US20180016983A1 - State determining device, operation controlling device, gas turbine, and state determining method - Google Patents

State determining device, operation controlling device, gas turbine, and state determining method Download PDF

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Publication number
US20180016983A1
US20180016983A1 US15/545,872 US201515545872A US2018016983A1 US 20180016983 A1 US20180016983 A1 US 20180016983A1 US 201515545872 A US201515545872 A US 201515545872A US 2018016983 A1 US2018016983 A1 US 2018016983A1
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Prior art keywords
output
turbine
value
gas turbine
fuel
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Abandoned
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US15/545,872
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English (en)
Inventor
Takashi Sonoda
Ryuji TAKENAKA
Sosuke Nakamura
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Mitsubishi Power Ltd
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Mitsubishi Hitachi Power Systems Ltd
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Assigned to MITSUBISHI HITACHI POWER SYSTEMS, LTD. reassignment MITSUBISHI HITACHI POWER SYSTEMS, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: NAKAMURA, SOSUKE, SONODA, TAKASHI, TAKENAKA, Ryuji
Publication of US20180016983A1 publication Critical patent/US20180016983A1/en
Assigned to MITSUBISHI POWER, LTD. reassignment MITSUBISHI POWER, LTD. CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
Abandoned legal-status Critical Current

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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
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10—Adaptations for driving, or combinations with, electric generators
    • 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
    • F02C7/057—Control or regulation
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • F02C9/263—Control of fuel supply by means of fuel metering valves
    • 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
    • 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
    • F01D25/34—Turning or inching gear
    • F01D25/36—Turning or inching gear using electric motors
    • 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
    • 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
    • F05D2270/303—Temperature
    • 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

Definitions

  • the present invention relates to a state determining device, an operation controlling device, a gas turbine, and a state determining method.
  • a gas turbine has a compressor, a combustor, and a turbine.
  • the gas turbine compresses air introduced from an air inlet using the compressor to obtain high-temperature and high-pressure compression air, supplies fuel to the compression air to be combusted by the combustor to obtain high-temperature and high-pressure combustion gas (working fluid), and drives the turbine with the combustion gas.
  • An electric generator is coupled to a rotating shaft of the gas turbine, and the gas turbine rotates the coupled electric generator to generate electricity.
  • the combustion gas used for driving the turbine is discharged as flue gas from a discharge side of the turbine.
  • An operation controlling device that controls the gas turbine detects states of the compressor, the combustor, and the turbine and adjusts the amount of air to be introduced into the compressor and the amount of fuel to be supplied on the basis of detection results and an instruction value on the operation to control the operation of the gas turbine.
  • Patent Literature 1 describes a gas-turbine controlling device that has a plurality of gas-turbine inlet-gas-temperature detectors that are placed in an annular manner at an inlet high-temperature part of a gas turbine to detect gas-turbine inlet-gas temperatures, a plurality of gas-turbine flue-gas-temperature detectors that are placed in an annular manner at a discharge part of the gas turbine to detect gas-turbine flue-gas temperatures, a first determining unit that determines whether a gas-turbine inlet-gas temperature deviation of the temperatures detected by the gas-turbine inlet-gas-temperature detectors is equal to or larger than an allowable value, a second determining unit that, for one of the gas-turbine inlet-gas-temperature detectors that has detected a largest or smallest temperature value, estimates an estimation temperature of the relevant gas-turbine inlet-gas-temperature detector on the basis of temperatures of gas-turbine inlet-gas-temperature detectors that are adjacent to the relevant gas-turbine inlet-
  • Patent Literature 1 Japanese Laid-open Patent Publication No. 4-81527 A
  • the gas turbine controls the operation using the detection results of the respective parts.
  • the gas turbine uses an output of an electric generator connected to the gas turbine as a parameter to be used for the control of the operation, instead of using a mechanical output that is difficult to detect.
  • the gas turbine may be destabilized.
  • An object of the present invention is to provide a state determining device, an operation controlling device, a gas turbine, and a state determining method for determining an operation state of a gas turbine to enable the gas turbine to operate more stably.
  • a state determining device determines a state of a gas turbine connected to an electric generator.
  • the gas turbine includes a compressor that compresses intake air into compression air, a fuel supply device that supplies fuel, a combustor that mixes the compression air supplied from the compressor and the fuel supplied from the fuel supply device and combusts a resultant mixture to generate combustion gas, and a turbine that is rotated with the generated combustion gas.
  • the state determining device includes an instruction-value detecting unit that detects a difference in an instruction value related to an output of the gas turbine, an output detecting unit that detects a difference in an output of the electric generator, and a determining unit that determines an operation of the gas turbine has departed from a predetermined relation when a difference between the difference in the instruction value and the difference in the output is equal to or larger than a threshold.
  • the instruction value is a fuel-flow instruction value of fuel to be supplied from the fuel supply device to the combustor.
  • the instruction-value detecting unit detects a difference between a detected instruction value and an instruction value detected at a last time
  • the output detecting unit detects a difference between a detected output and an output detected at a last time
  • an operation controlling device includes any of the above-described state determining device, and a controlling device that controls the gas turbine on a basis of the instruction value and the output of the electric generator.
  • the controlling device changes a value of the detected output of the electric generator to a value with smaller fluctuation when the state determining device has determined that an operation of the gas turbine departs from a predetermined relation.
  • the controlling device uses a value at a last time as a value of the output of the electric generator when the state determining device has determined that an operation of the gas turbine departs from a predetermined relation.
  • the controlling device changes a calculated value to a value with smaller fluctuation on a basis of a value of the output of the electric generator when the state determining device has determined that an operation of the gas turbine departs from a predetermined relation.
  • a gas turbine includes a compressor that compresses intake air into compression air, a fuel supply device that supplies fuel, a combustor that mixes the compression air supplied from the compressor and the fuel supplied from the fuel supply device and combusts a resultant mixture to generate combustion gas, a turbine that is rotated with the generated combustion gas, and any of the above-described operation controlling device.
  • a state determining method determines a state of a gas turbine connected to an electric generator.
  • the gas turbine includes a compressor that compresses intake air into compression air, a fuel supply device that supplies fuel, a combustor that mixes the compression air supplied from the compressor and the fuel supplied from the fuel supply device and combusts a resultant mixture to generate combustion gas, and a turbine that is rotated with the generated combustion gas.
  • the state determining method includes steps of detecting a difference in an instruction value related to an output of the gas turbine, detecting a difference in an output of the electric generator, and determining that an operation of the gas turbine has departed from a predetermined relation when a difference between the difference in the instruction value and the difference in the output is equal to or larger than a threshold.
  • FIG. 1 is a schematic diagram illustrating a gas turbine according to an embodiment of the present invention.
  • FIG. 2 is a schematic diagram illustrating a general configuration of a state determining device.
  • FIG. 3 is a flowchart illustrating an example of a processing operation of the state determining device.
  • FIG. 4 is a schematic diagram illustrating a general configuration of a turbine-inlet-temperature calculating unit.
  • FIG. 5 is a flowchart illustrating an example of a processing operation of the turbine-inlet-temperature calculating unit.
  • FIG. 6 is a flowchart illustrating an example of a processing operation of the turbine-inlet-temperature calculating unit.
  • FIG. 7 is a schematic diagram illustrating a general configuration of another example of the turbine-inlet-temperature calculating unit.
  • FIG. 1 is a schematic diagram illustrating a gas turbine according to an embodiment of the present invention.
  • a gas turbine 1 according to the present embodiment has a compressor 11 , a combustor 12 , a turbine 13 , a fuel supply device 14 , a controlling device 16 , and a rotor 18 as illustrated in FIG. 1 .
  • the rotor 18 is arranged at central parts of the compressor 11 , the combustor 12 , and the turbine 13 to pass therethrough.
  • the compressor 11 and the turbine 13 of the gas turbine 1 are coupled by the rotor 18 to be capable of rotating together.
  • the gas turbine 1 is controlled by the controlling device (operation controlling device) 16 .
  • An electric generator 15 is coupled to the gas turbine 1 .
  • the electric generator 15 has a rotating part coupled to the rotor 18 to be capable of rotating together, and rotates with the rotor 18 to generate electricity.
  • the compressor 11 compresses air A introduced from an air inlet into compression air A 1 .
  • An inlet guide vane (IGV) 22 that adjusts an intake amount of the air A introduced from the air inlet is installed in the compressor 11 .
  • the intake amount of the air A is adjusted by adjustment of the opening of the inlet guide vane 22 .
  • the inlet guide vane 22 has a plurality of vane bodies 22 a , and an IGV activating unit 22 b for changing the vane angle of the vane bodies 22 a .
  • the vane angle of the vane bodies 22 a is adjusted by the IGV activating unit 22 b to adjust the opening of the inlet guide vane 22 and adjust the intake amount of the air A.
  • the intake amount of the air A is increased, so that a pressure ratio of the compressor 11 is increased.
  • the intake amount of the air A is reduced, so that the pressure ratio of the compressor 11 is lowered.
  • the combustor 12 supplies fuel F to the compression air A 1 compressed by the compressor 11 , mixes the compression air A 1 and the fuel F, and combusts the resultant mixture to generate combustion gas.
  • the turbine 13 is rotated with the combustion gas generated by the combustor 12 .
  • the rotor 18 is rotatably supported at both end parts in the axial direction by bearings (not illustrated) and is provided to be rotatable on an axial center.
  • a drive shaft of the electric generator 15 is coupled to one end of the rotor 18 on the side of the compressor 11 (the positional placement is not particularly limited).
  • the electric generator 15 is provided coaxially with the turbine 13 and can generate electricity with rotation of the turbine 13 .
  • the air A introduced from the air inlet of the compressor 11 passes the inner part of the compressor 11 through the inlet guide vane 22 and is compressed into the high-temperature and high-pressure compression air A 1 .
  • the fuel F is supplied from the combustor 12 to the compression air A 1 and the compression air A 1 and the fuel F are mixed and combusted to generate high-temperature and high-pressure combustion gas.
  • the high-temperature and high-pressure combustion gas generated by the combustor 12 passes through the inner part of the turbine 13 , thereby activating (rotating) the turbine 13 to drivingly rotate the rotor 18 and drive the electric generator 15 coupled to the rotor 18 . Accordingly, the electric generator 15 coupled to the rotor 18 is rotationally driven to generate electricity. Meanwhile, the combustion gas used for driving the turbine 13 is discharged as flue gas to the atmosphere.
  • a casing pressure gauge 51 , an intake-air state detector 52 , a blade path thermometer 53 , and a flue gas thermometer 54 are provided in the gas turbine 1 .
  • the casing pressure gauge 51 is provided on a line through which the compression air A 1 flows from the compressor 11 to the combustor 12 , specifically on a casing inner part of the combustor 12 , and measures the pressure (casing pressure) of the compression air A 1 .
  • the intake-air state detector 52 has an intake air thermometer 52 A that measures an intake air temperature of the air A to be introduced into the compressor 11 , and an intake-air pressure gauge 52 B that detects an intake air pressure.
  • the blade path thermometer 53 is provided on a line through which the flue gas discharged from the turbine 13 flows, and measures the temperature of the flue gas that has passed a last-stage blade provided on the downstream side of the turbine 13 in a flue-gas flowing direction.
  • the flue gas thermometer 54 is provided on the downstream side of the blade path thermometer 53 and measures the temperature of the flue gas.
  • the gas turbine 1 also acquires information of an output from the electric generator 15 for detecting load of the gas turbine 1 .
  • the output of the electric generator 15 can be measured by an output meter provided in the electric generator 15 . Signals measured by the casing pressure gauge 51 , the intake-air state detector 52 , the blade path thermometer 53 , and the flue gas thermometer 54 are input to the controlling device 16 .
  • the controlling device 16 controls parts such as the inlet guide vane 22 and a fuel adjusting valve 35 on the basis of at least one of an instruction value corresponding to an output such as an output request or a fuel-flow instruction value, measurement results of measurement devices such as the casing pressure gauge 51 , the intake-air state detector 52 , the blade path thermometer 53 , and the flue gas thermometer 54 , and a measurement result of the output of the electric generator 15 , to control the operation of the gas turbine 1 .
  • the controlling device 16 has a state determining device 62 , a turbine-inlet-temperature calculating unit 64 , and an operation control unit 66 .
  • the controlling device 16 includes other calculating units that estimate a state amount on the basis of the measurement results of the measurement devices such as the casing pressure gauge 51 , the intake-air state detector 52 , the blade path thermometer 53 , and the flue gas thermometer 54 , and an instruction value, besides the turbine-inlet-temperature calculating unit 64 .
  • FIG. 2 is a schematic diagram illustrating a general configuration of the state determining device.
  • the state determining device 62 determines an operation state of the gas turbine. Specifically, the state determining device 62 determines whether a relation between an instruction value on the fuel flow and an output of the electric generator 15 meets or departs from a predetermined relation.
  • the state determining device 62 has an instruction-value detecting unit 102 , an output detecting unit 104 , and a determining unit 106 .
  • the instruction-value detecting unit 102 processes a fuel-flow instruction signal to detect a change in the fuel-flow instruction signal.
  • the flue-flow instruction signal is a signal designating a flow rate of the fuel to be supplied to the combustor 12 .
  • the instruction-value detecting unit 102 has a first-order lag filter 112 and a subtracter 114 .
  • the first-order lag filter 112 and the subtracter 114 are arranged in parallel and the fuel-flow instruction signal is input thereto.
  • the first-order lag filter (LAG) 112 outputs a fuel-flow instruction signal that is the latest one signal before the current fuel-flow instruction signal.
  • the first-order lag filter 112 outputs the latest one fuel-flow instruction signal to the subtracter 114 .
  • the subtracter 114 calculates a difference between the fuel-flow instruction signal and the latest one fuel-flow instruction signal which is output from the first-order lag filter 112 .
  • the subtracter 114 outputs the calculated difference in the fuel-flow instruction signal to the determining unit 106 .
  • first-order lag filter 112 Although only one first-order lag filter 112 is arranged in the instruction-value detecting unit 102 , a plurality of first-order lag filters 112 can be placed to be connected in series. When the number of the first-order lag filters 112 is increased, a fuel-flow instruction signal to be subtracted can be a more previous fuel-flow instruction signal.
  • the instruction-value detecting unit 102 in the present embodiment uses the fuel-flow instruction signal, it suffices to use an instruction value on the output of the gas turbine 1 and an output request signal for the gas turbine 1 can be used instead of the fuel-flow instruction signal. It suffices that the instruction-value detecting unit 102 can detect a change rate (% /Sec) of the instruction value and a target for which the difference is to be extracted or a target for which the change rate is to be extracted is not particularly limited.
  • the output detecting unit 104 processes an electric generator output (detection value of an output of the electric generator) to detect a change in the electric generator output.
  • the electric generator output is a value of electricity output from the electric generator 15 .
  • the output detecting unit 104 has a first-order lag filter 122 and a subtracter 124 .
  • the first-order lag filter 122 and the subtracter 124 are arranged in parallel and the electric generator output is input thereto.
  • the first-order lag filter (LAG) 122 outputs an electric generator output which is the latest one output before the current electric generator output. That is, the first-order lag filter 122 outputs the latest one electric generator output to the subtracter 124 .
  • the subtracter 124 calculates a difference between the electric generator output and the latest one electric generator output which is output from the first-order lag filter 122 .
  • the subtracter 124 outputs the calculated difference in the electric generator output to the determining unit 106 . It suffices that the output detecting unit 104 can detect a change rate (% /Sec) of the output and a target for which the difference is to be extracted or a target for which the change rate is to be extracted is not particularly limited.
  • the determining unit 106 determines whether the operation state of the gas turbine 1 meets a predetermined relation, specifically whether a relation between the instruction value on the fuel flow and the output of the electric generator 15 meets or departs from a predetermined relation on the basis of a difference x 1 detected by the instruction-value detecting unit 102 and a difference x 2 detected by the output detecting unit 104 .
  • the predetermined relation is a relation in which the fuel flow and the output can be regarded to be proportional to each other.
  • the determining unit 106 has a comparing unit 132 and a signal output unit 136 .
  • the comparing unit 132 compares the difference x 1 detected by the instruction-value detecting unit 102 with the difference x 2 detected by the output detecting unit 104 .
  • the comparing unit 132 in the present embodiment multiplies the difference x 2 by a factor “a” to match the scales of the difference x 1 and the signal, and then detects a difference therebetween to determine whether the difference is larger than a threshold ⁇ . Specifically, the comparing unit 132 compares whether
  • the signal output unit 136 outputs a signal based on a result of the comparing unit 132 .
  • the signal output unit 136 outputs a signal indicating that the state departs from the relation when the comparing unit 132 has determined that the operation state departs from the relation, and outputs a signal indicative of meeting of the relation when the comparing unit 132 has determined that the operation state meets the relation.
  • FIG. 3 is a flowchart illustrating an example of the processing operation of the state determining device.
  • the state determining device 62 detects a difference in the fuel-flow instruction value with the instruction-value detecting unit 102 (Step S 12 ), and detects a difference in the output of the electric generator 15 with the output detecting unit 104 (Step S 14 ).
  • the processes at Step S 12 and Step S 14 can be performed in parallel or in a reverse order.
  • the state determining device 62 detects a difference in the fuel-flow instruction value and a difference in the output of the same timing.
  • the state determining device 62 determines whether
  • the signal output unit 136 outputs a signal indicating that the operation state departs from the relation (Step S 18 ).
  • the signal output unit 136 outputs a signal indicating that the operation state keeps the relation (Step S 20 ).
  • the state determining device 62 outputs only either the signal indicating that the state departs from the relation or the signal indicating that the state keeps the relation, without outputting both thereof. In this case, when the signal is not output, the state can be regarded to be the other state than that indicated by the signal.
  • FIG. 4 is a schematic diagram illustrating a general configuration of the turbine-inlet-temperature calculating unit.
  • the turbine-inlet-temperature calculating unit 64 estimates a turbine inlet temperature that is difficult to measure.
  • the turbine-inlet-temperature calculating unit 64 calculates an estimation value of the turbine inlet temperature on the basis of the output (gas-turbine (GT) electric-generator output) detected by the electric generator 15 , an IGV signal indicating the opening of the inlet guide vane 22 , detected by the IGV activating unit 22 b , the compressor inlet temperature detected by the intake air thermometer 52 A, and the compressor inlet pressure detected by the intake-air pressure gauge 52 B.
  • GT gas-turbine
  • the turbine-inlet-temperature calculating unit 64 has a turbine-inlet-temperature computing unit 140 , a turbine-inlet-temperature-corresponding-signal output unit 142 , a filter 144 , a signal switcher 146 , a signal generator 148 , and a signal generator 149 .
  • the output (gas-turbine (GT) electric-generator output) detected by the electric generator 15 , the IGV signal indicating the opening of the inlet guide vane 22 , detected by the IGV activating unit 22 b , the compressor inlet temperature detected by the intake air thermometer 52 A, and the compressor inlet pressure detected by the intake-air pressure gauge 52 B are input to the turbine-inlet-temperature computing unit 140 .
  • the turbine-inlet-temperature computing unit 140 performs computing based on the input values to calculate an estimation value of the turbine inlet temperature.
  • the turbine-inlet-temperature-corresponding-signal output unit 142 outputs a signal corresponding to the turbine inlet temperature calculated by the turbine-inlet-temperature computing unit 140 to respective parts that execute control using the turbine inlet temperature.
  • the filter 144 is arranged on a channel through which the GT electric-generator output is input to the turbine-inlet-temperature computing unit 140 .
  • the filter 144 is a filter capable of changing the time constant, and generates a lag in fluctuation of the signal detected by the electric generator 15 and input to the turbine-inlet-temperature computing unit 140 by changing the time constant.
  • the filter 144 switches the filter time constant on the basis of a signal input via the signal switcher 146 .
  • the signal switcher 146 is connected to the signal generators 148 and 149 and switches whether the signal generated by the signal generator 148 is input to the filter 144 or the signal generated by the signal generator 149 is input to the filter 144 on the basis of the signal input from the state determining device 62 .
  • the signal generators 148 and 149 generate different signals, respectively.
  • the signal switcher 146 When receiving the signal indicating that the state keeps the relation, the signal switcher 146 outputs the signal from the signal generator 148 to the filter 144 .
  • the signal switcher 146 When receiving the signal indicating that the state departs from the relation, the signal switcher 146 outputs the signal from the signal generator 149 to the filter 144 .
  • the filter 144 applies a first time constant (time constant in normal times) when the signal from the signal generator 148 is input thereto, and applies a second time constant having a value larger than the first time constant when the signal from the signal generator 149 is input thereto.
  • FIG. 5 is a flowchart illustrating an example of a processing operation of the turbine-inlet-temperature calculating unit.
  • FIG. 5 illustrates a selection process of the filter.
  • the turbine-inlet-temperature calculating unit 64 determines whether the state determining device 62 has determined that the state departs from the relation (Step S 30 ). When the state determining device 62 has determined that the state does not depart from the relation (NO at Step S 30 ), the turbine-inlet-temperature calculating unit 64 uses the time constant in normal times (Step S 32 ). When the state determining device 62 has determined that the state departs from the relation (YES at Step S 30 ), the turbine-inlet-temperature calculating unit 64 uses the time constant having a value larger than the normal times (Step S 34 ).
  • the turbine-inlet-temperature calculating unit 64 switches between the time constants of the filter 144 on the basis of the result of the state determining device 62 in the manner as described above, thereby causing a value with smaller fluctuation than the value of the output detected by the electric generator 15 to be input to the turbine-inlet-temperature computing unit 140 in the state departing from the relation.
  • the operation control unit 66 controls operations of the respective parts in the gas turbine 1 on the basis of information output from the state determining device 62 and the turbine-inlet-temperature calculating unit 64 , the measurement results of the various measurement devices, and the instruction value. For example, the operation control unit 66 executes IGV control to control the IGV activating unit 22 b that activates the inlet guide vane 22 to adjust the amount of air (the intake amount of air) to be introduced into the compressor 11 .
  • the operation control unit 66 controls the IGV activating unit 22 b to change the opening (hereinafter, “IGV opening”) of the inlet guide vane 22 to adjust the intake amount of the air A to be introduced into the compressor 11 .
  • the operation control unit 66 controls the IGV opening to be a rated opening at the time of a full-load operation.
  • the rated opening is an opening at a time when the gas turbine output becomes a rated output.
  • the operation control unit 66 also executes fuel control to control the fuel adjusting valve 35 that is provided on a fuel supply line 34 for supplying the fuel F to the combustor 12 to adjust the supply amount of the fuel F.
  • the operation control unit 66 controls the fuel adjusting valve 35 to adjust the supply amount of the fuel F to be supplied (injected) to the compression air A 1 .
  • the state determining device 62 can determine whether the gas turbine 1 is operating in a state meeting the predetermined relation or departing from the predetermined state. That is, the state determining device 62 can determine whether the output of the electric generator 15 is affected by the number of rotations of a system connected to the electric generator 15 , by performing comparison on a difference between the change rate (% /Sec) of the GT electric-generator output and the change rate (% /Sec) of the fuel-flow instruction (CSO) signal which is an example of the change rate of the mechanical output of the gas turbine 1 .
  • CSO fuel-flow instruction
  • the controlling device 16 of the present embodiment can stably operate the gas turbine by adjusting the gas-turbine electric-generator output to be input to the turbine-inlet-temperature calculating unit 64 on the basis of the result of the state determining device 62 , specifically by setting the gas-turbine electric-generator output to a value with smaller fluctuation than the actual value when the state departs from the relation.
  • the time constant is adjusted to set the gas-turbine electric-generator output to a value with smaller fluctuation than the actual value when the state determining device 62 has determined that the state departs from the relation.
  • the adjustment is not limited thereto and it suffices that fluctuation in the gas-turbine electric-generator output can be reduced.
  • a value at a time when the state is determined to keep the relation (a value immediately before departing, a last value) can be set as the gas-turbine electric-generator output.
  • the turbine-inlet-temperature calculating unit 64 may switch between using and not using the result of the state determining device 62 depending on the state of the gas turbine.
  • FIG. 6 is a flowchart illustrating an example of a processing operation of the turbine-inlet-temperature calculating unit.
  • the turbine-inlet-temperature calculating unit 64 determines whether the gas turbine 1 is in a stable operation state (Step S 40 ).
  • the stable operation state is a state in which the gas turbine 1 is operated under a rated condition or in a state keeping a predetermined output for a time equal to or longer than a predetermined period.
  • Step S 40 When the turbine-inlet-temperature calculating unit 64 has determined that the gas turbine 1 is in the stable operation state (YES at Step S 40 ), control is executed based on the result of the state determining device 62 (Step S 42 ). That is, the processes in FIG. 5 described above are performed. When the turbine-inlet-temperature calculating unit 64 has determined that the gas turbine 1 is not in the stable operation state (NO at Step S 40 ), control is executed without using the result of the state determining device 62 (Step S 44 ).
  • the turbine-inlet-temperature calculating unit 64 does not use the result of the state determining device 62 , thereby enabling to control with high responsivity in an operation such as at the time of start-up or during when the output is fluctuated based on an instruction value.
  • the turbine-inlet-temperature calculating unit 64 can adjust a result of calculation based on the GT electric-generator output, that is, the calculation value of the turbine-inlet-temperature in the present embodiment, on the basis of the result of the state determining device 62 .
  • FIG. 7 is a schematic diagram illustrating a general configuration of another example of the turbine-inlet-temperature calculating unit.
  • a turbine-inlet-temperature calculating unit 64 a illustrated in FIG. 7 has the turbine-inlet-temperature computing unit 140 , the turbine-inlet-temperature-corresponding-signal output unit 142 , the filter 144 , a filter 150 , a signal switcher 152 , a signal generator 156 , and a signal generator 154 .
  • the output (gas-turbine (GT) electric-generator output) detected by the electric generator 15 , the IGV signal indicating the opening of the inlet guide vane 22 , detected by the IGV activating unit 22 b , the compressor inlet temperature detected by the intake air thermometer 52 A, and the compressor input pressure detected by the intake-air pressure gauge 52 B are input to the turbine-inlet-temperature computing unit 140 .
  • the turbine-inlet-temperature computing unit 140 performs computing based on the input values to calculate the estimation value of the turbine inlet temperature.
  • the turbine-inlet-temperature-corresponding-signal output unit 142 outputs a signal corresponding to the turbine inlet temperature calculated by the turbine-inlet-temperature computing unit 140 to respective parts that execute control using the turbine inlet temperature.
  • the filter 144 is arranged on a channel through which the GT electric-generator output is input to the turbine-inlet-temperature computing unit 140 .
  • the filter 144 is a filter to which the time constant is set, and generates a lag in fluctuation of the signal detected by the electric generator 15 and input to the turbine-inlet-temperature computing unit 140 . It is unnecessary to generate a lag by adjusting the time constant of the filter 144 .
  • the filter 150 is arranged between the turbine-inlet-temperature computing unit 140 and the turbine-inlet-temperature-corresponding-signal output unit 142 .
  • the filter 150 is a filter that can change the time constant and generates a lag in fluctuation of a signal input from the turbine-inlet-temperature computing unit 140 to the turbine-inlet-temperature-corresponding-signal output unit 142 by changing the time constant.
  • the filter 150 switches the time constant of the filter 150 on the basis of a signal input via the signal switcher 152 .
  • the signal switcher 152 is connected to the signal generators 156 and 154 and switches whether a signal generated by the signal generator 156 is input to the filter 150 or a signal generated by the signal generator 154 is input to the filter 150 on the basis of the signal input from the state determining device 62 .
  • the signal generators 156 and 154 generate different signals, respectively.
  • the signal switcher 152 When a signal indicating that the state keeps the relation is received, the signal switcher 152 outputs the signal of the signal generator 156 to the filter 150 .
  • the signal switcher 152 outputs the signal of the signal generator 154 to the filter 150 .
  • the filter 150 applies a first time constant (time constant in normal times) when the signal of the signal generator 156 is input thereto, and applies a second time constant having a value larger than the first time constant when the signal of the signal generator 154 is input thereto.
  • the first time constant may be a time constant that allows a signal to pass through as it is.
  • the turbine-inlet-temperature calculating unit 64 a adjusts the computing result of the turbine-inlet-temperature computing unit 140 on the basis of the result of the state determining device 62 to reduce fluctuation in the value calculated when the state departs from the relation and stabilize the operation of the gas turbine 1 . In this way, identical effects can be obtained also by reducing the fluctuation in the value calculated based on the gas-turbine electric-generator output, instead of adjusting the gas-turbine electric-generator output.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Control Of Eletrric Generators (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
US15/545,872 2015-02-03 2015-11-27 State determining device, operation controlling device, gas turbine, and state determining method Abandoned US20180016983A1 (en)

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JP2015019674A JP6173367B2 (ja) 2015-02-03 2015-02-03 状態判定装置、運転制御装置、ガスタービン及び状態判定方法
JP2015-019674 2015-02-03
PCT/JP2015/083455 WO2016125370A1 (ja) 2015-02-03 2015-11-27 状態判定装置、運転制御装置、ガスタービン及び状態判定方法

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111989630A (zh) * 2018-02-27 2020-11-24 伍德沃德有限公司 异常检测和基于异常的控制
CN112639268A (zh) * 2018-11-08 2021-04-09 三菱动力株式会社 燃气涡轮机的控制装置、燃气涡轮机设备、燃气涡轮机的控制方法及燃气涡轮机的控制程序
US11274610B2 (en) * 2018-04-23 2022-03-15 Siemens Energy Global GmbH & Co. KG Combustion system control
CN114893301A (zh) * 2022-04-14 2022-08-12 北京动力机械研究所 小型涡扇发动机参控温度参数判故方法及冗余控制方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201721389D0 (en) * 2017-12-20 2018-01-31 Rolls Royce Plc Methods, computer programs, non-transitory computer readable storage mediums, signals, and apparatus for controlling electrical power supplied to a component

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3692340B2 (ja) * 2002-07-30 2005-09-07 三菱重工業株式会社 コンバインドプラントの燃料制御方法、それに供する制御装置
JP3930462B2 (ja) * 2003-08-01 2007-06-13 株式会社日立製作所 一軸コンバインドサイクル発電設備及びその運転方法
JP2006029162A (ja) * 2004-07-14 2006-02-02 Toshiba Corp ガスタービンの制御装置および制御方法
JP4581957B2 (ja) * 2005-10-17 2010-11-17 トヨタ自動車株式会社 車両制動装置および車両制動装置の異常検出方法
US7997083B2 (en) * 2007-08-28 2011-08-16 General Electric Company Method and system for detection of gas turbine combustion blowouts utilizing fuel normalized power response
JP5523949B2 (ja) * 2010-06-24 2014-06-18 三菱重工業株式会社 燃料異常検出装置、燃料調整装置および燃料異常検出方法
US8793004B2 (en) * 2011-06-15 2014-07-29 Caterpillar Inc. Virtual sensor system and method for generating output parameters
JP6082299B2 (ja) * 2013-03-28 2017-02-15 三菱日立パワーシステムズ株式会社 原動機の異常検出方法、この方法を実行する原動機の制御装置、及びこの装置を備えている発電プラント
US9002617B2 (en) * 2013-07-10 2015-04-07 General Electric Company Gas turbine engine controller with event trigger

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111989630A (zh) * 2018-02-27 2020-11-24 伍德沃德有限公司 异常检测和基于异常的控制
US11274610B2 (en) * 2018-04-23 2022-03-15 Siemens Energy Global GmbH & Co. KG Combustion system control
CN112639268A (zh) * 2018-11-08 2021-04-09 三菱动力株式会社 燃气涡轮机的控制装置、燃气涡轮机设备、燃气涡轮机的控制方法及燃气涡轮机的控制程序
US20220042466A1 (en) * 2018-11-08 2022-02-10 Mitsubishi Power, Ltd. Device for controlling gas turbine, gas turbine facility, method for controlling gas turbine, and program for controlling gas turbine
US11585281B2 (en) * 2018-11-08 2023-02-21 Mitsubishi Heavy Industries, Ltd. Device for controlling gas turbine, gas turbine facility, method for controlling gas turbine, and program for controlling gas turbine
CN114893301A (zh) * 2022-04-14 2022-08-12 北京动力机械研究所 小型涡扇发动机参控温度参数判故方法及冗余控制方法

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DE112015006101T5 (de) 2017-11-30
CN107208554A (zh) 2017-09-26
KR20170100630A (ko) 2017-09-04
WO2016125370A1 (ja) 2016-08-11
KR101878625B1 (ko) 2018-07-13
JP6173367B2 (ja) 2017-08-02
CN107208554B (zh) 2019-04-26
JP2016142212A (ja) 2016-08-08
US20210310409A1 (en) 2021-10-07

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