JPH11117702A - Gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a refrigerant recovery type gas turbine which forms cooling channels well suited for the supply and recovery of refrigerant for moving blades, in the inside of turbine rotor. SOLUTION: With this gas turbine, moving blade refrigerant supply paths 70a, 70b (70) and recovery paths 71a, 71b (71) are formed on the outer peripheral side from a hub of a turbine rotor 6, and the refrigerant supplied from the shaft end is supplied to a moving blade 5 through the supply paths. The refrigerant is recovered to the combustion chamber side after cooling, while the air extracted by compression is supplied from the center side of the turbine rotor through a slit 74 formed in the hub to cool the after-stage moving blades or the outer wall of the rotor, to reduce the thermal stress of the rotor 6 and the pressure loss of the refrigerant channels 70, 71, and to cool the higher stage side of a compressor rotor.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine for cooling rotor blades using a refrigerant, and more particularly to a refrigerant recovery type gas intended to supply the refrigerant from the shaft end and recover the cooled refrigerant. Related to turbines.

[0002]

2. Description of the Related Art The blades of gas turbines are usually cooled by air supplied through the interior of a rotor to protect them from high-temperature combustion gases. As the air source, a part of the compressed air for combustion is usually used, and after cooling, it is discharged to a passage of a combustion gas (hereinafter, abbreviated as a gas path).

The efficiency of a gas turbine increases as the temperature of the combustion gas increases. However, since the heat load increases by increasing the temperature, the flow rate of the cooling air naturally increases. When this air is released into the gas path, not only does the temperature of the combustion gas drop, but also the flow of the gas path becomes turbulent, lowering the aerodynamic performance of the turbine. Further, the refrigerant flowing through the rotary flow passage in the rotor has a swirling energy proportional to the square of the radius. However, when this refrigerant is discharged from the rotor blades arranged on the outer periphery of the rotor, a large pumping power loss occurs, resulting in a loss. Increases in proportion to the refrigerant flow rate. Therefore,
Simply increasing the temperature of the combustion gas does not provide an effective improvement in efficiency.

Therefore, in order to further improve the performance, it is necessary to recover the air used for cooling the blades in order to solve the above-mentioned problems.

For this reason, for example, in Japanese Patent Application Laid-Open No. 54-13809, a supply / recovery path for the refrigerant is formed by piping inside the rotor, and in Japanese Patent Application Laid-Open No. 3-275946, There has been proposed a method of configuring a supply / recovery path of the fuel.

[0006]

In order to constitute a refrigerant recovery type gas turbine, a supply flow path for supplying a moving blade refrigerant to the inside of a turbine rotor and a recovery path for recovering the cooled refrigerant are provided. It is necessary to form a channel. However, since the temperature of the refrigerant is increased by cooling the blades, a thermal stress due to the temperature difference of the refrigerant is generated in the rotor component in which the supply channel and the recovery channel coexist.

In a gas turbine with a combustion gas temperature of 1500 ° C., the temperature of the refrigerant rises by 200 to 250 ° C., so that an excessive thermal stress exceeding the allowable value of the material is generated depending on the configuration of the flow path. Therefore, in order to realize a highly efficient refrigerant recovery type gas turbine by increasing the temperature of the combustion gas, one of the major issues is how to reduce the thermal stress in the supply and recovery refrigerant flow paths inside the rotor.

Further, in an air-cooled refrigerant recovery type gas turbine that cools the blades by using a part of the compressed air for combustion and recovers the cooled air to the combustor, the recovery pressure is set to at least the discharge pressure of the compressor. It is necessary to raise it more than pressure. For this reason, the refrigerant will be pressurized by the boost compressor before supply,
If the flow rate of the refrigerant is increased to raise the temperature, the compression power of the boost compressor is inevitably increased, which greatly affects the efficiency of the entire gas turbine system. Therefore, in order to obtain the expected high efficiency, it is necessary to devise a flow path configuration capable of minimizing the pressure loss of the refrigerant flowing in the rotor. These points are not considered in any known examples.

SUMMARY OF THE INVENTION It is an object of the present invention to provide an efficient refrigerant recovery type gas turbine by reducing thermal stress and pressure loss in a rotor.

[0010]

SUMMARY OF THE INVENTION The present invention provides a compressor for discharging compressed air, a combustor for burning the compressed air and fuel, and a turbine rotor driven by combustion gas supplied from the combustor. A turbine having a moving blade and a stationary blade disposed on the outer peripheral side of the rotor and having a refrigerant flow path, and a turbine connected to the compressor. And a first refrigerant flow path through which a first refrigerant to be supplied to a first rotor blade positioned on the most upstream side flows, and is extracted from the compressor and passes through a connection portion between the compressor and the turbine. And a second refrigerant flow path through which the second refrigerant flows and is supplied to the rotor blade on the most downstream side of the rotor blade having the refrigerant flow path.

For example, a first rotor supplied from the shaft end into the rotor and supplied into a first rotor blade located on the most upstream side.
A first refrigerant flow path through which the refrigerant flows, and a second air flow extracted from the compressor, supplied through the connection portion between the compressor and the turbine, and located on the last stream side of the rotor blade having the refrigerant flow path. And a second refrigerant flow path through which a second refrigerant having a lower pressure than the first refrigerant flows and which is supplied into the second moving blade. Also, for example, in the rotor,
A first refrigerant flow path through which a first refrigerant is supplied from a shaft end and supplied into a first rotor blade located on the most upstream side; The second refrigerant, which is supplied through the connection portion and is supplied to the second moving blade located on the last stream side of the moving blade having the refrigerant flow path and in which the second refrigerant having a higher temperature than the first refrigerant flows, And a refrigerant flow path. Even in a gas turbine having moving blades arranged under gas conditions such as a large temperature difference between the front stage and the rear stage, by optimally supplying or recovering different refrigerants, thermal stress is reduced and pressure loss is reduced. Good cooling is possible while reducing the amount of water.

Alternatively, a compressor for discharging compressed air, a combustor for burning the compressed air and fuel, and a turbine driven by a combustion gas supplied from the combustor and arranged on an outer peripheral side of the rotor. And a turbine having a moving blade and a stationary blade having a refrigerant flow path, and a turbine connected to the compressor.
A first refrigerant introduced from the other end of the rotor toward the end of the compressor, and a refrigerant formed on the most upstream rotor blade. A first refrigerant flow path communicating with the flow path, and a refrigerant recovery path for supplying the first refrigerant after cooling the rotor blades to compressed air discharged from the compressor; A path for supplying the second refrigerant extracted from the compressor to the compressor side end of the rotor is provided at a connection between the compressor and the turbine,
In the rotor, the second refrigerant introduced from the compressor side end flows toward the other end side of the rotor, and communicates with the refrigerant flow path formed in the second-stage bucket from the downstream side. In addition to disposing a second refrigerant flow path, the moving blade includes a discharge unit that discharges the supplied and heated second refrigerant into the combustion gas flow.

[0013] This can further reduce the complexity of the flow path configuration and reduce the flow rate of the high-pressure first refrigerant supplied to the compressed air discharged from the compressor. The efficient operation can be performed while suppressing the pressure loss caused by the supply and recovery of the refrigerant.

Alternatively, a compressor for discharging compressed air, comprising a compressor rotor, rotor blades and stationary blades arranged on the outer periphery of the rotor, a combustor for burning the compressed air and fuel, A turbine driven by combustion gas supplied from the compressor, having a moving blade and a stationary blade, and being connected to the compressor. A plurality of disks are arranged, and a disk is formed in a region including the shaft core portion of the rotor with a gap between the disk and an adjacent disk, and an annular connection is formed in contact with the disk adjacent to the outer peripheral side of the region including the shaft center portion. A bleed port that supplies a part of the compressed air flowing through the compressor into the rotor, and a disk downstream of the disk on which the bleed port is formed, wherein the outer peripheral portion is formed from the contact portion or the contact portion. The gas extracted from the extraction port To form a compressor cooling flow path, a communication passage communicating said gap with said cooling channel,
On the downstream side of the disk on which the bleeding port is formed, a communication hole communicating with each of the gaps is formed in a region including the shaft core of the rotor, and flows through the compressor cooling flow path or the gap. A path for supplying the extracted air to the turbine is provided at a connecting portion between the compressor and the turbine, and the extracted air flowing through the connecting portion is provided as a cooling medium to a second-stage moving blade from a downstream side of the turbine in the turbine. A path for supplying another refrigerant to a downstream end of the turbine, and a path for guiding the other refrigerant as a cooling medium to the most upstream rotor blade of the turbine. Features.

[0015] Thus, by optimally supplying or recovering different refrigerants, thermal cooling can be suppressed and good cooling can be performed while reducing pressure loss. Further, a high-temperature region, such as a high-pressure section on the downstream side, of the blade cascade of the high-temperature compressor can be efficiently cooled.

[0016]

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

FIG. 1 shows a cross-sectional structure of the upper half of a closed air-cooled four-stage gas turbine, in which a casing 1, a compressor 2, a combustor 3, and a stationary blade 4 are arranged.
And turbine 10 having rotor blades 5, turbine rotor 6, and the like
0, a bearing 8 and an exhaust duct 9.

The moving blade 5 is supported on the outer periphery of the turbine rotor 6, and has a shape corresponding to the heat load inside the first to third moving blades so as to withstand the heat load of the combustion gas flowing through the gas path 91. Are formed.

The turbine rotor 6 has four disks 61a to 61d on which moving blades are implanted and three spacers 62a to 62d.
c and the shaft 63 are fastened by bolts at the hub portion.
Are connected to the rotor. Distant piece 64,
Center holes 65a to 65d are formed in the first and second stage disks 61a and 61b and the shaft 63, respectively, and the third and fourth stage disks are solid.

At the hub of the rotor, 4
A plurality of supply main flow paths 66 penetrating in the axial direction up to the stage disk, a distant piece 64, and a first stage disk 61a
A plurality of recovery main flow paths 67 penetrating through the ス ペ ー サ spacers 62 a are formed in the circumferential direction. Supply main channel 6
One end of 6 is in communication with the shaft center hole 65d on the downstream side of the rotor via the inner cavity 68b at the rear of the fourth-stage disk 61d and the supply slit 70c, and one end of the recovery main flow path 67 is provided with seals 32a and 32b. It is open to the partitioned wheel space 31a.

The distant piece 64, the first stage disk 61a, the second stage disk 61b, and the 2/3 spacer 6
Supply slits 70a and 70b,
A recovery slit 7 is provided at both ends of the half-spacer hub.
1a and 71b are formed, one end of the supply slit 70 communicates with the supply main flow path 66, one end of the recovery slit 71 communicates with the recovery main flow path 67, and the other ends of the cavities 69a to 69d outside the hub and the outer periphery of the disk. It communicates with the cooling channel 51 of the rotor blade through the supply hole 72 and the recovery hole 73 of the section.

Further, a bleeding system slit 74 is formed in the hub joint portion between the 2 / 3-stage spacer and the three-stage disk so as to radially communicate the inner cavity 68a and the outer cavity 69e of the hub connected to the center hole 65c. I have.

On the other hand, the rotor of the compressor 2 has rotor blades 21 on its outer periphery.
, And a bleed port 23 is formed at the root of a moving blade of a specific stage selected from the intermediate stages. The disk upstream of the air extraction port 23 is solid, and the disk downstream of the air extraction port 23 is formed with a center hole 28 which is a communication hole communicating the gap between the disks. Are communicated through an outer cavity 24, a plurality of slits 26, and an inner cavity 27. The outer cavities 24 are communicated with each other outside the hub by communication holes 25 which are communication flow paths.

FIG. 2 is a view taken in the direction of arrows XX in FIG.
The supply main flow path 66 and the recovery main flow path 67 are alternately formed at intermediate positions of a plurality of bolt holes 75 arranged in the circumferential direction of the hub. It can also be seen that the number of supply holes 72 and the number of recovery holes in the outer peripheral portion of the disk are equal to the number of blades.

FIG. 3 is a view taken in the direction of arrows Y--Y in FIG.
The bleeding system slits 74 are alternately arranged in the circumferential direction with the supply main flow path.

The refrigerant supplied from the end of the shaft 63 of the turbine rotor 6 upon activation of the gas turbine passes through the coaxial center hole 65d, the cavity 68b on the rear side of the four-stage disk, and the slit 70c, and is axially connected to the disk. It is introduced into the supply main channel 66 formed in the hub so as to penetrate the spacer (arrow 92a).

A part of the refrigerant introduced into the supply main flow path 66 is supplied to the two-stage rotor blade through the slit 70b, the cavity 69d and the supply hole in the outer periphery of the disk (arrow 92).
b) After cooling the blades, the blades are guided to the recovery main flow path 67 through the recovery hole in the outer peripheral portion of the disk, the cavity 69c on the front side of the disk, and the recovery slit 71b (arrow 92c), and are discharged from the discharge port 76 of the distant piece hub. Space 31
After being discharged to a, it is recovered to the combustor side through the recovery hole 33 of the inner barrel (arrow 92f). And it is supplied to a combustor with compressor discharge air.

The remaining refrigerant except for the two-stage moving blade is supplied to the cooling passage 51 of the first-stage moving blade 5 through the supply slit 70a, the cavity 69a on the front side of the first-stage disk, and the supply hole 72 on the outer periphery of the first-stage disk ( After cooling the blades (arrow 92d), the blades are guided to the recovery main flow path 67 through the recovery hole 73, the cavity 69b on the rear side of the disk, and the recovery slit 71a at the hub junction (arrow 92e), and in the case of a two-stage bucket. Similarly to the above, the gas is recovered from the discharge port 76 to the combustor via the wheel space 31a. That is, the refrigerant for the first rotor blade flows so as to go around the outside of the disk, and two types of refrigerant, supply and recovery, pass through the hub.

On the other hand, the refrigerant extracted from the extraction port 23 in the outer peripheral portion of the compressor at the intermediate stage of the compressor is almost uniformly distributed to the cavity 24 on the downstream side of the hub by the communication hole 25, and then the slit 26, After merging at the disk center hole 28 through the cavity 27 inside the hub, it flows into the center of the turbine rotor through the center hole 65a of the distant piece (arrow 93a). In the turbine rotor, it is supplied to the cooling passage inside the three-stage moving blade via the disk center holes 65b and 65c, the cavity 68a, the bleeding system slit 74 and the cavity 69e on the outer periphery of the hub, and is discharged into the gas path 91 after cooling the blade. (Arrow 93b).

As described above, by forming the refrigerant supply system from the shaft end and the bleed refrigerant system from the compressor in the rotor, the hub located at the intermediate radius of the rotor serves as the axial passage for the blade refrigerant. The outer diameter side is a communication passage with the blade, and the inner diameter side is a bleed refrigerant environment from the compressor. The final stage solid disk 61d partitions the shaft end supply flow path 68b and the bleed flow path 68a at the center of the rotor. This makes it possible to simply configure the three refrigerant flow paths of supply, recovery, and bleed without intersecting.

In addition, a basic flow path for supplying and recovering the moving blade refrigerant is formed in a hub portion to which a disk, a shaft and the like are joined, and the main flow path is communicated with a supply port at the shaft end. Along with opening the recovery main flow path to the first stage side foil space,
A supply slit and a recovery slit were formed at the joint of the hub such that one end communicated with each of the supply and recovery main flow paths. Further, a slit communicating with the disk center hole was formed in a hub joint of a three-stage disk having a three-stage blade on the final flow side of the blade having a refrigerant flow path. In such a configuration, the refrigerant supplied from the shaft end supply port is supplied to the rotor blades at a stage preceding the third stage through the supply main flow path and the supply slit, and the cooled refrigerant is supplied to the recovery slit and the recovery main flow path. Through the combustion chamber. Further, compressed air at an intermediate temperature between the supply refrigerant and the recovered refrigerant is extracted from the compressor, and this air is supplied to the three-stage rotor blades via the disk center hole and the slit of the n-stage disk.

With this arrangement, the hub located at the intermediate radius of the rotor is used as an axial passage for the blade refrigerant, the outer diameter side is used as a communication passage with the blades, and the inner diameter side is used as the temperature environment for the extracted refrigerant from the compressor. By dividing the shaft end supply flow path and the bleed flow path at the center of the rotor by the last stage disk, the structure can be simplified without intersecting the three refrigerant flow paths of supply, recovery and bleed. Reduction of thermal stress in steady and unsteady states, cooling of the compressor rotor, recovery of refrigerant, and the like can be more effectively exhibited.

It is known that a large pressure loss occurs in the rotor center hole due to the flow of the vortex before the hole flows into the rotor. , The pressure loss is small and the boost compression power of the refrigerant can be minimized.

The parts leaking along the path may include a shaft end supply part, a joint part between the disk and the spacer on the outer periphery of the outer cavity 68, a fitting part between the disk and the moving blade, and a seal 32b of the wheel space 31a. The leakage from the joints and fittings can be prevented by the contact surface seal, and the refrigerant leaked from the seal 32b can be used as seal air for preventing the combustion gas from leaking from the gas path into the wheel space 31b. Most of the used refrigerant can be efficiently recovered.

Further, since the rotational radius position of the discharge port 76 can be configured to be at least one half or less of the radial position of the rotor blade,
Pumping power loss due to refrigerant discharge can be reduced to one-fourth or less of the conventional case.

Further, the refrigerant extracted from the compressor is caused to flow in parallel through flow paths 24 to 28 formed on the side surface of the disk, and is guided to the center of the turbine rotor 6 via the distant piece 64, thereby increasing the compressor high stage. The disk on the side can be cooled uniformly, and the distant piece heated by the recovered refrigerant from the outer periphery can be cooled from the inside. For this reason, it is possible to increase the compressor discharge pressure without significantly increasing the heat resistance of the rotor material. Further, if the temperature of the extracted refrigerant is set to an intermediate temperature between the shaft end supply refrigerant and the recovered refrigerant, the low temperature portion around the shaft end supply main flow passage 66 formed in the hub is heated and recovered around the shaft end supply main flow passage 67. Cooling acts on the high-temperature portion, and a function of alleviating the level of the rotor temperature distribution works, thereby reducing the thermal stress.

Further, since it is not necessary to recover the extracted refrigerant, the boost compression power can be saved, and the advantage that the size of the compressor can be reduced can be obtained.

However, in the center hole of the disk, a pressure loss occurs due to the above-mentioned vortex flow before the hole enters, and the amount of loss largely depends on the flow rate. As a result, the flow rates of the individual flow paths are reduced, so that the pressure loss is also reduced, and the supply pressure to the three-stage moving blade can be sufficiently ensured.

Furthermore, when the gas turbine is started, the high temperature combustion gas flows through the gas path 91 at the same time as the ignition, so that the temperature on the rotor outer peripheral side rapidly rises due to the influence of the heat load from the gas path and the heat transfer area. . For this reason, a larger stress is generated in the central portion of the rotor where the temperature rise is gradual, but in this embodiment, the air extracted from the compressor flows simultaneously with the start of the central portion of the rotor and the air flows uniformly from the compressor. Therefore, a great effect can be obtained in reducing the unsteady thermal stress at the time of starting. In addition, since the state quantity such as the flow rate and the temperature of the refrigerant supplied from the shaft end can be manipulated outside the machine, it is possible to minimize the unsteady thermal stress of the rotor by the supply delay means or the like.

The reason that the refrigerant for the first stage rotor blades is supplied from the front side of the disk is to cool the same portion by flowing a low-temperature refrigerant to the hub and the front side of the first stage disk. In addition, the temperature of the disk hub becomes approximately the average temperature of the supplied refrigerant and the recovered refrigerant, and the temperature rise can be maintained at a lower temperature than when only the recovered refrigerant flows from the rear side of the disk to the hub. However, 1
Although the temperature outside the / 2 stage spacer rises to near the recovery temperature, no axial temperature gradient is formed, the outer periphery is cooled by the seal air, the hub is cooled by the first stage cooling supply refrigerant, and the rotor blades are centrifuged. Stress is less of a problem than a disk because the centrifugal load of the spacer is smaller than that of the loaded disk.

Further, by supplying the refrigerant from the front side of the rotor blade to the internal cooling passage 51, a temperature difference between the refrigerant and the combustion gas flowing through the gas path 91 is effectively formed for cooling, so that the cooling efficiency of the blade is improved. It is also effective in raising.

Next, from the viewpoint of the pressure loss, the flow path is formed so that the length of the flow path from the shaft end to the combustion chamber bypassing the cooling flow path of the rotor blade is reduced as much as possible. In addition, the center hole flow path having a large pressure loss is avoided.
Therefore, the pressure loss in the passage is small, and the boost compression power of the refrigerant can be minimized.

However, in the center hole 28 of the compressor disk, the swirling speed of the vortex is increased while the refrigerant flowing out of the slit 26 of the hub flows inward through the cavity 27, and the energy of the swirling speed is increased by the axial flow of the center hole. Although the pressure loss occurs in the process, a pressure loss occurs. However, in the embodiment, since the flow is divided and the flow rate of each flow path is reduced, the swirling component is attenuated by the friction of the wall surface in the process of flowing through the cavity 27. For this reason, pressure loss in the center hole is small. Therefore, on the high stage side, a sufficient supply pressure to the three-stage bucket can be ensured regardless of the bleed stage.

As the flow path configuration in the case where no air is extracted from the compressor, it is most effective in terms of high efficiency to recover the entire amount of the moving blade refrigerant and reduce the loss due to the discharge of the refrigerant to the gas path. However, in this case, it is necessary to boost-compress the entire amount of the refrigerant. On the other hand, in the present embodiment, the refrigerant of the three-stage rotor blade is discharged to the gas path, so that the efficiency of the gas turbine is reduced by this amount. However, the refrigerant is discharged because boost compression power is not required. The loss is replaced.

By forming as in the present embodiment, a good refrigerant can be obtained while suppressing the amount of the refrigerant requiring compression to a small amount and reducing the required power.

As can be seen from the refrigerant paths for the first stage rotor blade and the second stage rotor blade, the turbine rotor is exposed to the high-temperature recovered refrigerant outside the hub shown in the area A and in front of the two-stage disk. Limited to a small area. However, about half of the refrigerant wetting surface in the area is exposed to the low-temperature supply refrigerant.

On the other hand, since the refrigerant extracted from the compressor flows from the compressor rotor to the region B at the center of the turbine rotor, the members included in the region are exposed to the environment of the extracted refrigerant. The area C consisting of the 2/3 step spacer and the outside of the 3 step disk is a section exposed to the supply refrigerant and the bleed refrigerant, and the area D behind the remaining 3/4 step spacer is mainly exposed to the low temperature supply refrigerant. Is done.

Thus, as an example, when a refrigerant at 230 ° C. is supplied from the shaft end and compressed air at 370 ° C. is extracted from the compressor, the recovery temperature after cooling the blades with a 1500 ° C. class gas turbine becomes 450 ° C. to 500 ° C. Rise. Accordingly, the average temperature of the members in the region A exposed to the supply refrigerant and the recovered refrigerant rises to 340 ° C. to 365 ° C., the average temperature of both refrigerants, and the members in the region D exposed only to the supply refrigerant The temperature rises to around 220 ° C. of the supply refrigerant.

On the other hand, the temperature of the member in the region B where the extracted refrigerant flows rises to around 370 ° C. of the extracted refrigerant, and the temperature of the member in the region C is approximately 300 ° C. of the average temperature of the extracted refrigerant and the supplied refrigerant.
Rise and fall. In addition, since the distant pieces are heated by the recovered refrigerant from the outer circumference and the bleed refrigerant from the inner circumference,
The average temperature of both increases to 410-430 ° C.

That is, if the shaft end supply refrigerant at 230 ° C. and the compressor bleed air at 370 ° C. are used as the blade cooling refrigerant,
It is possible to configure a rotor internal refrigerant flow path in which the average temperature of the rotor is approximately 430 ° C. or less.

The temperature distribution in the axial direction of the hub is in the regions A, C,
It changes in the downward direction to D, and there is little change in elevation even if a partial change in each area is included. This is effective in minimizing the difference in elongation of the hub joint in the radial direction and reducing the stress in the fitting part.

The center portion of the disk is a section where the maximum centrifugal stress is generated by the high-speed rotation. By making the temperature of the center portion higher than the outer diameter side, the centrifugal stress is reduced by thermal expansion. As described above, the temperature of the hub portion is approximately the intermediate temperature between the supply refrigerant and the recovered refrigerant, so if the temperature of the bleed air from the compressor is increased to the intermediate temperature or higher, the temperature of the hub is increased by the bleed refrigerant at the center of the rotor and higher than that of the hub. Becomes Therefore, if the bleeding temperature is appropriately selected, the effect of reducing the stress in the same portion can be obtained. At this time, since the temperature of the bleed air is determined by the stage position of the bleed port 23, the bleed stage that is most effective in reducing the thermal stress should be selected for the configuration of the refrigerant flow path formed inside the rotor.

In this embodiment, the bleed path indicated by the arrow 93b is formed on the front side of the three-stage disk, but the disk may be formed with a center hole and supplied to the three-stage blade from the rear side. Formed on the front side is a cavity 68c in which the refrigerant does not flow between the disks, and reduces the thermal stress generated on the side surface of the central portion of the fourth stage disk 61d due to the temperature difference between the shaft end supply refrigerant and the bleed refrigerant. If the temperature difference between the coaxial end supply refrigerant and the bleed refrigerant can be reduced in terms of reducing the thermal stress of the entire rotor, even if the bleed path is formed on the rear side of the three-stage disk, it is the same as described above, and is equivalent. The effect of is obtained.

In the embodiment described above, the spacer is provided between the disks in order to reduce the stress by shortening the axial span of the disk hub and the outer peripheral rim. However, the paragraph span of the turbine can be shortened. In such a case, the spacer may be omitted.

FIG. 4 shows a cross-sectional structure of a turbine rotor having a cooling passage without a spacer.
The rotor 10 includes disks 11a to 11d and a shaft 63, and is connected to the compressor rotor via a distant piece 64 on the first stage side. The disks from the first stage to the third stage are formed with a center hole 19, and the four-stage disk is formed solid, and the rotor blades 5 are implanted on the outer periphery of the disk. Has been cooled from.

Also in this case, the supply main flow path 12 and the recovery main flow path 13 of the hub can be formed in the same manner as in the previous embodiment. However, since there is no spacer, the supply slits 14a, 14b, the recovery slit 15, and the bleeding system slit 16 from the compressor are formed between the hub joints of the disk 11, and in particular, the recovery slit 15 is formed between the first stage rotor blade and the second stage rotor blade. Commonly used for recovery of the moving blade refrigerant.

In such a flow path configuration, a part of the refrigerant supplied from the shaft end and introduced into the supply main flow path 12 is supplied to the two-stage moving blade via the supply slit 14b and the outer disk cavity 17c, and the remaining. Refrigerant supply slit 17
a to the first stage rotor blade via the front side of the disk. Then, after merging in the cavity 17b, the gas is recovered to the combustion chamber side via the recovery slit 15 and the recovery main flow path 13. On the other hand, the refrigerant extracted from the compressor flows into the center hole 19 of the turbine rotor via the distant piece, and is supplied to the three-stage rotor blades via the inner cavity 18, the extraction slit 16 and the outer cavity 17d.

In this case, the same effects as those of the previous embodiment can be obtained with respect to reduction of steady and unsteady thermal stress and pressure loss, cooling of the compressor rotor, and the like. There is an advantage that can be simply configured.

The third stage rotor blade may have a solid structure, and the other may have a hollow structure.

The difference from FIG. 1 and the like is that the refrigerant flowing through the center hole 65d is not introduced into the supply main flow path 66 through the cavity 68b and the slit 70c on the rear side of the four-stage disk, but the center hole is formed in the four-stage disk. And the refrigerant flowing through 65d is introduced into the supply main passage 66 through the center hole of the fourth-stage disk 61d, through the slit from the cavity 68c formed between the third-stage disk and the fourth-stage disk, and through the slit. It is.

The specific configuration of the rotor is as follows.

A coolant passage (first coolant passage) supplied from the shaft end uses a center hole at the center of the disc as a first through passage configured to penetrate the axis of the four-stage disc. Further, a cavity and a slit (first communication path) are formed between the fourth-stage disk and the adjacent three-stage disk, and are configured so that the refrigerant flowing through the center hole flows in the outer peripheral direction. The refrigerant flowing through the communication path is supplied to the supply main path 66 (second through path). Then, the refrigerant flowing through the supply main path 66 is supplied to the refrigerant flow path in the first-stage bucket via the supply slit 70a (second connection path). The flow path of the bleed refrigerant from the compressor (the second refrigerant flow path) is a disk center hole 65b or 65c configured to penetrate a disk through an axis from the compression side of the rotor.
(Third penetration path), the refrigerant flowing through the central holes 65b and 65c is radially outwardly directed along the disk having the three-stage moving blades to the refrigerant passage in the three-stage moving blades. The air is supplied to the bleed system slit 74 (third communication path) configured to perform the cooling operation, and introduces the refrigerant into the rotor blades.

In such a case as well, steady and unsteady thermal stress can be reduced, and efficient cooling can be performed while reducing pressure loss.

[0064]

As described above, according to the present invention, a coolant supply and recovery flow path suitable for reducing thermal stress and pressure loss and cooling the compressor rotor is formed inside the turbine rotor. An efficient refrigerant recovery type gas turbine is provided.

[Brief description of the drawings]

FIG. 1 is an upper half sectional view of a refrigerant recovery type gas turbine showing one embodiment of the present invention.

FIG. 2 is a view taken in the direction of arrows XX in FIG. 1;

FIG. 3 is a view taken in the direction of arrows YY in FIG. 1;

FIG. 4 shows another embodiment according to the present invention.

[Explanation of symbols]

2 Compressor, 3 Combustor, 5 Blade, 6, 10 Turbine rotor, 14, 70 Supply slit, 15, 71 Recovery slit, 16, 74 Extraction system slit, 19, 2
8, 65: center hole, 22, 61: disk, 23: extraction port, 24, 68, 69: cavity, 25: communication hole, 2
6 ... Slit, 31 ... Foil Hesa, 62 ... Spacer, 63 ... Shaft, 64 ... Distant piece, 66 ... Supply main flow path, 67 ... Recovery main flow path, 76 ... Discharge port, 91 ...
Gas path, 92: arrow, 93: arrow, areas A to D.

 ────────────────────────────────────────────────── ─── Continued on the front page (72) Inventor Kazuhiko Kawaike 7-2-1, Omika-cho, Hitachi City, Ibaraki Pref.

Claims (6)

[Claims] 1. A compressor for discharging compressed air, a combustor for burning the compressed air and fuel, and a turbine driven by combustion gas supplied from the combustor and arranged on an outer peripheral side of the rotor. A turbine having a moving blade and a stationary blade having a refrigerant flow path and being connected to the compressor, wherein the rotor is supplied from a shaft end and located on the most upstream side. A first refrigerant flow path through which a first refrigerant to be supplied into the first rotor blade flows; and a bleed air from the compressor, which is supplied through a connection between the compressor and the turbine, and The second refrigerant flowing into the rotor blade on the most downstream side of the rotor blade has a second flow.
And a refrigerant flow path. 2. A compressor for discharging compressed air, a combustor for burning the compressed air and fuel, and a turbine driven by a combustion gas supplied from the combustor and arranged on an outer peripheral side of the rotor. A turbine having a moving blade and a stationary blade having a refrigerant flow path, and a turbine connected to the compressor, comprising: a path for supplying a first refrigerant to the other end of the rotor; A first refrigerant introduced into the rotor from the other end of the rotor toward the compressor end, and a first refrigerant connected to a refrigerant flow path formed on the most upstream rotor blade; The first channel after cooling the rotor blades while arranging the flow path
A refrigerant recovery path for supplying the refrigerant to the compressed air discharged from the compressor, and a path for supplying the second refrigerant extracted from the compressor to a compressor side end of the rotor. In the connection portion, the second refrigerant introduced from the compressor side end into the rotor flows toward the other end side of the rotor, and the second refrigerant from the downstream side is configured as a moving blade. While arranging the second refrigerant flow path communicating with the flow path,
The gas turbine according to claim 1, wherein the moving blade includes discharge means for discharging the supplied and heated second refrigerant into the combustion gas flow. 3. A compressor for discharging compressed air, comprising: a compressor rotor; a rotor blade and a stationary blade arranged on an outer peripheral portion of the rotor;
A combustor that burns the compressed air and fuel, and a turbine that is driven by combustion gas supplied from the combustor, has a moving blade and a stationary blade, and is connected to the compressor. The rotor is provided with a plurality of disks provided with rotor blades on the outer peripheral side in the axial direction. The disk forms a gap between adjacent disks in a region including the shaft center portion of the rotor, and the shaft center portion is formed. Forming an annular connection portion which is in contact with the adjacent disk on the outer peripheral side of the region including the air extraction port, for supplying a part of the compressed air flowing through the compressor into the rotor, and downstream from the disk on which the air extraction port is formed; A compressor cooling flow path through which gas extracted from the bleed port flows on the outer side of the contact portion or the contact portion, and a communication flow connecting the cooling flow passage and the gap. Path and the data where the bleed port is formed. On the downstream side of the disk, a communication hole is formed in a region including the shaft center portion of the rotor to communicate the gaps between the rotors, and the bleed air flowing through the compressor cooling passage or the gap is supplied to the turbine. A path is provided at a connection between the compressor and the turbine, and a path is provided within the turbine for guiding the bleed air flowing through the connection from the downstream side of the turbine to a second-stage moving blade as a cooling medium. A path for supplying another refrigerant is provided at the downstream end,
A gas turbine, wherein a path for guiding the other refrigerant as a cooling medium to a rotor blade on the most upstream side of the turbine is provided in the turbine. 4. A compressor for discharging compressed air, a combustor for burning the compressed air and fuel, and a turbine driven by a combustion gas supplied from the combustor and arranged on an outer peripheral side of the rotor. A turbine having a moving blade and a stationary blade having a refrigerant flow path, and a turbine connected to the compressor. In a gas turbine in which a plurality of fixing means for fixing are inserted in an annular shape through each disk, the rotor is supplied from the shaft end and supplied at least into the first rotor blade on the most upstream side. A first refrigerant flow path through which the first refrigerant flows; and a second refrigerant flow extracted from the compressor, supplied through a connection between the compressor and the turbine, and located downstream of the first rotor blade. The second refrigerant supplied into the rotor blade of A second refrigerant flow path, wherein the first refrigerant flow path is configured to penetrate an axis of a disk having a rotor blade most downstream from an end of the rotor opposite to the compressor. A first communication path formed between the most downstream-side disk and the adjacent disk, and configured to allow the refrigerant flowing through the communication path to flow in the outer peripheral direction; A second through-path configured in an area between the adjacent fixing means so that the refrigerant flowing through the path flows through the disk toward the compressor side; and the refrigerant flowing through the through-path is the first refrigerant. A second communication path configured to communicate with a refrigerant flow path in the rotor blade, wherein the second refrigerant flow path passes through a disk through an axis from the compression side of the rotor. A third through-passage configured as described above, A third communication path configured to communicate radially outward along a disk having the second moving blade with a refrigerant flow path in the second moving blade. And gas turbine. 5. A compressor for discharging compressed air, a combustor for burning the compressed air and fuel, and a turbine driven by a combustion gas supplied from the combustor and arranged on an outer peripheral side of the rotor. A turbine having a moving blade and a stationary blade having a refrigerant flow path and being connected to the compressor, wherein the rotor is supplied from a shaft end and located on the most upstream side. A first refrigerant flow path through which a first refrigerant to be supplied into the first rotor blade flows; and a bleed air from the compressor, which is supplied through a connection between the compressor and the turbine, and And a second refrigerant flow path through which a second refrigerant having a pressure lower than that of the first refrigerant flows and is supplied into a second moving blade located on the last stream side of the moving blade. gas turbine. 6. A compressor for discharging compressed air, a combustor for burning the compressed air and fuel, and a turbine driven by a combustion gas supplied from the combustor and disposed on an outer peripheral side of the rotor. A turbine having a moving blade and a stationary blade having a refrigerant flow path and being connected to the compressor, wherein the rotor is supplied from a shaft end and located on the most upstream side. A first refrigerant flow path through which a first refrigerant to be supplied into the first rotor blade flows; and a bleed air from the compressor, which is supplied through a connection between the compressor and the turbine, and And a second refrigerant flow path through which a second refrigerant having a temperature higher than that of the first refrigerant flows and is supplied into a second moving blade located on the last flow side of the moving blade. gas turbine.