JP4691950B2 - Gas turbine and refrigerant supply method thereof - Google Patents

Description

  The present invention relates to a gas turbine and a refrigerant supply method thereof.

  In order to improve the performance of the gas turbine in the power plant, it is desirable that the tip clearance between the turbine blade and the shroud (hereinafter referred to as the blade tip clearance) be as small as possible. This is because if the gap between the rotor blade tips is large, leakage loss increases at the tip of the rotor blades, which greatly affects the turbine performance. However, if the gap between the blade tips is too small, the blade tips contact (rubbing) the shroud and cause destruction. Therefore, in general, in order to prevent rubbing, the initial rotor blade tip clearance is determined so as not to fall below the design minimum clearance value in each of the starting, rated, and stopped operating states of the gas turbine.

  Therefore, in Patent Document 1, in a gas turbine facility equipped with a steam-cooled gas turbine, the cooling medium supplied to the rotor and blades of the gas turbine is cooled, and the temperature of the cooling medium is controlled, thereby rubbing the blades. A technique for avoiding this is disclosed.

JP-A-8-270459

  In the gas turbine equipment of Patent Document 1, the cooling air is not divided into a stationary system (static blade and casing) and a rotating system (moving blade), but a common system is used. However, the stationary blade and the casing have a relatively large volume compared to the moving blade, and the response of thermal expansion is slow. Therefore, it is difficult for the stationary blade and the casing to follow the thermal elongation of the moving blade. Therefore, in the process from the stop of the gas turbine to the rated rotation, even if a cooling medium of the same temperature is supplied to the stationary blade and the moving blade, the expansion due to the thermal expansion of the rotating rotor and the moving blade and the centrifugal stress of the rotation is dominant. This increases the possibility of rubbing. From the above, in order to avoid rubbing when starting the gas turbine, it was necessary to increase the initial rotor blade tip clearance in advance.

  SUMMARY OF THE INVENTION Accordingly, an object of the present invention is to improve the performance of a gas turbine by avoiding rubbing during start-up and ensuring the reliability of the gas turbine, while reducing the rotor blade tip clearance during rated load operation.

The invention, hand in flow direction upstream branch to said cooling system the coolant supply compressed air from the compressor to the stationary blade and the other of the cooling system increased from the humidifying tower (5) The cooling system is configured to supply wet air to the stationary blades, and the cooling system of the stationary blades is configured to be able to switch between the discharge air of the compressor and the humidified air from the humidifying tower. In the gas turbine, the discharge air from the compressor is supplied to the stationary blade at the time of start-up, and then the humidified air from the humidification tower is switched to be supplied to the stationary blade .

  According to the present invention, it is possible to improve the performance of the gas turbine by reducing the rotor blade tip clearance during rated load operation while avoiding rubbing during startup and ensuring the reliability of the gas turbine.

  2. Description of the Related Art Conventionally, a gas turbine that is generally employed is configured to drive a turbine by adding fuel to a working fluid compressed by a compressor and burning it to obtain a high-temperature and high-pressure working fluid. The rotational energy of the driven turbine is typically converted to electrical energy by a generator coupled to the turbine.

  In recent years, high-humidity gas turbine power plants have been attracting attention because they are designed to increase efficiency by adding moisture to gas turbine working gas. FIG. 2 shows the equipment configuration of the high-humidity gas turbine power plant. One feature of the high-humidity gas turbine power plant is to increase the energy potential and increase the output of the gas turbine by adding moisture to the combustion gas in the humidification tower 5 and the intake sprayer 14 to increase the humidity. . Yet another feature is that the heat energy is recovered by the regenerator 6 and the feed water heater 8, and further the water recovery is performed by the water recovery device 10, thereby improving the power generation efficiency of the plant itself.

  Here, when considering further improvement of the performance of the gas turbine in such a power plant, the turbine blade tip clearance is a loss at the blade tip leakage. Therefore, it is desirable that the influence on the turbine performance is large and as small as possible. On the other hand, if this gap is too small, the tip of the rotor blade contacts (rubbing) the shroud and causes destruction. Therefore, in general, the minimum design clearance value in each of the starting, rated, and stopped operating conditions so as not to cause rubbing. The initial gap is determined so as not to fall below.

  However, when the initial gap is determined in this way, the gap is minimized at the time of start-up (the rotor disk and rotor blade of the rotating system are in a hot state, and the stationary casing having a slow response is in a cold state. When the initial gap is designed so as to avoid rubbing in this state, the casing becomes hot during rated load operation, and the gap widens, causing a decrease in turbine performance.

  Therefore, the purpose of avoiding rubbing during startup and reducing the tip clearance of the gas turbine rotor blade during rated operation was realized with a small equipment configuration.

  FIG. 2 shows a system diagram of the gas turbine power plant in this embodiment. The solid line in the figure indicates the gas path. In this embodiment, the gas path and the devices installed in the path are collectively referred to as an air system. Moreover, the dotted line in a figure shows the path | route of water. And in a present Example, the path | route of water and the apparatus installed in this path | route are collectively called a humidification system | strain. The path of the cooling medium is referred to as a cooling air system.

  The gas system will be described. In the power plant shown in FIG. 2, a turbine 1, a compressor 2, and a generator 3 are coupled to one shaft. The compressor 2 takes in air in the atmosphere and compresses it to generate high-pressure compressed air at a temperature of about 300 ° C. and a pressure of about 2 MPa in the rated load operation state. At this time, an intake sprayer 14 is disposed at the inlet of the compressor 2 and humidifies the air. The air cooler 4 cools the compressed air to about 100 ° C. and then supplies the compressed air to the humidification tower 5. The humidification tower 5 adds moisture to the compressed air to obtain humidified air at about 150 ° C. The humidified air from the humidifying tower 5 is heated to about 550 ° C. in the regenerator 6 and burned with fuel in the combustor 7 to be a high-temperature and high-pressure combustion gas having a temperature of 1300 ° C. or higher and a pressure of about 1.9 MPa. It becomes. This combustion gas is supplied to the turbine 1 and drives the generator 3. Thus, by burning the humidified air, the combustion gas contains a large amount of moisture and the weight flow rate increases. Moreover, since the specific heat of water vapor is larger than that of air and can hold more energy in the interior, the output can be increased as compared with the case of normal air combustion. The exhaust gas that has expanded to a low pressure in the turbine 1 has a temperature of about 600 ° C. and is still sufficiently hot. Therefore, the exhaust gas is heat-exchanged with humidified air in the regenerator 6 and further heat-exchanged with water in the feed water heater 8 to recover the thermal energy of the exhaust gas. The exhaust gas exiting the feed water heater 8 is cooled in the exhaust gas regenerator 9 and then supplied to the water recovery device 10. In the water recovery device 10, the temperature of the exhaust gas is lowered by spraying low temperature water on the exhaust gas, and the moisture in the exhaust gas is condensed to recover the water. Exhaust gas containing a part of water without condensing is led again to the exhaust gas regenerator 9, heated and discharged from the chimney 11 to the atmosphere.

  Next, the humidification system will be described. In the humidification system, the humidification tower 5 and the intake sprayer 14 humidify the air, and the water recovery device 10 recovers water from the exhaust gas. The humidification tower 5 humidifies the compressed air by spraying the high-temperature water heated in the air cooler 4 and the feed water heater 8 directly on the compressed air. The high-temperature water that has not evaporated in the humidification tower 5 forms a circulation system that is supplied to the air cooler 4 or the feed water heater 8 again.

  On the other hand, the water recovery device 10 sprays low temperature water cooled by the cooler 17 onto the exhaust gas, lowers the temperature of the exhaust gas, condenses moisture in the exhaust gas into water, and collects water as much as possible. To do. A part of the moisture that could not be recovered yet is released into the atmosphere by the chimney 11 and lost, but the water corresponding to the loss (humidity) is newly supplied from the cooling water supply tank 15. The water collected and replenished in this way is boosted by the pump 12, purified by the desalinator 13, and supplied to the air cooler 4 and the intake sprayer 14.

  Next, the cooling air system of the high temperature part of the turbine 1 will be described. The combustion temperature of the gas turbine power plant according to the present embodiment is 1300 ° C. or higher, and is higher than the allowable temperature of the members constituting the gas path of the turbine 1, so that the turbine cooling section needs to be cooled. Here, there are mainly two systems for cooling the cooling section of the turbine 1 that needs to be cooled: a compressed air system 21 compressed by the compressor 2 and a humidified air system 28 branched from the humidifying tower 5. It is a system. Further, a system 29 of air extracted from the intermediate stage of the compressor 2 is used for cooling the latter stage of the turbine 1. In either system, after cooling the cooling part of the turbine 1, it is discharged into the gas path. In the present embodiment, since the humidification condition is not sufficiently established such as at the time of start-up, on the upstream side of the humidified air system 28, the air from the cooler 4 and the humidifying tower 5 It branches off to the air system 24. A switching device 27 having a function of switching the two systems 23 and 24 while mixing the two systems of air is disposed. Thus, by providing the air system 23 from the cooler 4 and the air system 24 from the humidification tower 5 on the upstream side of the humidified air system 28, the air from the cooler increases at the initial stage of startup. The humid air system 28 can be warmed up. If the humidified air system 28 is warmed up at the initial stage of startup, condensation in the piping due to the humidity of the humidified air generated due to cooling of the cooling path of the piping, rotor blades, and rotor, and blockage and corrosion of the flow path. It can be suppressed.

  FIG. 1 is a more detailed view of a gas turbine cooling system. The description of the components with the same numbers as those in FIG. 2 is omitted. In FIG. 1, a turbine 1 of a gas turbine includes a stationary blade 30 and a moving blade 31, a turbine casing 50 includes a stationary blade 30, and a turbine rotor 51 includes a moving blade 31. In the turbine 1, the stationary blade 30 and the turbine casing 50 form a stationary system, and the moving blade 31 and the turbine rotor 51 form a rotating system. In the present embodiment, the moving blade 31 and the rotor 51 are cooled by the air of the humidified air system 28 a, and on the upstream side of the humidified air system 28 a, the air system 23 from the cooler 4 and the humidifying tower 5 It branches off to the air system 24. Therefore, a switching device 27 is disposed at a branch point between the air system 23 from the cooler 4 and the air system 24 from the humidification tower 5. The stationary blade 30 is supplied with air of two systems via the casing 50 via a switching device 60 that switches between the compressed air system 21 compressed by the compressor 2 and the air of the humidified air system 28b. Is done. Here, when considering the thermal efficiency of the gas turbine power plant, the amount of air used for cooling should be as small as possible. Therefore, for cooling the turbine cooling section during gas turbine rated operation, humidified air with a high cooling effect should be used. Use.

  About the gas turbine comprised in this way, operation | movement from starting to a rated operation and a stop is demonstrated. Here, for convenience, the operation state of the gas turbine is divided into the following four processes. The first process is the state until the gas turbine is started up to the rated speed no-load operation, the second process is the condition until the load is gradually applied in the rated rotation state until the rated load operation is reached, the third process is the rated rotation rated load The state of operation, the fourth process, is the state from the rated rotational load operation state to the stop. FIG. 3 shows a comparison between the switching state of the switching device 60 at the time of starting the gas turbine and the change in the gap between the rotor blade tips between the present embodiment and the conventional case. The horizontal axis indicates the operating state of the gas turbine, the vertical axis indicates the state of the switching device 60 that switches between the two air systems in the stationary system, the amount of shroud displacement in the radial direction, the amount of displacement of the rotor blade tip that is the rotating system, and the blade tip clearance. Is the ratio. Here, the rotor blade tip clearance ratio on the vertical axis is 1.0 at the normal temperature when the turbine is stopped in the conventional case, and 0 is the case where the blade tip clearance is 0. Shown as a ratio. The operating state of the gas turbine on the horizontal axis is the region where the turbine speed ranges from 0 to 100%, that is, the first process, and the state where the turbine speed is 100%, ie, when the load reaches 0 to 100% at the rated speed. That is, the second process to the third process are shown.

  In the first process, the switching device 27 is set to flow the air of the air system 23 from the cooler 4 to the system 28a, and the switching device 60 is switched to the compressed air system 21 side compressed by the compressor 2. Therefore, the air of the cooler 4 is supplied to the moving blade 31 and the rotor 51 that are the rotating system, and the compressed air compressed by the compressor 2 is supplied to the stationary blade 30 and the casing 50 that are the stationary system.

  In the second process, the humidifying tower 5 operates in earnest, and the switching device 27 gradually switches from the air in the air system 23 from the cooler 4 to the air system 24 from the humidifying tower 5. The switching device 60 is gradually switched from the compressed air system 21 compressed by the compressor 2 to the humidified air system 28b. Therefore, cooling air is supplied to the rotor blades 31 and the rotor 51 which are rotating systems while gradually switching from the air from the cooler 4 to the humidified air from the humidifying tower 5. Further, the stationary blade 30 and the casing 50 are supplied while switching from compressed air to humid air.

  In the third process, the switching device 27 is set to supply the air system 24 from the humidification tower 5, and the switching device 60 is also on the humidified air system 28b side. For this reason, both the rotating system and the stationary system are cooled by humidified air.

  In the fourth process, the switching device 27 gradually switches from the air system 24 from the humidification tower 5 to the air in the air system 23 from the cooler 4. The switching device 60 is gradually switched from the humidified air system 28b to the compressed air system 21 compressed by the compressor 2. Cooling air is supplied to the rotor blades 31 and the rotor 51, which are rotating systems, while gradually switching from the humid air from the humidification tower 5 to the air from the cooler 4. Further, compressed air is supplied to the stationary blade 30 and the casing 50 in place of the humid air.

Here, the gap between the tip 91 of the rotor blade 31 and the shroud 90 mounted on the gas path side of the casing 50 is referred to as a rotor blade tip gap 92. The blade tip clearance 92 is desirably as small as possible in terms of turbine performance. However, if rubbing that causes the blade tip 91 to contact the shroud 90 during operation is caused, both the blade tip 91 and the shroud 90 are damaged. Depending on the damage state, the entire rotor blade 31 may be damaged, and operation may be hindered. For this reason, in general, the rotor blade tip gap 92 is designed not to fall below a minimum value set in consideration of a margin in all operating states from the start. The blade tip clearance is minimized at the time of startup between the first process and the second process.

  As described above, the gas turbine power plant according to the present embodiment includes the cooler 4, the humidification tower 5, and the regenerator 6. Therefore, the compressed air from the compressor and the air from the cooler are used as cooling air. , It is possible to use mainly four types of cooling media having different temperatures, ie, air from the humidification tower and air from the regenerator. Moreover, since these are of the system supplied to the combustor inlet as mainstream air, the conditions for the supply pressure are satisfied. In this embodiment, the gap control at the tip of the rotor blade is performed by effectively switching these cooling media in accordance with the operating state of the gas turbine.

  Specifically, one of the cooling systems branched into a plurality of upstream sides in the flow direction of the refrigerant supplied to the stationary blades supplies compressed air from the compressor to the stationary blades, The refrigerant is configured so that a refrigerant having a higher temperature than other systems is supplied to the stationary blade when the gas turbine is started.

  Thus, at the time of starting the gas turbine, the compressor is a refrigerant having a higher temperature than other systems among the compressed air from the compressor, the air from the cooler, the air from the humidification tower, and the air from the regenerator. By supplying the compressed air from the casing to the casing, the casing can be warmed up and its thermal elongation can be accelerated. As a result, the amount of reduction in the rotor blade tip clearance ratio in the first process can be reduced, and the clearance ratio at the time of stopping, that is, the initial clearance ratio can be set small even if the minimum value for avoiding rubbing is the same.

  Next, in the second process after exceeding the minimum value for avoiding rubbing, in order to suppress the thermal expansion of the casing by supplying humidified air having a temperature lower than that of the compressed air from the compressor to the casing, the rated operation is performed. In other words, the amount of displacement of the shroud in the third process finally becomes the same as in the conventional case, and the gap ratio during rated operation can be reduced by the amount that the initial gap ratio can be reduced.

  Therefore, it is possible to improve the performance of the gas turbine by avoiding rubbing during startup and ensuring the reliability of the gas turbine, and by reducing the rotor blade tip clearance during rated load operation.

  It should be noted that the effect of the rotor blade tip clearance control shown in the present embodiment is not limited in particular because it has a certain effect even by switching the stationary cooling air system.

  In the present embodiment, the reason why the air from the cooler 4 and the humidified air from the humidifying tower 5 which are the air before and after being supplied to the humidifying tower 5 is used as the cooling air for the rotating system is that the temperature difference between the two. This is because it is relatively small at about 50 ° C., and the thermal shock to the rotating system at the time of switching can be mitigated. Compressed air from the compressor 2 can be considered in place of the air from the cooler 4, but in this case, since the temperature difference is about 150 ° C., the thermal shock to the rotating system at the time of switching increases. Further, this is because the rotating system is warmed by compressed air having a high temperature when the gas turbine is started, and the amount of heat elongation increases, so that the initial gap needs to be expanded. Therefore, it is desirable to use the air from the cooler 4 and the humidified air from the humidification tower 5 as the cooling air for the rotating system.

  A detailed view of the gas turbine cooling system in the second embodiment is shown in FIG. 4, the description of the structure having the same number as in FIG. 1 is omitted. In this embodiment, the moving blade 31 and the rotor 51 are cooled by the air of the humidified air system 28a. In addition, the stationary blade 30 is switched by the switching device 61 while mixing the compressed air system 21 compressed by the compressor 2 and the system 70 air from the regenerator 6, and either one of the above-mentioned warming systems is heated. Cooling air is supplied by switching by the switching device 60b while mixing the machine air and the air of the humidified air system 28b.

The gas turbine configured as described above will be described in four operating states as in FIG. FIG. 5 shows the switching state of the switching device 60b and the switching device 61 at the time of starting the gas turbine and the change in the rotor blade tip clearance in comparison with the first embodiment and the conventional case, as in FIG. In FIG. 5, the definition of the blade tip clearance ratio is the same as in FIG.

  In the first process, the switching device 27 is set to flow the air of the air system 23 from the cooler 4 to the system 28 a, and the switching device 60 b is the compressed air system 21 compressed by the compressor 2 or the air of the regenerator 6. It is set to the warm-up air side to which the system 70 is supplied. Specifically, from the start to the initial stage, the switching device 61 is set to the side of supplying the air system 70 of the regenerator 6 and then gradually changing the mixing ratio to the compressed air system 21 compressed by the compressor. Switch to Therefore, the air of the cooler 4 is supplied to the rotor blades 31 and the rotor 51 which are rotating systems, and the air from the regenerator 6 is supplied to the stationary blades 30 and the casing 50 which are stationary systems from the start to the initial stage. After that, the compressed air of the compressor 2 is supplied.

  In the second process, the humidifying tower 5 operates in earnest, and the switching device 27 gradually switches from the air in the air system 23 from the cooler 4 to the air in the air system 24 from the humidifying tower 5. . The switching device 60b gradually switches from the compressed air system 21 to the humidified air system 28b. Therefore, cooling air is supplied to the rotor blades 31 and the rotor 51 which are rotating systems while gradually switching from the air from the cooler 4 to the humidified air from the humidifying tower 5. Further, humid air is supplied to the stationary blade 30 and the casing 50 in place of the compressed air.

  In the third process, the switching device 27 is set so that the humidified air is supplied from the air system 24 from the humidifying tower 5, and the switching device 60b is also set on the humidified air system 28b side. For this reason, both the rotating system and the stationary system are cooled by humidified air.

  In the fourth process, the switching device 27 gradually switches from the air system 24 from the humidification tower 5 to the air in the air system 23 from the cooler 4. The switching device 60b gradually switches from the humidified air system 28b to the compressed air system 21. Therefore, cooling air is supplied to the rotor blades 31 and the rotor 51, which are rotating systems, while gradually switching from the humid air from the humidification tower 5 to the air from the cooler 4. Further, compressed air is supplied to the stationary blade 30 and the casing 50 in place of the humid air.

  The basic effects are the same as those of the previous embodiment. However, the pressure ratio of the compressor does not rise sufficiently in the initial state when the gas turbine is started, and the temperature of the air from the regenerator 6 is higher than that of the compressed air. It is more effective. That is, by adopting such a configuration, the thermal expansion of the casing at the time of startup can be further accelerated, so that the initial gap can be further reduced. Therefore, the rotor blade tip gap at the time of rating can be further reduced. Alternatively, if the initial gap is set to be the same as that in the first embodiment, a margin can be secured for the minimum value for avoiding rubbing.

  In addition, there is a hot restart in which the gas turbine is restarted without taking sufficient cooling time after the operation is stopped. In this case, since the casing is exposed to the outside air, the temperature is lowered to some extent by heat radiation. However, since the rotor blades and the rotor of the rotating system are covered with the casing, the heat radiation is small and the casing is not completely cooled. In such a case, since the rotor blades and the rotor are already thermally expanded, it is conceivable that the gap exceeds the minimum value for avoiding rubbing. However, with the configuration of the present embodiment, the casing can be warmed by the residual heat of the regenerator. Therefore, the reduction in the blade tip clearance in the first process is mitigated by accelerating the thermal expansion of the casing. Thus, it is possible to control so as not to exceed the minimum value of rubbing avoidance.

  The blade tip clearance control described in the present embodiment is effective regardless of the blade and rotor cooling system, and is not particularly limited.

FIG. 6 shows a detailed view of the gas turbine cooling system in the third embodiment. In FIG. 6, a compressed air system 21 b is used as switching air at the time of startup on the upstream side of the humidified air system 28 a that cools the moving blade 31 and the rotor 51. In the case of such a system configuration, by using compressed air having a temperature higher than that of the cooler at the time of warming up, warming up in the cooling path of the piping and the moving blades 31 and the rotor 51 is promoted, and the starting time is shortened. I can do it. In this embodiment, since the regenerator air system 70 is used as a stationary system, the warm-up temperature has a margin. Therefore, the blade tip clearance can be made smaller than before by selecting the conditions.

  In the present embodiment, the system 70 has been described using the air at the outlet of the regenerator 6, but depending on the temperature conditions, the air extracted from the middle of the regenerator 6 may be extracted, and the take-out position is not particularly limited. .

  In this embodiment, since the compressed air of the compressor 2 and the air of the regenerator 6 are mixed while being mixed as the casing warm-up air, an arbitrary temperature is set between the two systems. Can be set.

  Further, although the present embodiment has been described by taking a high-humidity gas turbine plant as an example, even in a simple regenerative gas turbine, it is possible to warm up the casing using the air of the regenerator at the time of startup. This is effective when controlling the blade tip clearance, and is not particularly limited.

  In any case, by using the present invention, the blade tip clearance can be reduced during rated load operation to improve performance and to solve the problem of rubbing during startup to ensure reliability. Gas turbine can be provided.

It is a turbine cooling system figure showing an example of a gas turbine power plant. Example 1 It is a block diagram of the high humidity gas turbine power plant by one Embodiment. Example 1 It is a moving blade tip clearance explanatory diagram in a gas turbine. Example 1 It is a turbine cooling system figure showing other examples of a gas turbine power plant. (Example 2) It is a moving blade tip clearance explanatory diagram in a gas turbine. (Example 2) It is a turbine cooling system figure which shows the modification of the other Example of a gas turbine power plant. (Example 2)

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 ... Turbine, 2 ... Compressor, 3 ... Generator, 4 ... Cooler, 5 ... Humidification tower, 6 ... Regenerator, 7 ... Combustor, 8 ... Feed water heater, 9 ... Exhaust gas regenerator, 10 ... Water Recovery device, 11 ... chimney, 12,
DESCRIPTION OF SYMBOLS 16 ... Pump, 13 ... Desalination apparatus, 14 ... Intake sprayer, 15 ... Cooling water supply tank, 17 ... Cooler, 21 ... System of compressed air, 23 ... Air system from cooler, 24 ... From a humidification tower Air system, 27, 60, 60b, 61 ... switching device, 29 ... extracted air system from compressor intermediate stage, 30 ... stationary blade, 31 ... moving blade, 50 ... casing, 51 ... rotor, 70 ... from regenerator 90 ... shroud, 91 ... blade tip, 92 ... blade tip gap.

Claims (3)

A compressor for compressing the working fluid; a humidifying tower for humidifying the compressed air from the compressor; a combustor for mixing and burning the working fluid and fuel from the humidifying tower; and combustion from the combustor A turbine that is rotationally driven by gas, and a refrigerant supply method for a gas turbine, comprising: a stationary blade provided in a casing of the turbine; and a cooling system that supplies and cools a refrigerant to a moving blade provided in the turbine. ,
One of the cooling systems branched on the upstream side in the flow direction of the refrigerant supplied to the stationary blades supplies compressed air from the compressor to the stationary blades, and the other cooling system supplies an increase from the humidification tower. The cooling system is configured to supply wet air to the stationary blade,
In the gas turbine formed so that the cooling system of the stationary blades can switch between the discharge air of the compressor and the humidified air from the humidification tower, the discharge air from the compressor is A gas turbine refrigerant supply method comprising: switching to supply to a stationary blade and then supplying humidified air from the humidification tower to the stationary blade. Compressor for compressing working fluid; humidifier tower for increasing humidified compressed air from compressor; regenerator for heating humidified air from humidifier tower; working fluid and fuel from regenerator And a turbine that is rotationally driven by the combustion gas from the combustor, and supplies refrigerant to the stationary blades provided in the casing of the turbine and the moving blades provided in the turbine. A refrigerant supply method of a gas turbine including a cooling system for cooling,
One of the cooling systems branched on the upstream side in the flow direction of the refrigerant supplied to the stationary blades supplies air from the regenerator to the stationary blades, and the other cooling system is a humidifier from the humidifying tower. The cooling system is configured to supply air to the stationary blade,
In the gas turbine in which the cooling system of the stationary blade is configured to be able to switch between the air from the regenerator and the humidified air from the humidifying tower, the air from the regenerator is circulated at the start-up. A gas turbine refrigerant supply method comprising: switching to supply to the blades, and then switching to supplying the humidified air from the humidification tower to the stationary blades. The refrigerant supply method for a gas turbine according to claim 1 or 2,
One of the cooling systems branched on the upstream side in the flow direction of the refrigerant supplied to the moving blades supplies air to the moving blades before being supplied to the humidifying tower, and the other cooling system is the humidifying tower. The cooling system is configured to supply humidified air from
In the gas turbine formed so that the cooling system of the moving blade can be switched so as to supply the air before and after the supply to the humidifying tower, the air before being supplied to the humidifying tower is supplied to the moving blade at the time of start-up Then, the refrigerant supply method of the gas turbine is characterized by switching to supply the humidified air from the humidification tower to the moving blade.

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