JPH08277725A - Gas turbine - Google Patents

Abstract

PURPOSE: To clarify the constitution of steam supply or recovery by providing, in a cooling system, a supply system to supply steam to a moving blade and a recovery system to recover the steam from the moving blade, and forming a recovery channel on an inside of a supply channel. CONSTITUTION: Steam supplied from a steam supply port 43 at a stub shaft end is branched in three systems in such a process that it axially flows into a supply channel 74 through a steam channel 44 in a shaft center hole. In a first system, the steam flows into a cavity 62 after cooling a second stage moving blade 52. In a second system, the steam flows into the cavity 62 after cooling a first stage moving blade 51, joined with the recovery steam in the first system and flows toward a recovery channel 72 which is a part centering around a cavity 65. In a third system, the steam is led to the recovery channel 72 of a rotor center part through a cavity on side surfaces of rotor discs 21, 22 after cooling the outer circumference of a compressor rotor 2, joined with steam after it cools the moving blade and recovered from a recovery port 46 to the outside. Low temperature steam thusly flows into the supply channel 74 which is passing through the discs, so that thermal stress of each part can be reduced.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine which employs a steam cooling system for cooling moving blades using steam, and more particularly to a gas turbine which recovers steam after cooling the moving blades.

[0002]

2. Description of the Related Art As a steam-cooled gas turbine, for example, the document A.S.M.E./I.E.E.
EPower General Conference (Jt.A
Proceedings 8 of SME / IEEE Power Generation Conference)
As described in 7-JPGC-GT-1 (1987), there is one that recovers the steam used for cooling and returns it to the plant.

[0003]

However, it cannot be said that the prior art specifically discloses the supply and recovery of steam when the steam-cooled gas turbine is used as an actual plant.

Therefore, an object of the present invention is to clarify a concrete configuration of supply or recovery of steam used in a steam-cooled gas turbine. Another object of the present invention is to provide a gas turbine with improved plant efficiency.

[0005]

The gas turbine of the present invention has a cooling system for cooling moving blades using steam.

The gas turbine according to the present invention comprises a compressor for compressing air (atmosphere), a combustor for combusting the air and fuel compressed by the compressor to generate high temperature combustion gas, and a combustor for combusting the combustor. And a turbine for moving the blades by the combustion gas of the above. In addition to this, a system for supplying steam to the turbine is provided.

In the combustor, 1400 ° C. or higher, for example,
Combustion gas of 1350 to 1650 ° C. is generated, and the higher the temperature, the larger the output. In addition, the turbine has three or four paragraphs in which a stationary blade and a moving blade are combined.
Have steps.

The cooling system of the present invention comprises a supply system for supplying steam to the moving blade and a recovery system for recovering steam from the moving blade, and the recovery passage of the recovery system is located inside the supply passage of the supply system. It is characterized in that it is formed. Here, the steam is specifically generated by a steam generator, such as a waste heat recovery boiler, and the so-called steam is mainly composed of H ₂ O.

The steam supply system referred to in the present invention is a system for supplying steam from the steam generator to the moving blades of the turbine, and has a supply passage in a part of this system. Here, the supply channel is formed in the rotor of the turbine. Further, the recovery system refers to a system for recovering and reusing steam from the moving blades of the turbine, for example, a system including a waste heat recovery boiler and a condenser, and a recovery flow path is provided in a part of this system. Here, the recovery passageway is formed toward the center of the rotor of the turbine. Further, the supply system or the recovery system may be considered from the moving blade to the rotor shaft end of the turbine, respectively.

The cooling system of the present invention has a supply port formed at the rotor shaft end for supplying steam to the moving blade, and a recovery port formed at the rotor shaft end for collecting steam from the moving blade. The recovery port is formed closer to the center of the rotor shaft than the supply port.

As described above, by passing the recovered steam through the central axis side of the rotor with respect to the supplied steam, thermal stress in the rotor and the like is relieved and stable turbine operation becomes possible.

Further, the supply passage is preferably formed in a cavity formed between the final stage disc of the rotor and the stub shaft, and in a portion where the disc and the disc are joined. In addition, one recovery channel consists of the first stage and 2
It is preferably formed between the discs of the stages, and it is preferable to utilize a cavity for collecting the vapor supplied to the first stage rotor blade and the second stage rotor blade.

On the other hand, the present invention is characterized in that the compressor rotor is cooled by using steam. This steam is supplied through a steam flow path formed in a distant piece that connects the turbine rotor and the compressor rotor, and is recovered through a steam flow path formed on the axial center side of the distant piece. It Cooling the rotor of the compressor with steam also enables effective use of steam.

Further, when the cooled steam is recovered, the recovered steam is passed through the spacer portion formed between the disks of the rotor, and the steam is injected into the cavity formed between the disks. It is preferable to form a vapor flow path for recovery. By collecting steam through this portion, the space in the rotor can be effectively used.

Further, it is preferable that the spacer portion has a protruding portion that guides the recovered steam to the steam passage.
Thereby, steam can be recovered more efficiently. In addition, in addition, a part of the steam flowing through the supply channel is used to cool the side surface of the disk, whereby the thermal stress can be relaxed.

On the other hand, in the gas turbine of the present invention, the moving blade is cooled by using steam and the steam is recovered.
It uses a closed steam cooling system. And, the paragraph structure of the moving blade and the stationary blade has three or four stages, and the combustion gas temperature introduced into the turbine is 1400 ° C.
When the above class output is limited to 400 MW or more, the temperature of the steam supplied to the moving blade is 250 ° C. or less, for example, 250 to
180 ℃, the temperature of the steam recovered from the rotor blade 450 ℃
A steam cooling system can be achieved by setting the temperature to 450 to 380 ° C., for example. It is also possible to operate by changing these temperatures.
In some cases, the temperature is 0 ° C, and the latter is 500 to 430 ° C. That is, it is determined by considering the heat load in the turbine, the allowable material temperature of the moving blades, and the like. It is also determined by considering the steam flow rate and the allowable material temperature of the rotor.

By adopting such a configuration, it is possible to improve the efficiency by 5 to 6% and the output by 13 to 16% as compared with the gas turbine adopting the open cooling system. Moreover, more than the conventional closed cooling system,
It is possible to improve the efficiency by 0.8 to 1.2% and the output by 2 to 3%.

That is, in order to recover the steam used for cooling the moving blades, it is preferable to construct two steam paths for supply and recovery inside the rotor supporting the moving blades. In the case of a gas turbine whose temperature exceeds 1400 ° C, the temperature difference between the supplied steam and the recovered steam will be 200 degrees or more, so there is sufficient consideration that the flows of the two systems do not intersect and that it is a high-speed rotating body. It is important to keep the temperature rise of the rotor due to steam below the heat-resistant temperature and to keep the thermal stress caused by the temperature difference below the allowable stress.

Further, in order to increase the specific output of the gas turbine (output per unit fuel), it is necessary to increase the compression ratio of the compressor. However, if the compression ratio is increased, the temperature of the compressed discharge air rises. Therefore, the outer peripheral portion of the compressor rotor is heated and exceeds the allowable temperature, so that cooling is required as in the present invention. Since the compressor rotor and the turbine rotor are connected and rotate integrally, the turbine rotor and the compressor rotor can be cooled by sharing the steam system.

The present invention can provide a steam-cooled gas turbine suitable for improving efficiency by constructing a steam supply or recovery path as a high-speed rotating body in the rotor, which is less troublesome.

Further, in the combined power generation plant of the present invention in which the gas turbine and the steam turbine are combined, the exhaust heat of the gas turbine exhaust gas is used to generate steam for the steam turbine. By increasing the temperature, not only the thermal efficiency of the turbine alone but also the power generation efficiency of the entire plant can be improved.

Therefore, the temperature of the working gas greatly exceeds the heat resistant temperature of the blade, but can be kept within the heat resistant temperature by the present invention.

Since vapor is used as the refrigerant, it is necessary to consume extra compression power for increasing the flow rate of the air as the refrigerant as the temperature of the working gas becomes higher than in the case of using compressed air. Disappears. Moreover, since the air having a low temperature used for cooling is not discharged to the working gas flow path (hereinafter referred to as a gas path), the working gas is not diluted and the temperature of the working gas is not lowered, and there is no problem that the output of the turbine is reduced. . Therefore, by using the steam for cooling, the efficiency can be improved as compared with the gas turbine using the compressed gas for combustion as the refrigerant.

In the combined cycle power plant of the present invention, a steam-cooling type gas turbine using steam introduced from another system as a refrigerant is proposed.

As the steam, it is preferable to use superheated steam generated by utilizing exhaust heat in order to avoid the accumulation of impurities in the water in the cooling flow path, because of the influence of the viscosity coefficient and the number of plants. It has advantages such as a larger heat transfer coefficient (about 1.5 times) than that of air, and a small specific temperature rise when heat is applied (one half or less of air) due to its large specific heat.

Also in the steam cooling type, the smaller the flow rate of steam used for cooling is, the better in order to improve the efficiency of the entire plant, and the steam after cooling is not released into the working gas but recovered. And does not affect the working gas,
Improve efficiency.

[0027]

As described above, in a gas turbine having a cooling system for cooling moving blades using steam, the gas turbine includes a supply system for supplying steam to the moving blades and a recovery system for collecting cooled steam. Since the recovery flow path of the recovery system is formed inside the supply flow path of the supply system, the high-temperature recovery steam flows inside the low-temperature supply steam. The expansion relaxes the centrifugal stress in the center of the rotor.

Further, a supply port and a recovery port are provided at the shaft end of the rotor, and the recovery port is formed closer to the axial center of the rotor than the supply port, so that the above-mentioned high-temperature recovery steam flow can be formed more smoothly. The advantage is that it is easy to do.

Further, in a gas turbine having a cooling system for cooling moving blades using steam, a cavity is formed between the stub shaft and the final stage disk of the rotor of the gas turbine, and the disks are joined together. By supplying the steam by forming the supply flow path in the portion where the steam is supplied, the temperature of the joint portion is maintained at a temperature lower than that of the recovered steam by the supply steam, and the thermal strain of the portion is reduced.

Further, a supply passage is formed in a portion where the disks of the rotor of the gas turbine are joined to each other to supply steam, and the steam is supplied through a cavity formed between the first-stage and second-stage disks. By collecting, the temperature rise of the disk and the generation of thermal stress due to the high temperature steam can be reduced as much as possible.

Further, steam is used to cool the compressor rotor, and the steam is supplied through a steam passage formed in a distant piece connecting the turbine rotor and the compressor rotor. The compressor rotor can be cooled by sharing the steam flow path with the turbine rotor by recovering the steam via the steam flow path formed on the axial center side of the distant piece.

Further, in a gas turbine for cooling moving blades using steam, a spacer having a steam flow path for recovering steam is interposed between the disk of the rotor of the gas turbine and the disk, and the spacer has the disk. By forming it inside the cavity formed between the disk and the disk, it is possible to prevent the disk joint from being directly exposed to the recovered steam, and to project the steam recovered by the spacer into the steam flow path. By forming parts
The flow of the recovered steam on the side surface of the outer peripheral portion of the disk is deflected, heat transfer is weakened, and the thermal stress of the disk is reduced.

Further, in the gas turbine, a steam passage is formed in a portion where the disks are joined to each other, and a side surface of the disk is cooled by using a part of steam in the steam passage. Since the side surface of the disk is effectively cooled by the low temperature steam flowing out, the temperature rise and the thermal stress are reduced more effectively.

[0034]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described in detail below with reference to FIGS.

FIG. 1 shows a cross-sectional structure of the upper half of the gas turbine, taking a case of an air compression type three-stage turbine as an example. A casing 80, a compressor rotor 2 and a compressor composed of blade rows at the outer peripheral portion, and a combustion Vessel 84, stationary blades 81 to 83 and moving blades 51 to 53
The gas paths 85 and the turbine rotor 1 are formed by alternately arranging.

The turbine rotor 1 has three disks 11,
12 and 13 and the stub shaft 4 and the joint 14
It is closely joined as a high-speed rotating body. Moving blades 51 to 53 are planted on the outer circumference of each disk, and are connected to the compressor rotor 2 via a distant piece 3 and are rotatably supported by a bearing 40.

In such a structure, the high-temperature, high-pressure working gas generated in the combustor 84 using the air compressed by the compressor flows while expanding the gas path 85, whereby the turbine rotor is rotated and power is generated. To be done.

For example, the pressure of the working gas at the outlet of the combustor is set to 2
When the temperature is 2 to 25 ata and the temperature is 1500 ° C, the power of 400 MW or more is generated even in a gas turbine with a rotor outer diameter of about 2.5 m, but the gas relative total temperature at the blade inlet is about 12
50 to 1300 ° C, the second stage is about 950 to 1000 ° C, which far exceeds the allowable temperature of the blade (850 to 900 ° C for normal blade material), and the heat load is about 1.5% of the output (about 6000k
W) and 1.2% (5000kW).

In order to set the pressure of the working gas to 22 to 25 ata, the compression ratio must be 22 or more. In this case, the discharge temperature of the compressor is about 500 ° C. When using (450 ° C.), it is necessary to cool the outer peripheral portion of the compressor rotor 2.

Therefore, in order to cool the outer peripheral portions of the first and second rotor blades and the compressor rotor with steam, a plurality of supply passages 74 for supplying steam to the disk joint portion 14 of the turbine rotor 1 in the axial direction. Are formed so as to pass through the three disks, and a recovery passage 72 is formed in the center of the rotor.

Further, between the distant piece 3 and the first-stage disc 11 and the discs 11 to 13, and between the last-stage disc 13 and the stub shaft 4, there are cavities 61, 62 and 63 on the outer peripheral side of the joint portion 14, and on the inner peripheral side. The cavity 64,
65, 66, 67 are formed, a steam flow path 75 is provided on one end of the supply flow path 74 so as to communicate with the cavity 67, and a cavity 61 is provided on the outer diameter side of the other end on the distant piece side. A steam flow path 76 and a steam flow path 77 are formed on the inner diameter side so as to communicate with each other, and a steam flow path 78 communicating with the cavity 63 is formed at the joint between the second-stage disk 12 and the final-stage disk 13. ing.

Further, steam passages 54, 55 and 56, 57 communicating with the cooling passages of the rotor blades 51, 52 are formed on the outer peripheral portions of the first-stage disc 11 and the second-stage disc 12 so as to open from the outer periphery to the side faces. A vapor passage 79 is formed between the first-stage disc and the second-stage disc so that the cavities 62 and 65 communicate with each other, so that the vapor passage 79 does not communicate with the supply passage 74 formed in the disc joint portion 14 described above. The short pipe 15 is attached.

On the other hand, a guide tube 41 is installed in the center hole formed in the stub shaft 4 and fixed by a flange 43. A steam flow path 44 is formed between the guide tube 41 and the inner wall of the center hole, and one end of the steam flow path is opened to the outside of the rotor as a steam supply port 45. Further, a steam flow path 42 is formed inside the steam flow path 44, one end of which is opened as a steam recovery port 46 to the axial center side from the steam supply port 45, and the other end is closely attached to the inner wall of the recovery flow path 72. It is installed to do.

On the other hand, the distant piece 3 is formed with a plurality of steam flow passages 31 each having one end communicating with the cavity 77 and the other end communicating with the cavity 23 on the outer peripheral side of the compressor disk 22. A passage 32 is formed.

FIG. 2 shows a view taken along the line XX of FIG. The same number of steam flow passages 55 as the number of blades 51 are formed in the outer peripheral portion of the disk 11, and the supply flow passages 74 and the steam flow passages 76 utilize the phases between the stacking bolts 16 fastening the rotor 1. Are arranged. In this figure, the supply flow path 74 is arranged so as to be included within the width of the steam flow path 79.
4 may be provided outside the width of the steam flow passage 79 to omit the short pipe 15.

In the steam flow path in the rotor configured as described above, the steam supplied from the steam supply port 43 at the axial end of the stub shaft into the rotor 1 is steam in the center hole of the stub shaft as shown by an arrow 90. Channel 44, cavity 67,
The supply flow path 74 flows in the axial direction via the steam flow path 75, and is divided into three systems in the axial flow process.

The first system is a steam system for cooling the two-stage rotor blade 52, which is supplied from the steam passage 78 through the cavity 63 and the steam passage 57 to the rotor blade, and after cooling, the steam passage 5
6 and flows into the cavity 62.

The second system is a steam system for cooling the first stage moving blade 51, which is supplied from the steam flow path 76 to the moving blade via the cavity 61 and the steam flow path 54, and after cooling, the steam flow path 5
5, it flows into the cavity 62, merges with the recovered steam of the first system, and flows through the steam passage 79 and the cavity 65 toward the recovery passage 72 in the center of the rotor.

The third system is a steam system for cooling the outer peripheral portion of the compressor rotor 2, and flows from the steam passage 77 through the cavity 64 and the steam passage 31 of the distant piece into the cavity 23 at the outer peripheral portion of the compressor rotor. After being supplied and after cooling the outer peripheral portion thereof, it passes through the cavity 24 on the side surface of the compressor rotor disk 21 or 22, the central hole 25 of the disk, the steam passage 32 in the central portion of the distant piece, and the recovery passage in the central portion of the turbine rotor. 72, and joins the steam after cooling the moving blades in the recovery flow path 72, and the steam flow path 42 in the guide pipe.
After that, it is recovered from the recovery port 46 to the outside of the rotor.

By the steam path described above, the low-temperature supply steam first flows through the supply flow path 74 formed through the disk, so that the temperature of the disk joint portion 14 forms the recovery steam flow path 79. Except for the joints, the temperature of the supplied steam is kept low. Therefore, the occurrence of thermal strain or thermal stress in the joint is reduced, the stability as a high-speed rotating body can be maintained, and the rotational force can be smoothly transmitted.

Further, since the recovered steam flows in the recovery passageway in the center of the rotor, most of the disk on the center side of the joint 14 is exposed to the high temperature steam and rises to almost the same temperature. In the case of the gas turbine whose working gas temperature is 1500 ° C. as described above, the steam temperature rise due to the heat load exceeds 200 ° C., but the steam temperature (250 ° C.) is lower than the allowable temperature of the disk (usually 450 ° C.). ), The temperature at the center of the rotor can be suppressed below the allowable temperature.

Further, the maximum stress due to the centrifugal force is generated in the central portion of the disk, but by maintaining the temperature of the joint portion 14 at a low temperature and raising the temperature only in the central portion, the distortion due to the thermal expansion of the portion is caused. Since the stress relieves the stress, the great advantage of reducing the centrifugal stress at the center of the disk is obtained.

Further, it is necessary to keep the temperature of the shaft of the bearing portion supporting the rotation as low as possible, but in the present invention, in order to flow the low temperature supply steam to the outside of the recovered steam in the central hole of the stub shaft 4, The temperature rise due to the recovery of steam can be minimized.

On the other hand, at least one side of the outer peripheral side surface of the disk is cooled by the low-temperature supply steam, so that the average temperature of the outer peripheral section of the disk is approximately the intermediate temperature between the supply steam and the recovered steam (about 350 ° C)
Therefore, even if the temperature distribution is taken into consideration, the recovery temperature will not be exceeded, and the temperature rise of the disk can be suppressed below the allowable temperature. Further, since the expansion due to the thermal expansion of the outer circumference of the disk in the radial direction can be minimized, it is possible to reduce the sealing clearance between the blade tip clearance 91 and the labyrinth seal 92 to contribute to the improvement of the efficiency of the gas turbine.

Further, the steam flow path 31 is provided in the distant piece.
And 32 to form the third steam system, it is possible to cool the outer peripheral portion of the compressor rotor by sharing the steam system of the turbine rotor with a simple structure. Can be used to increase the compression ratio,
As a result, it can contribute to raising the working gas temperature of the gas turbine.

On the outer peripheral portion of the distant piece 3,
Sealing air 94 is supplied to prevent the hot working gas from flowing out of the gas path 85 through the gap 93. Because this air is extracted from the compressor discharge,
The distant piece is heated similarly to the outer peripheral portion of the compressor, but the third steam system has an effect of uniformly cooling the distant piece.

FIG. 3 shows another embodiment according to the present invention. In this embodiment, the rotor is composed of a four-stage turbine, and steam is cooled up to the third-stage rotor blade.

The rotor 5 has four disks 16, 17, 1
8 and 19, which are sandwiched between the distant piece 3 and the stub shaft 4 and fastened at the joint portion 35. Moving blades 36, 37, 38 and 39 are planted on the outer circumference of the disks 16 to 19, and the moving blades 36 to 38 are cooled by having a steam flow passage inside.

Also in this case, the steam supply passage 33 penetrating the disc is formed in the joint portion 35, and the same vapor passages as those in the previous embodiment are formed for the first, second and final discs 16, 17 and 19. Form. Moving blade 38 that needs new cooling
With respect to the three-stage disc 18 that supports the above, the vapor passages 26 and 27 are formed in the outer peripheral portion of the disc, and the vapor passage 34 is formed in the joint portion 35 via the short pipe 20.
Cavities 29 and 30 are formed between the stage disc and the four-stage disc.

By constructing the above steam path, the steam supplied from the supply port 46 flows in the rotor along the path shown by the arrow 95, and the fourth steam cooling for the three-stage rotor blade 38 is carried out. As a system, the cavity 28 to the steam flow path 26
Steam is supplied to the moving blade via the steam flow path 27, the cavity 29, the steam flow path 34 and the cavity 30 to reach the rotor central portion, and the recovery path at the central portion is connected to another path. They are merged and recovered from the recovery port 45 at the shaft end.

That is, even in the four-stage turbine rotor,
The steam supply and recovery paths of the steam-cooled gas turbine can be constructed with the same concept as the three-stage turbine rotor, the stability of high-speed rotation can be maintained by lowering the temperature of the disk joint described above, and the centrifugal due to thermal expansion of the disk center part. Effects such as stress relaxation and reduction of temperature rise due to recovery of high temperature steam in the outer peripheral portion of the disk can be obtained.

FIG. 4 shows another embodiment in which the recovery flow path between the disks is further improved.

That is, the gas turbine rotor 6 is constructed by interposing the spacer 10 between the first-stage disc and the second-stage disc of the rotor shown in FIG.
It is housed in cavities 88 and 89 formed between them. A plurality of vapor flow channels 49 arranged in the circumferential direction are provided in the spacer 10 via a short pipe 70 so as not to communicate with a vapor supply flow channel 60 formed by penetrating a joint portion 96 of the disc and the spacer. Is formed, and the protrusion 4 is formed on the outer peripheral portion.
7 and 48 are formed.

Therefore, the steam supplied from the shaft end supply port 45 and after cooling the moving blades 51 and 52 flows out into the cavity 88 via the steam flow passages 55 and 56 on the outer periphery of the disk, and inside the spacer. It is recovered from the recovery port 46 via the vapor flow path 49 and the cavity 89.

Therefore, since the disk joint is not directly exposed to the high temperature recovered vapor, the joint can be maintained at a lower temperature and uniformly. Further, by forming the protrusions 47 and 48, the flow of the recovery steam on the side surface of the disk is deflected, so that heat transfer is suppressed and thermal stress is reduced.

Further, at the joint between the disk and the spacer, a vapor flow path 86 for connecting the supply flow path 60 and the cavity 88,
By forming 87, a part of the low-temperature supply steam flows out into the cavity 88 through the steam flow path and flows so as to crawl on the side surface of the disk forming the cavity. Instead, the outer wall 97 is cooled. Therefore, the temperature rise in the outer peripheral portion of the disk is further suppressed and the temperature distribution is smoothed, so that the thermal stress associated with the vapor recovery is further reduced.

Further, since the temperature of the recovered steam is lowered by mixing the low temperature steam with the high temperature recovered steam, if the mixing flow rate is set to an appropriate amount, it is possible to prevent the temperature rise of the disk especially when the temperature of the working gas is high. It can be effectively used for reducing thermal stress.

In order to supply steam to the rotating rotor blade, Cr ^{2 with} respect to the radius r of rotation, the angular velocity ω, and the flow rate G of steam is used.
The pumping power of ω 1 is required, and this power is recovered as the rotational power of the rotor in the process of flowing to the inner diameter side after cooling. The power recovered is determined by the outflow radius position of the outlet 50 of the steam flow path 49, and the recovery power increases as the radius decreases. Therefore, since the spacer is attached to reduce the outflow radius position, there is a great effect in reducing steam pumping power accompanying cooling.

Further, it is known that a large pressure loss of the flow occurs in the axial flow process of the disk center hole from the free vortex flow in the cavity. This pressure loss is affected by the strength of the vortex in the cavity, but since the vortex is weakened by installing a spacer to reduce the outflow radius position,
Mounting the spacer has a great effect on reducing pressure loss.

In the above embodiments, the case where the compressed air is used to generate the working fluid of the gas turbine has been described. However, even if other gases are used, the same applies as long as the moving blade is cooled by using steam. The effect of is obtained.

[0071]

As described above, according to the present invention, it is possible to recover the steam after cooling the moving blades by solving the problems associated with the recovery of the high-temperature steam as described above. Since the working gas can be cooled and the temperature of the working gas can be further increased, a steam-cooled gas turbine suitable for improving efficiency can be obtained.

[Brief description of drawings]

FIG. 1 is a cross-sectional view of the upper half of a steam-cooled gas turbine.

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

FIG. 3 is another embodiment of a steam cooled gas turbine rotor.

FIG. 4 is another embodiment of the steam cooled gas turbine rotor.

[Explanation of symbols]

1, 5, 6 ... Turbine rotor, 2 ... Compressor rotor, 10
... Spacers, 11, 12, 13 ... Disks, 14, 3
5, 96 ... Joined portion, 33, 60, 74 ... Supply channel, 3
8, 51, 52 ... Moving blades, 45 ... Steam supply port, 46 ... Steam recovery port, 61, 62, 63, 64, 65, 66, 67 ...
Cavities, 31, 32, 49 ... Steam flow paths, 47, 48
... Spacer protrusion, 72 ... Recovery flow path, 74, 79, 8
6, 87 ... junction vapor flow path.

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Shunichi Anzai 502 Jinritsu-cho, Tsuchiura-shi, Ibaraki Machinery Research Institute, Hiritsu Seisakusho Co., Ltd. Mechanical Research Laboratory (72) Inventor Nobuaki Kizuka 502 Jinritsucho, Tsuchiura City, Ibaraki Prefecture Hiritsu Manufacturing Co., Ltd.Mechanical Research Laboratory (72) Inventor Shinichi Higuchi, 502 Jinmachicho, Tsuchiura City, Ibaraki Hiritsu Manufacturing Co., Ltd.

Claims (10)

[Claims] 1. A gas turbine having a cooling system for cooling moving blades using steam, wherein the cooling system includes a supply system for supplying steam to the moving blades and a recovery system for collecting steam from the moving blades. A gas turbine, comprising: a recovery flow path of the recovery system formed inside a supply flow path of the supply system. 2. A gas turbine having a cooling system for cooling moving blades using steam, wherein the cooling system supplies steam to the moving blades, and a supply port formed at a rotor shaft end of the gas turbine, And a recovery port formed at the rotor shaft end of the gas turbine, the recovery port being formed closer to the rotor shaft center of the gas turbine than the supply port. And a gas turbine. 3. A gas turbine having a cooling system for cooling moving blades using steam, wherein a cavity formed between a stub shaft and a final stage disk of a rotor of the gas turbine, and the disk and the disk are joined together. A gas turbine characterized in that a steam supply passage is provided in a portion where the gas is supplied. 4. A gas turbine having a cooling system for cooling moving blades using steam, wherein the cooling system is a supply passage formed in a portion of a rotor of the gas turbine where disks are joined to each other. And a cavity formed between the first-stage and second-stage disks for collecting steam supplied to the first-stage moving blade and the second-stage moving blade. 5. A gas turbine characterized in that steam is used to cool a compressor rotor. 6. The gas turbine according to claim 5, wherein steam is supplied through a steam passage formed in a distant piece connecting the turbine rotor and the compressor rotor, and a shaft center is provided from the distant piece. A gas turbine, wherein steam is recovered through a steam flow path formed on the side. 7. A gas turbine for cooling a moving blade using steam, wherein the inside of a cavity formed between the disks of the gas turbine rotor is passed through a spacer portion between the disks. A gas turbine, characterized in that a steam flow path for collecting steam that has cooled the moving blade is formed in the gas turbine. 8. The gas turbine according to claim 7, wherein the spacer portion has a protruding portion that guides the recovered steam to the steam passage. 9. The gas turbine according to claim 8, further comprising a supply passage for supplying steam to a moving blade at a portion where the disks are joined to each other, and one of the steam in the supply passage is provided. A gas turbine, wherein a side surface of the disk is cooled by using a portion. 10. A steam turbine is used to cool three or four stages of moving blades, the combustion gas temperature is 1400 ° C. or higher, and the output is 4.
A gas turbine of 00 MW or more, wherein the temperature of the steam supplied to the moving blade is 250 ° C. or lower, and the temperature of the steam recovered from the moving blade is 450 ° C. or lower.