WO2015111636A1 - ガスタービンの運転方法および運転制御装置 - Google Patents
ガスタービンの運転方法および運転制御装置 Download PDFInfo
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- WO2015111636A1 WO2015111636A1 PCT/JP2015/051576 JP2015051576W WO2015111636A1 WO 2015111636 A1 WO2015111636 A1 WO 2015111636A1 JP 2015051576 W JP2015051576 W JP 2015051576W WO 2015111636 A1 WO2015111636 A1 WO 2015111636A1
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- WIPO (PCT)
- Prior art keywords
- gas turbine
- drain water
- turbine
- water discharge
- discharge valve
- Prior art date
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- 238000000034 method Methods 0.000 title claims abstract description 17
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 146
- 238000001816 cooling Methods 0.000 claims abstract description 105
- 239000007789 gas Substances 0.000 description 145
- 239000000567 combustion gas Substances 0.000 description 12
- 239000003507 refrigerant Substances 0.000 description 12
- 238000009833 condensation Methods 0.000 description 10
- 230000005494 condensation Effects 0.000 description 10
- 238000010586 diagram Methods 0.000 description 9
- 238000010248 power generation Methods 0.000 description 9
- JEIPFZHSYJVQDO-UHFFFAOYSA-N iron(III) oxide Inorganic materials O=[Fe]O[Fe]=O JEIPFZHSYJVQDO-UHFFFAOYSA-N 0.000 description 8
- 230000002093 peripheral effect Effects 0.000 description 8
- 238000011017 operating method Methods 0.000 description 6
- 239000000446 fuel Substances 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 239000007858 starting material Substances 0.000 description 4
- 230000007423 decrease Effects 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000011084 recovery Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000009529 body temperature measurement Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 239000000498 cooling water Substances 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 238000010926 purge Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
- F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/125—Cooling of plants by partial arc admission of the working fluid or by intermittent admission of working and cooling fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
- F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F17/00—Removing ice or water from heat-exchange apparatus
- F28F17/005—Means for draining condensates from heat exchangers, e.g. from evaporators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/602—Drainage
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/95—Preventing corrosion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/304—Spool rotational speed
Definitions
- the present invention relates to a gas turbine operation method and an operation control device.
- the gas turbine is composed of a compressor, a combustor, and a turbine.
- the compressor compresses the air taken in from the air intake to produce high-temperature and high-pressure compressed air.
- the combustor generates high-temperature and high-pressure combustion gas by supplying fuel to the compressed air and burning it.
- the turbine is configured by alternately arranging a plurality of turbine stationary blades and turbine rotor blades in a passage in a casing, and the turbine rotor blades are driven by combustion gas supplied to the passage, thereby generating a generator.
- the turbine shaft connected to is rotated.
- the combustion gas that has driven the turbine is released into the atmosphere as exhaust gas.
- a drain recovery pipe is connected between the stages of the compressor that compresses the air sprayed with the liquid and a discharge unit to discharge the liquid drain to the outside. It is shown.
- the present invention solves the above-described problems, and an object of the present invention is to provide a gas turbine operation method and an operation control apparatus that can remove water accumulated in a cooling air system while preventing performance loss of the gas turbine. .
- the gas turbine operating method of the present invention comprises a cooling air system for connecting compressed air extracted from the compressor by connecting an intermediate stage or outlet of the compressor and the turbine to the turbine.
- a gas turbine operating method comprising: a heat exchanger that cools the compressed air in the middle of the cooling air system; and a drain water discharge valve provided on the downstream side of the compressed air of the heat exchanger. The drain water discharge valve is opened at least for a predetermined period after reaching the rated speed in starting the gas turbine, and then the drain water discharge valve is closed.
- the temperature of the heat exchanger itself and the refrigerant provided in the cooling air system are low.
- the compressed air extracted from the compressor is supplied to the heat exchanger through the cooling air system.
- the temperature of the heat exchanger itself and the refrigerant is low, so that the compressed air
- the temperature drops significantly and a large amount of drainage is generated.
- the temperature of the heat exchanger itself and the refrigerant rises, so that the amount of drain generated decreases.
- the inventors have found that a large amount of drain is generated immediately after the rated speed is reached in the startup sequence of the gas turbine.
- this gas turbine operating method it is possible to discharge the water of the cooling air system by opening the drain water discharge valve only at the time when a large amount of drain is accumulated. For this reason, the occurrence of rust in the cooling air system can be prevented, and the drain water discharge valve is closed when the predetermined period is exceeded, so that the escape of compressed air sent to the cooling air system is suppressed. The performance loss of the gas turbine can be prevented.
- the time point at which the outlet temperature of the heat exchanger rises to reach the set temperature after reaching the rated speed at the start of the gas turbine is the end of the predetermined period.
- the set temperature can be the temperature at which drain water stops due to condensation. Therefore, by closing the drain water discharge valve based on the outlet temperature of the heat exchanger, it is possible to suppress the escape of the compressed air sent to the cooling air system and to obtain the effect of preventing the performance loss of the gas turbine. be able to.
- the gas turbine operating method of the present invention is characterized in that a predetermined time elapses from the start of the start of the gas turbine is the end of the predetermined period.
- the set time can be the elapsed time from the start of the gas turbine to the point when the drain water due to condensation stops. Therefore, by closing the drain water discharge valve based on the set time from the start of gas turbine startup, it is possible to suppress the loss of compressed air sent to the cooling air system and prevent the performance loss of the gas turbine. Remarkably can be obtained.
- the drain water discharge valve is closed when the gas turbine is stopped, and the drain water discharge valve is opened after starting the gas turbine. To do.
- an operation control device for a gas turbine is a cooling air system that connects an intermediate stage or outlet of a compressor and a turbine and supplies compressed air extracted from the compressor to the turbine. And a heat exchanger for cooling the compressed air in the middle of the cooling air system, and a drain water discharge valve provided on the downstream side of the compressed air of the heat exchanger.
- the temperature of the heat exchanger itself and the refrigerant provided in the cooling air system are low.
- the compressed air extracted from the compressor is supplied to the heat exchanger through the cooling air system.
- the temperature of the heat exchanger itself and the refrigerant is low, so that the compressed air
- the temperature drops significantly and a large amount of drainage is generated.
- the temperature of the heat exchanger itself and the refrigerant rises, so that the amount of drain generated decreases.
- the inventors have found that a large amount of drain is generated immediately after the rated speed is reached in the startup sequence of the gas turbine.
- the drain water discharge valve can be controlled to be opened only when the large amount of drain is accumulated, and the water of the cooling air system can be discharged. For this reason, the occurrence of rust in the cooling air system can be prevented, and the drain water discharge valve is controlled to be closed when a predetermined period of time is exceeded, thereby suppressing the escape of compressed air sent to the cooling air system, The performance loss of the gas turbine can be prevented.
- the outlet temperature of the heat exchanger is detected, and the drain water discharge valve is closed when the outlet temperature rises to a set temperature.
- the set temperature can be the temperature at which drain water stops due to condensation. Therefore, by controlling closing of the drain water discharge valve based on the outlet temperature of the heat exchanger, it is possible to suppress the escape of compressed air sent to the cooling air system and to obtain a remarkable effect of preventing performance loss of the gas turbine. Can do.
- the elapsed time from the start of the start of the gas turbine is detected, and when the elapsed time reaches a preset time, the drain water discharge valve is closed and controlled. It is characterized by doing.
- the set time can be the elapsed time from the start of the gas turbine to the point when the drain water due to condensation stops. Therefore, the drain water discharge valve is controlled to be closed based on the set time from the start of gas turbine startup, thereby suppressing the loss of compressed air sent to the cooling air system and preventing the performance loss of the gas turbine. Can get to.
- the stop and start of the gas turbine are detected, the drain water discharge valve is controlled to be closed when the gas turbine is stopped, and the drain water discharge valve is controlled to open after the start of the start. It is characterized by.
- water accumulated in the cooling air system can be removed while preventing performance loss of the gas turbine.
- FIG. 1 is a schematic configuration diagram of an operation control apparatus for a gas turbine according to an embodiment of the present invention.
- FIG. 2 is a configuration diagram of a gas turbine to which an operation control device for a gas turbine according to an embodiment of the present invention is applied.
- FIG. 3 is a configuration diagram of a cooling air system in the gas turbine to which the operation control device for the gas turbine according to the embodiment of the present invention is applied.
- FIG. 4 is a schematic configuration diagram of another example of a cooling air system in a gas turbine to which an operation control device for a gas turbine according to an embodiment of the present invention is applied.
- FIG. 5 is a graph showing the relationship between air pressure and dew point.
- FIG. 6 is a graph showing the gas turbine load, the turbine shaft rotational speed, and the heat exchanger outlet temperature with respect to time in the gas turbine.
- FIG. 1 is a schematic configuration diagram of a gas turbine power generation facility according to the present embodiment
- FIG. 2 is a configuration diagram of a gas turbine in the gas turbine power generation facility according to the present embodiment
- FIG. It is a block diagram of the cooling air system
- FIG. 4 is a schematic configuration diagram of another example of the gas turbine power generation facility according to the present embodiment.
- FIG. 5 is a graph showing the relationship between air pressure and dew point
- FIG. 6 is a graph showing the gas turbine load, turbine shaft rotational speed, and heat exchanger outlet temperature with respect to time in the gas turbine.
- the gas turbine power generation facility 1 includes a generator 100, a gas turbine 200, a cooling air system 300, and a drain water discharge system 400.
- the generator 100 generates power when the drive shaft 101 is connected to a turbine shaft 204 of a gas turbine 200 described later, and rotational power of the turbine shaft 204 is applied.
- the generator 100 is also used as a starter motor that applies rotational power to the turbine shaft 204 when the gas turbine 200 is started.
- the gas turbine 200 includes a compressor 201, a combustor 202, and a turbine 203.
- a turbine shaft 204 is disposed through the center of the compressor 201, the combustor 202, and the turbine 203.
- the compressor 201, the combustor 202, and the turbine 203 are arranged in parallel along the axis R of the turbine shaft 204 from the front side to the rear side of the air flow.
- the turbine axial direction refers to a direction parallel to the axis R
- the turbine circumferential direction refers to a circumferential direction around the axis R.
- Compressor 201 compresses air into compressed air.
- the compressor 201 is provided with a compressor stationary blade 213 and a compressor moving blade 214 in a compressor casing 212 having an air intake port 211 for taking in air.
- a plurality of compressor vanes 213 are attached to the compressor casing 212 side and are arranged in parallel in the turbine circumferential direction.
- a plurality of compressor rotor blades 214 are attached to the turbine shaft 204 side and are arranged in parallel in the turbine circumferential direction.
- the compressor stationary blades 213 and the compressor rotor blades 214 are alternately provided along the turbine axial direction.
- the combustor 202 generates high-temperature and high-pressure combustion gas by supplying fuel to the compressed air compressed by the compressor 201.
- the combustor 202 covers, as a combustion cylinder, an inner cylinder 221 that mixes and burns compressed air and fuel, a tail cylinder 222 that guides combustion gas from the inner cylinder 221 to the turbine 203, and an outer periphery of the inner cylinder 221. And an outer cylinder 223 that forms an air passage 225 that guides compressed air from 201 to the inner cylinder 221.
- a plurality of (for example, 16) combustors 202 are juxtaposed in the turbine circumferential direction with respect to the combustor casing 224 forming the turbine casing.
- the turbine 203 generates rotational power by the combustion gas burned in the combustor 202.
- a turbine stationary blade 232 and a turbine rotor blade 233 are provided in a turbine casing 231.
- a plurality of turbine vanes 232 are attached to the turbine casing 231 side and are arranged in parallel in the turbine circumferential direction.
- a plurality of turbine rotor blades 233 are attached to the turbine shaft 204 side and arranged in parallel in the turbine circumferential direction.
- These turbine stationary blades 232 and turbine rotor blades 233 are provided alternately along the turbine axial direction.
- an exhaust chamber 234 having an exhaust diffuser 234 a continuous with the turbine 203 is provided on the rear side of the turbine casing 231.
- the turbine shaft 204 has an end portion on the compressor 201 side supported by the bearing portion 241 and an end portion on the exhaust chamber 234 side supported by the bearing portion 242 so as to be rotatable about the shaft center R.
- the turbine shaft 204 is connected to the drive shaft 101 of the generator 100 at the end on the compressor 201 side.
- the air taken in from the air intake port 211 of the compressor 201 is compressed by passing through the plurality of compressor stationary blades 213 and the compressor moving blades 214, thereby compressing at a high temperature and high pressure. It becomes air.
- the compressed air is mixed with fuel in the combustor 202 and burned, whereby high-temperature and high-pressure combustion gas is generated.
- the combustion gas passes through the turbine stationary blade 232 and the turbine rotor blade 233 of the turbine 203 so that the turbine shaft 204 is rotationally driven, and rotational power is applied to the generator 100 connected to the turbine shaft 204.
- the exhaust gas after rotationally driving the turbine shaft 204 is discharged into the atmosphere as exhaust gas through the exhaust diffuser 234a in the exhaust chamber 234.
- the cooling air system 300 is provided in the gas turbine 200 described above, and supplies the compressed air extracted from the compressor 201 to the turbine 203.
- the turbine shaft 204 is configured such that a plurality of turbine disks 251 and the like are integrally connected to the intermediate shaft 250 by connecting bolts 252, and can be freely rotated by the bearing portions 241 and 242. It is supported by.
- a turbine rotor blade 233 is attached to the outer peripheral portion of the turbine disk 251.
- the turbine rotor blade 233 includes a plurality of blade root portions 233a fixed to the outer peripheral end of the turbine disk 251 along the circumferential direction of the turbine, a planet home 233b connecting the blade root portions 233a, and a peripheral surface of the planet home 233b. And a plurality of moving blade portions 233c fixed at equal intervals in the direction.
- An intermediate shaft cover 253 having a ring shape along the circumferential direction of the turbine is attached to the outer periphery of the turbine shaft 204, and a plurality of combustion is provided in the combustor casing 224 on the outer periphery of the intermediate shaft cover 253.
- a turbine casing 254 is defined outside the vessel 202.
- the transition piece 222 communicates with a combustion gas passage 255 formed in an annular shape along the turbine circumferential direction in the turbine 203.
- a plurality of turbine stationary blades 232 and a plurality of turbine rotor blades 233 are alternately arranged along the turbine axial direction.
- the turbine shaft 204 is provided with a cooling air supply hole 256 provided in the turbine disk 251 along the turbine shaft direction and having an opening on the compressor 201 side.
- the cooling air supply hole 256 is formed along the turbine axial direction and communicates with a cooling hole (not shown) provided inside each turbine blade 233 via each turbine disk 251.
- a seal ring holding ring 257 having a ring shape along the turbine circumferential direction is provided in the intermediate shaft cover 253 around the inlet portion of the cooling air supply hole 256.
- the seal ring retaining ring 257 is mounted on its outer peripheral surface side so that each end in the turbine shaft direction is in close contact with the inner peripheral portion of the intermediate shaft cover 253 and between the intermediate shaft cover 253 at the center in the turbine shaft direction.
- a space 262 is defined along the circumferential direction of the turbine.
- the seal ring holding ring 257 has a plurality of seals 258, 259, 260, and 261 that seal gaps between the inner peripheral surface of the seal ring holding ring 257 and the outer peripheral surface of the turbine shaft 204 on the inner peripheral surface side thereof. Is provided.
- the space portion 262 defined between the intermediate shaft cover 253 and the seal ring holding ring 257 communicates with the inlet portion of the cooling air supply hole 256 through the through hole 263 formed in the seal ring holding ring 257. Yes.
- the combustor casing 224 is connected to one end side of a cooling air pipe 301 that forms a cooling air system 300 so as to communicate with the turbine casing 254 to the outside.
- a cooling air pipe 301 that forms a cooling air system 300 so as to communicate with the turbine casing 254 to the outside.
- one end of the cooling air pipe 301 is provided as shown in FIG. 1 and is connected to one connecting portion 302 formed in the combustor casing 224 as shown in FIG.
- the cooling air pipe 301 is formed by branching the other end side into a plurality (four in FIG. 1), each of which passes through the combustor casing 224 and is attached to the intermediate shaft cover 253.
- the cooling air supply hole 256 communicates with the cooling air through the space 262.
- the cooling air pipe 301 is provided with a TCA cooler 303 as a heat exchanger in the middle thereof.
- a TCA cooler 303 In the TCA cooler 303, an inlet header 303a connected to one end of the cooling air pipe 301 and an outlet header 303b connected to the other end of the cooling air pipe 301 are provided in the heat exchange section 303c.
- the supplied compressed air is heat exchanged with the refrigerant in the heat exchanging section 303c, and the compressed air after the heat exchange is discharged from the outlet header 303b.
- the TCA cooler 303 is disposed outside the building 1a of the gas turbine power generation facility 1 in which the gas turbine 200 and the like are accommodated, as shown in FIG.
- the cooling air pipe 301 is provided with a filter 304 on the other end side of the TCA cooler 303 in the middle thereof.
- compressed air compressed by the compressor 201 of the gas turbine 200 is supplied to the turbine casing 254.
- This compressed air is guided from the turbine casing 254 to the combustor 202, and high-temperature and high-pressure combustion gas is generated in the combustor 202, flows into the combustion gas passage 255 through the tail cylinder 222, and is sent to the turbine 203.
- the cooling air system 300 a part of the compressed air supplied to the turbine casing 254 leading to the outlet of the compressor 201 is extracted from one end side of the cooling air pipe 301, and a space portion is formed from the other end side of the cooling air pipe 301.
- the cooling air is supplied to the cooling air supply hole 256 on the turbine 203 side through the through hole 263 through the through hole 263, and passes through the cooling hole of each turbine rotor blade 233.
- the compressed air passing through the cooling air pipe 301 is cooled by the TCA cooler 303, and foreign matters are removed by the filter 304 to reach each turbine blade 233 to cool each turbine blade 233.
- FIG. 4 is a schematic configuration diagram of another example of the gas turbine power generation facility according to the present embodiment, and shows another example of the cooling air system.
- the cooling air system 500 bleeds compressed air from the intermediate stage of the compressor 201 and supplies it to the turbine 203 side.
- the compressor 201 communicates with the inside of the compressor casing 212 outside the position of the compressor vane 213 in the compressor casing 212 and in the turbine circumferential direction.
- a compressor bleed chamber 215 formed in a ring shape is provided.
- the turbine 203 is provided with a turbine blade ring cavity 235 formed in an annular shape along the turbine circumferential direction outside the position of the turbine stationary blade 232 in the combustor casing 224.
- the turbine blade ring cavity 235 communicates with cooling holes (not shown) provided inside each turbine stationary blade 232.
- one end of a cooling air pipe 501 that forms a cooling air system 500 is connected to the compressor bleed chamber 215.
- the other end of the cooling air pipe 501 is connected to the turbine blade ring cavity 235.
- the cooling air pipe 501 is provided with a TCA cooler 503 that is a heat exchanger in the middle thereof.
- an inlet header 503a connected to one end of the cooling air pipe 501 and an outlet header 503b connected to the other end of the cooling air pipe 501 are provided in the heat exchange unit 503c. Heat exchange is performed between the supplied cooling target and the heat exchanging unit 503c, and the cooling target after the heat exchange is discharged from the outlet header 503b.
- the TCA cooler 503 is disposed outside the building 1a of the gas turbine power generation facility 1 in which the gas turbine 200 and the like are accommodated, as shown in FIG. 501 is pulled out of the building 1 a and connected to the TCA cooler 503. Further, as shown in FIG. 4, the cooling air pipe 501 is provided with a filter 504 on the other end side of the TCA cooler 503 in the middle thereof. This filter 504 is also disposed outside the building 1 a of the gas turbine power generation facility 1.
- the compressed air compressed by the compressor 201 of the gas turbine 200 is extracted from one end side of the cooling air pipe 501 from the compressor bleed chamber 215, and the turbine blades from the other end side of the cooling air pipe 501. It passes through the cooling cavity of each turbine vane 232 via the ring cavity 235.
- the compressed air passing through the cooling air pipe 501 is cooled by the TCA cooler 503, and foreign matters brought from the compressor bleed chamber 215 are removed by the filter 504 to reach each turbine stationary blade 232, and each turbine stationary blade 232 is cooled. To do.
- the drain water discharge system 400 discharges drain water from the cooling air systems 300 and 500. Drain water is generated when moisture in the atmosphere is condensed when the temperature of high-temperature and high-pressure compressed air is lowered by the TCA cooler 303, and is likely to accumulate in the outlet header 303 b of the TCA cooler 303. In addition, a part of the drain water collected in the outlet header 303b of the TCA cooler 303 is sent along the flow of compressed air in the cooling air pipes 301 and 501, and in the cooling air system such as the casing of the filter 304. It tends to accumulate at a lowered position. For this reason, in the drain water discharge system 400, as shown in FIG. 1 and FIG.
- the drain water discharge pipe 401 is connected to the cooling air pipes 301 and 501 in the cooling air systems 300 and 500.
- the drain water discharge pipe 401 is connected to the outlet header 303b of the TCA cooler 303.
- the drain water discharge pipe 401 is connected to the casing of the filters 304 and 504.
- the drain water discharge pipe 401 is provided with a drain water discharge valve. Although there may be one drain water discharge valve, for safety, a first drain water discharge valve 402 and a second drain water discharge valve 403 provided along the drain water discharge pipe 401 may be provided.
- the drain water discharge pipe 401 is connected to a drain pit (not shown) in which drain water is stored. In some drain pits, the drain water discharge pipe 401 is connected exclusively, and drain water discharged from other facilities is also stored.
- the drain water discharge system 400 controls the opening and closing of the drain water discharge valves (the first drain water discharge valve 402 and the second drain water discharge valve 403) when the gas turbine 200 is operated. It has the control apparatus 404 which is.
- the control device 404 measures the temperature of the compressed air at the outlet headers 303b and 503b of the TCA coolers 303 and 503 (the outlet temperature of the TCA coolers 303 and 503) by temperature measurement provided at the outlet headers 303b and 503b of the TCA coolers 303 and 503. Obtained from the container 405. Further, the control device 404 acquires the start of starting the gas turbine 200 from a control device (not shown) on the gas turbine 200 side. In addition, the control device 404 acquires an elapsed time from the start of starting the gas turbine 200 from a control device (not shown) on the gas turbine 200 side.
- control device 404 controls the closing of the first drain water discharge valve 402 and the second drain water discharge valve 403, so that the set temperature ⁇ at the outlet temperature of the TCA coolers 303 and 503 shown in FIG. 5 and FIG.
- a set time ⁇ which is an elapsed time from the start of startup of the gas turbine 200 shown in FIG.
- a curve indicated by a solid line in FIG. 5 shows a change in dew point when air of a predetermined humidity is compressed. From this, it can be seen that the dew point increases by compressing the air.
- broken lines connecting points A, B, and C shown in FIG. 5 are exit conditions of the TCA coolers 303 and 503 in the startup sequence of the gas turbine 200. Point A is when the gas turbine starts to start, and point B is when the rated rotational speed is reached. Between points A and B, the pressure of the compressed air increases due to the increase in the rotation speed of the compressor 201, but the temperature of the TCA coolers 303 and 503 itself and the temperature of the refrigerant supplied to the TCA coolers 303 and 503 are low.
- the outlet temperature of the TCA coolers 303 and 503 does not rise so much. Therefore, the outlet temperature of the TCA coolers 303 and 503 is lower than the dew point temperature, condensation occurs, and drain water is generated. Thereafter, when the gas turbine 200 is inserted and the load is increased, the pressure of the compressed air increases, and the temperature of the TCA coolers 303 and 503 itself and the temperature of the refrigerant supplied to the TCA coolers 303 and 503 increase. Therefore, the outlet temperature of the TCA coolers 303 and 503 also increases. Then, after point C where the outlet temperatures of the TCA coolers 303 and 503 exceed the dew point temperature, no condensation occurs.
- the controller 404 sets the set temperature ⁇ according to the atmospheric temperature.
- the setting time ⁇ will be described.
- the horizontal axis represents time
- the solid line represents the rotational speed of the turbine shaft 204
- the broken line represents the temperature (outlet temperature) of the outlet headers 303 b and 503 b of the TCA coolers 303 and 503
- the alternate long and short dash line represents the gas turbine 200. Shows the load.
- the rotational speed of the turbine shaft 204 was increased by the rotational power applied by the starter motor at the time of startup (point A) after the gas turbine 200 stopped (turbine stationary or turning state), and passed through a purge operation at a constant speed.
- the combustor 202 is ignited, the turbine 203 can be operated independently, the starter motor is disconnected, and a no-load rated speed (for example, 3600 rpm) is obtained at point D. .
- a no-load rated speed for example, 3600 rpm
- the generator 100 is inserted after the point D, and the load increases while maintaining the rotational speed of the turbine shaft 204 at the rated speed. Then, the temperature (outlet temperature) of the outlet headers 303b and 503b of the TCA coolers 303 and 503 reaches the set temperature ⁇ in the process of increasing the load of the gas turbine 200.
- the gas turbine 200 When the gas turbine 200 is started, the elapsed time from the point A at the time of start-up until the temperature of the outlet headers 303b and 503b of the TCA coolers 303 and 503 rises to reach the set temperature ⁇ is set time ⁇ .
- the generator 100 When the gas turbine 200 is stopped, the generator 100 is disconnected and the load is reduced while maintaining the rotational speed of the turbine shaft 204 at the rated speed, and then the supply of fuel to the combustor 202 is stopped.
- the control apparatus 404 discharges
- the first drain water discharge valve 402 and the temperature of the outlet headers 303b, 503b of the TCA coolers 303, 503 reach the set temperature ⁇ .
- the second drain water discharge valve 403 is controlled to be closed, in order to surely discharge the drain water generated before reaching the set temperature ⁇ , the set temperature ⁇ + x obtained by adding a temperature x having a slight margin to the set temperature ⁇ .
- the first drain water discharge valve 402 and the second drain water discharge valve 403 may be controlled to be closed.
- the control device 404 controls the opening of the first drain water discharge valve 402 and the second drain water discharge valve 403 at the time of starting from the stop of the gas turbine 200 (point A), and the gas turbine 200
- the first drain water discharge valve 402 and the second drain water discharge valve 403 may be controlled to be closed when the set time ⁇ has elapsed from the start of the start of the gas turbine 200 after reaching the rated speed (point D) at the start of the 200. .
- the control device 404 maintains this closing control until the next start (point A) from the stop of the gas turbine 200.
- the first drain water discharge valve 402 and the second drain water discharge valve 403 are closed and controlled when the set time ⁇ has elapsed since the start of the gas turbine 200.
- the first drain water discharge valve is passed when the set time ⁇ + y obtained by adding a time y with a slight margin to the set time ⁇ . 402 and the second drain water discharge valve 403 may be closed.
- the control device 404 controls the opening of the first drain water discharge valve 402 and the second drain water discharge valve 403 from the start (point A) of the gas turbine 200 until the set temperature ⁇ or the set time ⁇ . This is not the case.
- the drain water is generated most after reaching the rated speed at the start of the gas turbine 200, and the generation of drain water ends after the start of the load increase at the start of the gas turbine 200.
- the control device 404 controls to open the first drain water discharge valve 402 and the second drain water discharge valve 403 at least in a predetermined period after reaching the rated speed in starting the gas turbine 200.
- the end point of the predetermined period may be a point at which condensation can be stopped and all the drain water accumulated can be drained.
- the start of the predetermined period is set to the time when the gas turbine 200 is started (point A) or the rated speed is reached when the gas turbine 200 is started (point D), and the end of the predetermined period is set to the set temperature ⁇ described above.
- the time when ( ⁇ + x) is reached or the time when the set time ⁇ ( ⁇ + y) elapses can be used.
- the start of the predetermined period may be the time when the set temperature ⁇ is reached or the time when the set time ⁇ has passed, or the time when the set temperature ⁇ is passed or the set time ⁇ is passed. It may be the time when it has passed, or the end of the predetermined period may be the time when the required drainage time of all drain water obtained in advance by a test or the like has elapsed.
- the operation method of the gas turbine 200 includes a cooling air system 300 that connects the intermediate stage or outlet of the compressor 201 and the turbine 203 and supplies compressed air extracted from the compressor 201 to the turbine 203.
- 500 TCA coolers (heat exchangers) 303 and 503 for cooling the compressed air in the middle of the cooling air systems 300 and 500, and drain water discharge provided on the downstream side of the compressed air of the TCA coolers 303 and 503
- a valve first drain water discharge valve 402 and second drain water discharge valve 403
- a method for operating the gas turbine 200 wherein at least a predetermined period after reaching the rated speed in starting the gas turbine 200 The drain valve is opened, and then the drain water drain valve is closed when a predetermined period is exceeded.
- the temperatures of the TCA coolers 303 and 503 themselves provided in the cooling air systems 300 and 500 and the refrigerant thereof are low.
- the compressed air extracted from the compressor 201 is supplied to the TCA coolers 303 and 503 through the cooling air systems 300 and 500.
- the TCA coolers 303 and 503 themselves and the refrigerant Due to the low temperature, the temperature of the compressed air is greatly reduced and a large amount of drain is generated. Thereafter, the TCA coolers 303 and 503 themselves and the temperature of the refrigerant rise, so that the amount of drain generation decreases.
- the inventors have found that a large amount of drain is generated immediately after the rated speed is reached in the startup sequence of the gas turbine 200. Therefore, according to the operation method of the gas turbine 200, the cooling water system 300 is opened by opening the first drain water discharge valve 402 and the second drain water discharge valve 403 only at a time when a large amount of drain is accumulated. , 500 drain water can be discharged. For this reason, it is possible to prevent the occurrence of rust in the cooling air systems 300 and 500, and to close the first drain water discharge valve 402 and the second drain water discharge valve 403 when a predetermined period is exceeded, The escape of compressed air sent to the cooling air systems 300 and 500 can be suppressed, and the performance loss of the gas turbine 200 can be prevented.
- the time when the temperature of the outlet headers 303b and 503b of the TCA coolers 303 and 503 rises and reaches the set temperature ⁇ after reaching the rated speed at the start of the gas turbine 200 is predetermined. The end of the period.
- the set temperature ⁇ can be the temperature at which drain water stops due to condensation. Therefore, the first drain water discharge valve 402 and the second drain water discharge valve 403 are closed based on the temperatures of the outlet headers 303b and 503b of the TCA coolers 303 and 503, so that they are sent to the cooling air systems 300 and 500. In addition, the effect of suppressing the loss of compressed air and preventing the performance loss of the gas turbine 200 can be significantly obtained.
- the time when the set time ⁇ has elapsed since the start of the gas turbine 200 is set as the end of the predetermined period.
- the set time ⁇ can be an elapsed time from the start of the start of the gas turbine 200 to the time when the drain water due to condensation stops. Therefore, the compressed water sent to the cooling air systems 300 and 500 is closed by closing the first drain water discharge valve 402 and the second drain water discharge valve 403 based on the set time ⁇ from the start of the start of the gas turbine 200. The effect of suppressing the escape of air and preventing the performance loss of the gas turbine 200 can be significantly obtained.
- the first drain water discharge valve 402 and the second drain water discharge valve 403 are closed, and after the start of the gas turbine 200, the first drain water discharge valve 403 is closed.
- the drain water discharge valve 402 and the second drain water discharge valve 403 are opened.
- the drain water discharge pipe 401 provided with the first drain water discharge valve 402 and the second drain water discharge valve 403 is connected to a drain pit in which drain water discharged from other facilities is stored together.
- moisture may be sent from other equipment through the drain water discharge pipe 401 and taken into the cooling air system 300, 500, which may cause rust in the cooling air system 300, 500. Therefore, when the gas turbine 200 is stopped, the first drain water discharge valve 402 and the second drain water discharge valve 403 are closed, and the first drain water discharge valve 402 and the second drain water discharge valve are started after the gas turbine 200 is started.
- By setting 403 to the open state it is possible to prevent the moisture from being taken into the cooling air systems 300 and 500 when the gas turbine 200 is stopped.
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Abstract
Description
201 圧縮機
203 タービン
300,500 冷却空気系統
303,503 TCAクーラ(熱交換器)
303b,503b 出口ヘッダ
400 ドレン水排出系統
401 ドレン水排出配管
402 第一ドレン水排出弁
403 第二ドレン水排出弁
404 制御装置
α 設定温度
β 設定時間
Claims (8)
- 圧縮機の中間段または出口とタービンとを接続して前記圧縮機から抽気した圧縮空気をタービンに供給する冷却空気系統を備えており、前記冷却空気系統の途中に前記圧縮空気を冷却する熱交換器と、前記熱交換器の前記圧縮空気の下流側に設けられたドレン水排出弁とを備えるガスタービンの運転方法であって、
少なくとも前記ガスタービンの起動における定格速度到達の後の所定期間に前記ドレン水排出弁を開状態とし、その後、前記ドレン水排出弁を閉状態とすることを特徴とするガスタービンの運転方法。 - 前記ガスタービンの起動における定格速度到達の後に前記熱交換器の出口温度が上昇して設定温度に至る時点を前記所定期間の終わりとすることを特徴とする請求項1に記載のガスタービンの運転方法。
- 前記ガスタービンの起動開始から設定時間が経過した時点を前記所定期間の終わりとすることを特徴とする請求項1に記載のガスタービンの運転方法。
- 前記ガスタービンの停止時は前記ドレン水排出弁を閉状態とし、前記ガスタービンの起動開始後に前記ドレン水排出弁を開状態とすることを特徴とする請求項1~3のいずれか一つに記載のガスタービンの運転方法。
- 圧縮機の中間段または出口とタービンとを接続して前記圧縮機から抽気した圧縮空気をタービンに供給する冷却空気系統を備えており、前記冷却空気系統の途中に前記圧縮空気を冷却する熱交換器と、前記熱交換器の前記圧縮空気の下流側に設けられたドレン水排出弁とを備えるガスタービンの運転制御装置であって、
前記ガスタービンの起動における定格速度到達の後の所定期間を検出し、少なくとも前記所定期間に前記ドレン水排出弁を開放制御し、前記所定期間を超えた場合に前記ドレン水排出弁を閉鎖制御することを特徴とするガスタービンの運転制御装置。 - 前記熱交換器の出口温度を検出し、当該出口温度が上昇して設定温度に至った場合に前記ドレン水排出弁を閉鎖制御することを特徴とする請求項5に記載のガスタービンの運転制御装置。
- 前記ガスタービンの起動開始からの経過時間を検出し、当該経過時間が予め設定された設定時間となった場合に前記ドレン水排出弁を閉鎖制御することを特徴とする請求項5に記載のガスタービンの運転制御装置。
- 前記ガスタービンの停止および起動開始を検出し、停止時に前記ドレン水排出弁を閉鎖制御し、起動開始後に前記ドレン水排出弁を開放制御することを特徴とする請求項5~7のいずれか一つに記載のガスタービンの運転制御装置。
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CN201580003967.8A CN105899782B (zh) | 2014-01-27 | 2015-01-21 | 燃气涡轮机的运转方法以及运转控制装置 |
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Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS6240300U (ja) * | 1985-08-29 | 1987-03-10 | ||
JPH0882226A (ja) * | 1994-09-13 | 1996-03-26 | Mitsubishi Heavy Ind Ltd | 空気冷却器 |
JP2000161084A (ja) * | 1998-11-26 | 2000-06-13 | Toshiba Corp | 燃料加温装置 |
JP2012154290A (ja) * | 2011-01-28 | 2012-08-16 | Hitachi Ltd | 圧縮機のドレン排出装置及びガスタービンシステム |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS6240300A (ja) | 1985-08-13 | 1987-02-21 | Wako Pure Chem Ind Ltd | 体液中のアデノシンデアミナ−ゼの活性測定法 |
JP3849473B2 (ja) * | 2001-08-29 | 2006-11-22 | 株式会社日立製作所 | ガスタービンの高温部冷却方法 |
EP1293655A1 (en) * | 2001-09-13 | 2003-03-19 | Mitsubishi Heavy Industries, Ltd. | Gas turbine, driving method thereof and gas turbine combined electric power generation plant |
JP4004800B2 (ja) * | 2002-01-10 | 2007-11-07 | 株式会社東芝 | コンバインドサイクル発電システム |
CN1571879A (zh) * | 2002-03-04 | 2005-01-26 | 三菱重工业株式会社 | 涡轮设备、复合发电设备和涡轮工作方法 |
JP2007146787A (ja) | 2005-11-29 | 2007-06-14 | Mitsubishi Heavy Ind Ltd | ガスタービン |
US8075245B2 (en) * | 2009-05-27 | 2011-12-13 | Dresser-Rand Company | Removal of moisture from process gas |
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS6240300U (ja) * | 1985-08-29 | 1987-03-10 | ||
JPH0882226A (ja) * | 1994-09-13 | 1996-03-26 | Mitsubishi Heavy Ind Ltd | 空気冷却器 |
JP2000161084A (ja) * | 1998-11-26 | 2000-06-13 | Toshiba Corp | 燃料加温装置 |
JP2012154290A (ja) * | 2011-01-28 | 2012-08-16 | Hitachi Ltd | 圧縮機のドレン排出装置及びガスタービンシステム |
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