JP2001193482A - Gas turbine intake air cooling device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a compact gas turbine intake air cooling device, with high cooling efficiency. SOLUTION: This gas turbine intake air cooling device 100 cools intake air from an air compressor 72 of a gas turbine 70, and is equipped with a low- temperature air generation part 10 for cooling air extracted from the air compressor 72 and generating low-temperature air in a supercooled state before liquefaction, and a gas turbine intake air cooling part 20 for cooling the intake air from the air compressor 72 of the gas turbine 70 with the use of the low- temperature air generated at the low-temperature air generation part 10. This gas turbine intake air cooling device 100 efficiently cools the air extracted from the air compressor 72 to generate the low-temperature air and returns it to the intake air to the air compressor 72 of the gas turbine 70. Thus, the power to generate the low-temperature air is reduced and the compact gas turbine with high cooling efficient can be provided.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine intake air cooling system for cooling the intake air of an air compressor of a gas turbine.

[0002]

2. Description of the Related Art Conventionally, gas turbines (hereinafter referred to as appropriate)
Called GT. As a method for preventing a decrease in output and efficiency during the operation of ()), a method of cooling the intake air of a GT compressor is known, and specific examples thereof include the following method. (1) A method of lowering the temperature of the intake air at the inlet of the compressor by directly injecting liquid air into the intake air immediately before being taken into the compressor, (2) Mixing fine water particles at normal temperature into the intake air of the compressor Method of cooling (intercooling) the compressor from inside by sending it between compressor stages
(Journal of the Gas Turbine Society of Japan, vol.25, No.98, pp.99-105 (19
97)), (3) A method of intercooling a compressor by mixing fine ice particles into the intake air of the compressor and sending the mixed ice between compressor stages (Japanese Patent Laid-Open No. Hei 10-317988).

In the above methods (1) and (2), most of the liquid air or water particles charged into the compressor is vaporized near the compressor inlet, so that a large temperature gradient is generated in the intake air inside the compressor, and Cannot be cooled sufficiently. On the other hand, the method (3) is a method of cooling the intake air inside the compressor using the heat of liquefaction of ice particles and the heat of vaporization of water that follows. That is, as described in JP-A-10-317988, by adjusting the particle size and particle size distribution of the input ice particles, the position where the ice particles are liquefied and the position where the water after liquefaction evaporates are set in the compressor stage. Can be adjusted in a wide range between.
Therefore, in the method (3), the intake air traveling from the compressor to the turbine can be precisely and efficiently cooled so as to correspond to the temperature gradient of the intake air inside the compressor, and the input ice particles can be cleaned with GT clean. This is particularly effective because it can be used as a low-cost cleaning agent.

Here, in the method (3), it is important to minimize the power required to generate ice particles and the power required to feed the generated ice particles to the compressor as much as possible. . As the method, for example, JP-A-10-3
In 17988, liquid air was used to generate ice particles, but as a more efficient method, an ice particle generation and injection system utilizing low-temperature low-pressure high-pressure air is disclosed in JP-A-10-300296. ing. In this method, compressed air obtained by compressing the atmosphere is once cooled and then adiabatically expanded to provide a low-temperature, high-pressure air below zero (indicating air in a supercooled state before liquefaction, hereinafter referred to as “cold air”). ) Is obtained under desired temperature and pressure conditions, and the chilled air can be used not only to generate ice particles but also to be used as power for jetting the ice particles.

[0005]

However, even with the above-described system for producing and injecting ice particles, the power consumed for producing cryogenic air is still large, so that it is used as an intake air cooling system for a GT. Had problems in terms of installation space and efficiency.

The present invention has been made in view of the above problems, and has as its object to provide a gas turbine intake air cooling device that is compact and has high cooling efficiency.

[0007]

According to a first aspect of the present invention, there is provided a gas turbine intake air cooling system for cooling the intake air of an air compressor of a gas turbine. Refrigerated air generator that cools the cooled air and generates cryogenic air that is in a supercooled state before liquefaction, and an air compressor for a gas turbine using the cryogenic air generated by the cryogenic air generator. And a gas turbine intake cooling unit for cooling the intake air.

[0008] According to the gas turbine intake air cooling device of the first aspect, the cryogenic air generation unit can be configured as a small-scale heat engine by using the bleed air of the GT air compressor as pre-pressurized air. In addition, cryogenic air can be generated with less power than before. The GT intake cooling unit cools the GT intake using the cryogenic air generated by the cryogenic air generation unit, generates ice particles, and mixes the ice particles into the GT intake.
Therefore, it is possible to efficiently cool (intercool) the air in the air compressor of the GT, and it is possible to improve the output and efficiency of the GT.

Further, in the gas turbine intake air cooling device according to the first aspect, the cryogenic air generating section compresses the air extracted from the air compressor of the gas turbine and discharges the air from the bleed air compressor. It is preferable to have a turbine driven by compressed air to discharge cryogenic air.

In this case, the bleeding compressor can be constructed on a small scale because air extracted from the air compressor of the gas turbine is used as precompressed air, and the precompressed air can be compressed with low power. it can. Further, cryogenic air can be efficiently generated by adiabatically expanding the compressed air while recovering power by a turbine driven by the compressed air from the extraction compressor.

Further, in the gas turbine intake air cooling apparatus according to claim 1 or 2, the cryogenic air generated by the cryogenic air generating section is used to generate ice particles and compress the ice particles into the air of the gas turbine. It is preferable that the apparatus further comprises an ice particle generating means to be mixed into the intake air of the machine. Thereby, ice particles can be efficiently generated. This “ice particle generating means” may be arranged outside the above-described gas turbine intake air cooling unit, or may be arranged inside the gas turbine intake air cooling unit.

Further, in the gas turbine intake cooling device according to any one of claims 1 to 3, the ice particle generating means is configured to precool water by using cryogenic air generated by a cryogenic air generating unit. It is preferable to have a pre-cooling means and a pre-cooling water injecting means for injecting pre-cooled water from the water pre-cooling means and mixing it into the intake air of the air compressor of the gas turbine and generating ice particles. By providing the water pre-cooling means and the pre-cooled water injection means, it is possible to generate ice particles more efficiently and to inject it in a desired state during GT intake.

Further, in the gas turbine intake air cooling apparatus according to the fourth aspect, the water precooling means and the precooled water injection means in the ice particle generating means are arranged in series on an intake line of an air compressor of the gas turbine. Is also good.

According to a fourth aspect of the present invention, the water pre-cooling means and the pre-cooled water injection means in the ice particle generating means are arranged in parallel on an intake line of an air compressor of the gas turbine. Is also good.

Further, in the gas turbine intake air cooling device according to any one of claims 2 to 6, further provided is a bleed air cooling means for cooling the air bleed from the air compressor of the gas turbine and introducing it to the bleed air compressor. Is preferred. With this configuration, the temperature of the compressed air discharged from the extraction compressor can be reduced, so that it is possible to generate lower-temperature cryogenic air in the subsequent turbine.

Further, in the gas turbine intake cooling system according to any one of claims 2 to 7, the compressed air discharged from the extraction compressor is disposed on a gas line between the extraction compressor and the turbine. It is preferable to further include a turbine supply air cooling unit that cools and supplies the turbine supply air to the turbine. By doing so, the temperature of the compressed air discharged from the bleed air compressor can be reduced in the same manner as in the above-described bleed air cooling means, so that the temperature of the cryogenic air discharged from the subsequent turbine can be further reduced. You can do it.

Further, in the gas turbine intake cooling device according to any one of claims 2 to 8, the gas turbine intake cooling device is disposed on a gas line between the turbine and the gas turbine intake cooling unit,
The gas turbine may further include a turbine outlet cooling unit that further cools the cryogenic air discharged from the turbine and supplies the cooled air to the gas turbine intake air cooling unit. By doing so, the temperature of the chilled air discharged from the turbine can be further reduced, so that the intake air of the GT can be efficiently cooled and ice particles can be generated.

Further, in the gas turbine intake air cooling device according to the first aspect, the cryogenic air generation unit has a turbine driven by the air extracted from the air compressor of the gas turbine to discharge the cryogenic air. It may be. Since this turbine uses the bleed air of the air compressor of the gas turbine as a working fluid to generate cryogenic air, it is possible to obtain cryogenic air without using external power.

[0019]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Preferred embodiments of a gas turbine intake air cooling device according to the present invention will be described below in detail with reference to the drawings. In the following description, the same or corresponding parts will be denoted by the same reference characters, without redundant description.

[First Embodiment] FIG. 1 is a schematic diagram showing a first embodiment of a gas turbine intake air cooling apparatus according to the present invention. As shown in the figure, a gas turbine intake cooling device 100 is attached to a gas turbine (GT) power generation unit 70, and mainly includes a cryogenic air generation unit 10, a gas turbine intake cooling unit 20, a bleed cooling unit. 40, turbine supply air cooling means 50, and turbine outlet cooling means 60. In addition, this gas turbine (GT)
The power generation unit 70 is provided with an ST unit 80 including a steam turbine (ST) or the like at a subsequent stage.

First, the GT power generator 70 will be described.

The GT power generation section 70 includes an air supply section 71, an air compressor 72, a generator 73, a combustor 74, a gas turbine 75, and a fuel gas supply section 76.

The gas turbine 75 recovers power using the combustion gas G74 discharged from the combustor 74 as a working fluid. The air compressor 72 is coaxially connected to the gas turbine 75, for example, and is driven by the power of the gas turbine 75, supplied from the air supply unit 71, and converts the air A20 coming through the gas turbine intake cooling unit 20. The air is sucked and compressed, and the compressed air A72 is supplied to the combustor 74. Further, the air compressor 72 is provided with a bleed port, and a part A70 of the compressed air is bleed toward the gas turbine intake cooling device 100. Here, the bleed port is provided between the compressor stages according to conditions such as temperature and pressure required for the compressed air to be bleed and a balance between the scale of the gas turbine intake cooling device 100 and the scale of the GT power generation unit. Alternatively, it is provided appropriately at the discharge port.

The generator 73 is coaxially connected to the gas turbine 75 via the air compressor 72, and operates by the power of the gas turbine 75 to generate electric power. The combustor 74 mixes the natural gas F50 supplied from the fuel gas supply unit 76, which passes through the heat exchanger 50, and the compressed air A72 discharged from the air compressor 72, and burns the mixture. To the gas turbine 75.

The ST unit 80 (details not shown) includes, for example, a steam generator (HRSG), a steam turbine (ST), a generator, a condenser, a heat exchanger, a chimney, and the like. Consists of

Next, the gas turbine intake air cooling device 100 according to the present invention will be described.

In the present embodiment, the bleed air cooling means 40 of the gas turbine intake air cooling device 100 comprises only a heat exchanger. The heat exchanger 40 is provided with a low-temperature natural gas F60 via a turbine outlet cooling means 60 described later.
And heat exchange between the compressed air A70 extracted from the air compressor 72 of the GT power generation unit 70, whereby the temperature of the low-temperature natural gas F60 is raised and the compressed air A7
0 will be cooled.

The cryogenic air generator 10 includes a bleed air compressor 12
, A turbine 14 and an electric motor 16. These bleed compressor 12, turbine 14, and electric motor 1
6 is coaxially connected to each other, for example, such that the bleeding compressor 12 is disposed between the turbine 14 and the electric motor 16. The bleed compressor 12 is operated by the power of the electric motor 16 and the power of the turbine 14 connected coaxially.

As described above, the bleed compressor 12 sucks and compresses the compressed air A40 extracted from the GT generator 70 and passing through the heat exchanger 40. The turbine 14 operates with the compressed air A50 discharged from the extraction compressor 12 and cooled via a turbine supply air cooling unit 50 described later as a working fluid, recovers power, drives the extraction compressor 12 and Compressed air A50 Adiabatic expansion and cryogenic air A
14 is generated. In the cryogenic air generation unit 10, liquid air may be generated in addition to cryogenic air.
Also in this case, the liquid air is used in the gas turbine intake cooling unit.

The turbine supply air cooling means 50 is arranged on a gas line between the bleed air compressor 12 and the turbine 14, and in this embodiment is constituted only by a heat exchanger. The turbine supply air cooling means 50 exchanges heat between the compressed air A12 discharged from the bleed air compressor 12 and the low-temperature natural gas F40 heated through the heat exchanger 40 to further raise the temperature of the natural gas F40. At the same time, the compressed air A12 is cooled and supplied to the turbine 14.

The turbine outlet cooling means 60 includes a turbine 1
It is arranged on a gas line between the gas turbine 4 and the gas turbine intake cooling unit 20, and in the case of this embodiment, is constituted only by a heat exchanger. The heat exchanger 60 further cools the cryogenic air A14 discharged from the turbine 14 and supplies the cooled chilled air A14 to the gas turbine intake cooling unit 20.

The gas turbine intake cooling section 20 is disposed on a gas line between the air supply section 71 of the GT power generation section 70 and the air compressor 72, and is provided with cryogenic air flowing through the heat exchanger 60. A60 and air A71 supplied from the air supply unit 71 are mixed and introduced into the intake port of the air compressor 72 of the GT power generation unit. In the gas turbine intake cooling unit 20, the air A71 supplied from the air supply unit 71 is cooled by the cold heat of the cryogenic air A60 and introduced into the intake port of the air compressor 72 of the GT power generation unit.

The gas turbine intake cooling unit 20 condenses water (precipitated water) from the air in accordance with conditions such as the temperature and flow rate of the supplied chilled air A60, thereby removing water particles or ice particles. It can also be generated and mixed into the intake air of the air compressor 72. By preliminarily setting various conditions of the gas turbine intake cooling device 100 so that ice particles are generated from the moisture in the air supplied from the air supply unit 71, the air compressor 72 in the GT power generation unit 70 The compressed air in the inside can be cooled more efficiently.

The pressure, flow rate, temperature, etc. of the compressed air A 72 extracted from the air compressor 72 are determined based on the balance between the size of the cryogenic air generation unit 10 and the size of the GT power generation unit 70 and the relationship between their operation procedures. In some cases, air may be further added to the compressed air A72 extracted from the air compressor 72 and introduced into the extraction compressor 12. In this case, an air supply means 90 for the bleed compressor 12 may be appropriately provided on a gas line between the heat exchanger 40 and the bleed compressor 12. The air supply unit 90 includes an air supply unit 92 and an air mixing valve 94, mixes the compressed air A40 and the air A92 via the heat exchanger 40, and supplies the mixed air to the extraction compressor.

The operation of the gas turbine intake air cooling device 100 according to the present embodiment will be described below.

A part A70 of the compressed air extracted from the air compressor 72 of the GT power generator 70 is cooled by a heat exchanger (extraction cooling means) 40 by exchanging heat with the low-temperature natural gas F60. The compressed air A40 that has passed through the heat exchanger 40 is switched to the air supply means 90 for the bleed air compressor 12 as necessary, and is introduced into the bleed air compressor 12 of the cryogenic air generation unit 10. The compressed air A40 introduced into the bleed air compressor 12 is further compressed and discharged to the turbine supply air cooling means 50. The high-pressure compressed air A12 discharged from the extraction compressor 12 is cooled by exchanging heat with the low-temperature natural gas F40 passing through the extraction cooling means 40 in the turbine supply air cooling means 50. The high-pressure compressed air A50 cooled by passing through the turbine supply air cooling means 50 is introduced into the turbine 14 as a working fluid. In the turbine 14, the compressed air A50 is adiabatically expanded, converted into cryogenic air A14, and discharged.

The cryogenic air A1 discharged from the turbine 14
4 is introduced into a heat exchanger (turbine outlet cooling means) 60, where the liquefied natural gas F 76 supplied from the fuel gas supply unit 76 of the GT power generation unit 70 in the turbine outlet cooling means 60
It exchanges heat with and is further cooled. The cryogenic air A60 that has passed through the heat exchanger 60 is introduced into the gas turbine intake cooling unit 20, and cools the air A71 supplied from the air supply unit 71. In the gas turbine intake cooling unit 20, the air A7
1 is cooled by the cryogenic air A60, and ice particles are generated from the water vapor component according to the set condition of the cooling. Chilled air A20 containing ice particles passed through the gas turbine intake cooling unit 20
Is introduced as intake air of the air compressor 72 to cool the compressed air in the air compressor 72 more efficiently. A part A of the compressed air that has been compressed and heated in the air compressor 72
70 is bled toward the gas turbine intake cooling device 100.

The fuel gas supply unit 7 of the GT power generation unit 70
The liquefied natural gas F76 supplied from 6 gradually passes through the heat exchanger (turbine outlet cooling means) 60, the heat exchanger (bleed air cooling means) 40, and the heat exchanger (turbine supply air cooling means) 50 in this order. GT is heated and vaporized.
It is introduced into the combustor 74 of the power generation unit 70.

The compressed air A discharged from the air compressor 72
72 and natural gas F50 passing through the heat exchanger 50
The fuel burns in the combustor 74. The high-temperature and high-pressure combustion gas G74 discharged from the combustor 74 is introduced into the gas turbine 75 to operate the gas turbine 75. The exhaust gas G75 discharged from the gas turbine 75 is supplied to a steam generator (H
(RSG) or ST unit 80 provided with a chimney, etc., and heat is recovered and exhausted to the chimney.

As described above, the gas turbine intake air cooling device 100 uses the cryogenic air (which may include liquid air) containing water particles and ice particles to operate the stage (compressed air inside) of the air compressor 72. Can be effectively cooled, so that the compressor power can be reduced and the GT power generation output can be easily improved. Further, the pre-compressed air A 70 extracted from the air compressor 72 of the gas turbine
, The size of the bleeding compressor 12 can be made relatively small, so that the electric motor 1 that operates the bleeding compressor 12
6 can easily be minimized.

Further, the bleed air cooling means 40, the turbine supply air cooling means 50, and the turbine outlet cooling means 60 can effectively utilize the cold energy of the liquefied natural gas to assist the generation of cryogenic air. In this respect, the power required for cryogenic air generation can be reduced. Further, in this case, the fuel gas used in the combustor 74 of the GT power generation unit 70 is effectively preheated before being introduced into the combustor 70, which contributes to fuel saving.
As a result, the efficiency of the GT power generation unit 70 can be improved.

In the above description, liquefied natural gas is used as a refrigerant in order to effectively generate cryogenic air from the bleed air of the air compressor 72 of the GT power generation unit 70. However, an alternative to liquefied natural gas is used. Other fluids, for example, boiler feedwater or the like may be used. In addition, as a method of using the air supply means 90 for the bleed compressor 12, it is used when the bleed air is not introduced into the bleed compressor 12 at the initial stage of starting the GT power generator 70 and the gas turbine cooling device 100. A method of completely switching to bleeding when the gas turbine cooling device 100 reaches a predetermined condition may be adopted.

[Second Embodiment] FIG. 2 is a schematic configuration diagram showing a second embodiment of the gas turbine intake air cooling device according to the present invention. Gas turbine intake cooling device 100A shown in FIG.
1 is different from the gas turbine intake air cooling device 100 shown in FIG.

The ice particle generation means 30 is disposed on a gas line between the gas turbine intake cooling unit 20 and the air compressor 72 of the GT power generation unit 70. The ice particle generating means 30 sprays water W30 supplied from the outside into the cryogenic air A20 traveling in the gas line from the gas turbine intake cooling unit 20 to the air compressor 72, and uses cold heat. To produce ice particles. Further, the ice particle generation means 30 sets a desired water particle size and particle size distribution by setting water spray conditions in accordance with conditions such as the temperature and flow rate of the cryogenic air A20 introduced from the gas turbine intake cooling unit 20. Can be generated.

In the gas turbine intake cooling unit 100 shown in FIG. 1, the ice particle generating means 30 is arranged independently of the gas turbine intake cooling unit 20. It may be arranged.
A more detailed basic configuration of the ice particle generating means 30 and a mode of arrangement in the gas turbine intake air cooling device will be described in third to fifth embodiments of the present invention described later.

As described above, the gas turbine intake air cooling device 10
0A is provided with an ice particle generation means 30 and can actively introduce water from the outside to generate ice particles under desired generation conditions. Therefore, the gas turbine intake cooling device 100 shown in FIG. In comparison, the compressed air can be more efficiently cooled in a wide range extending to the subsequent stage in the compressor stage of the air compressor 72 of the GT power generation unit 70. Therefore, the power required for the air compressor 72 can be reduced, and as a result, the output of the GT power generation unit 70 can be improved. Ice can also reduce compressor power efficiently,
The same effect can be obtained even if the temperature of the cryogenic air generated in the cryogenic air generation unit 10 is higher than the temperature of the cryogenic air in the gas turbine intake cooling device 100 shown in FIG. The power of the electric motor 16 in the generator 10 can be reduced. Therefore, the efficiency of the GT power generation unit 70 can be improved.

[Third Embodiment] FIG. 3 is a schematic configuration diagram showing a third embodiment of the gas turbine intake air cooling device according to the present invention. Gas turbine intake cooling device 100B shown in FIG.
Is different from the gas turbine intake air cooling apparatus 100 shown in FIG. 1 in that the apparatus further includes an ice particle generation unit 30 and that the turbine supply air cooling unit 50 is configured by a plurality of elements having a heat exchange function. different.

The ice particle generating means 30 is disposed on a gas line between the gas turbine intake cooling section 20 and the air compressor 72 of the GT power generating section 70, and includes water precooling means 32, precooled water injection means 34, It is composed of The water precooling means 32 and the precooled water injection means 34 are
They are arranged in series from the side.

The water pre-cooling means 32 comprises only a heat exchanger in this embodiment. The water precooling means 32 is provided with the cryogenic air A introduced from the gas turbine intake cooling unit 20.
The water supplied from the outside is pre-cooled by utilizing a part of the cold heat of 20 and is supplied to the pre-cooled water injection means 34 at the subsequent stage. Also, the cryogenic air A2 introduced from the gas turbine intake cooling unit 20
0 is supplied to the pre-cooled water injection unit 34 after a part of the water is pre-exchanged in the water pre-cooling unit 32.

The pre-cooled water injection means 34 has a configuration in which, for example, a spray nozzle N34 for spraying water pre-cooled by the ice particle generating means 30 is disposed in a cylindrical duct. The pre-cooled water sprayed from the spray nozzle N34 easily becomes ice particles due to the cold heat of the cryogenic air A20 flowing around. Further, the pre-cooled water injection means 34 is supplied with the pre-cooled water spray conditions such as the size of the nozzle orifice of the nozzle, the jet water pressure, the jet angle, the nozzle shape, and the nozzle arrangement condition from the gas turbine intake cooling unit 20. By setting according to the conditions such as the temperature and flow rate of the cryogenic air A20, the desired particle size,
The specifications are to generate ice particles having a particle size distribution.

The turbine supply air cooling means 50 comprises a steam generator (HRSG) 52 and heat exchangers 54, 56, 58.

The steam generator 52 generates steam using the heat of the compressed air A12 discharged from the bleed compressor 12, and converts the steam S52 into an external steam turbine (not shown).
To supply. The steam turbine is a GT power generator 7.
0 may be a steam turbine (not shown) in the ST unit 80 at the subsequent stage, or may be a steam turbine arranged separately from the ST unit 80.

The heat exchanger 54 is disposed on the gas line at the subsequent stage of the steam generator 52, and the water W 50 supplied thereto is supplied to the compressed air A 5 passing through the steam generator 52.
Using the heat of No. 2, the hot water W54 is supplied to the steam generator 52 or a steam generator (not shown) in the ST unit 80 to preheat water.

The heat exchanger 56 is disposed on the gas line at the subsequent stage of the heat exchanger 54, and converts the natural gas F 40 passing through the extraction cooling means 40 into compressed air passing through the heat exchanger 54. Preheating is performed using the heat of A54 and the preheated air is supplied to the combustor 74.

The heat exchanger 58 is disposed on the gas line at the subsequent stage of the heat exchanger 56, and performs heat exchange by utilizing the cold heat of a part F76b of the liquefied natural gas F76 supplied from the fuel gas supply unit 76. This is for cooling the compressed air A56 passing through the vessel 56. The compressed air A58 cooled in the heat exchanger 58 is supplied to the turbine 14.
On the other hand, the natural gas F58 heated and vaporized in the heat exchanger 58 is combined with the natural gas F60 passing through the turbine outlet cooling means 60 and supplied to the extraction cooling means 40. In this embodiment, the liquefied natural gas F76 supplied from the fuel gas supply unit 76 is branched into two, F76a and F76b. The F76a is supplied to the turbine outlet cooling means 60, and the F76b is supplied to the heat exchanger 58. However, a supply unit for supplying liquefied natural gas to the heat exchanger 58 may be provided separately from the fuel gas supply unit 76.

The exhaust heat of the compressed air A12 discharged from the bleed air compressor 12 by the function of each component in the turbine supply air cooling means 50 is sufficiently consumed by being used as preheating of fuel gas or external power. The Rukoto. As a result, the compressed air A5 supplied to the turbine 14
8, the temperature of the cryogenic air A60 supplied to the gas turbine intake air cooling unit 20 is sufficiently reduced, so that cold intake air and ice particles can be easily generated.

As described above, the gas turbine intake air cooling device 10
The gas turbine inlet cooling device 0B shown in FIG. 1 is capable of generating ice particles under desired conditions by actively introducing water from the outside by providing the ice particle generating means 30. As compared with 100, the wide stage can be more efficiently cooled in a wide range within the compressor stage of the air compressor 72 of the GT power generation unit 70. Therefore, the power of the air compressor 72 can be reduced, and as a result, the output of the GT power generation unit 70 can be improved. Also,
Since the size and number of ice particles can be controlled by the ice particle generation means 30, the number of cooling stages of the compressor can be freely designed.

FIG. 4 is a schematic configuration diagram showing one embodiment in a case where the ice particle generating means 30 is disposed in the gas turbine intake cooling unit 20. In this case, as described below, the ice particle generation unit 30 is disposed in the gas turbine intake cooling unit 20A.

The gas turbine intake cooling unit 20A supplies air A supplied from the air supply unit 71 to the air compressor 72.
It is configured as a duct (gas line) D1 through which 71 passes and a duct D2 arranged inside the duct (gas line) D1. The refrigerated intake air A60 passing through the turbine outlet cooling means 60 is introduced into the gas turbine intake air cooling unit 20A, and the A60 flowing out of the duct D2 and the air A71 supplied from the air supply unit 71 are merged. Thus, the air A71 can be cooled. In order for the chilled intake air A60 and the air A71 to smoothly merge, the duct D2 is connected to the duct D1.
And the flow of the refrigerated intake air A60 flowing inside the duct D2 is changed to the air A7 flowing outside the duct D2.
1 and in the same direction. The duct D2 is provided with a gas line that penetrates the duct D1 and is directly connected to the turbine outlet cooling means 60.
Further, the duct D2 has a double-pipe structure so that chilled air A60 can flow through the inner pipe D2a and air A2 can flow through the outer pipe D2b. Thus, the outer tube D2
By flowing air into b, the moisture of the air A71 supplied from the air supply unit 71 contacts the outer wall of the duct D2 and freezes, thereby preventing a problem that the flow of the air A71 in the duct D1 is obstructed. can do.

The ice particle generating means 30A is configured as a duct disposed inside the gas turbine intake cooling unit 20A. The ice particle generation means 30A has a double tube structure. The inner pipe D3a is a water supply line for introducing water from the outside, and penetrates through the side surfaces of the duct D2 and the duct D1, and is directly connected to an external water supply unit (not shown). In addition, inner pipe D3
The downstream end of “a” is branched into a plurality of parts, and a plurality of spray nozzles N34 for injecting water into the duct D2 to generate ice particles are provided at the respective ends. The outer pipe D3b is a gas line for flowing the air A3, and penetrates through the side surfaces of the duct D2 and the duct D1, and is directly connected to an external air supply unit (not shown). Air A3 to outer tube D3
By flowing to b, it is possible to prevent water flowing in the inner pipe D3a from being frozen before the injection by the chilled air A60 flowing in the duct D2 and to pre-cool the water before the injection.

The water pre-cooled in the inner pipe D3a in this way is sprayed from the spray nozzle N34 into the duct D2 to form ice particles. At this time, a part A60a of the cryogenic air A60 flowing in the duct D2 flowing through the spray area of the spray nozzle N34 is used for ice particle generation, and the remaining part A60b is used.
Is mainly used for cooling the air A71.

As shown in the figure, the air A3 may be circulated in the outer pipe D3b or a part of the air A3 may be discharged into the duct D2 according to the degree of precooling. In addition, air A2 and A3
May be supplied from the high-pressure system of the gas turbine intake cooling device 100B, or may be supplied from a separately provided supply unit. Further, the shape of the bottom surface of the duct D2 facing the air supply unit 71 is a shape for reducing the pressure loss of the air A71 in the duct D2 and smoothing the flow of the air A71.
[For example, a cone or the like (see a two-dot chain line in the figure)].

As the spray nozzle N34 of the ice particle generating means 30A, the one shown in FIG. 5 may be used.

The spray nozzle N34A shown in the figure is arranged concentrically in multiple circles, and has a plurality of injection ports projecting stepwise from the outer layer toward the center.
With such a configuration having a step in the axial direction of the spray nozzle N34A, the water particles I ejected from each injection port are perpendicular to the axial direction of the spray nozzle N34A and the axial direction of the spray nozzle N34A as shown in the figure. Are distributed in different areas in different directions (I1,
I2, I3). On the other hand, the flux of the chilled air A60 traveling in the axial direction of the duct D2a is not used only once in a certain cross section in the duct D2a, but is used in the duct D2a.
As it progresses in the axial direction, it may be used in contact with water particles multiple times. That is, the chilled air A60 can be effectively used in a narrow space, and as a result,
The number of nozzles in the ice particle generation means 30A can be reduced, and ice particles can be generated efficiently.

Further, as the shape of the duct D1 and the duct D2 and the style of the duct D2 disposed in the duct D1, for example, those shown in FIGS.

FIG. 6A is a cross-sectional view of the duct D1. A plurality of ducts D2 are concentrically arranged in a duct D1 having a circular cross section. Inside the duct D2, there is provided a duct D3 having a spray nozzle N34 (the ice particle generating means 30).
A) are arranged at regular intervals. Further, the outer wall of the outermost duct D2 has a structure in which a predetermined interval is provided without contacting the inner wall of the duct D1. With this configuration, the pipe formed by the inner wall of the duct D1 and the outer wall of the duct D2 disposed at the outermost position includes:
The air A71 supplied from the air supply unit 71 flows, so that the duct D1 can be easily insulated from the outside.

FIG. 6B is a longitudinal sectional view of the duct D1. As described above, the portion where the duct D2 is arranged in the duct D1 shown in FIG.
It is also possible to arrange a plurality of stages at predetermined intervals in the flow direction.

The sectional shapes of the ducts D1 and D2 and the arrangement of the ducts D2 arranged in the duct D1 are not limited to those shown in FIG. 6 (a).
And a straight duct D1 and a duct D2 may be alternately arranged as shown in FIG. 7 (b).

The type of the spray nozzle N34 arranged in the duct D3 in the gas turbine intake cooling system 100B shown in FIG.
11 may be used.

FIG. 8A shows that all of the plurality of spray nozzles N34 in the duct D1 change their jetting directions to the duct D1.
3 shows a mode in which water droplets are sprayed in parallel to the axial direction and downstream. Water particles of the pre-cooled water are jetted in parallel with the traveling direction of the air A71 supplied from the air supply unit 71.

The spray direction of each spray nozzle N34 is not particularly limited, and may be independently set in accordance with desired ice particle generation conditions. For example,
As shown in FIG. 8 (b), the generation region of the ice particles is set in the duct D1.
When it is desired to concentrate on the central part of the inside, the spray angle α of each spray nozzle N34 can be adjusted. By doing so, it is possible to concentrate or disperse the ice particle generation region in a desired region of the duct.

As a condition for the generated ice particles to be smoothly introduced into the air compressor 72, it may be necessary to consider the gravity applied to the ice particles. FIG.
9A and 9B, the case where the duct D1 is installed horizontally with respect to the ground surface and gravity is applied vertically downward with respect to the traveling direction of the ejected ice particles has been described. As shown in a) and (b), the duct D1 may be installed in a direction perpendicular to the ground surface. FIG. 9A shows FIG.
A mode is shown in which the mode shown in (a) is rotated by 90 °, and the spray direction of the plurality of spray nozzles N34 is made to match the direction of gravity so as to spray water droplets. With this arrangement, the pre-cooled water is smoothly injected from the nozzle portion. FIG. 9 (b) shows a water droplet obtained by rotating the style shown in FIG. 8 (a) by 90 ° in a direction opposite to that of FIG. 9 (a) so that the spray directions of the plurality of spray nozzles N34 are opposed to gravity. FIG. By doing so, it is possible to prevent water leakage from the nozzle portion.

The duct D1 is not limited to a straight pipe as shown in FIGS. 8 and 9. For example, as shown in FIG. Alternatively, as shown in FIG. 10B, the middle of the pipe may be bent gently. In the case shown in FIG. 10A, a straightening plate GV for maintaining a smooth flow of the cryogenic air may be provided before the bent portion as needed.

Further, in FIGS. 8 to 10, a description has been given of a mode (cocurrent type) in which the spray direction of water droplets from the spray nozzle N34 is along the traveling direction of the air A71, but the spraying of water droplets from the spray nozzle N34 is described. The direction is not limited to the co-current type. For example, as shown in FIG. 11 (a), a mode in which water particles are jetted so as to face the traveling direction of the air A71 (counter-current type) may be used. As shown in FIG. 11B, a mode (cross-flow type) of injecting water particles from a direction perpendicular to the traveling direction of the air A71 or a direction of the inclination α may be adopted. In the case of the countercurrent type, the spread of the surface formed by the sprayed water droplets is larger than in the case of the cocurrent type, so that the contact surface with the air A71 increases,
Since the relative speed of the water particles with respect to the air A71 is larger than that in the case of the co-current type, the heat transfer boundary layer becomes thinner, so that the efficiency of water generation can be improved.

FIG. 12 is a schematic configuration diagram showing a second mode in which the ice particle generation means 30 in the gas turbine intake air cooling device 100B shown in FIG.

The second embodiment shown in FIG. 11 is the same as the first embodiment shown in FIG.
Compared with the embodiment, the difference is that a plurality of ducts D2 having one duct D3 are provided independently. When a plurality of ducts D3 (ice particle generating means 30B) are provided in the duct D2 as in the first embodiment shown in FIG. 4, the ice particles in each spray nozzle N34 may vary depending on the arrangement position in the duct D2. Although the generation conditions may be slightly different,
By providing the integral duct D2 corresponding to the integral duct D3, it is possible to easily control the ice particle generation conditions of each duct D3 so as to match each other, so that ice having a desired particle size and particle size distribution can be obtained. Grains can be obtained.

Note that, in the case of the second embodiment as well, the gas turbine intake cooling unit 20 and the ice particle generating means
The devices shown in FIGS. 5 to 11 can be applied.

FIG. 13 is a schematic configuration diagram showing a third mode in which the ice particle generating means 30 in the gas turbine intake air cooling device 100B shown in FIG. The third embodiment shown in the same drawing is different from the first embodiment shown in FIG. 4 in that a plurality of ducts D2 integrally having a duct D3 are provided independently, And a duct D4 for cooling the air A71 in advance.

In the third embodiment shown in FIG. 13, similar to the second embodiment shown in FIG. 12, by providing an integral duct D2 corresponding to the integral duct D3, the ice particle generation conditions for each duct D3 are provided. Can easily be controlled so as to match, and ice particles having a desired particle size and particle size distribution can be obtained.

Further, by independently providing a duct D4 for pre-cooling the air A71 upstream of the duct D2 in the duct D1, near the outlet of the duct D2, a low-temperature pre-cooled duct D4 is provided. Since the air A71 is supplied, the duct D near the outlet of the duct D2
(2) The temperature gradient between the inside and the outside can be reduced, and the melting of the sprayed ice particles can be suppressed to a minimum.

Incidentally, also in the case of the third aspect, the gas turbine intake cooling unit 20 and the ice particle generating means
The devices shown in FIGS. 5 to 11 can be applied.

[Fourth Embodiment] FIG. 14 is a schematic configuration diagram showing a fourth embodiment of the gas turbine intake air cooling system according to the present invention. Gas turbine intake cooling device 100 shown in FIG.
C differs from the gas turbine intake air cooling device 100 shown in FIG. 1 in further including an ice particle generation unit 30 and in that the bleed cooling unit 40 is composed of a plurality of elements having a heat exchange function. .

The ice particle generation means 30 is disposed on a gas line between the gas turbine intake cooling section 20 and the air compressor 72 of the GT power generation section 70, and is provided with water precooling means 32 and precooled water injection means 34. It is configured. The water pre-cooling means 32 and the pre-cooled water injection means 34 are arranged in parallel on the gas line, and the cryogenic air A20 supplied from the gas turbine intake cooling unit 20 receives water at the inlet of the ice particle generating means 30 at the inlet. A32 is introduced into the precooling means 32 side and A34 is introduced into the precooling water injection means 34.

The water pre-cooling means 32 comprises only the heat exchanger 32 in this embodiment. Heat exchanger 32
Utilizes the cold heat of the cryogenic air A32 introduced from the gas turbine intake cooling unit 20 to pre-cool water supplied from the outside and supplies it to the adjacent pre-cooled water injection means 34.

The pre-cooled water injection means 34 has a configuration in which a spray nozzle N34 for spraying water pre-cooled by the ice particle generation means 30 is disposed in a cylindrical duct.
The pre-cooled water sprayed from the spray nozzle N34 is cryogenic air A34 flowing around (this is A20 itself and FIG.
(I.e., lower than the air heat exchanged by the heat exchanger 32 as described above). Further, the pre-cooled water injection means 34
The water spray conditions such as the size of the nozzle orifice of the nozzle, the jet water pressure, the jet angle, the nozzle shape, the nozzle arrangement condition, and the like, the temperature of the deep cold air A34 introduced from the gas turbine intake cooling unit 20, By setting according to conditions such as the flow rate, ice particles having a desired particle size and particle size distribution can be generated. This is the same as the case shown in FIGS.

On the other hand, the bleed air cooling means 40
2, 44, a turbine 46, and a generator 48.

The heat exchanger 42 is connected to the air compressor 72 on a gas line between the air compressor 72 and the bleed air compressor 12.
And cools the compressed air A72 extracted from the air compressor 72 by using the cold heat of the natural gas F60 passing through the turbine outlet cooling means 60.

The heat exchanger 44 is arranged on the gas line at the subsequent stage of the heat exchanger 42, and is for further cooling the compressed air A42 passing through the heat exchanger 42.
The compressed air A44 cooled in the heat exchanger 44 is supplied to a turbine 46. The refrigerant S44 used for cooling the compressed air A42 in the heat exchanger 44
Is not particularly limited. For example, a part of the natural gas F60 which goes to the heat exchanger 42 via the turbine outlet cooling means 60 may be branched and used. The steam generator may be provided with a steam turbine power generation system.

The turbine 46 is arranged on the gas line at the subsequent stage of the heat exchanger 44, and operates by using the compressed air A44 passing through the heat exchanger 44 as a working fluid to recover power. The generator 48 is coaxially connected to the turbine 46 and operates by the power of the turbine 46 to generate power.

The heat of the compressed air A 70 extracted from the air compressor 72 by the function of each component in the extraction cooling means 40 is used as preheating of the fuel gas and as an external output, so that it can be sufficiently utilized. Becomes Also,
Since the temperature of the compressed air A46 supplied to the extraction compressor 12 has been sufficiently lowered, the power of the electric motor 16 for operating the extraction compressor 12 can be reduced. That is, the power required to generate the cryogenic air can be reduced. Furthermore, since the heat of the compressed air A70 extracted from the air compressor 72 is used as an external output in the turbine 46, the plant efficiency is also improved.

As described above, the gas turbine intake air cooling device 10
Since 0C is provided with the ice particle generation means 30, it is possible to actively introduce water from the outside and generate ice particles under desired generation conditions, so that the air compressor 72 of the GT power generation unit 70 The compressed air can be cooled more efficiently in a wide range between the compressor stages. Further, since the pre-cooled water injection means 34 of this embodiment is arranged on the gas line in parallel with the water pre-cooling means 32, the cold heat of the chilled air A20 supplied from the gas turbine intake cooling unit 20 is converted to water. Since it can be directly used without any loss in the precooling means 32, the control of the generation of ice particles is facilitated.

Further, when the outlet pressure of the expansion turbine 46 is set to the atmospheric pressure in the generator 48, a usage method of reducing the intake air of the bleed compressor 12 by mixing with the intake air from the air supply unit 92 is possible.

[Fifth Embodiment] FIG. 15 is a schematic diagram showing a fifth embodiment of the gas turbine intake air cooling system according to the present invention. Gas turbine intake cooling device 100 shown in FIG.
D is different from the gas turbine intake air cooling device 100 shown in FIG. 1 in that it further includes an ice particle generation unit 30, the cryogenic air generation unit 10 has different components, and the turbine supply air cooling unit. It differs in that 50 is omitted and that the turbine outlet cooling means 60 is composed of a plurality of components.

[0094] The cryogenic air generator 10 includes a heat exchanger 13 and
It comprises a turbine 15 and a generator 17.

The heat exchanger 13 is disposed on the gas line at the subsequent stage of the bleed air cooling means 40.
Is used to cool the compressed air A40 passing through the bleed cooling means 40 by using the heat of vaporization of a part F76b of the liquefied natural gas F76 supplied from the air. The compressed air A12 sufficiently cooled in the heat exchanger 13 is supplied to the turbine 1
5 is supplied. On the other hand, the natural gas F13 that has been heated and vaporized in the heat exchanger 13 is appropriately selected for the supply destination in accordance with the temperature, and is directly combusted with the natural gas F40 passing through the heat exchanger 40, for example. Is introduced into the vessel 74. In this embodiment, the fuel gas supply unit 7
The liquefied natural gas F76 supplied from 6 is branched into two, F76a and F76b, and F76a is supplied to the turbine outlet cooling means 60, and F76b is supplied to the heat exchanger 13. A supply section for supplying liquefied natural gas to the vessel 44 may be provided separately from the fuel gas supply section 76.

The turbine 15 is disposed on the gas line at the subsequent stage of the heat exchanger 13, and operates by using the low-temperature compressed air A 13 passing through the heat exchanger 44 as a working fluid to recover power and at the same time to recover power. The cold air A15 is generated. The generator 17 is coaxially connected to the turbine 15,
It operates by the power of the turbine 15 to generate power.

The turbine outlet cooling means 60 is connected to the heat exchanger 6
2, a gas-liquid separator 64, a liquid air tank 66, and a liquid air supply pump 68.

The heat exchanger 62 is disposed on the gas line at the subsequent stage of the turbine 15, and is supplied from the turbine 15 by utilizing the heat of vaporization of a part F 76 a of the liquefied natural gas F 76 supplied from the fuel gas supply unit 76. This is for further cooling the deep cold air A15. The refrigerated air A62 sufficiently cooled in the heat exchanger 62 becomes a part including liquid air. On the other hand, the natural gas F60 that has been heated and vaporized in the heat exchanger 62 is introduced into the bleed cooling unit 40.

The gas-liquid separator 64 is disposed on the gas line downstream of the heat exchanger 62, and converts the cryogenic air A62 containing liquid air supplied from the heat exchanger 62 into the cryogenic air component A.
64 and a liquid air component L64. Gas-liquid separator 6
A gas line and a liquid sending line are provided on the downstream side of 4, and the cryogenic air component A64 is introduced into the gas turbine intake cooling unit 20 through the gas line. On the other hand, the liquid air component L64 is introduced into the liquid air tank 66 through the liquid sending line.

The liquid air tank 66 is for temporarily storing the liquid air L64 supplied from the gas-liquid separator 64.

The liquid air supply pump 68 is disposed on the liquid supply line at the subsequent stage of the liquid air tank 66, and the liquid air supply pump 68 stored in the liquid air tank 66 as necessary.
64, the gas turbine intake cooling unit 20 and the ice particle generating means 30
Respectively. Liquid air L64
Is introduced into the gas turbine intake cooling unit 20 and the ice particle generating means 30 according to desired ice particle generation conditions. In other words, the liquid air supplied from the liquid air supply pump 68 to the gas turbine intake cooling unit 20 or the ice particle generating means 30 can generate a lot of low-temperature air and ice particles. The cooling state of the compressed air can be further easily controlled.

The ice particle generating means 30 is disposed on a gas line between the gas turbine intake cooling unit 20 and the air compressor 72 of the GT power generating unit 70. In the case of this embodiment, since liquid air is directly introduced into the ice particle generating means 30 in addition to the chilled air A60 passing through the gas-liquid separator 64, no special water precooling means is provided. In both cases, the water sprayed from the spray nozzle N34 can instantaneously become ice particles. Further, as described above, also in this embodiment, the spray nozzle N34 has water spray conditions such as the size of the nozzle orifice, the jet water pressure, the jet angle, the nozzle shape, and the nozzle arrangement condition. Is set in accordance with the conditions such as the temperature and flow rate of the cryogenic air A34 introduced from the gas turbine intake cooling unit 20, thereby making it possible to generate ice particles having a desired particle size and particle size distribution.

The compressed air A46 supplied to the turbine 15
Since the temperature is sufficiently lowered, cryogenic air can be easily generated. As in the present embodiment, the air compressor 72
Of the extracted air (compressed air) A72 is sufficiently cooled and adiabatically expanded by a single turbine 15 (single-stage adiabatic expansion)
The configuration of the device that generates the cryogenic air A15 is particularly effective when only a small amount of the cryogenic air and the liquid air required for the gas turbine intake cooling unit 20 and the ice particle generation unit 30 are required.

As described above, the gas turbine intake air cooling devices 100 and 100A to 100D of the present invention can lower the temperature of the intake air of the compressor by several tens of degrees below the atmospheric temperature. In the case of performing the intercooling, the effect of the interstage cooling can be exerted over a wider range extending to the subsequent stage as compared with the case of performing only the water injection. Since the temperature of the intake port of the compressor is kept below zero by the action of the interstage cooling, the gas turbine intake cooling system of the present invention is useful and has a high operation rate even in winter. On the other hand, the gas turbine intake cooling system of the type that mixes water particles into the intake air of the compressor can be effectively used only in the summer season because the temperature of the intake inlet of the compressor can be cooled only to about 15 to 30 ° C. Operating rate is low.

The use of ice grains means that the latent heat of melting of ice grains of 80 kcal / kg can be fed into the compressor between the water latent heat of water drops of 600 kcal / kg, and that only the water grains can be thrown in. On the other hand, the input of ice particles is about 1.2 ｛= (600 + 80
+30) / 600 °.
That is, the gas turbine intake cooling system of the present invention reduces the pure water consumption by about 1 / 1.2 when the same effect as that of the gas turbine intake cooling system of the type in which water particles are mixed into the intake air of the compressor.
That is, it can be reduced twice.

Furthermore, from the above two effects, the interstage cooling effect of the gas turbine intake cooling system of the present invention extends to the latter stage as compared with the system in which water particles are mixed into the intake air of the compressor. Compressor power can be greatly reduced. Further, the cleaning effect between the compressor stages due to the collision of the ice particles is superior to that of the water particles, and the dirt between the compressor stages can be more efficiently removed.

Although the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the above embodiments. For example, the combination of the gas turbine intake air cooling devices 100A to 100D shown in the second embodiment to the fifth embodiment and the ice particle generation unit 30 and the gas turbine power generation unit 70, which are the components of these devices, will be described for convenience of explanation. Although illustrated as representative examples, these may be freely combined.

[0108]

As described above, according to the gas turbine intake air cooling system of the present invention, the air extracted from the air compressor is efficiently cooled by charging the ice particles into the air compressor, and the air is cooled. The basic ability to produce cool air and return it to the intake of a gas turbine air compressor to cool it can be improved. Accordingly, by performing the cooling process on the compressor bleed air by the heat exchanger and the expansion turbine, the power required for cryogenic air generation can be reduced, and a compact and high cooling efficiency gas turbine intake air cooling device can be provided.

[Brief description of the drawings]

FIG. 1 shows a first embodiment of a gas turbine intake air cooling system according to the present invention.
It is a schematic structure figure showing an embodiment.

FIG. 2 shows a second embodiment of the gas turbine intake air cooling system according to the present invention.
It is a schematic structure figure showing an embodiment.

FIG. 3 shows a third embodiment of the gas turbine intake air cooling system according to the present invention;
It is a schematic structure figure showing an embodiment.

FIG. 4 is a schematic configuration diagram showing a first mode when an ice particle generation unit according to a third embodiment is disposed in a gas turbine intake cooling unit.

FIG. 5 is a schematic diagram illustrating an example of a configuration of a spray nozzle used for an ice particle generation unit according to a third embodiment.

FIGS. 6A and 6B are cross-sectional views illustrating an example of a configuration of a duct D1 and a duct D2 according to a third embodiment.

FIGS. 7A and 7B are cross-sectional views showing another example of the configuration of the ducts D1 and D2 shown in FIG.

FIGS. 8A and 8B are schematic diagrams illustrating an example of an arrangement mode and a spray mode of a spray nozzle arranged in a duct D1 according to the third embodiment.

9 (a) and 9 (b) are schematic views showing another example of the arrangement of spray nozzles and the spraying mode arranged in the duct D1 shown in FIG.

FIGS. 10A and 10B are schematic diagrams showing a case where the duct D1 shown in FIGS. 8 and 9 is bent.

11 (a) and 11 (b) are schematic diagrams showing another example of the arrangement and the ejection of the spray nozzles arranged in the duct D1 shown in FIGS. 8 and 9. FIG.

FIG. 12 is a schematic configuration diagram illustrating a second mode when the ice particle generation unit according to the third embodiment is disposed in a gas turbine intake cooling unit.

FIG. 13 is a schematic configuration diagram showing a third mode when the ice particle generation means according to the third embodiment is arranged in a gas turbine intake cooling unit.

FIG. 14 is a schematic configuration diagram showing a fourth embodiment of the gas turbine intake air cooling device according to the present invention.

FIG. 15 is a schematic configuration diagram showing a fifth embodiment of the gas turbine intake air cooling device according to the present invention.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 10 ... Cryogenic air generation part, 12 ... Bleed air compressor, 13 ... Heat exchanger, 14,15 ... Turbine, 16 ... Electric motor, 17 ... Generator, 20, 20A, 20B, 20C ... Gas turbine intake cooling part, 30 , 30A, 30B, 30C: ice particle generating means, 32: water precooling means, 34: precooled water injection means 34, 4
0 ... extraction air cooling means, 42, 44 ... heat exchanger, 46 ... turbine, 48 ... generator, 50 ... turbine supply air cooling means,
52: steam generator, 54, 56, 58: heat exchanger, 6
0: turbine outlet cooling means, 62: heat exchanger, 64: gas-liquid separator, 66: liquid air tank, 68: liquid air supply pump, 70: gas turbine (GT) power generation unit, 71: air supply unit, 72 ... air compressor, 73 ... generator, 74 ... combustor, 75 ... gas turbine, 76 ... fuel gas supply unit, 8
0: Steam turbine (ST) unit, 90: Air supply means, 92: Air supply unit, 94: Air mixing valve, 10
0, 100A, 100B, 100C, 100D: gas turbine intake cooling device, D1, D2, D3, D4: duct, D2a: pipe inside duct D2, D2b: pipe outside duct D2, D3a: inside duct D3 Plumbing,
D3b: piping outside the duct D3, GV: rectifying plate, N3
4: Spray nozzle.

Claims (10)

[Claims] 1. A gas turbine intake air cooling device for cooling the intake air of an air compressor of a gas turbine, wherein the air extracted from the air compressor is cooled, and cryogenic air in a supercooled state before liquefaction is removed. And a gas turbine intake cooling unit that cools the intake air of the air compressor of the gas turbine using the cryogenic air generated by the cryogenic air generating unit. Characteristic gas turbine intake air cooling device. 2. The cryogenic air generating section is configured to compress air extracted from an air compressor of the gas turbine, and to drive the cryogenic air by driving compressed air discharged from the bleed air compressor. The gas turbine intake cooling device according to claim 1, further comprising a turbine that discharges air. 3. An ice particle generating means for generating ice particles by using cryogenic air generated by the cryogenic air generating unit and mixing the ice particles into intake air of an air compressor of the gas turbine. The gas turbine intake air cooling device according to claim 1 or 2, further comprising: 4. The ice particle generating means includes: a water pre-cooling means for pre-cooling water using cryogenic air generated by the cryogenic air generating unit; and The gas turbine intake air cooling device according to any one of claims 1 to 3, further comprising a pre-cooled water injection unit that mixes with the intake air of the air compressor of the gas turbine and generates ice particles. 5. The apparatus according to claim 4, wherein the water precooling means and the precooled water injection means in the ice particle generating means are arranged in series on an intake line of an air compressor of the gas turbine. A gas turbine intake cooling device as described. 6. The water precooling means and the precooled water injection means in the ice particle generating means are arranged in parallel on an intake line of an air compressor of the gas turbine. A gas turbine intake cooling device as described. 7. The gas turbine according to claim 2, further comprising a bleed air cooling unit that cools air extracted from the air compressor of the gas turbine and introduces the air into the bleed air compressor. Gas turbine intake cooling system. 8. A turbine supply air cooling means disposed on a gas line between the extraction compressor and the turbine, for cooling compressed air discharged from the extraction compressor and supplying the compressed air to the turbine. The gas turbine intake air cooling device according to claim 2, further comprising: 9. A turbine that is disposed on a gas line between the turbine and the gas turbine intake cooling unit, and further cools cryogenic air discharged from the turbine and supplies it to the gas turbine intake cooling unit. The gas turbine intake air cooling device according to any one of claims 2 to 8, further comprising an outlet cooling means. 10. The cryogenic air generator includes a turbine driven by air extracted from an air compressor of the gas turbine to discharge the cryogenic air. 2. The gas turbine intake cooling device according to 1.