Turbine blade and gas turbine

Abstract

The present application relates to a turbine blade and a gas turbine. The turbine blade is provided with: a blade main body; a cooling passage which extends along a blade height direction inside the blade main body; and a plurality of turbulators which are provided to an inner wall surface of the cooling passage and which are arranged along the cooling passage, the blade main body having a first end portion and a second end portion as both end portions in the blade height direction, a passage width of the cooling passage in a dorsal-ventral direction of the blade main body at the second end portion being larger than the passage width of the cooling passage at the first end portion, and heights of the plurality of turbulators being higher in the blade height direction as they go from the first end portion side toward the second end portion side.

Description

Technical Field

[0001] This invention relates to turbine blades and gas turbines. Background Technology

[0002] In turbine blades of gas turbines and the like, it is known to cool the turbine blades exposed to high-temperature gas flows by having cooling fluid flow through cooling passages formed inside the turbine blades. On the inner wall of such cooling passages, ribbed turbulence diffusers are sometimes provided to increase the heat transfer rate between the cooling fluid and the turbine blades by promoting turbulence in the flow of the cooling fluid within the cooling passages.

[0003] For example, Patent Document 1 discloses a turbine blade with multiple turbulence generators arranged on the inner wall surface of a cooling passage extending along the blade height direction in the direction of cooling fluid flow.

[0004] Prior art literature

[0005] Patent documents

[0006] Patent Document 1: Japanese Patent Application Publication No. 2004-225690 Summary of the Invention

[0007] The problem that the invention aims to solve

[0008] However, in recent years, for example in gas turbines, with the increasing output, the load acting on the turbine blades has tended to increase. In order to make the turbine blades strong enough to withstand such an increasing load, the blade width in the dorsal direction of the turbine blade is sometimes made larger on one side of the turbine's radial direction (i.e., in the direction of the blade height) than on the other side.

[0009] Thus, when the blade width in the dorsal direction of the turbine blade is increased on the radial side, the width (or flow path cross-sectional area) of the cooling passage formed inside the turbine blade may also increase on that radial side.

[0010] The desired blade structure is one that has a cooling path that optimizes internal cooling by selecting an appropriate turbulence generator according to the variation of the turbine blade width.

[0011] In view of the above, the object of at least one embodiment of the present invention is to provide a turbine blade and a gas turbine capable of achieving efficient cooling.

[0012] Solution for solving the problem

[0013] (1) The turbine blade of at least one embodiment of the present invention comprises:

[0014] The blade body has a first end and a second end, which are two ends in the blade height direction;

[0015] Cooling passages extending along the height of the blade within the blade body; and

[0016] Multiple turbulence generators are disposed on the inner wall surface of the cooling passage and arranged along the cooling passage.

[0017] The width of the cooling passage in the dorsal direction of the blade body at the second end is greater than the width of the cooling passage at the first end.

[0018] The height of the plurality of turbulence generators increases in the blade height direction as they move from the first end side toward the second end side.

[0019] In the structure described in (1) above, as the turbulence generator increases in the blade height direction from the first end side (where the cooling passage width is smaller) to the second end side (where the cooling passage width is larger), the heat transfer efficiency improvement effect caused by the turbulence generator can be obtained to the same extent as that on the first end side. Furthermore, in the structure described in (1) above, the turbulence generator height is lower on the first end side in the blade height direction. Therefore, on the first end side, where the cooling passage width is narrower and pressure loss tends to increase, pressure loss due to the presence of the turbulence generator can be suppressed. Therefore, according to the structure described in (1) above, turbine blades with varying cooling passage widths in the blade height direction can be cooled efficiently.

[0020] (2) In several embodiments, based on the structure described in (1) above,

[0021] The ratio (e / D) of the height e of the plurality of turbulents to the width D of the cooling passage in the dorsal direction at the position of the blade height of the plurality of turbulents, and the average (e / D) of the ratio (e / D) with respect to the plurality of turbulents. AVE The relation satisfies 0.5 ≤ (e / D) / (e / D) AVE ≤2.0.

[0022] According to the structure described in (2) above, the ratio (e / D) of the height e of the turbulent associated with one of the multiple turbulents provided in the cooling passage to the width D of the passage becomes approximately the average (e / D) of the multiple turbulents associated with the cooling passage. AVE The value of this property allows for the suppression of extreme changes in heat transfer rate along the blade height direction, such as a decrease or an increase in pressure loss of the cooling fluid. Therefore, turbine blades can be cooled efficiently.

[0023] (3) In several embodiments, based on the structure of (1) or (2) above,

[0024] When the width of the cooling passage at the position of the turbulent device located closest to the first end side in the blade height direction among the plurality of turbulent devices is set as D1, and the width of the cooling passage at the position of the turbulent device located closest to the second end side in the blade height direction among the plurality of turbulent devices is set as D2, the ratio of the passage width D1 to the passage width D2 (D2 / D1) satisfies the relationship 1.5≤(D2 / D1).

[0025] According to the structure described in (3), in turbine blades where the cooling passage width D2 on the second end side is significantly larger than the cooling passage width D1 on the first end side, the height of the turbulence generator increases at the blade height position on the second end side where the cooling passage width is larger. Therefore, as described in (1), the turbine blades can be cooled efficiently.

[0026] (4) In several embodiments, based on any of the structures in (1) to (3) above,

[0027] The spacing between adjacent pairs of turbulents in the blade height direction increases as the blades move from the first end toward the second end.

[0028] The improvement in heat transfer efficiency brought about by the turbulence varies depending on the spacing between adjacent turbulences in the blade height direction. There exists a ratio of spacing to height for turbulences that yields a high heat transfer efficiency. In this regard, according to the structure described in (4) above, as the height of the turbulence increases from the first end to the second end in the blade height direction, the spacing between adjacent turbulences in the blade height direction increases. Therefore, a high heat transfer efficiency can be obtained within the blade height direction range in which turbulences are installed in the cooling passage.

[0029] (5) In several embodiments, based on any of the structures in (1) to (4) above,

[0030] The ratio (P / ea) of the spacing P between adjacent pairs of turbulents in the blade height direction to the average height ea of ​​that pair of turbulents, and the average of the ratios (P / ea) with respect to the plurality of turbulents. AVE The relation satisfies 0.5 ≤ (P / ea) / (P / ea) AVE ≤2.0.

[0031] According to the structure described in (5) above, the (P / ea) associated with a pair of turbulents among the plurality of turbulents provided in the cooling passage becomes close to the average (P / ea) associated with the plurality of turbulents provided in the cooling passage. AVE The value of therefore tends to increase the spacing between adjacent turbulence generators in the blade height direction as the height of the turbulence generator increases from the first end to the second end. Therefore, by appropriately setting (P / ea) or (P / ea) AVE It can achieve a high heat transfer rate in the height direction of the blades with turbulence generators installed in the cooling passage.

[0032] (6) In several embodiments, based on any of the structures in (1) to (5) above,

[0033] The cooling passage is one of a plurality of channels forming a curved flow path inside the blade body.

[0034] In the structure described in (6) above, in a turbine blade where a curved flow path is provided as an internal flow path for cooling fluid flow, the channel constituting the curved flow path is a cooling passage having the structure described in (1) above. Therefore, at the second end side of the aforementioned channel (cooling passage), the heat transfer rate improvement effect brought about by the turbulence generator can be obtained to the same extent as at the first end side, and at the first end side where the channel (cooling passage) has a narrower passage width and tends to have greater pressure loss, the pressure loss caused by the presence of the turbulence generator can be suppressed. Therefore, according to the structure described in (6) above, turbine blades where the passage width of the curved flow path (cooling passage) changes in the blade height direction can be cooled efficiently.

[0035] (7) In several embodiments, based on the structure described in (6) above,

[0036] The cooling passage is the channel that is located at the trailing edge of the plurality of channels constituting the curved flow path, excluding the final channel.

[0037] The turbine blades have multiple final channel turbulence generators disposed on the inner wall surfaces of the back and front sides of the final channel and arranged along the blade height direction.

[0038] When the height of the turbulence generator or the final channel turbulence generator is set to e, and the width of the cooling passage or the final channel in the dorsal direction at the position of the blade height of the turbulence generator or the final channel turbulence generator is set to D,

[0039] Regarding the ratio (e / D) of the height of the turbulent turbine located closest to the first end side in the blade height direction among the plurality of turbulent turbines.E1 The average (e / D) of the ratio (e / D) of the height to the width of the passage for the plurality of turbulence generators. AVE Regarding the ratio (e / D) of the height to the passage width of the final channel turbulent located closest to the first end in the blade height direction among the plurality of final channel turbulents. T_E1 And the ratio (e / D) of the height to the path width of the plurality of final channel turbulence generators. T The average (e / D) T_AVE Relationship satisfaction

[0040] [(e / D) E1 / (e / D) AVE ]<[(e / D) T_E1 / (e / D) T_AVE ].

[0041] As described in (1) above, for a turbulent aerator located in a channel (cooling passage) other than the final channel, the height of the turbulent aerator increases as it moves from the first end side where the cooling passage width is narrower towards the second end side where the cooling passage width is wider. Therefore, the ratio of the height e of the turbulent aerator to the passage width D (e / D) tends to be nearly constant (i.e., the left side of the above relationship is close to 1). Thus, the above relationship means that in the final channel, as the passage width D of the final channel decreases in the blade height direction from the second end side towards the first end side, the height e of the final channel turbulent aerator does not decrease by the same amount as the passage width D.

[0042] That is, according to the structure described in (7) above, the height e of the multiple final channel turbulents in the curved flow path does not change significantly in the blade height direction. Therefore, in the final channel where the cooling fluid is at a higher temperature in the curved flow path, the flow velocity of the cooling fluid, which is usually located downstream of the flow of the cooling fluid, can be increased. As a result, the turbine blades can be cooled more efficiently by the cooling fluid flowing through the final channel.

[0043] (8) In several embodiments, based on the structures described in (1) to (7) above,

[0044] The cooling passage is the channel other than the final channel located at the trailing edge side among the plurality of channels forming a curved flow path inside the blade body.

[0045] The turbine blades have multiple final channel turbulence generators disposed on the inner wall surfaces of the back and front sides of the final channel and arranged along the blade height direction.

[0046] The height of the final channel turbulent in the blade height direction relative to the second end is below the height of the turbulent at the same position in the blade height direction of the other channels located upstream of the flow direction of the cooling fluid.

[0047] According to the structure described in (8), when comparing the heights of the turbulents at the same position in the blade height direction, the height of the final turbulent is lower than that of the turbulents in the other channels. Therefore, the high heat transfer rate of the final turbulent can be maintained, while suppressing the excessive pressure loss caused to the cooling fluid flowing through the final channel.

[0048] (9) In several embodiments, based on any of the structures in (1) to (8) above,

[0049] The cooling passage is the channel other than the final channel located at the trailing edge side among the plurality of channels forming a curved flow path inside the blade body.

[0050] The turbine blades have multiple final channel turbulence generators disposed on the inner wall surfaces of the back and front sides of the final channel and arranged along the blade height direction.

[0051] The height of the final channel turbulence generator is below the height of the turbulence generator in the upstream cooling passage of the plurality of channels, which is located adjacent to and interconnected with the final channel on the upstream side in the flow direction of the cooling fluid.

[0052] According to the structure described in (9), since the height of the turbulence generator (final channel turbulence generator) in the final channel located at the trailing edge in the curved flow path is lower than the height of the turbulence generator in the upstream cooling passage adjacent to and connected to the final channel, more turbulence generators can be installed in the final channel, which has a narrow flow area and where the cooling fluid reaches a relatively high temperature, among the multiple channels constituting the curved flow path. As a result, the turbine blades can be cooled more efficiently by the cooling fluid flowing through the final channel.

[0053] (10) In several embodiments, based on any of the structures in (1) to (9) above,

[0054] The turbine blades also possess:

[0055] A leading-edge side passage, which is disposed inside the blade body at a position closer to the leading edge of the blade body than the cooling passage, and extends along the blade height direction; and

[0056] Multiple leading-edge turbulence generators are disposed on the inner wall of the leading-edge passage and arranged along the blade height direction.

[0057] When the height of the turbulence generator or the leading-edge side turbulence generator is set to e, and the width of the cooling passage or the leading-edge side passage in the dorsal-ventral direction at the position of the blade height of the turbulence generator or the leading-edge side turbulence generator is set to D,

[0058] Regarding the ratio (e / D) of the height of the turbulent turbine located closest to the second end side in the blade height direction among the plurality of turbulent turbines. E2 The average (e / D) of the ratio of the height to the width of the passage for the plurality of turbulence generators. AVE Regarding the ratio (e / D) of the height to the passage width of the leading-edge turbulence generator located closest to the second end in the blade height direction among the plurality of leading-edge turbulence generators. L_E2 And the ratio (e / D) of the height to the passage width of the plurality of leading-edge turbulence generators. L The average (e / D) L_AVE Relationship satisfaction

[0059] [(e / D) E2 / (e / D) AVE ]>[(e / D) L_E2 / (e / D) L_AVE ].

[0060] As described in (1) above, for a turbulent aerator installed in a cooling passage, the height of the turbulent aerator increases as it moves from the first end side, where the passage width of the cooling passage is narrower, toward the second end side, where the passage width of the cooling passage is wider. Therefore, the ratio of the height e of the turbulent aerator to the passage width D (e / D) tends to be nearly constant (i.e., the left side of the above relationship is close to 1). Thus, the above relationship means that as the passage width D of the final channel increases in the blade height direction from the first end side toward the second end side, the height e of the leading edge turbulent aerator does not increase by the same amount as the passage width D.

[0061] That is, according to the structure described in (10) above, the height e of the multiple leading-edge turbulence generators in the leading-edge side passage does not change significantly in the blade height direction. Therefore, in the leading-edge side passage supplied with lower-temperature cooling fluid, the effect of increased heat transfer rate caused by the turbulence generator located on the second end side upstream of the cooling fluid flow is suppressed, thereby suppressing the temperature rise of the cooling fluid flowing toward the first end side. As a result, the turbine blades can be cooled more efficiently.

[0062] (11) In several embodiments, based on any of the structures in (1) to (10) above,

[0063] The cross-sectional area of ​​the cooling passage increases in the direction of blade height from the first end toward the second end.

[0064] According to the structure described in (11), the height of the turbulence generator increases in the blade height direction as it approaches the second end of the cooling passage with a larger flow path cross-sectional area from the first end with a smaller flow path cross-sectional area. Therefore, at the second end, the heat transfer efficiency improvement effect brought about by the turbulence generator can be obtained to the same extent as at the first end. Furthermore, in the structure described in (11), the height of the turbulence generator is lower at the first end in the blade height direction. Therefore, at the first end, where the flow path cross-sectional area is narrower and pressure loss tends to increase, pressure loss due to the presence of the turbulence generator can be suppressed. Therefore, according to the structure described in (11), turbine blades with varying flow path cross-sectional areas in the blade height direction can be cooled efficiently.

[0065] (12) In several embodiments, based on any of the structures in (1) to (11) above,

[0066] The tilt angle θ of the plurality of turbulence generators relative to the flow direction of the cooling fluid in the cooling path and the average θ of the tilt angles of the plurality of turbulence generators. AVE The relationship satisfies 0.5 ≤ θ / θ AVE ≤2.0.

[0067] The improvement in heat transfer rate brought about by the turbulence generator varies depending on the tilt angle θ of the turbulence generator relative to the flow direction of the cooling fluid in the cooling passage. There is a tilt angle of the turbulence generator that can achieve a high heat transfer rate. In this regard, according to the structure described above (12), since the tilt angle θ of the turbulence generator is kept approximately constant in the blade height direction, a high heat transfer rate can be obtained in the range of the blade height direction in which the turbulence generator is installed in the cooling passage.

[0068] (13) In several embodiments, based on any of the structures in (1) to (12) above,

[0069] The turbine blades are moving blades.

[0070] The first end is located radially outside the second end.

[0071] According to the structure described in (13), since the moving blade of the gas turbine, which is a turbine blade, has any one of the structures described in (1) to (12), the moving blade can be cooled efficiently, thereby improving the thermal efficiency of the gas turbine.

[0072] (14) In several embodiments, based on any of the structures in (1) to (12) above,

[0073] The turbine blades are stationary blades.

[0074] The first end is located radially inside the second end.

[0075] According to the structure described in (14), since the stationary blades of the gas turbine, which are turbine blades, have any of the structures described in (1) to (12), the stationary blades can be cooled efficiently, thereby improving the thermal efficiency of the gas turbine.

[0076] (15) The gas turbine of at least one embodiment of the present invention comprises:

[0077] The turbine blade described in any one of (1) to (14) above; and

[0078] A burner for generating combustion gases that flow in a combustion gas path in which the turbine blades are disposed.

[0079] According to the structure described in (15), since the turbine blades have any of the structures described in (1) to (14), the amount of cooling fluid supplied to the serpentine flow path for cooling the turbine blades can be reduced, thereby improving the thermal efficiency of the gas turbine.

[0080] Invention Effects

[0081] According to at least one embodiment of the present invention, the cooling path of the turbine blades is optimized, the amount of cooling fluid is reduced, and the thermal efficiency of the turbine is improved. Attached Figure Description

[0082] Figure 1 This is a schematic diagram of a gas turbine with turbine blades applied according to one embodiment.

[0083] Figure 2 This is a partial cross-sectional view of the moving blade (turbine blade) along the blade height direction in one embodiment.

[0084] Figure 3 It means Figure 2 A cross-sectional view of BB.

[0085] Figure 4A yes Figure 2 A cross-sectional view of the moving blade in section AA.

[0086] Figure 4B yes Figure 2 A cross-sectional view of the moving blade in the BB section.

[0087] Figure 4C yes Figure 2 A cross-sectional view of the moving blade in the CC section.

[0088] Figure 5This is a schematic diagram illustrating the structure of a turbulence generator according to one embodiment.

[0089] Figure 6 This is a schematic diagram illustrating the structure of a turbulence generator according to one embodiment.

[0090] Figure 7 yes Figures 2 to 4C A schematic cross-sectional view of the moving blade (turbine blade) shown.

[0091] Figure 8 It means Figure 7 A schematic diagram of the DD cross section.

[0092] Figure 9 This is a schematic cross-sectional view of a stator blade (turbine blade) according to one embodiment. Detailed Implementation

[0093] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. The dimensions, materials, shapes, and relative arrangements of the constituent components described in the embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0094] First, a gas turbine with turbine blades using several implementation methods will be described.

[0095] Figure 1 This is a schematic structural diagram of a gas turbine with turbine blades according to one embodiment. (See diagram for example.) Figure 1 As shown, the gas turbine 1 includes a compressor 2 for generating compressed air, a burner 4 for generating combustion gases using compressed air and fuel, and a turbine 6 configured to rotate driven by the combustion gases. In the case of a gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6.

[0096] The compressor 2 includes a plurality of stationary blades 16 fixed to the side of the compressor housing 10, and a plurality of moving blades 18 installed on the rotor 8 in an alternating manner relative to the stationary blades 16.

[0097] Air introduced from air inlet 12 is delivered to compressor 2, where it is compressed by multiple stationary vanes 16 and multiple moving vanes 18, thus becoming high-temperature and high-pressure compressed air.

[0098] Fuel and compressed air generated by compressor 2 are supplied to burner 4, where the fuel and compressed air are mixed and burned to generate combustion gas, which serves as the working fluid of turbine 6. Figure 1 As shown, multiple burners 4 can also be arranged circumferentially around the rotor within the housing 20.

[0099] The turbine 6 has a combustion gas flow path 28 formed in the turbine housing 22, including a plurality of stationary blades 24 and moving blades 26 disposed in the combustion gas flow path 28.

[0100] The stator blades 24 are fixed to the side of the turbine housing 22, and multiple stator blades 24 arranged circumferentially along the rotor 8 constitute a stator blade cascade. Additionally, the moving blades 26 are mounted on the rotor 8, and multiple moving blades 26 arranged circumferentially along the rotor 8 constitute a moving blade cascade. The stator blade cascade and the moving blade cascade are arranged alternately in the axial direction of the rotor 8.

[0101] In turbine 6, combustion gas from burner 4 flows into combustion gas flow path 28 and drives rotor 8 to rotate via multiple stationary vanes 24 and multiple moving vanes 26, thereby driving a generator connected to rotor 8 to generate electricity. The combustion gas driving turbine 6 is then discharged to the outside via exhaust chamber 30.

[0102] In several embodiments, at least one of the moving blade 26 or the stationary blade 24 of the turbine 6 is the turbine blade 40 described below.

[0103] The following explanation will mainly refer to the diagram of the moving blade 26 of the turbine blade 40, but the same explanation can also be applied to the stationary blade 24 of the turbine blade 40.

[0104] Figure 2 This is a partial cross-sectional view of the moving blade 26 (turbine blade 40) along the blade height direction according to one embodiment. Figure 3 It means Figure 2 The diagram shows a BB cross-section. It should be noted that the arrows in the diagram indicate the direction of the cooling fluid flow. Additionally, Figures 4A to 4C These are cross-sectional views of the moving blade 26 at three different positions along the blade height. Figure 4A It means Figure 2 A diagram of the AA section near the top 48. Figure 4B It means Figure 2 A diagram of the BB cross-section near the middle region in the blade height direction (i.e., with...). Figure 3 (Equivalent diagram) Figure 4C It means Figure 2 A diagram of the CC section near the base 50.

[0105] like Figure 2 and Figure 3 As shown, in one embodiment, the moving blade 26 of the turbine blade 40 includes a blade body 42, a platform 80, and a blade root 82. The blade root 82 is embedded in the rotor 8 (see reference). Figure 1 In this configuration, the moving blade 26 rotates together with the rotor 8. The platform 80 and the blade root 82 are integrally formed.

[0106] The blade body 42 is arranged to extend along the radial direction (hereinafter, sometimes simply referred to as "radial" or "span direction") of the rotor 8, and has: a base end 50, which has a fixed platform 80; and a top end 48, which is located on the opposite side (radially outward) of the base end 50 in the blade height direction (radial direction of the rotor 8), and is formed by a top plate 49 forming the top of the blade body 42.

[0107] In addition, the blade body 42 of the moving blade 26 has a leading edge 44 and a trailing edge 46 from the base 50 to the tip 48. The blade surface of the blade body 42 includes a concave pressure surface (ventral surface) 56 and a convex negative pressure surface (back surface) 58 extending along the blade height direction between the base 50 and the tip 48.

[0108] A cooling flow path is provided inside the blade body 42 for the flow of cooling fluid (e.g., air) to cool the turbine blades 40. Figure 2 and Figure 3 In the exemplary embodiment shown, two curved flow paths (serpentine flow paths) 61A and 61B and a leading edge side passage 36, which is located on the leading edge 44 side of the curved flow paths 61A and 61B, are formed in the blade body 42 as cooling flow paths. Cooling fluid from the outside is supplied to the curved flow paths 61A and 61B and the leading edge side passage 36 via internal flow paths 84A, 84B and 85, respectively.

[0109] In this way, by supplying cooling fluid to the curved flow paths 61A, 61B, leading edge side passage 36 and other cooling flow paths, the blade body 42, which is located in the combustion gas flow path 28 of the turbine 6 and exposed to high temperature combustion gas, is convectively cooled from the inner wall side of the blade body 42.

[0110] The two curved flow paths include a curved flow path 61A located on the leading edge 44 side and a curved flow path 61B located on the trailing edge 46 side. The curved flow paths 61A and 61B are separated by ribs (partitions) 31 disposed inside the blade body 42 and extending along the blade height direction.

[0111] In addition, the curved flow path 61A located on the leading edge side and the leading edge side passage 36 are separated by a rib 29 provided inside the blade body 42 and extending along the blade height direction.

[0112] In addition, the two curved flow paths 61A and 61B each have multiple channels 60 (channels 60a to 60c, 60d to 60f) extending along the blade height direction.

[0113] In each of the curved flow paths 61A and 61B, adjacent channels 60 are separated by ribs 32 located inside the blade body 42 and extending along the blade height direction.

[0114] Furthermore, in each of the curved flow paths 61A and 61B, adjacent channels 60 are interconnected at either the top end 48 or the base end 50. A return flow path 33 is formed at this connection, where the flow direction of the cooling fluid reverses in the blade height direction. Thus, the curved flow paths 61A and 61B as a whole have a radially meandering shape. That is, multiple channels 60a-60c and multiple channels 60d-60f are interconnected via the return flow path 33 to form curved flow paths 61A and 61B.

[0115] exist Figure 2 and Figure 3 In the exemplary embodiment shown, the curved flow path 61A on the leading edge side includes three channels 60a to 60c, which are arranged sequentially from the trailing edge 46 side toward the leading edge 44 side. Additionally, the curved flow path 61B on the trailing edge side includes three channels 60d to 60f, which are arranged sequentially from the leading edge 44 side toward the trailing edge 46 side.

[0116] The multiple channels 60 forming the tortuous flow paths 61A and 61B include a final channel 66 located on the downstream side of the flow of the cooling fluid. That is, in the tortuous flow path 61A, the channel 60c located on the leading edge 44 side is the final channel 66, and in the tortuous flow path 61B, the channel 60f located on the trailing edge 46 side is the final channel 66.

[0117] In the turbine blade 40 having the aforementioned curved flow paths 61A and 61B, cooling fluid is introduced, for example, through internal flow paths 84A and 84B formed inside the blade root 82 into the upstream passage of the curved flow paths 61A and 61B. Figure 2 and Figure 3 In the example shown, channels 60a and 60d flow sequentially downstream in the plurality of channels 60 constituting the curved flow paths 61A and 61B. Furthermore, the cooling fluid flowing in the final channel 66, the most downstream side of the cooling fluid flow direction in the plurality of channels 60, flows out through outlet openings 64A and 64B provided on the tip 48 side of the blade body 42 to the combustion gas flow path 28 outside the turbine blade 40. Outlet openings 64A and 64B are openings formed in the top plate 49. At least a portion of the cooling fluid flowing in the final channel 66 is discharged from the outlet opening 64B. By providing the outlet opening 64B in the final channel 66 on the trailing edge 46 side, a stagnation space for the cooling fluid is created in the space near the top plate 49 of the final channel 66, thereby suppressing overheating of the inner wall surface of the top plate 49.

[0118] It should be noted that the shapes of the curved flow paths 61A and 61B are not limited to... Figure 2 and Figure 3The shape shown. For example, the number of curved flow paths formed inside the blade body 42 of a turbine blade 40 is not limited to two, but can also be one or more than three. Alternatively, the curved flow path can branch into multiple flow paths at the branching point of the curved flow path. In either case, the channel located on the trailing edge side of the channel constituting the curved flow path is usually the final channel of the curved flow path.

[0119] Furthermore, the leading-edge side passage 36 is the cooling passage 59 closest to the leading edge 44 and has the highest heat load. The leading-edge side passage 36 communicates with the internal flow path 85 at the base end 50 and with the outlet opening 38 of the top plate 49 formed at the top end 48. Cooling fluid supplied to the leading-edge side passage 36 via the internal flow path 85 flows from the base end 50 to the top end 48 in the unidirectional leading-edge side passage 36 and is discharged from the outlet opening 38 into the combustion gas flow path 28. During its flow through the leading-edge side passage 36, the cooling fluid convectively cools the inner wall surface of the leading-edge side passage 36.

[0120] In several implementations, such as Figure 2 As shown, a plurality of cooling holes 70 are formed on the trailing edge portion 47 (including the portion of the trailing edge 46) of the blade body 42 in an arrangement along the blade height direction. The plurality of cooling holes 70 communicate with a cooling flow path formed inside the blade body 42 (in the illustrated example, the final channel 66, i.e., channel 60f, of the curved flow path 61B on the trailing edge side), and open on the surface of the trailing edge portion 47 of the blade body 42, i.e., the trailing edge end face 46a. It should be noted that... Figure 3 The illustration of cooling hole 70 is omitted in the text.

[0121] A portion of the cooling fluid flowing in the cooling flow path passes through the aforementioned cooling hole 70, which is connected to the cooling flow path, and flows out from the opening of the trailing edge end face 46a of the trailing edge portion 47 of the blade body 42 to the combustion gas flow path 28 outside the turbine blade 40. By the cooling fluid passing through the cooling hole 70 in this way, the trailing edge portion 47 of the blade body 42 is convectively cooled.

[0122] The blade body 42 of the moving blade 26 has two ends in the blade height direction, namely a first end 101 and a second end 102. The first end 101 is the end on the tip 48 side of the blade body 42, and the second end 102 is the end on the base 50 side of the blade body 42. That is, in the moving blade 26, the first end 101 is located radially outward of the second end 102.

[0123] like Figures 4A to 4CAs shown, the blade width in the dorsal-ventral (back side 58 - ventral side 56) direction of the blade body 42 is greater on the second end 102 side (base end 50 side) than on the first end 101 side (apex 48 side). That is, in the blade body 42, the blade width in the dorsal-ventral direction of the second end 102 is greater than the blade width in the dorsal-ventral direction of the first end.

[0124] In addition, such as Figures 4A to 4C As shown, in the moving blade 26, the width D2 of each channel 60 of the curved flow paths 61A and 61B in the dorsal and ventral directions of the blade body 42 at the second end 102 (i.e., the base end 50 side) and the leading edge side passage 36 is ( Figure 4C The terms DL2, Da2, Db2, etc., are shown; hereinafter, they will also be uniformly referred to as "D2". The width of the cooling flow path D1 at the first end 101 (i.e., the top 48 side) is greater than the width of the cooling flow path D1 at the first end 101 (i.e., the top 48 side). Figure 4A The terms DL1, Da1, Db1, etc., are shown below; hereinafter, they will also be uniformly referred to as "D1".

[0125] Here, the passage width D (DL, Da, Db, etc.; hereinafter, it is also uniformly referred to as "D") of the cooling flow path in the dorsal and ventral directions of the blade body 42 is defined as follows: in each passage (each channel 60 and the leading edge side passage 36), from the inner wall surface 63P on the pressure surface 56 side of the blade body 42 (refer to...) Figure 4B The inner wall surface 63P and the inner wall surface 63S on the negative pressure surface 58 side were measured (refer to...). Figure 4B The maximum value of the distance between ).

[0126] It should be noted that, regarding the cooling flow path width D, considering cases where the path shape is not rectangular but deformed, such as a rhomboid, trapezoidal, or triangular cross-section, it is sometimes represented by the equivalent diameter ED shown in Equation (I) below. The equivalent diameter ED is equivalent to the aforementioned path width D.

[0127] ED = 4A / L···(I)

[0128] In equation (I) above, ED represents the equivalent diameter, A represents the cross-sectional area of ​​the passage, and L represents the wetted perimeter length of the passage profile (the length of a complete circumference of a passage profile). Therefore, in the following explanation, the passage width D can also be understood as the equivalent diameter ED.

[0129] For example, considering the third passage 60b (counting from the leading edge 44 side) among the multiple passages (each passage 60 of the curved flow paths 61A and 61B and the leading edge side passage 36) provided in the blade body 42, the passage width Db1 on the first end 101 side (top 48 side) and the passage width Db2 on the second end 102 side (base 50 side) satisfy the relationship Db1 < Db2. Furthermore, the same relationship holds for other passages.

[0130] It should be noted that, alternatively, the passage width D can gradually increase in the blade height direction as it moves from the first end 101 side toward the second end 102 side.

[0131] Alternatively, the cross-sectional area of ​​each channel 60 may increase in the direction of blade height as it approaches the second end from the first end.

[0132] Ribbed turbulence generators 34 are provided on at least a few of the inner wall surfaces 63 (inner wall surface 63P on the pressure surface 56 side and / or inner wall surface 63S on the negative pressure surface 58 side) of the plurality of channels 60 constituting the curved flow paths 61A and 61B. Figures 2 to 4C In the exemplary embodiment shown, multiple turbulence generators 34 are provided on the inner wall surface 63P on the pressure surface 56 side and the inner wall surface 63S on the negative pressure surface 58 side of the multiple channels 60 along the blade height direction.

[0133] In addition, in several implementations, such as Figures 2 to 4C As shown, multiple turbulence generators 35 (leading-edge turbulence generators 35) are also provided on the inner wall surface of the leading-edge side passage 36 along the blade height direction.

[0134] Here, Figure 5 and Figure 6 These are schematic diagrams illustrating the structure of the turbulence generator 34 in one embodiment. Figure 5 yes Figures 2 to 4C The diagram shows a partial cross-section of the turbine blade 40 along a plane that includes the blade height direction (radial direction of rotor 8) and the dorsal direction (approximately circumferential direction of rotor 8). Figure 6 yes Figures 2 to 4C A schematic diagram of a partial cross-section of the turbine blade 40 along a plane including the blade height direction (radial direction of rotor 8) and the axial direction of rotor 8.

[0135] like Figure 5 As shown, each turbulence generator 34 is disposed on the inner wall surface 63 of the channel 60, and the height of the turbulence generator 34 relative to the inner wall surface 63 is e. Additionally, as... Figure 5 and Figure 6 As shown, in channel 60, multiple turbulence generators 34 are arranged at intervals of spacing P. Additionally, as... Figure 6As shown, the flow direction of the cooling fluid in channel 60 is ( Figure 6 The angle between the arrow LF and each turbulence generator 34 (where θ is an acute angle; hereinafter also referred to as the "tilt angle") is the tilt angle θ.

[0136] If the aforementioned turbulence generator 34 is provided in the channel 60, when the cooling fluid flows in the channel 60, turbulence such as the generation of vortices is promoted near the turbulence generator 34. That is, the cooling fluid passing over the turbulence generator 34 forms vortices between adjacent turbulence generators 34 located downstream. As a result, near the midpoint between adjacent turbulence generators 34 in the direction of cooling fluid flow, turbulent vortices of cooling fluid are formed and come into contact with the inner wall surface 63 of the channel 60, thereby increasing the heat transfer rate between the cooling fluid and the blade body 42, and enabling efficient cooling of the turbine blade 40.

[0137] That is, with the increasing output of gas turbines, the thermal load applied to the turbine blades increases. Therefore, there is a need to increase the blade width in the dorsal direction of the second end 102 on the base end 50 side supporting the turbine blade, and to miniaturize the first end 101 on the tip 48 side. In this case, a blade shape that reduces the blade width on the first end 101 side and increases the blade width on the second end 102 side is selected. Therefore, the cooling flow path disposed inside the blade body is selected such that the cross-sectional area of ​​the cooling flow path on the first end 101 side is smaller, and the cross-sectional area of ​​the cooling flow path on the second end 102 side is larger. The turbulence enhancer 34 is a turbulence promoting member used to increase heat transfer on the inner wall surface of the cooling flow path. It is important to select an appropriate height e, spacing P, and tilt angle θ of the turbulence enhancer according to the change in the cross-sectional area of ​​the cooling flow path to maximize the cooling performance of the blade body.

[0138] The improvement in heat transfer efficiency brought about by the turbulence generator 34 varies depending on the height e, spacing P, tilt angle θ, and channel (path) width D of the turbulence generator.

[0139] For example, the change in the generation state of vortices in the cooling fluid, depending on the tilt angle θ of the turbulence diffuser 34, affects the heat transfer rate between the turbulence diffuser and the inner wall of the blade. Furthermore, if the height e of the turbulence diffuser 34 is too high compared to the spacing P, the vortices may sometimes not contact the inner wall surface 63. Therefore, there exists an appropriate range between the heat transfer rate and the tilt angle θ of the turbulence diffuser 34, and between the heat transfer rate and the ratio of spacing P to height e (P / e), as will be described later. Additionally, if the height e of the turbulence diffuser 34 is too high compared to the passage width D, the pressure loss of the cooling fluid increases. On the other hand, if the passage width D in the back-to-back direction is too wide compared to the height e of the turbulence diffuser 34, the increased heat transfer rate due to the vortices cannot be expected, resulting in a decrease in heat transfer rate and reduced cooling performance. In other words, there exists an appropriate height e, spacing P, and tilt angle θ of the turbulence diffuser 34 that yields a high heat transfer rate based on the shape of the cooling flow path.

[0140] It should be noted that, similar to the case of the turbulence 34 described above, the effect of improving the heat transfer rate brought about by the turbulence 35 (leading edge turbulence 35) provided on the leading edge side passage 36 also varies depending on the tilt angle, spacing, height of the turbulence 35, and the passage width of the leading edge side passage 36 in the dorsal and ventral directions.

[0141] The following is for reference Figures 2 to 4C ,and Figures 7-9 The features of the turbine blade 40 in several embodiments, including the features of the turbulence generator 34, will be described in more detail, but prior to that, refer to Figure 9 The structure of the stator blade 24 (turbine blade 40) in one embodiment will be described.

[0142] Here, Figure 7 yes Figures 2 to 4C The schematic cross-sectional view of the moving blade 26 (turbine blade 40) shown is shown. Figure 8 It means Figure 7 A schematic diagram of the DD cross-section. Additionally, Figure 9 This is a schematic cross-sectional view of the stator blade 24 (turbine blade 40) according to one embodiment. The arrows in the figure indicate the direction of flow of the cooling fluid LF.

[0143] like Figure 9 As shown, in one embodiment, the stator blade 24 (turbine blade 40) includes a blade body 42, an inner shroud 86 located radially inward relative to the blade body 42, and an outer shroud 88 located radially outward relative to the blade body 42. The outer shroud 88 is supported on the turbine housing 22 (see reference 22). Figure 1The stator blade 24 is supported in the turbine housing 22 via the outer shroud 88. The blade body 42 has an outer end 52 located on the side of the outer shroud 88 (i.e., radially outer) and an inner end 54 located on the side of the inner shroud 86 (i.e., radially inner).

[0144] The blade body 42 of the stationary blade 24 has a leading edge 44 and a trailing edge 46 from the outer end 52 to the inner end 54. The blade surface of the blade body 42 includes a pressure surface (ventral surface) 56 and a negative pressure surface (back surface) 58 extending along the blade height direction between the outer end 52 and the inner end 54.

[0145] Inside the blade body 42 of the stationary blade 24, a curved flow path 61 formed by multiple channels 60 is created. Figure 9 In the exemplary embodiment shown, a curved flow path 61 is formed by five channels 60a to 60e. The channels 60a to 60e are arranged sequentially from the leading edge 44 side toward the trailing edge 46 side.

[0146] exist Figure 9 In the stationary blade 24 (turbine blade 40) shown, cooling fluid is introduced into the curved flow path 61 via an internal flow path (not shown) formed inside the outer shroud 88, and flows sequentially downstream in multiple channels 60. Furthermore, the cooling fluid flowing in the final channel 66 (channel 60e) at the downstream end of the flow direction of the cooling fluid in the multiple channels 60 flows out to the combustion gas flow path 28 outside the stationary blade 24 (turbine blade 40) via an outlet opening 64 provided on the inner end 54 side (inner shroud 86 side) of the blade body 42, or is discharged into the combustion gas from the cooling hole 70 of the trailing edge portion 47 described later.

[0147] In the still blade 24, at least several of the inner wall surfaces of the multiple channels 60 are provided with the aforementioned turbulence generators 34. Figure 9 In the exemplary embodiment shown, a plurality of turbulence generators 34 are provided on the inner wall surface of each of the plurality of channels 60.

[0148] In the stationary blade 24, multiple cooling holes 70 may also be formed on the trailing edge 47 of the blade body 42 in a manner arranged along the blade height direction.

[0149] The blade body 42 of the stationary blade 24 has a first end 101 and a second end 102 as two ends in the blade height direction. The first end 101 is the end on the inner end 54 side of the blade body 42, and the second end 102 is the end on the outer end 52 side of the blade body 42. That is, in the stationary blade 24, the first end 101 is located radially inside the second end 102.

[0150] The blade width in the dorsal direction of the blade body 42 of the stator blade 24 (turbine blade 40) is greater on the outer end 52 side (second end 102 side) than on the inner end 54 side (first end 101 side). That is, in the blade body 42, the blade width at the second end 102 is greater than the blade width at the first end 101.

[0151] In addition, although not specifically illustrated, regarding the passage width D of the channel 60, similar to the case of the moving blade 26 described above, the passage width D2 of each channel 60 of the curved flow path 61 in the dorsal direction of the blade body 42 at the second end 102 (i.e. the outer end 52 side) is larger than the passage width D1 at the first end 101 (i.e. the inner end 54 side).

[0152] Alternatively, the passage width D gradually increases in the blade height direction from the first end 101 side toward the second end 102 side.

[0153] Alternatively, the flow path cross-sectional area of ​​each of the channels 60 can increase in the blade height direction as it approaches the second end from the first end. It should be noted that the aforementioned idea of ​​the equivalent diameter ED can also be applied to the passage width D of the stationary blade 24.

[0154] Next, refer to Figures 2 to 4C ,as well as Figures 7-9 More specific features of the turbine blade 40 in several embodiments will be described.

[0155] In several embodiments of the turbine blade 40 (moving blade 26 or stationary blade 24), a characteristic is that, with respect to the height of the plurality of turbulence generators 34 disposed in at least one of the cooling passages 59 serving as channels 60a to 60f, the height increases in the blade height direction from the first end 101 side (the tip 48 side of the moving blade 26, the inner end 54 side of the stationary blade 24) towards the second end 102 side (the base 50 side of the moving blade 26, the outer end 52 side of the stationary blade 24). That is, in the blade height direction, as the passage width D of the cooling passage 59 increases from the first end 101 side towards the second end 102 side, the height e of the turbulence generator 34 increases. Alternatively, in the blade height direction, as the flow path cross-sectional area of ​​the cooling passage 59 increases from the first end 101 side towards the second end 102 side, the height e of the turbulence generator 34 (the height based on the inner wall surface 63 of the cooling passage 59) increases.

[0156] Alternatively, the height of the multiple turbulence generators 34 can vary gradually for each turbulence generator 34 in the blade height direction. That is, the height e of the multiple turbulence generators 34 disposed in the cooling passage 59 can be set such that the height e of the turbulence generator 34 closer to the second end 102 is higher than the height of the other turbulence generator 34 (i.e., the turbulence generator 34 closer to the first end 101) among any two turbulence generators 34 with different positions in the blade height direction.

[0157] Alternatively, the height of the multiple turbulence generators 34 can vary in stages for each region along the blade height direction. That is, the cooling passage 59 can be divided into multiple regions along the blade height direction, with the turbulence generators 34 belonging to the same region along the blade height direction having the same height e. Based on this, the height e of each of the multiple turbulence generators 34 can be set such that the height e of the turbulence generators 34 belonging to the region along the blade height direction closer to the second end 102 is higher than the height e of the turbulence generators 34 belonging to the region along the blade height direction closer to the first end 101.

[0158] Thus, referring to Figure 8 An example illustrating the variation of the height of multiple turbulence generators 34 in the direction of each blade height is given. Here, Figure 8 This is a cross-sectional view of one of the cooling passages 59 that constitute the curved flow path 61 (here, the passage 60b of the curved flow path 61A of the moving blade 26).

[0159] Figure 8 The exemplary cooling passage 59 shown is divided into three regions in the blade height direction. Furthermore, the plurality of turbulence generators 34 disposed in the cooling passage 59 include, among the three regions, a turbulence generator 34a belonging to the region closest to the first end 101 (the region on the side of the top tip 48), a turbulence generator 34c belonging to the region closest to the second end 102 (the region on the side of the base end 50), and a turbulence generator 34b belonging to the region between the two (the middle region).

[0160] The representative path width Da of the cooling passage 59 in the dorsal direction at the location of the turbulent 34a in the region of the top 48, the representative path width Db of the cooling passage 59 in the dorsal direction at the location of the turbulent 34b in the middle region, and the representative path width DDc of the cooling passage 59 in the dorsal direction at the location of the turbulent 34c in the region of the base 50 satisfy the relationship Da < Db < Dc.

[0161] It should be noted that the representative passage width D in the dorsal and ventral directions of the cooling passage 59 in each region can also be the average value of the passage width D of the cooling passage 59 at the position of the blade height of the respective turbulent 34 in that region.

[0162] In addition, the multiple turbulence generators 34a, 34b, and 34c belonging to the regions in each blade height direction have the same height. The height ea of ​​turbulence generator 34a belonging to the region on the top 48 side, the height eb of turbulence generator 34b belonging to the middle region, and the height ec of turbulence generator 34c belonging to the region on the base 50 side satisfy the relationship ea < eb < ec.

[0163] In this way, the height e of the multiple turbulence generators 34 located in the cooling passage 59 can vary in stages for each blade height region.

[0164] It should be noted that, in Figure 7 The turbine blade 40 (moving blade 26) shown is... Figure 9 In the turbine blade 40 (stationary blade 24) shown, for the final channel 66 (of the channels 60a to 60f that constitute the curved flow path 61) Figure 7 Channel 60f in the middle, and Figure 9 Cooling passage 59 other than channel 60e) in the middle, and Figure 8 Similarly, multiple turbulence generators 34 vary in stages for each blade height region.

[0165] It should be noted that, in Figure 8 In the example shown, the cooling passage 59 is divided into three regions in the blade height direction, and the height of the turbulent 34 varies in three stages. However, in other examples (other cooling passages 59), the cooling passage 59 may be divided into n regions in the blade height direction, and the height of the turbulent 34 may vary in n stages (where n is an integer greater than 2).

[0166] It should be noted that, Figure 7 The shown blade 26 contains channels 60a to 60e (cooling passages). Figure 9 The channels 60a to 60d (cooling passages) in the stationary blade 24 shown are divided into n regions (where n is more than 2 and less than 5) in the blade height direction, and the height of the turbulence generator 34 changes in n stages in the blade height direction.

[0167] By providing a turbulence generator 34 on the inner wall surface 63 of the cooling passage 59, the heat transfer rate between the cooling fluid and the turbine blades 40 is improved compared to a smooth surface on the inner wall surface 63 without the turbulence generator 34. However, when the passage width D of the cooling passage 59 varies in the blade height direction, if the height e of the turbulence generator 34 is set to a constant height, the effect of improving the heat transfer rate is reduced in the blade height direction where the passage width D of the cooling passage 59 is wider compared to the blade height direction where the passage width D of the cooling passage 59 is narrower. This is because if the height of the turbulence generator 34 is relatively low relative to the passage width D of the cooling passage 59, it is difficult to efficiently generate turbulent eddies in the cooling fluid flowing through the relatively wide cooling passage 59.

[0168] Regarding this, in the above-described embodiment, it is preferable to select the height e of the turbulence generator 34 in a manner that maintains the heat transfer rate on the blade surface even when the width D of the cooling passage 59 varies in the blade height direction. In the blade height direction, the height of the turbulence generator 34 is increased as it approaches the second end 102 of the cooling passage 59, where the width D is smaller, from the first end 101, which has a larger width D, in order to maintain the heat transfer rate on the blade surface. As a result, on the second end 102 side, vortices can be generated efficiently by the turbulence generator 34, and the same level of improvement in heat transfer rate brought about by the turbulence generator 34 can be obtained as on the first end 101 side.

[0169] On the other hand, compared to the second end 102 side with a larger passage width D, from the viewpoint of increased pressure loss of the cooling fluid, it is undesirable to have the turbulence generator height e on the first end 101 side with a smaller passage width D be higher than an appropriate height. In the above embodiment, the passage width D of the cooling passage 59 is smaller on the first end 101 side in the blade height direction, and the height e of the turbulence generator 34 is set lower. Therefore, from the viewpoint of pressure loss of the cooling fluid flowing in the cooling flow path, on the first end 101 side, which tends to have greater pressure loss due to the narrower passage width D of the cooling passage 59, the increase in pressure loss due to the presence of the turbulence generator 34 can be suppressed.

[0170] Therefore, according to the above-described embodiment, turbine blades 40 with varying path width D of cooling passage 59 in the blade height direction can be cooled efficiently.

[0171] In several embodiments, the ratio (e / D) of the height e of any one of the plurality of turbulence generators 34 disposed in the cooling passage (at least one of channels 60a to 60f) to the passage width D in the dorsal direction of the cooling passage 59 at the position in the blade height direction of the turbulence generator 34, and the average (e / D) of the ratio (e / D) of the plurality of turbulence generators 34 disposed in the cooling passage 59 (i.e., all the turbulence generators 34 disposed in the cooling passage 59) is used. AVE The condition is satisfied that 0.5 ≤ (e / D) / (e / D) AVE Relationships ≤2.0.

[0172] Furthermore, in several embodiments, the above-mentioned (e / D) and (e / D) are... AVE It can also satisfy 0.9≤(e / D) / (e / D) AVE ≤1.1.

[0173] Alternatively, in several implementations, the above-described (e / D) and (e / D) are... AVE It can also satisfy (D1 / D2)≤(e / D) / (e / D) AVE ≤(D2 / D1). Here, D1 is the width of the cooling passage 59 at the position of the turbulent 34 closest to the first end 101 in the blade height direction among the plurality of turbulent 34. D2 is the width of the cooling passage 59 at the position of the turbulent 34 closest to the second end 102 in the blade height direction.

[0174] It should be noted that the above relationship can also be made true for each (all) of the plurality of turbulence generators 34 provided in the cooling passage 59 described above.

[0175] In the above embodiment, the (e / D) associated with any one of the plurality of turbulents 34 provided in the cooling passage 59 is set to be close to the average (e / D) of all the plurality of turbulents provided in the cooling passage. AVE The value of (e / D) is set such that, in the blade height direction from the first end 101 to the second end 102, the change in (e / D) is smaller than the change in the passage width D of the cooling passage. Therefore, it is possible to suppress extreme reductions in heat transfer rate or extreme increases in pressure loss in the blade height direction, thereby suppressing uneven distribution of metal temperature on the blade wall and efficiently cooling the turbine blade 40.

[0176] In several embodiments, when the passage width D of the cooling passage 59 located at the position of the turbulent 34 closest to the first end 101 in the blade height direction among the plurality of turbulent 34 provided in the cooling passage 59 (at least one of the channels 60a to 60f) is set as D1, and the passage width D of the cooling passage 59 located at the position of the turbulent 34 closest to the second end 102 in the blade height direction is set as D2, the ratio of the passage width D1 to the passage width D2 (D2 / D1) satisfies the relationship 1.5≤(D2 / D1).

[0177] Alternatively, the path width D1 and the path width D2 can also satisfy the relationship 2.0 ≤ (D2 / D1).

[0178] Alternatively, the path width D1 and the path width D2 can also satisfy the relationship 2.5 ≤ (D2 / D1).

[0179] In the above embodiment, in the turbine blade 40 where the passage width D2 of the cooling passage 59 on the second end 102 side is significantly larger than the passage width D1 of the cooling passage 59 on the first end 101 side, since the height of the turbulence generator 34 increases at the position in the blade height direction on the second end 102 side where the passage width D of the cooling passage 59 is larger, the turbine blade 40, where the passage width D of the cooling passage 59 varies in the blade height direction, can be cooled efficiently.

[0180] In several embodiments, the spacing P in the blade height direction of a pair of adjacent turbulents 34 in the cooling passage 59 (at least one of passages 60a to 60f) increases in the blade height direction as the distance from the first end 101 to the second end 102 increases.

[0181] The improved heat transfer rate brought about by the turbulence generator 34 varies depending on the spacing P between adjacent turbulence generators 34 in the blade height direction. There exists a ratio (P / e) of spacing P to height e for which a high heat transfer rate can be obtained. In this regard, according to the above-described embodiment, as the height e of the turbulence generators 34 increases from the first end 101 to the second end 102 in the blade height direction, the spacing P between adjacent turbulence generators 34 increases. Therefore, within this cooling passage 59, a high heat transfer rate can be obtained over the entire range from the first end 101 to the second end 102 in the blade height direction where the turbulence generators 34 are installed.

[0182] It should be noted that, in the above-described embodiments, the spacing P of a pair of adjacent turbulence generators 34 in the blade height direction may also gradually vary for each pair of turbulence generators 34 in the blade height direction. That is, the spacing P of the plurality of turbulence generators 34 disposed in the cooling passage 59 may be set such that the spacing P of the pair of turbulence generators 34 closer to the second end 102 in any two pairs of turbulence generators 34 with different positions in the blade height direction is greater than the spacing P of the pair of turbulence generators 34 closer to the first end 101 in the other pair of turbulence generators 34.

[0183] Alternatively, the spacing P of a pair of adjacent turbulence generators 34 in the blade height direction can vary periodically for each region in the blade height direction. That is, the cooling passage 59 can be divided into multiple regions in the blade height direction, such that multiple turbulence generators 34 belonging to the same region in each blade height direction have the same spacing P. Furthermore, the spacing P of the multiple turbulence generators 34 provided in the cooling passage 59 can be set such that the spacing P of the multiple turbulence generators 34 belonging to the region in the blade height direction near the second end 102 is larger than the spacing P of the turbulence generators 34 belonging to the region in the blade height direction near the first end 101.

[0184] For example, as mentioned above, Figure 8 The exemplary cooling passage 59 shown is divided into three regions in the blade height direction. The plurality of turbulencers 34 disposed in the cooling passage 59 include a turbulencer 34a belonging to the region closest to the first end 101 (the region on the side of the top 48), a turbulencer 34c belonging to the region closest to the second end 102 (the region on the side of the base 50), and a turbulencer 34b belonging to the region between the two (the middle region).

[0185] The spacing Pa of the multiple turbulence generators 34a belonging to the top 48 side, the spacing Pb of the multiple turbulence generators 34b belonging to the middle region, and the spacing Pb of the multiple turbulence generators 34c belonging to the base 50 side satisfy the relationship Pa < Pb < Pc.

[0186] Thus, the spacing P of the multiple turbulence generators 34 disposed in the cooling passage 59 can vary in stages for each region in the height direction of the blade.

[0187] That is, in a certain cooling passage 59, the cooling passage 59 may be divided into n regions in the direction of blade height, and the spacing P of the turbulence generator 34 may vary in n stages (where n is an integer greater than 2).

[0188] In several embodiments, the ratio (P / ea) between the spacing P between any pair of adjacent turbulents 34 in the blade height direction of the plurality of turbulents 34 disposed in the cooling passage 59 (at least one of the passages 60a to 60f) and the average height ea of ​​the pair of turbulents 34, and the average of the ratio (P / ea) of the plurality of turbulents 34. AVE The condition is satisfied that 0.5 ≤ (P / ea) / (P / ea) AVE Relationships ≤2.0.

[0189] Furthermore, in several embodiments, the above-mentioned (P / ea) and (P / ea) are... AVE It can also satisfy 0.9≤(P / ea) / (P / ea) AVE ≤1.1.

[0190] In the above embodiment, the (P / ea) associated with any pair of turbulents 34 among the plurality of turbulents 34 provided in the cooling passage 59 becomes close to the average (P / ea) associated with the plurality of turbulents 34 (all the turbulents 34) provided in the cooling passage 59. AVE The value of therefore tends to increase the spacing P between adjacent turbulence generators 34 in the blade height direction as the blade approaches the second end 102 from the first end 101, i.e., as the height e of the turbulence generator 34 increases. Therefore, by appropriately setting (P / ea) or (P / ea) AVE This allows for a high heat transfer rate within the blade height direction of the turbulence generator 34 located within the cooling passage 59.

[0191] In several embodiments, the tilt angle θ of any turbulent 34 relative to the flow direction of the cooling fluid in the cooling passage 59 (at least one of channels 60a to 60f) and the average θ of the tilt angles θ of the plurality of turbulent 34 (all the turbulent 34 provided in the cooling passage 59) are considered. AVE Satisfying 0.5≤θ / θ AVE Relationships ≤2.0.

[0192] The improved heat transfer rate brought about by the turbulence generator 34 varies depending on the tilt angle θ of the turbulence generator 34 relative to the flow direction of the cooling fluid in the cooling passage 59. There exists a tilt angle of the turbulence generator 34 from which a high heat transfer rate can be obtained. In this regard, according to the embodiment described above, since the tilt angle θ of the turbulence generator 34 is kept approximately constant in the blade height direction, a high heat transfer rate can be obtained within the range of the blade height direction in which the turbulence generator 34 is installed in the cooling passage 59.

[0193] In several embodiments, the cooling passage 59 described above is one of the multiple channels 60a to 60f constituting the curved flow path 61, excluding the final channel (channel 60f in the moving blade 26, see reference). Figure 7 Channel 60e in leaf 24 (refer to) Figure 9 At least one of the channels 60 other than the final channel. Figure 7 Channel 60f Figure 9 The inner wall surfaces 63 of the back side (negative pressure surface 58) and the ventral side (positive pressure surface 56) of the channel 60e are provided with a plurality of final channel turbulence generators 37 arranged along the blade height direction.

[0194] Furthermore, when the height of the turbulence generator 34 or the final channel turbulence generator 37 is set to e, and the width of the cooling passage 59 or the final channel 66 in the dorsal direction at the position of the blade height of the turbulence generator 34 or the final channel turbulence generator 37 is set to D, the following relationship (II) holds.

[0195] [(e / D) E1 / (e / D) AVE ]<[(e / D) T_E1 / (e / D) T_AVE ]

[0196] ···(II)

[0197] In equation (II) above, (e / D) E1 This pertains to the turbulence generator 34T located on the side closest to the first end 101 in the blade height direction among the multiple turbulence generators 34 (see reference). Figure 7 and Figure 9 The ratio of the height to the width of the passage, (e / D) AVE It is the average of the ratio (e / D) of the height to the width of the passage for the plurality of turbulence generators 34. T_E1 This pertains to the final channel turbulence generator 37T located on the side closest to the first end 101 in the blade height direction among the multiple final channel turbulence generators 37 (see reference). Figure 7 and Figure 9 The ratio of the height to the width of the passage, (e / D) T_AVE It is the average of the ratio (e / D)T of the height to the width of the multiple final channel turbulencers 37.

[0198] As described above, for the turbulence 34 disposed in the cooling passage 59 of the passage 60 other than the final passage 66, as the height e of the turbulence 34 increases from the first end 101 side where the passage width D of the cooling passage 59 is narrower towards the second end 102 side where the passage width D of the cooling passage 59 is wider, the ratio of the height e of the turbulence 34 to the passage width D (e / D) tends to be nearly constant (i.e., the left side of the above relationship is close to 1). Thus, the above relationship means that in the final passage 66, as the passage width D of the final passage 66 decreases in the blade height direction from the second end 102 side towards the first end 101 side, the height e of the final passage turbulence 37 does not decrease by the same amount as the passage width D.

[0199] That is, in the above-described embodiment, in the final channel 66 of the curved flow path 61, the height e of the plurality of final channel turbulencers 37 does not change significantly in the blade height direction compared to other channels 60. In other words, in the final channel 66 near the trailing edge 47, the passage width D of the final channel 66 narrows, making it difficult to select a turbulencer height e corresponding to the passage width D of the aforementioned cooling passage 59. Specifically, there is a situation where the height e of the final turbulencer 37 becomes too small relative to the passage width D of the final channel 66, making the fabrication of the turbulencer difficult. Therefore, there is a need to select a final turbulencer 37 with a height e relatively larger than the appropriate height e of the turbulencer 34 relative to the passage width D, within the range allowing for pressure loss of the cooling fluid flowing in the final channel 66. The height e of the final turbulencer 37 formed in the final channel 66 is smaller than that of the turbulencers 34 in other channels 60 besides the final channel 66, but the ratio of height e to passage width D (e / D) is larger than the ratio of height e to passage width D applied to other channels 60. Furthermore, as mentioned earlier, the ratio of the spacing P to the height e (P / e) of the final turbulence diffuser 37 is selected in a manner that makes it constant in the blade height direction. Since the height e of the final turbulence diffuser 37 is smaller than that of the other channels 60, the number of final turbulence diffusers 37 configured is greater than that of the other channels. Therefore, considering both the ratio of height e to passage width D (e / D) and the ratio of spacing P to height e (P / e), the heat transfer efficiency of the final channel 66 is higher than that of the other channels 60.

[0200] Furthermore, in the final channel 66 where the cooling fluid reaches a higher temperature in the curved flow path 61, the flow path cross-sectional area of ​​the final channel 66 decreases as it moves from the second end 102 toward the first end 101, thereby increasing the flow velocity of the cooling fluid compared to other channels 60. Thus, in the final channel 66, the increased flow velocity of the cooling fluid flowing in the cooling passage 59, the increased ratio of the height e to the passage width D of the final turbulence generator 37 (e / D), and the increased number of final turbulence generators 37 all work together to form a cooling passage 59 with a higher heat transfer rate than other channels 60. Therefore, the turbine blades 40 can be cooled more efficiently by the cooling fluid flowing in the thermally demanding final channel 66.

[0201] In several embodiments, the height e of the final channel turbulence 37 disposed in the final channel 66 is below the height of the turbulence 34 of the upstream cooling passage located adjacent to and communicating with the final channel 66 on the upstream side in the flow direction of the cooling fluid among the plurality of channels 60.

[0202] For example, in Figure 7 In the embodiment of the blade 26 shown, the upstream cooling passage located adjacent to and communicating with the final channel 66 (channel 60f) on the upstream side in the flow direction of the cooling fluid is channel 60e. Furthermore, the height of the final channel turbulence generator 37 provided in the final channel 66 (channel 60f) is below the height of the turbulence generator 34 provided in channel 60e, which serves as the upstream cooling passage.

[0203] Additionally, for example, in Figure 9 In the embodiment of the stationary vane 24 shown, the upstream cooling passage located adjacent to and communicating with the final channel 66 (channel 60e) on the upstream side in the flow direction of the cooling fluid is channel 60d. Furthermore, the height of the final channel turbulence generator 37 provided in the final channel 66 (channel 60e) is below the height of the turbulence generator 34 provided in channel 60d, which serves as the upstream cooling passage.

[0204] Furthermore, when comparing the turbulencer heights e of each channel 60 at positions where the height in the blade height direction is the same from the base end 50 at the second end 102 to the tip 48 of the first end 101, the height e of the final turbulencer 37 of the final channel 66 is selected to be lower than the height e of the turbulencer 34 at a position with the same blade height as the other channels 60 located upstream of the flow direction of the cooling fluid. As a result, it is possible to maintain a high heat transfer rate of the final turbulencer while suppressing the generation of excessive pressure loss of the cooling fluid supplied through the final channel.

[0205] According to the above embodiment, since the height of the turbulence generator (final channel turbulence generator 37) in the final channel 66 located at the far trailing edge in the curved flow path 61 is selected to be below the height of the turbulence generator that forms an upstream cooling passage adjacent to and connected to the final channel 66, more turbulence generators (final channel turbulence generators 37) can be installed in the final channel 66, which has a narrow flow area and where the cooling fluid reaches a relatively high temperature, among the multiple channels 60 constituting the curved flow path 61. Therefore, the turbine blades 40 can be cooled more efficiently by the cooling fluid flowing in the final channel 66.

[0206] In several embodiments, when the height of the turbulence 34 or the leading edge turbulence 35 of the cooling passage 34 or the leading edge passage 36 is set to e, and the width of the cooling passage 59 or the leading edge passage 36 in the dorsal direction at the position of the blade height of the turbulence 34 or the leading edge turbulence 35 is set to D, the following formula (III) holds.

[0207] [(e / D) E2 / (e / D) AVE ]>[(e / D) L_E2 / (e / D) L_AVE ]

[0208] ···(III)

[0209] In equation (III) above, (e / D) E2 This pertains to the turbulence generator 34H located on the side closest to the second end 102 in the blade height direction among the multiple turbulence generators 34 (see reference). Figure 7 The ratio of the height to the width of the passage, (e / D) AVE It is the average of the ratio (e / D) of the height e to the path width D of the multiple turbulence generators 34. L_F2 It refers to the ratio of the height e to the passage width D of the leading-edge side turbulence 35H located on the side closest to the second end 102 in the blade height direction among the plurality of leading-edge side turbulence 35, (e / D). L_AVE It is the average of the ratio (e / D)L of the height e to the passage width D of the multiple leading-edge side turbulence generators 35.

[0210] As described above, regarding the turbulence generator 34 disposed in the cooling passage 59, as the height e of the turbulence generator increases from the first end 101 side where the passage width D of the cooling passage 59 is narrower towards the second end 102 side where the passage width D of the cooling passage 59 is wider, the ratio (e / D) of the height e of the turbulence generator 34 to the passage width D tends to be nearly constant (i.e., the left side of the above relationship is close to 1). Thus, the above relationship means that as the passage width D of the final channel 66 increases in the blade height direction from the first end 101 side towards the second end 102 side, the height e of the leading edge side turbulence generator 35 does not increase by the same amount as the passage width D.

[0211] That is, according to the above embodiment, the height e of the plurality of leading-edge turbulence diffusers 35 in the leading-edge side passage 36 does not change significantly in the blade height direction. Therefore, in the leading-edge side passage 36 supplied with a lower-temperature cooling fluid, the increased heat transfer rate caused by the turbulence diffusers (leading-edge turbulence diffusers 35) located on the second end 102 side upstream of the cooling fluid flow can be suppressed, and the temperature rise of the cooling fluid flowing toward the first end 101 side can be suppressed. As a result, the turbine blade 40 can be cooled more efficiently.

[0212] The embodiments of the present invention have been described above, but the present invention is not limited to the embodiments described above, and also includes modifications to the embodiments described above, and ways in which these methods are appropriately combined.

[0213] In this specification, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" that indicate relative or absolute configuration not only strictly indicate such configuration, but also indicate a state of relative displacement by angle or distance with tolerance or to the extent that the same function can be obtained.

[0214] For example, expressions such as "same," "equal," and "homogeneous" that indicate the state of equality of things not only indicate a state of strict equality, but also indicate a state of difference in the degree to which the same function can be obtained due to tolerances.

[0215] Furthermore, in this specification, the terms "quadrilateral shape," "cylindrical shape," etc., which refer to shapes, not only refer to shapes in a strictly geometric sense, but also to shapes that include concave and convex parts, chamfered parts, etc., within the range where the same effect can be obtained.

[0216] Furthermore, in this specification, expressions such as "possessing," "comprises," or "have" a constituent element are not exclusive expressions that exclude the existence of other constituent elements.

[0217] Explanation of reference numerals in the attached figures:

[0218] 1...gas turbine;

[0219] 2...compressor;

[0220] 4...burner;

[0221] 6... Turbo;

[0222] 8... rotor;

[0223] 10... Compressor room;

[0224] 12... Air inlet;

[0225] 16...Quiet Leaf;

[0226] 18...moving leaves;

[0227] 20...outer shell;

[0228] 22... Turbine room;

[0229] 24...Quiet Leaf;

[0230] 26...moving leaves;

[0231] 28... Combustion gas flow path;

[0232] 29...ribs;

[0233] 30...exhaust chamber;

[0234] 31...ribs;

[0235] 32...ribs;

[0236] 33...Return flow path;

[0237] 34... Turbulence generator;

[0238] 35...leading-edge side turbulence generator;

[0239] 36... Anterior lateral pathway;

[0240] 38...Exit opening;

[0241] 37...Final Channel Turbulence Filter;

[0242] 40... turbine blades;

[0243] 42...blade body;

[0244] 44...front edge;

[0245] 46... trailing edge;

[0246] 46a... trailing edge end face;

[0247] 47...posterior margin;

[0248] 48...top;

[0249] 49...top plate;

[0250] 50...base terminal;

[0251] 52...outer end;

[0252] 54...inner end;

[0253] 56... Pressure surface (ventral side);

[0254] 58... Negative pressure side (back side);

[0255] 59...cooling path;

[0256] Channels 60, 60a-60f...

[0257] 61, 61A, 61B... curved flow paths;

[0258] 63...Inner wall surface;

[0259] 64...Exit opening;

[0260] 66...Final passage;

[0261] 70...cooling holes;

[0262] 80... platform;

[0263] 82... leaf base;

[0264] 84A, 84B...internal flow path;

[0265] 85...Internal flow path;

[0266] 86...Inner protective cover;

[0267] 88...Outer protective cover;

[0268] 101...First end;

[0269] 102...Second end;

[0270] D...path width;

[0271] P.. Turbulence generator spacing;

[0272] e... Turbulence generator height;

[0273] θ... Inclination angle.

Claims

1. A turbine blade, wherein, The turbine blades have: The blade body has a first end and a second end, which are two ends in the blade height direction; Cooling passages extending along the height of the blade within the blade body; and Multiple turbulence generators are disposed on the inner wall surface of the cooling passage and arranged along the cooling passage. The width of the cooling passage in the dorsal-ventral direction of the blade body at the second end is greater than the width of the cooling passage in the dorsal-ventral direction of the blade body at the first end. The height of the plurality of turbulence generators increases from the first end side toward the second end side in the direction of blade height. The cooling passage is one of a plurality of channels forming a tortuous flow path inside the blade body. The cooling passage is the channel that is located at the trailing edge of the plurality of channels constituting the curved flow path, excluding the final channel. The turbine blades have multiple final channel turbulence generators disposed on the inner wall surfaces of the back and front sides of the final channel and arranged along the blade height direction. When the height of the turbulence generator or the final channel turbulence generator is set to e, and the width of the cooling passage or the final channel in the dorsal direction at the position of the blade height of the turbulence generator or the final channel turbulence generator is set to D, Regarding the ratio (e / D) of the height to the passage width of the turbulent located closest to the first end side in the blade height direction among the plurality of turbulents. E1 The average (e / D) of the ratio (e / D) of the height to the width of the passage for the plurality of turbulence generators. AVE Regarding the ratio (e / D) of the height to the passage width of the final channel turbulent located closest to the first end in the blade height direction among the plurality of final channel turbulents. T＿E1 And the ratio (e / D) of the height to the passage width of the plurality of final channel turbulence generators. T The average (e / D) T＿AVE Relationship satisfaction [(e / D) E1 / (e / D) AVE ]<[(e / D) T＿E1 / (e / D) T＿AVE ]。 2. The turbine blade according to claim 1, wherein, The ratio (e / D) of the height e of the plurality of turbulents to the width D of the cooling passage in the dorsal direction at the position of the blade height of the plurality of turbulents in the plurality of turbulents in the dorsal direction, and the average (e / D) of the ratio (e / D) with respect to the plurality of turbulents. AVE The relation satisfies 0.5 ≤ (e / D) / (e / D) AVE ≤2.

0.

3. The turbine blade according to claim 1, wherein, When the width of the cooling passage at the position of the turbulent device located closest to the first end side in the blade height direction among the plurality of turbulent devices is set as D1, and the width of the cooling passage at the position of the turbulent device located closest to the second end side in the blade height direction among the plurality of turbulent devices is set as D2, the ratio of the passage width D2 to the passage width D1 (D2 / D1) satisfies the relationship 1.5≤(D2 / D1).

4. The turbine blade according to claim 1, wherein, The spacing between adjacent pairs of turbulents in the blade height direction increases from the first end toward the second end in the blade height direction.

5. The turbine blade according to claim 1, wherein, The ratio (P / ea) of the spacing P between adjacent pairs of turbulents in the blade height direction to the average height ea of ​​the pair of turbulents, and the average of the ratios (P / ea) of the plurality of turbulents. AVE The relation satisfies 0.5 ≤ (P / ea) / (P / ea) AVE ≤2.

0.

6. The turbine blade according to claim 1, wherein, The height of the final channel turbulent in the blade height direction relative to the second end is below the height of the turbulent at the same position in the blade height direction of the other channels located upstream of the flow direction of the cooling fluid.

7. The turbine blade according to claim 1, wherein, The height of the final channel turbulence generator is below the height of the turbulence generator in the upstream cooling passage of the plurality of channels, which is located adjacent to and interconnected with the final channel on the upstream side in the flow direction of the cooling fluid.

8. The turbine blade according to any one of claims 1 to 7, wherein, The cross-sectional area of ​​the cooling passage increases from the first end toward the second end in the direction of blade height.

9. The turbine blade according to any one of claims 1 to 7, wherein, The tilt angle θ of the plurality of turbulence generators relative to the flow direction of the cooling fluid in the cooling path and the average θ of the tilt angles of the plurality of turbulence generators. AVE The relationship satisfies 0.5 ≤ θ / θ AVE ≤2.

0.

10. The turbine blade according to claim 1, wherein, The turbine blades are moving blades. The first end is located radially outside the second end.

11. The turbine blade according to claim 1, wherein, The turbine blades are stationary blades. The first end is located radially inside the second end.

12. A turbine blade, wherein, The turbine blades have: The blade body has a first end and a second end, which are two ends in the blade height direction; Cooling passages extending along the height of the blade within the blade body; and Multiple turbulence generators are disposed on the inner wall surface of the cooling passage and arranged along the cooling passage. The width of the cooling passage in the dorsal-ventral direction of the blade body at the second end is greater than the width of the cooling passage in the dorsal-ventral direction of the blade body at the first end. The height of the plurality of turbulence generators increases from the first end side toward the second end side in the direction of blade height. The turbine blades also possess: A leading-edge side passage is provided inside the blade body at a position closer to the leading edge of the blade body than the cooling passage, and extends along the blade height direction; as well as Multiple leading-edge turbulence generators are disposed on the inner wall of the leading-edge passage and arranged along the blade height direction. When the height of the turbulence generator or the leading-edge side turbulence generator is set to e, and the width of the cooling passage or the leading-edge side passage in the dorsal-ventral direction at the position of the blade height of the turbulence generator or the leading-edge side turbulence generator is set to D, Regarding the ratio (e / D) of the height to the passage width of the turbulent located closest to the second end side in the blade height direction among the plurality of turbulents. E2 The average (e / D) of the ratio (e / D) of the height to the width of the passage for the plurality of turbulence generators. AVE Regarding the ratio (e / D) of the height to the passage width of the leading-edge turbulence generator located closest to the second end side in the blade height direction among the plurality of leading-edge turbulence generators. L＿E2 And the ratio (e / D) of the height to the passage width of the plurality of leading-edge turbulence generators. L The average (e / D) L＿AVE Relationship satisfaction [(e / D) E2 / (e / D) AVE ]>[(e / D) L＿E2 / (e / D) L＿AVE ]。 13. The turbine blade according to claim 12, wherein, The cross-sectional area of ​​the cooling passage increases from the first end toward the second end in the direction of blade height.

14. The turbine blade according to claim 12, wherein, The tilt angle θ of the plurality of turbulence generators relative to the flow direction of the cooling fluid in the cooling path and the average θ of the tilt angles of the plurality of turbulence generators. AVE The relationship satisfies 0.5 ≤ θ / θ AVE ≤2.

0.

15. The turbine blade according to claim 12, wherein, The turbine blades are moving blades. The first end is located radially outside the second end.

16. The turbine blade according to claim 12, wherein, The turbine blades are stationary blades. The first end is located radially inside the second end.

17. A gas turbine, wherein, The gas turbine includes: The turbine blade according to any one of claims 1 to 16; and A burner for generating combustion gases that flow in a combustion gas path in which the turbine blades are disposed.

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