JPH08270402A - Stationary blade of gas turbine - Google Patents

Abstract

PURPOSE: To enable a moving blade to attain a high temperature operation and large capacity without needing to cool the interior of the moving blade disposed immediately behind a stationary blade. CONSTITUTION: A stationary blade 1 is provided in the interior with a hollow part 3 from which air having the temperature lower than that of main flow gas is jetted to the outside of a stationary blade to be mixed with main flow gas. A jetting flow path 4a for jetting the air from the stationary blade 1 is directed toward the moving blade 2 located right behind the stationary blade, while the air jetted from the jetting flow path is set to lower the temperature of the main flow gas flowing into the moving blade 2.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine stationary blade used for power generation or the like, and more particularly to a gas turbine stationary blade capable of effectively cooling the moving blade when the mainstream gas temperature is high. .

[0002]

2. Description of the Related Art A conventional example will be described with reference to FIGS. The blade row shown in the figure constitutes a general paragraph mainly used in a low pressure part of a gas turbine, and a stationary blade 1 and a moving blade 2 are sequentially arranged.

When the temperature of the mainstream gas is equal to or lower than the allowable temperature of the member, the moving blade 2 is usually a solid blade having no internal cooling passage, and the stationary blade 1 has a hollow portion 3 as an internal cooling passage. Then
The low-temperature air supplied to the hollow portion 3 is blown out from the inter-blade clearance 5 between the stationary blade row and the moving blade row for sealing the blade root side.

On the other hand, when the mainstream gas temperature at the blade row inlet exceeds the member allowable temperature, both the stationary blades 1 and the moving blades 2 have a hollow portion (not shown), and the cooling air supplied to the hollow portion. By performing internal cooling by means of, the member temperature is lowered to an allowable value.

[0005]

By the way, when a gas turbine is used in a power plant, its performance is evaluated by its thermal efficiency and output per unit. Increasing the turbine inlet gas temperature and increasing the turbine low-pressure stage blade height to increase the capacity are effective means for improving thermal efficiency and increasing output, respectively.

In general, a gas turbine moving blade is designed so that the centrifugal stress applied to the moving blade cross section by rotation is lower than the allowable stress of the moving blade member. If the number of revolutions is constant, the centrifugal stress applied to an arbitrary cross section of the gas turbine rotor blade is proportional to the position of the center of gravity of the member existing on the outer diameter side. As the blade height increases, the position of the center of gravity also rises accordingly, so that centrifugal stress also increases.

On the other hand, the allowable stress of a moving blade member is a function of the member temperature, and in the case of a member generally used for a gas turbine moving blade, the allowable stress decreases as the member temperature rises.
Therefore, when the member temperature rises and the moving blade height increases, there arises a problem that the centrifugal stress exceeds the allowable stress.

FIG. 34 shows an example of the relationship between the centrifugal stress 13 and the permissible stress 12 of the gas turbine rotor blade when the temperature is increased and the capacity is increased for the paragraph having the conventional turbine stator blade. It is the graph shown. The horizontal axis of the graph represents the radial height of the moving blade inlet, and the vertical axis represents the stress and the gas temperature.

In a general gas turbine combustor, due to the fuel concentration distribution, the mixing of cooling air on the wall surface of the combustor, and the like, a combustion gas temperature distribution is generated in which the central portion of the flow passage has a higher temperature than the vicinity of the wall surface. This temperature distribution is maintained even while passing through the turbine blade row, and the temperature 14 of the mainstream gas is lower than the radial average temperature at the blade root portion and the blade tip portion and higher than the radial average temperature near the blade center. Has a distribution of

Therefore, the allowable stress 12 decreases near the center of the blade where the temperature becomes high. On the other hand, the centrifugal stress 13 becomes maximum at the blade root portion and monotonically decreases with respect to the blade height. In the illustrated example, the centrifugal stress 13 exceeds the allowable stress 12 in the range of 25% to 65% of the blade height.

When the centrifugal stress applied to the cross section of the moving blade exceeds the allowable stress as in this example, conventionally, the moving blade has a hollow structure, and the moving blade reaches a temperature at which the allowable stress is reached by cooling air ventilation. As described above, the means for lowering the member temperature is taken.

However, as represented by the last stage of the gas turbine, when the rotor blade is thin and has a shape twisted in the radial direction, effective cooling from the inside is difficult.

Further, especially in the case of the final stage rotor blade, if internal cooling is carried out, there is no means for recovering the energy of the used cooling air, which leads to a significant decrease in thermal efficiency, which leads to an increase in turbine inlet temperature. This results in a loss of cycle benefits.

Therefore, it is necessary to keep the turbine inlet temperature and the capacity within the condition that the turbine last stage moving blade is established without applying the internal cooling, which is one of the restrictions for improving the performance of the gas turbine.

The present invention has been made in view of the above circumstances, and provides a gas turbine stationary blade capable of achieving high temperature and large capacity without internal cooling of a moving blade disposed immediately after. The purpose is to do.

[0016]

According to a first aspect of the present invention, a hollow portion is provided inside a stationary blade, and air having a temperature equal to or lower than a mainstream gas is blown out from the hollow portion to the outside of the stationary blade to be mixed with the mainstream gas. In the gas turbine stationary blade, the blowing passage for blowing air from the stationary blade is directed to the moving blade located immediately after the stationary blade, and the air blown from the blowing passage is the moving blade. It is characterized in that it is set to lower the temperature of the mainstream gas flowing into the.

According to a second aspect of the present invention, in the gas turbine stationary blade according to the first aspect, the blowout passage is located at a position of 25% to 75% in radial length ratio from the tip end side of the stationary blade outlet portion. It is arranged or divided into a plurality of parts within the same arrangement, or the blowout flow path is formed as a diagonal flow path in order to concentrate the blowout air to a radial position where the temperature of the mainstream gas at the blade inlet needs to be lowered. Characterize.

According to a third aspect of the present invention, in the gas turbine stationary blade according to the first aspect, the blowout passage is disposed at the trailing edge of the stationary blade,
In addition, the blowout flow path portion at the trailing edge of the vane is projected toward the downstream side of the mainstream gas.

According to a fourth aspect of the present invention, in the gas turbine vane according to the first aspect, the blowout passage is arranged on a side surface portion of the vane, and the flow passage area is changed in the radial direction of the vane. The radial distribution of the blown air flow rate is set.

According to a fifth aspect of the present invention, in the gas turbine stationary blade according to the first aspect, the stationary blade having the blowing passage is arranged immediately before the final stage moving blade.

[0021]

According to the first aspect of the present invention, the temperature of the gas at the inlet of the moving blade immediately after the stationary blade is lowered by blowing out air having a temperature equal to or lower than the mainstream gas from the hollow portion inside the stationary blade and mixing the air with the mainstream gas. It becomes possible. Therefore, for example, since the member temperature can be lowered even when the moving blade is not cooled, it can be sufficiently used in a range where the allowable stress exceeds the centrifugal stress.

According to the second aspect of the invention, from the radial tip of the stationary blade outlet immediately before the portion where the centrifugal stress of the moving blade is highly likely to exceed the allowable stress, the radial height ratio is 2
Since the air is blown out to the radial position of 5% to 75%, it is possible to supply the mixing air only to a necessary portion to locally lower the temperature of the gas at the blade inlet.

Further, in the present invention, by providing a plurality of blow-out flow passages and having a structure capable of controlling the air flow rate in the radial direction, it is possible to supply the mixing air to the required place at the required flow rate.

Further, in the present invention, by making the blow-out flow path an oblique flow path, diffusion is prevented until the low temperature region after mixing reaches the leading edge of the moving blade immediately after, and the mixing air is effectively used. it can.

According to the third aspect of the present invention, the blowout passage is arranged at the trailing edge of the vane, and the blowout passage portion of the trailing edge of the vane is projected toward the downstream side of the mainstream gas. It is possible to allow the air to flow into the moving blade in a state where the distance between the portion and the leading edge of the moving blade is reduced, and the low temperature region is concentrated at the required radial position.

According to the fourth aspect of the present invention, by changing the area of the flow passage of the vane in the blade height direction, the radial distribution of the flow rate of the blown air can be set well, and it is necessary to set it at a necessary place. Air can be supplied at a flow rate.

According to the fifth aspect of the present invention, by disposing the gas turbine stationary blade immediately before the final stage moving blade, it is possible to lengthen the moving blade without internal cooling, so that the gas turbine efficiency is reduced. It is possible to increase the temperature and increase the size without involving.

[0028]

Embodiments of the present invention will be described below with reference to the drawings.

Embodiment 1 (FIGS. 1 to 9) FIG. 1 is a circumferential sectional view of a gas turbine low pressure stage according to the present embodiment, and FIG. 2 is a sectional view taken along the line AA of FIG.

In this embodiment, the gas turbine stage is composed of a pair of stationary blades 1 and moving blades 2. The stationary blade 1 has a hollow portion 3, and cooling air is supplied into the hollow portion 3 from the outer diameter side of the blade.

The hollow portion 3 may also be constructed so as to utilize a space for supplying seal air, which is the same as the conventional one, for blowing the seal air from the clearance 5 between the blade rows, or an internal cooling passage provided for cooling the stationary blade 1 itself. good. Inside the vane on the trailing edge side of the vane 1, as shown by the graduation display at the right end of FIG. 1, a hollow portion extends from 25% to 75% in length ratio from the tip along the radial direction of the vane 1. A trailing edge slit 4a is provided as a flow passage for the cooling air that communicates the portion 3 with the outside.

The trailing edge slit 4a as the blowout flow passage may be arranged in any range as long as it is in the range of 25% to 75% of the height of the stationary blade outlet.

FIG. 3 is a sectional view taken along line BB of FIG. 2, and FIG. 4 is shown in FIG.
FIG. 4 is a right side view of the trailing edge slit 4 as an outlet flow path.
The detailed shape of a is shown.

As shown in these figures, the trailing edge slit 4
The width 4b of a is equal to or less than the trailing edge thickness of the stationary blade 1, and the trailing edge slit 4a is divided into a plurality of step-shaped flow passages by the upper and lower ribs 6a provided in the trailing edge slit 14a. ing. The number of divided channels and the channel width 4b by the rib 6a can be arbitrarily selected.

5 and 6 show modifications of the trailing edge slit 4a, which correspond to FIGS. 3 and 5, respectively. In the example shown in FIGS. 5 and 6, a columnar structure 6b is provided in the trailing edge slit 4a instead of the flow path forming rib 6. As in the above case, the favorable air is blown out also by the blowout flow path formed by the trailing edge slit 4a divided by the columnar structure 6b.

FIG. 7 and FIG. 8 show another modification of the blowout flow path. In the examples shown in FIGS. 7 and 8,
Instead of the trailing edge slit 4a, a plurality of parallel small-diameter holes are formed to provide a blowout flow path including the hole flow path 4c.

FIG. 9 shows the trailing edge slit 4a or hole channel 4
The distribution state of the amount of air blown out from c is shown. As shown in the figure, in this embodiment, part of the cooling air supplied to the hollow portion 3 is a trailing edge slit 4 a provided in the stationary blade 1.
Alternatively, it is blown out substantially evenly through the hole flow path 4c, is mixed with the mainstream gas, and reaches the inlet of the moving blade 2 in a state where the gas temperature is lowered.

According to this embodiment, the cooling air is directed to the moving blade 2 side from the trailing edge slit 4a or the hole flow passage 4c extending from the radial tip of the stationary blade 1 in the length ratio from 25% to 75%. Since it is blown out, the cooling air for gas mixture can be blown out to a portion where the centrifugal stress of the moving blade 2 is likely to exceed the allowable stress, and the inlet portion of the moving blade 2 can be cooled well.

Embodiment 2 (FIGS. 10 to 18) In this embodiment, the trailing edge slit serving as the blowout flow path is provided with the stationary blade 1.
Within the range of 25% to 75% in length ratio from the radial tip of the above, the blowing direction of the mixed cooling air is concentrated at a predetermined position.

That is, FIG. 10 is a circumferential sectional view of a gas turbine low pressure stage according to this embodiment, and FIG. 11 is a sectional view taken along the line CC of FIG. 12 is a sectional view taken along the line DD of FIG. 11, and FIG. 13 is a side view of FIG.
Shows the details of.

Also in this embodiment, the trailing edge slit 4a is divided into a plurality of flow paths for the ribs 6a, but the gap between the roots of the ribs 6a on the hollow portion 3 side, that is, the flow rate of the mixing air is adjusted. Width (7a, 7b, 7c, 7d, 7 in FIG. 12)
(See e) is different so that it has a large value at the intermediate position.

Further, the flow passage outlet side end of each rib 6a forms an inclined flow passage which opposes so as to concentrate the mixed cooling air toward the radial center 4d of the blowout portion.

The radial center 4d of the blowout portion is the position where the mixing air is most needed, and the height ratio of the stationary blade outlet is set in the range of 40% to 50%.

In this embodiment, a part of the mixed cooling air supplied to the hollow portion 3 is blown out to the outside via the trailing edge slit 4a provided inside the blade. in this case,
As shown in FIG. 12, the flow rate adjustment range is set to, for example, 7a <7b <
By setting 7c>7d> 7e, the mixed cooling air can be concentrated in the vicinity of the radial center 4d of the blowout portion, which requires the most flow rate. Further, since the mixed cooling air flows out in accordance with the inclination of the rib 6a, the radial diffusion of the mixed region is suppressed.

In this embodiment, the blowout flow path of the stationary blade 1 is the trailing edge slit 4a, but instead of this, the hole flow path 4c may be used as in the first embodiment.

14 and 15 show an example in which the blowout flow path of the stationary blade 1 is the hole flow path 4c, and the inner diameter 4e of the hole flow path 4c is changed along the radial direction of the stationary blade 1. Is shown. As shown in these figures, mixing is performed by setting the inner diameter 4e of the hole flow passage 4c at a location where a large amount of mixed cooling air is to be supplied compared to the inner diameter 4e of the hole flow passage 4c at another location. The flow rate of the cooling air blown out can be controlled.

16 and 17 show an example in which the distance 4f between the hole flow paths 4c is changed in the radial direction. As shown in these figures, by setting the spacing 4f between the hole flow paths 4c at a location where a large amount of mixed cooling air is desired to be supplied, as compared to other locations, the blowout flow rate of the mixed cooling air can be increased. Can be controlled. In addition, the hole flow path 4c is the stationary blade 1
The parallel flow paths may be along the direction orthogonal to the radial direction of.

According to the above embodiment, the radial center 4d
By blowing out the required amount of mixed cooling air toward
For example, as shown in FIG. 18, the amount of air blown out on the radial center 4d side increases, whereby the mainstream gas temperature can be lowered to a temperature at which the allowable stress of the moving blade member is sufficiently high. The radial position where the mixed cooling air is blown out is appropriate in a range in which the centrifugal stress of the moving blade is likely to exceed the allowable stress, that is, in a range where the stationary blade outlet height ratio is 25% or more and 75% or less.

FIG. 19 is a graph showing the relationship between the mixed cooling air flow rate 15, the allowable stress 12, and the centrifugal stress 13. The horizontal axis represents the radial height of the moving blade inlet, and the vertical axis represents the stress and flow rate.

As shown in FIG. 19, by allowing the mixed cooling air to be blown at the moving blade inlet, that is, at the position of 33% to 63% in the height direction of the stationary blade outlet, the allowable stress 12 causes the centrifugal stress 13 to occur. It turns out that it exceeds.

Embodiment 3 (FIGS. 20 and 21) In this embodiment, with respect to the stationary blade 1 having the trailing edge slit 4a similar to that of the above-described Embodiment 2, the stationary blade trailing edge is projected toward the downstream direction of the mainstream gas. The curved rear edge 8 is formed. The stationary blade curved trailing edge 8 projects most at the center position in the radial direction, and the distance 1 between the projecting portion and the leading edge of the moving blade 2 immediately after it is 1
0a is shorter than the distance 10b between the straight trailing edge 9 and the leading edge of the moving blade 2 of the conventional example shown by the phantom line in FIG.

According to this embodiment having such a configuration, the mixed cooling air supplied from the hollow portion 3 of the stationary blade 1 flows out along the trailing edge slit 4a, but its outflow position is the same as in the conventional straight line. Compared with the case where the trailing edge 9 is provided, since it is closer to the leading edge of the immediately following moving blade 2, the diffusion of the mixed cooling air until it flows into the moving blade 2 is suppressed.

Embodiment 4 (FIGS. 22 to 25) In this embodiment, the mixed cooling air blowing passage is arranged not on the trailing edge of the stationary blade but on the blade side surface of the stationary blade 1.

As shown in FIGS. 22 and 23, the stationary blade 1
Of the back blade surface 1a and the ventral blade surface 1b of the stator blade within the range of 25% to 75% in the stator blade outlet height ratio.
And a plurality of hole flow paths 4c communicating with the outside of the blade are formed toward the trailing edge side of the stationary blade. The hole channel 4c may be formed only on one of the back surface 1a of the stationary blade 1 or the ventral surface 1b of the stationary blade 1.

FIG. 24 is a view on arrow G in FIG. As shown in FIG. 24, the hole flow paths 4c are arranged in the vicinity of the center 4d in the radial direction of the blowout portion at a distance 4f closer to the blade tip and blade root sides.

Therefore, the mixed cooling air supplied from the hollow portion 3 flows out of the blade from the hole flow passage 4c, but its flow rate becomes maximum in the vicinity of the radial center 4d of the blowout portion.

According to this embodiment having such a configuration, the required amount of mixing cooling air can be blown to the radial position where the centrifugal stress of the moving blade 2 is likely to exceed the allowable stress.

FIG. 25 shows a modification of this embodiment, in which the inner diameter 4e of the hole channel 4c is changed along the radial direction. According to such a configuration, the blowout flow rate is controlled by setting the inner diameter 4e of the hole flow passage 4c at a position where a large amount of mixed cooling air is to be supplied to be larger than the inner diameter 4e of the other hole flow passage 4c. Therefore, it is possible to obtain the same effect as that when the distance 4f between the hole channels 4c is changed.

Embodiment 5 (FIGS. 26 to 29) In this embodiment, a slit is arranged on the blade surface of the stationary blade 1 as a mixed cooling air blowing passage.

As shown in FIGS. 26 and 27, the stationary blade outlet height ratio of the stationary blade back side 1a and the ventral side blade surface 1b is 25.
% To 75%, a plurality of blade surface slits 11a that communicate the hollow portion 3 inside the stationary blade and the outside of the blade are formed. The blade surface slit 11a may be formed on only one of the stationary blade back surface 1a and the stationary blade ventral surface 1b.

FIG. 28 is a view on arrow I of FIG. As shown in FIG. 28, the slit width 1 of the blade slit 11a is 1
1b has a maximum width at the radial center 4d of the blowout portion.

Accordingly, the mixed cooling air supplied from the hollow portion 3 flows out from the blade surface slit 11a to the outside of the stationary blade, but its flow rate becomes maximum at the blowout portion radial center 4d where the slit width 11b is maximum. , The width of the slit 11b decreases toward the root side and the tip side.

According to the present embodiment having such a configuration, by determining the radial direction distribution of the slit width 11b so as to obtain a desired flow rate distribution, the required flow rate of the mixed cooling air is adjusted to an appropriate radial position. Can be supplied to.

FIG. 29 shows a modification of this embodiment, in which a plurality of slits 11c are arranged when the blade surface slits 11a cannot be arranged alone due to problems such as the strength of the stationary blade. According to such a configuration, each slit 11
As shown in FIG. 29, c is in a staggered arrangement, the slit width 11b arranged at the blowout portion radial direction center 4d is maximized, and the position of each slit 11c is decreased toward the blade root side and the tip side. By setting, it is possible to obtain the same effect as in the case of using a single slit.

Embodiment 6 (FIGS. 30 and 31) In this embodiment, the gas turbine stationary blade 1 is arranged immediately before the final stage moving blade 2a.

In this embodiment, for example, the stationary blade 1 described in the third embodiment is applied, but the stationary blade 1 having the structure described in other embodiments may be applied.

With this arrangement, the internal cooling of the final stage rotor blade 2a becomes unnecessary, and the temperature of the gas turbine rises and the temperature of the gas turbine is increased without increasing the efficiency due to the cooling air being ineffective as exhaust gas. Capacity can be increased at the same time.

[0068]

As described in detail in the above embodiments, according to the present invention, when the rotor blade disposed immediately behind is thin and twisted and it is difficult to cool the inside, the rotor blade of the last stage rotor blade is Even when there is a significant loss in thermal efficiency of the gas turbine due to internal cooling, the temperature of the mainstream gas flowing into the blade is effectively controlled by the low-temperature air mixing that blows out from the stationary blade, and the internal cooling of the blade, which has a large cycle disadvantage, is greatly reduced. It is possible to increase the turbine inlet temperature and increase the capacity at the same time without involving the above.

[Brief description of drawings]

FIG. 1 is a paragraph configuration diagram showing a first embodiment of a gas turbine stationary blade according to the present invention.

FIG. 2 is a sectional view taken along line AA of FIG.

FIG. 3 is a sectional view taken along line BB of FIG. 2;

FIG. 4 is a right side view of FIG.

5 is a cross-sectional view showing a modification of the first embodiment and corresponding to FIG.

6 is a right side view of FIG.

7 shows another modified example of the first embodiment, and FIG.
Sectional drawing corresponding to.

8 is a right side view of FIG. 7.

FIG. 9 is an explanatory view of the operation of the first embodiment.

FIG. 10 is a paragraph configuration diagram showing a second embodiment of a gas turbine stationary blade according to the present invention.

FIG. 11 is a sectional view taken along line CC of FIG. 10;

12 is a cross-sectional view taken along the line DD of FIG.

13 is a right side view of FIG.

FIG. 14 shows a modified example of the second embodiment, and FIG.
Figure corresponding to.

FIG. 15 is a right side view of FIG.

FIG. 16 is a view showing another modification of the second embodiment and is a view corresponding to FIG. 12;

FIG. 17 is a right side view of FIG. 16.

FIG. 18 is an operation explanatory view of the second embodiment.

FIG. 19 is an operation explanatory view of the second embodiment.

FIG. 20 is a paragraph configuration diagram showing a third embodiment of a gas turbine stationary blade according to the present invention.

21 is a cross-sectional view taken along the line EE of FIG.

FIG. 22 is a paragraph configuration diagram showing a fourth embodiment of a gas turbine stationary blade according to the present invention.

23 is a cross-sectional view taken along the line FF of FIG.

FIG. 24 is a view on arrow G in FIG. 23.

FIG. 25 is a view showing a modified example of the fourth embodiment.

FIG. 26 is a paragraph configuration diagram showing a fifth embodiment of a gas turbine stationary blade according to the present invention.

27 is a cross-sectional view taken along the line HH of FIG.

FIG. 28 is a view on arrow I of FIG. 27.

FIG. 29 is a view showing a modified example of the fifth embodiment.

FIG. 30 is a paragraph configuration diagram showing a sixth embodiment of a gas turbine stationary blade according to the present invention.

31 is a cross-sectional view taken along the line JJ of FIG.

FIG. 32 is a paragraph configuration diagram showing a conventional example.

FIG. 33 is a sectional view taken along line KK of FIG. 32.

FIG. 34 is an operation explanatory view showing a conventional example.

[Explanation of symbols]

 1 Gas Turbine Blade 2 Gas Turbine Blade 2a Gas Turbine Final Stage Blade 3 Hollow Blade Inner Hollow Portion 4a Trailing Edge Slit 4b Slit Width 4c Hole Channel 6a Rib 6b Columnar Structure 7a to 7e Flow Control Width 8 Curved Trailing Edge 9 straight trailing edge 11a blade surface slit 11b slit width 11c slit group

Claims (5)

[Claims] 1. A gas turbine stationary blade in which a hollow portion is provided inside a stationary blade, and air having a temperature equal to or lower than the mainstream gas is blown out of the stationary blade to mix with the mainstream gas. The blowout passage for blowing out air is directed to the moving blade located immediately after the stationary blade, and the air blown out from the blowout passage is set to lower the temperature of the mainstream gas flowing into the moving blade. A gas turbine stationary blade characterized by the above. 2. The gas turbine stationary blade according to claim 1, wherein the blowout passage is arranged at a position of 25% to 75% in length ratio along the radial direction from the tip side of the stationary blade outlet portion, or the same. Divide into a plurality in the arrangement, or the blowout flow path,
A gas turbine stationary blade having an oblique flow path for concentrating blown air at a radial position where the temperature of the mainstream gas at the blade inlet needs to be lowered. 3. The gas turbine stationary blade according to claim 1, wherein the blowout flow passage is arranged at a trailing edge of the stationary blade, and the blowout flow passage portion at the trailing edge of the stationary blade is projected toward the downstream side of the mainstream gas. A gas turbine vane characterized by 4. The gas turbine stationary blade according to claim 1, wherein the blowout flow passage is arranged on a side surface portion of the stationary vane, and the flow passage area is changed in a radial direction of the stationary vane, whereby the blowout air flow rate is increased. A gas turbine vane characterized by having a radial distribution set. 5. The gas turbine stationary blade according to claim 1, wherein the stationary blade having the blow-out passage is arranged immediately before the final stage moving blade.