WO2010005120A1 - ガスタービンの運転制御装置 - Google Patents
ガスタービンの運転制御装置 Download PDFInfo
- Publication number
- WO2010005120A1 WO2010005120A1 PCT/JP2009/062934 JP2009062934W WO2010005120A1 WO 2010005120 A1 WO2010005120 A1 WO 2010005120A1 JP 2009062934 W JP2009062934 W JP 2009062934W WO 2010005120 A1 WO2010005120 A1 WO 2010005120A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- gas turbine
- ammonia
- fuel
- gas
- supplied
- Prior art date
Links
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/40—Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/24—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being liquid at standard temperature and pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N1/00—Regulating fuel supply
- F23N1/002—Regulating fuel supply using electronic means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/36—Supply of different fuels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2227/00—Ignition or checking
- F23N2227/02—Starting or ignition cycles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2237/00—Controlling
- F23N2237/08—Controlling two or more different types of fuel simultaneously
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2241/00—Applications
- F23N2241/20—Gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/32—Direct CO2 mitigation
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
- Y02T50/678—Aviation using fuels of non-fossil origin
Definitions
- thermal power plant can be cited as one that consumes a particularly large amount of stone fuel and emits a large amount of C.
- thermal power plants account for 70% of the world's electricity, but thermal power plants use natural gas, heavy oil, and coal stone fuel to produce large amounts of CO 2 day and night.
- steam turbines are mainly used for gas turbines as the power to turn generators at thermal power plants.
- the gas turbine is a seed of internal combustion engine.
- the gas turbine directly burns the material in the gas turbine to generate high temperature and high pressure. Move it to extract power.
- natural gas is mainly used as fuel for gas turbines.
- the turbine is a kind of engine, and fuel is burned in a boiler to generate high-temperature and high-pressure steam, and the turbine is driven by this steam to extract power.
- heavy oil and coal pulverized coal are used as fuel.
- water vapor is generated by the heat of the gas turbine, and the turbine is driven by this steam. Power is taken out from the gas turbine.
- ammonia in Japan, one of which is to use it in thermal power plants. If ammonia is used as a fuel at a power plant, CO is not cut out, so it is possible to reduce CO output. In addition, it will be possible to meet the future power demand without consuming fossil fuels. Therefore, it is clear that, in the gas turbine cabins of thermal power plants, ammonia is used as a fuel instead of the fossil fuel currently used as a fuel, thereby reducing CO production and fossil fuel costs. Is the purpose.
- ammonia contains a large amount of element as shown in molecule 8), and it becomes elemental when completely burned.
- ammonia is of a quality and does not burn easily.
- the minimum energy required for fire is 30 times 8 J gasoline.
- the degree of self is over 6500C, which is very fixed. Furthermore, even if it burns
- S degree of gasoline and flammable is also 5 to 28 very narrow. For this reason, ammonia is a very difficult quality to burn and has not been used as a fuel for gas turbines.
- the vaporization heat required for this conversion depends on the fuel. At atmospheric pressure, ammonia evaporates at 5 and changes from body to gas, but the heat of vaporization required at this time is very large, 37 Jk, which is 4 compared to gas and petroleum stone fuel. Since the heat of conversion of ammonia is so great, the combustion gas is cooled and the mixture cannot be given enough heat. For this reason, ammonia is insufficient and the gas mixture is greatly improved. Second, it is in the vicinity of ammonia. If the flammable range is wide, such as gas, it is possible to burn the aikia even if its properties are somewhat lost. However, ammonia
- An object of the present invention is to provide a gas turbine installation capable of stably starting, rotating and stopping the gas turbine even when ammonia is used as a material.
- the deterioration operation is an operation region in which ammonia conversion is incomplete when ammonia is supplied to the gas turbine as a material.
- the deterioration operation is an operation region in which the ambient temperature around the fuel where the fuel burns is lower than that during normal operation.
- the deteriorated operation is an operation region after the gas turbine is activated.
- the fuel is supplied to the gas turbine in an operating region where the fuel is supplied to the gas turbine as compared with the deteriorated operation and the normal operation.
- the deteriorated operation is an operation region before the gas turbine.
- the amount of fuel supplied to the gas turbine when changing the amount of fuel supplied to the gas turbine and the amount of fuel other than ammonia, the amount of fuel supplied to the gas turbine is gradually reduced and increased.
- ammonia is not supplied to the gas turbine in the deteriorated operation region.
- the gas tabine is supplied with a material other than the above-mentioned ammonia even during the rotation.
- an amount of the pre-ammonia corresponding to 3 to 3 of the heat quantity of the fuel is supplied to the gas turbine.
- the gas turbine includes combustion in which fuel and air are supplied and the aerated gas is combusted.
- It is equipped with a pilot that injects a diffusion charge into the aiki area and a plurality of main bodies that inject a precharge charge into the area, and ammonia is supplied to the gas turbine when the charge is higher than ammonia. Fired from the hole.
- the pilot hole always supplies more charge than the ammonia.
- the gas turbine includes combustion in which fuel and air are supplied and the aerated gas is combusted.
- combustion in which fuel and air are supplied and the aerated gas is combusted.
- the combination of fuel other than ammonia and fuel supplied to the gas turbine including a pilot that injects a diffusion charge into the area and a plurality of mains that inject preliminary charge into the area The fuel sprayed from the multiple main holes is switched on the main floor.
- thermo power plant having a gas tab that is controlled by the arrangement of the gas tab.
- a gas turbine installation capable of stably starting, operating and stopping the gas turbine.
- Fig. 4 is a side view of a gas turbine whose operation is controlled by a light fixture.
- 3 is the time chart of the amount of ammonia supplied and the amount of gas supplied during and after the movement of the gas turbine.
- 5 is the time chart of the ratio between the pilot fee and the main ammonia natural gas during and after the movement of the gas turbine.
- 6 is a time chart of the ratio between the pilot charge and the main ammonia natural gas before the gas tabine.
- Fig. 4 is a side view of a gas turbine whose operation is controlled by a light fixture.
- the gas turbine in the embodiment is used in a thermal power plant to drive a generator (not) in the gas turbine.
- ammonia is mainly used as the fuel, but it is basically the same as the construction of the gas tabin (below, gas gas tabin) using fossil fuel such as natural gas oil as the fuel of the gas tabin. .
- the gas tabine has an output 0, a casing 20, a compression 30, a combustion 40, and a tabine 50. 10 is housed in the case 20 and is rotatably supported with respect to the case 20.
- the casing 20 has an inlet 2 for sucking air into the casing 20 and 2 2 for discharging gas from the casing 20.
- 30 comprises the number 3 3 2 provided in the case 20 and arranged alternately. 3 is connected to casing 20 and compression 3 2 is connected to output 0.
- the tabine 50 is also arranged in the case 20 and includes a number of 5 52 arranged alternately.
- Tabin 5 is connected to casing 20 and turbine 52 is connected to output 0.
- the gas generated due to the aeration at 40 flows through the turbine 50, causing the turbine 52 to rotate relative to the turbine 5, and as a result, power is generated at the output 0. become.
- the air sucked from the inlet 2 of the casing 20 is first insulated by the compression 30. Air whose degree and power have been increased by 30
- combustion 40 Flows into combustion 40 and forms an air-fuel mixture with the material shot in combustion 40.
- This aerated gas burns in the combustion 40, becomes a high-temperature / pressure gas, flows into the tabine 50, and rotates the tabin 52 to generate power. In the power generation plant, this power is used to generate electricity by rotating the generator.
- the combustion 40 is the combustion 40 and shows the air and gas leakage.
- the combustion 40 includes the combustion 4 and the combustion 4 2 as the fuel 4.
- Pilot nozzles 43 are arranged on line 4, and a number of main nozzles 44 are arranged at angular intervals in the direction of pilot nozzles 43.
- the pilot nozzle 43 is piloted to the pilot nozzle 43.
- main nozzle 44 For supplying the main nozzle 44, and the main nozzle 44 is provided with a main bypass 44 for supplying the main nozzle 44.
- the air generated by 30 flows out of compression 30 as indicated by arrow A in 2. After flowing out of 30, it flows into the casing 20, flows from the mouth end of the combustion 4 into 4, and flows into the pilot nozzle 4 3 main nozzle 44.
- Pilot nozzle 43 The main nozzle 44 injects fuel to the inflowing air, and these nozzles 43 form aeration.
- the aerated gas emitted from the hole of the pilot nozzle 43 forms a pilot flame, and the aerated gas emitted from the hole of the main nozzle 44 contacts the pilot flame to form a flame and burns.
- the gas obtained by such an air-fuel mixture is supplied to the tabine 50 through the combustion 42, whereby the tabine 50 is rotated.
- ammonia is mainly used as fuel, so it is completely the same as the construction of a natural gas gas turbine. Absent.
- the construction of the gas tabine 40 is different from the combustion construction used in the natural gas gas turbine.
- the size of the nozzle that injects fuel is larger than that of natural gas gas turbines.
- the energy of the fuel is reduced to about half. Therefore, in order to obtain the same energy even if the fuel is changed, the supply time is approximately doubled.
- the fuel is theoretically completed. (Combustible) is smaller than natural gas. For this reason, even if the fuel is changed, in order to maintain the theory of Aiki, there is a lot of supply. Therefore, in order to be able to supply a large amount of fuel, it is necessary to increase the size of the nozzles for injecting fuel, particularly the pre-nozzles, and the number of nozzles.
- the composition of the gas tabine 40 is different from the composition of the gas gas turbine.
- ammonia is of a quality and does not burn easily.
- the stable and steady rotation of the gas turbine is performed when the gas turbine is rotating, that is, not when the gas turbine is moving or stopped.
- the fuel can be stably combusted by appropriately controlling the fuel supply amount and air supply amount, but the ammonia cannot be stably combusted during and before the gas turbine is moved.
- natural gas is supplied to the gas turbine, that is, 40 during and after the operation of the gas turbine, which is an operating region in which ammonia deteriorates as compared with the rotation of the gas turbine.
- the fuel is switched to natural gas ammonia after warming up.
- the combustion during and after the movement of the gas turbine that is, the ambient temperature of the fuel 4 (that is, the degree of combustion, the degree of compressed air, the degree of compressed gas,
- Time chart of gas supply amount of ammonia and gas supply amount As shown in Fig. 3, the ambient temperature in combustion 4 is lowered until the gas turbine is started at the time. In this state, when the gas turbine is started at the time, only natural gas is supplied to the gas turbine. Since gas is a combustible material compared to ammonia, it can be almost completely combusted even if the ambient temperature is low. Thus, by supplying only natural gas during and after operation of the gas turbine, the gas turbine can be operated satisfactorily.
- the gas turbine is driven by the natural gas, and as a result, the ambient temperature for the combustion 4 rises, and when the gas turbine is rotated, the ammonia gas
- the amount of gas supply to the gas turbine is started and the amount of ammonia supply to the gas turbine is started.
- the ambient temperature per combustion 4 is sufficiently high, even if ammonia is supplied to the gas turbine, it can be combusted satisfactorily without complete combustion of ammonia.
- the gas supply of the gas turbine is reduced to, and the supply of ammonia in the gas turbine is increased to, and eventually only ammonia is supplied to the gas turbine.
- the ambient temperature of all four is already high enough, so the ammonia can be burned well without incomplete combustion.
- the fuel to be supplied to the gas turbine Z is switched from ammonia to natural gas before the gas turbine, which is the operating area where ammonia is worse than when the gas turbine is rotating.
- the amount of ammonia supplied to the gas turbine is reduced to, and the amount of gas supplied to the gas turbine is increased to, and eventually only natural gas is supplied to the gas turbine Z. time ) .
- the speed of the gas turbine is started after only natural gas is supplied to the gas turbine. Since the gas turbine is operated by reducing the amount of natural gas supplied to the gas turbine, the ambient temperature of the combustion 4 gradually decreases with the speed of the gas turbine. When the gas supply to the gas turbine is finished, the gas turbine is stopped during 4). In this way, even if the ambient temperature for the combustion 4 is lowered, only natural gas is supplied to the gas turbine as the fuel, so that the supplied gas can be almost completely burned. Can be driven.
- the amount of ammonia is less than that during operation, before stopping, and when the gas turbine is rotating.
- the gas turbine can be operated satisfactorily in all regions while using ammonia as a material.
- conventional Ammonia which was never thought of as a gas for a turbine, can be used, which can contribute significantly to CO reduction and fossil fuels.
- the amount of fuel gas supplied to the gas turbine Z is increased in the combustion deterioration operating region as compared with the normal operation.
- the operation range before operation and stop is cited as the operation region where the ammonia deteriorates compared to when the gas tabine is rotated, but the operation that deteriorates combustion is not limited to these.
- ammonia is supplied as fuel, ammonia is only partially vaporized. If ammonia conversion is incomplete, complete combustion of ammonia is likely to occur, thus degrading ammonia.
- natural gas as fuel By using natural gas as fuel at such times, complete combustion of the fuel can be suppressed and the gas turbine can be operated satisfactorily.
- Such an operating range is also included during and after operation.
- an operating range where the ambient temperature around the ambient temperature of the combustion 4) is lower than when the gas turbine is rotating is an example of an operating region that deteriorates combustion.
- the ambient temperature is less than 4
- the ammonia is less likely to vaporize as described above. Ammonia worsens.
- Such operating ranges include both during and after operation.
- an operation area that deteriorates combustion is an operation where less fuel is supplied to the gas turbine Z than when the gas turbine is rotating. If the amount of fuel supplied to the gas turbine is small, the temperature of the combustion gas decreases due to the heat of conversion of the hydrogen ammonia, and the ambient temperature of the combustion 4 decreases. This will worsen the ammonia.
- natural gas as the fuel at this time, the complete combustion of the fuel can be suppressed and the gas turbine can be operated satisfactorily.
- Such operating range includes before operation.
- the gas may be continuously supplied by a gas corresponding to a very small amount, for example, 3 to the degree of heat of the body in preparation for the measurement state during operation. .
- a gas corresponding to a very small amount, for example, 3 to the degree of heat of the body in preparation for the measurement state during operation.
- This makes it possible to burn natural gas as a pilot burner, and can stably hold the flame as a nucleus, thereby preventing unexpected shutdown of the turbine.
- the nozzle that injects natural gas ammonia is a separate nozzle, this amount of material can cool the natural gas nozzle that is hot, so that the durability of the nozzle can be improved. It will be possible.
- the ratio of the fuel ammonia emitted from the nozzles 4 3 and 4 4 of the combustion 40 will be described.
- the following shows a case where a small amount of gas is continuously supplied when the gas turbine is rotated. 5 and 6 are respectively when It is a time chart of the rate of pilot charges and rates with main ammonia natural gas before and after.
- the natural nozzle 43 and the main nozzle 44 are both natural gas from the time, that is, until the ambient temperature from the beginning of the gas turbine is sufficiently high. Is injected. At this time, when a small amount of ammonia is injected, the ammonia is injected from the main nozzle 44.
- the amount of fuel ammonia emitted from the main nozzle 44 is gradually increased from when the ambient temperature of the four zones becomes sufficiently high until only the gas turbine ammonia is supplied.
- a mixture of natural gas and ammonia may be supplied to all the main nozzles 44, and the mixture of the ammonia may be gradually increased.
- the total amount of ammonia emitted from all the main nozzles 44 may be gradually increased.
- the fuel supplied every 40 may be switched to natural gas ammonia.
- the fuel sprayed from all the main nozzles 44 is ammonia.
- natural gas is injected from the nozzle 4 3 from time to time.
- the fuel sprayed from all the main nozzles 44 is natural gas, and the fuel sprayed from the pilot nozzle 43 is just a gas as it is, or a mixture of gas ammonia.
- the fuel injected from both nozzles 4 3 is switched from ammonia to natural gas in the reverse procedure after starting as shown in 6, and then supplied to the gas turbine.
- natural gas is used as a material other than ammonia, but oil and other fossil fuels can be used. If the material is other than ammonia, a material other than fossil fuel is used. Moyo.
- the gas turbine for other uses, for example, the gas turbine for pump operation, the vehicle, the aircraft, It can also be used to control gas turbines for ship movement.
- the tabine equipment provided with a tabine driven mainly by ammonia as a fuel is used as a gas turbine, but it is also possible to use such a turbine equipment as a turbine equipped with a boiler. It is. In place of the 40 in this combined gas turbine, fuel is delivered in the boiler.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN2009801354636A CN102149915A (zh) | 2008-07-11 | 2009-07-10 | 燃气轮机的运行控制装置 |
RU2011105003/06A RU2471082C2 (ru) | 2008-07-11 | 2009-07-10 | Система управления работой газотурбинного двигателя и тепловая электростанция, содержащая такую систему |
BRPI0915843A BRPI0915843A2 (pt) | 2008-07-11 | 2009-07-10 | sistema de controle operacional de turbina a gás |
US13/000,768 US20110100018A1 (en) | 2008-07-11 | 2009-07-10 | Operational control system of gas turbine |
EP09794558A EP2317098A1 (en) | 2008-07-11 | 2009-07-10 | Gas turbine operation-controlling device |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2008181751A JP5115372B2 (ja) | 2008-07-11 | 2008-07-11 | ガスタービンの運転制御装置 |
JP2008-181751 | 2008-07-11 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2010005120A1 true WO2010005120A1 (ja) | 2010-01-14 |
Family
ID=41507221
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2009/062934 WO2010005120A1 (ja) | 2008-07-11 | 2009-07-10 | ガスタービンの運転制御装置 |
Country Status (7)
Country | Link |
---|---|
US (1) | US20110100018A1 (ja) |
EP (1) | EP2317098A1 (ja) |
JP (1) | JP5115372B2 (ja) |
CN (1) | CN102149915A (ja) |
BR (1) | BRPI0915843A2 (ja) |
RU (1) | RU2471082C2 (ja) |
WO (1) | WO2010005120A1 (ja) |
Cited By (4)
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WO2012076496A1 (en) | 2010-12-07 | 2012-06-14 | Philip Morris Products S.A. | Method and apparatus for introducing objects into a continuous flow of material |
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WO2023162375A1 (ja) | 2022-02-25 | 2023-08-31 | 株式会社Ihi | 燃焼装置およびガスタービン |
WO2023181513A1 (ja) * | 2022-03-25 | 2023-09-28 | 株式会社Ihi | 燃焼システム |
KR102643208B1 (ko) * | 2022-03-28 | 2024-03-05 | 두산에너빌리티 주식회사 | 연소기용 노즐, 연소기 및 이를 포함하는 가스터빈 |
WO2024039828A1 (en) | 2022-08-18 | 2024-02-22 | L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude | Method for heating a reformer with an ammonia-fired burner producing a stable flame |
WO2024043268A1 (ja) * | 2022-08-25 | 2024-02-29 | 三菱パワー株式会社 | ガスタービン及びガスタービン設備 |
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Also Published As
Publication number | Publication date |
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RU2011105003A (ru) | 2012-08-20 |
JP2010019195A (ja) | 2010-01-28 |
EP2317098A1 (en) | 2011-05-04 |
US20110100018A1 (en) | 2011-05-05 |
JP5115372B2 (ja) | 2013-01-09 |
CN102149915A (zh) | 2011-08-10 |
BRPI0915843A2 (pt) | 2015-11-03 |
RU2471082C2 (ru) | 2012-12-27 |
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