WO2013058209A1 - 希薄燃料吸入ガスタービン - Google Patents
希薄燃料吸入ガスタービン Download PDFInfo
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- WO2013058209A1 WO2013058209A1 PCT/JP2012/076596 JP2012076596W WO2013058209A1 WO 2013058209 A1 WO2013058209 A1 WO 2013058209A1 JP 2012076596 W JP2012076596 W JP 2012076596W WO 2013058209 A1 WO2013058209 A1 WO 2013058209A1
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- WIPO (PCT)
- Prior art keywords
- fuel
- gas
- concentration
- mixer
- gas turbine
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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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
- F02C3/22—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 gaseous at standard temperature and pressure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
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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
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23K—FEEDING FUEL TO COMBUSTION APPARATUS
- F23K5/00—Feeding or distributing other fuel to combustion apparatus
- F23K5/002—Gaseous fuel
- F23K5/007—Details
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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
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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
- F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/70—Application in combination with
- F05D2220/75—Application in combination with equipment using fuel having a low calorific value, e.g. low BTU fuel, waste end, syngas, biomass fuel or flare gas
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23K—FEEDING FUEL TO COMBUSTION APPARATUS
- F23K2400/00—Pretreatment and supply of gaseous fuel
- F23K2400/20—Supply line arrangements
- F23K2400/201—Control devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23K—FEEDING FUEL TO COMBUSTION APPARATUS
- F23K2900/00—Special features of, or arrangements for fuel supplies
- F23K2900/05004—Mixing two or more fluid fuels
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- 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
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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
- 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]
Definitions
- a low-calorie gas such as CMM (Coal Mine Methane) generated in a coal mine is mixed with air, for example, as an air-fuel mixture having a flammable limit concentration or less so as not to be ignited by compression in a compressor.
- CMM Coal Mine Methane
- the present invention relates to a lean fuel intake gas turbine that uses an inflammable component contained in an engine as fuel.
- VAM Vehicle Air Methane
- CMM Complementary Metal-Oxide-Memiconductor
- the mixer is disposed in the vicinity of the intake port in order to ensure responsiveness at the time of starting and load fluctuation. For this reason, the control operation cannot follow the fluctuation of the CMM fuel concentration due to the measurement delay of the CMM fuel concentration meter and the operation delay of the CMM fuel control valve, and if the fuel concentration becomes excessively high, an explosion occurs in the compressor. If it becomes lower, the catalytic combustor may misfire.
- an object of the present invention is to solve the above-mentioned problems, even when the fuel concentration of the fuel gas to be mixed fluctuates, the explosion in the compressor and the catalytic combustor are not stopped without stopping the operation of the gas turbine.
- An object of the present invention is to provide a lean fuel intake gas turbine capable of avoiding misfire and operating stably.
- a lean fuel intake gas turbine is a lean fuel intake gas turbine using a mixed gas of two or less different fuel concentrations as a working gas and a mixed gas having a combustible concentration limit or less.
- a compressor that compresses the working gas to generate a compressed gas; a catalytic combustor that combusts the compressed gas by a catalytic reaction; a turbine that is driven by the combustion gas from the catalytic combustor; A first mixer configured to generate a first mixed gas by mixing a first fuel gas having a low fuel concentration among fuel gases having different fuel concentrations with a second fuel gas having a high fuel concentration; A second mixer that further mixes the second fuel gas with the secondary mixed gas to generate a secondary mixed gas that is the working gas.
- the second fuel gas having a high fuel concentration can be mixed in two stages by the two mixers, the entire working gas can be prevented from changing in the fuel concentration of the second fuel gas. It becomes easy to adjust the density. Accordingly, even when the fuel concentration of the second fuel gas (for example, CMM) fluctuates, it is possible to avoid the explosion in the compressor and the misfire of the catalytic combustor and to stably operate.
- the fuel concentration of the second fuel gas for example, CMM
- the fuel concentration of the primary mixed gas generated by the first mixer is adjusted to a minimum concentration necessary for the gas turbine to drive a load, and the second mixing is performed. It is preferable to provide a control device that adjusts the fuel concentration of the secondary mixed gas generated by the vessel to a concentration necessary for obtaining the rated output of the gas turbine. According to this configuration, since the minimum necessary fuel concentration for driving the load is ensured in the first mixer, the second fuel flowing into the second mixer when the fuel concentration of the second fuel gas becomes high. Even if the flow rate of the fuel gas is reduced, the misfire of the catalytic combustor can be surely avoided. Therefore, it becomes possible to operate more stably against fluctuations in the fuel concentration of the second fuel gas.
- the distance of the fuel flow path from the first mixer to the second mixer is such that the first mixed gas flows into the fuel flow during a delay time of concentration adjustment by the control device. It is preferable that the distance is set larger than the distance traveled on the road. According to this configuration, when the fuel concentration fluctuation of the second fuel gas occurs, the first mixed gas of the first fuel gas and the second fuel gas generates the final working gas. Since concentration adjustment control can be performed before it reaches, explosion in the compressor and misfire of the catalytic combustor can be avoided more reliably.
- control device has means for regulating an upper limit value of a total flow rate of the second fuel gas mixed with the first fuel gas. According to this configuration, even if the fuel concentration of the second fuel gas rises rapidly, an explosion in the compressor can be reliably avoided.
- FIG. 1 is a block diagram showing a schematic configuration of a lean fuel intake gas turbine according to an embodiment of the present invention. It is a block diagram which shows schematic structure of the control apparatus of the gas turbine of FIG. It is a block diagram which shows schematic structure of the lean fuel intake gas turbine which concerns on the modification of embodiment of FIG. It is a block diagram which shows schematic structure of the lean fuel intake gas turbine which concerns on the other modification of embodiment of FIG.
- FIG. 1 is a schematic configuration diagram showing a lean fuel intake gas turbine GT according to an embodiment of the present invention.
- the gas turbine GT includes a compressor 1, a catalytic combustor 2 including a catalyst such as platinum or palladium, and a turbine 3.
- the load L like the generator 4 is driven by the output of the gas turbine GT.
- VAM generated in a coal mine
- CMM having a higher combustible component (methane) concentration
- the obtained working gas G1 is introduced into the gas turbine GT through the intake port of the compressor 1.
- the fuel gas supply system will be described in detail later.
- the working gas G 1 is compressed by the compressor 1, and the high-pressure compressed gas G 2 is sent to the catalytic combustor 2.
- the compressed gas G2 is combusted by a catalytic reaction by a catalyst such as platinum or palladium in the catalytic combustor 2, and a high-temperature / high-pressure combustion gas G3 generated thereby is supplied to the turbine 3 to drive the turbine 3.
- the turbine 3 is connected to the compressor 1 and the generator 4 via the rotary shaft 5, and the compressor 1 and the generator 4 are driven by the turbine 3.
- the gas turbine GT further includes a heat exchanger 6 that heats the compressed gas G2 introduced from the compressor 1 to the catalytic combustor 2 by the exhaust gas G4 from the turbine 3.
- the exhaust gas G5 flowing out from the heat exchanger 6 is silenced through a silencer (not shown) and then released to the outside.
- the configuration of the fuel supply system to the gas turbine GT will be described in detail.
- the fuel supply system uses a first fuel gas (VAM in this example) having a leaner methane concentration (usually about 0.5%) and a second fuel gas having a higher methane concentration (usually 20 to 30%).
- a fuel supply path 17 is provided.
- the mixing of the CMM from the fuel auxiliary supply path 17 to the fuel main supply path 13 is performed by mixing two mixers, that is, the first mixer 21 provided on the upstream side of the fuel main supply path 13 and the first mixer 21 in the fuel main supply path 13.
- the second mixer 23 is provided downstream of the first mixer 21 and in the vicinity of the intake port of the compressor 1.
- the first mixer 21 mixes the CMM having the high fuel concentration with the VAM having the low fuel concentration out of the two types of fuel gases having the different fuel concentrations to generate the first mixed gas G6.
- the two mixers 23 further mix CMM with the primary mixed gas to generate a secondary mixed gas that is the working gas G1.
- a first fuel control valve 27 for adjusting the flow rate of the CMM fuel is provided in the middle of the first connection path 25 that communicates the fuel sub-supply path 17 with the first mixer 21.
- a second fuel control valve 31 that similarly adjusts the flow rate of the CMM fuel is provided in the middle of the second connection path 29 that communicates with the two mixers 23.
- a fuel cutoff valve 33 that blocks the flow of the CMM fuel is provided on the upstream side of the branch point to the first connection path 25 in the fuel auxiliary supply path 17, a fuel cutoff valve 33 that blocks the flow of the CMM fuel is provided.
- first to third methane concentration meters 35, 37, and 39 for measuring the methane concentration are disposed on the downstream sides of the CMM supply source 15, the first mixer 21, and the second mixer 23, respectively. Yes.
- the concentration values detected by the first to third methane concentration meters 35, 37, 39 are sent to the control device 41. Further, the power generation output value of the generator 4 is also sent to the control device 41. The control device 41 adjusts the fuel cutoff valve 33, the first fuel control valve 27, and the second fuel control valve 31 based on these input values, thereby adjusting the concentration of fuel supplied to the intake inlet of the compressor 1. Control.
- the load L is driven by adjusting the opening of the first fuel control valve 27 based on the fuel concentration value detected by the second methane concentration meter 37.
- the minimum fuel concentration for example, 1%) necessary is controlled.
- the second mixer 23 adjusts the second fuel control valve 31 based on the generated power value and the fuel concentration value detected by the third methane concentration meter 39, so that the fuel necessary for generating the rated output is obtained. Control to a concentration (eg 2%).
- the opening degree of the second fuel control valve 31 is based on the generated power value.
- the control is performed based on the detected fuel concentration value of the third methane concentration meter 39. Switch to density control. Switching between the controls is performed by the changeover switch 43.
- control device 41 further regulates the upper limit value of the opening degree command for the first and second fuel control valves 27 and 31 as means for regulating the upper limit value of the total flow rate of the CMM mixed with the VAM.
- the limiter circuit 45 is provided.
- the limiter circuit 45 includes first and second limits according to the maximum fuel amount that does not cause an explosion in the compressor, calculated based on the measured values of the CMM fuel concentration, the VAM fuel concentration, and the gas turbine intake flow rate in the limit calculation circuit 47.
- the opening command for the fuel control valves 27 and 31 is controlled.
- the first mixer 21 and the second mixer It is preferable to arrange
- the flow path distance between the first mixer 21 and the second mixer 23 (the distance along the fuel main supply path 13) is the primary mixed gas during the delay time of the concentration adjustment by the control device 41.
- the distance G6 moves through the fuel flow path, that is, the flow path length calculated from the flow rate in the fuel main supply path 13, the cross-sectional area of the flow path, and the delay time of the fuel concentration control is set.
- the flow path distance between the first mixer 21 and the second mixer 23 is preferably in the range of 2 to 15 m, for example, and preferably in the range of 3 to 10 m. More preferably, it is in the range of ⁇ 7 m.
- the control device 41 maintains the minimum fuel concentration necessary for maintaining the power generation state in the first mixer 21 while maintaining the second mixer.
- the opening degree of the second fuel control valve 31 located upstream of 23 is reduced.
- the first mixer 21 is positioned upstream of the second mixer 23 while maintaining the minimum fuel concentration necessary to maintain the power generation state.
- the opening degree of the second fuel control valve 31 is increased.
- a bypass passage 51 from the fuel auxiliary supply passage 17 to the second mixer 23 is provided, and a bypass fuel cutoff valve 53 is provided in the middle of the bypass passage 51. May be. Since the opening / closing operation of the bypass fuel cutoff valve 53 is faster than the opening / closing operation of the second fuel control valve 31, an explosion in the compressor 1 is more effectively avoided when a sudden increase in the CMM fuel concentration occurs. be able to.
- a second fuel cutoff valve 61 may be provided as shown in FIG. 4 instead of the second fuel control valve 31 in FIG. 4 instead of the second fuel control valve 31 in FIG.
- the opening operation is performed to obtain the rated power generation output. Further, when the CMM concentration increases, the second fuel cutoff valve 61 is closed.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
- Exhaust Gas After Treatment (AREA)
- Feeding And Controlling Fuel (AREA)
- Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
Description
2 触媒燃焼器
3 タービン
4 発電機
11 VAM供給源
15 CMM供給源
21 第1混合器
23 第2混合器
27 第1燃料制御弁
31 第2燃料制御弁
41 制御装置
GT 希薄燃料吸入ガスタービン
L 負荷
Claims (4)
- 2種類の相異なる燃料濃度の燃料ガスを混合した可燃濃度限界以下の混合ガスを作動ガスとする希薄燃料吸入ガスタービンであって、
前記作動ガスを圧縮して圧縮ガスを生成する圧縮機と、
前記圧縮ガスを触媒反応によって燃焼させる触媒燃焼器と、
前記触媒燃焼器からの燃焼ガスによって駆動されるタービンと、
前記2種類の相異なる燃料濃度の燃料ガスのうちの燃料濃度の低い第1燃料ガスに燃料濃度の高い第2燃料ガスを混合して第1次混合ガスを生成する第1混合器と、
前記第1次混合ガスにさらに前記第2燃料ガスを混合して前記作動ガスである第2次混合ガスを生成する第2混合器と、
を備える希薄燃料吸入ガスタービン。 - 請求項1に記載の希薄燃料吸入ガスタービンにおいて、前記第1混合器が生成する第1次混合ガスの燃料濃度を、当該ガスタービンが負荷を駆動するために必要な最低限の濃度に調整し、前記第2混合器が生成する第2次混合ガスの燃料濃度を、当該ガスタービンの定格出力を得るために必要な濃度に調整する制御装置を備える希薄燃料吸入ガスタービン。
- 請求項2に記載の希薄燃料吸入ガスタービンにおいて、前記第1混合器から前記第2混合器までの燃料流路の距離が、前記制御装置による濃度調整の遅延時間の間に前記第1次混合ガスが前記燃料流路を移動する距離よりも大きく設定されている希薄燃料吸入ガスタービン。
- 請求項2に記載の希薄燃料吸入ガスタービンにおいて、前記制御装置が、前記第1燃料ガスに混合される前記第2燃料ガスの総流量の上限値を規制する手段を有する希薄燃料吸入ガスタービン。
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
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JP2013539632A JP5723455B2 (ja) | 2011-10-17 | 2012-10-15 | 希薄燃料吸入ガスタービン |
US14/349,392 US20140250892A1 (en) | 2011-10-17 | 2012-10-15 | Lean fuel intake gas turbine |
RU2014119193/06A RU2014119193A (ru) | 2011-10-17 | 2012-10-15 | Газовая турбина с питанием обедненным топливом |
CN201280048769.XA CN103857891B (zh) | 2011-10-17 | 2012-10-15 | 贫燃料吸入燃气轮机 |
AU2012327118A AU2012327118B2 (en) | 2011-10-17 | 2012-10-15 | Lean fuel intake gas turbine |
Applications Claiming Priority (2)
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JP2011227642 | 2011-10-17 | ||
JP2011-227642 | 2011-10-17 |
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WO2013058209A1 true WO2013058209A1 (ja) | 2013-04-25 |
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PCT/JP2012/076596 WO2013058209A1 (ja) | 2011-10-17 | 2012-10-15 | 希薄燃料吸入ガスタービン |
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US (1) | US20140250892A1 (ja) |
JP (1) | JP5723455B2 (ja) |
CN (1) | CN103857891B (ja) |
AU (1) | AU2012327118B2 (ja) |
RU (1) | RU2014119193A (ja) |
WO (1) | WO2013058209A1 (ja) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2015140661A (ja) * | 2014-01-27 | 2015-08-03 | 三菱重工業株式会社 | 燃料供給装置、燃焼器、ガスタービン、及び燃料供給方法 |
JP2019107601A (ja) * | 2017-12-18 | 2019-07-04 | 三菱重工機械システム株式会社 | 液体混合装置 |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2014129254A (ru) * | 2011-12-22 | 2016-02-20 | Кавасаки Дзюкогё Кабусики Кайся | Способ работы газотурбинного двигателя с питанием обедненным топливом и электрогенераторное устройство на основе газовой турбины |
CH708276A1 (de) * | 2013-07-04 | 2015-01-15 | Liebherr Machines Bulle Sa | Gasmotor. |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6269625B1 (en) * | 1999-09-17 | 2001-08-07 | Solo Energy Corporation | Methods and apparatus for igniting a catalytic converter in a gas turbine system |
JP2011196355A (ja) * | 2010-03-24 | 2011-10-06 | Kawasaki Heavy Ind Ltd | 希薄燃料吸入ガスタービン |
Family Cites Families (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4472935A (en) * | 1978-08-03 | 1984-09-25 | Gulf Research & Development Company | Method and apparatus for the recovery of power from LHV gas |
WO1996014370A2 (en) * | 1994-10-27 | 1996-05-17 | Isentropic Systems Ltd. | Improvements in the combustion and utilisation of fuel gases |
US5993192A (en) * | 1997-09-16 | 1999-11-30 | Regents Of The University Of Minnesota | High heat flux catalytic radiant burner |
AU2341100A (en) * | 1998-08-17 | 2000-04-17 | Ramgen Power Systems, Inc. | Apparatus and method for fuel-air mixing before supply of low pressure lean pre-mix to combustor |
US6205768B1 (en) * | 1999-05-05 | 2001-03-27 | Solo Energy Corporation | Catalytic arrangement for gas turbine combustor |
US6578559B2 (en) * | 2000-08-31 | 2003-06-17 | Hadoga Industries, Inc. | Methane gas control system |
US6464210B1 (en) * | 2002-03-22 | 2002-10-15 | Agrimond, Llc | Fluid dissolution apparatus |
US6779333B2 (en) * | 2002-05-21 | 2004-08-24 | Conocophillips Company | Dual fuel power generation system |
AU2002951703A0 (en) * | 2002-09-27 | 2002-10-17 | Commonwealth Scientific And Industrial Research Organisation | A method and system for a combustion of methane |
UA78460C2 (en) * | 2003-06-13 | 2007-03-15 | Kawasaki Heavy Ind Ltd | Electric power supply system |
US7395670B1 (en) * | 2005-02-18 | 2008-07-08 | Praxair Technology, Inc. | Gas turbine fuel preparation and introduction method |
JP2006233920A (ja) * | 2005-02-28 | 2006-09-07 | Mitsubishi Heavy Ind Ltd | 燃料ガスカロリー制御装置及びガスタービンシステム |
JP4563242B2 (ja) * | 2005-04-19 | 2010-10-13 | 三菱重工業株式会社 | 燃料ガスカロリ制御方法及び装置 |
US7464555B2 (en) * | 2005-05-05 | 2008-12-16 | Siemens Energy, Inc. | Catalytic combustor for integrated gasification combined cycle power plant |
US7787997B2 (en) * | 2006-04-28 | 2010-08-31 | Caterpillar | Modular electric power generation system and method of use |
US7921651B2 (en) * | 2008-05-05 | 2011-04-12 | General Electric Company | Operation of dual gas turbine fuel system |
JP4538077B2 (ja) * | 2008-06-13 | 2010-09-08 | 川崎重工業株式会社 | 希薄燃料吸入ガスタービン |
WO2010038290A1 (ja) * | 2008-10-01 | 2010-04-08 | 三菱重工業株式会社 | ガスタービン装置 |
US7895821B2 (en) * | 2008-12-31 | 2011-03-01 | General Electric Company | System and method for automatic fuel blending and control for combustion gas turbine |
US8490406B2 (en) * | 2009-01-07 | 2013-07-23 | General Electric Company | Method and apparatus for controlling a heating value of a low energy fuel |
US20100175379A1 (en) * | 2009-01-09 | 2010-07-15 | General Electric Company | Pre-mix catalytic partial oxidation fuel reformer for staged and reheat gas turbine systems |
US8117821B2 (en) * | 2009-02-11 | 2012-02-21 | General Electric Company | Optimization of low-BTU fuel-fired combined-cycle power plant by performance heating |
US8381506B2 (en) * | 2009-03-10 | 2013-02-26 | General Electric Company | Low heating value fuel gas blending control |
US8151740B2 (en) * | 2009-06-02 | 2012-04-10 | General Electric Company | System and method for controlling the calorie content of a fuel |
US8833052B2 (en) * | 2009-11-30 | 2014-09-16 | General Electric Company | Systems and methods for controlling fuel mixing |
US8650851B2 (en) * | 2010-01-05 | 2014-02-18 | General Electric Company | Systems and methods for controlling fuel flow within a machine |
US8627668B2 (en) * | 2010-05-25 | 2014-01-14 | General Electric Company | System for fuel and diluent control |
JP5211115B2 (ja) * | 2010-06-28 | 2013-06-12 | 三菱重工業株式会社 | ガスエンジンの給気冷却器のドレン装置 |
-
2012
- 2012-10-15 JP JP2013539632A patent/JP5723455B2/ja active Active
- 2012-10-15 WO PCT/JP2012/076596 patent/WO2013058209A1/ja active Application Filing
- 2012-10-15 RU RU2014119193/06A patent/RU2014119193A/ru not_active Application Discontinuation
- 2012-10-15 US US14/349,392 patent/US20140250892A1/en not_active Abandoned
- 2012-10-15 CN CN201280048769.XA patent/CN103857891B/zh not_active Expired - Fee Related
- 2012-10-15 AU AU2012327118A patent/AU2012327118B2/en not_active Ceased
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6269625B1 (en) * | 1999-09-17 | 2001-08-07 | Solo Energy Corporation | Methods and apparatus for igniting a catalytic converter in a gas turbine system |
JP2011196355A (ja) * | 2010-03-24 | 2011-10-06 | Kawasaki Heavy Ind Ltd | 希薄燃料吸入ガスタービン |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2015140661A (ja) * | 2014-01-27 | 2015-08-03 | 三菱重工業株式会社 | 燃料供給装置、燃焼器、ガスタービン、及び燃料供給方法 |
JP2019107601A (ja) * | 2017-12-18 | 2019-07-04 | 三菱重工機械システム株式会社 | 液体混合装置 |
Also Published As
Publication number | Publication date |
---|---|
AU2012327118B2 (en) | 2016-04-14 |
CN103857891B (zh) | 2016-03-02 |
RU2014119193A (ru) | 2015-11-27 |
AU2012327118A1 (en) | 2014-04-24 |
JPWO2013058209A1 (ja) | 2015-04-02 |
US20140250892A1 (en) | 2014-09-11 |
JP5723455B2 (ja) | 2015-05-27 |
CN103857891A (zh) | 2014-06-11 |
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