WO2016121684A1 - ガスタービンの冷却系統、これを備えているガスタービン設備、及びガスタービンの部品冷却方法 - Google Patents
ガスタービンの冷却系統、これを備えているガスタービン設備、及びガスタービンの部品冷却方法 Download PDFInfo
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- WO2016121684A1 WO2016121684A1 PCT/JP2016/052000 JP2016052000W WO2016121684A1 WO 2016121684 A1 WO2016121684 A1 WO 2016121684A1 JP 2016052000 W JP2016052000 W JP 2016052000W WO 2016121684 A1 WO2016121684 A1 WO 2016121684A1
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- temperature
- valve
- gas turbine
- air
- output
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- 238000001816 cooling Methods 0.000 title claims abstract description 269
- 239000007789 gas Substances 0.000 claims description 258
- 238000000605 extraction Methods 0.000 claims description 163
- 239000000567 combustion gas Substances 0.000 claims description 60
- 230000000875 corresponding effect Effects 0.000 claims description 32
- 239000000446 fuel Substances 0.000 claims description 30
- 230000001276 controlling effect Effects 0.000 claims description 29
- 230000008859 change Effects 0.000 claims description 20
- 238000000034 method Methods 0.000 claims description 13
- 230000002596 correlated effect Effects 0.000 claims description 8
- 238000002156 mixing Methods 0.000 claims description 6
- 230000000740 bleeding effect Effects 0.000 abstract 2
- 230000007423 decrease Effects 0.000 description 24
- 238000007789 sealing Methods 0.000 description 15
- 238000011144 upstream manufacturing Methods 0.000 description 12
- 238000002485 combustion reaction Methods 0.000 description 9
- 230000008569 process Effects 0.000 description 8
- 238000004891 communication Methods 0.000 description 5
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 230000002093 peripheral effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000000284 extract Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000003491 array Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
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Classifications
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- 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
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- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/20—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted
- F01D17/22—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical
- F01D17/26—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical fluid, e.g. hydraulic
-
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- 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
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- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
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- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
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- 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
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- 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
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
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- 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
- F05D2260/211—Heat transfer, e.g. cooling by intercooling, e.g. during a compression cycle
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- 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
- F05D2260/606—Bypassing the fluid
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- 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
- F05D2270/01—Purpose of the control system
- F05D2270/11—Purpose of the control system to prolong engine life
- F05D2270/112—Purpose of the control system to prolong engine life by limiting temperatures
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- 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
- F05D2270/303—Temperature
Definitions
- a gas turbine component cooling method for achieving the above object is the gas turbine component cooling method according to the eighteenth aspect, wherein in the second control step, the intake air temperature is the predetermined value.
- the intake air temperature is the predetermined value.
- a control signal corresponding to a constant valve opening is output to the second valve regardless of changes in the intake air temperature.
- the intake air temperature is equal to or higher than the second temperature
- the gas turbine equipment of this embodiment includes a gas turbine 1, a cooling system 60 that cools components that constitute the gas turbine 1, and a control device 100.
- the gas turbine 1 includes a compressor 10 that compresses air, a combustor 30 that generates fuel gas by burning fuel F in the air compressed by the compressor 10, a turbine 40 that is driven by the combustion gas, It has.
- a stationary blade row 14 is disposed on each downstream side Dad of the plurality of blade rows 13. Each stationary blade row 14 is provided inside the compressor casing 18. Each stationary blade row 14 is composed of a plurality of stationary blades arranged in the circumferential direction Dc. An annular space between the radially outer peripheral side of the rotor shaft 12 and the radially inner peripheral side of the compressor casing 18 is a region where the stationary blade row 14 and the moving blade row 13 are arranged in the axial direction Da. An air compression flow path 19 that is compressed while air flows is formed. That is, the compressor 10 is an axial multistage compressor. The combustor 30 is housed and fixed at a position on the downstream side Dad from the position where the air compression flow path 19 is formed in the compressor casing 18.
- the turbine 40 includes a turbine rotor 41 that rotates about an axis Ar, a turbine casing 48 that covers the turbine rotor 41, and a plurality of stationary blade rows 53.
- the turbine rotor 41 includes a rotor shaft 42 extending in the axial direction Da around the axis line Ar, and a plurality of blade rows 43 attached to the rotor shaft 42.
- the plurality of blade arrays 43 are arranged in the axial direction Da.
- Each moving blade row 43 is configured by a plurality of moving blades 44 arranged in the circumferential direction Dc.
- a stationary blade row 53 is arranged on each upstream side Dau of the plurality of blade rows 43.
- Each stationary blade row 53 is provided inside the turbine casing 48.
- the stationary blade 54 includes a blade body 55 extending in the radial direction Dr, an inner shroud 56 provided inside the radial direction Dr of the blade body 55, and a radial direction Dr of the inner shroud 56. And a seal member 57 provided on the inside of the.
- the outer portion of the wing body 55 in the radial direction Dr is attached to the turbine casing 48.
- the inner shroud 56 is a member that defines a part of the inner side of the annular combustion gas passage 49 in the radial direction Dr.
- the seal member 57 faces the rotor shaft 42 of the rotating turbine rotor 41 with a space therebetween.
- a disk cavity 59 that is a space is formed inside the inner shroud 56 in the radial direction Dr and between the seal member 57 and the rotor shaft 42 of the turbine rotor 41.
- the moving blade 44 has a wing body 45 extending in the radial direction Dr and a platform 46 provided inside the wing body 45 in the radial direction Dr.
- the platform 46 is a member that defines a part of the inside of the annular combustion gas passage 49 in the radial direction Dr.
- the turbine 40 of this embodiment includes a first stator blade row, a second stator blade row, a third stator blade row, and a fourth stator blade row as the stator blade row 53.
- the moving blade row 43 includes a first moving blade row, a second moving blade row, a third moving blade row, and a fourth moving blade row.
- the orifice 65 limits the flow rate of air flowing through the low pressure bleed line 64.
- the connection line 66 connects the high pressure extraction line 61 and the low pressure extraction line 64.
- the first valve 67 is provided in the connection line 66.
- the bypass line 68 connects the connection line 66 and the low pressure extraction line 64.
- the second valve 69 is provided in the bypass line 68.
- a cooling passage 42 c that communicates with the high-pressure extraction line 61 is formed in the first stage shaft portion 42 a. Further, a cooling passage 44c communicating with the cooling passage 42c of the first stage shaft portion 42a is formed in the plurality of first row blades 44a constituting the first blade row. The cooling passage 44c of the first row blade 44a is opened at a portion in contact with the combustion gas G in the surface of the first row blade 44a.
- the high-pressure compressed air A1 extracted from the first extraction position Pb1 of the compressor 10 serves as the blade cooling air Am, the high-pressure extraction line 61, the cooling passage 42c formed in the first stage shaft portion 42a, the first The gas is discharged into the combustion gas passage 49 through a cooling passage 44c formed in the one row moving blade 44a.
- connection line 66 connects the position on the turbine rotor 41 side of the cooler 62 in the high-pressure extraction line 61 and the position on the second extraction position Pb2 side of the orifice 65 in the low-pressure extraction line 64.
- the bypass line 68 connects the position on the low pressure extraction line 64 side with respect to the first valve 67 in the connection line 66 and the position on the second row stationary blade 54 b side with respect to the orifice 65 in the low pressure extraction line 64.
- the fuel control unit 110 includes a command value related to the generator output, a generator output value detected by the output meter, an intake air temperature Ti of the air sucked by the gas turbine 1, an exhaust temperature of the exhaust gas discharged from the gas turbine 1, and the like. Accordingly, the flow rate of fuel supplied to the combustor 30 is obtained.
- the fuel control unit 110 creates a control signal corresponding to the fuel flow rate, and outputs this control signal to the fuel adjustment valve 36.
- the IGV control unit 120 obtains the IGV opening IGVp according to the command value related to the generator output, the generator output value detected by the output meter, the intake air temperature Ti of the air sucked by the gas turbine 1, and the like.
- the IGV control unit 120 creates a control signal corresponding to the IGV opening IGVp and outputs this control signal to the IGV 21.
- the IGV control unit 120 also outputs the obtained IGV opening IGVp to the first control unit 130 and the second control unit 140.
- the first control unit 130 includes the IGV opening IGVp obtained by the IGV control unit 120, the intake air temperature Ti detected by the intake air thermometer 71, and the disk cavity temperature detected by the disk cavity thermometer 73.
- the valve opening V1p of the first valve 67 is determined according to Td and the temperature Tc of the stationary blade cooling air As detected by the cooling air thermometer 72, and a control signal corresponding to the valve opening V1p is set as the first valve 67. Output to.
- Compressor 10 sucks outside air and compresses it to generate compressed air.
- a part of the compressed air generated by the compressor 10 is ejected into the combustion cylinder 31 via the fuel injector 32 of the combustor 30.
- the fuel F from the fuel injector 32 is injected into the combustion cylinder 31.
- This fuel F burns in the compressed air in the combustion cylinder 31.
- combustion gas G is generated, and this combustion gas G flows from the combustion cylinder 31 into the combustion gas flow path 49 of the turbine 40.
- the turbine rotor 41 rotates.
- the flow rate of the stationary blade cooling air As (component inflow air) supplied to the second row stationary blade 54b (second high temperature component) is controlled by the second valve (S6: second control step).
- the stationary blade cooling air As supplied to the second row stationary blade 54b is heated by heat exchange with the second row stationary blade 54b in the process of passing through the cooling passage 54c of the second row stationary blade 54b, and a part thereof is heated. It is discharged into the combustion gas flow path 49 from the two rows of stationary vanes 54b.
- a part of the air flowing into the disk cavity 59 passes between the inner shroud 56 of the second row stationary blades 54b and the platform 46 of the first row blades 44a, and then the combustion gas flow path 49. Flows in.
- the other part of the air flowing into the disk cavity 59 flows into the combustion gas flow path 49 through the space between the inner shroud 56 of the second row stationary blade 54b and the platform 46 of the second row moving blade 44b.
- the air that has flowed into the disk cavity 59 from the second row stationary blade 54 b flows into the combustion gas flow path 49, so that the high-temperature combustion gas G flowing in the combustion gas flow path 49 is changed into the disk cavity 59. It functions as seal air to prevent inflow.
- the first valve 67 of the cooling system 60 When the first valve 67 of the cooling system 60 is opened in the first control step (S1), the high-pressure compressed air A1 extracted from the first extraction position Pb1 of the compressor 10 and cooled by the cooler 62 is connected via the connection line 66. Then, it flows into the low pressure extraction line 64 and is mixed with the low pressure compressed air A2 in the low pressure extraction line 64. The temperature of the high-pressure compressed air A1 cooled by the cooler 62 is lower than the temperature of the low-pressure compressed air A2 extracted from the second extraction position Pb2. For this reason, in this embodiment, when lowering the temperature of the stationary blade cooling air As supplied to the second row stationary blade 54b, the first valve 67 is opened.
- the first control unit 130 corrects the valve opening degree V1p of the first valve 67 determined as described above according to the intake air temperature Ti. Specifically, when the intake air temperature Ti becomes equal to or higher than a predetermined first intake air temperature Ti1, as shown by the solid line in FIG. A correction coefficient that increases the valve opening degree V1p of the first valve 67 as it increases is obtained. And the 1st control part 130 multiplies this correction coefficient to the valve opening degree V1p of the 1st valve 67 defined as mentioned above, and correct
- the first control unit 130 corrects the valve opening V1p so that the valve opening V1p of the first valve 67 determined as described above increases as the intake air temperature Ti increases.
- the first control unit 130 determines the valve opening degree of the first valve 67 when the disk cavity temperature Td becomes equal to or higher than the first limit temperature Td1 and the IGV opening degree IGVp becomes larger than the second IGV opening degree IGVp2 at the time of high output. As V1p, a valve opening larger than the valve opening within the same range when the disk cavity temperature Td is lower than the first limit temperature Td1 is determined.
- the first control unit 130 obtains the valve opening change amount of the first valve 67 so that the temperature of the stationary blade cooling air As in the low-pressure extraction line 64 detected by the cooling air thermometer 72 becomes the target temperature.
- the target temperature of the stationary blade cooling air As changes according to the intake air temperature Ti, the IGV opening IGVp, and the like. For this reason, the 1st control part 130 calculates
- the first control unit 130 obtains a deviation between the temperature Tc of the stationary blade cooling air As detected by the cooling air thermometer 72 and the target temperature of the stationary blade cooling air As.
- the first control unit 130 obtains a PI control amount that is an opening change amount of the first valve 67 according to the deviation.
- the first control unit 130 responds to the valve opening V1p of the first valve 67 determined as described above according to the deviation between the temperature Tc of the stationary blade cooling air As detected by the cooling air thermometer 72 and its target temperature. The amount of change in the opening degree of the first valve 67 is added, and this result is set as the target valve opening degree V1p of the first valve 67.
- the first control unit 130 creates a control signal corresponding to the target valve opening degree V ⁇ b> 1 p and outputs this control signal to the first valve 67.
- the second-row static air As is cooled to the second-row stationary blade 54b. It can be sent to the wing 54b.
- the flow rate at which the low pressure compressed air A2 extracted from the second extraction position Pb2 of the compressor 10 is supplied as the stationary blade cooling air As to the second row stationary blade 54b through the low pressure extraction line 64 is basically the compressor 10. Depends on the pressure difference between the pressure at the second extraction position Pb2 and the pressure around the second row stationary blade 54b.
- FIG. 7 is used for the change in the pressure difference between the pressure at the second extraction position Pb2 of the compressor 10 and the pressure around the second row stationary blade 54b in accordance with the change in the gas turbine output, in other words, the IGV opening IGVp.
- the horizontal axis indicates the position in the axial direction Da of the gas turbine 1
- the vertical axis indicates the pressure.
- the pressure at the intake position of the compressor 10 and the exhaust position of the turbine 40 is basically atmospheric pressure regardless of the gas turbine output. Further, the pressure at the outlet of the compressor 10 ( ⁇ the inlet of the combustor 30 ⁇ the first extraction position Pb 1) is the highest pressure in the gas turbine 1.
- the compressor outlet ( ⁇ first extraction position Pb1) having the highest pressure in the gas turbine 1 is the same as when the gas turbine output is high.
- the pressure Pmax2 is smaller than the position pressure Pmax1 by a predetermined pressure.
- the pressure at each position on the upstream side Dau from the compressor outlet ( ⁇ first extraction position Pb1) is basically the pressure at the low output at each position compared to the pressure at the high pressure output at each position. It becomes smaller at a rate larger than the decrease rate. More specifically, the pressure increasing tendency is small on the intake side (upstream Dau) of the compressor 10, and the pressure increasing tendency is large on the compressor outlet side.
- the pressure at the compressor outlet ( ⁇ first extraction position Pb1) becomes the aforementioned pressure Pmax2.
- the pressure difference ⁇ P between the pressure at the second extraction position Pb2 and the pressure at the position Pc2 of the second row stationary blade 54b is similar to the above. Becomes smaller. Therefore, even when the intake air temperature Ti is low, the low-pressure compressed air A2 extracted from the second extraction position Pb2 of the compressor 10 is supplied as the stationary blade cooling air As to the second row stationary blade 54b via the low-pressure extraction line 64. The flow rate is smaller than when the intake air temperature Ti is high.
- the low-pressure compressed air A2 extracted from the second extraction position Pb2 of the compressor 10 passes through the low-pressure extraction line 64 and the second row stationary blades 54b.
- the flow rate supplied as the stationary blade cooling air As is reduced. Therefore, when the gas turbine output is low or when the intake air temperature Ti is low, the flow rate required for the stationary blade cooling air As to function as seal air may not be ensured.
- the flow rate of the low-pressure compressed air A2 extracted from the second extraction position Pb2 of the compressor 10 is limited by the orifice 65 in the low-pressure extraction line 64, and then supplied as the stationary blade cooling air As to the second row stationary blade 54b. Is done. Even when the second valve 69 of the cooling system 60 is opened, a part of the low-pressure compressed air A2 extracted from the second extraction position Pb2 of the compressor 10 passes through the orifice 65 and is second than the orifice 65. It is supplied to the second row stationary blade 54b through the low pressure bleed line 64 on the row stationary blade 54b side.
- the second valve 69 of the cooling system 60 when the second valve 69 of the cooling system 60 is opened, the other part of the low-pressure compressed air A2 extracted from the second extraction position Pb2 of the compressor 10 passes through the connection line 66 and the bypass line 68, and is bypassed. 68 is supplied to the second row stationary blades 54b through the low-pressure extraction line 64 on the second row stationary blades 54b side of the connection position with 68. Therefore, by opening the second valve 69, the flow rate of the stationary blade cooling air As supplied to the second row stationary blade 54b can be increased. For this reason, in this embodiment, when increasing the flow rate of the stationary blade cooling air As, the second valve 69 is opened.
- the second control unit 140 determines that the IGV opening IGVp, which is the correlation value of the gas turbine output Po, as shown in FIG.
- the valve opening V2p of the second valve 69 is determined.
- the second control unit 140 sets the valve opening V2p of the second valve 69 as the valve opening V2p when the IGV opening IGVp is larger than the first IGV opening IGVp1 and less than or equal to the second IGV opening IGVp2, and when the output is low.
- the valve opening V2p that becomes “0” is determined by the second IGV opening IGVp2 as the IGV opening IGFVp increases.
- the second control unit 140 determines fully closed “0” as the valve opening degree V2p of the second valve 69.
- the second control unit 140 corrects the valve opening degree V1p of the second valve 69 determined as described above according to the intake air temperature Ti. Specifically, at the time of low output, the second control unit 140, when the intake air temperature Ti is higher than the second intake air temperature Ti2 lower than the first intake air temperature Ti1, as shown in FIG. A correction coefficient indicating closing is obtained. Then, the second control unit 140 multiplies the correction coefficient by the valve opening degree V2p of the second valve 69 determined as described above to correct the valve opening degree V2p. The second control unit 140 obtains a correction coefficient for gradually increasing the valve opening degree V2p as the intake air temperature Ti decreases when the intake air temperature Ti becomes equal to or lower than the second intake air temperature Ti2. Then, the second control unit 140 multiplies the correction coefficient by the valve opening degree V2p of the second valve 69 determined as described above to correct the valve opening degree V2p.
- the second control unit 140 indicates full close when the intake air temperature Ti is higher than the third intake air temperature Ti3 that is lower than the second intake air temperature Ti2, as shown by the solid line in FIG. Find the correction factor. Then, the second control unit 140 multiplies the correction coefficient by the valve opening degree V2p of the second valve 69 determined as described above to correct the valve opening degree V2p. Further, the second control unit 140 obtains a correction coefficient at which the valve opening V2p gradually increases as the intake air temperature Ti decreases when the intake air temperature Ti becomes equal to or lower than the third intake air temperature Ti3. Then, the second control unit 140 multiplies the correction coefficient by the valve opening degree V2p of the second valve 69 determined as described above to correct the valve opening degree V2p.
- the second control unit 140 determines whether the valve opening V2p of the second valve 69 determined as described above increases as the intake air temperature Ti decreases at both low output and high output. V2p is corrected.
- the second control unit 140 changes the IGV opening IGVp from the first IGV opening IGVp1 as shown by the broken line in FIG.
- the valve opening V2p of the second valve 69 decreases as the IGV opening IGVp increases and the disk cavity temperature Td is lower than the first limit temperature Td1.
- a valve opening V2p larger than the valve opening V2p within the same range is determined.
- the second control unit 140 when the disk cavity temperature Td is higher than the first limit temperature Td1 and the intake air temperature Ti is lower than or equal to the third intake air temperature Ti3 at the time of high output, the intake air temperature from the constant valve opening V2p. A correction coefficient that increases the valve opening V2p of the second valve 69 as Ti decreases is obtained. Then, the second control unit 140 multiplies the correction coefficient by the valve opening degree V2p of the second valve 69 determined as described above to correct the valve opening degree V2p.
- the second control unit 140 creates a control signal corresponding to the valve opening V2p of the second valve 69 determined as described above, unless the disk cavity temperature Td becomes equal to or higher than the third limit temperature Td3. Output to the second valve 69.
- valve opening degree V2p of the second valve 69 becomes larger, so that the flow rate of air flowing through the bypass line 68 increases. For this reason, the flow rate of the stationary blade cooling air As supplied from the low pressure extraction line 64 to the second row stationary blade 54b increases, and the temperature rise of the second row stationary blade 54b can be suppressed.
- the gas turbine output is low, that is, when the IGV opening IGVp is equal to or less than the first IGV opening IGVp1, as shown in the column for when the gas turbine output is low output in FIG.
- the first valve 67 provided in the line 66 is basically fully closed.
- the low-pressure compressed air A2 extracted from the second extraction position Pb2 of the compressor 10 flows through the low-pressure extraction line 64 provided with the orifice 65 that restricts the flow rate, and also flows into the bypass line 68.
- the temperature of the low-pressure compressed air A2 extracted from the second extraction position Pb2 is higher than that when the gas turbine output is low. high.
- the intake air temperature Ti is low, even when the gas turbine output is high, the temperature of the low-pressure compressed air A2 extracted from the second extraction position Pb2 is lower than when the intake air temperature Ti is high. Therefore, if the low-pressure compressed air A2 from the second extraction position Pb2 is supplied to the second row stationary blade 54b as the stationary blade cooling air As, the second row stationary blade 54b is basically cooled below the target temperature. It is not necessary to send the high-pressure compressed air A1 cooled by the cooler 62 to the low-pressure extraction line 64.
- the gas turbine output is high, that is, when the IGV opening IGVp is larger than the first IGV opening IGVp1, as described above, the pressure at the second extraction position Pb2 of the compressor 10 and the surroundings of the second row stationary blades 54b The pressure difference from the pressure increases.
- the intake air temperature Ti is low, the pressure difference between the pressure at the second extraction position Pb2 of the compressor 10 and the pressure around the second row stationary blade 54b becomes small.
- the low-pressure compressed air A2 extracted from the second extraction position Pb2 passes through only the low-pressure extraction line 64 and is cooled to the second row stationary blade 54b.
- the flow rate supplied as air cannot secure the required flow rate as seal air.
- the first valve 67 is fully closed, and the second valve 69 is slightly opened according to the intake air temperature Ti.
- the first valve 67 is opened and the second valve 69 is further opened. Open.
- the temperature of the low-pressure compressed air A2 extracted from the second extraction position Pb2 is higher than when the intake air temperature Ti is low.
- the gas turbine output is low, even if the intake temperature Ti is high, the temperature of the low-pressure compressed air A2 extracted from the second extraction position Pb2 is high when the gas turbine output is high and the intake temperature Ti is high. Low compared to Therefore, if the low-pressure compressed air A2 from the second extraction position Pb2 is supplied to the second row stationary blade 54b as the stationary blade cooling air As, the second row stationary blade 54b is basically cooled below the target temperature. It is not necessary to send the high-pressure compressed air A1 cooled by the cooler 62 to the low-pressure extraction line 64.
- the intake air temperature Ti is high, as described above, the pressure difference between the pressure at the second extraction position Pb2 of the compressor 10 and the pressure around the second row stationary blade 54b increases. For this reason, when the intake air temperature Ti is high, the low-pressure compressed air A2 extracted from the second extraction position Pb2 passes through only the low-pressure extraction line 64 and is supplied at a flow rate as the stationary blade cooling air As to the second row stationary blade 54b. The required flow rate as sealing air can be secured.
- the temperature of the low-pressure compressed air A2 extracted from the second extraction position Pb2 is high and the intake air temperature Ti is low.
- the temperature Ti is high, the temperature is higher than at any time when the intake air temperature Ti is low at a low output.
- the low-pressure compressed air A2 extracted from the second extraction position Pb2 passes through only the low-pressure extraction line 64 to the second row stationary blade 54b and the stationary blade cooling air. With the flow rate supplied as As, the required flow rate as sealing air can be secured.
- the first valve 67 is opened and the second valve 69 is fully closed.
- the first valve 67 is further opened and the second valve 69 is opened. Open.
- the first control unit 130 determines the temperature Tc of the stationary blade cooling air As detected by the cooling air thermometer 72 and the target temperature of the stationary blade cooling air As.
- the valve opening degree V1p of the first valve 67 is controlled in accordance with the deviation. For this reason, in any of the four forms shown in FIG. 8, the valve opening degree V1p of the first valve 67 may be larger than the valve opening degree V1p of the first valve 67 illustrated in FIG. .
- the second row stationary blades are adjusted by adjusting the valve opening V1p of the first valve 67 in the connection line 66 and the valve opening V2p of the second valve 69 in the bypass line 68.
- the temperature and flow rate of the stationary blade cooling air As supplied to 54b can be controlled.
- the high pressure compressed air A1 extracted from the first extraction position Pb1 and cooled by the cooler 62 is flowed to the low pressure extraction line 64 via the connection line 66, thereby cooling into the low pressure extraction line 64. Even if a vessel is not provided, the second row stationary blades 54b can be suppressed to a target temperature or lower.
- A2 can be supplied to the second row stationary blade 54b as the stationary blade cooling air As.
- the flow rate of the low-pressure compressed air A2 flowing through the low-pressure bleed line 64 is limited by the orifice 65.
- the stationary blade cooling air As can be appropriately supplied to the second row stationary blade 54b that is the second high-temperature component.
- an orifice is exemplified as a minimum flow rate securing device that secures the minimum flow rate of air flowing through the low pressure extraction line 64 while restricting the flow rate of the low pressure compressed air A2 flowing through the low pressure extraction line 64.
- a minimum flow rate securing device in addition to an orifice, a device having a flow restrictor such as a flow nozzle or a venturi tube, a valve having a mechanism capable of securing a minimum flow rate, or the like can be used.
- a mechanism that can ensure the minimum flow rate a mechanism that mechanically prevents full closure, a mechanism that previously provides a hole in a member that closes the flow path, and the like can be used.
- the cooling system 60a of the present embodiment includes a high pressure bleed line 61, a cooler 62, a low pressure bleed line 64, a connection line 66, a first valve 67, a second valve 69, An intake thermometer 71, a cooling air thermometer 72, a disk cavity thermometer 73, a first controller 130a, and a second controller 140a are provided.
- the cooling system 60a of this embodiment does not have the orifice 65 and the bypass line 68 in the cooling system 60 of the first embodiment. For this reason, the second valve 69 is provided in the low pressure extraction line 64.
- the second valve 69 is provided in the low-pressure extraction line 64 and between the connection position with the connection line 66 and the cooling air thermometer 72.
- the cooling air thermometer 72 is provided in the low pressure extraction line 64 and between the connection position with the connection line 66 and the second row stationary blade 54b.
- the first control unit 130 a controls the valve opening degree of the first valve 67.
- the second controller 140 a controls the valve opening degree of the second valve 69.
- the first control unit 130a and the second control unit 140a of the present embodiment also form part of the functional configuration of the control device 100a. Similar to the control device 100 of the first embodiment, the control device 100a includes a fuel control unit 110 and an IGV control unit 120 in addition to the first control unit 130a and the second control unit 140a.
- the high pressure extraction step (S1), the cooling step (S2), the low pressure extraction step (S3), the first control step (S4), the mixing step (S5), and the second control. Step (S6) is performed.
- the operation of the first control unit 130a in the first control step (S4) and the operation of the second control unit 140a in the second control step (S6) are slightly different from those in the first embodiment.
- the first valve 67 of the cooling system 60a is opened in the first control step (S1), the high-pressure compressed air extracted from the first extraction position Pb1 of the compressor 10 and cooled by the cooler 62 is used.
- A1 flows into the low pressure bleed line 64 via the connection line 66 and mixes with the low pressure compressed air A2 in the low pressure bleed line 64.
- the first control step (S1) when the gas turbine output Po is low, the high pressure compressed air A1 after being cooled by the cooler 62 is mixed into the low pressure compressed air A1.
- the pressure of the stationary blade cooling air As (component inflow air) in which the high pressure compressed air A1 is mixed into the low pressure compressed air A1 is increased, and the stationary blade cooling air As (component inflow air) when the gas turbine output Po is low is output. A decrease in flow rate can be suppressed.
- the first control unit 130a sets the IGV opening IGVp, which is a correlation value of the gas turbine output Po, to the second IGV opening IGVp2 (gas turbine output Po2).
- the valve opening degree V1p of the first valve 67 is determined to be fully closed or close to full closing.
- the first control unit 130a determines the opened valve opening as the valve opening V1p of the first valve 67.
- the first control unit 130a has a first IGV opening IGVp within a range from the second IGV opening IGVp2 (gas turbine output Po2) to the first IGV opening IGVp1 (gas turbine output Po1).
- a valve opening degree that gradually increases as the IGV opening degree IGVp decreases is determined.
- the first control unit 130a determines a valve opening that gradually decreases as the IGV opening IGVp increases as the valve opening V1p of the first valve 67.
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Abstract
Description
本願は、2015年1月30日に、日本国に出願された特願2015-016717号に基づき優先権を主張し、この内容をここに援用する。
本発明に係るガスタービン設備の第一実施形態について、図1~図9を参照して説明する。
本発明に係るガスタービン設備の第二実施形態について、図10~図12を参照して説明する。
上記実施形態では、ガスタービン出力に相関する出力相関値として、IGV制御部120が求めたIGV開度IGVpを用いている。しかしながら、IGV21の可動翼22の開度を検知する開度検知器を設け、この開度検知計で検知されたIGV開度IGVpを出力相関値として用いてよい。
Claims (20)
- 空気を圧縮する圧縮機と、前記圧縮機で圧縮された空気中で燃料を燃焼させて燃焼ガスを生成する燃焼器と、前記燃焼ガスにより駆動するタービンと、を備えているガスタービンの冷却系統において、
前記圧縮機の第一抽気位置から空気を抽気して、前記ガスタービンを構成する部品のうちで前記燃焼ガスに接する第一高温部品に、前記第一抽気位置から抽気した空気を送る高圧抽気ラインと、
前記高圧抽気ラインを通る空気を冷却する冷却器と、
前記第一抽気位置から抽気される空気よりも低圧の空気を前記圧縮機の第二抽気位置から抽気して、前記ガスタービンを構成する部品のうちで前記燃焼ガスに接し且つ前記第一高温部品よりも低圧環境下に配置されている第二高温部品に、前記第二抽気位置から抽気した空気を送る低圧抽気ラインと、
前記低圧抽気ラインを流れる空気の流量を制限しつつ、前記低圧抽気ラインを流れる空気の最低流量を確保する最低流量確保器と、
前記高圧抽気ライン中で前記冷却器よりも前記第一高温部品側の位置と、前記低圧抽気ライン中で前記最低流量確保器よりも前記第二抽気位置側の位置とを接続する接続ラインと、
前記接続ラインに設けられている第一弁と、
前記接続ライン中で前記第一弁よりも前記低圧抽気ライン側の位置と、前記低圧抽気ライン中で前記最低流量確保器よりも前記第二高温部品側の位置とを接続するバイパスラインと、
前記バイパスラインに設けられている第二弁と、
を備えているガスタービンの冷却系統。 - 請求項1に記載のガスタービンの冷却系統において、
前記第一弁の弁開度を制御する第一制御部と、
前記第二弁の弁開度を制御する第二制御部と、
を備え、
前記第一制御部は、前記圧縮機が吸い込む空気の温度である吸気温度と、ガスタービン出力又は前記ガスタービン出力に相関する値である出力相関値とのうち、少なくとも一方のパラメータ値に基づいて前記第一弁の弁開度を制御し、
前記第二制御部は、前記パラメータ値に基づいて前記第二弁の弁開度を制御する、
ガスタービンの冷却系統。 - 空気を圧縮する圧縮機と、前記圧縮機で圧縮された空気中で燃料を燃焼させて燃焼ガスを生成する燃焼器と、前記燃焼ガスにより駆動するタービンと、を備えているガスタービンの冷却系統において、
前記圧縮機の第一抽気位置から空気を抽気して、前記ガスタービンを構成する部品のうちで前記燃焼ガスに接する第一高温部品に、前記第一抽気位置から抽気した空気を送る高圧抽気ラインと、
前記高圧抽気ラインを通る空気を冷却する冷却器と、
前記第一抽気位置から抽気される空気よりも低圧の空気を前記圧縮機の第二抽気位置から抽気して、前記ガスタービンを構成する部品のうちで前記燃焼ガスに接し且つ前記第一高温部品よりも低圧環境下に配置されている第二高温部品に、前記第二抽気位置から抽気した空気を送る低圧抽気ラインと、
前記高圧抽気ライン中で前記冷却器よりも前記第一高温部品側の位置と、前記低圧抽気ラインとを接続する接続ラインと、
前記接続ラインに設けられている第一弁と、
前記高温抽気ライン中で、前記接続ラインとの接続位置よりも前記第一高温部品側の位置に設けられている第二弁と、
前記第一弁の弁開度を制御する第一制御部と、
前記第二弁の弁開度を制御する第二制御部と、
を備え、
前記第一制御部は、前記圧縮機が吸い込む空気の温度である吸気温度と、ガスタービン出力又は前記ガスタービン出力に相関する値である出力相関値とのうち、少なくとも一方のパラメータ値に基づいて前記第一弁の弁開度を制御し、
前記第二制御部は、前記パラメータ値に基づいて前記第二弁の弁開度を制御する、
ガスタービンの冷却系統。 - 請求項2又は3に記載のガスタービンの冷却系統において、
前記パラメータ値には、前記吸気温度が含まれ、
前記第一制御部は、前記吸気温度が所定温度以上になると、前記吸気温度が前記所定温度よりも小さい値のときの前記第一弁の弁開度以上の弁開度に応じた制御信号を前記第一弁に出力する、
ガスタービンの冷却系統。 - 請求項4に記載のガスタービンの冷却系統において、
前記第一制御部は、前記第二高温部品の近傍における温度を受け付け、前記温度が予め定められた温度以上になると、開いた弁開度に応じた制御信号を前記第一弁に出力する、
ガスタービンの冷却系統。 - 請求項2から5のいずれか一項に記載のガスタービンの冷却系統において、
前記パラメータ値には、前記出力相関値が含まれ、
前記第一制御部は、前記出力相関値が所定相関値以上になると、前記出力相関値が前記所定相関値よりも小さい値のときの前記第一弁の弁開度以上の弁開度に応じた制御信号を前記第一弁に出力する、
ガスタービンの冷却系統。 - 請求項2から5のいずれか一項に記載のガスタービンの冷却系統において、
前記パラメータ値には、前記出力相関値が含まれ、
前記第一制御部は、前記出力相関値が所定相関値以下になると、前記出力相関値が該所定相関値よりも大きい値のときの前記第一弁の弁開度以上の弁開度に応じた制御信号を前記第一弁に出力する、
ガスタービンの冷却系統。 - 請求項2から7のいずれか一項に記載のガスタービンの冷却系統において、
前記パラメータ値には、前記吸気温度が含まれ、
前記第二制御部は、前記吸気温度が所定温度以下になると、前記吸気温度が前記所定温度よりも大きい値のときの前記第二弁の弁開度以上の弁開度に応じた制御信号を前記第二弁に出力する、
ガスタービンの冷却系統。 - 請求項8に記載のガスタービンの冷却系統において、
前記第二制御部は、前記吸気温度が前記所定温度である第一温度と前記第一温度よりも高い第二温度との間の温度になると、前記吸気温度の変化に関わらず一定の弁開度に応じた制御信号を前記第二弁に出力し、前記吸気温度が前記第二温度以上になると、前記吸気温度が前記第二温度よりも小さい値のときの前記第二弁の弁開度以下の弁開度に応じた制御信号を前記第二弁に出力する、
ガスタービンの冷却系統。 - 請求項8又は9に記載のガスタービンの冷却系統において、
前記第二制御部は、前記第二高温部品の近傍における温度を受け付け、前記温度が予め定められた温度以上になると、開いた弁開度に応じた制御信号を前記第二弁に出力する、
ガスタービンの冷却系統。 - 請求項2から10のいずれか一項に記載のガスタービンの冷却系統において、
前記パラメータ値には、前記出力相関値が含まれ、
前記第二制御部は、前記出力相関値が所定相関値以下になると、前記出力相関値が前記所定相関値よりも大きい値のときの前記第二弁の弁開度以上の弁開度に応じた制御信号を前記第二弁に出力する、
ガスタービンの冷却系統。 - 請求項1から11のいずれか一項に記載のガスタービンの冷却系統において、
前記低圧抽気ラインは、前記第二高温部品としての前記タービンの静翼に接続されている、
ガスタービンの冷却系統。 - 請求項1から12のいずれか一項に記載のガスタービンの冷却系統と、
前記ガスタービンと、
を備えているガスタービン設備。 - 空気を圧縮する圧縮機と、前記圧縮機で圧縮された空気中で燃料を燃焼させて燃焼ガスを生成する燃焼器と、前記燃焼ガスにより駆動するタービンと、を備えているガスタービンの部品冷却方法において、
前記圧縮機の第一抽気位置からの空気を第一空気として抽気し、前記ガスタービンを構成する部品のうちで前記燃焼ガスに接する第一高温部品に、前記第一空気を送る高圧抽気工程と、
前記高圧抽気工程で前記第一高温部品に送られる前記第一空気を冷却する冷却工程と、
前記第一空気よりも低圧の第二空気を前記圧縮機の第二抽気位置から抽気して、前記ガスタービンを構成する部品のうちで前記燃焼ガスに接し且つ前記第一高温部品よりも低圧環境下に配置されている第二高温部品に、前記第二空気を送る低圧抽気工程と、
前記第二高温部品に送られる前記第二空気中に、前記冷却工程で冷却された前記第一空気を混入させる混入工程と、
第一弁の弁開度を制御することで、前記第二空気中に混入させる前記第一空気の流量を制御する第一制御工程と、
第二弁の弁開度を制御することで、前記第一制御工程により流量制御されて前記第二空気中に混入する又は混入した前記第一空気と、前記第二空気と、を併せた空気である部品流入空気の流量を制御する第二制御工程と、
を実行し、
前記第一制御工程では、前記圧縮機が吸い込む空気の温度である吸気温度と、ガスタービン出力又は前記ガスタービン出力に相関する値である出力相関値とのうち、少なくとも一方のパラメータ値に基づいて、前記第二空気中に混入させる前記第一空気の流量を制御し、
前記第二制御工程では、前記パラメータ値に基づいて、前記部品流入空気の流量を制御する、
ガスタービンの部品冷却方法。 - 請求項14に記載のガスタービンの部品冷却方法において、
前記パラメータ値には、前記吸気温度が含まれ、
前記第一制御工程では、前記吸気温度が所定温度以上になると、前記吸気温度が前記所定温度よりも小さい値のときの前記第一弁の弁開度以上の弁開度に応じた制御信号を前記第一弁に出力する、
ガスタービンの部品冷却方法。 - 請求項15に記載のガスタービンの部品冷却方法において、
前記パラメータ値には、前記出力相関値が含まれ、
前記第一制御工程では、前記出力相関値が所定相関値以上になると、前記出力相関値が前記所定相関値よりも小さい値のときの前記第一弁の弁開度以上の弁開度に応じた制御信号を前記第一弁に出力する、
ガスタービンの部品冷却方法。 - 請求項15に記載のガスタービンの部品冷却方法において、
前記パラメータ値には、前記出力相関値が含まれ、
前記第一制御工程では、前記出力相関値が所定相関値以下になると、前記出力相関値が該所定相関値よりも大きい値のときの前記第一弁の弁開度以上の弁開度に応じた制御信号を前記第一弁に出力する、
ガスタービンの部品冷却方法。 - 請求項15から17のいずれか一項に記載のガスタービンの部品冷却方法において、
前記パラメータ値には、前記吸気温度が含まれ、
前記第二制御工程では、前記吸気温度が所定温度以下になると、前記吸気温度が前記所定温度よりも大きい値のときの前記第二弁の弁開度以上の弁開度に応じた制御信号を前記第二弁に出力する、
ガスタービンの部品冷却方法。 - 請求項18に記載のガスタービンの部品冷却方法において、
前記第二制御工程では、前記吸気温度が前記所定温度である第一温度と前記第一温度よりも高い第二温度との間の温度になると、前記吸気温度の変化に関わらず一定の弁開度に応じた制御信号を前記第二弁に出力し、前記吸気温度が前記第二温度以上になると、前記吸気温度が前記第二温度よりも小さい値のときの前記第二弁の弁開度以下の弁開度に応じた制御信号を前記第二弁に出力する、
ガスタービンの部品冷却方法。 - 請求項15から19のいずれか一項に記載のガスタービンの部品冷却方法において、
前記パラメータ値には、前記出力相関値が含まれ、
前記第二制御工程では、前記出力相関値が所定相関値以下になると、前記出力相関値が前記所定相関値よりも大きい値のときの前記第二弁の弁開度以上の弁開度に応じた制御信号を前記第二弁に出力する、
ガスタービンの部品冷却方法。
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US15/545,072 US10634058B2 (en) | 2015-01-30 | 2016-01-25 | Cooling system for gas turbine, gas turbine equipment provided with same, and parts cooling method for gas turbine |
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KR1020177020809A KR101933819B1 (ko) | 2015-01-30 | 2016-01-25 | 가스 터빈의 냉각 계통, 이것을 구비하고 있는 가스 터빈 설비, 및 가스 터빈의 부품 냉각 방법 |
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