WO2004033874A1 - 燃焼器制御装置 - Google Patents
燃焼器制御装置 Download PDFInfo
- Publication number
- WO2004033874A1 WO2004033874A1 PCT/JP2003/013013 JP0313013W WO2004033874A1 WO 2004033874 A1 WO2004033874 A1 WO 2004033874A1 JP 0313013 W JP0313013 W JP 0313013W WO 2004033874 A1 WO2004033874 A1 WO 2004033874A1
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- WO
- WIPO (PCT)
- Prior art keywords
- combustor
- fuel
- flow rate
- pilot
- turbine inlet
- Prior art date
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Classifications
-
- 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
- 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
- F02C7/22—Fuel supply systems
- F02C7/228—Dividing fuel between various burners
-
- 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
- F02C9/32—Control of fuel supply characterised by throttling of fuel
- F02C9/34—Joint control of separate flows to main and auxiliary burners
Definitions
- the present invention relates to a combustor control device for a gas turbine, and more particularly to a combustor control device for controlling a fuel-air ratio of fuel and air supplied to a combustor.
- a gas turbine combustor having a pilot nozzle for diffusing fuel gas and diffusing it with a pilot flame and a main nozzle for mixing air and fuel for premixed combustion has been used.
- the gas turbine rotates by using the combustion gas from such a combustor, and the power of the gas turbine generates the power. Therefore, in a power generation facility using a gas turbine, the output of the generator can be controlled by controlling the combustion of the combustor.
- FIG. 6 shows a configuration of a conventional combustor control device for controlling a combustor having such a pilot nozzle and a main nozzle.
- the combustor control device 100 shown in FIG. 6 converts the bypass valve control signal for controlling the opening of the combustor bypass valve 8 into the output from the generator 4 by the bypass valve opening calculating section 10'2. It controls the amount of air generated on the basis of the air flow and supplied to the combustor bypass valve 8 and supplied to the combustor 3.
- the combustor control device 100 generates an IGV control signal for controlling the opening of the inlet guide vane (IGV) 5 based on the output from the generator 4 by the IGV opening calculation unit 103. Then, it is supplied to the IGV 5 to control the amount of air flowing into the compressor 1.
- IGV inlet guide vane
- the bypass valve opening calculation unit 102 and the IGV opening calculation unit 103 obtain the values of the bypass valve control signal and the IGV control signal based on the graphs in FIGS. 3 and 4. .
- the horizontal axis in FIGS. 3 and 4 represents the output from the generator 4.
- the combustor control device 100 determines the output from the generator 4 and the target
- the PI component 10 gives an integral component to generate a fuel flow rate command signal (c SO).
- c SO fuel flow rate command signal
- the value of CSO from the PI unit 10 is compared with a predetermined value L by a limiter 11, and when the value becomes lower than the predetermined value L, the CSO is divided into a pilot ratio calculation unit 101 and a multiplication unit. Give to part 1 and 2.
- the pilot ratio calculation unit 101 sets the multiplication value in the multiplication unit 12 based on CSO and gives it to the multiplication unit 12.
- the multiplication unit 12 multiplies the CSO given by the limiter 11 by the multiplication value given by the pilot ratio calculation unit 101 to generate a pilot fuel control signal, and Give to control valve 7. Further, the subtractor 13 subtracts the pilot fuel control signal supplied from the multiplier 12 from the CSO supplied from the limiter 11 to generate a main fuel control signal. give.
- the pilot ratio calculation unit 101 obtains the value of the pilot fuel control signal based on the graph of FIG.
- the horizontal axis in FIG. 2 represents the value of CSO.
- the opening of the IGV 5 is closed and compressed in order to suppress combustion oscillation and perform stable combustion.
- the opening degree of the combustor bypass valve 8 is opened to increase the flow rate of the compressed air flowing directly from the compressor 1 to the gas turbine 2. In this way, the fuel-air ratio is increased by reducing the air flow rate to the combustor 3.
- the opening of the IGV 5 is opened to increase the flow rate of air flowing into the compressor 1 in order to suppress NOX emissions.
- the opening degree of the combustor bypass valve 8 is closed to reduce the flow rate of the compressed air flowing directly from the compressor 1 to the gas turbine 2.
- the fuel-air ratio is reduced by increasing the air flow rate to the combustor 3.
- the opening of the main fuel control valve 6 is closed and the pilot fuel is activated in order to activate the combustion of the pilot nozzle and suppress the combustion vibration for stable combustion.
- the ratio of the pilot fuel to all the fuel supplied to the combustor 3 (pilot ratio) is increased.
- the opening of the main fuel control valve 6 and the opening of the pilot fuel control valve 7 are opened in order to suppress the combustion of the pilot nozzle and suppress the NOX emission. Close And lower the pilot ratio.
- the air flow supplied to the combustor and the fuel flow supplied to the pilot nozzle and the main nozzle are set based on the output of the generator. Accurate control cannot be performed when the power factor changes or when there is a sudden load change in the combined power generation system that uses steam turbines.
- the output of the generator is equivalent to the sum of the gas turbine propulsion torque and the steam turbine propulsion torque. Therefore, the output of the generator based on the propulsion torque of the gas turbine is obtained by estimating the propulsion torque of the steam turbine in a steady state, and the output of the generator corresponding to the obtained propulsion torque of the gas turbine is obtained.
- the pilot ratio and fuel-air ratio in the combustor are controlled based on this. Therefore, the output of the generator, which corresponds to the propulsion torque of the gas turbine, is not accurately obtained.When sudden load fluctuations occur, accurate control of the pilot ratio and the fuel-air ratio in the combustor is required. I can't.
- the temperature of the combustion gas at the combustor outlet determines the pilot gas in the combustor. Ratio and fuel-air ratio should be controlled. Good. However, in recent gas turbines, the temperature at the turbine inlet has exceeded 150 ° C, so there is no temperature measuring device that can continuously measure the temperature at the turbine inlet for a long time. There is also a method of estimating the turbine inlet temperature by calculating from the combustor casing pressure and the gas turbine exhaust gas temperature, but the response of the exhaust gas temperature to the combustion state is poor. Therefore, as a result, a value in which the actual turbine inlet temperature is delayed is given, and a response delay occurs in controlling the pilot ratio and the fuel-air ratio in the combustor. Disclosure of the invention
- the present invention provides a combustor control capable of accurately calculating the turbine inlet temperature without response delay and controlling the combustor based on the calculated turbine inlet temperature. It is intended to provide a device.
- a combustor control device of the present invention is provided in a gas turbine provided coaxially with a generator, and controls a combustor that supplies a combustion gas to the gas turbine and rotates the gas turbine.
- a fuel flow calculating unit that sets a fuel flow rate to be supplied to the combustor based on a difference value between an output of the generator and a target output of the generator;
- a turbine inlet temperature calculation unit for obtaining a turbine inlet temperature which is a temperature of combustion gas flowing into the gas turbine from the combustor based on a flow rate and a temperature of each of the air; and a combustor for diffusing and burning a pilot flame.
- the total fuel and the main fuel to be supplied to the main nozzle in the combustor that performs premixed combustion by mixing the fuel and the fuel and the fuel to be supplied to the pilot nozzle A pilot ratio calculating unit that sets a pilot ratio, which is a ratio of the pilot fuel to a fuel flow rate, based on the turbine inlet temperature obtained by the turbine inlet temperature calculating unit; An air flow rate calculation unit that sets an air flow rate to be flowed into the turbine based on the turbine inlet temperature calculated by the turbine inlet temperature calculation unit; and a pilot ratio calculated by the pilot ratio calculation unit and the fuel flow rate.
- the flow rates of the pilot fuel and the main fuel are controlled based on the fuel flow rate calculated by the flow rate calculation unit, and the air flow rate calculated by the air flow rate calculation unit is used to control the inside of the combustor.
- the combustion of the combustor It is characterized by controlling the state.
- FIG. 1 is a block diagram showing a configuration of a gas turbine power generation facility equipped with a combustor control device of the present invention
- Figure 2 is a graph showing the relationship between the pilot ratio and the turbine inlet temperature or CSO.
- Fig. 3 is a graph showing the relationship between the opening of the combustor bypass valve and the turbine inlet temperature or generator output.
- Fig. 4 is a graph showing the relationship between the opening of IGV and the turbine inlet temperature or generator output.
- FIG. 5 is a diagram showing an example of an internal configuration of a turbine inlet temperature calculating section
- FIG. 6 is a block diagram showing a configuration of a conventional gas turbine power generation facility.
- FIG. 1 is a block diagram illustrating a configuration of a gas turbine power generation facility including a combustor control device according to the present embodiment.
- FIG. 1 the same parts as those in FIG. 6 are denoted by the same reference numerals, and detailed description thereof will be omitted.
- the gas turbine power generation facility shown in Fig. 1 has a compressor 1 equipped with an IGV 5, which is the first stage stationary blade, a gas turbine 2 coaxial with the compressor 1, and a combustion gas to rotate the gas turbine 2. And a generator 4 that generates power by rotating the gas turbine 2 when the gas turbine 2 rotates. Further, a main fuel control valve 6 for setting a fuel flow supplied to a main nozzle (not shown) of the combustor 3 and a pilot fuel control for setting a fuel flow supplied to a pilot nozzle (not shown) of the combustor 3.
- the amount of air flowing into the compressor 1 is set by the opening of the IGV, and the amount of air flowing from the compressor 1 to the combustor 3 is Set by bypass valve 8.
- diffusion combustion is performed by a pilot nozzle to which fuel is supplied through a pilot fuel control valve 7, and the main fuel control valve
- Premixed combustion is performed by a main nozzle to which fuel is supplied through 6, and high-temperature combustion gas obtained by combustion in the combustor 3 is supplied to the gas turbine 2.
- the gas turbine 2 rotates by the combustion gas supplied from the combustor 3
- the coaxial generator 4 also rotates, so that the generator 4 generates electric power and outputs electric power.
- the total fuel flow rate G f supplied to the combustor 3 is measured by the flow rate measuring device 21, and the temperature T f is measured by the temperature measuring device 22.
- the temperature T 3 of the air supplied from the compressor 1 to the combustor 3 is measured by the temperature measuring device 23.
- the differential pressure Pd of the air flowing into the compressor 1 is measured by the differential pressure measuring device 24.
- the measured fuel flow rate G f, fuel temperature T f, air temperature T 3, differential pressure P d, and opening k of the combustor bypass valve 8 are given to the combustor controller 20.
- the combustion air of the combustor 3 is controlled by the combustor control device 20.
- Ratio and pilot ratio are set.
- an IGV control signal, a main fuel control signal, a pilot fuel control signal, and a bypass valve control signal are respectively generated, and an IGV 5 and a main fuel control valve 6 are generated.
- the combustor control device 20 includes a subtraction unit 9 that receives the output E 0 of the generator 4 and obtains a difference value E 1 ⁇ E 0 from a target output E 1, and a difference from the subtraction unit 9.
- a PI unit 10 that adds the integral component to the values E 1 and E 0 to generate CSO
- a limiter 11 that outputs a CSO whose value becomes L when the value of the CSO from the PI unit 10 becomes L or more, and a pilot fuel control signal given the cso from the limiter 11
- a subtractor 13 that subtracts the value of the pilot fuel control signal from the multiplier 12 from the CSO value from the limiter 11 to generate a main fuel control signal.
- An air flow calculator 14 for obtaining an air flow G 3 flowing into the combustor 3 based on the differential pressure P d and the opening k of the combustor bypass valve 8, a fuel flow G i, a fuel temperature T f, A turbine inlet temperature calculating unit 15 for calculating the turbine inlet temperature T4 based on the air flow rate G3 and the air temperature T3, and a multiplying unit for determining the pilot ratio based on the turbine inlet temperature T4. Pilot ratio calculation unit 16 given to 12 and bypass valve opening to generate bypass valve control signal based on turbine inlet temperature T 4 A calculation unit 1 7, Ru and an IGV opening calculating unit 1 8 which generates an I GV control signal on the basis of turbine inlet mouth temperature T 4.
- the combustor control device 20 When the combustor control device 20 is configured as described above, when the output E 0 from the generator 4 is given to the subtraction unit 9, the actual output E 0 is subtracted from the target output E 1 of the generator 4. Then, the difference value E 1 — E 0 is obtained.
- the integral component is added to the difference value E 1 -E 0 in the PI section 10 to improve the response characteristics and C SO is generated, it is given to the limiter 11.
- the value of ⁇ 30 is compared with ⁇ , and if it is smaller than L, the CSO from the PI unit 10 is output as it is, and if it is more than L, the CSO whose value is L is output .
- the differential pressure Pd between the inside and outside of the IGV 5 measured by the differential pressure measuring device 24 and the opening k of the combustor bypass valve 8 are given to the air flow rate calculation unit 14, and the compressor 1 sends the combustor
- the air flow rate G3 supplied to the combustor 3 via the bypass valve 8 is determined.
- the temperature T 3 is provided to the turbine inlet temperature calculation unit 15.
- the turbine inlet temperature calculating section 15 obtains the turbine inlet temperature T4 based on the transfer function expressed by the equation (2) obtained from the equation (1).
- T4 (s) (Cpf Gf (s) Tf (s) + Cp3 G3 (s) T3 (s) + 77 Hf Gf (s))
- Equation (1) expresses the dynamic behavior of the turbine inlet temperature.
- the first term on the right-hand side represents the thermal energy of the fuel gas
- the second term on the right-hand side represents the thermal energy of the inflowing air
- the fourth term on the right is the energy required to raise the combustion gas to the current turbine inlet temperature T4
- the left is the change in turbine inlet temperature T4.
- the value of the turbine inlet temperature T 4 obtained based on the transfer function of equation (2) in the turbine inlet temperature calculator 15 is converted into a pilot ratio calculator 16, a bypass valve opening calculator 17 and an IGV.
- the opening degree calculation unit 18 is provided.
- the pilot ratio calculation unit 16 calculates the pilot ratio based on FIG. 2 and supplies the pilot ratio to the multiplication unit 12.
- the bypass valve solvability calculation unit 17 obtains a bypass valve control signal having a value based on FIG. 3 and supplies the control signal to the combustor bypass valve 8.
- the IGV opening calculating section 18 obtains an IGV control signal having a value based on FIG.
- the horizontal axis in FIGS. 2 to 4 represents the turbine inlet temperature T4.
- the pilot ratio calculated by the pilot ratio calculator 16 is provided to the multiplier 12, which multiplies the CSO provided by the limiter 11 by the multiplier 12. Is done.
- the multiplying unit 12 outputs a pilot fuel control signal having a value of PXCSO, which is supplied to the subtracting unit 13 and the pilot fuel control valve 7. Since this pilot fuel control signal is supplied to the subtraction unit 13, when the subtraction unit 13 subtracts from the CSO supplied from the limiter 11, the subtraction unit 12 obtains the main value of (11 ⁇ P) XCSO.
- the fuel control signal is output and given to the main fuel control valve 6.
- the combustion state of the combustor 3 can be controlled based on the turbine inlet temperature T4. That is, when the turbine inlet temperature T4 is high, the opening of the IGV 5 and the opening of the combustor bypass valve 8 are closed to increase the flow rate of the air flowing into the combustor 3 and increase the fuel-air ratio.
- the pilot ratio is lowered by lowering the opening of the main fuel control valve 6 and closing the pilot fuel control valve 7 to reduce the amount of NOX generated at high load. be able to.
- the opening of the IGV 5 is closed and the opening of the combustor bypass valve 8 is opened to increase the flow rate of the air flowing into the combustor 3 and increase the fuel-air ratio.
- the pilot ratio is increased by lowering the opening of the main fuel control valve 6 and the opening of the pilot fuel control valve 7, and the combustion vibration generated at low load is suppressed and stabilized. Can be burned.
- the turbine inlet temperature calculating section 15 obtains the turbine inlet temperature T4 based on the transfer function of the equation (2).
- the turbine inlet temperature calculator 15 shown in FIG. 5 has a configuration based on the following equation (3).
- T 4 current turbine inlet temperature
- T 4 k turbine inlet temperature which is the previous calculation result
- At timing time at which measured values are given from the measuring units 22 to 24 It is.
- the current turbine inlet temperature T 4 is expressed by the equation (3) according to the equation (3).
- Cp4 Vcb ⁇ 4X (T4- T4k) / ⁇ t Cpf Gf Tf + Cp3 G3 T3 + ⁇ Hf Gf
- T4 ((Cpf Gf Tf + Cp3 G3 T3 + ⁇ Hf Gf) X ⁇ t + Cp4 Vcb y 4XT4k)
- the fuel flow rate G f is multiplied by a constant 7; the thermal efficiency 7 of the combustor 3, which is a constant, and the fuel calorific value H f, which is a constant 7; Then, after the values obtained from the multipliers 32, 34 are added in the adder 35, the value obtained in the adder 35 and the value obtained in the multiplier 36 are added to the adder 3. Added by 7.
- the value (Cpf Gf Tf + Cp3 G3 T3 + ⁇ Hf Gf) output from the adder 37 is multiplied by the constant timing time ⁇ t in the multiplier 38.
- the memory 30 stores a turbine inlet temperature T 4 k which is a previous calculation result.
- the combustion gas specific heat C The product of p 4 and the volume V cb of the combustor 3 multiplied by the specific gravity ⁇ 4 of the combustion gas is multiplied, and further obtained in the adder 40 by the multiplier 38 (Cpf Gf Tf + Cp3 G3 T3 + n Hf Gf) X ⁇ is added.
- the addition unit 41 adds the fuel flow rate Gf and the air flow rate G3 to obtain the turbine inlet combustion gas flow rate G4, and then adds the constant timing time ⁇ t to the turbine inlet combustion gas flow rate G4.
- the multiplied value of the combustion gas and the specific heat of combustion gas C p 4 is multiplied by the multiplication unit 42.
- a value obtained by multiplying constant value of combustion gas specific heat C p4, volume V cb of combustor 3 and combustion gas specific gravity ⁇ 4 as a constant is added to the value obtained in multiplication section 42. Is done.
- the obtained turbine inlet temperature ⁇ 4 is given to each of the pilot ratio calculating section 16, the bypass valve opening calculating section 17 and the IGV opening calculating section 18 and the turbine inlet temperature is stored in the memory 30. Stored as temperature ⁇ 4 k.
- the turbine inlet temperature calculating section 15 is not limited to the configuration example shown in FIG. 5 as long as the turbine inlet temperature T4 is obtained based on the function of the equation (1). It does not matter. Further, the air flow rate G3 to the combustor 3 was determined based on the differential pressure Pd of the air flowing into the compressor 1 and the opening k of the combustor bypass valve 8, but the airflow G3 to the combustor 3 was determined. It is also possible to provide a flow meter in the path for supplying water, and measure directly with this flow meter. Industrial applicability
- the turbine inlet temperature is calculated based on the flow rate and the temperature of the fuel and the air supplied to the combustor in the turbine inlet temperature calculation unit, the turbine inlet temperature relatively close to the actual temperature is calculated. You can ask.
- the combustion state of the combustor is controlled based on the turbine inlet temperature, the responsiveness can be improved. Also, unlike in the past, since the combustion state of the combustor is not controlled based on the generator output, disturbances in the power system ⁇ always optimal combustion regardless of the state of the steam turbine installed coaxially with the gas turbine It can be controlled to keep the state.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Regulation And Control Of Combustion (AREA)
- Control Of Turbines (AREA)
Abstract
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Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
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DE10393442T DE10393442T5 (de) | 2002-10-10 | 2003-10-09 | Verbrennersteuerung |
US10/528,408 US7191588B2 (en) | 2002-10-10 | 2003-10-09 | Combustor controller |
Applications Claiming Priority (2)
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JP2002297400A JP2004132255A (ja) | 2002-10-10 | 2002-10-10 | 燃焼器制御装置 |
JP2002/297400 | 2002-10-10 |
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WO2004033874A1 true WO2004033874A1 (ja) | 2004-04-22 |
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US (1) | US7191588B2 (ja) |
JP (1) | JP2004132255A (ja) |
CN (1) | CN100360776C (ja) |
DE (1) | DE10393442T5 (ja) |
WO (1) | WO2004033874A1 (ja) |
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US4094142A (en) * | 1974-10-30 | 1978-06-13 | Engelhard Minerals & Chemicals Corp. | Turbine system method and apparatus |
GB2011091A (en) * | 1977-12-22 | 1979-07-04 | Gen Electric | Method and apparatus for calculating turbine inlet temperature |
JPS6196332A (ja) * | 1984-10-18 | 1986-05-15 | Mitsubishi Heavy Ind Ltd | ガスタ−ビン燃焼器バイパス弁制御方法 |
JPH08178290A (ja) * | 1994-12-20 | 1996-07-12 | Toshiba Corp | ガスタービン燃料供給装置 |
JPH1122490A (ja) * | 1997-07-07 | 1999-01-26 | Mitsubishi Heavy Ind Ltd | パイロット比自動調整装置 |
Family Cites Families (6)
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JPH0552174A (ja) | 1991-08-23 | 1993-03-02 | Nippondenso Co Ltd | 制御装置のバツクアツプ判定装置 |
JPH06323165A (ja) * | 1993-05-17 | 1994-11-22 | Hitachi Ltd | ガスタービン用制御装置及び制御方法 |
JPH07189743A (ja) | 1993-12-28 | 1995-07-28 | Hitachi Ltd | ガスタービン燃焼器の制御方法 |
US5966925A (en) * | 1996-04-26 | 1999-10-19 | Kabushiki Kaisha Toshiba | Gas turbine power plant control for starting and stopping |
US6095793A (en) * | 1998-09-18 | 2000-08-01 | Woodward Governor Company | Dynamic control system and method for catalytic combustion process and gas turbine engine utilizing same |
US7078825B2 (en) * | 2002-06-18 | 2006-07-18 | Ingersoll-Rand Energy Systems Corp. | Microturbine engine system having stand-alone and grid-parallel operating modes |
-
2002
- 2002-10-10 JP JP2002297400A patent/JP2004132255A/ja not_active Withdrawn
-
2003
- 2003-10-09 WO PCT/JP2003/013013 patent/WO2004033874A1/ja active Application Filing
- 2003-10-09 DE DE10393442T patent/DE10393442T5/de not_active Ceased
- 2003-10-09 CN CNB2003801009770A patent/CN100360776C/zh not_active Expired - Fee Related
- 2003-10-09 US US10/528,408 patent/US7191588B2/en not_active Expired - Lifetime
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4094142A (en) * | 1974-10-30 | 1978-06-13 | Engelhard Minerals & Chemicals Corp. | Turbine system method and apparatus |
GB2011091A (en) * | 1977-12-22 | 1979-07-04 | Gen Electric | Method and apparatus for calculating turbine inlet temperature |
JPS6196332A (ja) * | 1984-10-18 | 1986-05-15 | Mitsubishi Heavy Ind Ltd | ガスタ−ビン燃焼器バイパス弁制御方法 |
JPH08178290A (ja) * | 1994-12-20 | 1996-07-12 | Toshiba Corp | ガスタービン燃料供給装置 |
JPH1122490A (ja) * | 1997-07-07 | 1999-01-26 | Mitsubishi Heavy Ind Ltd | パイロット比自動調整装置 |
Also Published As
Publication number | Publication date |
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US20060005526A1 (en) | 2006-01-12 |
DE10393442T5 (de) | 2006-01-12 |
CN1703574A (zh) | 2005-11-30 |
JP2004132255A (ja) | 2004-04-30 |
CN100360776C (zh) | 2008-01-09 |
US7191588B2 (en) | 2007-03-20 |
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