JP2005315127A - Gas turbine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine for efficiently relieving reduction in output of a gas turbine by the high atmospheric temperature. <P>SOLUTION: This invention cools air inputted to a compressor by using exhaust heat of a rotary cooler for cooling moving blade cooling air of being conventionally effectively unused. Thus, gas turbine output reduction at the high atmospheric temperature can be relieved. <P>COPYRIGHT: (C)2006,JPO&NCIPI

Description

  The present invention relates to gas turbines, and more particularly to an intake air cooled gas turbine.

  In the current gas turbine, the output decreases in the summer when electricity demand is large. This is due to the fact that the air density introduced into the compressor of the gas turbine decreases in the summer due to the annual fluctuation of the temperature. In other words, since the amount of air taken into the combustor per unit time decreases in the summer, the amount of fuel per unit time combusted simultaneously in the combustor also decreases, and the output of the gas turbine itself decreases. by.

  In order to mitigate such a decrease in the output of the gas turbine during the summer, several methods for cooling the intake air to the compressor have been used in the conventional gas turbine. The method and the problems that the method has are described below.

(1) A method of injecting mist into the intake air and cooling the intake air by heat of vaporization. In this method, since the mist is vaporized only until the water vapor in the intake air is saturated, a sufficient cooling effect cannot be obtained when the humidity is high. Further, if the mist remains as a liquid at the compressor inlet, the compressor blades are corroded.

(2) A method of cooling the intake air by operating the absorption refrigerator using the heat of the exhaust gas.

    Normally, the heat of exhaust gas from a gas turbine is used as a steam turbine operation or heat source. However, if a part of the heat from the exhaust gas is used for the operation of an absorption chiller by this method, the heat from the steam turbine or heat source is used. The output will drop.

(3) A method of cooling the intake air using a separately installed refrigerator. The operation of this refrigerator requires fuel, power and electric power separately.

  With reference to FIG. 1, the whole structure of the conventional gas turbine which employ | adopted the method of said (3) is demonstrated. This conventional gas turbine includes a refrigerator 1, a compressor 2, a combustor 4, and a turbine 3.

  In the conventional gas turbine, the air 100 is introduced into the refrigerator 1, and the introduced air 100 is cooled in the refrigerator 1. The cold air 200 discharged from the refrigerator 1 is introduced into the compressor 2 and becomes compressed air. This compressed air and fuel are introduced into the combustor 4 and burned. By this combustion, combustion gas is generated in the combustor 4, and the turbine 3 is driven by the combustion gas. The output of the gas turbine is obtained by driving the turbine 3. The exhaust gas 300 discharged from the turbine 3 is also used for secondary applications such as a steam turbine (not shown).

  In a conventional gas turbine, a decrease in the output of the gas turbine due to an increase in atmospheric temperature in summer or the like can be mitigated by cooling the intake air introduced into the compressor by the refrigerator 1. However, in order to drive the refrigerator 1, fuel, power, and electric power are separately required as described in the prior art (3).

  Several proposals have been made in connection with the above problems.

  For example, in “combined cycle plant intake air cooling system” disclosed in Japanese Patent Application Laid-Open No. 8-158814, it is disposed between the exhaust heat boiler outlet and the stack in the combined cycle plant, and the high temperature exhaust gas at the exhaust heat boiler outlet is used. An exhaust heat recovery heat exchanger that recovers heat, a low-temperature water absorption refrigerator that uses hot water that has been recovered by the exhaust heat recovery heat exchanger as a heat source, and a gas turbine that is cooled by the low-temperature water absorption refrigerator An intake air cooling system for a combined cycle plant that includes an intake air cooler that cools the intake air is proposed.

  The "combined cycle system" disclosed in Japanese Patent Laid-Open No. 9-268905 includes a gas turbine, an exhaust heat recovery heat exchanger that transfers heat energy from the exhaust heat of the gas turbine to another fluid, and a steam turbine. A combined cycle system has been proposed. In this combined cycle system, the intake cooling of the gas turbine is performed by the intake cooling subsystem, and the exhaust heat energy of the gas turbine is used for the refrigerant heating of the absorption cooling subsystem.

  In addition, in the “combined cycle system and its intake air cooling method during summer full load” disclosed in Japanese Patent Laid-Open No. 10-238314, a combined cycle system including a gas turbine, an exhaust heat recovery heat exchanger, and a steam turbine is disclosed. Has been proposed. In this combined cycle system, thermal energy is output to the absorption cooling subsystem. In this absorption cooling subsystem, the refrigerant is evaporated by the heat energy of the vapor, and the refrigerant is further heated by the condensation heat of the evaporated refrigerant. The heated refrigerant is condensed by being cooled. The intake air entering the gas turbine is cooled by the heat of evaporation generated when the condensed refrigerant is evaporated under reduced pressure. As a result, compared to the same temperature and flow rate intake conditions when the gas turbine intake air is not cooled (winter season) when the temperature is high (summer) at full load, the steam flow is equivalent on the high pressure side of the steam turbine. On the low pressure side of the steam turbine, the same steam turbine can be used to reduce the steam flow rate to 1/10.

  In addition, in the “gas turbine intake air cooling device” disclosed in Japanese Patent Laid-Open No. 10-259737, a gas turbine, an intake air cooler for cooling outside air sucked by the gas turbine, and outside air sucked into the intake air cooler are disclosed. A gas turbine intake air cooling device has been proposed that includes an air cooling coil that sends cold water to cool the air and an absorption chiller that sends cold water to the air cooling coil. In this gas turbine intake air cooling device, an air cooling coil that sends cold water to cool outside air taken into the intake air cooler is divided into a plurality of systems. And the absorption refrigeration which the air cooling coil located in the most outside air is connected to the absorption refrigerator which sends cold water with the highest temperature, and the air cooling coil located in the gas turbine side sends cold water with the lowest temperature Connected to the machine.

  In addition, in the “chemical heat storage type intake air cooling device” disclosed in JP-A-11-117713, an air compressor having an intake air heat exchanger, a combustor, a gas turbine, a boiler, a steam turbine, A chemical heat storage type intake air cooling device installed in a combined cycle system equipped with a condenser and a generator has been proposed. The chemical heat storage type intake air cooling device includes a heat storage container that stores a chemical heat storage material, an evaporator that stores a refrigerant, and a condenser for condensing refrigerant vapor generated when the chemical heat storage material is regenerated. Further, there are provided means for thermally coupling the evaporator and the heat exchanger for cooling the intake air, and means for thermally coupling the heat storage container and the condenser to the condenser. Then, the chemical heat storage material is regenerated using exhaust heat from the gas turbine or steam generated from the boiler.

  In addition, in the “exhaust heat absorption chiller / heater / refrigerator” disclosed in JP-A-11-304274, an evaporator, an absorber, a condenser, a low temperature regenerator, a high temperature regenerator, a low temperature A reverse flow type waste heat utilizing absorption chiller / heater / refrigerator equipped with a heat exchanger, a high-temperature heat exchanger, and a solution pipe and a refrigerant pipe connecting these devices has been proposed. The solution pipe and the refrigerant pipe are connected and arranged so that the absorption liquid is pumped from the absorber to the low-temperature regenerator and further pumped to the high-temperature regenerator. By adding / installing at least one auxiliary regenerator to this waste heat absorption chiller / heater / refrigerator, heat and concentrate the absorption liquid by introducing combustion waste heat from the gas turbine into the high temperature regenerator. It has been used to A gas turbine combustion waste heat supply pipe is inserted into the high temperature regenerator and auxiliary regenerator so that the combustion waste heat whose temperature has decreased can be introduced into the auxiliary regenerator and used for heating and concentrating the absorption liquid. Yes.

  In addition, in the “gas turbine cogeneration system” disclosed in Japanese Patent Application Laid-Open No. 2002-266656, a gas turbine that drives a generator by burning fuel, and exhaust heat that recovers heat of exhaust gas from the gas turbine and generates steam. A gas equipped with a recovery boiler, a hot water boiler that further recovers the heat of exhaust gas that has passed through the exhaust heat recovery boiler and generates hot water, and an adsorption refrigeration machine that generates cold water using the hot water generated in the hot water boiler as a driving heat source A turbine cogeneration system has been proposed.

JP-A-8-158814 JP-A-9-268905 JP-A-10-238314 JP-A-10-259737 JP-A-11-117713 JP-A-11-304274 JP 2002-266656 A

  The subject of this invention is providing the gas turbine which relieves the output fall of the gas turbine by high atmospheric temperature efficiently.

  In the following, means for solving the problem will be described using reference numerals with parentheses used in [Best Mode for Carrying Out the Invention]. These symbols are added in order to clarify the correspondence between the description of [Claims] and the description of the best mode for carrying out the invention. ] Should not be used for interpretation of the technical scope of the invention described in the above.

  The gas turbine of the present invention includes a combustor (40), a turbine (30), a compressor (20), a heat exchanger (50), and an absorption refrigerator (70), and includes a compressor (20). When the compressed air is cooled by the heat exchanger (50), the turbine (30) heated by the combustion gas from the combustor (40) is air-cooled, and heat is exchanged when the compressed air is cooled. Using the heat generated by the vessel (50), the absorption chiller (70) cools the air and the cooled air (200) is introduced into the compressor (20).

  Moreover, the heat exchanger with which the gas turbine of this invention is equipped is a rotor cooler (50).

  The gas turbine of the present invention further includes a fuel preheater (150), and is the fuel preheater (150) connected in series between the heat exchanger (50) and the absorption refrigerator (70)? Or connected in parallel to the heat exchanger (50) together with the absorption refrigerator (70), the fuel preheater (150) is driven by the heat generated from the heat exchanger (50), and the fuel preheater (150 ) Is heated to the combustor (40).

  The gas turbine of the present invention further includes a heat flow rate supplied from the heat exchanger (50) to the absorption refrigerator (70) and a heat flow rate supplied from the heat exchanger (50) to the fuel preheater (150). And means for adjusting the flow rate ratio.

  Further, in the gas turbine of the present invention, the heat flow rate supplied from the heat exchanger (50) to the absorption refrigerator (70), and the heat flow rate supplied from the heat exchanger (50) to the fuel preheater (150), The flow rate adjustment valve (61, 152) installed at the branch part of the pipe for sending heat from the heat exchanger (50) to the absorption refrigerator (70) and the fuel preheater (150) It is.

  The absorption chiller of the gas turbine of the present invention is a multi-effect absorption chiller (700), and the multi-effect absorption chiller (700) is a plurality of regenerators (720A, 720B) driven at different temperatures. Have

  The gas turbine of the present invention further includes an exhaust heat recovery boiler (400), or an exhaust heat recovery boiler (400) and an exhaust heat recovery heat exchanger (500), and the exhaust heat recovery boiler (400) or the exhaust heat recovery. The absorption refrigerator (70) or the multi-effect absorption refrigerator (700) is driven by one of the heat exchangers (500).

  Moreover, the gas turbine of this invention is the fuel preheater (150), absorption refrigerator (70), and multi-effect absorption refrigerator (700) with which the gas turbine was equipped with the air compressed with the compressor (20). Is driven directly.

  Further, the gas turbine of the present invention further includes a bypass duct (600), the bypass duct (600) is installed at the inlet of the compressor, and the air introduced into the compressor (20) is absorbed into the absorption refrigerator (70) or It can be selected from air (200) cooled by the multi-effect absorption refrigerator (700) and air (100) taken directly from the atmosphere by the bypass duct (600).

  Further, the gas turbine of the present invention is an air (100) into which the intake cooling refrigerant (80) generated by the absorption refrigerator (70) or the multi-effect absorption refrigerator (700) is introduced into the compressor (20). It can be used for applications other than the cooling of

  The turbine of the present invention further includes an output monitoring monitor, and the heat flow rate supplied from the heat exchanger (50) to the absorption refrigerator (70) and from the heat exchanger (50) to the fuel preheater (150). A gas turbine that is adjusted so that an output display of an output monitoring monitor is maintained at a specified output value by means of adjusting a flow rate ratio with a supplied heat flow rate.

  The output control method for a gas turbine according to the present invention includes a combustor (40), a turbine (30), a compressor (20), a fuel preheater (150), a heat exchanger (50), and an absorption. The heat supplied to the absorption refrigerator (70) from the refrigerator (70), the output display monitor and the heat exchanger (50), and the heat supplied from the heat exchanger (50) to the fuel preheater (150). In a gas turbine comprising means for adjusting a flow rate ratio with respect to a flow rate, introducing a fuel and air compressed by a compressor (20) into a combustor (40) to generate combustion gas; The turbine (30) is driven to extract the output, the air compressed by the compressor (20) is cooled by the heat exchanger (50), and heated by the combustion gas from the combustor (40) Turbine (30) with cooled air And the step of cooling the air by the absorption refrigerator (70) using the heat generated by the heat exchanger (50) when cooling the compressed air, and the absorption refrigerator (70) A step of introducing cooled air into the compressor (20), a step of monitoring the output of the gas turbine by an output display monitor, and a step of controlling the output of the gas turbine based on the output monitoring result, The step of controlling the output of the turbine includes heat flow supplied from the heat exchanger (50) to the absorption refrigerator (70), heat flow supplied from the heat exchanger (50) to the fuel preheater (150), and And adjusting the flow rate ratio so that the output display of the output monitoring monitor is maintained at the specified output value.

  In the present invention, the air introduced into the compressor is cooled by utilizing the exhaust heat of the rotor cooler for cooling the rotor blade cooling air that has not been effectively used in the past. Thereby, the output fall of the gas turbine at the time of high atmospheric temperature can be relieved.

  The best mode for carrying out a gas turbine according to the present invention will be described below with reference to the accompanying drawings.

(First embodiment)
FIG. 2 shows an overall configuration diagram of the gas turbine according to the first embodiment. The gas turbine according to the present embodiment includes a compressor 20, a turbine 30, a combustor 40, a rotor cooler 50, an intake air cooling heat exchanger 10, and an absorption refrigerator 70. The absorption refrigerator 70 includes a condenser 71, a regenerator 72, an evaporator 73, an absorber 74, and a preheater 75.

  The evaporator 73 provided in the absorption refrigerator 70 has an internal pressure of about 0.01 atm. For this reason, the refrigerant (water) sprayed on the heat transfer tube of the evaporator 73 evaporates under a low pressure. At that time, since the cold water flowing in the heat transfer tubes is deprived of the heat of vaporization, the temperature of the cold water decreases. In the absorber 74 maintained at substantially the same pressure as the evaporator 73, the lithium bromide aqueous solution sprayed on the heat transfer tube absorbs the refrigerant evaporated in the evaporator 73. The solution whose concentration is reduced by absorbing the refrigerant is sent from the absorber 74 to the regenerator 72 by a circulation pump. In the regenerator 72, the solution is heated and concentrated by gas combustion or the like, the water absorbed by the absorber 74 is separated, regenerated into a high-concentration solution, and sent back to the absorber 74 again. Further, the vapor separated by the regenerator 72 is sent to the condenser 71, cooled by cooling water, condensed, and returned to the evaporator 73 again. Thus, the refrigerant goes around the absorption refrigerator 70. By repeating the cycle of the absorbing solution / refrigerant, the intake cooling refrigerant 80 (cold water) whose temperature has decreased due to the loss of vaporization heat (latent heat of vaporization) can be continuously taken out from the evaporator 73.

  In the gas turbine of the present embodiment, the fuel and the air compressed by the compressor 20 are introduced into the combustor 40 and burned. When combustion is performed in the combustion chamber, combustion gas is generated and ejected downstream of the combustion chamber. The turbine is driven by the jetted combustion gas, and the work of the gas turbine is taken out. The combustion gas after driving the turbine is discharged from a gas turbine casing (not shown) as exhaust gas 300. Turbine blades heated to a high temperature by combustion gas during combustion are compressed by a compressor 20 and cooled by turbine blade cooling air 90 cooled by a rotor cooler 50. The heat generated when the air compressed by the compressor 20 is cooled by the rotor cooler 50 is used to operate the absorption refrigerator 70 via the rotor cooler refrigerant 60. When the absorption refrigerator 70 is operated, the absorption cooling heat exchanger 10 is operated via the absorption cooling refrigerant 80 circulating through the evaporator 73 of the absorption refrigerator 70. And the air 100 is cooled with the heat exchanger 10 for absorption cooling, and the cold air 200 introduce | transduced into the compressor 20 of the gas turbine of this Embodiment is produced | generated. Thus, the gas turbine output can be kept constant throughout the year without reducing the mass flow rate of the air introduced into the compressor 20 even in summer.

  In the present embodiment, the exhaust heat generated when cooling the moving blade cooling air 90 that has not been used sufficiently effectively conventionally is used to drive the absorption refrigerator 70 via the rotor cooler refrigerant 60. . By this absorption refrigerator 70, the cooling air 200 introduced into the compressor 20 of the gas turbine is generated. Thereby, the increase in the intake air density introduced into the gas turbine combustor 40 can mitigate the decrease in gas turbine output in the summer.

(Second Embodiment)
FIG. 3 shows an overall configuration diagram of the gas turbine according to the second embodiment. The gas turbine of the present embodiment has basically the same structure as that of the first embodiment. However, the difference from the first embodiment is that this embodiment further includes a fuel preheater 150.

  In the gas turbine of the present embodiment, the fuel preheater 150 is driven to heat the fuel 151 by using the heat generated from the rotor cooler 50 that cools the turbine blade cooling air 90 through the rotor cooler refrigerant 60. doing. Thereafter, the dilute solution is heated in the regenerator 72 of the absorption refrigerator 70 by further passing through the rotor cooler refrigerant 60.

  Thus, in the present embodiment, in addition to the effects shown in the first embodiment, the efficiency of the gas turbine can be improved by preheating the fuel 151 using the exhaust heat of the rotor cooler 50. it can.

(Third embodiment)
FIG. 4 shows an overall configuration diagram of a gas turbine according to the third embodiment. The gas turbine of the present embodiment has basically the same structure as that of the second embodiment. However, the difference from the second embodiment is that this embodiment further includes a bypass flow rate adjusting valve 152.

  In the gas turbine according to the present embodiment, a part or all of the rotor cooler refrigerant 60 can bypass the fuel preheater 150. A bypass flow rate adjusting valve 152 is disposed at a branch portion between the pipe through which the rotor cooler refrigerant 60 is delivered to the fuel preheater 150 and the pipe to be bypassed. The bypass flow rate adjusting valve 152 can adjust the flow rate ratio between the rotor cooler refrigerant 60 delivered from the rotor cooler 50 to the fuel preheater 150 and the rotor cooler refrigerant 60 delivered to the bypass.

  In the gas turbine shown in the second embodiment, the efficiency of the gas turbine is increased by preheating the fuel 151 with the fuel preheater 150. However, in this case, the exhaust heat that can be used for intake air cooling decreases, so that the gas turbine output decreases as compared with the gas turbine shown in the first embodiment that does not include the fuel preheater 150.

  In the gas turbine of the present embodiment, by adjusting the provided bypass flow rate adjustment valve 152, when the gas turbine needs a large output, the flow rate delivered to the bypass of the rotor cooler refrigerant 60 is increased. Priority is given to the output of the gas turbine. Further, when it is desired to operate with priority on the efficiency of the gas turbine, the bypass flow rate adjusting valve 152 can increase the flow rate ratio of the rotor cooler refrigerant 60 delivered to the fuel preheater 150 to make the operation with emphasis on efficiency. .

  As described above, in the present embodiment, in addition to the effects shown in the first and second embodiments, by adjusting the bypass flow rate adjustment valve 152, the rotor curler refrigerant 60 delivered to the fuel preheater 150 is adjusted. By adjusting the flow rate, it is possible to perform an operation that prioritizes the output of the gas turbine or an operation that prioritizes the efficiency of the gas turbine according to the situation.

(Fourth embodiment)
FIG. 5 shows an overall configuration diagram of a gas turbine according to the fourth embodiment. In the second and third embodiments, the fuel preheater 150 and the absorption refrigerator 70 are connected in series. In the gas turbine of the present embodiment, the fuel preheater 150 and the absorption refrigerator 70 are roller coolers. 50 in parallel. Further, in the present embodiment, when the exhaust heat from the rotor cooler 50 is distributed to the fuel preheater 150 and the absorption chiller 70 via the rotor cooler refrigerant 60, the amount of distribution can be adjusted. A heat distribution amount adjusting valve 61 is provided.

  In the gas turbine of the present embodiment, the fuel preheater 150 and the absorption chiller 70 are connected in parallel to the roller cooler 50, so that both the fuel preheater 150 and the absorption chiller 70 have rotors. High temperature heat from the cooler 50 can be supplied. Thereby, the high-temperature fuel 151 is supplied to the combustor 40, and the efficiency of the gas turbine is increased. Further, the high-temperature heat circulates in the regenerator 72 of the absorption refrigerator 70, thereby increasing the heating and concentration efficiency of the solution. Thereby, the cooling efficiency of the absorption refrigeration machine 70 is improved, and as a result, the production efficiency of the cold air 200 sucked into the compressor 20 is increased, thereby increasing the efficiency of the gas turbine.

  Further, in the present embodiment, the exhaust heat distribution amount adjusting valve 61 is arranged at a branch portion of the pipe through which the rotor cooler refrigerant 60 is distributed to the fuel preheater 150 and the absorption refrigerator 70. The ratio of the distribution amount of the rotor cooler refrigerant 60 to the fuel preheater 150 and the distribution amount to the absorption refrigerator 70 can be adjusted by the exhaust heat distribution amount adjustment valve 61. Thereby, the exhaust heat from the rotor cooler 50 can be delivered to the fuel preheater 150 and the absorption refrigerator 70 at an arbitrary distribution ratio.

  In the gas turbine of the present embodiment, the flow rate delivered to the absorption refrigerator 70 of the rotor cooler refrigerant 60 when a large output is required for the gas turbine by adjusting the provided exhaust heat distribution amount adjustment valve 61. The ratio is increased. Further, when it is desired to operate with priority on the efficiency of the gas turbine, the exhaust heat distribution amount adjustment valve 61 increases the flow rate ratio of the rotor cooler refrigerant 60 delivered to the fuel preheater 150 to increase efficiency. be able to.

  Thus, in this embodiment, in addition to providing a gas turbine that is more efficient than the gas turbines shown in Embodiments 2 and 3, the exhaust heat is similar to the gas turbine shown in Embodiment 3. By adjusting the distribution amount adjusting valve 61, the flow rate of the rotor cooler refrigerant 60 delivered to the absorption refrigerator 70 and the fuel preheater 150 is adjusted, so that the output of the gas turbine is given priority according to the situation. It is possible to make the operation with priority given to the efficiency of the gas turbine or the efficiency of the gas turbine.

(Fifth embodiment)
FIG. 6 shows an overall configuration diagram of a gas turbine according to the fifth embodiment. The gas turbine of the present embodiment includes a multi-effect absorption refrigerator 700 having a plurality of regenerators driven at different temperatures, instead of the absorption refrigerator 70 shown in the first to fourth embodiments. Yes.

  The basic operation principle of the multi-effect absorption refrigerator 700 is the same as that of the absorption refrigerator 70 described in the first embodiment. However, the regenerator includes a high temperature regenerator 720A and a low temperature regenerator 720B. The exhaust heat from the rotor cooler 50 is delivered directly to the high temperature regenerator 720A through the rotor cooler refrigerant 60, and a high concentration solution is regenerated in the high temperature regenerator 720A. Thereafter, the rotor-cooler refrigerant 60 whose temperature has dropped is delivered from the high-temperature regenerator 720A to the low-temperature regenerator 720B. In the low-temperature regenerator 720 </ b> B, the solution is heated and concentrated by the rotor cooler refrigerant 60 that has fallen in temperature, and the rotor cooler refrigerant 60 is sent back to the rotor cooler 50 again. As described above, in the present embodiment, the high-temperature heat from the rotor cooler 50 is efficiently used for cooling the absorption cooling refrigerant 80 in the multi-effect absorption refrigerator 700. For this reason, the multi-effect absorption refrigerator 700 can produce the cold air 200 introduced into the compressor 20 more efficiently than the absorption refrigerator 70. Thereby, by increasing the intake air density introduced into the gas turbine combustor 40, the output of the gas turbine in summer can be improved more efficiently than in the first to fourth embodiments.

(Sixth embodiment)
FIG. 7 shows an overall configuration diagram of a gas turbine according to the sixth embodiment. The gas turbine according to the present embodiment is obtained by further adding fuel preheated air 150 to the gas turbine shown in the fifth embodiment.

  In the present embodiment, the high-temperature rotor cooler refrigerant 60 from the rotor cooler 50 is delivered to the high-temperature regenerator 720 </ b> A of the multi-effect absorption refrigerator 700 and sent to the fuel preheated air 150. Cold air 200 introduced into the compressor 20 through the multi-effect absorption refrigerator 700 is created. As a result, as described in the fifth embodiment, the output of the gas turbine can be improved. Further, the fuel preheater 150 heats the fuel 151 introduced into the combustor 40 of the gas turbine, whereby the efficiency of the gas turbine can be improved.

  In the present embodiment, by providing the multi-effect absorption refrigerator 700 and the fuel preheater 150, it is possible to efficiently create the cold air 200 introduced into the compressor 20, and to improve the efficiency of the gas turbine. The output efficiency of the gas turbine can be increased particularly in summer.

(Seventh embodiment)
FIG. 8 shows an overall configuration diagram of a gas turbine according to the seventh embodiment. The gas turbine of the present embodiment includes an absorption refrigerator 800 having a plurality of regenerators instead of the absorption refrigerator 70 shown in the first to fourth embodiments. Further, the present embodiment includes an exhaust heat recovery boiler 400 on the flow path of exhaust gas exhausted from the turbine, and further includes an exhaust heat recovery heat exchanger 500 downstream of the exhaust heat recovery boiler 400.

  In the gas turbine according to the present embodiment, the combustion gas generated in the combustor 40 drives the turbine 30 to work, and the combustion gas is discharged as an exhaust gas 300 from a gas turbine casing (not shown). The exhaust gas 300 is introduced into the exhaust heat recovery boiler 400, and steam or the like is generated in the exhaust heat recovery boiler 400 by the heat. The steam or the like drives a steam turbine (not shown) to take out work. Further, the exhaust gas 300 exhausted from the exhaust heat recovery boiler 400 is introduced into the exhaust heat recovery heat exchanger 500. Warm water and steam 550 are also generated in the exhaust heat recovery heat exchanger 500 by the heat of the exhaust gas 300.

  In the present embodiment, the rotor cooler refrigerant 60 for exchanging heat from the rotor cooler 50 and the water and steam 550 generated by the exhaust heat recovery heat exchanger 500 are simultaneously regenerated by the regenerators 820A and 820B of the absorption refrigerator 800. And the absorption refrigerator 800 is driven. By using the absorption refrigerator 800 having high driving efficiency, the production efficiency of the cold air 200 introduced into the compressor 20 is increased. Thereby, the gas turbine output of this form improves.

  In the present embodiment, the regenerator of the gas turbine may be separately provided as shown in FIG. 8, or one regenerator may be used in common. Further, the water and steam 550 of the exhaust heat recovery heat exchanger 500 may be configured to use the rotor-cooler refrigerant 60 in common. In addition to this, instead of providing the exhaust heat recovery heat exchanger 500 independently, a part of the heat transfer tube of the exhaust heat recovery boiler 400 can be used instead.

  In the present embodiment, the gas turbine shown in the first to fourth embodiments is further provided with an exhaust heat recovery boiler 400 and an exhaust heat recovery heat exchanger 500, so that in addition to work taken out by the gas turbine itself, The work taken out by a steam turbine (not shown) can be combined into the work taken out as a whole. Further, by driving the absorption refrigerator 800 with the heat of the rotor cooler 50 and the heat of the exhaust heat recovery heat exchanger 500, the cool air 200 can be efficiently created. Thereby, the output efficiency of the gas turbine in the summer can be improved by increasing the intake air density introduced into the gas turbine combustor 40.

(Eighth embodiment)
FIG. 9 shows an overall configuration diagram of a gas turbine according to the eighth embodiment. The gas turbine of the present embodiment includes a multi-effect absorption refrigerator 700 shown in the fifth and sixth embodiments in place of the absorption refrigerator 800 shown in the seventh embodiment.

  In the present embodiment, the rotor cooler refrigerant 60 is circulated to the high-temperature regenerator 720A of the multi-effect absorption refrigerator 700, and the water and steam 550 of the exhaust heat recovery heat exchanger 500 are circulated to the low-temperature regenerator 720B. . Thereby, the drive efficiency of the multi-effect absorption refrigerator 700 can be improved, and the production efficiency of the cool air 200 in the intake air cooling heat exchanger 10 is increased. And the output efficiency of the gas turbine in the summer can be improved by increasing the intake air density introduced into the gas turbine combustor 40.

(Ninth embodiment)
FIG. 10 shows an overall configuration diagram of a gas turbine according to the ninth embodiment. In the gas turbine of the present embodiment, the absorption chillers 70, 700, and 800 and the fuel preheater 150 are driven through the refrigerant in the gas turbine shown in the first to eighth embodiments. This is done by directly using the turbine blade cooling air 90 produced by the compressor 20.

  For this reason, in this Embodiment, the rotor cooler 50 can be abbreviate | omitted as a component, and a structure can be simplified. Further, the piping to which the rotor cooler refrigerant 60 is delivered is replaced with the piping to which the turbine rotor blade cooling air 90 is delivered, so that replenishment of refrigerant and maintenance of the refrigerant piping become unnecessary.

(Tenth embodiment)
FIG. 11 shows an overall configuration diagram of a gas turbine according to the tenth embodiment. In the gas turbine of the present embodiment, a bypass duct 600 is installed at the inlet of the compressor 20 in the gas turbine shown in the first to ninth embodiments. In the winter season when the air density is high, the air 100 is bypassed by the intake-air cooling heat exchanger 10 and introduced into the compressor 20.

  In the present embodiment, when the intake air density is high, such as in winter, the intake air pressure loss can be reduced by directly introducing the air 100 into the compressor 20 without going through the intake air cooling heat exchanger 10. Thereby, the efficiency of a gas turbine can be improved.

(Eleventh embodiment)
FIG. 12 shows an overall configuration diagram of a gas turbine according to the eleventh embodiment. In the gas turbine according to the present embodiment, in the gas turbine shown in the first to tenth embodiments, a part or all of the intake air cooling refrigerant 80 obtained by the absorption chillers 70, 700, and 800 may be a cooling or a refrigerator. Used for applications other than gas turbines.

  In the present embodiment, a part or all of the intake air cooling refrigerant 80 obtained by the absorption refrigerators 70, 700, and 800 is used for applications other than the gas turbine such as cooling and refrigerator, so that the absorption refrigerator absorption refrigerator 70, 700, 800 can be used in many ways.

(Twelfth embodiment)
FIG. 13 shows an overall configuration diagram of a gas turbine according to the twelfth embodiment. The gas turbine of the present embodiment is the same as the gas turbine shown in the third embodiment. However, the gas turbine according to the present embodiment includes an output monitoring device (not shown) that monitors the output of the turbine.

  As shown in FIG. 14, when a required output is defined, a bypass flow rate that results in this output is uniquely determined. In order to maintain this output, the bypass flow rate adjustment valve 152 is adjusted. When the current gas turbine output is small relative to the required gas turbine output, the bypass flow rate adjustment valve 152 is adjusted so that the flow rate ratio delivered to the bypass of the rotor cooler refrigerant 60 is increased. Further, when the current gas turbine output is larger than the required gas turbine output, the bypass flow rate adjustment valve 152 is adjusted so that the flow rate ratio delivered to the bypass of the rotor cooler refrigerant 60 becomes smaller.

  By performing such adjustment, in this embodiment, it is possible to obtain the maximum efficiency under the specified output while obtaining the necessary output.

(13th Embodiment)
FIG. 15 shows an overall configuration diagram of a gas turbine according to the thirteenth embodiment. The gas turbine of the present embodiment is the same as the gas turbine shown in the fourth embodiment. However, the gas turbine according to the present embodiment includes an output monitoring device (not shown) that monitors the output of the gas turbine.

  As shown in FIG. 16, when the required output is defined, the rotor-cooler refrigerant flow rate to the absorption refrigerator that provides this output is uniquely determined. In order to maintain this output, the exhaust heat distribution amount adjusting valve 61 is adjusted. When the current gas turbine output is smaller than the required gas turbine output, the exhaust heat distribution amount adjusting valve 61 is adjusted so that the rotor cooler refrigerant flow rate ratio of the rotor cooler refrigerant 60 to the absorption chiller is increased. In addition, when the current gas turbine output is larger than the required gas turbine output, the exhaust heat distribution amount adjusting valve 61 is adjusted so that the rotor cooler refrigerant flow ratio of the rotor cooler refrigerant 60 to the absorption refrigerator becomes smaller. The

  By performing such adjustment, in this embodiment, it is possible to obtain the maximum efficiency under the specified output while obtaining the necessary output.

It is a figure which shows the whole structure of the gas turbine concerning the conventional embodiment. 1 is a diagram illustrating an overall configuration of a gas turbine according to a first embodiment. FIG. 3 is a diagram illustrating an overall configuration of a gas turbine according to a second embodiment. FIG. 6 is a diagram illustrating an overall configuration of a gas turbine according to a third embodiment. FIG. 6 is a diagram illustrating an overall configuration of a gas turbine according to a fourth embodiment. FIG. 10 is a diagram illustrating an overall configuration of a gas turbine according to a fifth embodiment. FIG. 10 is a diagram illustrating an overall configuration of a gas turbine according to a sixth embodiment. FIG. 10 is a diagram illustrating an overall configuration of a gas turbine according to a seventh embodiment. FIG. 10 is a diagram illustrating an overall configuration of a gas turbine according to an eighth embodiment. FIG. 10 is a diagram illustrating an overall configuration of a gas turbine according to a ninth embodiment. FIG. 10 is a diagram illustrating an overall configuration of a gas turbine according to a tenth embodiment. FIG. 20 is a diagram illustrating an overall configuration of a gas turbine according to an eleventh embodiment. FIG. 18 is a diagram illustrating an overall configuration of a gas turbine according to a twelfth embodiment. It is a figure which shows the relationship between the flow volume of the flow path which bypasses the fuel preheater concerning Embodiment 12, and the output of a gas turbine. FIG. 20 is a diagram illustrating an overall configuration of a gas turbine according to a thirteenth embodiment. It is a figure which shows the relationship between the rotor-cooler refrigerant | coolant flow rate which enters into the absorption refrigerator concerning Embodiment 13, and the output of a gas turbine.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 ... Refrigerator 10 ... Heat exchanger 2 for intake air cooling, 20 ... Compressor 3, 30 ... Turbine 4, 40 ... Combustor 50 ... Rotor cooler 60 ... Rotor cooler refrigerant 70, 700, 800 ... Absorption refrigerator 71, 710 810: Condenser 72, 820A, 820B Regenerator 73, 730, 830 ... Evaporator 74, 740, 840 ... Absorber 75, 750A, 750B, 750C, 850 ... Preheater 80 ... Refrigerant 90 for intake air cooling ... Turbine Rotor cooling air 100 ... Air 150 ... Fuel preheater 151 ... Fuel 152 ... Bypass flow control valve 200 ... Cool air 300 ... Exhaust gas 400 ... Exhaust heat recovery boiler 500 ... Exhaust heat recovery heat exchanger 550 ... Water, steam 600 ... Bypass Duct 720A ... high temperature regenerator 720B ... low temperature regenerator

Claims (12)

A combustor,
A turbine,
A compressor,
A heat exchanger,
An absorption refrigerator,
The air compressed by the compressor is cooled by the heat exchanger, and the turbine heated by the combustion gas from the combustor is air-cooled,
Using the heat generated by the heat exchanger in cooling the compressed air, the absorption chiller cools the air,
The cooled air is a gas turbine that is introduced into the compressor. The gas turbine according to claim 1, wherein
The heat exchanger is a gas turbine which is a rotor cooler. The gas turbine according to claim 1 or 2,
It also has a fuel preheater,
The fuel preheater is connected in series between the heat exchanger and the absorption refrigerator, or connected in parallel with the absorption refrigerator to the heat exchanger,
The fuel preheater is driven by the heat generated from the heat exchanger,
A gas turbine in which fuel heated by the fuel preheater is introduced into the combustor. The gas turbine according to claim 3, wherein
Furthermore, a gas turbine comprising means for adjusting a flow rate ratio between a heat flow rate supplied from the heat exchanger to the absorption refrigerator and a heat flow rate supplied from the heat exchanger to the fuel preheater. The gas turbine according to claim 4, wherein
The said means is a gas turbine which is a flow control valve installed in the branch part of the piping which sends heat from the said heat exchanger to the said absorption refrigerator and the said fuel preheater. In the gas turbine according to any one of claims 1 to 5,
The absorption refrigerator is a multi-effect absorption refrigerator;
The multi-effect absorption refrigerator is a gas turbine having a plurality of regenerators driven at different temperatures. In the gas turbine according to any one of claims 1 to 6,
Furthermore, it has an exhaust heat recovery boiler, or an exhaust heat recovery boiler and an exhaust heat recovery heat exchanger,
A gas turbine that drives the absorption refrigerator or the multi-effect absorption refrigerator by one of the exhaust heat recovery boiler or the exhaust heat recovery heat exchanger. In the gas turbine according to any one of claims 1 to 7,
A gas turbine in which the fuel preheater, the absorption chiller, and the multi-effect absorption chiller provided in the gas turbine are directly driven by the air compressed by the compressor. The gas turbine according to any one of claims 1 to 8,
In addition, with a bypass duct,
The bypass duct is installed at the compressor inlet;
The gas turbine which can select the air introduce | transduced into the said compressor from the air cooled by the said absorption refrigerator or the said multi-effect absorption refrigerator, and the air taken in directly from air | atmosphere by a bypass duct. The gas turbine according to any one of claims 1 to 9,
The gas turbine which can use the refrigerant | coolant for intake air cooling produced | generated by the said absorption refrigerator or the said multi-effect absorption refrigerator for uses other than cooling of the air introduce | transduced into the said compressor. The gas turbine according to claim 4 or 5,
In addition, equipped with an output monitoring monitor,
By means for adjusting the flow rate ratio between the heat flow rate supplied from the heat exchanger to the absorption refrigerator and the heat flow rate supplied from the heat exchanger to the fuel preheater,
A gas turbine that is adjusted so that an output display of the output monitor is maintained at a specified output value. Combustor, turbine, compressor, fuel preheater, heat exchanger, absorption refrigerator, output display monitor, heat flow supplied from the heat exchanger to the absorption refrigerator, and heat exchange A gas turbine comprising: means for adjusting a flow rate ratio with a heat flow rate supplied from a gas generator to the fuel preheater;
Introducing fuel and air compressed by the compressor into the combustor to generate combustion gas;
Driving the turbine with the combustion gas to extract output;
Cooling the air compressed by the compressor with the heat exchanger;
Cooling the turbine heated by the combustion gas from the combustor with the cooled air;
The absorption chiller cools the air using heat generated by the heat exchanger when cooling the compressed air; and
Introducing the air cooled by the absorption refrigerator into the compressor;
Monitoring the output of the gas turbine with the output display monitor;
Controlling the output of the gas turbine based on the monitoring result of the output,
The step of controlling the output of the gas turbine comprises:
An output display of the output monitor monitor by the means for adjusting a flow rate ratio between a heat flow rate supplied from the heat exchanger to the absorption refrigerator and a heat flow rate supplied from the heat exchanger to the fuel preheater. Adjusting the output so as to be maintained at a specified output value.

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