JP3444161B2 - 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 for cooling moving blades using a refrigerant, and in particular, a refrigerant recovery type gas intended to recover the cooled refrigerant by supplying the refrigerant from a shaft end. Regarding the turbine.

[0002]

BACKGROUND OF THE INVENTION Gas turbine blades are typically cooled by air supplied through the interior of the rotor to protect them from hot combustion gases. A part of the compressed air for combustion is usually used as an air source, and after cooling, it is discharged to a passage of combustion gas (hereinafter, abbreviated as gas path).

The efficiency of the gas turbine increases as the temperature of the combustion gas increases. However, since the heat load is increased by increasing the temperature, the flow rate of the cooling air is inevitably increased. When this air is discharged into the gas path, not only the temperature of the combustion gas is lowered, but also the flow of the gas path is disturbed to deteriorate 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, but if this refrigerant is discharged from the rotor blades arranged on the outer circumference of the rotor, a great loss of pumping power occurs, resulting in a loss. Increases in proportion to the refrigerant flow rate. Therefore,
An effective improvement in efficiency cannot be expected simply by raising the temperature of combustion gas.

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.

Therefore, for example, in JP-A-54-13809, a coolant supply / recovery path is constructed by piping inside the rotor, and in JP-A-3-275946, a coolant is formed by piercing inside the rotor constituent member. There has been proposed a method of configuring a supply and recovery route for

[0006]

In order to construct a refrigerant recovery type gas turbine, a supply passage for supplying a refrigerant for a moving blade to the inside of a turbine rotor and a recovery passage for recovering the cooled refrigerant. It is necessary to form a flow path. However, since the temperature of the refrigerant rises by cooling the blades, thermal stress due to the temperature difference of the refrigerant is generated in the rotor constituent member in which the supply passage and the recovery passage are mixed.

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 depending on the structure of the flow path, excessive thermal stress exceeding the allowable value of the material is generated. 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 problems is how to reduce the thermal stress in the supply and recovery refrigerant flow passages inside the rotor.

Further, in the air-cooled refrigerant recovery type gas turbine in which the blades are cooled by utilizing a part of the compressed air for combustion and the cooled air is recovered in the combustor, the recovery pressure is at least discharged from the compressor. It needs to be raised above the pressure. Therefore, the refrigerant will be pressurized by the boost compressor before supply,
Increasing the flow rate of the refrigerant to increase the temperature inevitably increases the compression power of the boost compressor, 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 structure that can reduce the pressure loss of the refrigerant flowing in the rotor as much as possible. These points are not considered in any of the known examples.

Therefore, the present invention aims to reduce thermal stress and pressure loss in the rotor, and to supply a refrigerant suitable for cooling the compressor rotor.
An object of the present invention is to provide a highly efficient refrigerant recovery type gas turbine by forming supply and recovery flow paths .

[0010]

SUMMARY OF THE INVENTION The present invention is a turbine rotor driven by a compressor for discharging compressed air, a combustor for combusting the compressed air and fuel, and a combustion gas supplied from the combustor. In a gas turbine including: a turbine that has a moving blade and a stationary blade that are arranged on the outer peripheral side of the rotor and that have a refrigerant flow path; and a turbine that is connected to the compressor, the gas turbine is supplied from the shaft end into the rotor. A first refrigerant flow path in which the first refrigerant supplied into the first moving blade located on the most upstream side flows, and the rotor is bleeded from the compressor to connect the compressor and the turbine. A second cooling medium flow path in which a second cooling medium is supplied, which is supplied through the connecting portion and the rotor central portion and is supplied into the moving blade on the most downstream side of the moving blade having the cooling fluid flow path. And

[0011]

Alternatively, a compressor for discharging compressed air, a combustor for combusting the compressed air and fuel, and a combustion gas supplied from the combustor are used to drive the turbine rotor and the outer peripheral side of the rotor. In a gas turbine including a turbine having a moving blade having a refrigerant flow path and a stationary blade, the turbine being connected to the compressor, a path for supplying a first refrigerant from an axial end of the rotor is provided , and A first refrigerant flow in the rotor, which flows the first refrigerant introduced from the shaft end of the rotor toward the compressor end side and communicates with the refrigerant flow path formed in the most upstream rotor blade. A refrigerant recovery path for arranging a passage and supplying the first refrigerant after cooling the moving blades to the compressed air discharged from the compressor, and the second refrigerant extracted from the compressor to the rotor. Of the supply path to the compressor side end of Provided in a connecting part between the machine and the turbine, in the rotor, the second refrigerant introduced from the compressor side end with flow toward the shaft end of the rotor, from the downstream side of the second stage moving A second refrigerant flow passage that is in communication with a refrigerant flow passage that is formed in the blade is arranged, and the moving blade has a discharge means that discharges the supplied second coolant whose temperature has risen into the combustion gas flow, It is characterized by being provided.

As a result, it is possible to further suppress the complication of the flow path structure, and it is possible to reduce the flow rate of the high-pressure first refrigerant supplied to the compressed air discharged from the compressor. It is possible to operate efficiently while suppressing the pressure loss due to the refrigerant supply and recovery.

Alternatively, a compressor having a compressor rotor, a moving blade and a stationary blade arranged on the outer peripheral portion of the rotor for discharging compressed air, a combustor for burning the compressed air and fuel, and the combustion Driven by combustion gas supplied from a compressor, has a moving blade and a stationary blade, and includes a turbine connected to the compressor, and the compressor rotor has a disk provided with the moving blade on the outer peripheral side in the axial direction. A plurality of the disks are arranged, and the disks are the shaft
The region including the heart portion to form a gap between the adjacent disks, to form a contact contact portion of the annular contact with a disk adjacent to the outer peripheral side of the area including the axial center portion, flow through the compressor Forming an extraction port that supplies a part of compressed air into the rotor
And, between the bleed port formed downstream of the plurality of <br/> disks from the disk, a plurality of the outer peripheral side of the contact part cavity
To form a tee, to form a communication passage communicating the cavity with the gap, the region including an axis portion of the rotor
A communication hole communicating with the gap is formed, and the bleed port is formed.
The bleed air is
Connect the cavities through which the gas extracted from the mouth flows.
A connecting hole that forms a communicating hole and that supplies the extracted air from the communication hole to the turbine is provided in the connecting portion between the compressor and the turbine, and the extracted air that has flowed through the connecting portion is waked in the turbine in the wake of the turbine. From the side to the second-stage rotor blade as a cooling medium, a path for supplying another refrigerant to the downstream end of the turbine, and the other refrigerant in the turbine at the most upstream side of the turbine. It is characterized in that it is provided with a path for guiding a cooling medium to the moving blade.

Thus, by optimally supplying or recovering different refrigerants, thermal stress can be suppressed to a low level, and good cooling can be achieved while reducing pressure loss. Further, it is possible to efficiently cool a high-temperature region such as a high-pressure portion on the downstream side of the blade row of the high-temperature compressor.

[0016]

BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of the present invention will be described in detail below with reference to FIG.

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

The rotor blades 5 are supported on the outer periphery of the turbine rotor 6, and inside the rotor blades of one to three stages are shaped according to the heat load so as to withstand the heat load of the combustion gas flowing through the gas path 91. Different cooling flow paths 51 are formed.

The turbine rotor 6 includes four disks 61a to 61d having rotor blades and three spacers 62a to 62.
It is configured by bolting the c and the shaft 63 at the hub portion, and the compressor 2 via the distant piece 64.
Is connected to the rotor. Distant piece 64,
Center holes 65a to 65d are formed in the first and second tier disks 61a and 61b and the shaft 63, respectively, and the third and fourth tier disks are solid.

At the hub portion of the rotor, 4 from the first stage disk
A plurality of supply backbone channels 66 that penetrate axially up to the stage disc, distant piece 64, first stage disc 61a
A plurality of recovery trunk flow channels 67 that pass through the 1/2 spacer 62a are arranged in the circumferential direction. Supply main flow path 6
One end of 6 is communicated with the axial center hole 65d on the downstream side of the rotor through the inner cavity 68b at the rear of the four-stage disc 61d and the supply slit 70c, and one end of the recovery trunk flow channel 67 is formed by the seals 32a and 32b. It is opened in the partitioned wheel space 31a.

Further, the distant piece 64, the first-stage disc 61a, the second-stage disc 61b, and the 2/3 spacer 6
Supply slits 70a and 70b at the hub joint of 2b,
A collection slit 7 is provided on both sides of the 1 / 2-step spacer hub.
1a and 71b are formed, one end of the supply slit 70 communicates with the supply basic flow channel 66, one end of the recovery slit 71 communicates with the recovery main flow channel 67, and the other end communicates with the cavities 69a to 69d outside the hub and the disk outer periphery. Through a supply hole 72 and a recovery hole 73 of the portion, the cooling flow path 51 of the moving blade is communicated.

Further, a bleed system slit 74 is formed at the hub joining portion of the 2 / 3-stage spacer and the 3-stage disc to connect the inner cavity 68a of the hub and the outer cavity 69e communicating with the central hole 65c in the radial direction. There is.

On the other hand, the rotor of the compressor 2 has rotor blades 21 on the outer circumference.
Is formed by a plurality of disks 22, and an extraction port 23 is formed at the root of the blade of a specific stage selected from the intermediate stages. The disc on the front side of the extraction port 23 is solid, and the disc on the rear side is formed with a central hole 28 which is a communication hole communicating the gap between the discs. The extraction port 23 and the central hole 28 are hubs. The outer cavity 24, the plurality of slits 26, and the inner cavity 27 communicate with each other. Further, the outer cavities 24 are communicated with each other on the outer side of the hub by a communication hole 25 which is a communication channel.

FIG. 2 shows a view taken along the line XX in FIG.
The supply trunk flow paths 66 and the recovery trunk flow paths 67 are alternately formed at intermediate positions of a plurality of bolt holes 75 arranged in the circumferential direction of the hub. Further, it can be seen that the supply holes 72 and the recovery holes on the outer peripheral portion of the disk are formed in the same number as the blades.

FIG. 3 shows a view taken along the line YY of FIG.
The extraction system slits 74 are alternately arranged in the circumferential direction with the supply main flow paths.

Therefore, the refrigerant supplied from the end of the shaft 63 of the turbine rotor 6 when the gas turbine is started passes through the coaxial central hole 65d, the cavity 68b and the slit 70c on the rear side of the four-stage disk, and is axially transferred to the disk. It is introduced into the supply trunk flow 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 peripheral portion of the disk (arrow 92).
b) After cooling the blade, it is guided to the recovery main flow path 67 (arrow 92c) 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, and then the foil is 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). Then, it is supplied to the combustor together with the compressor discharge air.

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

On the other hand, the refrigerant extracted from the extraction port 23 on the outer peripheral portion of the compressor at the intermediate stage of the compressor is distributed almost evenly to the cavity 24 on the downstream side outside the hub by the communication holes 25, and then the slits 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 flow passage inside the three-stage rotor blade through the disk center holes 65b and 65c, the cavity 68a, the bleed system slit 74, and the cavity 69e on the outer circumference of the hub, and after cooling the blade, it is discharged into the gas path 91. (Arrow 93b).

As described above, by constructing the refrigerant supply system from the shaft end and the extraction refrigerant system from the compressor in the rotor, the hub located at the intermediate radius of the rotor serves as the axial passage of the blade refrigerant. , The outer diameter side is a communication passage with the blades, and the inner diameter side is an extraction refrigerant environment from the compressor, and the solid disk 61d in the final stage separates the shaft end supply flow path 68b and the extraction flow path 68a in the rotor central part. As a result, the refrigerant flow paths of the three systems of supply, recovery, and extraction can be simply configured without crossing.

Further, a main flow passage for supplying and recovering the moving blade refrigerant is formed in the hub portion to which the disk, the shaft and the like are joined, and the supply main flow passage is communicated with the supply port at the shaft end, and While opening the recovery main flow path to the foil space on the first stage side,
A supply slit and a recovery slit were formed in the joint portion of the hub so that one end communicates with each of the supply and recovery basic flow paths. Further, a slit communicating with the disk center hole is formed in the hub joint portion of the three-stage disk having the three-stage moving blade on the final flow side of the moving blade provided with the refrigerant flow path. In such a configuration, the refrigerant supplied from the shaft end supply port is supplied to the moving blades in the stage preceding the third stage through the supply basic flow passage and the supply slit, and the cooled coolant is the recovery slit and the recovery main flow passage. And is collected in the combustion chamber side. Compressed air having an intermediate temperature between the supply refrigerant and the recovered refrigerant is extracted from the compressor, and this air is passed through the slits formed in the disc center hole and the hub joint portion of the three- stage disc to provide three-stage rotor blades. Supply to.

As a result, the hub located at the intermediate radius of the rotor serves as the axial passage of the blade refrigerant, the outer diameter side of the hub is the communication passage with the blade, and the inner diameter side is the extraction refrigerant temperature environment from the compressor. By partitioning the shaft end supply passage and the extraction passage at the center of the rotor with the final stage disk, it is possible to simply configure the refrigerant passages of the three systems of supply, recovery and extraction without intersecting each other. The thermal stress can be reduced during steady and unsteady conditions, the compressor rotor can be cooled, and the refrigerant can be recovered more effectively.

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

Further, as a section for leaking along the path, the shaft end supply section and the outer cavities 69a, 69b, 69c, 6 are provided.
9d: Peripheral disc-spacer joint, disc-blade fitting, and foil space 31a seal 32
Although b etc. are considered, leakage from the joint and the fitting part can be prevented by the contact surface seal, and the seal 32
Refrigerant leaking from b passes from the gas path to the foil space 3
Since it can be utilized as seal air for preventing combustion gas from leaking into the 1b, most of the refrigerant supplied from the shaft end can be efficiently recovered.

Further, since the radial position of rotation of the discharge port 76 can be configured to be at least half the radial position of the moving blade or less,
The pumping power loss associated with refrigerant discharge can be reduced to one fourth or less of the conventional one.

Further, the refrigerant extracted from the compressor is caused to flow in parallel with the flow paths 24 to 28 formed on the side surface of the disk, and is guided to the central portion of the turbine rotor 6 through the distant piece 64, so that the compressor high stage is formed. The disk on the side can be cooled uniformly, and the distant piece heated by the recovered refrigerant from the outer circumference can be cooled from the inside. Therefore, the compressor discharge pressure can be increased without increasing the heat resistance of the rotor material. Further, if the temperature of the extraction refrigerant is set to an intermediate temperature between the shaft end supply refrigerant and the recovery refrigerant, the low temperature portion around the shaft end supply main flow path 66 formed in the hub is heated and recovered around the recovery main flow path 67. The cooling acts on the high temperature portion of the above, and the function of alleviating the height of the rotor temperature distribution works, and the thermal stress is reduced.

Further, since it is not necessary to recover the extracted refrigerant, boost compression power can be saved and the compressor can be downsized.

However, in the disc center hole, pressure loss occurs due to the above-mentioned vortex flow before the hole inflow, and the loss amount largely depends on the flow rate, but the bleed refrigerant should be divided into a plurality of inter-disk flow passages. As a result, the flow rate of each flow path is reduced, and accordingly, the pressure loss is also reduced, and the supply pressure to the three-stage rotor blade can be sufficiently secured.

Further, when the gas turbine is started, high temperature combustion gas flows through the gas path 91 simultaneously with ignition, so that the temperature on the outer peripheral side of the rotor rises rapidly 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 center of the rotor where the temperature rises gradually than in the steady operation. However, in this embodiment, the air extracted from the compressor flows into the center of the rotor at the same time as the rotor starts, and the same part is uniformly generated. Since it is heated to a high temperature, a great effect can be obtained in reducing the unsteady thermal stress at startup. Further, since the refrigerant supplied from the shaft end can be manipulated outside the machine in terms of state quantities such as flow rate and temperature, it is also possible to control unsteady thermal stress of the rotor to a minimum by means of a supply delay means or the like.

The refrigerant for the first-stage moving blades is supplied from the front side of the disk in order to cool the same portion by flowing a low-temperature refrigerant to the hub and the front side of the first-stage disk. Also, the temperature of the disk hub becomes almost the average temperature of the supply refrigerant and the recovery refrigerant, and the temperature rise can be maintained at a low temperature as compared with the case where only the recovery refrigerant flows from the rear side of the disk and flows to the hub. However, due to this effect, 1
The temperature outside the / 2 stage spacer rises near the recovery temperature, but no temperature gradient is formed in the axial direction, the outer periphery is cooled by the seal air, and the hub is cooled by the coolant supplied for the first stage cooling. Due to the smaller centrifugal load of the spacer compared to the loaded disc, stress is less of an issue than the disc.

Further, by supplying the refrigerant from the front side of the moving blade to the internal cooling passage 51, the 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 it.

From the viewpoint of pressure loss, the flow passage is formed so that the length of the flow passage from the shaft end to the combustion chamber bypassing the cooling passage of the rotor blade is shortened as much as possible. Further, the central hole flow path with a large pressure loss is avoided.
Therefore, the pressure loss in the path is small, and the boost compression power of the refrigerant can be minimized.

In the center hole 28 of the compressor disk, however, the swirling speed of the vortex increases as the refrigerant flowing out from the hub slit 26 flows inwardly in the cavity 27, and this swirling speed energy causes the axial flow of the central hole. Although it disappears in the process to generate a pressure loss, 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. Therefore, the pressure loss in the central hole is small. Therefore, on the high stage side, a sufficient supply pressure to the third stage moving blade can be secured regardless of the extraction stage.

The most effective way of improving the efficiency is to recover the entire amount of the refrigerant for the moving blades and reduce the loss due to the refrigerant discharge to the gas path, as the flow path configuration when the air is not extracted from the compressor. However, in this case, it is necessary to boost-compress all the refrigerant. On the other hand, in the present embodiment, since the refrigerant of the three-stage rotor blade is discharged to the gas path, the efficiency of the gas turbine is reduced accordingly, but the boost compression power is not necessary for this refrigerant, so the refrigerant is discharged. Loss is replenished.

By forming as in this embodiment, it is possible to reduce the amount of the refrigerant that needs to be compressed and to reduce the required power and to make a good refrigerant.

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 second-stage disk. Limited to a small area. However, about half of the coolant-wetting surface in the region is exposed to the low-temperature supply coolant.

On the other hand, since the refrigerant extracted from the compressor flows from the compressor rotor to the area B in the central portion of the turbine rotor, the members included in the area are exposed to the environment of the extracted refrigerant. A region C formed outside the 2 / 3-stage spacer and the 3-stage disc is a unit exposed to the supply refrigerant and the extraction refrigerant, and a region D behind the remaining 3 / 4-stage spacer is exposed mainly to the low-temperature supply refrigerant. To be done.

Therefore, as an example, when a refrigerant of 230 ° C. is supplied from the shaft end and compressed air of 370 ° C. is extracted from the compressor, the recovery temperature after blade cooling in a 1500 ° C. class gas turbine becomes 450 ° C. to 500 ° C. To rise. Along with this, the average temperature of the members in the area A exposed to the supply refrigerant and the recovered refrigerant rises to 340 ° C. to 365 ° C. which is the average temperature of both refrigerants, and the average temperature of the members in the area D exposed to only the supply refrigerant is increased. The temperature rises to near 220 ° C of the supply refrigerant.

On the other hand, the member temperature in the area B where the extracted refrigerant flows rises to a temperature of the extracted refrigerant near 370 ° C., and the member temperature in the area C is about 300 ° C. which is the average temperature of the extracted refrigerant and the supply refrigerant.
Go up and down. Further, since the distant piece is heated by the recovered refrigerant from the outer circumference and the extracted refrigerant from the inner circumference,
Both average temperatures rise 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 refrigerant for cooling the blades,
It is possible to configure the rotor internal refrigerant flow path in which the average temperature of the rotor is approximately 430 ° C. or lower.

Further, the temperature distribution in the axial direction of the hub has regions A, C,
There is little change in height even if it includes a partial change in each region. This is effective in reducing the difference in elongation of the hub joint portion in the radial direction as much as possible and reducing the stress in the fitting portion.

However, the central portion of the disk is the section where the maximum centrifugal stress is generated by high-speed rotation, but by making the temperature of the central portion higher than the outer diameter side, the centrifugal stress is alleviated by thermal expansion. Since the temperature of the hub is approximately the intermediate temperature between the supply refrigerant and the recovered refrigerant as described above, if the extraction temperature from the compressor is raised above the intermediate temperature, it will be heated by the extraction refrigerant in the center of the rotor and higher than the hub temperature. Becomes Therefore, by appropriately selecting the extraction temperature, the effect of reducing the stress in the same portion can be obtained. At this time, since the temperature of the extracted air is determined by the paragraph position of the extraction port 23, it is necessary to select the extraction stage that is most effective in reducing the thermal stress for the structure of the refrigerant passage formed inside the rotor.

In this embodiment, the extraction 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 central hole and supplied to the three-stage rotor blade from the rear side. Formed on the front side is a cavity 68c in which the refrigerant does not flow between the disks to reduce the thermal stress generated on the side surface of the central portion of the four-stage disk 61d due to the temperature difference between the shaft end supply refrigerant and the extracted refrigerant. In order to reduce the thermal stress of the rotor as a whole, if the temperature difference between the coaxial end supply refrigerant and the bleed refrigerant can be reduced, forming the bleed path on the rear side of the three-stage disk is no different from the above. The effect of is obtained.

[0054] The through spacers between the disks in the embodiments described above, but in order to reduce the stress by shortening the axial span of the disc hub and the outer peripheral rim can be configured short paragraph span of the turbine In some cases, the spacer may be omitted.

FIG. 4 shows a sectional structure of a turbine rotor in which a cooling passage is formed without a spacer.
The rotor 10 is composed of disks 11a to 11d and a shaft 63, and is connected to the compressor rotor through a distant piece 64 on the first stage side. The discs from the first stage to the third stage are formed with a central hole 19 and the four-stage disc is formed solid. The rotor blades 5 are planted on the outer periphery of the disc, and the rotor blades from the first stage to the third stage are inside. Has been cooled from.

In this case as well, 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 and 14b, the recovery slit 15, and the extraction system slit 16 from the compressor are formed between the disks 11 , and particularly the recovery slit 15
Is commonly used for recovering the refrigerant for the first-stage rotor blade and the second-stage rotor blade.

In such a flow path structure, a part of the refrigerant supplied from the shaft end and introduced into the supply basic flow path 12 is supplied to the two-stage rotor blades via the supply slit 14b and the outer inter-disk cavity 17c, and the rest. Refrigerant supply slit 17
It is supplied to the first stage moving blade from a through the front side of the disk. After merging in the cavity 17b, they are recovered to the combustion chamber side through 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 through the distant piece, and is supplied to the three-stage rotor blades through the inside cavity 18, the extraction system slit 16 and the outside cavity 17d.

Even in this case, the effects of reducing steady and unsteady thermal stress and pressure loss, cooling of the compressor rotor, etc. are almost the same as those of the previous embodiment, and by omitting the spacer, the rotor structure itself is eliminated. Has the advantage that it can be configured simply.

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. To introduce the refrigerant flowing through 65d through the center hole of the four-stage disc 61d into the supply trunk route 66 through the slit from the cavity 68c formed between the third-stage disc and the fourth-stage disc. Is.

The specific structure of the rotor is as follows.

The flow path of the refrigerant supplied from the shaft end (first refrigerant flow path) uses the center hole at the center of the disk as the first through path configured to penetrate the axis of the four-stage disk. In addition, a cavity and a slit (first communication path) formed between the four-stage disc and the adjacent three-stage disc are formed so that the coolant flowing through the central hole flows in the outer peripheral direction. The refrigerant flowing through the communication path is supplied to the supply backbone path 66 (second penetration path). Then, the refrigerant flowing through the supply backbone path 66 is supplied to the refrigerant flow path in the first-stage rotor blade via the supply slit 70a (second communication path). The flow path of the extracted refrigerant from the compressor (the second refrigerant flow path) is a disk center hole 65b or 65c configured to penetrate the disk from the compression side of the rotor through the shaft center.
Etc. (third penetration path), and the refrigerant flowing through the central holes 65b and 65c is connected to the refrigerant passage in the three-stage moving blades toward the radially outer side along the disk having the three-stage moving blades. Is supplied to the extraction system slit 74 (third communication path) configured to perform the introduction of the refrigerant into the moving blades.

Even in such a case, steady and unsteady thermal stress can be relaxed, and efficient cooling can be performed while reducing pressure loss.

[0064]

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

[Brief description of drawings]

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

FIG. 2 is a view on arrow XX in FIG.

FIG. 3 is a view taken along the line YY of FIG.

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

[Explanation of symbols]

2 ... Compressor, 3 ... Combustor, 5 ... Moving 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 ... Bleed port, 24, 68, 69 ... Cavity, 25 ... Communication hole, 2
6 ... Slits, 31 ... Foil spasers, 62 ... Spacers, 63 ... Shafts, 64 ... Distant pieces, 66 ... Supply trunk channels, 67 ... Recovery trunk channels, 76 ... Discharge ports, 91 ...
Gas path, 92 ... arrow, 93 ... arrow, areas A to D.

─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Takashi Ikeguchi 7-2-1 Omika-cho, Hitachi-shi, Ibaraki Hitachi, Ltd. Electric Power and Electric Development Division (72) Inventor Kazuhiko Kawaike Seven-mika-machi, Hitachi-shi, Ibaraki 2-2-1 Hitachi Electric Power Co., Ltd. Electric Power & Electric Machinery Development Division (56) Reference JP 10-47006 (JP, A) JP 10-103004 (JP, A) JP 10-252497 (JP , A) JP 8-277725 (JP, A) JP 10-89086 (JP, A) JP 9-13902 (JP, A) JP 3349056 (JP, B2) JP 3362643 (JP, B2) Patent 2941748 (JP, B2) Patent 3276276 (JP, B2) International Publication 98/23851 (WO, A1) (58) Fields investigated (Int.Cl. ⁷ , DB name) F01D 1/00-11/10 F02C 1 / 00-9/58 F23R 3/00-7/00

Claims (5)

(57) [Claims] 1. A compressor that discharges compressed air, a combustor that combusts the compressed air and fuel, and a combustion gas that is supplied from the combustor. The compressor is disposed on the outer peripheral side of the turbine rotor and the rotor. A gas turbine having a moving blade having a refrigerant flow path and a stationary blade, the turbine being connected to the compressor, wherein the rotor is supplied from the shaft end and is located on the most upstream side. 1 of the first refrigerant flow path through which a first refrigerant supplied to the motion within the wings, in the rotor, bled from the compressor, through the connecting portion and the rotor center portion between the turbine and the compressor And a second refrigerant flow path in which a second refrigerant supplied into the moving blade on the most downstream side of the moving blade having the refrigerant flow path flows. 2. A compressor that discharges compressed air, a combustor that combusts the compressed air and fuel, and a combustion gas that is supplied from the combustor. The turbine rotor and the outer peripheral side of the rotor are arranged. In a gas turbine including a turbine having moving blades having a refrigerant flow path and a stationary blade, the turbine being connected to the compressor, a path for supplying the first refrigerant from the shaft end of the rotor is provided.
Only, in the rotor, the flow of the first refrigerant introduced from the shaft end of the rotor toward the compressor end side, the contact refrigerant flow path configured on the most upstream side blade 1 Of the first flow path after cooling the moving blade with the cooling medium flow path
A refrigerant recovery path for supplying the compressed air discharged from the compressor to the compressed air, and a path for supplying the second refrigerant extracted from the compressor to the compressor side end of the rotor is connected to the compressor and the turbine. The second refrigerant introduced from the compressor side end is provided in the connecting portion and flows toward the shaft end side of the rotor in the rotor, and is configured as a second-stage rotor blade from the wake side. A second refrigerant flow path communicating with the refrigerant flow path is arranged, and the moving blade includes a discharging means for discharging the supplied and heated second refrigerant into the combustion gas flow. A gas turbine. 3. A compressor having a compressor rotor, a moving blade and a stationary blade arranged on an outer peripheral portion of the rotor, and discharging compressed air,
A compressor that combusts the compressed air and fuel; and a turbine that is driven by combustion gas supplied from the combustor and that has moving blades and stationary blades and that is connected to the compressor. the rotor disk with blades on the outer peripheral side is more axially arranged, the disc is a region including an axis portion of the rotor to form a gap between the adjacent disks, the axis portion contacting the disc adjacent to the outer peripheral side of the region including an annular contact touch <br/> portion is formed, a part of the compressed air flowing through the compressor to form a bleed port for supplying into the rotor, the bleed A plurality of cavities are provided on the outer peripheral side of the contact portion between the plurality of discs on the downstream side of the disc in which the mouth is formed.
To form a form a communication passage communicating the cavity with the gap, the gap in a region including an axis portion of the rotor
Part forming a contact hole communicating with a plurality of Di downstream of the disk the bleed ports are formed
In the disc, the gas extracted from the extraction port flows
Forming a communication hole that communicates a number of cavities , providing a path for supplying the extraction air from the communication hole to the turbine to a connecting portion between the compressor and the turbine, and extracting the extraction air flowing through the connecting portion into the turbine. The turbine has a path from the wake side of the turbine to the second stage blade as a cooling medium, and a path for supplying other refrigerant to the downstream end of the turbine.
A gas turbine, wherein a path for guiding the other refrigerant as a cooling medium to the moving blade on the most upstream side of the turbine is provided in the turbine. 4. The gas turbine according to claim 1, wherein the second refrigerant has a pressure lower than that of the first refrigerant. 5. The gas turbine according to claim 1, wherein the second refrigerant has a temperature higher than that of the first refrigerant.