JPH0828205A - Stationary blade of gas turbine - Google Patents

Abstract

PURPOSE:To provide the stationary blade of a gas turbine, which is suitable for a coolant recovery type gas turbine being the stationary blade of a turbine which has long-term high reliability. CONSTITUTION:A flange 6 for forming a cooling flow path and a protrusion 7 for accelerating the turbulent flow of a coolant to enhance a cooling effect are provided in an insert 3, thereby making it possible to make the wall thickness of a blade main body 2 nearly uniform to obtain a high cooling effect. Therefore, in the cooling structure of the stationary blade 1 of a turbine, the temperature difference and the temperature unevenness of a blade can be reduced by making the wall thickness of the blade main body 2 nearly uniform.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine vane of a gas turbine, and more particularly to a turbine vane of a gas turbine having an improved cooling structure.

[0002]

2. Description of the Related Art A conventional structure of a turbine vane of a gas turbine is disclosed in Japanese Patent Laid-Open No. 4-179802 and Japanese Patent Laid-Open No. 4-259.
It is described in Japanese Patent No. 603. A cooling structure of a turbine vane of a gas turbine having a relatively low working gas temperature processes a plurality of holes in a blade body, and supplies a cooling medium to the holes to cool them.

However, a gas turbine having a high turbine working gas temperature cannot provide sufficient cooling performance. The turbine vane is composed of a blade body and an insert. The blade main body has an internal cavity, a plurality of flanges in the blade span direction are provided on a wall surface of the internal cavity, and a plurality of protrusions are provided on a surface wall between the flange and the flange. A cooling medium is supplied to a plurality of flow paths formed by the blade body inner cavity wall, the insert wall, and the collar to cool the turbine stationary blade.

[0004]

However, even with such a conventional structure, there has been a drawback of lacking reliability in long-term operation of the gas turbine. That is, in the conventional cooling structure for a gas turbine stationary blade, the wall thickness of the blade main body continuously changes irregularities in the blade cord direction due to the formation of the collar, so that temperature difference and temperature unevenness occur in the blade main body. As a result, the blade was cracked and damaged during long-term use, and the turbine performance deteriorated due to the accumulated deformation of the blade due to temperature unevenness, and further, the cooling performance deteriorated. That is, it is considered that the conventional cooling structure lacks long-term reliability of the gas turbine.

SUMMARY OF THE INVENTION It is an object of the present invention to provide a turbine stator vane having high long-term reliability by solving the conventional structural defects, and also a turbine stator vane suitable for a cooling medium recovery type gas turbine. As a result, the efficiency of the gas turbine and the combined power generation plant using this gas turbine stationary blade is improved.

[0006]

A drawback of the conventional gas turbine stationary blade is that the wall thickness of the blade main body is changed by continuously repeating unevenness in the blade cord direction, resulting in a large temperature difference and temperature unevenness of the blade main body. It is due to that.

According to the present invention, the insert is provided with a plurality of collars which are integrally formed with the insert and extend in the blade span direction at intervals in the blade cord direction. A plurality of jetty walls are provided with a gap in the direction, and such an insert is inserted into the hollow blade.

The cooling medium is supplied to the flow passage formed by the inner wall of the blade main body and the insert, and effectively cools the blade main body by the turbulent flow promoting effect of the cooling medium by the jetty provided on the surface of the insert. The blade body wall thickness can be made substantially uniform while maintaining the cooling effect of the blade body, thus achieving the object of the invention.

Here, the brim or jetty does not necessarily have to be integrated with the insert, and may be separately formed by welding or the like. All of them are formed on the outer surface of the insert with a predetermined interval, and are not formed on the inner wall of the blade body.

Further, the brim or jetty is formed at a predetermined interval. In particular, since the heat flux on each blade surface is different depending on the degree of collision of the combustion gas with the blade, the brim or jetty is formed. It is necessary to consider the pitch to play.
For example, since the heat flux increases in the order of the front part of the vane, the front part of the back side, and the back part of the ventral side, it is necessary to increase the pitch of this part.

Further, the heat transfer coefficient of the cooling surface can be improved by considering the shape of the jetty. For example, it is advisable to divide the jetty formed between the tsuba and the tsuba at the substantially central portion thereof so as to be formed obliquely to the direction in which the cooling medium flows.

Therefore, the gas turbine vane of the present invention has a blade main body having a cavity inside, an insert installed in the cavity, and a gap formed by an inner cavity wall of the blade main body and an outer surface of the insert. A cooling medium is supplied and has ribs formed on the outer surface of the insert to resist the flow of the cooling medium.

According to the present invention, by adopting such a body-flow cooling structure, for example, the blade main body is formed with a substantially uniform thickness in the blade head portion, and the temperature difference on the blade surface is small, The distribution is almost uniform.

Further, the present invention is characterized in that a plurality of jetty walls are provided on the outer surface of the insert in the blade span direction to guide the cooling medium supplied to the gap from one end to the other end in the blade span direction. To do.

The present invention is a system having a so-called closed cooling structure using air or steam, in which the medium whose stator vanes have been cooled is recovered in a combustor or a steam turbine for reuse. Therefore, the recovery path of the cooling medium is important, and efficient recovery can be achieved by guiding the cooling medium from one end to the other end in the blade span direction.

The gas turbine vane of the present invention has a plurality of flanges extending in the blade span direction on the outer surface of the insert,
It is characterized in that a plurality of jetties are provided in the blade span direction between the brims. Here, the blade span direction is the blade length direction and the radial direction. Further, by partitioning the gap with the collar, the flow velocity of the cooling medium can be increased and the cooling efficiency can be improved.

The relationship between the height of the tsuba and the height of the jetty is
It is preferable that the height of the jetty is lower than the height of the tsuba. As a result, an appropriate flow path for the cooling medium can be secured.

As a method of collecting the cooling medium, the cooling medium supplied to the gap from one end in the blade span direction is
It can also be recovered via the air flow path inside the insert, the cooling medium supplied to a part of the gap from one end in the blade span direction is introduced into the remaining gap via the other end, and the cooling medium It can also be discharged from the supply side to the outside of the blade and collected.

Further, the gas turbine vane of the present invention has a blade body having a cavity inside, an insert installed in the cavity, a gap formed by an inner cavity wall of the blade body and an outer surface of the insert. A cooling medium is supplied to the blade, and the temperature distribution of the blade body is substantially uniform.

A plurality of these jetties are formed at intervals in the blade span direction, and the number thereof is appropriately selected in consideration of turbine specifications and the like. Also, the insert formed on the outer surface of the insert is installed in the cavity of the wing body,
This cavity may be divided into a plurality of parts.

Further, the gas turbine of the present invention is driven by a compressor for sucking and compressing air, a combustor for combusting the air and fuel compressed by the compressor, and combustion gas from the combustor, A turbine having a paragraph structure of moving blades and stationary blades. The insert formed in the vane of the turbine has ribs that promote turbulent flow in the cooling medium.

Further, in the gas turbine of the present invention, the ribs formed in the insert inside the stationary blade cause the air from the compressor to turbulently flow, cool the stationary blade, and then use the air for the combustor. It is characterized by collecting as.

Further, in particular, in the gas turbine of the present invention, a blade body having a cavity inside, an insert installed in the cavity, a gap formed by an inner cavity wall of the blade body and an outer surface of the insert. A turbine in which a gas turbine stationary blade for supplying a cooling medium to the inside, a blade main body having a cavity inside, and a gas turbine moving blade for supplying the cooling medium inside the cavity are combined, wherein the stationary blade is outside the insert. The moving blade has a rib formed on a side surface, and the moving blade has a rib formed on an inner surface of the blade body. By combining the moving blades having the ribs with the stationary blades in this way, it is possible to achieve a gas turbine with even higher cooling efficiency. In particular, the rib shape of the moving blade is divided on the cooling surface at almost the center thereof, and is formed into a so-called V-shape obliquely with respect to the direction in which the cooling medium flows. It is possible to improve the thermal efficiency, which is expressed as an electric output obtained from the above, to about 33 to 35%. Input fuel is usually 10,000 to 1100
Use 0 kcal / kg. In addition, 1kW is 860
Convert to kcal.

Further, the combined cycle plant of the present invention is driven by a compressor for sucking and compressing air, a combustor for combusting the air and fuel compressed by the compressor, and a combustion gas from the combustor. A gas turbine including a turbine having a paragraph structure of moving blades and stationary blades;
The boiler includes a boiler that exchanges heat with exhaust gas from the turbine to generate steam, and a steam turbine that is driven by the steam generated in the boiler. Then, the ribs formed in the insert inside the vane are used to turbulently flow the steam from the boiler to cool the vane, and then the steam is recovered as steam to be used in the steam turbine.

As described above, by recovering and reusing the air, it is possible to increase the combustion fuel amount as the combustion air amount increases. As a result, the output can be improved and the efficiency of the gas turbine can be improved. Further, if the operation is performed with the output and efficiency kept almost constant as compared with the conventional one, the air amount can be increased, so that the low N
Ox can be achieved.

[0026]

By doing so, the temperature difference and temperature unevenness of the blade main body can be reduced, and by eliminating the deformation of the blade, the conventional cracking can be prevented. That is, this structure can provide a turbine vane with high long-term reliability.

In a combined power generation plant having a steam turbine system, steam is used as a cooling medium for turbine blades. In that case, since the temperature of the mainstream gas is lowered when the cooling steam having a large specific heat is released into the mainstream gas, it is preferable to collect the steam outside the gas turbine and use it as a part of the working steam of the steam turbine.

The gas turbine system is a system in which high pressure air compressed by a compressor is used as an oxidant to combust a fuel, and the high temperature and high pressure gas generated drives a turbine to convert it into energy such as electric power. It is desirable to obtain as much electric energy as possible for the consumed fuel, that is, it is expected that the performance of the gas turbine will be improved, and one of the means is to increase the working gas temperature and pressure.

On the other hand, a method of improving the total energy conversion efficiency including the gas turbine and the steam turbine is also conceivable by increasing the temperature of the gas turbine working gas and using a combined power generation plant with a steam turbine system using the high-temperature exhaust gas.

The working gas temperature of a gas turbine is limited by the ability of the turbine blade material to withstand thermal stress primarily due to the gas temperature. In order to satisfy the service temperature of the turbine blade when increasing the working gas temperature, a method of forming a passage inside the turbine blade and passing cooling air therethrough to cool the turbine blade from the inside can be considered.

Since such cooling air uses a part of the air extracted from the compressor, the consumption of a large amount of cooling air causes a decrease in gas turbine efficiency, and it is important to cool efficiently with less air.

On the other hand, there is also a demand for reducing NOx in the gas turbine exhaust gas, and a lean mixed combustion technique of a gas turbine combustor is considered as one of means for reducing NOx.

In order to solve these problems at the same time,
A method of recovering the air that has cooled the turbine blades to a combustor and utilizing it as a part of the combustion air is conceivable, and is due to the present invention. That is, by utilizing the cooling air of the turbine blades as the combustion air, it is possible to recover the turbine cooling heat, further increase the combustion air, and perform leaner combustion to reduce NOx. If necessary, more fuel can be added to increase gas turbine output.
The main reason for adopting such a structure is to form a cooling flow path in which a jetty for promoting cooling heat transfer is arranged near the blade surface in order to effectively cool the turbine blade.

[0034]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention will be described below with reference to FIGS.
3 and FIG.

FIG. 1 is a cross-sectional view of a gas turbine stationary blade 1 embodying the present invention, and FIG. 2 is a sectional view taken along the line AA of FIG. 1, that is, a vertical sectional view of the gas turbine stationary blade 1. 1 and 2
2 is a turbine vane main body having at least one internal cavity, and 3 is an insert inserted in the internal cavity of the vane main body 2. FIG. 3 is a partial perspective view showing the outer structure of the insert 3 for easy understanding.

The embodiment of the present invention will be described in more detail. 1, 2 and 3, reference numeral 2 denotes a turbine vane main body having at least one cavity and, if necessary, a plurality of cavities by the partition wall 4. Inserts 3 are inserted in such cavities to improve the flow velocity and reduce the cooling air. Although both the blade body and the insert are made of a chrome-based material, the blade body material is required to have higher heat resistance. For example, the blade body has a temperature of about 900 ° C, while the insert has a temperature of about 600 ° C. The outer wall surface of the insert 3 is provided with a plurality of collars 6 (partitioning ribs) extending integrally in the blade span direction in the blade spanwise direction with a structure integrated with the insert, and is integrated with the insert in the gap with the collar 6. Plural jetties 7 (turbulent flow promoting ribs) are provided at intervals in the blade span direction of the structure. The height of the collar 6 and the height of the jetty 7 in the insert 3 need to be lower than the height of the jetty 7, but their height, installation gap, and spacing are determined by the cooling target of the turbine. It is a thing. 24 is 18
, 25 has the same function as 19 and 26 has substantially the same function.

Thus, in the turbine vane 1, the cooling medium passage 12 is formed in the blade span direction by the blade main body inner wall 10, the insert outer surface 11, and the collar 6. One of the cooling medium flow passages 12 communicates with a cooling medium reservoir 14 provided on the upper vane end wall 13 and the other one communicates with a cooling medium reservoir 16 of the lower end wall 15.

A trailing edge cooling passage 27 is formed in the trailing edge portion of the blade having a small blade thickness, the trailing edge cooling passage 27 communicating with the cavity communicating with the upper cooling medium reservoir 14 and the lower cooling medium reservoir 16, and the passage for promoting heat transfer. A pin fin 28 is provided for this purpose.

The operation of the present invention will be described. The cooling medium (cooling medium supply flow 17) supplied from the upper portion of the vane is injected from the impingement hole 19 of the upper impingement cover 18,
The upper end wall 13 is cooled and supplied to the cooling medium reservoir 14, a part of which is guided to the cooling medium flow path 12,
In the process of passing through the cooling medium passage 12, the turbine stationary blade 1 is cooled by the inner wall 10 of the blade body.

Still another part is supplied from the upper cooling medium reservoir 14 to the blade trailing edge passage to cool the blade trailing edge portion. The cooling medium that has contributed to the cooling of the stationary vanes is collected in the cooling medium reservoir 16 of the lower end wall 15, and is further collected from the outlet 21 to the outside of the blade (cooling medium collecting flow 22). The cooling medium collected to the outside of the blade has different usage forms depending on the system configuration of the gas turbine and the purpose of installation, and the cooling medium applied to the present invention is not particularly limited. For example, air is used as the cooling medium. In this case, the gas turbine exhaust gas can be supplied to the gas turbine combustor and used as combustion air to reduce the NOx of the gas turbine exhaust gas or contribute to the increase of the gas turbine output. Further, when used in a combined power plant gas turbine, part of the steam from the steam turbine system system is used as a cooling medium, and the recovered steam is returned to the steam turbine system, which can contribute to improvement of the combined power plant performance.

One of the features of the present invention is that a jetty, which is conventionally provided on the inner wall surface of the turbine vane, for the purpose of promoting turbulent flow of the cooling medium is provided on the insert side. That is,
The purpose is to cool a smooth surface facing the surface provided with the turbulence promoting body in the cooling medium flow path. The effect of promoting heat transfer on the surface opposite to the surface provided with the turbulence promoter was confirmed by model experiments. The model experiment is 10 mm on one side and 5 mm on the other side.
With a rectangular flow path of 10 mm long and one of the two opposing surfaces is a non-heating surface, the height of which is 0.7 mm and the width is 0.7 mm.
Of the cooling medium flow is provided, and the other smooth surface is used as a heating surface (simulating a smooth blade cooling surface facing the insert provided with the turbulence promoting jetty of the present invention), and the cooling medium is air. Was experimented with. FIG. 4 is a characteristic diagram showing experimental results. In FIG. 4, the horizontal axis represents the dimensionless Reynolds number Re representing the flow state of the cooling medium, and the vertical axis represents the dimensionless Nusselt number Nu representing the heat transfer characteristics.

[0042]

[Equation 1]

D: Equivalent diameter of cooling medium flow path ν: Cooling medium flow velocity α: Heat transfer coefficient ν: Dynamic coefficient of cooling medium λ: Thermal conductivity of cooling medium On a smooth surface facing the turbulence promoting jetty surface In addition, the four opposing surfaces exhibit heat transfer characteristics about twice that of a smooth smooth flow path, and the turbulent flow effect of the turbulence-promoting jetty on the cooling medium affects the opposing smooth surfaces to improve the heat transfer characteristics. It shows that the improvement effect appears. The effect varies depending on the shape of the turbulent flow accelerating jetty, but a heat transfer accelerating effect commensurate with the turbulent flow accelerating effect of the jetty appears on the opposite smooth surface. That is, by forming a jetty, a secondary flow is generated to improve the heat transfer coefficient of the cooling surface.

The gas turbine vane of the present invention constructed as described above has the following effects. In the structure of the turbine vane according to the present invention, the turbulent flow promoting jetty for obtaining a high cooling effect and the brim for forming the cooling passage are provided on the insert side, and the blade main body wall thickness is made substantially uniform. The difference in temperature between the blades and the temperature unevenness can be reduced, and by eliminating the deformation of the blade, it is possible to prevent the occurrence of crack damage in the blade as in the conventional case. That is, it is possible to provide a cooling medium recovery type gas turbine stationary blade having high long-term reliability while maintaining the same blade cooling performance as the conventional one.

That is, the present invention achieves a turbine blade that is resistant to thermal stress and highly reliable by forming irregularities on the insert without forming irregularities on the blade body.

The basic part of the present invention has been described above. Hereinafter, another embodiment of the present invention will be described with reference to FIGS. The cooling medium recovery system path must be appropriate for the system configuration and structure of the gas turbine. The following application examples show examples suitable for various systems.

The embodiment of FIG. 1 shows the structure in which the cooling medium is supplied to the upper end wall and recovered from the lower end wall. However, depending on the gas turbine structure, the cooling medium may be recovered from the same direction as the supply side. There are good cases.

FIGS. 5 and 6 show a second embodiment of the present invention for such a case. FIG. 5 is a cross-sectional view of a gas turbine stationary blade according to another embodiment of the present invention, and FIG. 6 is a cross-sectional view taken along the line AA of FIG. 5, that is, a vertical sectional view of the gas turbine stationary blade. In FIG. 5 and FIG. 6, the first
The same parts as those in the embodiment of FIG. In FIGS. 5 and 6, reference numeral 30 denotes an internal space 31 inserted into the stationary blade main body 2.
The inner wall structure of the blade body 2, the outer wall structure of the insert 30, and the cooling medium flow passage 12 are the same as those of the first embodiment. Upper end wall 1
The cooling medium supplied to the cooling medium reservoir 14 of No. 3 is guided to the cooling medium passage 12 and cools the turbine vane. The cooling medium that has cooled the stationary vanes is collected in the cooling medium reservoir 16 of the lower end wall 15, passes through the internal space 31 of the insert 30, and is collected outside the vanes from the discharge pipe 32.

Although the action and effect of blade cooling in this embodiment are the same as those in the above-described example, it is possible to provide a structure in which the supply and recovery of the cooling medium to the turbine vanes are suitable in the same direction.

FIG. 7 is a vertical cross-sectional view showing another embodiment of a gas turbine stationary blade in which the present invention is applied to a stationary blade in which cooling medium supply and recovery are in the same direction. 1
Same as). The same parts as those in FIG. 2 and FIG. 7 are denoted by the same reference numerals. The cooling medium reservoir 16 of the lower end wall connects the blade front cooling medium channel and the blade rear cooling medium channel, and further the blade rear cooling medium. The cooling medium discharge pipe 33 is provided at the upper end of the flow path.
Connected to. Then, the cooling medium reservoir 1 on the upper end wall
The cooling medium supplied to No. 4 is guided to the blade front cooling medium passage to cool the vane front portion, is collected in the cooling medium reservoir 16 of the lower end wall 15, and is further introduced to the blade rear cooling medium passage. After being blown, the rear portion of the vane is cooled and collected outside the vane through the discharge pipe 33. Although illustration is omitted, as a modification of the present embodiment, a system path in which cooling air is supplied to the blade rear side and is collected from the blade front is also conceivable.

In the high-pressure gas turbine, in order to obtain mechanical strength of the blade, a method of dividing the inside of the blade by a plurality of partition walls to subdivide the cooling air flow path is adopted. 8 and 9 show an embodiment in which the present invention is applied to such a gas turbine stationary blade. 8 shows a sectional view of a gas turbine vane, and FIG. 9 shows a sectional view taken along the line AA in FIG. FIG.
And in FIG. 9, the same parts as those in the above-mentioned embodiment are shown by the same numbers, 35 is a turbine blade main body, 36 is a partition wall, 3
Reference numeral 7 is an insert, 38 is a cooling medium passage formed by the blade inner wall, partition wall and insert, and 39 is a jetty provided on the outer side surface of the insert 37 in an integrated structure with the insert.

The cooling air supplied to the cooling air reservoir 15 from the upper side of the turbine vane is the inner wall of the blade body and the insert 37.
And the cooling medium passage 38 formed by the blade partition wall 36
When passing through the blade, the blade body is cooled and recovered outside the blade via the cooling medium reservoir 16 and the cooling medium discharge pipe 21 provided at the lower end of the blade.

In the other embodiments described above, the inner wall structure of the blade body, the outer surface structure of the insert, and the cooling medium flow path are basically the same as those of the first embodiment, and the blade cooling action, The effect is the same as the above example. That is, in the structure of the turbine vane according to this embodiment, the temperature difference and temperature unevenness of the blade can be reduced by making the thickness of the blade main body wall substantially uniform. The occurrence of crack damage can be prevented.

Therefore, according to the present embodiment, it is possible to provide a cooling medium recovery type gas turbine stationary blade having a long-term reliability while maintaining the cooling promotion regardless of the system configuration, scale and structure of any gas turbine. .

In the embodiment of the present invention, the shape of the turbulent flow promoting jetty of the insert is described as a shape perpendicular to the flow direction of the cooling medium as shown in FIG. The shape of these jetties may be an inclined shape, a mountain shape, a pin fin shape, or the like, and can be a structure more suitable for the design concept of the gas turbine stationary blade, and does not limit the present invention.

Further, in the text, an example in which air is used as the cooling medium has been described, but it goes without saying that other cooling medium such as steam may be used, and the kind of the cooling medium is not limited.

In addition to the above description, the turbine vane has various parts that require cooling. For example, as shown in FIG. 2, the upper and lower end walls, the blade trailing edge having a relatively small blade thickness, and the like. For cooling these parts, it is possible to directly implement the conventional method, for example, the impingement cooling structure, the film cooling structure, the pin fin convection cooling structure, the turbulent flow accelerating jetty cooling structure, etc. shown in the text. Does not limit.

The blade body and insert of the present invention can be manufactured by precision casting, electric discharge machining, machining or the like.

The usage method and effects of the gas turbine stationary blade of the present invention will be described. FIG. 10 is an example showing a gas turbine 45 equipped with the gas turbine stationary blade 1 of the present invention. FIG.
In 0, 46 is a compressor, 47 is a compressed air chamber, 48 is a combustor, 49 is a turbine, 50 is a boost compressor, 51 is a cooling air recovery passage, and 52 is a generator. The high-pressure air compressed by the compressor 46 is introduced into the compressed air chamber 47 and further supplied to the combustor 48 to burn the fuel and generate high-temperature high-pressure gas. The high-temperature high-pressure gas drives the turbine 49 to rotate, the power of which drives the compressor 46 and the generator 52 to obtain an electric output.

The turbine vane 1 of the present invention is mounted as the first stage vane of the turbine 49. A part of the compressed air is extracted from the compressed air chamber 47, further boosted by the boost compressor 50 and supplied to the turbine stationary blade 1 to cool the turbine stationary blade. The cooling air is recovered from the lower end of the blade to the outside of the blade, is guided to the compressed air chamber 47 through the cooling air recovery passage 51, and is used as the combustion air.

Therefore, the gas turbine 45 equipped with the gas turbine stationary blade 1 of the present invention secures the reliability of the gas turbine itself by the turbine stationary blade having high long-term reliability as described above, and further burns the cooling air. By collecting as air, it is possible to provide a gas turbine that meets the requirements for the energy conversion device described at the beginning, such as improving the output and thermal efficiency of the gas turbine or reducing the NOx of exhaust gas.

The gas turbine 45 is replaced by the steam turbine 5
The configuration of the combined power generation plant 53 in combination with No. 7 is shown in FIG. In FIG. 11, reference numeral 56 is an exhaust heat recovery boiler that uses the exhaust gas of the gas turbine to generate steam, and 57 is a steam turbine that is driven by such steam. Reference numeral 54 is a condenser, and 55 is a water supply pump for supplying condensed water to the exhaust heat recovery boiler 56. In such a combined power generation plant, the relatively high temperature exhaust gas of the gas turbine is guided to the exhaust heat recovery boiler 56, and the steam turbine 57 is driven by the generated steam.
5 and the output of the steam turbine 57 increase the heat utilization efficiency with respect to the input fuel. By combining the gas turbine 45 equipped with the turbine vane 1 of the present invention, it is possible to provide a combined power generation plant having high long-term reliability, high thermal efficiency, and low NOx in exhaust gas similarly to the above. .

Further, in a combined power generation plant, a method of utilizing steam of a steam turbine system for cooling turbine blades can be considered. FIG. 12 shows a plant configuration diagram when steam is used as the turbine cooling medium of the combined power generation plant 59 incorporating the gas turbine 45 equipped with the turbine vane 1 of the present invention. A part of the steam generated in the exhaust heat recovery boiler 56 is guided to the turbine stationary blade 1 of the present invention of the gas turbine 45, and after cooling the turbine stationary blade, it is recovered and supplied to the steam turbine. Therefore, in the combined power generation plant of the present invention, in addition to the above-mentioned effects, the effect that the thermal energy obtained by cooling the turbine stationary blades can be recovered as power by the steam turbine is further obtained.

That is, an object of the present invention is to provide a turbine vane having high long-term reliability, and also a turbine vane suitable for a cooling medium recovery type gas turbine. It is intended to improve the efficiency of the gas turbine and power plant used, and to reduce the temperature difference and temperature unevenness of the blade body, which were the drawbacks of conventional gas turbine stationary blades, to reduce the unevenness of the wall thickness of the blade body in the blade cord direction. Solve it,
Eliminates continuous repeated changes. It is possible to make the blade body wall thickness almost uniform by installing a ridge to form a cooling flow path and a jetty for promoting turbulent flow of the cooling medium and improving the cooling effect on the insert, and a high cooling effect In addition to the above, the object of the invention was achieved. The cooling structure of the turbine vane can reduce the temperature difference and temperature unevenness of the blade by making the thickness of the blade body wall almost uniform. By eliminating the deformation of the blade, the conventional crack damage of the blade occurs. Can be prevented. Therefore, according to the present invention, it is possible to provide a long-term reliable cooling medium recovery type gas turbine stationary blade, and thus to realize a high temperature and high efficiency gas turbine and a highly efficient power generation plant using the gas turbine. Can contribute. The effect of promoting heat transfer on the smooth surfaces facing each other when the turbulent flow promoting jetty is attached to the insert side is
It was confirmed by a model experiment.

[0065]

As described above, the cooling structure for a turbine vane according to the present invention can obtain a high blade cooling performance, can reduce the temperature difference and temperature unevenness of the blade, and can eliminate the deformation of the blade in the conventional case. It is possible to prevent the occurrence of such crack damage to the blade.

Therefore, according to the present invention, it is possible to provide a cooling medium recovery type gas turbine stationary blade having high cooling performance and high reliability, which results in high temperature and high efficiency gas turbine and high efficiency utilizing the gas turbine. It can contribute to the realization of a power plant.

[Brief description of drawings]

FIG. 1 is a cross-sectional structural view of a gas turbine stationary blade.

FIG. 2 is a vertical sectional structural view of a gas turbine stationary blade (A- in FIG. 1).
(A sectional view).

FIG. 3 is a partial perspective view of the insert 3.

FIG. 4 is a diagram showing a result of a heat transfer characteristic experiment.

FIG. 5 is a cross-sectional structural view of a gas turbine stationary blade.

FIG. 6 is a vertical sectional structural view of a gas turbine stationary blade (A- in FIG. 5).
(A sectional view).

FIG. 7 is a vertical cross-sectional structural diagram of a gas turbine stationary blade.

FIG. 8 is a cross-sectional structural diagram of a gas turbine stationary blade.

FIG. 9 is a vertical sectional structural view of a gas turbine stationary blade (A- in FIG. 8).
(A sectional view).

FIG. 10 is a gas turbine.

FIG. 11 is a combined power generation plant.

FIG. 12 is a combined power generation plant.

[Explanation of symbols]

1 ... Gas turbine stationary blade, 2 ... Blade body, 3 ... Insert,
4 ... Partition wall, 6 ... Tsuba, 7 ... Jetty, 10 ... Stator vane body inner wall surface, 11 ... Insert outer wall surface, 12 ... Cooling medium flow path,
13 ... Upper end wall, 14 ... Cooling medium reservoir, 15 ...
Lower end wall, 16 ... Cooling medium reservoir, 17 ... Cooling medium supply flow, 18 ... Upper impingement cover, 19 ... Impingement hole, 21 ... Cooling medium discharge pipe, 22 ... Cooling medium recovery flow, 24 ... Lower impingement cover, 25 ... Impingement holes, 26 ... Cooling medium supply flow, 27 ... Trailing edge cooling flow path.

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Manabu Matsumoto 502 Jinritsucho, Tsuchiura-shi, Ibaraki Hiritsu Manufacturing Co., Ltd.Mechanical Research Institute (72) Nobuaki Kizuka 502 Jinritsucho, Tsuchiura-shi, Ibaraki Hiritsu Manufacturing Co., Ltd. Inside the Mechanical Research Laboratory (72) Inventor Shinichi Higuchi 502 Jinritsucho, Tsuchiura City, Ibaraki Prefecture Hiritsu Mfg. Co., Ltd. Inside the Mechanical Research Laboratory (72) Inventor Isao Takehara 3-1-1 Sachimachi Hitachi City, Ibaraki Hitachi Ltd. Hitachi factory

Claims (11)

[Claims] 1. A gas turbine static supply for supplying a cooling medium to a gap formed by a blade body having a cavity inside, an insert installed in the cavity, an inner cavity wall of the blade body and an outer surface of the insert. In the blade, a gas turbine stationary blade having ribs formed on an outer side surface of the insert so as to provide resistance to the flow of the cooling medium. 2. A gas turbine static supply for supplying a cooling medium to a gap formed by a blade body having a cavity inside, an insert installed in the cavity, and an inner cavity wall of the blade body and an outer surface of the insert. In the blade, a plurality of jetty walls are provided in the blade span direction on the outer surface of the insert to guide the cooling medium supplied to the gap from one end to the other end of the blade span direction. . 3. A gas turbine static supply for supplying a cooling medium to a gap formed by a blade body having a cavity inside, an insert installed in the cavity, an inner cavity wall of the blade body and an outer surface of the insert. In the blade, a gas turbine having a plurality of flanges extending in a blade span direction on an outer surface of the insert, and providing a plurality of jetties in the blade span direction between the flanges and the collar. Shizuka. 4. The gas turbine stationary blade according to claim 3, wherein the height of the jetty is lower than the height of the flange. 5. A cooling medium in a gap formed by a blade main body having a cavity inside, an insert installed in the cavity and having an air flow path inside, and a gap formed by an inner cavity wall of the blade main body and an outer surface of the insert. In the gas turbine stationary blade for supplying, a plurality of flanges extending in the blade span direction on the outer surface of the insert, between the collar and the collar, a plurality of jetty is provided in the blade span direction, A gas turbine stationary blade, wherein the cooling medium supplied from one end in the blade span direction to the gap is recovered via an air flow path inside the insert. 6. A blade body having a plurality of cavities inside, inserts respectively installed in the plurality of cavities, a cooling medium in a gap formed by an inner cavity wall of the blade body and an outer surface of the insert. In the gas turbine stationary blade to be supplied, the outer surface of the insert has a plurality of flanges extending in the blade span direction, and between the flange and the collar, a predetermined interval in the blade span direction on the outer surface of the insert. By providing a plurality of jetties, the cooling medium supplied from one end of the blade span direction to part of the gap is introduced into the remaining gap via the other end, and discharged from the supply side of the cooling medium to the outside of the blade. A gas turbine stationary blade characterized by: 7. A gas turbine static supply for supplying a cooling medium to a gap formed by a blade body having a cavity inside, an insert installed in the cavity, an inner cavity wall of the blade body and an outer surface of the insert. In the blade, a gas turbine stationary blade, wherein the temperature distribution of the blade main body is substantially uniform. 8. A compressor for sucking and compressing air, and a combustor for burning the air compressed by the compressor and fuel.
In a gas turbine that is driven by the combustion gas from the combustor and that includes a turbine having a moving blade and a stationary blade, a turbulent flow is generated in a cooling medium in an insert formed in the stationary blade of the turbine. A gas turbine, characterized in that it has ribs that promote it. 9. A compressor for sucking and compressing air, and a combustor for burning the air compressed by the compressor and fuel.
A gas turbine, which is driven by combustion gas from the combustor and includes a turbine having a moving blade and a stationary blade, wherein a rib formed in an insert inside the stationary blade is used to remove air from the compressor. Turbulent flow to cool the stationary vanes and then recover the air as the air used in the combustor. 10. A gas turbine static supply for supplying a cooling medium to a gap formed by a blade body having a cavity inside, an insert installed in the cavity, an inner cavity wall of the blade body and an outer surface of the insert. In a gas turbine having a turbine in which a blade, a blade main body having a cavity inside, and a gas turbine blade for supplying a cooling medium into the cavity are combined, the stationary blade includes a rib formed on an outer surface of the insert. The gas turbine has a rib formed on the inner surface of the blade body. 11. A compressor for sucking in and compressing air, a combustor for combusting air and fuel compressed by the compressor, and a combustion blade driven by combustion gas from the combustor, the moving blade and the stationary blade. In a combined cycle plant including a gas turbine including a turbine having a paragraph structure, a boiler that exchanges heat with exhaust gas from the turbine to generate steam, and a steam turbine driven by the steam generated in the boiler A combined cycle plant, characterized in that steam generated from the boiler is turbulently flowed by a rib formed in an insert inside the stationary vane to cool the stationary vane and then recovered as steam to be used in the steam turbine.