JP5180653B2 - Gas turbine blade and gas turbine provided with the same - Google Patents

Description

  The present invention relates to a turbine blade having a cooling structure and a gas turbine having the same.

A gas turbine is known in which air is compressed by a compressor, fuel is combusted in a combustor using the compressed air, and the obtained combustion gas is introduced into the turbine to rotate the turbine. And in the industrial gas turbine, electric power is obtained by converting the rotation output obtained in a turbine into electrical energy with a generator.
The efficiency of such a gas turbine can be improved by increasing the turbine inlet temperature of the combustion gas. At present, a gas turbine capable of realizing a turbine inlet temperature of about 1700 ° C. has been intensively studied.
However, when the turbine inlet temperature rises, the thermal environment of the turbine blades becomes severe, and is particularly severe in the first stage gas turbine stationary blade where the combustion gas first flows.

  Thus, various cooling methods for gas turbine stationary blades have been proposed. For example, in Patent Document 1, a steam passage through which cooling steam flows is formed along the shroud end portion of the gas turbine stationary blade, and the shroud end portion is cooled. Technology is disclosed.

Japanese Patent Laid-Open No. 9-228802 (see FIG. 1)

  However, since the steam passage is bent at the corner portion of the shroud, there is a possibility that a dead water area of the cooling steam may be generated, and the cooling performance in this area may be lowered.

  This invention is made | formed in view of such a situation, Comprising: It aims at providing the gas turbine blade which improved the cooling performance of the shroud, and the gas turbine provided with the same.

In order to solve the above problems, the gas turbine blade of the present invention and the gas turbine provided with the same employ the following means.
That is, a gas turbine blade according to the present invention includes a shroud portion provided with a cooling wall portion in contact with combustion gas, and a blade portion connected to the shroud portion, and the shroud portion cools the cooling wall portion. As described above, in the gas turbine blade in which an end cooling passage through which a cooling fluid flows along the end of the shroud portion is formed, the cooling wall portion located at a corner where the end cooling passage is bent. On the other hand, in addition to the end cooling flow path, corner cooling flow paths that are pores for blowing a cooling fluid are provided.

Since the cooling fluid is sprayed onto the cooling wall portion of the corner portion by the corner cooling flow path, cooling of the corner portion that may become a dead water area can be promoted.
As the cooling fluid, for example, steam obtained from an exhaust gas boiler is preferable.

  The gas turbine blade according to the present invention includes a shroud portion having a cooling wall portion in contact with the combustion gas, and a blade portion connected to the shroud portion, and the shroud portion cools the cooling wall portion. As described above, in the gas turbine blade in which the end cooling passage through which the cooling fluid flows along the end portion of the shroud portion is formed, the cooling fluid is disposed upstream of the corner portion where the end cooling passage is bent. Is provided with a first restricting portion that restricts the tip of the corner portion toward the front end side of the corner portion.

  Since the cooling fluid is guided to the corner portion while being accelerated by the first throttle portion, it is possible to promote the cooling of the tip portion of the corner portion that may become a dead water area.

  Furthermore, the gas turbine blade according to the present invention is characterized in that a second cooling flow path for cooling a region where the flow of the cooling fluid is inhibited by the first throttle portion is provided.

An area (dead water area) in which the flow is hindered by the first throttle and the cooling fluid stagnates may be formed. Therefore, in the present invention, a second cooling flow path for cooling a region (dead water region) where the flow of the cooling fluid is inhibited by the first throttle portion is provided to prevent a decrease in cooling performance.
As the second cooling flow path, for example, a film cooling flow path that causes the air obtained from the compressor to flow as a cooling fluid and flows out from the cooling wall portion to the combustion gas flow path to perform film cooling may be used. preferable.

  The gas turbine blade according to the present invention includes a shroud portion having a cooling wall portion in contact with the combustion gas, and a blade portion connected to the shroud portion, and the shroud portion cools the cooling wall portion. As described above, in the gas turbine blade in which the end cooling passage through which the cooling fluid flows along the end of the shroud portion is formed, on the downstream side of the end cooling passage inclined in the cooling fluid flow direction. A second restricting portion is provided for restricting the cooling fluid so as to guide the cooling fluid to the cooling wall portion side.

In the case where the end cooling flow path is inclined in the flow direction of the cooling fluid, the cooling fluid drifts and the main flow of the cooling fluid moves away from the cooling wall, which may reduce the cooling performance. On the other hand, by squeezing and accelerating the cooling fluid to the cooling wall portion side by the second restricting portion, a necessary flow velocity in the cooling wall portion is ensured to prevent a decrease in cooling performance.
In particular, when a turbulator for breaking the boundary layer of the cooling fluid is provided on the surface of the cooling wall, the second throttle is effective because the main flow of the cooling fluid tends to move away from the cooling wall. is there.

  Furthermore, in the gas turbine blade of the present invention, an impingement cooling unit that impinges and cools the cooling wall by spraying a cooling fluid is provided inside the end cooling channel, and the impingement cooling unit includes: The cooling fluid is divided into an upstream region and a downstream region, and the cooling fluid is guided to the upstream region and then guided to the downstream region.

An impingement cooling section that performs impingement cooling is provided inside the end cooling flow path. As a cooling fluid for impingement cooling, for example, steam obtained from an exhaust gas boiler is preferable. By dividing the impingement cooling section into an upstream region and a downstream region, the flow of the jet flow for impingement cooling is limited by limiting the region in which the cross flow flowing in the direction orthogonal to the jet flow for impingement cooling flows. The cross flow that inhibits can be reduced. In addition, since the cooling fluid is guided to the upstream region and then flows to the downstream region, the flow of the cooling fluid can be appropriately set according to the heat load.
The upstream region and the downstream region are preferably connected by a pipe provided on the back surface of the shroud portion (the side opposite to the main flow of the combustion gas).

  A gas turbine according to the present invention includes a compressor that compresses air, a combustor that burns fuel using the air compressed by the compressor, and a gas turbine blade that receives combustion gas from the combustor. The gas turbine blade is any one of the gas turbine blades described above.

  By providing the gas turbine blade excellent in the cooling performance described above, the temperature of the combustion gas flowing into the turbine can be increased, and a highly efficient gas turbine can be provided.

  ADVANTAGE OF THE INVENTION According to this invention, the gas turbine blade which improved cooling performance by reducing the dead water area of the edge part cooling flow path provided in the shroud part, and a gas turbine provided with the same can be provided.

Embodiments according to the present invention will be described below with reference to the drawings.
The gas turbine according to the present embodiment includes a compressor that compresses air, a combustor that combusts fuel using the air compressed by the compressor, and a turbine that guides combustion gas from the combustor. . The turbine is an axial turbine in which stationary blades and moving blades are alternately provided in the rotation axis direction.
FIG. 1 is a longitudinal sectional view showing a shroud portion 3 of a stationary blade (gas turbine blade) 1. The stationary blade 1 is a first-stage stationary blade provided on the most upstream side. However, the stationary blade 1 shown in the figure can also be used for the second and subsequent stationary blades.
The shroud portion 3 shown in the figure is an outer shroud provided on the outer peripheral side of the stationary blade 1, and the outer peripheral end of the blade portion 5 is connected thereto. Although not shown, an inner shroud is connected to the inner peripheral end of the wing part 5.

The shroud portion 3 includes a cooling wall portion 7 that contacts the combustion gas. The cooling wall portion 7 is inclined so as to decrease in diameter toward the rotating shaft side of the turbine from the upstream side to the downstream side of the combustion gas. On the back surface of the cooling wall portion 7 (surface opposite to the main flow of combustion gas), a lid body 9 is provided that extends substantially in parallel with the cooling wall portion 7 at a position separated by a predetermined distance. A steam cooling space 11 is formed by the lid body 9 and the cooling wall portion 7. A cooling steam S as a cooling fluid is introduced into the steam cooling space 11.
In addition, the code | symbol 6 shows the flange for connecting with the transition piece of a combustor.

  As shown in FIG. 2, the cooling steam space 11 is divided into a plurality of rooms 11a, 11b, 11c, and 11d. The first chamber 11 a is formed in contact with the downstream side of the wing portion 5, the second chamber 11 b is formed in contact with the downstream side of the wing portion 5, and the third chamber 11 c is formed on the wing portion 5. The fourth chamber 11d is formed in contact with the front edge of the wing portion 5 and the abdomen side upstream. The first room 11a and the fourth room 11d are partitioned by a first partition wall 15a, and the second room 11b and the third room 11c are partitioned by a second partition wall 15b.

  As shown in FIG. 3, in each of the rooms 11a, 11b, 11c, and 11d, impingement plates 13a, 13b, 13c, and 13d having a plurality of small holes having a diameter of about 1.5 mm are formed. Has been placed. As shown in FIG. 1, the impingement plate 13 is disposed substantially parallel to the cooling wall portion 7 in the cooling steam space 11. The impingement cooling section is constituted by the impingement plate 13 and the cooling steam space formed therebelow. That is, impingement cooling is performed when the jet J of the cooling steam ejected from the small hole of the impingement plate 13 collides with the back surface of the cooling wall portion 7.

  As shown in FIG. 1, the upstream end of the first pipe 17 is connected to the third impingement plate 13c provided in the third chamber 11c. The 1st piping 17 is provided so that it may bend in the back side of the shroud part 3, The downstream end is connected to the cover body 9 so that it may open in the 4th chamber 11d. FIG. 3 shows a connection position of the first pipe 17 with respect to the third impingement plate 13c.

Further, as shown in FIG. 4, the upstream end of the second pipe 18 is connected to the first impingement plate 13a provided in the first chamber 11a. The 2nd piping 18 is provided so that it may bend in the back side of the shroud part 3, The downstream end is connected to the cover body 9 so that it may open in the 4th chamber 11d. FIG. 3 shows a connection position of the second pipe 18 with respect to the first impingement plate 13a.
The fourth impingement plate 13d is connected to a cooling steam recovery pipe 19 that recovers the cooling steam that has finished cooling the shroud portion 3. However, these cooling steam recovery pipes 19 are not shown in FIGS.

As shown in FIG. 2, an end cooling flow path 20 is formed so as to surround each of the rooms 11a, 11b, 11c, and 11d. The end cooling flow path 20 is provided along four sides of the shroud portion 3 that has a substantially rhombus shape when viewed in plan, and cools the end portion of the shroud portion 3. Accordingly, the rooms 11a, 11b, 11c, and 11d are located inside the end cooling flow path 20.
A turbulator 22 for promoting heat transfer is provided on the back surface of the cooling wall portion 7 constituting the end cooling flow path 20.
The end cooling channel 20 includes a first end cooling channel 20a, a second end cooling channel 20b connected to the first end cooling channel 20a at a first corner 21a, A third end cooling channel 20c connected to the second end cooling channel 20b at a second corner 21b, and a third corner 21c to the third end cooling channel 20c. And a fourth end cooling channel 20d connected to each other. The fourth end cooling channel 20d and the first end cooling channel 20a are connected by a fourth corner 21d.

  The first end cooling channel 20a is located on the back side of the wing part 5, and is provided in contact with the second chamber 11b and the third chamber 11c. The second end cooling channel 20b is located on the ventral side of the wing part 5, and is provided in contact with the first chamber 11a and the fourth chamber 11d. The third end cooling channel 20c is located on the front edge side of the wing part 5 and is in contact with the fourth chamber 11d. The fourth end cooling channel 20d is located on the front edge side and the back side of the wing part 5, and is provided in contact with the fourth chamber 11d and the third chamber 11c.

In the first corner portion 21a and the third corner portion 21c, the flow paths are connected so as to intersect at an acute angle (for example, about 50 °). In the 2nd corner | angular part 21b and the 4th corner | angular part 21d, it connects so that a flow path may cross | intersect an obtuse angle (for example, about 130 degrees).
The channel width of the first end cooling channel 20a is wider than the other end cooling channels 20b, 20c, 20d.

In the vicinity of the fourth corner portion 21d of the first cooling flow path 20a, a cooling steam introduction port 24 for introducing cooling steam is provided. A cooling steam outlet 25 through which cooling steam flows out to the fourth chamber 11d side is provided in the vicinity of the third corner portion 21c of the fourth cooling flow path 20d.
The cooling steam supplied from the cooling steam inlet 24 to the first cooling flow path 20a is divided into two directions, one flowing to the first corner 21a and the other flowing to the fourth corner 21d. The cooling steam that has flowed to the first corner portion 21a changes the flow direction at the first corner portion 21a to flow through the second flow path 20b, and further changes the flow direction at the second corner portion 21b to change the third flow. After flowing through the passage 20c and changing the flow direction at the third corner portion 21c to flow into the fourth flow path 20d, it flows from the cooling steam outlet 25 to the fourth chamber 11d. The cooling steam that has flowed to the fourth corner portion 21d changes the flow direction at the fourth corner portion 21d, flows through the fourth flow path 20d, and reaches the third corner portion 21c before passing through the cooling steam outlet 25. It flows into 4 rooms 11d.

  As shown in FIG. 4, a first corner cooling introduction passage 27 is provided above the first corner 21 a (that is, on the back side). As shown in FIG. 5, the first corner portion cooling introduction path 27 is formed over a region including the first corner portion 21a of the first end portion cooling passage 20a, and cooling steam is supplied from the second chamber 11b. It has come to be guided. The first corner portion that blows out toward the rear surface of the cooling wall portion 3 at the front end of the first corner portion 21a at the downstream end of the first corner portion cooling introduction path 27, that is, the position corresponding to the front end of the first corner portion 21a. Cooling holes (corner cooling flow paths) 29 are formed. The number of the first corner cooling holes 29 is appropriately set according to the region to be cooled, and is set to two in the present embodiment. The diameter of the first corner cooling hole 29 is, for example, about 1 mm. As shown in FIGS. 4 and 6, the first corner cooling hole 29 is formed in the plate thickness direction so as to communicate the first corner cooling introduction path 27 and the first end cooling flow path 20a. The pores are made.

As shown in FIG. 2, a first throttle portion 31 is provided at a position immediately before flowing into the fourth corner portion 21d of the first end cooling flow path 20a. The first throttle part 31 is configured by a wall part formed so as to extend from the inner wall part 20d1 of the fourth end cooling channel 20d. Accordingly, the first throttle part 31 extends so as to be substantially orthogonal to the flow path direction of the first end cooling flow path 20a. The inner end portion 31a of the first throttle portion 31 is connected to the inner wall portion 20a1 of the first end cooling channel 20a. On the other hand, the outer end portion 31b of the first throttle portion 31 is separated from the outer wall portion 20a2 of the first end portion cooling channel 20a, and a gap 33 through which cooling steam flows is formed. As shown in FIG. 6, the height of the first throttle wall 31 is of a size that closes the first end cooling channel 20a.
In this way, the cooling steam that flows through the first end cooling channel 20a and travels toward the fourth corner 21d is throttled by the gap 33 and accelerated.

  As shown in FIG. 2, a second throttle 35 is provided in the immediate vicinity of the second corner 21b of the third end cooling channel 20c. The second throttle portion 35 is provided across the channel width of the third end cooling channel 20c. However, as shown in FIG. 7, it is provided only in the upper part of the third end cooling channel 20c, and a gap 37 is formed in the lower part. Therefore, the cooling steam passing through the second throttle part 35 is throttled and accelerated so as to flow downward (cooling wall part 7 side).

  As shown in FIG. 2, the inner side of the fourth end cooling channel 20 d and the back side of the blade portion 5 are provided substantially in parallel with the fourth end cooling channel 20 d. A film cooling section (second cooling flow path) 39 is provided. The film cooling unit 39 is provided on the upstream side of the combustion gas in the region A serving as a dead water region for the cooling steam formed by the first throttle unit 31. Cooling air is introduced into the film cooling unit 39, and compressed air obtained from a compressor of a gas turbine is used as the cooling air. As shown in FIGS. 8 and 9, the film cooling unit 39 includes a plurality of film cooling holes 41. The film cooling hole 41 is connected to the small hole 42 formed on the upstream side, and the cross-sectional area of the flow path increases as it goes downstream, and is formed on the surface of the cooling wall portion 7 (surface in contact with the combustion gas). And a trumpet-shaped channel 43 formed so as to flow out along.

Next, a cooling method for the stationary blade having the above configuration will be described.
The cooling steam guided from the exhaust gas boiler is guided to the first room 11a, the second room 11b, and the third room 11c which are upstream regions. The cooling steam guided to each of the rooms 11a, 11b, and 11c passes through the impingement plates 13a, 13b, and 13c, then collides with the back surface of the cooling wall portion 7, and impingement cooling of the cooling wall portion 7 is performed. I do. As shown in FIGS. 1 and 4, the steam after impingement cooling is collected by the first pipe 17 and the second pipe 18 and guided to the fourth chamber 11d. In addition, the cooling steam which performed the impingement cooling in the 2nd chamber 11b is guide | induced to the 1st corner | angular part cooling introduction path 27, as FIG. 5 shows.
The cooling steam guided to the fourth chamber 11d passes through the fourth impingement plate 13d and performs the impingement cooling of the cooling wall portion 7, and is then recovered by the cooling steam recovery pipe 19 (see FIG. 3). Returned to the exhaust gas boiler.

The cooling of the end portion of the shroud portion 3 is performed as follows.
As shown in FIG. 2, the cooling steam is supplied from the cooling steam inlet 24 and flows into the first end cooling flow path 20a. The cooling steam that flows through the first end cooling channel 20a and travels toward the first corner 21a changes its direction at the first corner 21a. At this time, the first corner portion 21a has an acute bend angle and flows from the first end cooling channel 20a having a wider channel width to the second end cooling channel 20b having a smaller channel width. There is a possibility that a dead water area may be formed at the tip of the first corner portion 21a. In the present embodiment, another cooling steam is ejected from the first corner cooling hole 29 toward the cooling wall portion 7 with respect to this position to promote cooling. As shown in FIG. 5, the cooling steam supplied to the first corner cooling hole 29 is guided from the second chamber 11 through the first corner cooling introduction path 27.

  Then, the cooling steam flows through the second end cooling passage 20b, changes the flow direction at the second corner portion 21b, and flows into the third end cooling passage 20c. Immediately after flowing into the third end cooling channel 20 c, the cooling steam is throttled by the second throttle 35 (see FIGS. 2 and 7) and throttled downward toward the back surface of the cooling wall 7. And accelerate. The operational effects of the second aperture 35 are as follows. As shown in FIGS. 1 and 4, the second end cooling flow path 20 b is inclined in the flow direction of the cooling steam. And the turbulator 22 is formed in the 2nd end part cooling flow path 20b at the cooling wall part 7 side. Therefore, the main stream of the cooling steam tends to flow away from the cooling wall portion 7. In this case, the necessary flow velocity in the vicinity of the cooling wall portion 7 cannot be ensured and the cooling performance is deteriorated. Therefore, in the present embodiment, by providing the second throttle portion 35, the flow after passing through the second end cooling channel 20b is throttled toward the cooling wall portion 7 side. Thereby, the cooling steam which flows through the 3rd end part cooling channel 20c comes to flow through the cooling wall part 7, and cooling performance improves.

  Then, the cooling steam flows through the third end cooling channel 20c, changes the flow direction at the third corner 21c, and flows into the fourth end cooling channel 20d. The cooling steam that has flowed into the fourth end cooling channel 20d flows into the fourth chamber 11d through the cooling steam outlet 25 and is recovered by the cooling steam recovery pipe 19 (see FIG. 3).

On the other hand, the cooling steam supplied from the cooling steam inlet 24 and flowing through the first end cooling flow path 20a to the fourth corner 21d is throttled by the first throttle 31 just before flowing into the fourth corner 21d. To be accelerated. When squeezing in this way, the cooling steam passes through the gap 33 provided on the tip end side of the fourth corner portion 21d, so that the tip end of the fourth corner portion 21d that may become a dead water area is effectively cooled. .
Then, the cooling steam flows through the fourth end cooling flow path 20d toward the third corner 21c, passes through the cooling steam outlet 25 provided on the upstream side of the third corner 21c, and enters the fourth chamber 11d. And is recovered by the cooling steam recovery pipe 19 (see FIG. 3).

In the film cooling unit 39, film cooling is performed as follows.
Cooling air obtained from the compressor of the gas turbine is guided to the film cooling unit 39 and passes through the film cooling hole 41 formed so as to penetrate the cooling wall unit 7. Out to the surface). The cooling air that has flowed out to the surface of the cooling wall portion 7 flows in a film form along the surface of the cooling wall portion 7 and cools the cooling wall portion 7. In particular, the film air that has flowed out flows on the surface of the cooling wall portion 7 corresponding to the region A (see FIG. 2) that becomes a dead water region because the flow of the cooling steam is inhibited by the first throttle portion 31.

According to this embodiment mentioned above, there exist the following effects.
Since the tip portion that may become the dead water area of the first corner portion 21a is separately cooled by the cooling steam blown out from the first corner portion cooling hole 29, the lack of cooling in the first corner portion 21a can be solved. it can.

  Since the cooling steam is throttled by the first throttling portion 31 and is forced to flow to the tip end portion of the fourth corner portion 21d, it is possible to improve cooling of a region that may become a dead water zone.

  Since the surface of the cooling wall portion 7 corresponding to the dead water area A of the cooling steam formed by the first throttle portion 31 is cooled by the film air from the film cooling portion 39, it is formed by the first throttle portion 31. The cooling performance in the area A, which is a dead water area, is not impaired. Furthermore, since the film cooling part 39 is provided on the back side of the wing part 5, it is possible to intensively cool an area where cooling is required.

  By providing the second throttle part 35, the flow of the cooling steam that has flowed through the second cooling flow path 20 b inclined in the flow direction and moved away from the cooling wall part 7 is directed to the cooling wall part 7. Thereby, the cooling performance of the 3rd end part cooling channel 20c can be improved.

  The chambers 11a, 11b, 11c, and 11d that perform impingement cooling are provided inside the end cooling flow path 20, and include an upstream region that includes the first to third chambers 11a, 11b, and 11c and a fourth chamber 11d. It was decided to divide it into the downstream area. Thereby, the area | region where the crossflow which flows in the direction orthogonal to the jet which performs impingement cooling flows is limited, and the crossflow which inhibits the flow of the jet which performs impingement cooling can be reduced. In addition, since the cooling fluid is guided to the upstream region and then flows to the downstream region, the flow of the cooling fluid can be appropriately set according to the heat load.

It is the longitudinal cross-sectional view which showed the shroud part periphery of the stationary blade concerning one Embodiment of this invention. FIG. 2 is a transverse sectional view taken along a cutting line II-II in FIG. 1. FIG. 3 is a transverse sectional view taken along a cutting line III-III in FIG. 1. It is the longitudinal cross-sectional view which showed the shroud part periphery of the stationary blade cut | disconnected in the position different from FIG. FIG. 5 is a transverse sectional view taken along a cutting line VV in FIG. 4. It is a longitudinal cross-sectional view in the cutting line VI-VI of FIG. It is a longitudinal cross-sectional view in the cutting line VII-VII of FIG. It is the top view which expanded and showed the film cooling part and was seen from the surface side of the cooling wall part. It is the longitudinal cross-sectional view which expanded and showed the film cooling part.

Explanation of symbols

1 Static blade (gas turbine blade)
3 shroud part 5 wing part 7 cooling wall part 9 cover body 11 cooling steam space 13 impingement plate 17 first pipe 18 second pipe 20 end cooling flow path 20a first end cooling flow path 20b second end cooling flow Path 20c third end cooling channel 20d fourth end cooling channel 21a first corner 21b second corner 21c third corner 21d fourth corner 29 first corner cooling hole (corner cooling channel) )
31 First throttle 33 33 Gap 35 Second throttle 37 Gap 39 Film cooling part (second cooling flow path)

Claims (6)

A shroud portion having a cooling wall portion in contact with the combustion gas, and a wing portion connected to the shroud portion,
In the gas turbine blade, in the shroud portion, an end cooling flow path in which a cooling fluid flows along an end portion of the shroud portion so as to cool the cooling wall portion,
In addition to the end cooling flow path, a corner cooling flow path that is a pore for blowing cooling fluid is provided on the cooling wall portion positioned at the corner where the end cooling flow path is bent. A gas turbine blade characterized by comprising: The upstream side of the corner front Kitan portion cooling passage is bent, claims cooling fluid, characterized in that the first throttle portion for throttling as toward the tip end side of the corner portion is provided 1 The gas turbine blade described in 1 .   3. The gas turbine blade according to claim 2, wherein a second cooling flow path for cooling a region where the flow of the cooling fluid is inhibited by the first throttle portion is provided. Claims before Symbol downstream of said end portion cooling passage which is inclined in the flow direction of the cooling fluid, wherein the second throttle portion for throttling to guide the cooling fluid to the cooling wall portion is provided Item 4. The gas turbine blade according to Item 1 . An impingement cooling part that impinges and cools the cooling wall part by spraying a cooling fluid is provided inside the end cooling channel,
The impingement cooling part is divided into an upstream region and a downstream region,
The gas turbine blade according to claim 1, wherein the cooling fluid is guided to the downstream region after being guided to the upstream region. A compressor for compressing air;
A combustor that burns fuel using air compressed by the compressor;
A gas turbine blade to which combustion gas from the combustor is guided,
The gas turbine blade is a gas turbine blade according to any one of claims 1 to 5, wherein the gas turbine blade is a gas turbine blade.

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