Turbine blade and gas turbine
阅读说明:本技术 涡轮叶片及燃气轮机 (Turbine blade and gas turbine ) 是由 若园进 高村启太 羽田哲 于 2019-04-12 设计创作,主要内容包括:本发明涉及一种涡轮叶片及燃气轮机。涡轮叶片具备:叶片主体;冷却通路,其在所述叶片主体的内部沿着叶片高度方向延伸;以及多个湍流器,它们设置于所述冷却通路的内壁面,且沿着所述冷却通路排列,所述叶片主体具有作为所述叶片高度方向上的两端部的第一端部和第二端部,所述第二端部的所述叶片主体的背腹方向上的所述冷却通路的通路宽度大于所述第一端部的所述冷却通路的所述通路宽度,所述多个湍流器的高度在所述叶片高度方向上随着从所述第一端部侧朝向所述第二端部侧而变高。(The present invention relates to a turbine blade and a gas turbine. The turbine blade is provided with: a blade main body; a cooling passage extending in a blade height direction inside the blade body; and a plurality of turbulators provided on an inner wall surface of the cooling passage and arranged along the cooling passage, the blade body having a first end portion and a second end portion that are both end portions in the blade height direction, a passage width of the cooling passage in a back-and-forth direction of the blade body of the second end portion being larger than the passage width of the cooling passage of the first end portion, a height of the plurality of turbulators increasing from the first end portion side toward the second end portion side in the blade height direction.)
1. A turbine blade wherein, in the turbine blade,
the turbine blade is provided with:
a blade body having a first end and a second end as both ends in a blade height direction;
a cooling passage extending in the blade height direction inside the blade body; and
a plurality of turbulators provided on an inner wall surface of the cooling passage and arranged along the cooling passage,
A passage width of the cooling passage in a dorsal-ventral direction of the blade body at the second end portion is larger than the passage width of the cooling passage at the first end portion,
the heights of the plurality of turbulators become higher from the first end side toward the second end side in the blade height direction.
2. The turbine blade of claim 1,
a ratio of a height of the plurality of turbulators (e) to a passage width of the cooling passage in the ventral direction (D) at the blade height direction position of the plurality of turbulators (e/D), and an average of the ratios with respect to the plurality of turbulators (e/D)AVESatisfies the relationship (e/D)/(e/D) of 0.5. ltoreqAVE≤2.0。
3. The turbine blade of claim 1 or 2,
a ratio (D2/D1) of the passage width D1 to the passage width D2 satisfies a relationship of 1.5 ≦ (D2/D1) with the passage width of the cooling passage at a position of a turbulator of the plurality of turbulators located most toward the first end side in the blade height direction being set to D1, and the passage width of the cooling passage at a position of a turbulator of the plurality of turbulators located most toward the second end side in the blade height direction being set to D2.
4. The turbine blade of any one of claims 1-3,
the pitch in the blade height direction of a pair of turbulators adjacent in the blade height direction increases from the first end toward the second end in the blade height direction.
5. The turbine blade of any one of claims 1-4,
a ratio of a pitch P between a pair of turbulators of the plurality of turbulators adjacent in the blade height direction to an average ea of heights of the pair of turbulators (P/ea), and an average of the ratios with respect to the plurality of turbulators (P/ea)AVESatisfies the relation of (P/ea)/(P/ea) of 0.5. ltoreq.AVE≤2.0。
6. The turbine blade of any one of claims 1-5,
the cooling passage is one of a plurality of passages constituting a curved flow path formed inside the blade body.
7. The turbine blade of claim 6,
the cooling passage is a passage other than a final passage located at the most trailing edge side among the plurality of passages constituting the curved flow path,
the turbine blade includes a plurality of final passage turbulators that are provided on inner wall surfaces of a back side and a ventral side of the final passage and are arranged in a blade height direction,
When the height of the turbulator or the final channel turbulator is set to e, and the channel width in the dorsal direction of the cooling channel or the final channel at the position of the blade-height direction of the turbulator or the final channel is set to D,
with respect to a turbulator of the plurality of turbulators located at the most first end side in the blade height directionRatio (e/D) of the height to the width of the viaE1Average (e/D) with respect to a ratio (e/D) of the height to the channel width of the plurality of turbulatorsAVEWith respect to a ratio (e/D) of the height to the passage width of a final channel turbulator of the plurality of final channel turbulators located most to the first end side in the blade height directionT_E1And an average (e/D) with respect to a ratio (e/D) T of the height to the channel width of the plurality of final channel turbulatorsT_AVESatisfy the relationship of
[(e/D)E1/(e/D)AVE]<[(e/D)T_E1/(e/D)T_AVE]。
8. The turbine blade of any one of claims 1-7,
the cooling passage is a passage other than a final passage located at the most trailing edge side among the plurality of passages constituting the curved flow path formed inside the blade body,
The turbine blade includes a plurality of final passage turbulators that are provided on inner wall surfaces of a back side and a ventral side of the final passage and are arranged in a blade height direction,
the height of the final channel turbulator in the blade height direction of the final channel with respect to the second end portion is equal to or less than the height of a turbulator at the same position in the blade height direction of another channel located on the upstream side in the flow direction of the cooling fluid.
9. The turbine blade of any one of claims 1-8,
the cooling passage is a passage other than a final passage located at the most trailing edge side among the plurality of passages constituting the curved flow path formed inside the blade body,
the turbine blade includes a plurality of final passage turbulators that are provided on inner wall surfaces of a back side and a ventral side of the final passage and are arranged in a blade height direction,
a height of the final channel turbulator of the final channel is below a height of the turbulator of an upstream side cooling passage of the plurality of channels that is located adjacent to the final channel on an upstream side in a flow direction of the cooling fluid and that is in communication with the final channel.
10. The turbine blade of any one of claims 1-9,
the turbine blade is further provided with:
a leading edge side passage provided inside the blade body on a leading edge side of the blade body with respect to the cooling passage and extending in the blade height direction; and
a plurality of leading edge side turbulators provided on an inner wall surface of the leading edge side passage and arranged in the blade height direction,
when the height of the turbulator or the leading edge side turbulator is set to e, and the passage width in the flank direction of the cooling passage or the leading edge side passage at the position in the blade height direction of the turbulator or leading edge side turbulator is set to D,
a ratio (e/D) of the height to the passage width with respect to turbulators of the plurality of turbulators located most to the second end side in the blade height directionE2Average (e/D) with respect to a ratio e/D of the height to the channel width of the plurality of turbulatorsAVEWith respect to a ratio (e/D) of the height of a leading edge-side turbulator of the plurality of leading edge-side turbulators located closest to the second end side in the blade height direction to the passage width L_E2And a ratio (e/D) of the height to the channel width for the plurality of leading edge side turbulatorsLAverage (e/D)L_AVESatisfy the relationship of
[(e/D)E2/(e/D)AVE]>[(e/D)L_E2/(e/D)L_AVE]。
11. The turbine blade of any one of claims 1-10,
the cooling passage has a flow path cross-sectional area that increases from the first end portion toward the second end portion in the blade height direction.
12. The turbine blade of any one of claims 1-11,
an inclination angle θ of the plurality of turbulators relative to a flow direction of a cooling fluid in the cooling passage and an average θ with respect to the inclination angle of the plurality of turbulatorsAVESatisfies the relationship of 0.5 ≦ theta/thetaAVE≤2.0。
13. The turbine blade of any one of claims 1-12,
the turbine blades are moving blades of a turbine,
the first end is located radially outward of the second end.
14. The turbine blade of any one of claims 1-12,
the turbine blades are stationary blades and are,
the first end is located radially inward of the second end.
15. A gas turbine, wherein,
the gas turbine is provided with:
the turbine blade of any one of claims 1 to 14; and
A combustor for generating combustion gas flowing in a combustion gas flow path in which the turbine blade is provided.
Technical Field
The present invention relates to a turbine blade and a gas turbine.
Background
In a turbine blade of a gas turbine or the like, it is known that a turbine blade exposed to a high-temperature gas flow or the like is cooled by flowing a cooling fluid through a cooling passage formed inside the turbine blade. On the inner wall surface of such a cooling passage, a rib-shaped turbulator may be provided in order to promote turbulence of the flow of the cooling fluid in the cooling passage and to improve the heat transfer rate between the cooling fluid and the turbine blade.
For example, patent document 1 discloses a turbine blade in which a plurality of turbulators are provided along the flow direction of a cooling fluid on the inner wall surface of a cooling passage extending in the blade height direction.
Prior art documents
Patent document
Patent document 1: japanese laid-open patent publication No. 2004-225690
Disclosure of Invention
Problems to be solved by the invention
However, in recent years, for example, in a gas turbine, the load acting on the turbine blade tends to increase with an increase in output. In order to provide the turbine blade with strength capable of withstanding such a load that tends to increase, the blade width of the turbine blade in the flank-flank direction may be made larger on one side than on the other side in the radial direction of the turbine (i.e., the blade height direction of the turbine blade).
In this way, when the blade width in the back-and-forth direction of the turbine blade is increased in one side in the radial direction, the width (or the flow path cross-sectional area) of the cooling passage formed inside the turbine blade may be increased in the one side in the radial direction.
A blade structure having a cooling passage in which appropriate turbulators are selected in accordance with changes in the blade width of a turbine blade to optimize the internal cooling of the cooling passage is desired.
In view of the above, an object of at least one embodiment of the present invention is to provide a turbine blade and a gas turbine that can achieve efficient cooling.
Means for solving the problems
(1) A turbine blade according to at least one embodiment of the present invention includes:
a blade body having a first end and a second end as both ends in a blade height direction;
a cooling passage extending in the blade height direction inside the blade body; and
a plurality of turbulators provided on an inner wall surface of the cooling passage and arranged along the cooling passage,
a passage width of the cooling passage in a dorsal-ventral direction of the blade body at the second end portion is larger than the passage width of the cooling passage at the first end portion,
the heights of the plurality of turbulators become higher from the first end side toward the second end side in the blade height direction.
In the configuration of the above (1), since the height of the turbulator increases as the cooling passage approaches from the first end side where the passage width of the cooling passage is small to the second end side where the passage width of the cooling passage is large in the blade height direction, the effect of improving the heat transfer rate by the turbulator can be obtained on the second end side to the same extent as on the first end side. In the configuration of the above (1), since the height of the turbulator is low on the first end side in the blade height direction, the pressure loss due to the presence of the turbulator can be suppressed on the first end side where the passage width of the cooling passage is narrow and the pressure loss tends to increase. Therefore, according to the configuration of the above (1), the turbine blade having the passage width of the cooling passage varying in the blade height direction can be efficiently cooled.
(2) In some embodiments, in addition to the structure of the above (1),
a ratio of a height of the plurality of turbulators (e) to a passage width of the cooling passage in the ventral direction (D) at the blade height direction position of the plurality of turbulators (e/D), and an average of the ratios with respect to the plurality of turbulators (e/D)AVESatisfies the relationship (e/D)/(e/D) of 0.5. ltoreqAVE≤2.0。
According to the configuration of the above item (2), the ratio (e/D) of the height e of a turbulator associated with a turbulator of a plurality of turbulators provided in a cooling passage to the passage width D is close to the average (e/D) of the plurality of turbulators provided in the cooling passageAVEThus, it is possible to suppress an extreme change in the decrease in the heat transfer rate in the blade height direction or the increase in the pressure loss of the cooling fluid. Therefore, the turbine blade can be efficiently cooled.
(3) In some embodiments, in addition to the structure of the above (1) or (2),
a ratio (D2/D1) of the passage width D1 to the passage width D2 satisfies a relationship of 1.5 ≦ (D2/D1) with the passage width of the cooling passage at a position of a turbulator of the plurality of turbulators located most toward the first end side in the blade height direction being set to D1, and the passage width of the cooling passage at a position of a turbulator of the plurality of turbulators located most toward the second end side in the blade height direction being set to D2.
According to the configuration of the above (3), in the turbine blade in which the passage width D2 of the cooling passage on the second end side is significantly larger than the passage width D1 of the cooling passage on the first end side, the height of the turbulator is increased at the position in the blade height direction on the second end side where the passage width of the cooling passage is large, and therefore, as described in the above (1), the turbine blade can be efficiently cooled.
(4) In several embodiments, in addition to any one of the structures (1) to (3) above,
the pitch in the blade height direction of a pair of turbulators adjacent in the blade height direction increases from the first end toward the second end in the blade height direction.
The effect of the heat transfer rate enhancement by the turbulators varies depending on the spacing between adjacent turbulators in the blade height direction, and there is a ratio of the spacing to the height of the turbulators that can achieve a high heat transfer rate. In this regard, according to the configuration of the above (4), as the turbulators are closer to the second end portion from the first end portion in the blade height direction, that is, as the height of the turbulators becomes higher, the pitch between adjacent turbulators in the blade height direction increases, so that a high heat transfer rate can be obtained in the blade height direction range in which the turbulators are provided in the cooling passage.
(5) In several embodiments, in addition to any one of the structures (1) to (4) above,
a ratio of a pitch P between a pair of turbulators of the plurality of turbulators adjacent in the blade height direction to an average ea of heights of the pair of turbulators (P/ea), and an average of the ratios with respect to the plurality of turbulators (P/ea)AVESatisfies the relation of (P/ea)/(P/ea) of 0.5. ltoreq.AVE≤2.0。
According to the configuration of the above item (5), the (P/ea) associated with a pair of turbulators among the plurality of turbulators provided in the cooling passage approaches the average (P/ea) which is the (P/ea) associated with the plurality of turbulators provided in the cooling passageAVETherefore, the pitch between adjacent turbulators tends to increase as the turbulators approach the second end from the first end in the blade height direction, that is, as the height of the turbulators increases. Therefore, by appropriately setting (P/ea) or (P/ea)AVEThe high heat transfer rate can be obtained in the range of the height direction of the blade in which the turbulator is provided in the cooling passage.
(6) In several embodiments, in addition to any one of the structures (1) to (5) above,
the cooling passage is one of a plurality of passages constituting a curved flow path formed inside the blade body.
In the turbine blade having the structure of the above (6) in which the curved flow path is provided as the internal flow path through which the cooling fluid flows, the passage constituting the curved flow path is the cooling passage having the structure of the above (1). Therefore, the effect of improving the heat transfer rate by the turbulators can be obtained on the second end side of the passage (cooling passage) as much as the first end side, and the pressure loss due to the presence of the turbulators can be suppressed on the first end side where the passage width of the passage (cooling passage) is narrow and the pressure loss tends to increase. Therefore, according to the configuration of the above (6), it is possible to efficiently cool the turbine blade in which the passage width of the passage (cooling passage) of the curved flow passage changes in the blade height direction.
(7) In some embodiments, in addition to the structure of (6) above,
the cooling passage is a passage other than a final passage located at the most trailing edge side among the plurality of passages constituting the curved flow path,
the turbine blade includes a plurality of final passage turbulators that are provided on inner wall surfaces of a back side and a ventral side of the final passage and are arranged in a blade height direction,
When the height of the turbulator or the final channel turbulator is set to e, and the channel width in the dorsal direction of the cooling channel or the final channel at the position of the blade-height direction of the turbulator or the final channel is set to D,
a ratio (e/D) of the height to the passage width with respect to a turbulator of the plurality of turbulators located closest to the first end side in the blade height directionE1Average (e/D) with respect to a ratio (e/D) of the height to the channel width of the plurality of turbulatorsAVEWith respect to a ratio (e/D) of the height to the passage width of a final channel turbulator of the plurality of final channel turbulators located most to the first end side in the blade height directionT_E1And a ratio (e/D) of the height to the channel width for the plurality of final channel turbulatorsTAverage (e/D)T_AVESatisfy the relationship of
[(e/D)E1/(e/D)AVE]<[(e/D)T_E1/(e/D)T_AVE]。
As described in the above (1), in the turbulator provided in the channel (cooling passage) other than the final channel, the height of the turbulator increases from the first end portion side where the passage width of the cooling passage is narrow toward the second end portion side where the passage width of the cooling passage is wide, and therefore, the ratio (e/D) of the height e of the turbulator to the passage width D tends to be nearly constant (that is, the left side of the above-described relational expression is nearly 1). Thus, the above-described relational expression means that the passage width D of the final channel decreases from the second end portion side toward the first end portion side in the blade height direction in the final channel, and the height e of the final channel turbulator does not decrease by the amount of the passage width D described above.
That is, according to the structure of the above (7), in the final passage of the curved flow path, the heights e of the plurality of final passage turbulators do not greatly change in the blade height direction. Therefore, in the final passage in which the cooling fluid becomes a relatively high temperature in the curved flow path, the flow velocity of the cooling fluid on the first end portion side, which is normally located on the downstream side of the flow of the cooling fluid, can be increased. Thereby, the turbine blade can be cooled more efficiently by the cooling fluid flowing through the final passage.
(8) In several embodiments, in addition to the structures of (1) to (7) above,
the cooling passage is a passage other than a final passage located at the most trailing edge side among the plurality of passages constituting the curved flow path formed inside the blade body,
the turbine blade includes a plurality of final passage turbulators that are provided on inner wall surfaces of a back side and a ventral side of the final passage and are arranged in a blade height direction,
the height of the final channel turbulator in the blade height direction of the final channel with respect to the second end portion is equal to or less than the height of a turbulator at the same position in the blade height direction of another channel located on the upstream side in the flow direction of the cooling fluid.
According to the configuration of the above (8), in the case where the heights of the turbulators at the same positions in the blade height direction are compared between the final turbulator and the turbulators of the other passages, the height of the final turbulator is equal to or less than the height of the turbulators of the other passages, and therefore, it is possible to suppress the generation of excessive pressure loss to the cooling fluid flowing through the final passage while maintaining a high heat transfer rate of the final turbulator.
(9) In several embodiments, in addition to any one of the structures (1) to (8) above,
the cooling passage is a passage other than a final passage located at the most trailing edge side among the plurality of passages constituting the curved flow path formed inside the blade body,
the turbine blade includes a plurality of final passage turbulators that are provided on inner wall surfaces of a back side and a ventral side of the final passage and are arranged in a blade height direction,
a height of the final channel turbulator of the final channel is below a height of the turbulator of an upstream side cooling passage of the plurality of channels that is located adjacent to the final channel on an upstream side in a flow direction of the cooling fluid and that is in communication with the final channel.
According to the configuration of the above (9), since the height of the turbulator (final passage turbulator) of the final passage located closest to the trailing edge side in the curved passage is equal to or less than the height of the turbulator of the upstream side cooling passage communicating adjacent to the final passage, it is possible to provide more turbulators in the final passage in which the flow passage area is narrow and the cooling fluid has a high temperature, among the plurality of passages constituting the curved flow passage. Thereby, the turbine blade can be cooled more efficiently by the cooling fluid flowing through the final passage.
(10) In several embodiments, in addition to any one of the structures (1) to (9) above,
the turbine blade is further provided with:
a leading edge side passage provided inside the blade body on a leading edge side of the blade body with respect to the cooling passage and extending in the blade height direction; and
a plurality of leading edge side turbulators provided on an inner wall surface of the leading edge side passage and arranged in the blade height direction,
when the height of the turbulator or the leading edge side turbulator is set to e, and the passage width in the flank direction of the cooling passage or the leading edge side passage at the position in the blade height direction of the turbulator or leading edge side turbulator is set to D,
A ratio (e/D) of the height to the passage width with respect to turbulators of the plurality of turbulators located most to the second end side in the blade height directionE2Average (e/D) with respect to a ratio e/D of the height to the channel width of the plurality of turbulatorsAVEWith respect to a ratio (e/D) of the height of a leading edge-side turbulator of the plurality of leading edge-side turbulators located closest to the second end side in the blade height direction to the passage widthL_E2And a ratio (e/D) of the height to the channel width for the plurality of leading edge side turbulatorsLAverage (e/D)L_AVESatisfy the relationship of
[(e/D)E2/(e/D)AVE]>[(e/D)L_E2/(e/D)L_AVE]。
As described in the above (1), since the height of the turbulator provided in the cooling passage increases from the first end portion side where the passage width of the cooling passage is narrow toward the second end portion side where the passage width of the cooling passage is wide, the ratio (e/D) of the height e of the turbulator to the passage width D tends to be nearly constant (that is, the left side of the above-described relation is nearly 1). Thus, the above-described relational expression means that the passage width D of the final passage increases from the first end portion side toward the second end portion side in the blade height direction, whereas the height e of the leading edge-side turbulator does not increase by the amount of the passage width D described above.
That is, according to the configuration of the above (10), in the leading edge side passage, the heights e of the plurality of leading edge side turbulators do not change greatly in the blade height direction. Therefore, in the leading edge side passage to which the cooling fluid of a relatively low temperature is supplied, the effect of improving the heat transfer rate by the turbulator located on the second end portion side on the upstream side of the flow of the cooling fluid is suppressed, and the temperature rise of the cooling fluid flowing toward the first end portion side can be suppressed. This enables the turbine blade to be cooled more efficiently.
(11) In several embodiments, in addition to any one of the structures (1) to (10) above,
the cooling passage has a flow path cross-sectional area that increases from the first end portion toward the second end portion in the blade height direction.
According to the configuration of the above (11), since the height of the turbulator is increased as approaching from the first end portion of the cooling passage having a small flow passage cross-sectional area to the second end portion of the cooling passage having a large flow passage cross-sectional area in the blade height direction, the effect of improving the heat transfer rate by the turbulator can be obtained on the second end portion side to the same extent as on the first end portion side. In the configuration of the above (11), since the height of the turbulator is low on the first end side in the blade height direction, the pressure loss due to the presence of the turbulator can be suppressed on the first end side where the flow path cross-sectional area is narrow and the pressure loss tends to be large. Therefore, according to the configuration of the above (11), the turbine blade having the flow path cross-sectional area of the cooling passage varying in the blade height direction can be efficiently cooled.
(12) In several embodiments, in addition to any one of the structures (1) to (11) described above,
an inclination angle θ of the plurality of turbulators relative to a flow direction of a cooling fluid in the cooling passage and an average θ with respect to the inclination angle of the plurality of turbulatorsAVESatisfies the relationship of 0.5 ≦ theta/thetaAVE≤2.0。
The effect of improving the heat transfer rate by the turbulators varies depending on the inclination angle θ of the turbulators with respect to the flow direction of the cooling fluid in the cooling passage, and there are inclination angles of the turbulators that can obtain a high heat transfer rate. In this regard, according to the configuration of the above (12), since the inclination angle θ of the turbulator is made substantially 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 turbulator is provided in the cooling passage.
(13) In several embodiments, in addition to any one of the structures (1) to (12) described above,
the turbine blades are moving blades of a turbine,
the first end is located radially outward of the second end.
According to the configuration of the above (13), since the rotor blade of the gas turbine, which is the turbine blade, has any one of the configurations of the above (1) to (12), the rotor blade can be efficiently cooled, and therefore the thermal efficiency of the gas turbine can be improved.
(14) In several embodiments, in addition to any one of the structures (1) to (12) described above,
the turbine blades are stationary blades and are,
the first end is located radially inward of the second end.
According to the structure of the above (14), since the stator blade of the gas turbine, which is the turbine blade, has any one of the structures of the above (1) to (12), the stator blade can be efficiently cooled, and therefore the thermal efficiency of the gas turbine can be improved.
(15) A gas turbine according to at least one embodiment of the present invention includes:
the turbine blade of any one of (1) to (14) above; and
a combustor for generating combustion gas flowing in a combustion gas flow path in which the turbine blade is provided.
According to the configuration of the above (15), since the turbine blade has any one of the configurations of the above (1) to (14), the amount of the cooling fluid supplied to the serpentine channel for cooling the turbine blade can be reduced, and the thermal efficiency of the gas turbine can be improved.
Effects of the invention
According to at least one embodiment of the present invention, optimization of the cooling passage of the turbine blade is achieved, the amount of cooling fluid is reduced, and the thermal efficiency of the turbine is improved.
Drawings
Fig. 1 is a schematic configuration diagram of a gas turbine to which a turbine blade according to an embodiment is applied.
Fig. 2 is a partial sectional view of a bucket (turbine blade) according to an embodiment in the blade height direction.
Fig. 3 is a view showing a section B-B of fig. 2.
FIG. 4A is a cross-sectional view of the bucket in section A-A of FIG. 2.
FIG. 4B is a cross-sectional view of the bucket in section B-B of FIG. 2.
FIG. 4C is a cross-sectional view of the bucket in section C-C of FIG. 2.
Fig. 5 is a schematic view for explaining the structure of a turbulator of an embodiment.
Fig. 6 is a schematic view for explaining the structure of a turbulator of an embodiment.
Fig. 7 is a schematic cross-sectional view of the rotor blade (turbine blade) shown in fig. 2 to 4C.
Fig. 8 is a schematic view showing a D-D section of fig. 7.
FIG. 9 is a schematic cross-sectional view of a vane (turbine blade) of an embodiment.
Detailed Description
Hereinafter, several embodiments of the present invention will be described with reference to the drawings. The dimensions, materials, shapes, relative arrangements, and the like of the constituent members described as the embodiments or shown in the drawings are not intended to limit the scope of the present invention, and are merely illustrative examples.
First, a gas turbine to which the turbine blade according to some embodiments is applied will be described.
Fig. 1 is a schematic configuration diagram of a gas turbine to which a turbine blade according to an embodiment is applied. As shown in fig. 1, a gas turbine 1 includes a compressor 2 for generating compressed air, a combustor 4 for generating combustion gas using the compressed air and fuel, and a turbine 6 configured to be driven and rotated by the combustion gas. In the case of the gas turbine 1 for power generation, a generator, not shown, is connected to the turbine 6.
The compressor 2 includes a plurality of stator vanes 16 fixed to the compressor casing 10 side and a plurality of rotor blades 18 implanted in the rotor 8 so as to be alternately arranged with respect to the stator vanes 16.
The air introduced from the air inlet 12 is sent to the compressor 2, and the air is compressed by the plurality of stationary vanes 16 and the plurality of movable blades 18 to become high-temperature and high-pressure compressed air.
The combustor 4 is supplied with fuel and compressed air generated by the compressor 2, and the fuel and the compressed air are mixed and combusted in the combustor 4 to generate combustion gas as a working fluid of the turbine 6. As shown in fig. 1, a plurality of combustors 4 may be arranged in the circumferential direction around the rotor in the casing 20.
The turbine 6 has a combustion gas flow path 28 formed in the turbine casing 22, and includes a plurality of vanes 24 and
The stator blades 24 are fixed to the turbine casing 22 side, and a plurality of stator blades 24 arranged in the circumferential direction of the rotor 8 constitute a stator blade cascade. The
In the turbine 6, the combustion gas from the combustor 4 flowing into the combustion gas flow path 28 drives the rotor 8 to rotate by the plurality of vanes 24 and the plurality of
In some embodiments, at least one of the
Hereinafter, description will be given mainly with reference to the drawings of the
Fig. 2 is a partial cross-sectional view of the bucket 26 (turbine blade 40) according to an embodiment taken along the blade height direction, and fig. 3 is a view showing a cross-section B-B of fig. 2. The arrows in the drawing indicate the direction of the flow of the cooling fluid. Fig. 4A to 4C are sectional views of the
As shown in fig. 2 and 3, the
The
The
A cooling flow path through which a cooling fluid (for example, air) for cooling the
By supplying the cooling fluid to the cooling passages such as the curved passages 61A and 61B and the leading
The two curved flow paths include a curved flow path 61A on the leading
The curved flow path 61A on the leading edge side and the leading
The two curved flow paths 61A and 61B each have a plurality of passages 60 (
The
Further, the
In the exemplary embodiment shown in fig. 2 and 3, the curved flow path 61A on the leading edge side includes three
The plurality of
In the
The shape of the curved flow paths 61A and 61B is not limited to the shape shown in fig. 2 and 3. For example, the number of curved flow paths formed inside the
The leading
In several embodiments, as shown in fig. 2, a plurality of cooling holes 70 are formed in the trailing edge portion 47 (including the portion of the trailing edge 46) of the
A part of the cooling fluid flowing through the cooling flow path passes through the cooling hole 70 described above, which communicates with the cooling flow path, and flows out from the opening of the trailing
The
As shown in fig. 4A to 4C, the blade width in the dorsal-ventral (dorsal 58-ventral 56) direction of the blade
As shown in fig. 4A to 4C, in the
Here, the passage width D (DL, Da, Db., etc.; hereinafter also collectively referred to as "D") of the cooling flow passage in the ventral direction of the
The passage width D of the cooling passage may be represented by an equivalent diameter ED shown in the following formula (I) in consideration of the fact that the passage has a deformed passage shape such as a rhombic cross section, a trapezoidal cross section, or a triangular cross section, instead of a rectangular cross section. The equivalent diameter ED corresponds to the above-described via width D.
ED=4A/L···(I)
In the above formula (I), ED represents an equivalent diameter, a represents a passage cross-sectional area, and L represents a wet circumferential length of a passage cross-section (a length of the entire circumference of one passage cross-section). Therefore, in the following description, the passage width D may also be understood as the equivalent diameter ED.
For example, when attention is paid to the channel 60B that is the third channel counted from the leading
The passage width D may gradually increase from the
Further, the flow path cross-sectional area of each of the
Rib-
In some embodiments, as shown in fig. 2 to 4C, a plurality of turbulators 35 (leading edge turbulators 35) are also provided along the blade height direction on the inner wall surface of the leading
Here, fig. 5 and 6 are schematic views for explaining the structure of the
As shown in fig. 5, each turbulator 34 is provided on an
When the
That is, as the thermal load applied to the turbine blade increases with an increase in the output of the gas turbine, there is a case where it is desired to increase the blade width in the back-and-forth direction of the
The effect of the improvement of the heat transfer rate by the
For example, according to the inclination angle θ of the
Similarly to the case of the
Hereinafter, the features of the
Here, fig. 7 is a schematic cross-sectional view of the blade 26 (turbine blade 40) shown in fig. 2 to 4C, and fig. 8 is a schematic view showing a D-D cross-section of fig. 7. Fig. 9 is a schematic cross-sectional view of a vane 24 (turbine blade 40) according to an embodiment. The arrows in the figure indicate the direction of flow of the cooling fluid LF.
As shown in fig. 9, the vane 24 (turbine blade 40) according to one embodiment includes a
The blade
A
In the vane 24 (turbine blade 40) shown in fig. 9, the cooling fluid is introduced into the
In the stator blade 24, the
In the vane 24, a plurality of cooling holes 70 may be formed in the trailing
The
The blade width of the
Further, although not particularly shown, the passage width D of the
The passage width D may gradually increase from the
Further, the flow path cross-sectional area of each of the
Next, more specific features of the
In the turbine blade 40 (the
It is also possible that the height of the plurality of
Alternatively, the heights of the plurality of
As described above, an example of a case where the heights of the plurality of
The exemplary cooling passage 59 shown in FIG. 8 is divided into three regions in the blade height direction. The plurality of
The representative passage width Da in the back-and-forth direction of the cooling passage 59 at the position of the turbulator 34a belonging to the region on the tip end 48 side, the representative passage width Db in the back-and-forth direction of the cooling passage 59 at the position of the turbulator 34b belonging to the intermediate region, and the representative passage width DDc in the back-and-forth direction of the cooling passage 59 at the position of the turbulator 34c belonging to the region on the base end 50 side satisfy the relationship Da < Db < Dc.
The representative passage width D in the ventral direction of the cooling passage 59 in each region may be an average value of the passage widths D of the cooling passages 59 at the positions in the blade height direction of the
The plurality of turbulators 34a, 34b, and 34c belonging to each blade height direction region have the same height, and the height ea of the turbulator 34a belonging to the region on the tip end 48 side, the height eb of the turbulator 34b belonging to the intermediate region, and the height ec of the turbulator 34c belonging to the region on the base end 50 side satisfy the relationship of ea < eb < ec.
As described above, the heights e of the plurality of
In the turbine blade 40 (the blade 26) shown in fig. 7 and the turbine blade 40 (the vane 24) shown in fig. 9, the plurality of
In the example shown in fig. 8, the cooling passage 59 is divided into three regions in the blade height direction, and the height of the
The
By providing the
In this regard, in the above-described embodiment, the height e of the
On the other hand, it is not desirable to make the turbulator height e on the
Therefore, according to the above-described embodiment, the
In several embodiments, the ratio (e/D) of the height e of any one
In addition, in some embodiments, (e/D) and (e/D) are as described aboveAVECan also satisfy the requirement of (e/D)/(e/D) of more than or equal to 0.9AVE≤1.1。
Alternatively, in several embodiments, (e/D) and (e/D) are as described aboveAVECan also meet the requirements of (D1/D2) less than or equal to (e/D)/(e/D)AVEIs less than or equal to (D2/D1). Here, D1 is the passage width of the cooling passage 59 at the position of the
The relationship of the relational expression may be established for each (all) of the plurality of
In the above-described embodiment, it is set that (e @) is associated with any
In some embodiments, when a passage width D of the cooling passage 59 at a position of the
Alternatively, the passage width D1 and the passage width D2 may also satisfy the relationship of 2.0 ≦ (D2/D1).
Alternatively, the passage width D1 and the passage width D2 may also satisfy the relationship of 2.5 ≦ (D2/D1).
In the above-described embodiment, in the
In some embodiments, the pitch P in the blade height direction of a pair of
The effect of improving the heat transfer rate by the
In the above-described embodiment, the pitch P in the blade height direction of a pair of
Alternatively, the pitch P in the blade height direction of a pair of
For example, as described above, the exemplary cooling passage 59 shown in fig. 8 is divided into three regions in the blade height direction, and the plurality of
The pitch Pa of the plurality of turbulators 34a belonging to the region on the tip end 48 side, the pitch Pb of the plurality of turbulators 34b belonging to the intermediate region, and the pitch Pb of the plurality of turbulators 34c belonging to the region on the base end 50 side satisfy the relationship Pa < Pb < Pc.
As described above, the pitch P of the plurality of
That is, in a certain cooling passage 59, the cooling passage 59 may be divided into n regions in the blade height direction, and the pitch P of the
In several embodiments, the ratio (P/ea) of the pitch P between any pair of
In addition, in several embodiments, (P/ea) and (P/ea)AVECan also satisfy the condition of (P/ea)/(P/ea) of 0.9 ≦ andAVE≤1.1。
in the above-described embodiment, the (P/ea) associated with any pair of
In some embodiments, the inclination angle θ of any turbulator 34 with respect to the flow direction of the cooling fluid in the cooling passage 59 (at least one of the
The effect of the improvement in heat transfer rate by the
In some embodiments, the cooling passage 59 is at least one of the
When the height of the
[(e/D)E1/(e/D)AVE]<[(e/D)T_E1/(e/D)T_AVE]
···(II)
In the above formula (II), (e/D)E1With respect to the ratio of the height of the turbulator 34T (refer to fig. 7 and 9) located at the most
As described above, with the
That is, in the above-described embodiment, in the
Further, in the
In several embodiments, the height e of the
For example, in the embodiment of the
In addition, for example, in the embodiment of the vane 24 shown in fig. 9, the upstream side cooling passage located adjacent to the final passage 66 (
In addition, when the turbulator heights e of the
According to the above-described embodiment, since the height of the turbulator (final passage turbulator 37) of the
In some embodiments, the following formula (III) is satisfied when the height of the
[(e/D)E2/(e/D)AVE]>[(e/D)L_E2/(e/D)L_AVE]
···(III)
In the above formula (III), (e/D)E2About the second end 102-most side in the blade height direction of the turbulators 34The ratio of the height of the turbulator 34H (see FIG. 7) to the passageway width, (e/D)AVEIs the average of the ratio (e/D) of the height e to the channel width D of the plurality of turbulators 34 (e/D)L_F2With respect to the ratio of the height e of the leading edge side turbulator 35H located at the side closest to the
As described above, with respect to the
That is, according to the above-described embodiment, in the leading
While the embodiments of the present invention have been described above, the present invention is not limited to the above embodiments, and includes a mode in which modifications are applied to the above embodiments and a mode in which the modes are appropriately combined.
In the present specification, expressions indicating relative or absolute arrangement such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "central", "concentric", or "coaxial" indicate not only such arrangement strictly, but also a state in which relative displacement is achieved with a tolerance, or an angle or a distance to the extent that the same function can be obtained.
For example, expressions indicating states of equivalent things such as "identical", "equal", and "homogeneous" indicate not only states of exact equivalence but also states of tolerance or difference in degree to which the same function can be obtained.
In the present specification, the expression "a shape" such as a rectangular shape or a cylindrical shape means not only a shape such as a geometrically strict rectangular shape or a cylindrical shape, but also a shape including a concave-convex portion, a chamfered portion, and the like within a range in which the same effect can be obtained.
In the present specification, the expression "including", or "having" a component is not an exclusive expression excluding the existence of another component.
Description of reference numerals:
a gas turbine;
a compressor;
a burner;
a turbine;
a rotor;
a compressor housing;
an air intake;
a stationary vane;
a bucket;
a housing;
a turbine chamber;
a stationary vane;
a movable blade;
a combustion gas flow path;
ribs;
an exhaust chamber;
ribs;
ribs;
a return flow path;
a turbulator;
a leading edge side turbulator;
A leading edge side passage;
an outlet opening;
a final channel turbulator;
a turbine blade;
a blade body;
a leading edge;
a trailing edge;
a trailing edge end face;
a trailing edge portion;
a tip;
a top plate;
a base end;
an outboard end;
an inboard end;
56.. pressure side (ventral side);
58.. negative pressure side (back side);
a cooling passage;
60. a channel;
61. 61A, 61b.. the flow path is curved;
63... inner wall face;
an outlet opening;
66.. final channel;
cooling holes;
80.. a platform;
82.. blade root;
84A, 84b.. the internal flow path;
85.. an internal flow path;
86.. an inboard shroud;
88.. an outboard shield;
a first end portion;
a second end portion;
a via width;
p. turbulator spacing;
turbulator height;
tilt angle.
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