Turbine rotor blade and gas turbine

Abstract

To reduce a pressure loss of a cooling medium while reducing a stress increase of a blade cross section in a turbine moving blade.SOLUTION: A turbine rotor blade according to an embodiment includes an airfoil portion extending in a blade height direction, a shroud portion located closer to a tip side than the airfoil portion, a plurality of hub-side cooling passages extending in the blade height direction inside the airfoil portion and provided with a plurality of turbulators, and a plurality of tip-side cooling passages extending in the blade height direction, connecting a cavity provided in the shroud portion and a tip side of the hub-side cooling passage, and having a passage cross-sectional area smaller than that of the hub-side cooling passage. The plurality of tip-side cooling passages include a first tip-side cooling passage and a second tip-side cooling passage different from the first tip-side cooling passage. A first connection portion between the first tip-side cooling passage and the hub-side cooling passage is different in position in the blade height direction from a second connection portion between the second tip-side cooling passage and the hub-side cooling passage.SELECTED DRAWING: Figure 2

Description

[Technical Field]

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

[0002] The turbine rotor blades in gas turbines are exposed to high-temperature, high-pressure working fluids and therefore have an internal cooling structure. Specifically, for example, the cooling structure has internal flow paths through which cooling air is circulated as a cooling medium, thereby cooling the turbine rotor blades from the inside.

[0003] For example, the turbine rotor blade described in Patent Document 1 has cavities with pin fins protruding from the inner walls inside the hub and blade root, and multiple holes are drilled inside the blade on the tip side of the hub that connect the cavities to openings provided at the blade tip and allow cooling air to pass from the cavities to the openings. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] Japanese Patent Application Publication No. 9-053407 Summary of the Invention [Problem to be solved by the invention]

[0005] However, in the turbine blade described in Patent Document 1, cooling air flows through the interior of the multi-holes to cool the tip side. To ensure the required heat transfer coefficient, the flow velocity of the cooling air flowing through the multi-holes as a cooling medium must be increased, resulting in large pressure losses. Therefore, cooling air must be supplied at a high supply pressure on the upstream blade root side. Supplying cooling air at a high supply pressure increases leakage flow on the blade root side, which may increase the amount of cooling air supplied.

[0006] Therefore, one possible approach is to reduce pressure loss by shortening the extension length of the multi-holes while leaving the multi-holes near the blade tip where cross-sectional rigidity is required.Another possible approach is to provide multiple cooling flow channels extending in the blade height direction from the hub to the tip, each with a larger passage cross-sectional area than the multi-holes and multiple turbulence promoters such as turbulators provided inside, and to connect these cooling flow channels to the multi-holes to cool the turbine rotor blades.

[0007] In this case, stress may be concentrated at the connection between the cooling flow passage and the multi-hole, which have different passage cross-sectional areas, resulting in high stress in the blade cross section, so it is desirable to take measures to reduce the increase in stress in the blade cross section.

[0008] In view of the above circumstances, at least one embodiment of the present disclosure has an object to reduce pressure loss of a cooling medium while reducing an increase in stress on the blade cross section in a turbine blade. [Means for solving the problem]

[0009] (1) A turbine blade according to at least one embodiment of the present disclosure comprises: an airfoil portion extending in a blade height direction; a shroud portion located on the tip side of the airfoil portion; a plurality of hub-side cooling passages extending in the height direction within the airfoil portion and each having a plurality of turbulators; a plurality of tip-side cooling passages extending in the blade height direction, connecting cavities provided in the shroud portion to the tip side of the hub-side cooling passage, the tip-side cooling passages having a smaller cross-sectional area than the hub-side cooling passages; Equipped with the plurality of chip-side cooling passages include a first chip-side cooling passage and a second chip-side cooling passage different from the first chip-side cooling passage, A first connection portion between the first tip-side cooling passage and the hub-side cooling passage is positioned differently in the blade height direction from a second connection portion between the second tip-side cooling passage and the hub-side cooling passage.

[0010] (2) A gas turbine according to at least one embodiment of the present disclosure includes: A compressor; a turbine provided with a plurality of turbine rotor blades having the configuration of (1) above; Equipped with. [Effects of the Invention]

[0011] According to at least one embodiment of the present disclosure, it is possible to reduce the pressure loss of the coolant in a turbine blade while reducing the increase in stress on the blade cross section. [Brief explanation of the drawings]

[0012] [Figure 1] 1 is a schematic configuration diagram of a gas turbine to which turbine rotor blades according to some embodiments are applied. [Figure 2] 1 is a schematic diagram of a turbine rotor blade according to some embodiments, viewed in a direction from a suction surface to a pressure surface (direction along the rotor circumferential direction). FIG. [Figure 3] 1 is a diagram illustrating a cross section of a turbine rotor blade according to an embodiment, taken along the blade height direction, in the vicinity of an end portion on the tip side. FIG. [Figure 4] FIG. 10 is a diagram illustrating a cross section of a turbine rotor blade according to another embodiment, taken along the blade height direction, in the vicinity of an end portion on the tip side. [Figure 5A] FIG. 10 is a diagram illustrating a cross section of a turbine rotor blade according to yet another embodiment, taken along the blade height direction, in the vicinity of an end portion on the tip side. [Figure 5B] FIG. 5B is a diagram showing a cross section of the same turbine rotor blade as FIG. 5A taken along the blade height direction in the vicinity of the tip-side end portion, and is used to explain dimensions not shown in FIG. 5A for the sake of convenience. DETAILED DESCRIPTION OF THE INVENTION

[0013] 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.

[0014] (Gas turbine configuration) First, a gas turbine to which turbine rotor blades according to some embodiments are applied will be described. Fig. 1 is a schematic configuration diagram of a gas turbine to which turbine rotor blades according to some embodiments 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 a gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6.

[0015] The compressor 2 includes a plurality of stator vanes 16 fixed to the compressor casing 10 side, and a plurality of moving blades 18 implanted in the rotor 8 so as to be arranged alternately with respect to the stator vanes 16. Air taken in from an air intake 12 is sent to the compressor 2, and this air is compressed as it passes through the plurality of stator vanes 16 and the plurality of moving blades 18, becoming high-temperature, high-pressure compressed air.

[0016] The combustor 4 is supplied with fuel and compressed air generated by the compressor 2, and the fuel and compressed air are mixed and combusted in the combustor 4 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 in the casing 20 along the circumferential direction with the rotor 8 at the center.

[0017] The turbine 6 has a combustion gas flow path 28 formed in a turbine casing 22, and includes a plurality of stator vanes 24 and moving blades (turbine moving blades) 30 provided in the combustion gas flow path 28. The stator vanes 24 are fixed to the turbine casing 22 side, and the plurality of stator vanes 24 arranged along the circumferential direction of the rotor 8 constitute a stator vane row. The moving blades 26 are implanted in the rotor 8, and the plurality of moving blades 26 arranged along the circumferential direction of the rotor 8 constitute a moving blade row. The stator vane rows and moving blade rows are arranged alternately in the axial direction of the rotor 8.

[0018] In the turbine 6, the combustion gas from the combustor 4 flows into a combustion gas flow path 28 and passes through the plurality of stator vanes 24 and the plurality of rotor blades 26, thereby driving the rotor 8 to rotate, which in turn drives a generator connected to the rotor 8 to generate electricity. After driving the turbine 6, the combustion gas is discharged to the outside via an exhaust chamber 29.

[0019] (Configuration of turbine blades) Several embodiments of the turbine rotor blade 30 are described in more detail below. FIG. 2 is a schematic diagram of a turbine rotor blade 30 according to some embodiments, viewed in a direction from the suction surface to the pressure surface (direction along the rotor circumferential direction). FIG. 3 is a diagram illustrating a cross section of a turbine rotor blade 30 according to one embodiment, taken along the blade height direction, in the vicinity of the tip end portion. FIG. 4 is a diagram showing a cross section of a turbine rotor blade 30 according to another embodiment, taken along the blade height direction in the vicinity of the tip end portion. FIG. 5A is a diagram showing a cross section of a turbine rotor blade 30 according to yet another embodiment, taken along the blade height direction in the vicinity of the tip end portion. FIG. 5B is a diagram showing a cross section of the same turbine rotor blade 30 as FIG. 5A taken along the blade height direction near the tip end, and is used to explain dimensions not shown in FIG. 5A for ease of explanation.

[0020] 2 , a turbine rotor blade 30 according to some embodiments includes a platform 32, an airfoil portion 34 and a blade root portion 36 connected to the platform 32, a shroud portion 52 located closer to the blade tip than the airfoil portion 34, and a fillet portion 40 connected to the shroud portion 52. The turbine rotor blade 30 also includes fins 54 for reducing fluid leakage at the blade tip of the turbine rotor blade 30.

[0021] The airfoil portion 34 extends in the blade height direction (span direction), has a base end 38 and a tip end 39 which are opposite ends in the blade height direction, and is connected to the platform 32 on the base end 38 side (hub side). The airfoil portion 34 also has a leading edge 42 and a trailing edge 44 extending along the blade height direction, and has a pressure surface 46 and a suction surface 48 extending between the leading edge 42 and the trailing edge 44. The airfoil portion 34 may have a shape that is twisted from the base end 38 to the tip end 39 in the blade height direction.

[0022] The blade root portion 36 is located on the opposite side of the platform 32 from the airfoil portion 34 in the blade height direction. The blade root portion 36 includes an engagement portion having a concave-convex shape, and the turbine rotor blade 30 is attached to the rotor 8 of the turbine 6 by the engagement portion being engaged with a blade groove provided in a rotor disk (not shown) that rotates together with the rotor 8.

[0023] When the turbine rotor blades 30 are attached to the rotor 8, the blade height direction is aligned with the radial direction of the turbine 6. That is, the blade height direction of the turbine rotor blades 30 and the radial direction of the turbine 6 substantially coincide with each other.

[0024] The fillet portion 40 is formed by the curved surface 40a and is connected to the hub-side end of the shroud portion 52. In other words, the fillet portion 40 is formed between the airfoil portion 34 and the shroud portion 52. The fillet portion 40 may be connected to the hub-side flat surface 52a of the shroud portion 52. The fillet portion 40 formed by the curved surface 40a can alleviate stress concentration at the connection portion of the shroud portion 52 to the airfoil portion 34.

[0025] The shroud portion 52 is fixed to the tip portion 39 of the airfoil portion 34 via the fillet portion 40. The shroud portion 52 shown in Figures 3 and 4 is configured to extend parallel to the axial direction of the rotor 8 so that the radial position of the rotor 8 is the same regardless of the axial position of the rotor 8. The shroud portion 52 shown in Figures 5A and 5B is configured to be inclined with respect to the axial direction of the rotor 8 so as to move radially outward of the rotor 8 from the upstream side to the downstream side in the axial direction of the rotor 8. The upstream side of the rotor 8 in the axial direction is the upstream side of the flow of combustion gas flowing through the combustion gas flow passage 28, and the downstream side of the rotor 8 in the axial direction is the downstream side of the flow of combustion gas flowing through the combustion gas flow passage 28.

[0026] The fins 54 are provided so as to protrude from the shroud portion 52 toward the blade tip side (tip side) and extend along the circumferential direction. The fins 54 of the multiple turbine rotor blades 30 arranged in the circumferential direction form an annular seal portion. In the following description, the base end 38 side in the blade height direction is also referred to as the hub side, and the tip end 39 side is also referred to as the tip side. In other words, the hub side is the radially inner side of the rotor 8, and the tip side is the radially outer side of the rotor 8.

[0027] The turbine blade 30 includes a plurality of turbulator passages 60 , a plurality of multi-holes 70 , and at least one cooling cavity 80 . The plurality of turbulator passages 60 each extend from at least the base end 38 inside the airfoil 34 in the blade height direction toward the tip side. In the example shown in FIG. 2, the plurality of turbulator passages 60 extend to the hub-side end of the blade root 36 and open at that end. In the example shown in FIGS. 2-5B, the plurality of turbulator passages 60 extend to near the tip 39 of the airfoil 34. In some embodiments of the turbine blade 30, the multiple turbulator passages 60 are straight passages that allow cooling air to flow from the hub side to the tip side, and are not formed in a serpentine manner like a serpentine passage.

[0028] Each of the multiple turbulator passages 60 is provided with multiple rib-shaped turbulators 69 that protrude from the inner circumferential surface of the turbulator passage 60. The turbulators 69 are provided for the purpose of promoting turbulence in the flow of the cooling medium in the turbulator passage 60 and improving the heat transfer coefficient between the cooling medium and the turbine rotor blades 30. Note that the base end of the turbulator 69 in the protruding direction is connected to the inner wall surface of the airfoil portion 34 that constitutes the turbulator passage 60, but the tip end of the turbulator 69 in the protruding direction is not connected to the inner wall surface of the airfoil portion 34.

[0029] The plurality of turbulator passages 60 are arranged in sequence along the camber line of the airfoil 34 from the leading edge 42 side toward the trailing edge 44 side. 2 to 5B, the multiple turbulator passages 60 include, in order from the leading edge 42 side, a first turbulator passage 61, a second turbulator passage 62, a third turbulator passage 63, and a fourth turbulator passage 64. Note that the number of the multiple turbulator passages 60 is not limited to four.

[0030] The multiple multi-holes 70 are cooling passages that extend in the blade height direction inside the airfoil portion 34 and have a smaller passage cross-sectional area than the turbulator passages 60. Each of the multiple multi-holes 70 has a hub-side end connected to the tip-side end of one of the multiple turbulator passages 60, and each of the tip-side ends connected to one of the cooling cavities 80 described below. 2 to 5B, the multiple multi-holes 70 include, in order from the leading edge 42 side, first multi-holes 71, second multi-holes 72, third multi-holes 73, fourth multi-holes 74, fifth multi-holes 75, sixth multi-holes 76, seventh multi-holes 77, and eighth multi-holes 78. The number of multiple multi-holes 70 is not limited to eight. In some embodiments of the turbine blade 30, the multiple multi-holes 70 are straight passages that allow cooling air to flow from the hub side to the tip side, and are not formed in a serpentine manner like a serpentine passage.

[0031] In the example shown in Figures 2 to 5B, the first multi-holes 71 and the second multi-holes 72 are connected to the first turbulator passage 61, and the third multi-holes 73 and the fourth multi-holes 74 are connected to the second turbulator passage 62. In the example shown in Figures 2 to 5B, the fifth multi-holes 75 and the sixth multi-holes 76 are connected to the third turbulator passage 63, and the seventh multi-holes 77 and the eighth multi-holes 78 are connected to the fourth turbulator passage 64. The number of multi-holes 70 connected to one turbulator passage 60 is not limited to two, but may be one, or three or more.

[0032] The cooling cavity 80 is a void space that is at least partially provided inside the shroud portion 52 and communicates with any one of the multiple multi-holes 70 . In the example shown in FIGS. 2 to 5B, the cooling cavity 80 includes a first cooling cavity 81 and a second cooling cavity 82 located closer to the trailing edge 44 than the first cooling cavity 81. 2 to 5B, the first cooling cavity 81 communicates with the first multi-holes 71, the second multi-holes 72, the third multi-holes 73, and the fourth multi-holes 74. In the example shown in Figures 2 to 5B, the second cooling cavity 82 communicates with the fifth multi-holes 75, the sixth multi-holes 76, the seventh multi-holes 77, and the eighth multi-holes 78.

[0033] The shroud portion 52 is provided with a plurality of cooling holes (not shown), one end of which is connected to either the first cooling cavity 81 or the second cooling cavity 82, and the other end of which is open to the surface of the shroud portion 52.

[0034] In the turbine rotor blades 30 configured in this manner, compressed bleed air extracted from the compressor 2 is used as cooling air, which serves as a cooling medium for the turbine rotor blades 30. The gas turbine 1 is configured so that the compressed bleed air extracted from the compressor 2 is supplied to each of the multiple turbulator passages 60 of each turbine rotor blade 30 from the hub-side end of the blade root portion 36.

[0035] The compressed bleed air (cooling air) supplied to each of the multiple turbulator passages 60 flows from the hub side to the tip side in each of the multiple turbulator passages 60, removing heat from the airfoil portion 34 and cooling the airfoil portion 34 from the inside. The cooling air that has flowed through each of the plurality of turbulator passages 60 flows into the plurality of multi-holes 70 to remove heat from the airfoil portion 34 and cool the airfoil portion 34 from the inside. The cooling air that has circulated through each of the multiple multi-holes 70 flows into either the first cooling cavity 81 or the second cooling cavity 82, then flows through one of the multiple cooling holes (not shown) described above, removes heat from the shroud portion 52, cools the shroud portion 52 from the inside, and is then discharged to the outside of the turbine rotor blade 30.

[0036] In the turbine rotor blade 30 configured in this manner, the length in the blade height direction of the plurality of turbulator passages 60, which have a relatively large passage cross-sectional area, i.e., a passage area in a cross section perpendicular to the blade height direction, is made relatively large, and the length in the blade height direction of the plurality of multi-holes 70, which have a relatively small passage area, is made relatively short, thereby reducing pressure loss of the cooling air. This makes it possible to reduce the supply pressure of the cooling air and reduce leakage flow of the cooling air, thereby improving the efficiency of the gas turbine 1.

[0037] Furthermore, according to the gas turbine 1 including the turbine rotor blades 30 configured in this manner, the pressure loss of the cooling air can be reduced, and therefore the efficiency of the gas turbine 1 can be improved. According to the gas turbine 1 including the turbine rotor blades 30 configured in this manner, the airfoil portions 34 can be cooled by compressed bleed air with a relatively low pressure, thereby reducing leakage of compressed bleed air.

[0038] As described above, the passage cross-sectional area of ​​the turbulator passages 60 differs from the passage cross-sectional area of ​​the multi-holes 70, and therefore the passage cross-sectional area changes from the turbulator passages 60 to the multi-holes 70 at the connection portions 90 between the turbulator passages 60 and the multi-holes 70. Therefore, the shape of the inner wall of the airfoil section 34 that constitutes the turbulator passages 60 and the multi-holes 70 changes from the turbulator passages 60 to the multi-holes 70. When the rotor 8 is rotating, a relatively large centrifugal force acts on the turbine rotor blades 30, and since stress tends to concentrate near the connection portion 90, there is a risk that stress on the blade cross section will increase.

[0039] Therefore, in the turbine rotor blade 30 according to some embodiments, the position in the blade height direction of at least one of the plurality of connection portions 90 is made different from the position in the blade height direction of at least one of the other connection portions 90, thereby reducing the increase in stress on the blade cross section. This will be described in detail below.

[0040] The connection portion 90 between the turbulator passage 60 and the multi-holes 70 is an inlet for cooling air to the multi-holes 70. Therefore, for ease of explanation, the connection portion 90 between the first multi-hole 71 and the turbulator passage 60 (first turbulator passage 61) will also be referred to as a first inlet portion 91, the connection portion 90 between the second multi-hole 72 and the turbulator passage 60 (first turbulator passage 61) will also be referred to as a second inlet portion 92, the connection portion 90 between the third multi-hole 73 and the turbulator passage 60 (second turbulator passage 62) will also be referred to as a third inlet portion 93, and the connection portion 90 between the fourth multi-hole 74 and the turbulator passage 60 (second turbulator passage 62) will also be referred to as a fourth inlet portion 94. The connection portion 90 between the fifth multi-hole 75 and the turbulator passage 60 (third turbulator passage 63) is also referred to as the fifth inlet portion 95, the connection portion 90 between the sixth multi-hole 76 and the turbulator passage 60 (third turbulator passage 63) is also referred to as the sixth inlet portion 96, the connection portion 90 between the seventh multi-hole 77 and the turbulator passage 60 (fourth turbulator passage 64) is also referred to as the seventh inlet portion 97, and the connection portion 90 between the eighth multi-hole 78 and the turbulator passage 60 (fourth turbulator passage 64) is also referred to as the eighth inlet portion 98.

[0041] The connection 90 between the turbulator passage 60 and the multi-holes 70 is also the tip-side end of the turbulator passage 60 for the turbulator passage 60, and is also the hub-side end of the multi-holes 70 for the multi-holes 70.

[0042] In the following description, the position P of the connection portion 90 in the blade height direction will be expressed as the position P of the connection portion 90 in the blade height direction when the position P of the hub-side end portion of the leading edge 42 of the airfoil portion 34 is set to 0% as shown in Figure 2, and the position P of the tip-side end portion of the leading edge 42 of the airfoil portion 34 is set to 100%. Note that position P of the hub-side end of the leading edge 42 of the airfoil portion 34 is, for example, the intersection position of the leading edge 42 and the tip-side surface of the platform 32. When a fillet portion exists at the connection portion between the leading edge 42 and the platform 32, the intersection position is set to the position where the leading edge 42 and the tip-side surface of the platform 32 would intersect if the fillet portion did not exist. The position P of the tip-side end of the leading edge 42 of the airfoil portion 34 is, for example, the intersection position between the leading edge 42 and the hub-side surface (flat surface 52a) of the shroud portion 52, and is the position where the leading edge 42 and the hub-side surface (flat surface 52a) of the shroud portion 52 would intersect if the fillet portion 40 did not exist.

[0043] In some embodiments of the turbine rotor blade 30, the position P in the blade height direction of the first inlet section 91 is a first position P1, the position P in the blade height direction of the second inlet section 92 is a second position P2, the position P in the blade height direction of the third inlet section 93 is a third position P3, and the position P in the blade height direction of the fourth inlet section 94 is a fourth position P4. In some embodiments of the turbine rotor blade 30, the position P in the blade height direction of the fifth inlet section 95 is designated as a fifth position P5, the position P in the blade height direction of the sixth inlet section 96 is designated as a sixth position P6, the position P in the blade height direction of the seventh inlet section 97 is designated as a seventh position P7, and the position P in the blade height direction of the eighth inlet section 98 is designated as an eighth position P8.

[0044] In some embodiments of the turbine blade 30, as described below, at least one of the positions P in the blade height direction of the multiple connection sections 90, i.e., the first inlet section 91 to the eighth inlet section 98, is made different from at least one of the positions P in the blade height direction of the other connection sections 90 (inlet sections), thereby reducing stress increase in the blade cross section.

[0045] In the examples shown in FIGS. 3, 5A, and 5B, a first position P1 of the first inlet portion 91 in the blade height direction is the same as a second position P2 of the second inlet portion 92 in the blade height direction. In the example shown in FIG. 4, a first position P1 of the first inlet portion 91 in the blade height direction is different from a second position P2 of the second inlet portion 92 in the blade height direction.

[0046] In the example shown in Figures 3 to 5B, the third position P3 of the third inlet portion 93 in the blade height direction is the same as the fourth position P4 of the fourth inlet portion 94 in the blade height direction, but they may be different. In the example shown in FIGS. 3 to 5B, the fifth position P5 of the fifth inlet portion 95 in the blade height direction is the same as the sixth position P6 of the sixth inlet portion 96 in the blade height direction, but may be different. In the example shown in Figures 3 to 5B, the seventh position P7 of the seventh inlet portion 97 in the blade height direction is the same as the eighth position P8 of the eighth inlet portion 98 in the blade height direction, but they may be different. In the following description, the first position P1 in the blade height direction will also be referred to simply as position P1. Similarly, for the second position P2 to the eighth position P8 in the blade height direction, the words "in the blade height direction" and "second" to "eighth" may be omitted.

[0047] In the examples shown in FIGS. 3 to 5B, positions P1 and P2 are different in position in the blade height direction from other positions P3 to P8. In the examples shown in FIGS. 3 to 5B, positions P3 and P4 are different in position in the blade height direction from other positions P1, P2, and P5 to P8. In the examples shown in FIGS. 3 to 5B, positions P5 and P6 are different in position in the blade height direction from the other positions P1 to P4, P7, and P8. In the examples shown in FIGS. 3 to 5B, positions P7 and P8 are different in position in the blade height direction from the other positions P1 to P6.

[0048] (Regarding the relationship between the position P in the wing height direction for different connection parts 90) In the turbine rotor blade 30 according to some embodiments, one of the multiple multi-holes 70 is a first tip-side cooling passage, and one of the remaining multi-holes 70 is a second tip-side cooling passage. The connection 90 between the first tip-side cooling passage and the turbulator passage 60 is a first connection, and the connection 90 between the second tip-side cooling passage and the turbulator passage 60 is a second connection.

[0049] (When the first multi-holes 71 are used as cooling passages on the first chip side) 3, 5A, and 5B, the first multi-hole 71 is the first chip-side cooling passage, and any one of the third multi-holes 73 to eighth multi-holes 78 is the second chip-side cooling passage. In this case, the position P1 in the blade height direction of the first connection part (first inlet part 91) is different from the position P (any one of positions P3 to P8) in the blade height direction of the second connection part (any one of the third inlet part 93 to eighth inlet part 98).

[0050] 4, for example, first multi-hole 71 is the first chip-side cooling passage, and any one of second multi-hole 72 to eighth multi-hole 78 is the second chip-side cooling passage. In this case, position P1 in the blade height direction of the first connection part (first inlet part 91) is different from position P (any one of positions P2 to P8) in the blade height direction of the second connection part (any one of second inlet part 92 to eighth inlet part 98).

[0051] (When the second multi-holes 72 are used as cooling passages on the first chip side) 3, 5A, and 5B, the second multi-hole 72 is the first chip-side cooling passage, and any one of the third multi-holes 73 to eighth multi-holes 78 is the second chip-side cooling passage. In this case, position P2 of the first connection part (second inlet part 92) in the blade height direction is different from position P (any one of positions P3 to P8) of the second connection part (any one of the third inlet part 93 to eighth inlet part 98) in the blade height direction.

[0052] 4, for example, second multi-hole 72 is the first chip-side cooling passage, and first multi-hole 71 or any one of third multi-hole 73 to eighth multi-hole 78 is the second chip-side cooling passage. In this case, position P2 in the blade height direction of the first connection part (second inlet part 92) is different from position P (position P1 or any one of positions P3 to P8) in the blade height direction of the second connection part (first inlet part 91 or any one of third inlet part 93 to eighth inlet part 98).

[0053] (When the third multi-holes 73 are used as cooling passages on the first chip side) 3 to 5B, for example, third multi-hole 73 is the first chip-side cooling passage, and any one of first multi-hole 71, second multi-hole 72, or fifth multi-hole 75 to eighth multi-hole 78 is the second chip-side cooling passage. In this case, position P3 in the blade height direction of the first connection part (third inlet part 93) is different from position P (position P1, position P2, or any one of positions P5 to P8) in the blade height direction of the second connection part (any one of first inlet part 91, second inlet part 92, or fifth inlet part 95 to eighth inlet part 98).

[0054] (When the fourth multi-holes 74 are used as cooling passages on the first chip side) 3 to 5B, for example, the fourth multi-hole 74 is the first chip-side cooling passage, and any one of the first multi-hole 71, the second multi-hole 72, or the fifth multi-hole 75 to the eighth multi-hole 78 is the second chip-side cooling passage. In this case, the position P4 in the blade height direction of the first connection part (the fourth inlet part 94) is different from the position P (the position P1, the position P2, or any one of the positions P5 to P8) in the blade height direction of the second connection part (the first inlet part 91, the second inlet part 92, or any one of the fifth inlet part 95 to the eighth inlet part 98).

[0055] (When the fifth multi-hole 75 is used as the cooling passage on the first chip side) 3 to 5B, for example, fifth multi-hole 75 is the first chip-side cooling passage, and any one of first multi-hole 71 to fourth multi-hole 74, seventh multi-hole 77, or eighth multi-hole 78 is the second chip-side cooling passage. In this case, position P5 in the blade height direction of the first connection portion (fifth inlet portion 95) is different from position P (any one of position P1 to position P4, position P7, or position P8) in the blade height direction of the second connection portion (any one of first inlet portion 91 to fourth inlet portion 94, seventh inlet portion 97, or eighth inlet portion 98).

[0056] (When the sixth multi-hole 76 is used as the cooling passage on the first chip side) 3 to 5B, the sixth multi-hole 76 is the first chip-side cooling passage, and any one of the first multi-holes 71 to 74, the seventh multi-hole 77, or the eighth multi-hole 78 is the second chip-side cooling passage. In this case, the position P6 in the blade height direction of the first connection portion (sixth inlet portion 96) is different from the position P (any one of the positions P1 to P4, P7, or P8) in the blade height direction of the second connection portion (any one of the first inlet portion 91 to 4th inlet portion 94, the seventh inlet portion 97, or the eighth inlet portion 98).

[0057] (When the seventh multi-hole 77 is used as the cooling passage on the first chip side) 3 to 5B, for example, the seventh multi-hole 77 is the first chip-side cooling passage, and any one of the first multi-holes 71 to sixth multi-holes 76 is the second chip-side cooling passage. In this case, the position P7 in the blade height direction of the first connection part (seventh inlet part 97) is different from the position P (any one of positions P1 to P6) in the blade height direction of the second connection part (any one of the first inlet part 91 to sixth inlet part 96).

[0058] (When the eighth multi-hole 78 is used as a cooling passage on the first chip side) 3 to 5B, for example, the eighth multi-hole 78 is the first chip-side cooling passage, and any one of the first multi-holes 71 to sixth multi-holes 76 is the second chip-side cooling passage. In this case, position P8 in the blade height direction of the first connection part (eighth inlet part 98) is different from position P (any one of positions P1 to P6) in the blade height direction of the second connection part (any one of the first inlet part 91 to sixth inlet part 96).

[0059] Thus, in some embodiments of the turbine blade 30, the first connection between the first tip-side cooling passage and the turbulator passage 60 is at a different position P in the blade height direction than the second connection between the second tip-side cooling passage, which is different from the first tip-side cooling passage, and the turbulator passage 60. As a result, the connection 90 between the turbulator passage 60 and the multi-hole 70 has different passage cross-sectional areas, and the positions P in the blade height direction of the first connection part and the second connection part, where stress is relatively likely to concentrate, are different, so the increase in stress in the blade cross section can be reduced compared to when the positions P in the blade height direction of the first connection part and the second connection part are the same. Furthermore, according to the gas turbine 1 including the turbine rotor blades 30 according to some embodiments, the increase in stress on the blade cross section of the turbine rotor blades 30 can be reduced, and therefore the reliability of the gas turbine 1 can be improved.

[0060] In the turbine rotor blade 30 according to some embodiments, at least one of the first connection portion and the second connection portion may be located closer to the hub than the fillet portion 40 . In some embodiments, the turbine rotor blade 30 has a shroud portion 52 located closer to the tip than the airfoil portion 34, and therefore, a relatively large stress is generated in the fillet portion 40 due to the centrifugal force acting on the shroud portion 52 during operation of the gas turbine 1. According to the turbine rotor blade 30 of some embodiments, at least one of the first connection portion and the second connection portion, where stress is relatively likely to concentrate, is located at a position away from the fillet portion 40, where relatively large stress occurs. Therefore, it is possible to reduce the increase in stress on the blade cross section compared to when both the first connection portion and the second connection portion are located at the same position in the blade height direction as the fillet portion 40.

[0061] In the turbine rotor blade 30 according to some embodiments, it is preferable that all of the connection portions 90 between the multi-holes 70 and the turbulator passages 60 are located closer to the hub than the fillet portion 40 . By positioning all of the connection portions 90 closer to the hub than the fillet portions 40, it is possible to effectively reduce the increase in stress on the blade cross section.

[0062] In some embodiments of the turbine blade 30, the first tip-side cooling passage may be connected at a first connection portion to a first hub-side cooling passage that is one of the turbulator passages 60. The second tip-side cooling passage may be connected at a second connection portion to a second hub-side cooling passage that is a turbulator passage 60 different from the first hub-side cooling passage. 3, 5A, and 5B, the first multi-hole 71 is the first chip-side cooling passage, and any one of the third multi-holes 73 to eighth multi-holes 78 is the second chip-side cooling passage. In this case, the second chip-side cooling passage is connected to any one of the second turbulator passages 62 to 64, which is a turbulator passage 60 different from the first turbulator passage 61 to which the first multi-hole 71 is connected. The position P1 of the first connection portion (first inlet portion 91) and the position P (any one of positions P3 to P8) of the second connection portion (any one of the third inlet portion 93 to eighth inlet portion 98) are different. As a result, even when the first tip-side cooling passage and the second tip-side cooling passage are connected to different turbulator passages 60, an increase in stress on the blade cross section can be reduced.

[0063] In some embodiments of the turbine blade 30 , the first tip-side cooling passage and the second tip-side cooling passage may be connected to the same turbulator passage 60 . 4, for example, the first multi-holes 71 are the first chip-side cooling passages, and the second multi-holes 72 are the second chip-side cooling passages. In this case, the first chip-side cooling passages and the second chip-side cooling passages are connected to the first turbulator passages 61, which are the same turbulator passages 60. The position P1 of the first connecting portion (first inlet portion 91) and the position P2 of the second connecting portion (second inlet portion 92) are different. As a result, even when the first tip side cooling passage and the second tip side cooling passage are connected to the same turbulator passage 60, an increase in stress on the blade cross section can be reduced.

[0064] In the turbine rotor blade 30 according to some embodiments, the tip-side end (connection portion 90) of at least one turbulator passage 60 may be located at a position P that is 70% or more in the blade height direction. This allows the length of the multi-holes 70, whose passage cross-sectional area is smaller than that of the turbulator passages 60, to be relatively short, thereby reducing the pressure loss of the cooling air.

[0065] In the turbine rotor blade 30 according to some embodiments, it is preferable that all of the connection portions 90 between the multi-holes 70 and the turbulator passages 60 are located at positions P that are 50% or more in the blade height direction. This allows the length of all of the multiple multi-holes 70 whose passage cross-sectional area is smaller than that of the turbulator passages 60 to be relatively short, thereby reducing the pressure loss of the cooling air.

[0066] In the turbine rotor blade 30 according to some embodiments, the first connection portion and the second connection portion may be located at a position P that is 60% to 90% in the blade height direction. In other words, the position P in the blade height direction of at least one of the multiple connection portions 90 that are located at a position P that is 60% to 90% in the blade height direction may be different from the position P in the blade height direction of at least one of the other connection portions 90. As a result, even if the connection parts 90 tend to be close to each other by making the length of the multi-holes 70, which have a smaller passage cross-sectional area than the turbulator passages 60, relatively short, the positions of the first connection part and the second connection part in the blade height direction can be made different, thereby reducing pressure loss of the cooling air.

[0067] (Regarding the relationship between the distance from the shroud portion 52 for different connection portions 90) The distance L from the tip side surface (radially outer surface) 52b of the shroud portion 52 to the connecting portion 90 will be described below. As described above, during operation of the gas turbine 1, centrifugal force acts on the shroud portion 52, which is located closer to the tip than the airfoil portion 34, and therefore relatively large stress is generated in the region of the airfoil portion 34 that is relatively close to the shroud portion 52. Therefore, if all of the connection portions 90 are arranged so that the distance L from the tip-side surface 52b of the shroud portion 52 is the same, stress is likely to be concentrated at the connection portions 90, resulting in an undesirable increase in stress in the airfoil cross section.

[0068] Therefore, in some embodiments of the turbine blade 30, as described below, the distance L from the surface 52b to at least one of the multiple connection portions 90 (the first inlet portion 91 to the eighth inlet portion 98) is made different from the distance L from the surface 52b to at least one of the other multiple connection portions 90, thereby reducing the increase in stress in the blade cross section.

[0069] In the following description, the distance L from the surface 52b to the first inlet portion 91 is referred to as the first distance L1, the distance L from the surface 52b to the second inlet portion 92 is referred to as the second distance L2, the distance L from the surface 52b to the third inlet portion 93 is referred to as the third distance L3, and the distance L from the surface 52b to the fourth inlet portion 94 is referred to as the fourth distance L4. In some embodiments of the turbine blade 30, the distance L from the surface 52b to the fifth inlet section 95 is the fifth distance L5, the distance L from the surface 52b to the sixth inlet section 96 is the sixth distance L6, the distance L from the surface 52b to the seventh inlet section 97 is the seventh distance L7, and the distance L from the surface 52b to the eighth inlet section 98 is the eighth distance L8.

[0070] In the example shown in FIG. 3, the first distance L1 from the surface 52b to the first inlet portion 91 is the same as the second distance L2 from the surface 52b to the second inlet portion 92. In the example shown in FIG. 4, a first distance L1 from the surface 52b to the first inlet portion 91 is different from a second distance L2 from the surface 52b to the second inlet portion 92.

[0071] In the example shown in FIGS. 3 and 4, the third distance L3 from the surface 52b to the third inlet portion 93 is the same as the fourth distance L4 from the surface 52b to the fourth inlet portion 94, but may be different. In the example shown in Figures 3 and 4, the fifth distance L5 from the surface 52b to the fifth inlet portion 95 is the same as the sixth distance L6 from the surface 52b to the sixth inlet portion 96, but may be different. In the example shown in Figures 3 and 4, the seventh distance L7 from the surface 52b to the seventh inlet 97 is the same as the eighth distance L8 from the surface 52b to the eighth inlet 98, but they may be different.

[0072] In the example shown in Figures 5A and 5B, the distance L from surface 52b to any one inlet portion (connection portion 90) is different from the distance L from surface 52b for all other inlet portions (connection portions 90), but it is sufficient that the distance L from surface 52b to at least one inlet portion (connection portion 90) is different from the distance L from surface 52b to at least one of the other inlet portions (connection portions 90). In the following description, the first distance L1 will also be referred to simply as distance L1. Similarly, the terms "second" to "eighth" may be omitted for the second distance L2 to the eighth distance L8.

[0073] (When the first multi-holes 71 are used as cooling passages on the first chip side) 3, for example, first multi-hole 71 is the first tip-side cooling passage, and any one of third multi-hole 73 to eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L1 from tip-side surface 52b of shroud portion 52 to first connection portion (first inlet portion 91) is different from distance L (any one of distances L3 to L8) from tip-side surface 52b of shroud portion 52 to second connection portion (any one of third inlet portion 93 to eighth inlet portion 98).

[0074] 4, 5A, and 5B, first multi-hole 71 is the first tip-side cooling passage, and any one of second multi-holes 72 to eighth multi-holes 78 is the second tip-side cooling passage. In this case, distance L1 from tip-side surface 52b of shroud portion 52 to the first connection portion (first inlet portion 91) is different from distance L (any one of distances L2 to L8) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of second inlet portion 92 to eighth inlet portion 98).

[0075] (When the second multi-holes 72 are used as cooling passages on the first chip side) 3, for example, second multi-hole 72 is the first tip-side cooling passage, and any one of third multi-hole 73 to eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L2 from tip-side surface 52b of shroud portion 52 to first connection portion (second inlet portion 92) is different from distance L (any one of distances L3 to L8) from tip-side surface 52b of shroud portion 52 to second connection portion (any one of third inlet portion 93 to eighth inlet portion 98).

[0076] 4, 5A, and 5B, second multi-hole 72 is the first tip-side cooling passage, and first multi-hole 71 or any one of third multi-hole 73 to eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L2 from tip-side surface 52b of shroud portion 52 to first connection portion (second inlet portion 92) is different from distance L (distance L1 or any one of distances L3 to L8) from tip-side surface 52b of shroud portion 52 to second connection portion (first inlet portion 91 or any one of third inlet portion 93 to eighth inlet portion 98).

[0077] (When the third multi-holes 73 are used as cooling passages on the first chip side) 3 and 4, third multi-hole 73 is the first tip-side cooling passage, and any one of first multi-hole 71, second multi-hole 72, or fifth multi-hole 75 to eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L3 from tip-side surface 52b of shroud portion 52 to the first connection portion (third inlet portion 93) is different from distance L (any one of distance L1, distance L2, or distance L5 to distance L8) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of first inlet portion 91, second inlet portion 92, or fifth inlet portion 95 to eighth inlet portion 98).

[0078] 5A and 5B, third multi-hole 73 is the first tip-side cooling passage, and any one of first multi-hole 71, second multi-hole 72, or fourth multi-hole 74 to eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L3 from tip-side surface 52b of shroud portion 52 to first connection portion (third inlet portion 93) is different from distance L (any one of distance L1, distance L2, or distance L4 to distance L8) from tip-side surface 52b of shroud portion 52 to second connection portion (any one of first inlet portion 91, second inlet portion 92, or fourth inlet portion 94 to eighth inlet portion 98).

[0079] (When the fourth multi-holes 74 are used as cooling passages on the first chip side) 3 and 4, for example, fourth multi-hole 74 is the first tip-side cooling passage, and any one of first multi-hole 71, second multi-hole 72, or fifth multi-hole 75 to eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L4 from tip-side surface 52b of shroud portion 52 to the first connection portion (fourth inlet portion 94) is different from distance L (any one of distance L1, distance L2, or distance L5 to distance L8) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of first inlet portion 91, second inlet portion 92, or fifth inlet portion 95 to eighth inlet portion 98).

[0080] 5A and 5B, fourth multi-hole 74 is the first tip-side cooling passage, and any one of first multi-hole 71 to third multi-hole 73 or fifth multi-hole 75 to eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L4 from tip-side surface 52b of shroud portion 52 to the first connection portion (fourth inlet portion 94) is different from distance L (any one of distances L1 to L3, or distances L5 to L8) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of first inlet portion 91 to third inlet portion 93 or fifth inlet portion 95 to eighth inlet portion 98).

[0081] (When the fifth multi-hole 75 is used as the cooling passage on the first chip side) 3 and 4, fifth multi-hole 75 is the first tip-side cooling passage, and any one of first multi-hole 71 to fourth multi-hole 74, seventh multi-hole 77, or eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L5 from tip-side surface 52b of shroud portion 52 to the first connection portion (fifth inlet portion 95) is different from distance L (any one of distance L1 to distance L4, distance L7, or distance L8) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of first inlet portion 91 to fourth inlet portion 94, seventh inlet portion 97, or eighth inlet portion 98).

[0082] 5A and 5B, fifth multi-hole 75 is the first tip-side cooling passage, and any one of first multi-hole 71 to fourth multi-hole 74 or sixth multi-hole 76 to eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L5 from tip-side surface 52b of shroud portion 52 to the first connection portion (fifth inlet portion 95) is different from distance L (any one of distances L1 to L4, or distances L6 to L8) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of first inlet portion 91 to fourth inlet portion 94 or sixth inlet portion 96 to eighth inlet portion 98).

[0083] (When the sixth multi-hole 76 is used as the cooling passage on the first chip side) 3 and 4, sixth multi-hole 76 is the first tip-side cooling passage, and any one of first multi-hole 71 to fourth multi-hole 74, seventh multi-hole 77, or eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L6 from tip-side surface 52b of shroud portion 52 to the first connection portion (sixth inlet portion 96) is different from distance L (any one of distance L1 to distance L4, distance L7, or distance L8) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of first inlet portion 91 to fourth inlet portion 94, seventh inlet portion 97, or eighth inlet portion 98).

[0084] 5A and 5B, sixth multi-hole 76 is the first tip-side cooling passage, and any one of first multi-hole 71 to fifth multi-hole 75, seventh multi-hole 77, or eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L6 from tip-side surface 52b of shroud portion 52 to the first connection portion (sixth inlet portion 96) is different from distance L (any one of distance L1 to distance L5, distance L7, or distance L8) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of first inlet portion 91 to fifth inlet portion 95, seventh inlet portion 97, or eighth inlet portion 98).

[0085] (When the seventh multi-hole 77 is used as the cooling passage on the first chip side) 3 and 4, for example, seventh multi-hole 77 is the first tip-side cooling passage, and any one of first multi-hole 71 to sixth multi-hole 76 is the second tip-side cooling passage. In this case, distance L7 from tip-side surface 52b of shroud portion 52 to the first connection portion (seventh inlet portion 97) is different from distance L (any one of distances L1 to L6) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of first inlet portion 91 to sixth inlet portion 96).

[0086] 5A and 5B, seventh multi-hole 77 is the first tip-side cooling passage, and any one of first multi-hole 71 to sixth multi-hole 76 or eighth multi-hole 78 is the second tip-side cooling passage. In this case, distance L7 from tip-side surface 52b of shroud portion 52 to the first connection portion (seventh inlet portion 97) is different from distance L (any one of distances L1 to L6, or distance L8) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of first inlet portion 91 to sixth inlet portion 96 or eighth inlet portion 98).

[0087] (When the eighth multi-hole 78 is used as a cooling passage on the first chip side) 3 and 4, eighth multi-hole 78 is the first tip-side cooling passage, and any one of first multi-hole 71 to sixth multi-hole 76 is the second tip-side cooling passage. In this case, distance L8 from tip-side surface 52b of shroud portion 52 to the first connection portion (eighth inlet portion 98) is different from distance L (any one of distances L1 to L6) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of first inlet portion 91 to sixth inlet portion 96).

[0088] 5A and 5B, eighth multi-hole 78 is the first tip-side cooling passage, and any one of first to seventh multi-holes 71 to 77 is the second tip-side cooling passage. In this case, distance L8 from tip-side surface 52b of shroud portion 52 to the first connection portion (eighth inlet portion 98) is different from distance L (any one of distances L1 to L7) from tip-side surface 52b of shroud portion 52 to the second connection portion (any one of first inlet portion 91 to seventh inlet portion 97).

[0089] Thus, in some embodiments of the turbine blade 30, the distance L from the tip side surface 52b of the shroud portion 52 to the first connection portion may be different from the distance L from the tip side surface 52b of the shroud portion 52 to the second connection portion. According to the turbine rotor blade 30 of some embodiments, the distance L from the tip side surface 52b of the shroud portion 52 is different between the first connection portion and the second connection portion, thereby reducing an increase in stress on the blade cross section.

[0090] Furthermore, as described above, when the distance L from the tip side surface 52b of the shroud portion 52 to the first connection portion is different from the distance L from the tip side surface 52b of the shroud portion 52 to the second connection portion, it is preferable that the first connection portion and the second connection portion are located at a position equal to or greater than 85% in the blade height direction. As a result, the first connection portion and the second connection portion are located in an area relatively close to the shroud portion 52, and therefore, by making the distance L from the tip side surface 52b of the shroud portion 52 different between the first connection portion and the second connection portion, the effect of reducing the increase in stress in the blade cross section is greater.

[0091] 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.

[0092] The contents described in each of the above embodiments can be understood, for example, as follows. (1) A turbine rotor blade 30 according to at least one embodiment of the present disclosure includes an airfoil portion 34 extending in a blade height direction, a shroud portion 52 located closer to the tip side than the airfoil portion 34, a plurality of hub-side cooling passages (turbulator passages 60) extending in the blade height direction inside the airfoil portion 34 and provided with a plurality of turbulators 69, and a plurality of tip-side cooling passages (multi-holes 70) extending in the blade height direction and connecting cavities (cooling cavities 80) provided in the shroud portion 52 to the tip sides of the hub-side cooling passages (turbulator passages 60), the passage cross-sectional area of ​​which is smaller than that of the hub-side cooling passages (turbulator passages 60). The plurality of tip-side cooling passages (multi-holes 70) includes a first tip-side cooling passage (multi-holes 70) and a second tip-side cooling passage (multi-holes 70) different from the first tip-side cooling passage (multi-holes 70). The first connection portion (connection portion 90) between the first tip side cooling passage (multi-hole 70) and the hub side cooling passage (turbulator passage 60) has a different position P in the blade height direction from the second connection portion (connection portion 90) between the second tip side cooling passage (multi-hole 70) and the hub side cooling passage (turbulator passage 60).

[0093] According to the configuration (1) above, the connection portion 90 between the hub-side cooling passage (turbulator passage 60) and the tip-side cooling passage (multi-hole 70) has different passage cross-sectional areas, and the first connection portion (connection portion 90) and the second connection portion (connection portion 90), where stress is relatively likely to concentrate, are at different positions P in the blade height direction. This reduces the increase in stress on the blade cross section compared to when the first connection portion (connection portion 90) and the second connection portion (connection portion 90) are at the same position P in the blade height direction. Furthermore, according to the configuration (1) above, the hub-side cooling passage (turbulator passage 60) has a larger passage cross-sectional area than the tip-side cooling passage (multi-hole 70), so the pressure loss of the cooling medium can be reduced compared to when the tip-side cooling passage (multi-hole 70) extends over the entire area of ​​the airfoil portion 34 in the blade height direction.

[0094] (2) In some embodiments, the configuration of (1) above may include a fillet portion 40 formed between the airfoil portion 34 and the shroud portion 52. At least one of the first connection portion (connection portion 90) and the second connection portion (connection portion 90) may be located closer to the hub than the fillet portion 40.

[0095] The turbine blade 30 according to at least one embodiment of the present disclosure includes a shroud portion 52 located closer to the tip than the airfoil portion 34, and therefore, a relatively large stress is generated in the fillet portion 40 due to the centrifugal force acting on the shroud portion 52 during operation of the gas turbine 1. According to the configuration (2) above, at least one of the first connection portion (connection portion 90) and the second connection portion (connection portion 90), where stress is relatively likely to concentrate, is located at a position away from the fillet portion 40, where relatively large stress occurs. Therefore, it is possible to reduce the increase in stress on the blade cross section compared to when both the first connection portion (connection portion 90) and the second connection portion (connection portion 90) are located at the same position in the blade height direction as the fillet portion 40.

[0096] (3) In some embodiments, in the configuration of (2) above, the connection portions 90 between the tip-side cooling passages (multi-holes 70) and the hub-side cooling passages (turbulator passages 60) are preferably all located closer to the hub than the fillet portions 40.

[0097] According to the configuration (3) above, all of the connection portions (connection portions 90) are located closer to the hub than the fillet portion 40, so that the increase in stress on the blade cross section can be effectively reduced.

[0098] (4) In some embodiments, in any of the configurations (1) to (3) above, the multiple hub-side cooling passages (turbulator passages 60) may include a first hub-side cooling passage (turbulator passage 60) and a second hub-side cooling passage (turbulator passage 60) different from the first hub-side cooling passage (turbulator passage 60). The first tip-side cooling passage (multi-holes 70) may be connected to the first hub-side cooling passage (turbulator passage 60) by a first connecting portion (connecting portion 90), and the second tip-side cooling passage (multi-holes 70) may be connected to the second hub-side cooling passage (turbulator passage 60) by a second connecting portion (connecting portion 90).

[0099] According to the configuration (4) above, even when the first tip-side cooling passage (multi-hole 70) and the second tip-side cooling passage (multi-hole 70) are connected to different hub-side cooling passages (turbulator passages 60), the increase in stress on the blade cross section can be reduced.

[0100] (5) In some embodiments, in any of the configurations (1) to (3) above, the first tip-side cooling passage (multi-hole 70) and the second tip-side cooling passage (multi-hole 70) may be connected to the same hub-side cooling passage (turbulator passage 60).

[0101] According to the configuration (5) above, even when the first tip-side cooling passage (multi-hole 70) and the second tip-side cooling passage (multi-hole 70) are connected to the same hub-side cooling passage (turbulator passage 60), the increase in stress on the blade cross section can be reduced.

[0102] (6) In some embodiments, in any of the configurations (1) to (5) above, the distance L from the chip side surface (surface 52b) of the shroud portion 52 to the first connection portion (connection portion 90) may be different from the distance L from the chip side surface (surface 52b) to the second connection portion (connection portion 90).

[0103] As described above, when the gas turbine 1 is in operation, centrifugal force acts on the shroud portion 52, which is located closer to the tip than the airfoil portion 34, and therefore relatively large stress is generated in a region of the airfoil portion 34 that is relatively close to the shroud portion 52. Therefore, if the first connection portion (connection portion 90) and the second connection portion (connection portion 90) are arranged so that the distance L from the tip side surface (surface 52b) of the shroud portion 52 is the same, stress tends to concentrate on the first connection portion (connection portion 90) and the second connection portion (connection portion 90), resulting in an undesirable increase in stress in the airfoil cross section. According to the configuration (6) above, the distance L from the tip side surface (surface 52b) of the shroud portion 52 is different between the first connection portion (connection portion 90) and the second connection portion (connection portion 90), thereby reducing the increase in stress on the blade cross section.

[0104] (7) In some embodiments, in the configuration of (6) above, the position of the hub-side end of the leading edge 42 of the airfoil portion 34 in the blade height direction is defined as 0%, and the position of the tip-side end of the leading edge 42 of the airfoil portion 34 is defined as 100%. The first connecting portion (connecting portion 90) and the second connecting portion (connecting portion 90) may be located at a position P that is 85% or more in the blade height direction.

[0105] As described above, when the gas turbine 1 is in operation, centrifugal force acts on the shroud portion 52, which is located closer to the tip than the airfoil portion 34, and therefore, relatively large stress is generated in the area of ​​the airfoil portion 34 that is relatively close to the shroud portion 52. According to the configuration (7) above, the first connection portion (connection portion 90) and the second connection portion (connection portion 90) are located in an area relatively close to the shroud portion 52, and therefore, by making the distance L from the tip side surface (surface 52b) of the shroud portion 52 different between the first connection portion (connection portion 90) and the second connection portion (connection portion 90), the effect of reducing the increase in stress in the blade cross section is increased.

[0106] (8) In some embodiments, in any of the configurations (1) to (7) above, the position of the hub-side end of the leading edge 42 of the airfoil 34 in the blade height direction is defined as 0%, and the position of the tip-side end of the leading edge 42 of the airfoil 34 is defined as 100%. The tip-side end of at least one hub-side cooling passage may be located at a position 70% or more in the blade height direction.

[0107] According to the configuration (8) above, the length of the tip-side cooling passage (multi-holes 70), whose passage cross-sectional area is smaller than that of the hub-side cooling passage (turbulator passage 60), can be made relatively short, thereby reducing pressure loss of the cooling medium.

[0108] (9) In some embodiments, in any of the configurations (1) to (8) above, the position of the hub-side end of the leading edge 42 of the airfoil portion 34 in the blade height direction is defined as 0%, and the position of the tip-side end of the leading edge 42 of the airfoil portion 34 is defined as 100%. It is preferable that all connection portions 90 between the tip-side cooling passages (multi-holes 70) and the hub-side cooling passages (turbulator passages 60) are located at positions P that are 50% or greater in the blade height direction.

[0109] According to the configuration (9) above, the length of all of the multiple tip-side cooling passages (multi-holes 70) whose passage cross-sectional area is smaller than that of the hub-side cooling passage (turbulator passage 60) can be made relatively short, thereby reducing the pressure loss of the cooling medium.

[0110] (10) In some embodiments, in any of the configurations (1) to (9) above, the position of the hub-side end of the leading edge 42 of the airfoil portion 34 in the blade height direction is defined as 0%, and the position of the tip-side end of the leading edge 42 of the airfoil portion 34 is defined as 100%. The first connecting portion (connecting portion 90) and the second connecting portion (connecting portion 90) may be located at a position P that is 60% to 90% inclusive in the blade height direction.

[0111] According to the configuration (10) above, even if the connection parts 90 tend to be close to each other by making the length of the tip side cooling passage (multi-holes 70) relatively short, which has a smaller passage cross-sectional area than the hub side cooling passage (turbulator passage 60), the positions of the first connection part (connection part 90) and the second connection part (connection part 90) in the blade height direction can be made different, thereby reducing the pressure loss of the cooling medium.

[0112] (11) A gas turbine 1 according to at least one embodiment of the present disclosure includes a compressor 2 and a turbine 6 provided with a plurality of turbine rotor blades 30 having any one of the configurations described above in (1) to (10).

[0113] According to the configuration (11) above, it is possible to reduce the increase in stress on the blade cross section of the turbine rotor blade 30, thereby improving the reliability of the gas turbine 1. Furthermore, according to the configuration (11) above, it is possible to reduce the pressure loss of the cooling medium, thereby improving the efficiency of the gas turbine 1.

[0114] (12) In some embodiments, in the configuration of (11) above, compressed bleed air bled from the compressor 2 may be supplied to the multiple hub-side cooling passages (turbulator passages 60).

[0115] According to the configuration (12) above, the airfoil portion 34 can be cooled by compressed bleed air with a relatively low pressure, so that leakage of compressed bleed air can be reduced. [Explanation of symbols]

[0116] 1. Gas turbine 2 Compressor 6 Turbine 8 rotors 30 Moving blades (turbine moving blades) 34 Airfoil 40 Fillet 42 leading edge 44 Trailing edge 52 Shroud section 52b surface 60 Turbulator Passage 69 Turbulator 70 Multi-Hole 80 Cooling cavity 90 Connection

Claims

1. an airfoil portion extending in a blade height direction; a shroud portion located on the tip side of the airfoil portion; a plurality of hub-side cooling passages extending in the height direction within the airfoil portion and each having a plurality of turbulators; a plurality of tip-side cooling passages extending in the blade height direction, connecting cavities provided in the shroud portion to the tip side of the hub-side cooling passage, the tip-side cooling passages having a smaller cross-sectional area than the hub-side cooling passages; Equipped with the plurality of chip-side cooling passages include a first chip-side cooling passage and a second chip-side cooling passage different from the first chip-side cooling passage, a first connection portion between the first tip-side cooling passage and the hub-side cooling passage is located at a different position in the blade height direction from a second connection portion between the second tip-side cooling passage and the hub-side cooling passage; Turbine blades.

2. a fillet portion formed between the airfoil portion and the shroud portion; Equipped with At least one of the first connection portion and the second connection portion is located closer to the hub than the fillet portion. The turbine blade of claim 1 .

3. all of the connection portions between the tip-side cooling passage and the hub-side cooling passage are located closer to the hub than the fillet portion; The turbine blade of claim 2 .

4. the plurality of hub-side cooling passages include a first hub-side cooling passage and a second hub-side cooling passage different from the first hub-side cooling passage, the first tip-side cooling passage is connected to the first hub-side cooling passage at the first connection portion, the second tip-side cooling passage is connected to the second hub-side cooling passage at the second connection portion; A turbine rotor blade according to any one of claims 1 to 3.

5. the first tip-side cooling passage and the second tip-side cooling passage are connected to the same hub-side cooling passage. A turbine rotor blade according to any one of claims 1 to 3.

6. a distance from a tip-side surface of the shroud portion to the first connection portion is different from a distance from the tip-side surface to the second connection portion; A turbine rotor blade according to any one of claims 1 to 3.

7. In the blade height direction, the position of the hub side end of the leading edge of the airfoil portion is set to 0%, and the position of the tip side end of the leading edge of the airfoil portion is set to 100%. The first connection portion and the second connection portion are located at a position equal to or greater than 85% in the blade height direction. The turbine blade of claim 6.

8. In the blade height direction, the position of the hub side end of the leading edge of the airfoil portion is set to 0%, and the position of the tip side end of the leading edge of the airfoil portion is set to 100%. a tip-side end of at least one of the hub-side cooling passages is located at a position equal to or greater than 70% in the blade height direction; A turbine rotor blade according to any one of claims 1 to 3.

9. In the blade height direction, the position of the hub side end of the leading edge of the airfoil portion is set to 0%, and the position of the tip side end of the leading edge of the airfoil portion is set to 100%. all of the connection portions between the tip-side cooling passage and the hub-side cooling passage are located at positions equal to or greater than 50% in the blade height direction; A turbine rotor blade according to any one of claims 1 to 3.

10. In the blade height direction, the position of the hub side end of the leading edge of the airfoil portion is set to 0%, and the position of the tip side end of the leading edge of the airfoil portion is set to 100%. The first connection portion and the second connection portion are located at a position equal to or greater than 60% and equal to or less than 90% in the blade height direction. A turbine rotor blade according to any one of claims 1 to 3.

11. A compressor; A turbine provided with a plurality of turbine rotor blades according to any one of claims 1 to 3; Equipped with Gas turbine.

12. The plurality of hub-side cooling passages are configured to be supplied with compressed bleed air bled from the compressor. The gas turbine of claim 11.

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