reduced due to a misalignment of the relative positions of the first through hole 101 and the first opening 261. Furthermore, since turbine rotor blades are generally manufactured by precision casting, it is difficult to ensure a certain degree of accuracy in the position of the internal passage 29 without carrying out cutting work.

[0030] Therefore, in the turbine rotor blade 50 according to some embodiments, the unintentional reduction in the area of ​​the overlap region 69 is suppressed as follows. FIG. 4A is a schematic diagram of a first through hole 101 and a first opening 261 according to one embodiment, viewed along the blade height direction from the blade root 85 side toward the tip 81a side of the blade body 81. Figure 4B is a schematic diagram of a first through hole 101 and a first opening 261 according to another embodiment, viewed along the blade height direction from the blade root 85 side toward the tip 81a side of the blade body 81.

[0031] As shown in Figures 3, 4A, and 4B, in the turbine rotor blade 50 according to some embodiments, the first through hole 101, the second through hole 102, and the third through hole 103 have a rectangular shape with rounded corners when viewed from the blade height direction. Each of the through holes 101, 102, 103 preferably has four sides that extend linearly when viewed in the blade height direction, which makes it easier to adjust the flow rate in each of the through holes 101, 102, 103. Each of the through holes 101, 102, and 103 may have a rectangular or square shape with adjacent sides perpendicular to each other when viewed from the blade height direction. The four corners of this rectangular or square shape may be rounded. In addition, when each of the through holes 101, 102, and 103 has two sides extending in the short direction and two sides extending in the long direction, such as a rectangular shape, the sides extending in the short direction may be curved, for example, like a circular arc.

[0032] In FIG. 4A, the longitudinal direction of the first through hole 101 is the circumferential direction of the rotor of the gas turbine, and the lateral direction of the first through hole 101 is the axial direction of the rotor of the gas turbine. In FIG. 4B, the longitudinal direction of the first through hole 101 is the axial direction of the rotor of the gas turbine, and the lateral direction of the first through hole 101 is the circumferential direction of the rotor of the gas turbine. As shown in Figure 3, the longitudinal direction of the second through hole 102 and the third through hole 103 is the axial direction of the gas turbine rotor, and the lateral direction of the second through hole 102 and the third through hole 103 is the circumferential direction of the gas turbine rotor. In the following description, the circumferential direction of the gas turbine rotor will also be simply referred to as the circumferential direction. Similarly, in the following description, the axial direction of the gas turbine rotor will also be simply referred to as the axial direction, and the radial direction of the gas turbine rotor will also be simply referred to as the radial direction.

[0033] 4A and 4B intersects with the first opening 261 when viewed from the blade height direction. This feature is referred to as feature A1. 4A and 4B has a first overlapping region 611 that overlaps with the first opening 261 and a first non-overlapping region 612 that does not overlap with the first opening 261 when viewed from the blade height direction. This feature is referred to as feature A2. Feature A1 and feature A2 are collectively referred to as feature A. As described above, the cooling air that cools the turbine rotor blades 50 passes through the first overlap region 611 . In the turbine blade 50 according to some embodiments, the presence of the first non-overlapping region 612 makes it possible to suppress a change in the area of ​​the first overlapping region 611 when viewed from the blade height direction even if the first openings 261 and the first through holes 101 are misaligned so that the distance between the edge portions (first edge portion 101a and second edge portion 101b) of the first through holes 101 that define the first non-overlapping region 612 and the edge portions (third edge portion 261a and fourth edge portion 261b) of the first openings 261 changes. As a result, even if the first through holes 101 are misaligned with respect to the first openings 261, a decrease in the flow rate of cooling air can be suppressed, and a desired flow rate of cooling air can be ensured.

[0034] As shown in FIG. 3, in some embodiments of the turbine rotor blade 50, the second through hole 102 and the third through hole 103 may be arranged so as to be located inside the second opening 271 and the third opening 281.

[0035] 4A and 4B is larger in the first direction Dr1 than the first opening 261 when viewed from the blade height direction. This feature is referred to as feature B1. 4A and 4B, the first through hole 101 has first non-overlapping regions 612 on one side and the other side in the first direction Dr1 when viewed from the blade height direction. This feature is referred to as feature B2. Feature B1 and feature B2 are collectively referred to as feature B. In the first through hole 101 shown in Fig. 4A, the first direction Dr1 is the circumferential direction, and in the first through hole 101 shown in Fig. 4B, the first direction Dr1 is the axial direction. The presence of the first non-overlapping region 612 on one side and the other side of the first direction Dr1 makes it possible to suppress a change in the area of ​​the first overlapping region 611 when viewed from the blade height direction, even if the positions of the first openings 261 and the first through holes 101 are shifted in either direction in the first direction Dr1. As a result, even if the positions of the first openings 261 and the first through holes 101 are shifted in either direction in the first direction Dr1, a decrease in the flow rate of cooling air can be suppressed, and a desired flow rate of cooling air can be secured.

[0036] In the first through hole 101 shown in Fig. 4A, the first direction Dr1 is the short-side direction of the first opening 261 when viewed from the blade height direction, i.e., the circumferential direction. In other words, the first through hole 101 shown in Fig. 4A is larger in the circumferential direction than the first opening 261. This feature is referred to as feature B1a, which is included in feature B1. As a result, even if the position of the first opening 261 and the position of the first through hole 101 are shifted to either one side or the other side of the short side direction (circumferential direction) of the first opening 261, a decrease in the flow rate of cooling air can be suppressed and the desired flow rate of cooling air can be secured.

[0037] In the first through hole 101 shown in Fig. 4B, the first direction Dr1 is the longitudinal direction of the first opening 261 when viewed from the blade height direction, i.e., the axial direction. In other words, the first through hole 101 shown in Fig. 4B is larger in the axial direction than the first opening 261. This feature is referred to as feature B1b, which is included in feature B1. This makes it possible to suppress a decrease in the flow rate of cooling air and ensure the desired flow rate of cooling air even if the position of the first opening 261 and the position of the first through hole 101 are shifted to one side or the other side of the longitudinal direction (axial direction) of the first opening 261.

[0038] 4A and 4B, the first through hole 101 is defined by a first side 111 extending along a first direction Dr1 when viewed from the blade height direction, and a second side 112 that is spaced from the first side 111 in a second direction Dr2 that intersects with the first direction Dr1 and is parallel to the first side 111. This feature is referred to as feature C. In the first through hole 101 shown in FIGS. 4A and 4B, the second direction Dr2 is a direction perpendicular to the first direction Dr1, but may be inclined with respect to the direction perpendicular to the first direction Dr1. As a result, even if the positions of the first openings 261 and the first through holes 101 are shifted to either one side or the other in the first direction Dr1, the distance between the first side 111 and the second side 112 in the first overlap region 611 does not change, and therefore it is possible to suppress a change in the area of ​​the first overlap region 611 when viewed from the blade height direction. As a result, even if the positions of the first openings 261 and the first through holes 101 are shifted to either one side or the other in the first direction Dr1, it is possible to suppress a decrease in the flow rate of cooling air and ensure a desired flow rate of cooling air.

[0039] 4A and 4B , the first opening 261, when viewed from the blade height direction, is defined by a third side 213 extending along a second direction Dr2 intersecting with the first direction Dr1, and a fourth side 214 spaced apart from the third side 213 in the first direction Dr1 and parallel to the third side 213. This feature is referred to as feature D. As a result, even if the positions of the first openings 261 and the first through holes 101 are shifted to either one side or the other in the second direction Dr2, the distance between the third side 213 and the fourth side 214 in the first overlap region 611 does not change, and therefore it is possible to suppress a change in the area of ​​the first overlap region 611 when viewed from the blade height direction. As a result, even if the positions of the first openings 261 and the first through holes 101 are shifted to either one side or the other in the second direction Dr2, it is possible to suppress a decrease in the flow rate of cooling air and ensure a desired flow rate of cooling air.

[0040] In some embodiments of the turbine rotor blade 50, Figures 1 and 2 As shown in Fig. 1, the blade root 85 may be formed with a second internal passage 27 extending in the blade height direction, and a second opening 271 that is an opening on one end side (inlet side) of the second internal passage 27 may be formed in the bottom 85a. The adjustment member 100 may be formed with a second through hole 102 that overlaps with the second opening 271 when viewed from the blade height direction. The second through hole 102 has a second overlap region 621 that overlaps with the second opening 271 when viewed from the blade height direction. This allows the cooling air to be supplied to the second internal passage 27, which is different from the first internal passage 26, so that the turbine rotor blades 50 can be cooled more effectively.

[0041] In some embodiments of the turbine blade 50, Figures 1 and 2 As shown in FIG. 1, the first opening 261 and the first through-hole 101 are located closer to the trailing edge 52 of the blade body 81 than the second opening 271 and the second through-hole 102 are. Therefore, compared with the relationship between the area of ​​the second through hole 102 when viewed from the blade height direction and the area of ​​the second opening 271, the area of ​​the first through hole 101 when viewed from the blade height direction is close to the area of ​​the first opening 261 when viewed from the blade height direction. Therefore, in order to suppress an unintended decrease in the flow rate of the cooling air passing through the first overlap region 611, it is preferable that the first through hole 101 and the first opening 261 have the above-mentioned characteristic A, and further have at least one of characteristics B, C, and D.

[0042] Since the first through hole 101 and the first opening 261 shown in Figures 4A and 4B have the above-mentioned characteristics, it is easier to ensure the desired flow rate of cooling air in the first opening 261 and the first through hole 101, which are more susceptible to changes in the position of the opening and the through hole than the second opening 271 and the second through hole 102.

[0043] In the first through hole 101 shown in Figures 4A and 4B, the value (S1a / S1b) obtained by dividing the area (S1a) of the first overlap region 611 when viewed from the wing height direction by the area (S1b) of the first opening 261 when viewed from the wing height direction is greater than the value (S2a / S2b) obtained by dividing the area (S2a) of the second overlap region 621 when viewed from the wing height direction by the area (S2b) of the second opening 271 when viewed from the wing height direction.

[0044] As described above, in the turbine rotor blade 50 according to some embodiments, the restriction of the cooling air flowing into the first internal passage 26 by the first through holes 101 tends to be milder than the restriction of the cooling air flowing into the second internal passage 27 by the second through holes 102 or the restriction of the cooling air flowing into the third internal passage 28 by the third through holes 103. Therefore, the ratio of the area (S1a) of the first overlap region 611 to the area (S1b) of the first opening 261, i.e., the value (S1a / S1b) obtained by dividing the area (S1a) of the first overlap region 611 by the area (S1b) of the first opening 261, is greater than the value (S2a / S2b) obtained by dividing the area (S2a) of the second overlap region 621 by the area (S2b) of the second opening 271. The larger the value (Sa / Sb) obtained by dividing the area Sa of the overlap region 69 by the area Sb of the internal passage opening 291, the more likely it is that the through hole 199 will unintentionally protrude outside the internal passage opening 291 when viewed from the blade height direction if the positions of the internal passage opening 291 and the through hole 199 are misaligned. That is, the larger the value (Sa / Sb) is, the more likely the area of ​​the overlap region 69 will change unintentionally, and the more likely the flow rate of the cooling air flowing through the overlap region 69 will decrease unintentionally.

[0045] 3, 4A, and 4B, the value (S1a / S1b) obtained by dividing the area (S1a) of the first overlap region 611 by the area (S1b) of the first opening 261 is greater than the value (S2a / S2b) obtained by dividing the area (S2a) of the second overlap region 621 by the area (S2b) of the second opening 271. Therefore, for example, if the first through hole 101 and the first opening 261 do not have the above-described features A, B, C, and D, like the through hole 199 and internal passage opening 291 shown in FIG. 5A, the area (S1a) of the first overlap region 611 is more likely to change unintentionally than the second overlap region 621, and the flow rate of cooling air flowing through the overlap region 69 is more likely to decrease unintentionally. In order to suppress an unintended decrease in the flow rate of cooling air passing through the first overlap region 611, the first through hole 101 and the first opening 261 may have the above-mentioned characteristic A, and may further have at least one of the characteristics B, C, and D. Since the first through hole 101 and first opening 261 shown in Figures 3, 4A and 4B have the above-mentioned characteristics, it is easier to ensure the desired flow rate of cooling air in the first opening 261 and first through hole 101, which are more susceptible to changes in the position of the opening and the through hole than the second opening 271 and second through hole 102.

[0046] In some embodiments of the turbine blade 50, Figure 1 As shown in Fig. 1, the blade root 85 may be formed with a third internal passage 28 extending in the blade height direction, and a third opening 281, which is an opening on one end side (inlet side) of the third internal passage 28, may be formed in the bottom 85a. The adjustment member 100 may be formed with a third through hole 103 that overlaps with the third opening 281 when viewed from the blade height direction. The third through hole 103 has a third overlapping region 631 that overlaps with the third opening 281 when viewed from the blade height direction. This allows cooling air to be supplied to the third internal passage 28, which is different from the first internal passage 26 and the second internal passage 27, so that the turbine rotor blades 50 can be cooled more effectively.

[0047] In some embodiments of the turbine blade 50, Figure 1As shown in FIG. 1, the first opening 261 and the first through-hole 101 are located closer to the trailing edge 52 of the blade body 81 than the second opening 271, the second through-hole 102, the third opening 281 and the third through-hole 103. Therefore, compared with the relationship between the area of ​​the second through hole 102 and the area of ​​the second opening 271 when viewed from the blade height direction and the relationship between the area of ​​the third through hole 103 and the area of ​​the third opening 281 when viewed from the blade height direction, the area of ​​the first through hole 101 when viewed from the blade height direction is close to the area of ​​the first opening 261 when viewed from the blade height direction. Therefore, in order to suppress an unintended decrease in the flow rate of the cooling air passing through the first overlap region 611, it is preferable that the first through hole 101 and the first opening 261 have the above-mentioned feature A and further have at least one of features B, C, and D.

[0048] Since the first through hole 101 and the first opening 261 shown in Figures 4A and 4B have the above-mentioned characteristics, it is easier to ensure the desired flow rate of cooling air in the first opening 261 and the first through hole 101, which are more susceptible to changes in the positions of the openings and the through holes than the second opening 271 and the second through hole 102 or the third opening 281 and the third through hole 103.

[0049] In the first through hole 101 shown in Figures 4A and 4B, the value (S1a / S1b) obtained by dividing the area (S1a) of the first overlap region 611 when viewed from the wing height direction by the area (S1b) of the first opening 261 when viewed from the wing height direction is greater than the value (S2a / S2b) obtained by dividing the area (S2a) of the second overlap region 621 when viewed from the wing height direction by the area (S2b) of the second opening 271 when viewed from the wing height direction, and the value (S3a / S3b) obtained by dividing the area (S3a) of the third overlap region 631 when viewed from the wing height direction by the area (S3b) of the third opening 281 when viewed from the wing height direction.

[0050] As described above, in some embodiments of the turbine rotor blade 50, the restriction of cooling air flowing into the first internal passage 26 caused by the first through hole 101 tends to be milder than the restriction of cooling air flowing into the second internal passage 27 caused by the second through hole 102 or the restriction of cooling air flowing into the third internal passage 28 caused by the third through hole 103. Therefore, the ratio of the area (S1a) of the first overlap region 611 to the area (S1b) of the first opening 261, i.e., the value (S1a / S1b) obtained by dividing the area (S1a) of the first overlap region 611 by the area (S1b) of the first opening 261, is larger than the value (S2a / S2b) obtained by dividing the area (S2a) of the second overlap region 621 by the area (S2b) of the second opening 271 or the value (S3a / S3b) obtained by dividing the area (S3a) of the third overlap region 631 by the area (S3b) of the third opening 281. Therefore, the area (S1a) of the first overlap region 611 is more likely to change unintentionally than the second overlap region 621 or the third overlap region 631, and the flow rate of the cooling air flowing through the overlap region 69 is more likely to decrease unintentionally. In order to suppress an unintended decrease in the flow rate of cooling air passing through the first overlap region 611, the first through hole 101 and the first opening 261 may have the above-mentioned characteristic A, and may further have at least one of the characteristics B, C, and D. Since the first through hole 101 and the first opening 261 shown in Figures 4A and 4B have the above-mentioned characteristics, it is easier to ensure the desired flow rate of cooling air in the first opening 261 and the first through hole 101, which are more susceptible to changes in the positions of the openings and the through holes than the second opening 271 and the second through hole 102 or the third opening 281 and the third through hole 103.

[0051] 4A and 4B, the first through hole 101 has a first edge 101a that defines a first non-overlapping region 612 located on one side in the first direction Dr1 and a second edge 101b that defines the first non-overlapping region 612 located on the other side in the first direction Dr1. The first opening 261 may have a third edge 261a that defines the first non-overlapping region 612 located on one side in the first direction Dr1 and a fourth edge 261b that defines the first non-overlapping region 612 located on the other side in the first direction Dr1. The distance between the first edge 101a and the third edge 261a along the first direction Dr1 may be 1.0 mm or more. The distance between the second edge 101b and the fourth edge 261b along the first direction Dr1 may be 1.0 mm or more. That is, the sum of the distance between the first edge 101a and the third edge 261a along the first direction Dr1 and the distance between the second edge 101b and the fourth edge 261b along the first direction Dr1 should be 2.0 mm or more.

[0052] Generally, turbine rotor blades are manufactured by precision casting, and therefore the position of the first opening 261 has a tolerance of, for example, about 1.0 mm to 1.5 mm in the first direction Dr1. 4A and 4B , the distance between the first edge 101a and the third edge 261a along the first direction Dr1 and the distance between the second edge 101b and the fourth edge 261b along the first direction Dr1 are equal to or greater than the positional tolerance of the first opening 261. This prevents the first edge 101a or the second edge 101b of the first through hole 101 from entering inside the first opening 261 when viewed from the blade height direction. This prevents a change in the area of ​​the first overlap region 611 when viewed from the blade height direction. Therefore, even if the positions of the first opening 261 and the first through hole 101 are shifted to either one side or the other side in the first direction Dr1, a decrease in the flow rate of cooling air can be prevented, and a desired flow rate of cooling air can be ensured.

[0053] The present disclosure is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations of these modifications. In the above-described embodiment, first through hole 101 and first opening 261 have at least feature A among the above-described features A to D. Second opening 271 and second through hole 102 may have feature A as described above, and may further have at least one of features B, C, and D. Similarly, third opening 281 and third through hole 103 may have feature A as described above, and may further have at least one of features B, C, and D.

[0054] Figure 6 is a schematic diagram of the through hole 199 and the internal passage opening 291 when viewed along the blade height direction from the blade root side toward the blade tip side, and shows other examples of the through hole 199 and the internal passage opening 291. In the other example shown in Figure 6, the through hole 199 is larger than the internal passage opening 291, and the entire internal passage opening 291 is located within the through hole 199 when viewed from the blade height direction. If at least one pair of the first through hole 101 and the first opening 261, the second opening 271 and the second through hole 102, or the third opening 281 and the third through hole 103 has at least feature A among the above-mentioned features A to D, the other through hole 199 may be larger than the internal passage opening 291, for example, as shown in Figure 6, and the entire internal passage opening 291 may be located within the through hole 199 when viewed from the blade height direction.

[0055] The contents described in each of the above embodiments can be understood, for example, as follows. (1) A turbine rotor blade 50 according to at least one embodiment of the present disclosure includes a blade root 85 having a first internal passage 26 extending in the blade height direction and a first opening 261 at one end of the first internal passage 26 formed in a bottom 85a, and an adjustment member 100 attached to the bottom 85a and having a first through hole 101 formed therein that overlaps with the first opening 261 when viewed from the blade height direction. When viewed from the blade height direction, the first through hole 101 intersects with the first opening 261 and has a first overlap region 611 that overlaps with the first opening 261 and a first non-overlapping region 612 that does not overlap with the first opening 261.

[0056] The cooling air that cools the turbine rotor blades 50 passes through the first overlap region 611. According to the configuration (1) above, even if there is a misalignment between the first openings 261 and the first through holes 101, it is possible to suppress a change in the area of ​​the first overlap region 611 when viewed from the blade height direction. As a result, even if there is a misalignment between the first openings 261 and the first through holes 101, it is possible to suppress a decrease in the flow rate of the cooling air, and it is possible to ensure a desired flow rate of the cooling air.

[0057] (2) In some embodiments, in the configuration of (1) above, the first through hole 101 may be larger in the first direction Dr1 than the first opening 261 when viewed from the blade height direction. The first through hole 101 may have first non-overlapping regions 612 on one side and the other side in the first direction Dr1.

[0058] According to the configuration (2) above, the presence of the first non-overlapping region 612 on one side and the other side of the first direction Dr1 makes it possible to suppress a change in the area of ​​the first overlapping region 611 when viewed from the blade height direction even if the positions of the first openings 261 and the first through holes 101 are shifted to either one side or the other side in the first direction Dr1. As a result, even if the positions of the first openings 261 and the first through holes 101 are shifted to either one side or the other side in the first direction Dr1, it is possible to suppress a decrease in the flow rate of cooling air and ensure a desired flow rate of cooling air.

[0059] (3) In some embodiments, in the configuration of (2) above, the first through hole 101 may be defined by a first edge 111 extending along a first direction Dr1 when viewed from the blade height direction, and a second edge 112 spaced from the first edge 111 in a second direction Dr2 intersecting the first direction Dr1 and parallel to the first edge 111.

[0060] According to the configuration (3) above, even if the positions of the first openings 261 and the first through holes 101 are shifted to either one side or the other side in the first direction Dr1, the distance between the first side 111 and the second side 112 in the first overlap region 611 does not change, and therefore it is possible to suppress a change in the area of ​​the first overlap region 611 when viewed from the blade height direction. As a result, even if the positions of the first openings 261 and the first through holes 101 are shifted to either one side or the other side in the first direction Dr1, it is possible to suppress a decrease in the flow rate of cooling air and ensure a desired flow rate of cooling air.

[0061] (4) In some embodiments, in the configuration of (2) or (3) above, the first opening 261 may be defined by a third side 213 extending along a second direction Dr2 intersecting with the first direction Dr1 when viewed from the blade height direction, and a fourth side 214 spaced apart from the third side 213 in the first direction Dr1 and parallel to the third side 213.

[0062] According to the configuration (4) above, even if the positions of the first openings 261 and the first through holes 101 are shifted to either one side or the other side in the second direction Dr2, the distance between the third side 213 and the fourth side 214 in the first overlap region 611 does not change, and therefore it is possible to suppress a change in the area of ​​the first overlap region 611 when viewed from the blade height direction. As a result, even if the positions of the first openings 261 and the first through holes 101 are shifted to either one side or the other side in the second direction Dr2, it is possible to suppress a decrease in the flow rate of cooling air and ensure a desired flow rate of cooling air.

[0063] (5) In some embodiments, in any of the configurations (2) to (4) above, the first direction Dr1 may be the short-side direction of the first opening 261 when viewed from the blade height direction.

[0064] According to the configuration (5) above, even if the position of the first opening 261 and the position of the first through hole 101 are shifted to one side or the other side in the short direction of the first opening 261, the desired flow rate of cooling air can be ensured.

[0065] (6) In some embodiments, in any of the configurations (2) to (4) above, the first direction Dr1 may be the longitudinal direction of the first opening 261 when viewed from the blade height direction.

[0066] According to the configuration (6) above, even if the position of the first opening 261 and the position of the first through hole 101 are shifted to one side or the other side in the longitudinal direction of the first opening 261, the desired flow rate of cooling air can be ensured.

[0067] (7) In some embodiments, in any of the configurations (1) to (6) above, the blade root 85 may be formed with a second internal passage 27 extending in the blade height direction, and a second opening 271 at one end of the second internal passage 27 may be formed in the bottom portion 85a. The adjustment member 100 may be formed with a second through hole 102 that overlaps with the second opening 271 when viewed from the blade height direction. The second through hole 102 has a second overlap region 621 that overlaps with the second opening 271 when viewed from the blade height direction.

[0068] According to the above configuration (7), cooling air can be supplied to the second internal passage 27 different from the first internal passage 26, so that the turbine rotor blades 50 can be cooled more effectively.

[0069] (8) In some embodiments, in the configuration of (7) above, the first opening 261 and the first through-hole 101 may be positioned closer to the trailing edge 52 of the wing body 81 than the second opening 271 and the second through-hole 102.

[0070] According to the configuration (8) above, since the first opening 261 and the first through hole 101 have any of the configurations (1) to (6) above, it becomes easier to ensure the desired flow rate of cooling air in the first opening 261 and the first through hole 101, which are more susceptible to changes in the positions of the opening and the through hole than the second opening 271 and the second through hole 102.

[0071] (9) In some embodiments, in the configuration of (7) or (8) above, the value (S1a / S1b) obtained by dividing the area (S1a) of the first overlap region 611 when viewed from the wing height direction by the area (S1b) of the first opening 261 when viewed from the wing height direction may be greater than the value (S2a / S2b) obtained by dividing the area (S2a) of the second overlap region 621 when viewed from the wing height direction by the area (S2b) of the second opening 271 when viewed from the wing height direction.

[0072] In the configuration (9) above, the value (S1a / S1b) obtained by dividing the area (S1a) of the first overlap region 611 by the area (S1b) of the first opening 261 is greater than the value (S2a / S2b) obtained by dividing the area (S2a) of the second overlap region 621 by the area (S2b) of the second opening 271. Therefore, the area (S1a) of the first overlap region 611 is more likely to change unintentionally than the second overlap region 621, and the flow rate of the cooling air flowing through the overlap region 69 is more likely to decrease unintentionally. According to the configuration (9) above, since the first opening 261 and the first through hole 101 have any of the configurations (1) to (6) above, it becomes easier to ensure the desired flow rate of cooling air in the first opening 261 and the first through hole 101, which are more susceptible to changes in the positions of the opening and the through hole than the second opening 271 and the second through hole 102.

[0073] (10) In some embodiments, in any of the configurations (7) to (9) above, the blade root 85 may be formed with a third internal passage 28 extending in the blade height direction, and a third opening 281 on one end side of the third internal passage 28 may be formed in the bottom 85a. The adjustment member 100 may be formed with a third through hole 103 that overlaps with the third opening 281 when viewed from the blade height direction. The third through hole 103 has a third overlap region 631 that overlaps with the third opening 281 when viewed from the blade height direction.

[0074] According to the configuration (10) above, the cooling medium can be supplied to the third internal passage 28, which is different from the first internal passage 26 and the second internal passage 27, so that the turbine rotor blades 50 can be cooled more effectively.

[0075] (11) In some embodiments, in the configuration of (10) above, the first opening 261 and the first through hole 101 may be located closer to the trailing edge 52 of the wing body 81 than the second opening 271, the second through hole 102, the third opening 281 and the third through hole 103.

[0076] According to the configuration (11) above, since the first opening 261 and the first through hole 101 have any of the configurations (1) to (6) above, it becomes easier to ensure the desired flow rate of cooling air in the first opening 261 and the first through hole 101, which are more susceptible to changes in the positions of the opening and the through hole than the second opening 271 and the second through hole 102 or the third opening 281 and the third through hole 103.

[0077] (12) In some embodiments, in the configuration of (10) or (11) above, the value (S1a / S1b) obtained by dividing the area (S1a) of the first overlap region 611 when viewed from the wing height direction by the area (S1b) of the first opening 261 when viewed from the wing height direction may be greater than the value (S2a / S2b) obtained by dividing the area (S2a) of the second overlap region 621 when viewed from the wing height direction by the area (S2b) of the second opening 271 when viewed from the wing height direction, and the value (S3a / S3b) obtained by dividing the area (S3a) of the third overlap region 631 when viewed from the wing height direction by the area (S3b) of the third opening 281 when viewed from the wing height direction.

[0078] According to the configuration (12) above, since the first opening 261 and the first through hole 101 have any of the configurations (1) to (6) above, it becomes easier to ensure the desired flow rate of cooling air in the first opening 261 and the first through hole 101, which are more susceptible to changes in the positions of the opening and the through hole than the second opening 271 and the second through hole 102 or the third opening 281 and the third through hole 103.

[0079] (13) In some embodiments, in the configuration of (2) above, the first through hole may have a first edge defining a first non-overlapping region located on one side in the first direction and a second edge defining the first non-overlapping region located on the other side in the first direction. The first opening may have a third edge defining the first non-overlapping region located on one side in the first direction and a fourth edge defining the first non-overlapping region located on the other side in the first direction. The sum of the distance between the first edge and the third edge along the first direction and the distance between the second edge and the fourth edge along the first direction may be 2.0 mm or more.

[0080] According to the configuration of (13) above, the distance between the first edge 101a and the third edge 261a along the first direction Dr1 and the distance between the second edge 101b and the fourth edge 261b along the first direction Dr1 are equal to or greater than the positional tolerance of the first opening 261, so that the first edge 101a or the second edge 101b of the first through hole 101 can be prevented from entering inside the first opening 261 when viewed from the blade height direction. This can prevent a change in the area of ​​the first overlap region 611 when viewed from the blade height direction. Therefore, even if the positions of the first opening 261 and the first through hole 101 are shifted to either one side or the other side in the first direction Dr1, a decrease in the flow rate of cooling air can be prevented, and a desired flow rate of cooling air can be ensured. [Explanation of symbols]

[0081] 26 1st internal passage 27 Second internal passage 28 Third internal passage 50 Turbine blades 51 leading edge 52 Trailing edge 81 Wing body 85 Wing root (wing root) 85a bottom 101 First through hole 101a First edge 101b 2nd edge 102 Second through hole 103 Third Through Hole 111 Side 1 112 Side 2 213 Third Side 214 Side 4 261 First Opening 261a Third edge 261b 4th edge 271 Second Opening 281 Third Opening 611 1st overlap area 612 1st non-overlapping area 621 2nd overlap area 631 Third overlap area

Claims

1. a blade root having a first internal passage extending in a blade height direction, the first internal passage having a first opening formed in a bottom portion thereof at one end thereof; a plate-shaped adjustment member attached to the bottom portion and having a first through hole formed therein that overlaps with the first opening when viewed from the blade height direction; Equipped with When viewed from the blade height direction, the first through hole has intersecting the first opening, a first overlapping region that overlaps with the first opening and a first non-overlapping region that does not overlap with the first opening; The first through hole is When viewed from the blade height direction, the opening is larger than the first opening in a first direction, the first non-overlapping region is provided on one side and the other side in the first direction; When viewed from the blade height direction, the first through hole is defined by a first side extending along the first direction, a second side spaced apart from the first side in a second direction intersecting the first direction and parallel to the first side, a first edge portion extending along the second direction, and a second edge portion spaced apart from the first edge portion in the first direction and parallel to the first edge portion, A direction from an opening on one side in the blade height direction of the first through hole toward an opening on the other side in the blade height direction coincides with a plate thickness direction of the adjustment member. Turbine blades.

2. When viewed from the blade height direction, the first opening is defined by a third side extending along a second direction intersecting the first direction, and a fourth side spaced apart from the third side in the first direction and parallel to the third side. The turbine blade of claim 1 .

3. The first direction is a short-side direction of the first opening when viewed from the blade height direction. The turbine blade according to claim 1 or 2.

4. The first direction is a longitudinal direction of the first opening when viewed from the blade height direction. The turbine blade according to claim 1 or 2.

5. a second internal passage extending in the blade height direction is formed in the blade root, and a second opening is formed in a bottom portion of the second internal passage at one end side thereof; a second through hole overlapping with the second opening when viewed from the blade height direction is formed in the adjustment member, The second through hole has a second overlap region that overlaps with the second opening when viewed from the blade height direction. The turbine blade according to claim 1 or 2.

6. The first opening and the first through-hole are located closer to the trailing edge of the blade body than the second opening and the second through-hole. The turbine blade of claim 5 .

7. A value (S1a / S1b) obtained by dividing the area (S1a) of the first overlap region when viewed from the wing height direction by the area (S1b) of the first opening when viewed from the wing height direction is greater than a value (S2a / S2b) obtained by dividing the area (S2a) of the second overlap region when viewed from the wing height direction by the area (S2b) of the second opening when viewed from the wing height direction. The turbine blade of claim 5 .

8. a third internal passage extending in the blade height direction is formed in the blade root, and a third opening is formed in a bottom portion of one end side of the third internal passage; a third through hole overlapping with the third opening when viewed from the blade height direction is formed in the adjustment member, The third through hole has a third overlap region that overlaps with the third opening when viewed from the blade height direction. The turbine blade of claim 5 .

9. The first opening and the first through hole are located closer to the trailing edge of the blade body than the second opening, the second through hole, the third opening, and the third through hole. The turbine blade of claim 8.

10. A value (S1a / S1b) obtained by dividing the area (S1a) of the first overlap region when viewed from the wing height direction by the area (S1b) of the first opening when viewed from the wing height direction is greater than a value (S2a / S2b) obtained by dividing the area (S2a) of the second overlap region when viewed from the wing height direction by the area (S2b) of the second opening when viewed from the wing height direction, and a value (S3a / S3b) obtained by dividing the area (S3a) of the third overlap region when viewed from the wing height direction by the area (S3b) of the third opening when viewed from the wing height direction. The turbine blade of claim 8.

11. the first edge portion defines the first non-overlapping region located on one side in the first direction, and the second edge portion defines the first non-overlapping region located on the other side in the first direction; the first opening has a third edge portion that defines the first non-overlapping region located on one side in the first direction and a fourth edge portion that defines the first non-overlapping region located on the other side in the first direction; The sum of the distance between the first edge portion and the third edge portion along the first direction and the distance between the second edge portion and the fourth edge portion along the first direction is 2.0 mm or more. The turbine blade of claim 1 .

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