WO2015119135A1 - ガスタービンの制御装置、ガスタービン、及びガスタービンの制御方法 - Google Patents
ガスタービンの制御装置、ガスタービン、及びガスタービンの制御方法 Download PDFInfo
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- WO2015119135A1 WO2015119135A1 PCT/JP2015/053057 JP2015053057W WO2015119135A1 WO 2015119135 A1 WO2015119135 A1 WO 2015119135A1 JP 2015053057 W JP2015053057 W JP 2015053057W WO 2015119135 A1 WO2015119135 A1 WO 2015119135A1
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- igv
- gas turbine
- turbine
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- inlet guide
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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
- F02C9/48—Control of fuel supply conjointly with another control of the plant
- F02C9/50—Control of fuel supply conjointly with another control of the plant with control of working fluid flow
- F02C9/54—Control of fuel supply conjointly with another control of the plant with control of working fluid flow by throttling the working fluid, by adjusting vanes
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- 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
-
- 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
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
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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
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
- F02C9/22—Control of working fluid flow by throttling; by adjusting vanes by adjusting turbine vanes
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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
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/18—Structural association of electric generators with mechanical driving motors, e.g. with turbines
- H02K7/1807—Rotary generators
- H02K7/1823—Rotary generators structurally associated with turbines or similar engines
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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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/05—Purpose of the control system to affect the output of the engine
- F05D2270/053—Explicitly mentioned power
-
- 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
- F05D2270/06—Purpose of the control system to match engine to driven device
- F05D2270/061—Purpose of the control system to match engine to driven device in particular the electrical frequency of driven generator
-
- 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
- F05D2270/306—Mass flow
- F05D2270/3061—Mass flow of the working fluid
Definitions
- the present invention relates to a gas turbine control device, a gas turbine, and a gas turbine control method.
- a gas turbine used in a power plant or the like injects fuel into air compressed in a compressor and burns it, and guides a high-temperature and high-pressure combustion gas obtained as a result to the turbine to extract output.
- FIG. 11 shows a basic configuration of this gas turbine.
- the gas turbine 100 includes a compressor 102, a combustor 103, and a turbine 101.
- the combustor 103 is supplied with air compressed by the compressor 102 and fuel gas whose flow rate is adjusted by a fuel flow rate adjustment valve 105 whose opening degree is adjusted according to the load.
- the combustor 103 the combusted high-temperature combustion gas is supplied to the turbine 101 and expands to drive the turbine 101.
- This driving force is transmitted to the generator 150 to generate power, and is transmitted to the compressor 102 to drive the compressor.
- the rotating shafts of the gas turbine 100, the generator 150, and the steam turbine 160 are coupled together.
- an inlet guide vane (InletVGuide Vane: IGV) 104 is provided in front of the first stage blade of the compressor 102.
- the inlet guide vane 104 changes the amount of air flowing between the moving blades of the compressor 102 and flowing into the combustor 103 by manipulating the opening degree of the guide vane at the compressor inlet. This is for controlling the exhaust gas temperature to a target value.
- the intake air is given a circumferential speed by the inlet guide vanes 104 and introduced into the compressor 102. In the compressor 102, energy is given to the introduced air through multistage moving blades and stationary blades, and the pressure rises.
- the inlet guide vanes 104 are configured such that a large number of movable vanes provided in the circumferential direction are movably supported, and an actuator is actuated by a drive signal from the operation control device 110 to move these movable vanes.
- the intake flow rate and combustion temperature are adjusted.
- the operation control device 110 has a configuration as shown in FIG. 12 in order to generate an IGV opening command to the actuator of the inlet guide vane 104. That is, the configuration includes a multiplier 11, a table function unit (FX1) 12, a limiter 13, a correction function unit (FX2) 14, and a limit function unit (FX3) 15. Basically, the IGV opening is set according to a function as shown in FIG. 13A in accordance with the generator output (GT output). Then, the correction function unit (FX2) 14 generates a GT output correction coefficient K2 based on the relationship corresponding to the compressor inlet temperature as shown in FIG. 13B, and the multiplier 11 outputs this correction coefficient K2 to the GT output.
- GT output generator output
- the limit function unit (FX3) 15 generates the IGV maximum opening M1 based on the relationship corresponding to the compressor inlet temperature as shown in FIG. 13C, and the limiter 13 generates the table function unit (FX1) 12. Is limited so that the IGV opening generated in step S1 does not exceed the IGV maximum opening M1.
- Patent Literature 1 and Patent Literature 2 are disclosed as prior arts for performing operation control corresponding to frequency fluctuations in this way.
- Patent Document 1 discloses a technique for switching to control based on recovery of a system frequency that is different from normal control when an abnormality in the system frequency is detected.
- Patent Document 2 discloses a governor-free control method for adjusting the rate of change of the system frequency to be within the limit.
- the gas turbine 100 increases the fuel with respect to the load increase according to the settling rate when the frequency is decreased due to the partial load or against the load increase command, while the combustion temperature (turbine inlet temperature) is increased. Since the temperature control operation is performed from the viewpoint of equipment protection such as equipment damage due to the rise of), there is a concern that a desired load cannot be obtained.
- the Grid Code request response for the shaft output shown in FIG. 14C may not be satisfied.
- the increase in the output (ST output) of the steam turbine 160 is delayed as shown in FIG.
- the present invention has been made in view of such circumstances, and is capable of increasing output without increasing the turbine inlet temperature, regardless of the operation state of the gas turbine, and a gas turbine control device. And it aims at providing the control method of a gas turbine.
- the gas turbine control device, gas turbine, and gas turbine control method of the present invention employ the following means.
- a gas turbine control apparatus supplies compressed air and fuel from a compressor having an inlet guide vane in a front stage to a combustor and rotates the turbine by combustion gas generated in the combustor.
- the IGV advance opening is performed.
- IGV control flag generating means for making the flag effective
- inlet guide blade opening setting means for setting the opening of the inlet guide blade to be opened as compared with the previous opening when the IGV preceding opening flag is effective Prepare.
- the IGV control flag generation means enables the IGV advance opening flag.
- the opening degree of the inlet guide vane is set by the inlet guide vane opening degree setting means so that the opening degree of the inlet guide vane is opened as compared with that.
- the turbine inlet temperature is proportional to the fuel / air ratio (fuel ratio / combustion air ratio)
- fuel / air ratio fuel ratio / combustion air ratio
- turbine inlet temperature decreases.
- turbine output turbine passage flow rate ⁇ turbine heat drop ⁇ efficiency
- the IGV control flag generation means may enable the IGV advance open flag when the system frequency is equal to or lower than a predetermined threshold value or when the output increase of the gas turbine is requested.
- the output can be increased without increasing the turbine inlet temperature regardless of the operating state of the gas turbine.
- the inlet guide vane opening degree setting means is configured such that the rate of change of the inlet guide vane opening degree is set so that the increase in turbine output is faster than the increase in compressor power. Also good.
- the temperature control means for setting the temperature adjustment according to the passenger compartment pressure is provided, and the temperature control means changes the opening degree of the inlet guide vane when the IGV advance open flag is valid.
- the followability of the exhaust gas temperature setting value or the blade path temperature setting value can be accelerated, and the temperature setting can be released in a transient manner, so that the load responsiveness to fluctuations in the system frequency can be improved.
- the temperature control means for setting the temperature adjustment according to the cabin pressure, and the temperature control means has a deviation between the target value based on the temperature adjustment setting and the measured blade path temperature or exhaust gas temperature.
- PI control means for generating a blade path temperature set value or an exhaust gas temperature set value of the turbine by performing proportional integral control based on the IGV, and when the IGV advance open flag is valid, control parameters in the PI control means are It may be set to a preset value.
- the temperature control means for setting the temperature adjustment according to the cabin pressure is provided, and the temperature control means changes the opening degree of the inlet guide blade when the IGV advance open flag is valid.
- a second correction unit that calculates a correction amount according to the rate of change by calculating a rate and corrects the blade path temperature setting value or the exhaust gas temperature setting value of the turbine generated based on the temperature control setting; Good.
- the blade path temperature setting value or the exhaust gas temperature setting value can be directly preceded, the follow-up performance can be accelerated, the temperature setting can be released in a transient manner, and the load response to fluctuations in the system frequency can be increased. Can be improved.
- the IGV control flag generation means may invalidate the IGV preceding opening flag with a certain delay when the IGV preceding opening flag switches from valid to invalid.
- the fuel flow rate may be increased according to the opening degree of the inlet guide vane when the IGV preceding opening flag is validated.
- the fuel flow rate can be increased in accordance with the increase in the air flow rate due to the opening of the inlet guide vanes becoming open, so that an excessive decrease in the turbine inlet temperature can be prevented.
- a gas turbine includes a compressor including an inlet guide vane in a front stage, a combustor that is supplied with compressed air and fuel from the compressor, and generates combustion gas, and the combustor.
- a turbine that is rotated by the generated combustion gas, a generator that is driven by the rotation of the turbine, and the control device described above are provided.
- compressed air and fuel from a compressor having an inlet guide vane in the preceding stage are supplied to the combustor, and the turbine is rotated by the combustion gas generated in the combustor.
- a gas turbine control method for driving a generator to increase an output of the gas turbine, and an IGV control flag valid step for validating an IGV advance open flag, and the IGV advance open flag is valid there is an inlet guide vane opening degree setting step for setting the opening degree of the inlet guide vane to be larger than before.
- FIG. 1 is a configuration diagram of a gas turbine according to a first embodiment of the present invention. It is a block diagram of the IGV control flag production
- FIG. 1 is a configuration diagram of a gas turbine 100 according to the first embodiment.
- a gas turbine 100 includes a compressor 102, a combustor 103, and a turbine 101.
- the air compressed by the compressor 102 and the fuel whose flow rate is adjusted by the fuel flow rate adjustment valve 105 are supplied to the combustor 103, where they are mixed and burned to generate high-pressure combustion gas.
- the high-temperature combustion gas is supplied to the turbine 101, and drives the turbine 101 by expanding. This driving force is transmitted to the generator 150 to generate power, and is transmitted to the compressor 102 to drive the compressor 102.
- the fuel flow rate adjustment valve 105 is actuated by a control signal 118 from the fuel control unit 112 of the operation control device 110.
- the fuel flow rate adjusting valve 105 adjusts the load and further the exhaust gas temperature by controlling the fuel flow rate of the fuel gas as described above.
- the rotating shafts of the gas turbine 100, the generator 150, and the steam turbine 160 are coupled together.
- An inlet guide vane (Inlet Guide Vane: IGV) 104 is provided on the front side of the first stage blade of the compressor 102.
- the intake air is given a circumferential speed by the inlet guide vanes 104 and introduced into the compressor 102.
- the inlet guide vanes 104 are configured such that a large number of movable vanes provided in the circumferential direction are rotatably supported, and the inlet guide vanes 104 are controlled by an IGV opening command from the IGV control unit 113 of the operation control device 110. These actuators are actuated to move these movable blades to adjust the intake air flow rate and the combustion temperature.
- a blade path temperature detector 123 that detects the temperature of the gas that has passed through the blades of the final stage is provided at the final stage of the turbine 101. Further, an exhaust gas temperature detector 124 for detecting the temperature of the exhaust gas is provided in the exhaust passage downstream of the position where the blade path temperature detector 123 is disposed. In addition, an intake air condition detector 121 that detects the intake air condition is provided to detect the intake air temperature and the intake air pressure. The pressure in the passenger compartment of the combustor 103 is detected by the passenger compartment pressure sensor 122. Furthermore, a generator output sensor (not shown) is provided to detect the load state of the turbine 101.
- the detection signals detected by the blade path temperature detector 123, the exhaust gas temperature detector 124, the intake air state detector 121, the vehicle interior pressure sensor 122, and the generator output sensor are input to the operation control device 110.
- the operation control device 110 includes a fuel control unit 112 that performs fuel supply control, a temperature control unit 114 that performs blade path temperature control and exhaust gas temperature control, and an IGV control unit 113 that performs opening degree control of the inlet guide vanes 104. And an IGV control flag generation unit 115 that generates an IGV preceding opening flag (IGV preceding opening signal).
- FIG. 2 is a configuration diagram of the IGV control flag generation unit 115.
- the IGV control flag generation unit 115 validates the IGV preceding open flag when increasing the output of the gas turbine 100. For example, the IGV control flag generation unit 115 receives a low frequency signal when the system frequency is equal to or lower than the predetermined threshold value ⁇ , or when an output increase request signal that requests an increase in the output of the gas turbine 100 is input.
- the IGV preceding open flag is generated as valid by the OR gate 3.
- the gas turbine 100 increases the output in order to increase the system frequency.
- the IGV control unit 113 is configured as shown in FIG.
- the multiplier 11, the table function unit (FX1) 12, the limiter 13, the correction function unit (FX2) 14, and the limit function unit (FX3) 15 have the same configuration as that of the conventional one (see FIG. 12).
- a configuration in which an addition amount based on the IGV preceding opening flag is added to the conventional IGV opening command and a configuration in which the rate of change of the IGV opening is limited are added. ing.
- the value of the GT output is input to the multiplier 11 via the filter 10.
- the signal generators (SG1) 17 and (SG2) 18 are switched by the signal switcher 19 in accordance with the IGV advance open flag, and the IGV in the normal operation by the adder 16 via the rate limiter 20. It is added to the opening command.
- the opening degree of the inlet guide vane 104 is set so as to be opened as compared to that. For example, when “0” is set in the signal generator (SG1) 17 and a predetermined value is set in the signal generator (SG2) 18, and the IGV advance open flag becomes valid, the IGV opening command during normal operation is set. Is added with a predetermined value of the signal generator (SG2) 18 so that the opening of the inlet guide vane 104 is opened more than usual.
- limits the change rate of IGV opening degree switches signal generator (SG3) 23 and (SG4) 24 with the signal switcher 25 according to a load cutoff flag, and supplies this to the change rate limiter 21
- the change rate limit value of the IGV opening is changed.
- the signal generator (SG3) 23 has a normal rate of change limit value (for example, 400 [% / min])
- the signal generator (SG4) 24 has a rate of change limit value at the time of load interruption ( For example, 3000 [% / min]) is set.
- the operation control device 110 of the gas turbine 100 When the gas turbine 100 is operated at a partial load and the system frequency is equal to or less than the predetermined threshold value ⁇ , or when the gas turbine 100 is operated at a partial load, an increase in the output of the gas turbine 100 is requested.
- the IGV control flag generation unit 115 validates the IGV advance open flag.
- the opening degree of the inlet guide vane 104 is set so as to be opened compared to that so far, and the opening degree of the inlet guide vane 104 is slightly open compared to the normal.
- the turbine inlet temperature is proportional to the fuel-air ratio (fuel amount / combustion air amount ratio)
- the fuel-air ratio that is, the turbine inlet temperature decreases. That is, when the IGV preceding opening flag is validated, the inlet guide vanes 104 are opened more easily than the normal setting, so that the intake air flow rate of the compressor 102 increases from the normal setting.
- the gas turbine 100 can be operated with a lower turbine inlet temperature than usual, so that the turbine output can be increased by increasing the air volume.
- the opening degree of the inlet guide vanes 104 is increased by 10 to 20%, and the air volume is increased by 5% to 10% from the rated flow rate.
- turbine output turbine passage flow rate ⁇ turbine heat drop ⁇ efficiency
- the inlet guide vanes 104 When the inlet guide vanes 104 are opened, the intake air flow rate of the compressor 102 increases, so that the power of the compressor 102 increases. Therefore, as shown in the example of FIG. 4, when the inlet guide vanes 104 are sharply opened, the power of the compressor 102 increases faster than the increase in turbine output, and as a result, the GT output (generator output) is temporarily increased. May decrease. For this reason, in the rate limiter 20, the rate of change is set so that the increase in turbine output is faster than the increase in power of the compressor 102. Thereby, the temporary reduction of GT output accompanying the increase in the motive power of the compressor 102 by opening the inlet guide blade 104 can be suppressed.
- the operation control device 110 for the gas turbine 100 enables the IGV preceding open flag when the system frequency is equal to or lower than the predetermined threshold value ⁇ or when the output of the gas turbine 100 is requested to increase.
- the opening degree of the inlet guide vane 104 is set so as to be opened as compared to that. Therefore, regardless of the operating state of the gas turbine 100, the output can be increased without increasing the turbine inlet temperature.
- the gas turbine 100 performs opening control of the fuel flow rate adjustment valve 105 by a control signal 118 from a fuel control unit 112 provided in the operation control device 110, and performs load adjustment by fuel flow rate control.
- a fuel control unit 112 provided in the operation control device 110, and performs load adjustment by fuel flow rate control.
- this fuel control unit 112 based on the blade path temperature set value BPCSO in the blade path temperature control, the exhaust gas temperature set value EXCSO in the exhaust gas temperature control, the governor set value GVCSO in the governor control, or the load limit set value LDCSO in the load limit control, Of these, the lowest value is used as the final control signal 118 for the fuel flow control valve 105.
- the blade path temperature (exhaust gas temperature immediately after the final stage of the turbine 101) is measured, and this is compared with a target value based on the temperature control setting, and the blade is controlled by proportional integral (PI) control.
- a pass temperature set value BPCSO is generated.
- the exhaust gas temperature control the exhaust gas temperature (exhaust gas temperature in the exhaust duct downstream from the final stage of the turbine 101) is measured, and this is compared with the target value based on the temperature control setting, and the proportional integral (PI)
- the exhaust gas temperature set value EXCSO is generated by the control.
- FIG. 5 is a configuration diagram of a portion that generates the temperature adjustment setting (exhaust gas temperature adjustment setting) EXREF in the temperature control unit 114 of the second embodiment.
- the portion of the temperature control unit 114 that generates the temperature adjustment setting EXREF includes a function unit (FX11) 31, an adder 210, and a preceding signal generation unit 200.
- the function unit (FX11) 31 is set with a function indicating the relationship between the passenger compartment pressure and the temperature control setting during normal operation. That is, the temperature adjustment setting EXREF based on the function unit (FX11) 31 is generated during normal operation in which the opening command value IGV of the inlet guide vane 104 is, for example, 0 [degrees] or more.
- the preceding signal generation unit 200 includes first-order lag filters 202 and 203, a subtractor 204, a function unit (FX16) 205, a function unit (FX15) 201, a multiplier 206, and a rate limiter 207.
- the number of the first-order lag filters 202 and 203 may be one (for example, only 202) or three.
- the subtractor 204 and the first-order lag filters 202 and 203 calculate a change rate, and are not limited to this configuration as long as the change rate is detected.
- the subtracter 204 obtains a deviation between the IGV opening command value and the signal delayed by the first-order lag filters 202 and 203 and the signal not delayed, and this deviation is calculated as the IGV opening command value.
- the rate of change (pseudo-differential value).
- a correction amount (preceding signal) to the temperature adjustment setting EXREF is set in accordance with the change rate (pseudo-differential value) of the IGV opening command value.
- the function unit (FX15) 201 sets the operating range of the preceding signal generation unit 200 only when the opening degree of the inlet guide vane 104 is within a predetermined range.
- the function FX15 has a partial IGV opening degree. A state in which the gas turbine 100 is operating at a partial load by using a function that sets the opening range at the time of loading to “1” and “0” at the time of full opening, and multiplying this by the multiplier 206
- the correction (preceding signal) by the preceding signal generation unit 200 can be made effective only at.
- the rate limiter 207 limits the correction amount to the obtained temperature adjustment setting EXREF, that is, the time change rate of the preceding signal.
- the correction amount via the rate limiter 207 is added by the adder 210, and the temperature adjustment is performed. Generated as setting EXREF.
- the temporal transition of the temperature adjustment setting EXREF at this time is as shown by T1 in FIG. 6A, but the actual blade path temperature or exhaust gas temperature has a temperature measurement delay, so T0 in FIG. 6A. As shown in the figure, it changes slowly. Therefore, in the second embodiment, by adding the correction amount (preceding signal) by the preceding signal generation unit 200 as shown in FIG. 6B, the temporal transition of the temperature adjustment setting EXREF is shown in FIG. As shown in T2, the followability of the actual blade path temperature or exhaust gas temperature is made faster.
- the leading signal generation unit 200 calculates the change rate of the opening degree of the inlet guide vane 104 and calculates the correction amount according to the change rate. Since the temperature control setting EXREF is corrected, the followability of the blade path temperature setting value and the exhaust gas temperature setting value can be accelerated, the temperature setting can be released transiently, and the load responsiveness to fluctuations in the system frequency can be improved. it can.
- FIG. 7 is a configuration diagram of the blade path temperature control unit in the temperature control unit 114 according to the third embodiment, and a portion that generates the temperature adjustment setting EXREF is omitted as the configuration according to the second embodiment is used. .
- the configurations of the gas turbine 100 and the IGV control unit 113 according to the third embodiment are the same as those of the first embodiment, and description of each component is omitted.
- the blade path temperature control unit provided in the temperature control unit 114 includes signal generators (SG15) 301, (SG16) 303, (SG17) 308, (SG18) 309, (SG19). 311 and (SG20) 312, signal switchers 310 and 313, adder 302, subtractors 305 and 306, low value selector 304, and PI controller 307.
- a value that becomes a lower value between the value obtained by adding the predetermined value SG15 to the temperature adjustment setting EXREF by the adder 302 and the predetermined value SG16 is selected by the low value selector 304 and is set as the target value BPREF.
- a deviation between the value BPREF and the blade path temperature measurement value BPT from the blade path temperature detector 123 is obtained by the subtractor 305, and proportional integration control based on the deviation is performed by the PI controller 307 to generate the blade path temperature set value BPCSO.
- the upper limit value in the PI controller 307 is a deviation between the deviation by the subtractor 305 and the standby value RCSO.
- the blade path temperature control unit is characterized in that the control parameter in the PI control 307 is set to a preset value when the IGV advance open flag is valid.
- the proportional gain and the time constant are switched and set according to the IGV preceding open flag.
- the proportional gain is generated by switching the signal generators (SG17) 308 and (SG18) 309 with the signal switcher 310 in accordance with the IGV preceding open flag.
- the proportional gain at the normal time is set in the signal generator (SG17) 308, and the proportional gain at the time of IGV pre-opening is set in the signal generator (SG18) 309.
- the time constant is generated by switching the signal generators (SG19) 311 and (SG20) 312 with the signal switcher 313 in accordance with the IGV preceding open flag.
- the time constant at the normal time is set in the signal generator (SG19) 311 and the time constant at the time of IGV pre-opening is set in the signal generator (SG20) 312.
- the proportional gain and the time constant are preferably set to smaller values.
- the system frequency is equal to or lower than the predetermined threshold value ⁇ or when the output of the gas turbine 100 is requested to increase, there is urgency and follow-up.
- the deviation between the target value BPREF based on the temperature adjustment setting EXREF and the measured blade path temperature BPT is calculated.
- proportional integral control is performed by the PI controller 307 to generate the blade path temperature set value BPCSO of the turbine 101.
- the control parameter (proportional gain and time constant) in the PI controller 307 is set to a preset value, so that the movement of the blade path temperature set value BPCSO is accelerated in advance. It is possible to improve load responsiveness to fluctuations in system frequency and load increase.
- FIG. 8 is a configuration diagram of the blade path temperature control unit according to the temperature control unit 114 of the fourth embodiment, and the configuration according to the second embodiment is used for the part that generates the temperature adjustment setting EXREF. Omitted. Note that the configurations of the gas turbine 100 and the IGV control unit 113 according to the fourth embodiment are the same as those of the first embodiment, and description of each component will be omitted.
- the blade path temperature control unit provided in the temperature control unit 114 includes signal generators (SG15) 301 and (SG16) 303, adders 302 and 410, and subtractors 305 and 306. And a low value selector 304, a PI controller 307, and a preceding signal generator 400.
- a value that becomes a lower value between the value obtained by adding the predetermined value SG15 to the temperature adjustment setting EXREF by the adder 302 and the predetermined value SG16 is selected by the low value selector 304 and is set as the target value BPREF.
- a deviation between the value BPREF and the blade path temperature measurement value BPT from the blade path temperature detector 123 is obtained by the subtractor 305, and proportional integration control based on the deviation is performed by the PI controller 307 to generate the blade path temperature set value BPCSO.
- the upper limit value in the PI controller 307 is a deviation between the deviation by the subtractor 305 and the standby value RCSO.
- the blade path temperature control unit in the temperature control unit 114 of the fourth embodiment calculates a change rate of the opening degree of the inlet guide vane 104, calculates a correction amount according to the change rate, and based on the temperature adjustment setting EXREF. It is characterized in that a preceding signal generation unit 400 (second correction means) for correcting the generated blade path temperature set value BPCSO is added.
- the preceding signal generation unit 400 includes first-order lag filters 402 and 403, a subtractor 404, a function unit (FX18) 405, a function unit (FX17) 401, a multiplier 406, and a rate limiter 407.
- One or three primary delay filters may be used.
- the subtractor 204 and the first-order lag filters 202 and 203 calculate a change rate, and are not limited to this configuration as long as the change rate is detected.
- a subtracter 404 obtains a deviation between a signal obtained by delaying the IGV opening command value by the first-order lag filters 402 and 403 and a signal not delayed, and this deviation is obtained as the IGV opening command value.
- rate of change pseudo-differential value
- FX18 function unit
- a correction amount (preceding signal) to the blade path temperature set value BPCSO is set according to the magnitude of the change rate of the IGV opening command value (pseudo differential value).
- the function unit (FX17) 401 sets the operating range of the preceding signal generation unit 400 only when the opening degree of the inlet guide vane 104 is within a predetermined range.
- the IGV opening degree is a partial value.
- a state in which the gas turbine 100 is operating at a partial load by using a function such that the opening range at the time of loading is “1” and when the valve is fully opened is “0”, and this is multiplied by the multiplier 306.
- the correction (preceding signal) by the preceding signal generation unit 400 can be made effective only at.
- the rate limiter 407 limits the correction amount to the blade path temperature set value BPCSO, that is, the time change rate of the preceding signal.
- the correction amount via the rate limiter 407 is added by the adder 410, and the blade path temperature setting value BPCSO is added. It is generated as a temperature set value BPCSO.
- the leading signal generation unit 400 calculates the change rate of the opening degree of the inlet guide vane 104, calculates the correction amount according to the change rate, and the blade path. Since correction is performed by adding a correction amount (preceding signal) directly to the temperature setting value BPCSO, the movement of the blade path temperature setting value BPCSO is directly preceded to further speed up the follow-up and make the temperature setting escape transient. The speed can be increased, and the load responsiveness to fluctuations in system frequency and load increases can be improved.
- FIG. 9 is a configuration diagram of the IGV control flag generation unit 115 according to the fifth embodiment.
- the overall configuration of the operation control apparatus 110 for the gas turbine 100 is the same as that of the first to fourth embodiments described above, and the description of each component is omitted.
- the IGV control flag generation unit 115 enables the IGV preceding open flag when the system frequency is equal to or less than the predetermined threshold value ⁇ or when the output of the gas turbine 100 is requested to increase.
- an off delay 5 is added to the output of the OR gate 3.
- This off-delay 5 makes it possible to invalidate the IGV advance open flag with a certain delay when the IGV advance open flag switches from valid to invalid.
- the delay time due to the off-delay 5 is, for example, about the boiler time constant, and is, for example, 5 to 10 minutes.
- the GTCC has a delay in the output (ST output) of the steam turbine 160 when the load increases and the upper limit due to the temperature control operation of the generator 150 output.
- the load responsiveness (followability) was poor at high loads.
- the load following performance is improved by opening the inlet guide vane 104 by a certain amount with the IGV preceding open flag. Since the operation frequently occurs, it is necessary to prevent the frequent occurrence from the viewpoint of performance and component life. Therefore, in the fifth embodiment, by adding the off-delay 5 to the IGV control flag generation unit 115, the IGV advance opening is continued for a certain period even after the frequency constant signal or the output increase request signal is turned off during the load increase. The flag is kept valid. Thus, frequent opening / closing operations of the inlet guide vanes 104 can be prevented from the viewpoint of performance and component life.
- FIG. 10 is a configuration diagram of the fuel control unit 112 according to the sixth embodiment. Further, the overall configuration of the operation control device 110 of the gas turbine 100 is the same as that of the first to fifth embodiments described above, and the description of each component is omitted.
- the fuel control unit 112 increases the fuel flow rate according to the opening degree of the inlet guide blade 104 when the IGV preceding opening flag is validated.
- the fuel control unit 112 includes a CSO correction unit 131 that corrects the CSO output from the low value selection unit 130.
- the low value selection unit 130 receives the governor set value GVCSO, the load limit set value LDCSO, the blade path temperature set value BPCSO, and the exhaust gas temperature set value EXCSO, and outputs the minimum CSO.
- the CSO correction unit 131 includes a signal generator (SG1) 17, a signal generator (SG2) 18, a signal switch 19, a rate limiter 20, a correction function unit (FX20) 136, and an adder 137. Yes.
- the signal generator (SG1) 17 generates a first signal which is set to 0, for example, the signal generator (SG2) 18 generates a second signal indicating a predetermined value, and the signal switcher 19 is a signal generator.
- (SG1) 17 and signal generator (SG2) 18 are switched according to whether the IGV preceding open flag is valid or invalid.
- the rate limiter 20 limits the rate of time change of the signal from the signal switching unit 19, and the correction function unit (FX20) 136 sets the fuel flow rate (CSO) corresponding to the increase in the air flow rate set by the IGV advance opening flag. A correction value is calculated.
- the adder 137 adds the correction value output from the correction function unit (FX20) 136 to the CSO output from the low value selection unit 130, and outputs the result as the corrected CSO.
- the signal switch 19 selects the first signal of the signal generator (SG1) 17 and the correction value corresponding to the first signal is a low value selection unit. It is added to the CSO output from 130. At this time, since the first signal is set to “0”, when the IGV preceding open flag is invalid, the CSO selected by the low value selection unit 130 is output as it is as the corrected CSO. On the other hand, when the IGV advance open flag is valid, the signal switch 19 selects the second signal of the signal generator (SG2) 18, and the correction value corresponding to the second signal is output from the low value selector 130. Added to CSO.
- the correction value is added to the CSO selected by the low value selection unit 130 and output as the corrected CSO.
- the flow rate of fuel supplied to the combustor 103 increases.
- the standby value RCSO is obtained by adding the value output from the signal generator (SG32) 138 to the CSO output from the adder 137 by the adder 139, and the change rate (output from the signal generator (SG33) 140 ( It is calculated via the rate limiter 141 according to (decrease rate).
- the turbine inlet temperature is excessively lowered by making the opening of the inlet guide vanes 104 more open than usual in order to improve load followability. Is concerned.
- the fuel flow rate can be increased according to the increase in the air flow rate due to the opening degree of the inlet guide vanes 104 becoming open, so that the turbine inlet port An excessive decrease in temperature can be prevented.
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Abstract
Description
なお、1軸型複合サイクル発電プラントの場合には、ガスタービン100、発電機150及び蒸気タービン160のそれぞれの回転軸が一体に結合されている。
部分負荷で周波数が低下した場合の調定率に従った負荷上昇に対して、或いは負荷増加指令に対して、従来技術では、ガスタービン100は燃料を増加させるが、一方で燃焼温度(タービン入口温度)の上昇による機器損傷といった機器保護の観点から温調動作するため、所望の負荷が得られないことが懸念される。
IGV先行開フラグが有効とされると、入口案内翼の開度をそれまでに比べて開くように、入口案内翼開度設定手段によって設定される。
また、「タービン出力=タービン通過流量×タービン熱落差×効率」の関係があり、入口案内翼が開く方向に開度を変化させれば、圧縮機の吸気流量が増加してタービン通過流量も増加するので、タービン入口温度低下による熱落差以上にタービン通過流量の増大が寄与すれば発電機の出力は増加することになる。
従って、ガスタービンの運転状態に係らず、タービン入口温度を上げることなく出力の上昇を可能とする。
本発明の第1実施形態に係るガスタービンの制御装置及び制御方法について説明する。
図1において、ガスタービン100は圧縮機102、燃焼器103及びタービン101を備える。圧縮機102で圧縮された空気、及び燃料流量調整弁105により流量調節された燃料は、燃焼器103に供給され、ここで混合・燃焼されることにより高圧の燃焼ガスが生成される。高温の燃焼ガスはタービン101に供給され、膨張することによりタービン101を駆動する。この駆動力は発電機150に伝達されて発電が行われるとともに、圧縮機102に伝達されることにより圧縮機102を駆動する。
燃料流量調整弁105は、運転制御装置110の燃料制御部112からの制御信号118によって作動される。この燃料流量調整弁105は、上述したように燃料ガスの燃料流量を制御することにより、負荷、さらには排ガス温度を調整している。なお、1軸型複合サイクル発電プラントの場合には、ガスタービン100、発電機150及び蒸気タービン160のそれぞれの回転軸が一体に結合されている。
IGV制御フラグ生成部115は、ガスタービン100の出力を増加させる場合に、IGV先行開フラグを有効とする。
例えば、IGV制御フラグ生成部115は、系統周波数が所定閾値α以下となって周波数低信号が入力された場合、又は、ガスタービン100の出力増加を要求する出力増要求信号が入力された場合に、ORゲート3によりIGV先行開フラグを有効として生成する。なお、系統周波数が所定閾値α以下の場合、系統周波数を上昇させるためにガスタービン100は出力増加を行うこととなる。
例えば、信号発生器(SG1)17に「0」を、信号発生器(SG2)18に所定値を設定しておき、IGV先行開フラグが有効になったときには、通常運転時のIGV開度指令に信号発生器(SG2)18の所定値を加算して、入口案内翼104の開度が通常よりも開くようにしている。
部分負荷でガスタービン100が運転された状態で、系統周波数が所定閾値α以下となった場合、又は、部分負荷でガスタービン100が運転された状態で、ガスタービン100の出力増加が要求された場合には、IGV制御フラグ生成部115でIGV先行開フラグが有効とされる。
すなわち、IGV先行開フラグが有効とされると、入口案内翼104は、通常設定に比べて開き気味とされことで、圧縮機102の吸気流量が通常の設定より増加する。これにより、ガスタービン100は、タービン入口温度を通常より下げ気味で運転ができるので、風量の増加によりタービン出力を増加できる。例えば、入口案内翼104の開度を10~20%増加させ、風量を定格流量よりも5%~10%増加させる。
具体的には、「タービン出力=タービン通過流量×タービン熱落差×効率」の関係があり、入口案内翼104が開く方向にIGV開度を変化させれば、圧縮機102の吸気流量が増加してタービン通過流量も増加する。このため、タービン入口温度低下による熱落差以上にタービン通過流量の増大が寄与すれば、発電機150の出力は増加することになる。
また、圧縮機102の吸気流量が増加してタービン入口温度を低下するので、燃焼器103へより多くの燃料投入が可能となり、燃料投入によってもタービン出力を増加できる。
このため、レートリミッタ20では、圧縮機102の動力の増加よりも、タービン出力の増加の方が速くなるように、変化率が設定されている。これにより、入口案内翼104を開くことによる圧縮機102の動力の増加に伴うGT出力の一時的な減少を抑制できる。
従って、ガスタービン100の運転状態に係らず、タービン入口温度を上げることなく出力の上昇が可能とされる。
以下、本発明の第2実施形態について説明する。
関数器(FX11)31は、通常運転時における車室圧力と温調設定との関係を示す関数が設定されている。つまり、入口案内翼104の開度指令値IGVが例えば0[度]以上の通常運転時には関数器(FX11)31に基づく温調設定EXREFが生成される。
以下、本発明の第3実施形態について説明する。
PI制御器307における上限値は、減算器305による偏差と待機値RCSOとの偏差としている。また、本第3実施形態に係るブレードパス温度制御部は、IGV先行開フラグが有効の場合に、PI制御307における制御パラメータを予め設定された値に設定する点に特徴があるが、ここでは、比例ゲイン及び時定数をIGV先行開フラグに応じて切替設定している。
以下、本発明の第4実施形態について説明する。
次に、本発明の第4実施形態に係るガスタービン100の運転制御装置110について説明する。
図8は、本第4実施形態の温度制御部114に係るブレードパス温度制御部の構成図であり、温調設定EXREFを生成する部分については、第2実施形態に係る構成を使用するものとして省略する。なお、本第4実施形態に係るガスタービン100及びIGV制御部113の構成は第1実施形態と同様であり、各構成要素の説明を省略する。
次に、第5実施形態に係るガスタービン100の運転制御装置110について説明する。
ここで、図9は本第5実施形態に係るIGV制御フラグ生成部115の構成図である。また、ガスタービン100の運転制御装置110の全体構成は上述した第1実施形態~第4実施形態と同様であり、各構成要素の説明を省略する。
そこで、本第5実施形態では、IGV制御フラグ生成部115にオフディレイ5を付加することによって、負荷上昇中に周波数定信号又は出力増要求信号がオフとなった後でも一定期間、IGV先行開フラグが有効に保持される。
これにより、性能及び部品寿命の観点から、入口案内翼104の開閉動作が頻繁に発生する事を防止する事ができる。
次に、第6実施形態に係るガスタービン100の運転制御装置110について説明する。
ここで、図10は本第6実施形態に係る燃料制御部112の構成図である。また、ガスタービン100の運転制御装置110の全体構成は上述した第1実施形態~第5実施形態と同様であり、各構成要素の説明を省略する。
信号発生器(SG1)17は、例えば0とされる第1信号を発生し、信号発生器(SG2)18は、所定値を示す第2信号を発生し、信号切換器19は、信号発生器(SG1)17と信号発生器(SG2)18とをIGV先行開フラグが有効か無効かに応じて切り替える。レートリミッタ20は、信号切換器19からの信号の時間変化率を制限し、補正関数器(FX20)136は、IGV先行開フラグで設定された空気流量の増加に応じた燃料流量(CSO)の補正値を算出する。加算器137は、低値選択部130から出力されたCSOに補正関数器(FX20)136から出力された補正値を加算し、補正後のCSOとして出力する。
一方、IGV先行開フラグが有効な場合には、信号切換器19により信号発生器(SG2)18の第2信号が選択され、第2信号に応じた補正値が低値選択部130から出力されたCSOに加算される。これにより、IGV先行開フラグが有効な場合には、低値選択部130によって選択されたCSOに補正値が加算され、補正後のCSOとして出力される。これにより、IGV先行開フラグが有効とされた場合に、燃焼器103へ供給される燃料流量が増加する。
101 タービン
102 圧縮機
103 燃焼器
104 入口案内翼
105 燃料流量調整弁
110 運転制御装置
112 燃料制御部
113 IGV制御部
114 温度制御部
115 IGV制御フラグ生成部
150 発電機
Claims (10)
- 前段に入口案内翼を備える圧縮機からの圧縮空気と燃料とを燃焼器に供給して該燃焼器で発生する燃焼ガスによってタービンを回転させて発電機を駆動するガスタービンの制御装置であって、
前記ガスタービンの出力を増加させる場合に、IGV先行開フラグを有効とするIGV制御フラグ生成手段と、
前記IGV先行開フラグが有効の場合に、前記入口案内翼の開度をそれまでに比べて開くように設定する入口案内翼開度設定手段と、
を備えるガスタービンの制御装置。 - IGV制御フラグ生成手段は、系統周波数が所定閾値以下又は前記ガスタービンの出力増加が要求された場合に、IGV先行開フラグを有効とする請求項1記載のガスタービンの制御装置
- 前記入口案内翼開度設定手段は、圧縮機の動力の増加よりも、タービン出力の増加の方が速くなるように、入口案内翼の開度の変化率が設定される請求項1又は請求項2記載のガスタービンの制御装置。
- 温調設定を車室圧力に応じて設定する温度制御手段を備え、
前記温度制御手段は、前記IGV先行開フラグが有効の場合に、前記入口案内翼の開度の変化率を算出して該変化率に応じた補正量を算出し、前記温調設定を補正する第1補正手段を有する請求項1から請求項3の何れか1項記載のガスタービンの制御装置。 - 温調設定を車室圧力に応じて設定する温度制御手段を備え、
前記温度制御手段は、前記温調設定に基づく目標値と計測したブレードパス温度又は排ガス温度との偏差に基づき比例積分制御を行って前記タービンのブレードパス温度設定値又は排ガス温度設定値を生成するPI制御手段を有し、前記IGV先行開フラグが有効の場合に、該PI制御手段における制御パラメータを予め設定された値に設定する請求項1から請求項4の何れか1項記載のガスタービンの制御装置。 - 温調設定を車室圧力に応じて設定する温度制御手段を備え、
前記温度制御手段は、前記IGV先行開フラグが有効の場合に、前記入口案内翼の開度の変化率を算出して該変化率に応じた補正量を算出し、前記温調設定に基づき生成した前記タービンのブレードパス温度設定値又は排ガス温度設定値を補正する第2補正手段を有する請求項1から請求項5の何れか1項記載のガスタービンの制御装置。 - 前記IGV制御フラグ生成手段は、前記IGV先行開フラグが有効から無効に切り替わるとき、一定の遅延を持たせて該IGV先行開フラグを無効とする請求項1から請求項6の何れか1項記載のガスタービンの制御装置。
- 前記IGV先行開フラグが有効とされた場合に、前記入口案内翼の開度に応じて燃料流量を増加させる請求項1から請求項7の何れか1項記載のガスタービンの制御装置。
- 前段に入口案内翼を備える圧縮機と、
前記圧縮機からの圧縮空気と燃料とが供給され、燃焼ガスを発生する燃焼器と、
前記燃焼器で発生する燃焼ガスによって回転するタービンと、
前記タービンの回転によって駆動する発電機と、
請求項1から請求項8の何れか1項に記載の制御装置と、
を備えるガスタービン。 - 前段に入口案内翼を備える圧縮機からの圧縮空気と燃料とを燃焼器に供給して該燃焼器で発生する燃焼ガスによってタービンを回転させて発電機を駆動するガスタービンの制御方法であって、
前記ガスタービンの出力を増加させる場合に、IGV先行開フラグを有効とするIGV制御フラグ有効ステップと、
前記IGV先行開フラグが有効の場合に、前記入口案内翼の開度をそれまでに比べて開くように設定する入口案内翼開度設定ステップと、
を有するガスタービンの制御方法。
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US15/105,344 US10161317B2 (en) | 2014-02-05 | 2015-02-04 | Gas-turbine control device, gas turbine, and gas-turbine control method |
DE112015000664.8T DE112015000664T5 (de) | 2014-02-05 | 2015-02-04 | Gasturbinen-Steuerungsvorrichtung, Gasturbine, und Gasturbinen-Steuerungsverfahren |
KR1020167017342A KR101819844B1 (ko) | 2014-02-05 | 2015-02-04 | 가스 터빈의 제어 장치, 가스 터빈, 및 가스 터빈의 제어 방법 |
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CN112360629A (zh) * | 2020-11-27 | 2021-02-12 | 国网北京市电力公司 | 室外抗御极寒气候的燃气轮机发电机组及其运行方法 |
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JP6257035B2 (ja) * | 2014-03-25 | 2018-01-10 | 三菱日立パワーシステムズ株式会社 | ガスタービンの燃焼制御装置および燃焼制御方法並びにプログラム |
US10221777B2 (en) * | 2014-03-25 | 2019-03-05 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine combustion control device and combustion control method and program therefor |
JP6335720B2 (ja) * | 2014-08-26 | 2018-05-30 | 三菱日立パワーシステムズ株式会社 | 制御装置、システム及び制御方法 |
JP6763629B2 (ja) * | 2016-12-15 | 2020-09-30 | 三菱パワー株式会社 | ガスタービン制御装置、ガスタービン制御方法 |
KR101971337B1 (ko) * | 2017-04-24 | 2019-04-22 | 두산중공업 주식회사 | 가스터빈 시스템 및 제어 방법 |
KR101898386B1 (ko) * | 2017-04-24 | 2018-09-12 | 두산중공업 주식회사 | 가스터빈 시스템 및 제어 방법 |
JP6867909B2 (ja) * | 2017-08-02 | 2021-05-12 | アズビル株式会社 | 熱式流量計 |
JP6934835B2 (ja) * | 2018-04-13 | 2021-09-15 | 三菱パワー株式会社 | ガスタービンの制御装置及びガスタービン並びにガスタービンの制御方法 |
US11486316B2 (en) | 2018-09-13 | 2022-11-01 | Pratt & Whitney Canada Corp. | Method and system for adjusting a variable geometry mechanism |
JP7173897B2 (ja) * | 2019-02-28 | 2022-11-16 | 三菱重工業株式会社 | ガスタービンの運転方法およびガスタービン |
CN110107407B (zh) * | 2019-04-19 | 2020-10-27 | 江苏国信淮安第二燃气发电有限责任公司 | 一种优化燃机igv控制提升燃气-蒸汽联合循环效率的方法 |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2009114956A (ja) * | 2007-11-06 | 2009-05-28 | Mitsubishi Heavy Ind Ltd | ガスタービンの運転制御装置および運転制御方法 |
JP2011111996A (ja) * | 2009-11-27 | 2011-06-09 | Mitsubishi Heavy Ind Ltd | ガスタービンの制御装置及びその方法並びに発電プラント |
Family Cites Families (9)
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JP3887777B2 (ja) * | 2001-12-10 | 2007-02-28 | 株式会社日立製作所 | ガスタービン発電設備のガバナフリー制御方法及び制御装置 |
JP2003206749A (ja) | 2002-01-17 | 2003-07-25 | Mitsubishi Heavy Ind Ltd | タービン設備及びその運転方法 |
JP3684208B2 (ja) | 2002-05-20 | 2005-08-17 | 株式会社東芝 | ガスタービン制御装置 |
JP4427532B2 (ja) * | 2006-09-21 | 2010-03-10 | 三菱重工業株式会社 | ガスタービンの運転制御装置 |
JP2008121513A (ja) * | 2006-11-10 | 2008-05-29 | Mitsubishi Heavy Ind Ltd | ガスタービン発電システムおよびそのカロリ異常検知方法 |
US8028511B2 (en) * | 2007-05-30 | 2011-10-04 | Mitsubishi Heavy Industries, Ltd. | Integrated gasification combined cycle power generation plant |
JP5868671B2 (ja) * | 2011-11-28 | 2016-02-24 | 三菱日立パワーシステムズ株式会社 | 弁制御装置、ガスタービン、及び弁制御方法 |
JP2014047728A (ja) * | 2012-08-31 | 2014-03-17 | Mitsubishi Heavy Ind Ltd | ガスタービンの制御装置、ガスタービン、及びガスタービンの制御方法 |
JP6332747B2 (ja) * | 2014-08-06 | 2018-05-30 | 三菱日立パワーシステムズ株式会社 | 流量比算出装置、これを備えている制御装置、この制御装置を備えているガスタービンプラント、流量比算出方法、及び燃料系統の制御方法 |
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112360629A (zh) * | 2020-11-27 | 2021-02-12 | 国网北京市电力公司 | 室外抗御极寒气候的燃气轮机发电机组及其运行方法 |
CN112360629B (zh) * | 2020-11-27 | 2024-05-28 | 国网北京市电力公司 | 室外抗御极寒气候的燃气轮机发电机组及其运行方法 |
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US20170002748A1 (en) | 2017-01-05 |
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