JP3303592B2 - gas turbine - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

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

[0002]

2. Description of the Related Art As a steam-cooled gas turbine, for example, as described in the literature ASME / IEEE /
E-Power Generation Conference (Jt.A
SME / IEEE Power Generation Conference)
As described in 7-JPGC-GT-1 (1987), there is a type in which steam provided for cooling is recovered and returned to a plant.

[0003]

However, the prior art cannot be said to specifically disclose the supply and recovery of steam when a steam-cooled gas turbine is employed as an actual plant.

It is an object of the present invention to provide a system for recovering steam in a cooling system.
Rotor bearings that smooth the rotation and support the rotation of the rotor
Minimize temperature rise due to cooling system steam recovery in the section
It is an object of the present invention to provide a gas turbine.

[0005]

SUMMARY OF THE INVENTION The present invention provides a method using steam.
Gas turbine with cooling system for cooling blades
The cooling system is provided at an end of a rotor shaft of the gas turbine.
A rotor shaft for the gas turbine, the supply shaft being formed;
A recovery port formed at an end, wherein the recovery port is the supply port
And formed at the rotor shaft center side of the gas turbine.
The recovery channel for recovering steam at the recovery port at the bearing
The gas turbine from the steam supply channel
Is formed on the center side of the rotor shaft.

A gas turbine according to the present invention includes a compressor for compressing air (atmosphere), a combustor for burning air and fuel compressed by the compressor to generate high-temperature combustion gas, and And a turbine for moving the blades with the combustion gas. In addition, a system for supplying steam to the turbine is provided.

In a combustor, a temperature of 1400 ° C. or higher, for example,
Combustion gas of 1350 to 1650 ° C. is generated, and the higher the temperature, the higher the output. In addition, the turbine is composed of three or four paragraphs combining a stationary blade and a moving blade.
Have a step.

The cooling system of the present invention includes a supply system for supplying steam to the rotor blades and a recovery system for recovering steam from the rotor blades, and the recovery passage of the recovery system is located inside the supply passage of the supply system. It is characterized by being formed in. Here, the steam is specifically generated by a steam generator, for example, a waste heat recovery boiler, and is a so-called steam containing H ₂ O as a main component.

The steam supply system according to the present invention refers to a system for supplying steam from a steam generator to a rotor blade of a turbine, and a part of the system has a supply passage. Here, the supply flow path is formed in the rotor of the turbine. The recovery system refers to a device that recovers and reuses steam from the rotor blades of the turbine, for example, a system up to a waste heat recovery boiler, a condenser, and the like, and has a recovery flow path in a part of this system. Here, the recovery flow path is formed toward the center of the rotor of the turbine. Further, the supply system or the recovery system may be considered from the rotor blade to the rotor shaft end of the turbine.

[0010] The cooling system of the present invention has a supply port formed at the rotor shaft end for supplying steam to the rotor blade and a recovery port formed at the rotor shaft end for recovering steam from the rotor blade. The recovery port is formed closer to the center of the rotor shaft than the supply port.

In this way, by passing the recovered steam through the central axis of the rotor from the supplied steam, thermal stress in the rotor and the like can be reduced, and stable turbine operation can be performed.

Further, the supply flow path is preferably formed in a cavity formed between the last stage disk of the rotor and the stub shaft, and in a portion where the disks are joined to each other. In addition, one recovery channel is used for the first stage and the second stage.
It is preferably formed between the disks of the stage, and it is preferable to use a cavity for collecting the steam supplied to the first stage blade and the second stage blade.

On the other hand, the present invention is characterized in that the compressor rotor is cooled using steam. This steam is supplied through a steam flow path formed in a distant piece connecting the turbine rotor and the compressor rotor, and is recovered through a steam flow path formed closer to the shaft center than the distant piece. You. By cooling the rotor of the compressor also with the steam, it is possible to effectively use the steam.

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

Further, it is preferable that the spacer section has a protruding portion for guiding the recovered steam to the steam flow path.
Thereby, steam can be collected more efficiently. In addition, by cooling the side surface of the disk using a part of the steam flowing through the supply flow path, thermal stress can be reduced.

On the other hand, the gas turbine of the present invention cools the rotor blades using steam and recovers the steam.
It employs a closed steam cooling system. The stage structure of the moving blade and the stationary blade has three or four stages, and the temperature of the combustion gas introduced into the turbine is 1400 ° C.
When the above class output is considered to be limited to those of 400 MW or more, the temperature of steam supplied to the moving blade at the temperature at each of the supply port and the recovery port is 250 ° C. or less, for example, 250 to
180 ° C and the temperature of steam recovered from the rotor blades is 450 ° C
Hereinafter, for example, by setting the temperature to 450 to 380 ° C., a steam cooling system can be achieved. It is also possible to operate the apparatus 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 permissible material temperature of the rotor blade, and the like. Further, it is determined by considering the steam flow rate and the allowable material temperature of the rotor.

By adopting such a configuration, the efficiency can be improved by 5 to 6% and the output can be improved by 13 to 16% over the gas turbine employing the open cooling system. In addition, more than conventional closed cooling system,
The efficiency can be improved by 0.8 to 1.2% and the output can be improved by 2 to 3%.

In other words, in order to recover the steam used for cooling the moving blades, it is preferable to form two steam paths of supply and recovery inside the rotor supporting the moving blades. In gas turbines whose temperature exceeds 1400 ° C, the temperature difference between the supplied steam and the recovered steam is more than 200 ° C. Therefore, it is necessary to carefully consider that the two systems do not cross each other and that they are high-speed rotating bodies. It is important to keep the temperature rise of the rotor due to steam below the allowable temperature limit, and to keep the thermal stress generated due to the temperature difference below the allowable stress.

Further, in order to increase the specific output (output per unit fuel) of the gas turbine, 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 increases. 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 forming a steam supply or recovery path in the rotor as a high-speed rotating body with little trouble.

Further, in the combined power generation plant in which the gas turbine and the steam turbine of the present invention are combined, the steam for the steam turbine is generated by using the exhaust heat of the exhaust gas of the gas 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.

For this reason, although the temperature of the working gas greatly exceeds the heat resistant temperature of the blade, it can be kept within the heat resistant temperature by the present invention.

Since steam is used as the refrigerant, it is necessary to consume extra compression power for increasing the flow rate of air as the refrigerant as the working gas temperature increases, as compared with the case where compressed air is used. Disappears. In addition, since the low-temperature air used for cooling is not released into the working gas flow path (hereinafter, gas path), the temperature of the working gas is not reduced due to dilution, and there is no problem that the output of the turbine is reduced. . Therefore, by using steam for cooling, efficiency can be improved as compared with a gas turbine using compressed gas for combustion as a refrigerant.

In the combined cycle power plant according to the present invention, a steam-cooled 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 using exhaust heat in order to avoid the accumulation of impurities in the moisture in the cooling passage. The heat transfer coefficient is larger than that of air (about 1.5 times), and the specific heat is large, so that the temperature rise when heat is applied is small (less than half of air).

In the steam cooling system, the flow rate of the steam to be cooled is preferably as small as possible in order to improve the efficiency of the whole plant, and the steam after cooling is not collected and discharged into the working gas. And does not affect the working gas,
Improve efficiency.

[0027]

[Function] Has a cooling system that cools the rotor blade using steam
In the gas turbine, the cooling system includes the gas turbine.
A supply port formed at a rotor shaft end of the bin, wherein the gas
A recovery port formed at a rotor shaft end of the turbine;
The recovery port is located between the supply port and the rotor shaft of the gas turbine.
It is formed on the core side, and the steam is collected at the recovery port by the rotor bearing.
The recovery flow path is the same as the flow path for the steam supplied from the supply port.
Formed at the center of the rotor shaft of the gas turbine.
This makes the flow of recovered steam in the cooling system smoother,
The rotation of the cooling system steam is
Temperature rise due to yield can be minimized.

Further, the supply port and the recovery port are provided at the shaft end of the rotor, and the recovery port is formed closer to the center of the rotor shaft than the supply port, so that the flow of the high-temperature recovery steam is more smoothly formed. The advantage of easy operation is obtained.

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

Further, a supply flow path is formed at a portion where the disks of the gas turbine rotor are joined to each other to supply steam, and the steam is supplied through a cavity formed between the first and second stage disks. By recovering, the temperature rise of the disk and the generation of thermal stress due to the high-temperature steam can be minimized and recovered.

Further, equipment for cooling the compressor rotor using steam is provided, and the equipment is supplied with steam through a steam flow passage formed in a distant piece connecting the turbine rotor and the compressor rotor. In addition, since the steam is recovered through the steam flow path formed closer to the shaft center than the distant piece, the compressor rotor can be cooled by sharing the steam flow path with the turbine rotor.

Further, in a gas turbine for cooling a rotor blade using steam, a spacer having a steam flow path for recovering steam is interposed between a disk of a rotor of the gas turbine and the disk. In addition to preventing the disc joint portion from being directly exposed to the recovered steam, the protrusion formed in the cavity formed between the spacer and the disc can also prevent the disc joint from being directly exposed to the recovered steam. By forming parts
The flow of the recovered steam on the outer peripheral side of the disk is deflected to weaken the heat transfer and reduce the thermal stress of the disk.

Further, in the gas turbine, a steam flow path is formed at a portion where the disk is joined to the disk, and a side surface of the disk is cooled by using a part of the steam in the steam flow path. In addition, since the side surface of the disk is effectively cooled by the discharged low-temperature steam, the temperature rise and the thermal stress are more effectively reduced.

[0034]

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

FIG. 1 shows the cross-sectional structure of the upper half of a gas turbine in the case of an air compression type three-stage turbine as an example. A compressor comprising a casing 80, a compressor rotor 2 and a cascade of outer peripheral portions, Vessel 84, stationary blades 81 to 83 and rotor blades 51 to 53
Are alternately arranged, and are formed by a gas path 85, a turbine rotor 1 and the like.

The turbine rotor 1 has three disks 11,
12, 13 and the stub shaft 4
And is closely bonded as a high-speed rotating body. Rotor blades 51 to 53 are implanted on the outer periphery of each disk, and are connected to the compressor rotor 2 via a distant piece 3, and are rotatably supported by bearings 40.

In this configuration, 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, thereby rotating the turbine rotor and generating power. Is done.

For example, if the working gas pressure at the combustor outlet is set to 2
When the temperature is set to 2 to 25 ata and the temperature is set to 1500 ° C., even a gas turbine having a rotor outer diameter of about 2.5 m generates power of 400 MW or more.
50 to 1300 ° C., the two stages are about 950 to 1000 ° C., which far exceeds the allowable temperature of the blade (850 to 900 ° C. for ordinary blade material), and the heat load is about 1.5% (about 6000k
W) and 1.2% (5000 kW).

Further, in order to set the pressure of the working gas to 22 to 25 at, it is necessary to set the compression ratio to 22 or more. In this case, the discharge temperature of the compressor becomes about 500 ° C., and the ordinary rotor material (allowable temperature) (450 ° C.), it is necessary to cool the outer periphery of the compressor rotor 2.

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

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

Further, on the outer periphery of the first stage disk 11 and the second stage disk 12, steam passages 54, 55 and 56, 57 communicating with the cooling passages of the moving blades 51, 52 are formed so as to open from the outer periphery to the side surfaces. A steam flow passage 79 is formed between the first-stage disk and the second-stage disk so that the cavities 62 and 65 communicate with each other, so as not to communicate with the supply flow passage 74 formed in the disk joint 14 described above. A short tube 15 is mounted.

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

On the other hand, a plurality of steam passages 31 are formed in the distant piece 3 such that one end communicates with the cavity 77 and the other end communicates with the cavity 23 on the outer peripheral side of the compressor disk 22. A passage 32 is formed.

FIG. 2 is a view taken along the line XX of FIG. The number of steam passages 55 on the outer peripheral portion of the disk 11 is equal to the number of rotor blades 51, and the supply passage 74 and the steam passage 76 use the phase between the stacking bolts 16 fastening the rotor 1. It is 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. However, if the flow path cross-sectional view can be sufficiently ensured, the supply flow path 7
4 may be provided outside the width of the steam channel 79, and the short pipe 15 may be omitted.

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

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

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

The third system is a steam system for cooling the outer peripheral portion of the compressor rotor 2, from the steam flow channel 77 to the cavity 23 at the outer peripheral portion of the compressor rotor through the cavity 64 and the steam flow channel 31 of the distant piece. After being supplied and 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, and the central steam passage 32 of the distant piece, and the recovery flow passage at the center of the turbine rotor. 72, and merges with the steam after cooling the moving blades in the recovery flow path 72 to form a steam flow path 42 in the guide pipe.
And is collected outside the rotor through the collection port 46.

Since the low-temperature supply steam flows first through the supply passage 74 formed through the disk by the above-described steam path, the temperature of the disk joint 14 is set to the recovery steam passage 79. Except for the welded part, the temperature is kept substantially at the low temperature of the supplied steam. Therefore, the occurrence of thermal distortion and thermal stress at the joint is reduced, and 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 through the recovery channel at the center of the rotor, most of the disk located closer to the center than the joint 14 is exposed to high-temperature steam and rises to almost the same temperature. In the case of a gas turbine having a working gas temperature of 1500 ° C., the temperature rise of the steam due to the heat load exceeds 200 ° C., but the steam (250 ° C.) having a temperature lower than the allowable temperature of the disk (usually 450 ° C.). If the steam of (1) is supplied, the temperature at the center of the rotor can be suppressed to an allowable temperature or lower.

The maximum stress due to the centrifugal force is generated at the center of the disk. However, by maintaining the temperature of the joining portion 14 at a low temperature and raising the temperature only at the center portion, the distortion due to the thermal expansion of the same portion is generated. However, there is a great advantage that the centrifugal stress at the center of the disk is reduced because the stress is reduced.

Further, it is necessary to keep the temperature of the shaft of the bearing part supporting the rotation as low as possible. However, in the present invention, in order to allow the low-temperature supply steam to flow outside the recovery steam in the center hole of the stub shaft 4. In addition, temperature rise due to steam recovery can be minimized.

On the other hand, since the outer peripheral side surface of each disk is cooled by low-temperature supply steam on at least one side of each disk, the average temperature of the outer peripheral portion of the disk is almost the intermediate temperature between the supply vapor and the recovery vapor (about 350 ° C)
Thus, even if the temperature distribution is considered, the temperature does not exceed the recovery temperature, and the temperature rise of the disk can be suppressed to an allowable temperature or less. In addition, since the elongation of the outer periphery of the disk due to radial thermal expansion can be minimized, the clearance between the rotor blade tip gap 91 and the labyrinth seal 92 can be reduced, thereby contributing to an improvement in gas turbine efficiency.

Further, the steam flow path 31 is provided in the distant piece.
And 32 to form the third steam system, the outer periphery of the compressor rotor can be cooled with a simple structure and shared with the steam system of the turbine rotor. Can be used to increase the compression ratio,
As a result, the working gas of the gas turbine can be increased in temperature.

On the outer periphery of the distant piece 3,
Seal air 94 is supplied to prevent hot working gas from flowing out of the gas path 85 through the gap 93. Because this air is extracted from the discharge part of the compressor,
The distant piece is heated in the same manner as 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 constituted by a four-stage turbine, and up to the three-stage moving blades are steam-cooled.

The rotor 5 has four disks 16, 17, 1
8 and 19, which are fastened at a joint 35 between the distant piece 3 and the stub shaft 4. Blades 36, 37, 38 and 39 are implanted on the outer circumference of the disks 16 to 19, and among them, the blades 36 to 38 are cooled with a steam flow path therein.

In this case as well, a steam supply passage 33 penetrating the disk is formed in the joint 35, and the first, second and final disks 16, 17, and 19 have the same steam flow path as in the previous embodiment. Form. Rotor blades 38 that require new cooling
The steam flow channels 26 and 27 are formed on the outer peripheral portion of the three-stage disk 18 supporting the gasket, and the steam flow channel 34 is formed at the joint 35 via the short pipe 20.
Cavities 29 and 30 are formed between the stepped disc and the four-stepped disc.

By configuring the above-described steam path, the steam supplied from the supply port 46 flows in the rotor along the path indicated by the arrow 95, and the fourth steam cooling for the three-stage bucket 38 is performed. As a system, the steam flow path 26
Through the steam passage 27, the cavity 29, the steam passage 34, and the cavity 30 to form a steam path extending to the center of the rotor. They are merged and collected from the collection port 45 at the shaft end.

That is, even in a four-stage turbine rotor,
The steam supply and recovery path of the steam-cooled gas turbine can be configured with exactly the same concept as the three-stage turbine rotor, maintaining the stability of high-speed rotation by lowering the temperature of the disk joint, and centrifuging by the thermal expansion of the center of the disk. Effects such as stress relaxation and reduction in temperature rise due to recovery of high-temperature steam from the outer periphery 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 constituted by interposing the spacer 10 between the first stage disk and the second stage disk of the rotor shown in FIG.
It is housed in cavities 88, 89 formed between them. In the spacer 10, a plurality of steam channels 49 arranged in the circumferential direction are connected via a short pipe 70 so as not to communicate with the steam supply channel 60 formed through the joint 96 between the disk and the spacer. Formed on the outer peripheral portion.
7 and 48 are formed.

Then, the steam supplied from the shaft end supply port 45 and cooling the moving blades 51 and 52 flows out into the cavity 88 through the steam passages 55 and 56 on the outer periphery of the disk, and flows into the cavity 88. The gas is recovered from the recovery port 46 via the steam flow path 49 and the cavity 89.

Therefore, since the disk joint is not directly exposed to the high-temperature recovered steam, the joint can be maintained at a lower temperature and more uniformly. Also, by forming the projections 47 and 48, the flow of the recovered steam on the side 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 steam flow passage 86 communicating the supply flow passage 60 and the cavity 88,
87, a part of the low-temperature supply steam flows out through the steam flow path into the cavity 88 and flows along the side surface of the disk forming the cavity. Instead, the outer wall 97 is cooled. Therefore, a rise in the temperature of the outer peripheral portion of the disk is further suppressed and the temperature distribution is smoothed, so that the thermal stress caused by the vapor recovery is further reduced.

Since the temperature of the recovered steam is lowered by mixing the low-temperature steam with the high-temperature recovered steam, setting the mixing flow rate to an appropriate amount can prevent the temperature of the disk from rising, especially when the temperature of the working gas is high. It can be effectively used to reduce thermal stress.

In order to supply steam to the rotating blades, Cr ^{2 with} respect to the turning radius r, the angular velocity ω, and the steam flow rate G
Although pumping power of ω is required, this power is recovered as rotational power of the rotor in the process of flowing to the inner diameter side after cooling. The power to be 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. Accordingly, since the outflow radius position is reduced by installing the spacer, there is a great effect in reducing steam pumping power accompanying cooling.

It is also known that a large flow pressure loss 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 and reducing the outflow radius position,
The mounting of the spacer has a great effect in reducing the pressure loss.

In the above embodiment, the case where compressed air is used to generate the working fluid for the gas turbine has been described. However, other gas may be used as long as the moving blades are cooled using steam. The effect of is obtained.

[0071]

According to the gas turbine of the present invention, the cooling system
Smooth the flow of recovered steam and support the rotation of the rotor
Temperature based on the recovery of steam in the cooling system at the rotating rotor bearing
It has the effect of minimizing the rise
You.

[Brief description of the drawings]

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

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

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

FIG. 4 shows 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 ... joint, 33, 60, 74 ... supply flow path, 3
8, 51, 52: moving blade, 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 channel, 74, 79, 8
6,87 ... Junction steam flow path.

Continued on the front page (72) Inventor Shunichi Anzai 502, Kandate-cho, Tsuchiura-shi, Ibaraki Pref. Machinery Research Laboratory, Hitachi, Ltd. (72) Inventor Masami Noda 502, Kantate-cho, Tsuchiura-shi, Ibaraki Pref. ) Inventor Noriaki Kitzuka 502, Kandate-cho, Tsuchiura-shi, Ibaraki Pref., Machinery Research Laboratory, Hitachi, Ltd. (72) Inventor Shinichi Higuchi 502, Kantate-cho, Tsuchiura-shi, Ibaraki Pref., Machinery Research Laboratory, Hitachi, Ltd. 3-275946 (JP, A) JP-A-54-13809 (JP, A) JP-A-63-134823 (JP, A) JP-A-61-226502 (JP, A) U.S. Patent 3,443,790 (US, A) ( 58) Field surveyed (Int.Cl. ⁷ , DB name) F02C 7/16 F01D 5/08

Claims (2)

(57) [Claims] 1. A cooling system for cooling a rotor blade using steam.
The cooling system is formed at a rotor shaft end of the gas turbine.
And a recovery port formed at the end of the rotor shaft of the gas turbine.
The recovery port is disposed between the supply port and the rotor of the gas turbine.
The recovery passage formed at the shaft center side and for recovering steam at the recovery port by the rotor bearing portion is
The gas turbine is supplied from a supply passage of steam supplied from a supply port.
Gas formed on the center side of a rotor shaft of a bottle
Turbine. 2. The apparatus is mounted on the outer periphery of a disk by using steam.
Gas Turbine with Cooling System for Cooling Rotor Blade
The cooling system has a supply flow path penetrating the disk.
A supply system for supplying steam to the moving blade,
And a recovery system for recovering steam from the disk.
So that the recovery flow path of the recovery system is
The supply system is formed inside the supply passage of the
A supply port formed at a rotor shaft end of the gas turbine , wherein the recovery system is formed at a rotor shaft end of the gas turbine.
The gas inlet of the gas turbine from the supply port.
The recovery passage formed at the shaft center side and for recovering steam at the recovery port by the rotor bearing portion is
The gas turbine is supplied from a supply passage of steam supplied from a supply port.
Gas formed on the center side of a rotor shaft of a bottle
Turbine.