JP2001349202A - Gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine capable of simplifying the constitution of a separating part of a closed cooling medium passage and an open cooling medium passage and capable of sufficiently preventing a leak of a refrigerant and supercooling of a blade part. SOLUTION: In this gas turbine having cooling medium flowing paths inside a turbine stationary blade 3 and formed so as to cool the stationary blade by making a cooling medium to flow to these cooling medium flowing paths, to partially recover the cooling medium after cooling the stationary blade and to blow off a part in main flow gas 20, the plural cooling medium flowing paths are arranged in the stationary blade 3, and at least one cooling medium flowing path in these cooling medium flowing paths cools the stationary blade by flow of the cooling medium supplied from an external part, and the cooling medium is recovered again after cooling, and the other cooling medium flowing path is formed so as to cool the stationary blade 3 by flow of the cooling medium 23 supplied from the external part, to blow off the partial cooling medium in the main flow gas 20 after cooling and to supply a cooling medium 23b of a residual part as a sealing medium to a rotary part arranged on the inner peripheral side of the stationary blade.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine, and more particularly to a compressor and a compressor, in which a fluid discharged from a compressor is cooled and pressurized by a cooler and a boost compressor, respectively. The present invention relates to a gas turbine formed so as to collect the refrigerant in a combustor.

[0002]

2. Description of the Related Art A conventional gas turbine of this type is configured to drive a turbine by adding fuel to a working fluid compressed by a compressor and burning the working fluid to obtain a high-temperature and high-pressure working fluid. I have. The rotational energy of the driven turbine is typically converted to electrical energy by a generator coupled to the turbine.

In recent years, great expectations have been placed on improving the efficiency of a combined cycle in which a gas turbine and a steam turbine are combined, and one of the means is to increase the temperature of the working fluid and increase the pressure ratio. .
In addition, by collecting the cooling medium in the gas turbine high-temperature section, which has been released into the mainstream gas together with the increase in temperature, for example, at the inlet of the combustor, thermal energy is effectively used to further improve efficiency. The development of gas turbines using a cooling system is also in progress.

In general, in the case of a gas turbine employing a closed cooling system on the premise of recovering a refrigerant, the stationary blades and the structure around the stationary blades must have improved sealing properties so that the closed cooling medium does not leak outside. . This seal configuration is significantly different from the open cooling type structure that discharges the refrigerant into the mainstream gas.

[0005] For example, in a structure in which a diaphragm is arranged between a disk rotor spacer on the inner peripheral side such as a second stage stationary blade, the rotating body is located on the inner peripheral side of the stationary blade for gas turbine operation. Mainstream gas for disc wheel,
In other words, since it is necessary to supply a sealing medium so that high-temperature gas does not enter, a supply path for an open cooling medium serving as a sealing medium is also required in the blade in addition to a cooling path using a closed cooling medium. And the open cooling passage intersect to form a complicated structure.

For example, Japanese Patent Application Laid-Open No. Hei 10-317908 discloses a structure in which a closed cooling passage in a blade has a bellows structure and an open air tube for absorbing thermal expansion is passed.

[0007]

The refrigerant supplied to the second stage stationary blade is a refrigerant which has been cooled and pressurized by a cooler and a boost compressor for a fluid discharged from a compressor, and a refrigerant discharged from the compressor or a compressor. There are two types of refrigerants: a refrigerant using a fluid extracted from the above, and the former is usually used as a closed cooling medium, and the latter is used as an open cooling medium.

After the cooling of the second stage stationary blades is completed, the former closed cooling medium is supplied to the combustor inlet through piping in the gas turbine casing, and finally joins the compressor discharge fluid. On the other hand, the latter open cooling medium cools a part of the stationary blade and is finally released into the mainstream gas.
In the case of this open cooling medium, a part of the open cooling medium is guided to a diaphragm arranged on the inner peripheral side of the stationary blade, and is used as a seal medium for wheel space. That is, the sealing medium serves to prevent the mainstream gas from entering the periphery of the diaphragm to increase the ambient temperature.

In order to maintain the supply pressure of the wheel space sealing medium, the flow area of the supply medium for the open cooling medium must have a certain large area to suppress the pressure loss in the flow path. At the same time, the wheel space seal medium supply temperature must be below a certain temperature in order not to raise the disk rotor above the allowable temperature,
That is, a flow path having a relatively small heat load must be selected to suppress the temperature rise. Due to these restrictions, it is necessary to pass through the flow path at the center of the blade profile except for the trailing edge flow path where the flow path area cannot be large and the leading edge flow path where the heat load is relatively high.

As a method for securing the open cooling medium supply flow path, a part of the blade cooling flow path is provided as a dedicated flow path for the open cooling medium separately from the closed cooling medium flow path.
Alternatively, a tube or the like for passing the open cooling medium into the closed cooling medium passage may be inserted. Here, since the closed cooling medium is pressurized and supplied to the blades as described above, the pressure of the closed cooling medium is higher than that of the open cooling medium, and the flow path of the closed cooling medium and the flow path of the open cooling medium are completely If separate and not individually sealed,
The closed cooling medium enters the flow path of the open cooling medium and leaks.

[0011] Even if the amount of the closed cooling medium leaks from the original path even if the amount is small, the work consumed in the cooler and the boost compressor is lost, so that the effect of the closed cooling is lost and the plant efficiency is reduced. There are problems such as connection. In the method of passing the tube for the open cooling medium through the closed cooling medium flow path, the number of welding points tends to increase for separation and sealing of each flow path, increasing the number of steps and increasing the probability of occurrence of welding defects,
Reliability may be impaired.

Another point to be noted when employing closed cooling is prevention of overcooling.
The closed cooling medium is supplied after being cooled by a cooler, and since the supply temperature is much lower than the open cooling medium and the cooling capacity is higher, when the outer surface of the blade is to be cooled to a certain temperature or less, the outer cooling surface is cooled. A large temperature difference, ie a large thermal gradient, occurs between the surface and the surface.

[0013] Here, for example, in a portion cooled by a closed cooling medium from both sides, such as a partition between blade cooling passages, the temperature is further lowered as compared with other portions of the blade, and supercooling is liable to occur. When supercooling occurs, excessive thermal stress occurs due to the large thermal gradient, and the structure of the separation part of the cooling medium flow path for relaxing thermal stress tends to be complicated, and cracks and breakage in the welded part Is likely to occur, which may shorten the life of the blades and impair the reliability of the gas turbine.

SUMMARY OF THE INVENTION The present invention has been made in view of the foregoing, and an object of the present invention is to simplify the structure of a separation section between a closed cooling medium flow path and an open cooling medium flow path, thereby allowing refrigerant leakage and supercooling of blade portions. It is an object of the present invention to provide a gas turbine of this type that can sufficiently prevent the occurrence of the gas turbine.

[0015]

That is, the present invention has a cooling medium circulation path inside a turbine vane,
The cooling medium is circulated through the cooling medium distribution path to cool the stationary blades, and the cooling medium after the stationary blade cooling is formed so that a part is recovered and a part is released into the mainstream gas. In the gas turbine, a plurality of cooling medium distribution paths are provided in the stationary blade, and at least one of the cooling medium distribution paths cools the stationary blade by flowing a cooling medium supplied from the outside. After cooling, the cooling medium is returned to the outside again, and another cooling medium flow path cools the stationary vanes by flowing the cooling medium supplied from the outside, and after cooling, a part of the cooling medium flows into the mainstream gas. The cooling medium discharged to the inside and the remaining cooling medium is formed so as to be supplied as a sealing medium to a rotating portion arranged on the inner peripheral side of the stationary blade so as to achieve an intended purpose.

In this case, a plurality of cooling medium distribution paths provided in the stationary blade are sequentially arranged in parallel from the leading edge to the trailing edge of the blade, and the cooling medium at the leading edge and the trailing edge of the blade is provided. The cooling medium discharged into the mainstream gas is formed to flow through the cooling medium flow path excluding the flow path. In addition, a plurality of cooling medium distribution paths provided in the stationary blade are sequentially arranged in parallel from the leading edge to the trailing edge of the blade, and the second cooling medium distribution path from the leading edge side of the blade is The cooling medium discharged into the mainstream gas is formed to flow.

Further, a plurality of cooling medium distribution paths provided in the stationary blade are sequentially provided in parallel from the leading edge to the trailing edge of the blade, and a cooling medium distribution path on the frontmost edge side of the blade and a front side of the blade. The third and subsequent cooling medium flow paths from the edge side are formed as flow paths for the cooling medium recovered after the cooling, and the second cooling medium flow path from the leading edge side of the blade is inserted into the mainstream gas. The cooling medium is formed as a flow path for the discharged cooling medium, and impingement cooling means is provided in each of the cooling medium flow paths.

Further, according to the present invention, a cooling medium circulation path is provided inside the turbine vane, and the cooling medium is circulated through the cooling medium circulation path to cool the stationary vane. In a gas turbine partially recovered and partially discharged into a mainstream gas, a plurality of cooling media sequentially arranged on the stationary blade from a leading edge to a trailing edge of the blade. In addition to establishing a distribution path,
The recovered cooling medium is supplied to the first cooling medium flow path from the leading edge side of the blade, and the second cooling is performed at the inner peripheral end wall portion of the rear blade after impingement cooling the leading edge of the blade. Bypassing the flow path, guided to the third cooling flow path, collected from the trailing edge flow path after the third cooling flow path to the outside of the blade, and released into the mainstream gas Cooling medium is supplied to the second cooling medium flow path from the leading edge side of the blade, impingement-cools the blade portion, and partially cools the impeller without using it for cooling the second cooling channel. It is formed so as to be directly guided to the seal portion on the inner circumferential side of the blade.

In this case, the recovery port of the cooling medium circulation path through which the cooling medium recovered after the cooling of the stationary blade flows is connected to the blade profile outer peripheral side on the outer peripheral end wall provided on the outer peripheral side of the stationary blade. A flow path that is provided near the center of the extension and that connects the trailing edge cooling flow path to the recovery port is provided on the outer peripheral side end wall. In addition, the outer peripheral side end wall is sealed with a cover, and a supply port of a cooling medium distribution path through which the collected cooling medium flows is provided on the cover, and the outer peripheral side end wall is provided with the supplied cooling medium. After the impingement cooling, it is supplied to the blade leading edge cooling flow path. Further, a part of the inner peripheral end wall is impingement-cooled with an open cooling medium guided to an inner peripheral end wall provided on the inner peripheral side of the wing,
Further, the inner peripheral end wall is cooled by discharging into the mainstream gas through convection cooling holes arranged on the upstream and downstream sides of the inner peripheral end wall.

That is, in the gas turbine formed as described above, the cooling medium flow path discharged into the mainstream gas, that is, the open cooling medium supply flow path has a low external heat load,
Since the airfoil is arranged at a position where the cross-sectional area of the flow path can be relatively large, the temperature rise and pressure loss of the open cooling medium in the cooling flow path are suppressed, and the air is supplied to the diaphragm as a good seal cooling medium. .

Further, a closed cooling medium having a high cooling capacity is supplied to a leading edge cooling flow path having a relatively high heat load, and an open cooling medium having a low cooling capacity is supplied to a cooling path second from the leading edge. Further, the third cooling channel is supplied with a closed cooling medium that has bypassed the second cooling channel from the leading edge cooling channel, so that the cooling is performed from both sides such as the partition between the cooling channels. It is possible to reduce the supercooling of the essential parts.

Further, in order to reduce the overcooling of the partition between the leading-edge cooling passage and the second cooling passage having a large degree of overcooling, the second cooling from the leading-edge cooling passage and the leading edge is performed. By employing impingement cooling in which the heat load can be adjusted in the flow path, the effect of reducing supercooling can be further enhanced. In addition, the leading cooling channel and the third cooling channel from the leading edge to the trailing edge cooling channel as a closed cooling medium distribution path, and the second cooling channel from the leading edge as an open cooling medium distribution path. Therefore, compared with the case where the open cooling medium is passed through the tube in the closed cooling medium flow path, the number of welding points can be reduced, and the closed cooling medium is opened due to damage to the tubes and welds during gas turbine operation. Leakage into the cooling medium flow path can also be prevented.

[0023]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below in detail with reference to the illustrated embodiments. FIG. 1 shows a cross section of a main part (blade section) of the gas turbine. Arrow 20 in the figure
Indicates the flow direction of the mainstream gas, where 1 is the first stage stationary blade, 3 is the second stage stationary blade, 2 is the first stage stationary blade, 4 is the second stage stationary blade, 5 is the second stage stationary blade diaphragm, and 6 is the second stage stationary blade diaphragm. A distant piece, 7 is a first stage rotor disk, 8 is a disk spacer, and 9 is a second stage rotor disk.

The first stage rotor blade 2 is fixed to the rotor disk 7, and the second stage rotor blade 4 is fixed to the rotor disk 9, respectively.
The distant piece 6, the rotor disk 7, the disk spacer 8, and the rotor disk 9 are integrally fixed by a stub shaft 10 to form a rotating body.

The operating principle of the gas turbine constructed as described above will be briefly described below.
Converts the high-pressure energy into the energy of the flow velocity by the stationary blades 1 and 2, and rotates the moving blades 2 and 3.
The generator uses the rotational energy to generate electricity, but some of the rotational energy is also used to drive the compressor. Since the mainstream gas temperature is higher than the allowable temperature of the wing material, the wing exposed to the hot gas must be cooled.

Taking the second-stage stationary blade 3 as an example, the cooling medium of the second-stage stationary blade includes a refrigerant discharged from the compressor and a refrigerant cooled and pressurized by a cooler and a boost compressor, respectively, and a compression stage. There are two bleed fluids, the former being a closed cooling medium and the latter being an open cooling medium. The former closed cooling medium 22 is supplied by a pipe 30 disposed on the outer peripheral side of the second stage stationary blade 3, and after being cooled by the second stage stationary blade 3, is recovered by the outer peripheral side pipe 31, and is collected in the gas turbine casing 11. And finally is supplied to the combustor inlet and merges with the compressor discharge fluid.

On the other hand, the latter open cooling medium 23 is supplied to the cavity 12 formed by the outer periphery of the second stage stationary blade 3 and the casing 11 by an external pipe, and further supplied to the cooling passage of the stationary blade 3 from the cavity 12. After cooling a part of the stationary blade 3, it is finally released into the mainstream gas, but a part of the open cooling medium 23 is guided to the diaphragm 5 arranged on the inner peripheral side of the stationary blade 3. Is released to the gap 14 between the shank portion 13 of the first stage rotor blade 2 and the diaphragm 5.

That is, it is used as a seal medium 23b for the wheel space, and prevents the mainstream gas 20 from entering the gap 14. Should the high-temperature mainstream gas 20 enter the gap 14 and raise the ambient temperature, not only the rotor blade shank portion 13 and the diaphragm 5 will be damaged by the high-temperature gas, but also the rotor disks 7 and 9 There is a possibility that an excessive thermal load is applied to the disk spacer 8 and the disk spacer 8, resulting in a reduction in life due to thermal stress, and furthermore, a thermal deformation may hinder the operation of the gas turbine.

FIG. 2 is a perspective view of the stationary blade 3 viewed from the outer peripheral side. The stationary blade of the present embodiment has an outer peripheral end wall 4.
Two wing portions 90a between the first end wall 48 and the inner peripheral end wall 48
In order to reduce the number of pipes in the casing by adopting a double-blade in which the closed cooling medium supply pipes 30 and 90b are disposed, one closed cooling medium supply pipe 30 and two closed cooling medium recovery pipes 31 are provided for each blade segment.

FIG. 3 is a sectional view in the axial direction of the stationary blade 3, showing a more detailed structure. A cavity 42 is formed by the end wall 40 and the cover 41 in a portion of the outer peripheral end wall 40 of the stationary blade 3, and an impingement plate 58 having a plurality of impingement cooling holes is formed in the cavity 42. Wall cooling surface 40
a with a certain distance.

On the other hand, a cavity 50 is formed in the inner peripheral end wall 48 by the end wall 48 and the cover 49, and an impingement plate 51 having a plurality of impingement cooling holes is formed in the cavity 50.
Are arranged at a certain distance from the inner peripheral side end wall cooling surface 48a.

The inner peripheral end wall has
Convection cooling holes 52 and 53 for communicating the cavity 50 with the mainstream gas path are provided. The second cooling flow path 44 is formed so as to communicate the outside of the outer peripheral end wall cover 41 and the inner peripheral end wall cavity 50, and the outlet 91 of the fifth flow path 47 is connected to the outer peripheral end wall cover 41. It is extended to the outside by the extension flow path 56 and is connected to the closed cooling medium recovery pipe 31 near the center of the blade profile outer peripheral side extension so as to be smoothly connected to the cooling medium recovery pipe 31.

Further, the first cooling channel 43 and the third cooling channel 45 are formed by an inner peripheral end wall 48 as shown in FIG. Without being connected, they are connected to each other by a bypass channel 54 formed so as to jump over the second cooling channel 44. The inner peripheral end wall cover 49 is provided with a bend 95 connected to the wheel space seal medium supply connection pipe 55.

The first cooling channel 43 and the second cooling channel 4
4, core plugs 60 and 61 having a plurality of impingement cooling holes are inserted, and turbulence promoting ribs 62 are provided on the cooling surfaces of the third cooling channel 45 and the fourth cooling channel 46. 47 are provided with pin fins 63, respectively.

Next, the second stage stationary blade 3 constructed as described above
Explaining the operation principle of the closed cooling medium 22,
Outer end wall cavity 4 by supply pipe 30
2 and impingement cooling of the outer peripheral side end wall by the impingement plate 58. After the outer peripheral side end wall cooling, the closed cooling medium 22a is guided to the core plug 60 arranged in the wing portion first cooling flow path 43, and impingement cools the first cooling flow path 43.

The closed cooling medium 22 b having cooled the first cooling channel 43 is guided to the third cooling channel 45 through the bypass channel 54 provided in the inner peripheral end wall 48. The third cooling channel 45 and the fourth cooling channel 46 are convectively cooled by the turbulence promoting ribs 62, and the fifth cooling channel is convectively cooled by the pin fins 63.
c passes through the extension flow path 56 and is collected in the collection pipe 31.

On the other hand, the open cooling medium 23 is supplied into the core plug inserted into the second cooling channel 44, and impingement-cools the second cooling channel 44. The cooling medium 23 a that has finished cooling the second cooling channel 44 is guided to the inner peripheral end wall cavity 50. A part of the cooling medium 23 b in the inner peripheral side wall cavity impinges the inner peripheral side end wall 48 by the impingement plate 51, and is further cooled by the convection cooling holes 52 and 53 of the inner peripheral side end wall 48. The peripheral end wall 48 is cooled and finally released into the mainstream gas. Further, a part of the cooling medium 23c in the inner peripheral side end wall cavity is supplied to the upstream side of the diaphragm 5 through the bend 95 and the wheel space sealing medium supply connection pipe 55 as a sealing medium.

The principle of the cooling operation of the gas turbine stationary blade according to the present invention has been described above. Here, when the blades are closed-cooled, care must be taken to prevent overcooling. Since the closed cooling medium is supplied to the combustor inlet through the recovery pipe after cooling the blades and merges with the compressor discharge medium, the recovery temperature after the blade cooling is equal to or higher than the compressor discharge medium temperature and the recovery pipe is allowed to improve gas turbine efficiency. Temperature, and the recovery temperature is generally lower than the temperature of the open cooling medium after the blade cooling. Therefore, as described above, since the closed cooling medium is cooled by the cooler and supplied to the blades, the supply temperature is lower than that of the open cooling medium, and the cooling capacity is higher. Therefore, when trying to cool the outer surface of the blade to a certain temperature or lower, a large temperature difference between the outer surface of the blade and the cooling surface, that is, a large thermal gradient is likely to occur. In a place where cooling is performed from both sides by a closed cooling medium, the temperature is further lowered as compared with other parts of the blade, and supercooling is likely to occur.

When supercooling occurs, an excessive thermal stress is generated due to a large thermal gradient, which may shorten the life of the entire blade and impair reliability. Therefore, in the present invention, as shown in the blade cross-sectional structure in FIG.
Is cooled by a closed cooling medium 22 having a high cooling capacity, and the cooling method is such that the impingement holes are densely arranged only in the portion to be cooled so that intensive cooling is possible, and the impingement holes are not provided in the portion not desired to be cooled. It adopts impingement cooling that can adjust the cooling capacity.

On the other hand, the second cooling flow path 44 has a relatively low heat load, is capable of suppressing a rise in temperature when passing the sealing medium, and has a relatively large cooling flow path area to reduce pressure loss. Adopts impingement cooling, in which the cooling capacity can be adjusted using the open cooling medium 23 for the same reason as described above. Here, the cross section of the turbine blade generally has a shape in which the thickness of the blade decreases from the leading edge to the trailing edge in an arc shape. Therefore, the partition partitioning between the blade cooling passages is longer on the leading edge side and shorter on the trailing edge side. Therefore, the partition 93 that separates the first cooling channel 43 and the second cooling channel 44 and the second cooling channel 4
The partition 94 separating the fourth cooling passage 45 from the third cooling passage 45 has an elongated shape. Since the partition portion is far from the superheated surface, that is, the blade surface, through the cooling medium on both sides, the partition center portion 93a or 94b of this type has another blade. Although the temperature tends to be particularly low as compared with that of the core plugs 60 and 61, the structure adopts impingement cooling for the first cooling channel 43 and the second cooling channel 44 as described above.
Since no impingement holes for cooling this part are provided, overcooling can be prevented.

As described above, the supply temperature of the closed cooling medium 22 is lower than the supply temperature of the open cooling medium 23 as described above. In the case of this structure, regarding the partition 93, the cooling path is configured such that the closed cooling medium 22 passes through the first cooling channel 43 side and the open cooling medium 23 passes through the second cooling channel 44 side. Overcooling can be further prevented as compared with the case where a closed cooling medium having a high cooling capacity passes on both sides.
The same applies to the partition 94. The second cooling flow path 44 side is an open cooling medium, and the third cooling flow path side 45 is a closed cooling medium.

As described above, in such a gas turbine, the closed cooling medium flow path and the open cooling medium flow path can be rationally formed in accordance with the blade cooling requirement, and the diaphragm can be stably formed. To prevent overcooling occurring in the partition between the blade cooling passages, thereby making the temperature of the blade more uniform, that is, reducing the thermal stress, and consequently reducing the life of the blade. Can be prevented. In addition, since it is not necessary to insert a tube or the like through which the open cooling medium is inserted into the closed cooling medium flow path, welding around the tube is eliminated, the number of steps is reduced, and the closed cooling medium and the open cooling medium are respectively cooled. Since the closed cooling medium is completely separated by the passage, it is possible to prevent the closed cooling medium from entering the open cooling medium flow path and impairing the effect of the closed cooling.

Note that the structure of the present invention is not limited to the two-blade, and the effect is not changed even if any number of wings are arranged in the outer and inner end walls such as a single wing, three wings, and four wings. There is no restriction.

Next, a modification of the present invention shown in FIG. 6 will be described. This figure is a cross-sectional view of the main part of the stationary blade. If the temperature of the cooling medium 23c after cooling the second cooling flow path 44 is too high to be supplied as a sealing medium, the second cooling flow path A seal medium supply hole 96 is provided at the lower end of the core plug 61 in the 44, and the supply hole 96 is extended so as to be inserted into the bend 95 beyond the inner peripheral end wall cover 49.

In the structure thus constructed, the cooling medium 23c after cooling the second cooling flow path 44 is used only for the inner peripheral end wall 48, and the impingement cooling of the blades in the core plug 61 is used as the sealing medium. The open cooling medium 23d that has not been used in the above, that is, the temperature of which has not risen due to the blade cooling, is supplied from the supply hole 96 to the bend 95,
Can solve the problem.

Although the embodiments of the present invention have been described above, the structure of the present invention can be applied and has an effect to other stages of stationary blades regardless of the second stage stationary blades. By using the structure of the present invention, the paths of the closed cooling medium cooling passage and the open cooling medium cooling passage can be separated without using complicated means and without applying many welding points,
An appropriate path configuration and cooling method can prevent a blade from overcooling and provide a highly reliable gas turbine without impairing the advantage of performing closed cooling.

[0047]

As described above, according to the present invention, the structure of the separation part between the closed cooling medium flow path and the open cooling medium flow path is simple, and the leakage of the refrigerant and the overcooling of the blades are sufficiently prevented. This type of gas turbine can be obtained.

[Brief description of the drawings]

FIG. 1 is a sectional view of a main part showing an embodiment of a gas turbine equipped with a stationary blade of the present invention.

FIG. 2 is a perspective view of the gas turbine stationary blade of the present invention as viewed from the outer peripheral side.

FIG. 3 is a cross-sectional view of the gas turbine stationary blade of the present invention.

FIG. 4 is a perspective view of the gas turbine vane of the present invention as viewed from the inner peripheral side.

FIG. 5 is a cross-sectional view of the gas turbine stationary blade of the present invention.

FIG. 6 is a perspective view of a main part showing a modified example of the gas turbine stationary blade of the present invention.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... 1st stage stationary blade, 2 ... 1st stage rotor blade, 3 ... 2nd stage stationary blade, 4
... second stage rotor blades, 5 ... second stage stationary blade diaphragm, 6 ... distant piece, 7 ... first stage rotor blade rotor disk, 8 ...
Disk spacer, 9 2nd stage rotor blade disk, 1
0: stub shaft, 11: gas turbine casing,
12: cavity, 13: first stage blade shank part, 14
... gap, 20 ... mainstream gas, 22 ... closed cooling medium,
23 ... Open cooling medium, 23b ... Seal medium for wheel space, 30 ... Closed cooling medium supply pipe, 31 ...
Closed cooling medium recovery pipe, 40: outer peripheral side end wall, 40a: outer peripheral side end wall cooling surface, 41: outer peripheral side end wall cover, 42: outer peripheral side cavity,
43 ... first cooling channel, 44 ... second cooling channel, 45 ... third cooling channel, 46 ... fourth cooling channel, 47 ... fifth cooling channel,
48 ... inner peripheral end wall, 49 ... inner peripheral side end wall cover, 50 ... inner peripheral side cavity, 51 ... inner peripheral side impingement plate, 52, 53 ... inner peripheral side end wall convection cooling hole, 54 ... bypass flow path, 55 ... connection piping, 56
… Extended flow path, 58… outer peripheral side impingement plate, 60…
First channel core plug, 61 ... second channel core plug, 62
... turbulence promoting ribs, 63 ... pin fins, 90a, 90b ...
Wings, 91: Fifth flow path outlet, 93, 93a ... Partition between first cooling flow path and second cooling flow path, 94, 94b ...
Partition between the second cooling passage and the third cooling passage, 95
... Bend, 96 ... Seal medium supply hole at the lower end of the second flow path core plug.

Continued on the front page (72) Inventor Shunichi Ansai 7-2-1, Omika-cho, Hitachi City, Ibaraki Prefecture Inside Electric Power & Electric Research Laboratory, Hitachi, Ltd. (72) Inventor Ueno Execution 7-2, Omika-cho, Hitachi City, Ibaraki Prefecture No.1 F-term in Hitachi, Ltd. Electric Power & Electric Development Laboratory (Reference) 3G002 GA08 GB01 HA01 HA03 HA18

Claims (8)

[Claims] 1. A cooling medium distribution path is provided inside a turbine stationary blade, a cooling medium is distributed through the cooling medium distribution path to cool the stationary blade, and a part of the cooling medium after the stationary blade cooling is partially cooled. In a gas turbine that is collected and partially formed to be released into mainstream gas, while providing a plurality of cooling medium circulation paths to the stationary blade,
At least one of the cooling medium distribution paths is configured such that a cooling medium supplied from the outside circulates to cool the stationary vanes, and after cooling, is recovered to the outside again, and the other cooling medium distribution paths are The cooling medium supplied from the outside circulates to cool the stationary blade, and after cooling, a part of the cooling medium is released into the mainstream gas, and the remaining cooling medium is disposed on the inner peripheral side of the stationary blade. A gas turbine formed to be supplied as a seal medium to a rotating part which is provided. 2. A plurality of cooling medium distribution paths provided on the stationary blade are sequentially provided in parallel from the leading edge to the trailing edge of the blade, and the cooling medium distribution paths at the leading edge and the trailing edge of the blade are provided. 2. The gas turbine according to claim 1, wherein a cooling medium discharged into the mainstream gas is formed to flow through a cooling medium flow path excluding the cooling medium. 3. 3. A plurality of cooling medium circulation paths provided on the stationary blade are sequentially arranged in parallel from the leading edge to the trailing edge of the blade, and a second cooling medium circulation path from the leading edge side of the blade is provided. The gas turbine according to claim 1, wherein the cooling medium discharged into the mainstream gas is formed to flow. 4. A plurality of cooling medium distribution paths provided in the stationary blade are sequentially arranged in parallel from a leading edge to a trailing edge of the blade, and a cooling medium distribution path on a leading edge side of the blade and a front side of the blade. The third and subsequent cooling medium flow paths from the edge side are formed as flow paths for the cooling medium recovered after the cooling, and the second cooling medium flow path from the leading edge side of the blade is inserted into the mainstream gas. 2. The gas turbine according to claim 1, wherein the gas turbine has a flow path for the discharged cooling medium, and is provided with impingement cooling means in each of the cooling medium flow paths. 5. A cooling medium distribution path is provided inside the turbine stationary blade, and a cooling medium is distributed through the cooling medium distribution path to cool the stationary blade, and a part of the cooling medium after the stationary blade cooling is partially cooled. In the gas turbine which is collected and partially formed so as to be released into the mainstream gas, the plurality of cooling medium distribution paths sequentially arranged in parallel from the leading edge to the trailing edge of the vane are provided on the vane. While providing, the recovered cooling medium is supplied to the first cooling medium flow path from the leading edge side of the blade, and the impeller impingement-cooled the leading edge of the blade. Bypassing the third cooling passage, leading to the third cooling passage, passing through the third and subsequent cooling passages, being collected outside the blade from the trailing edge passage, and in the mainstream gas Is discharged from the leading edge side of the wing It is supplied to the cooling medium flow path of the eye, impingement-cools the wing part, and guides the part directly to the seal part on the inner peripheral side of the stationary blade without using the part for cooling the second cooling flow path. A gas turbine characterized by being formed in a gas turbine. 6. A recovery port of a cooling medium circulation path through which a cooling medium recovered after cooling the stationary blade flows is provided near an outer peripheral side extension center of a blade profile on an outer peripheral end wall provided on an outer peripheral side of the stationary blade. 6. The gas turbine according to claim 2, further comprising a flow path provided from the trailing edge cooling flow path to the recovery port on the outer peripheral side end wall. 7. An outer peripheral side end wall is sealed with a cover, a supply port of a cooling medium distribution path through which the recovered cooling medium flows is provided on the cover, and the supplied cooling medium is supplied to the outer peripheral side. 7. The gas turbine according to claim 4, wherein the end wall is supplied to a blade leading edge cooling flow path after being impingement cooled. 8. An impingement cooling of a part of the inner peripheral end wall with an open cooling medium guided to an inner peripheral end wall provided on an inner peripheral side of the blade,
6. The inner peripheral side end wall is cooled by discharging into a mainstream gas through convective cooling holes arranged on an upstream side and a downstream side of the inner peripheral side end wall. , 6 or 7.