WO2014092185A1 - マルチ燃料対応のガスタービン燃焼器 - Google Patents
マルチ燃料対応のガスタービン燃焼器 Download PDFInfo
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- WO2014092185A1 WO2014092185A1 PCT/JP2013/083497 JP2013083497W WO2014092185A1 WO 2014092185 A1 WO2014092185 A1 WO 2014092185A1 JP 2013083497 W JP2013083497 W JP 2013083497W WO 2014092185 A1 WO2014092185 A1 WO 2014092185A1
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- fuel
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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
- 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
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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
- F02C7/228—Dividing fuel between various burners
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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
- 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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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
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/9901—Combustion process using hydrogen, hydrogen peroxide water or brown gas as fuel
Definitions
- the present invention relates to a multi-fuel compatible gas turbine combustor that can effectively use unused fuel such as hydrogen-containing fuel while ensuring low emission performance.
- Gas turbine engine combustors are produced by mixing fuel and compressed air in addition to wet-type combustors that inject water or steam into the combustor as a technology for obtaining low emission performance including low NOx enrichment.
- a DLE (Dry Low Emissions) combustor that is a dry type in which a premixed gas is injected into a combustion chamber to cause lean premix combustion.
- fuel for this DLE combustor fuel such as natural gas, kerosene, light oil, etc. having a characteristic range suitable for generating a premixed gas is used, and gas such as hydrogen is out of the characteristic range. It is difficult to use.
- hydrogen gas has a high combustion speed, so if it is mixed with a large amount of DLE combustor fuel, the flame goes back to a relatively long premixing passage, and this phenomenon is called backfire that causes heating and damage. May occur or abnormal combustion may occur.
- the porous coaxial jet burner of Patent Document 1 has a complicated structure, and in order to maintain good low emission performance, for example, the fuel distribution to a plurality of fuel nozzles is changed according to the ratio of the hydrogen concentration. The control becomes complicated, such as the need to make it.
- hydrogen gas is introduced from a reheating burner as in the combustor of Patent Document 2
- the main burner is a premixed combustion system
- there is little NOx so the action of reducing NOx with hydrogen gas is limited. is there. Therefore, in patent document 2, the case where the main burner of a premixed combustion system is used is not assumed. Therefore, Patent Document 2 does not suggest the combined use of the premixed combustion method and the method of introducing hydrogen gas from the reheating burner.
- the present invention is a multi-fuel compatible gas that can sufficiently utilize various fuels having characteristics outside the premixing characteristic range suitable for premixed gas generation while maintaining good low emission performance by premixed combustion.
- An object is to provide a turbine combustor.
- a multi-fuel compatible gas turbine combustor supplies a premixed gas containing a premixed first fuel to a first combustion region in a combustion chamber and performs premixed combustion.
- a main burner, and a reheating burner for supplying a second refueling fuel having a composition different from that of the first fuel to the second combustion region downstream of the first combustion region in the combustion chamber to perform diffusion combustion The first fuel has a premix characteristic range suitable for generating premixed gas, and the second fuel has a characteristic deviating from the premix characteristic range.
- a first fuel having a premix characteristic range suitable for generating a premixed gas is supplied to a main burner that supplies the premixed gas to the first combustion region and performs premixed combustion.
- the second fuel is supplied from the additional burner to the second combustion region.
- the additional burner is of the diffusion combustion type. Therefore, even if the second fuel having a characteristic out of the premixed characteristic range suitable for generating the premixed gas is supplied, backfire, abnormal combustion, misfire or the like does not occur. Therefore, as the second fuel, various fuels that are not currently used effectively, such as by-product hydrogen gas generated from petrochemical plants, refining plants, steelmaking facilities, and low-concentration fuel gas such as VAM can be sufficiently used. .
- premix characteristic range suitable for generating premixed gas here refers to the range of combustion speed at which backfire does not occur in the premixed passage, The range of the calorific value where no overheating occurs is included.
- “Different composition” means that the main component or element content is different.
- Diffusion combustion has a more stable flame than premixed combustion with a large air-fuel ratio, so in addition to being used at the start of gas turbines and at low loads, a small amount of combustion at high loads also prevents misfires.
- the premixed combustion can be stably maintained.
- the present invention it is preferable to further include an additional burner for supplying the first fuel also to the second combustion region for combustion.
- an additional burner for supplying the first fuel also to the second combustion region for combustion.
- hydrogen can be used as the second fuel.
- hydrogen gas generated from a chemical plant or the like can be effectively used as fuel for the combustor.
- natural gas can be used as the first fuel, and hydrogen or a hydrogen-containing gas can be used as the second fuel.
- hydrogen or a hydrogen-containing gas can be used as the second fuel.
- a combustion cylinder that forms the combustion chamber, and an introduction pipe that is provided in the combustion cylinder and introduces air from the outside of the combustion cylinder to an internal combustion chamber
- the reheating burner includes the introduction cylinder It is good also as a structure inserted in the hollow part of the pipe. By introducing air, the concentration of hydrogen is lowered and the combustion temperature is lowered. As a result, the amount of NOx generated can be suppressed.
- the second fuel for replenishment can be lean-burned in the second combustion region.
- the NOx generation amount can be further reduced.
- lean combustion refers to burning with a leanness of an equivalence ratio of 0.5 or less. Note that the equivalence ratio in the lean combustion is adjusted in accordance with the load within a range of more than 0 and 0.5 or less.
- FIG. 1 is a schematic longitudinal sectional view showing a gas turbine combustor according to a first embodiment of the present invention including a fuel supply system thereof. It is a characteristic view which shows the relationship between the load fluctuation
- the gas turbine engine GT to which the gas turbine combustor is applied is a single can type as shown in FIG. 1, but may be a multi can type.
- the gas turbine engine GT includes a centrifugal compressor 1 that compresses air A taken in from an air inlet 1a, a combustor 2 that supplies fuel to the compressed air A and burns it, and combustion gas from the combustor 2 And a turbine 3 driven by The combustor 2 is disposed so as to protrude substantially in the radial direction with respect to the engine rotation axis C.
- Combustion gas generated in the combustor 2 is guided to the turbine 3 to rotate the turbine 3, and drives the centrifugal compressor 1 connected to the turbine 3 by the rotating shaft 4 and a load 7 that is a generator, for example. To do.
- the exhaust gas EG that has passed through the turbine 3 is discharged from the exhaust duct 8 to the outside.
- the combustor 2 includes a reverse flow in which the compressed air A and the combustion gas G introduced into the air passage 22 from the centrifugal compressor 1 (FIG. 1) flow in opposite directions in the combustor 2.
- It is a can type, and a substantially cylindrical combustion cylinder 9 is accommodated in a cylindrical housing H.
- An air passage 22 for introducing the air A from the centrifugal compressor 1 is formed between the housing H and the combustion cylinder 9, and a combustion chamber 10 is formed inside the combustion cylinder 9.
- a burner unit (nozzle unit) 11 is attached to the top of the combustion cylinder 9.
- the burner unit 11 uses, as the first fuel F1, a fuel such as natural gas, natural gas mixed with about 5% hydrogen, or a liquid fuel such as kerosene or light oil.
- the burner unit 11 is configured to inject a premixed gas M including a first fuel F1 for premixing supplied from a first fuel supply source 18 into a first combustion region S1 in the combustion chamber 10 for premixed combustion.
- a burner 12 and a pilot burner 13 that directly injects the first fuel F1 into the first combustion region S1 and performs diffusion combustion are provided.
- the combustion cylinder 9 is directly injected with the second fuel F2 for replenishment supplied from the second fuel supply source 19 to the second combustion region S2 downstream of the first combustion region S1 in the combustion chamber 10.
- a diffusion injection type reheating burner 20 for diffusion combustion is provided.
- a plurality of, for example, 2 to 12 tracking burners 20 are provided at equal intervals in the circumferential direction of the combustion cylinder 9.
- the second fuel F2 in addition to natural gas, hydrogen gas, LPG (liquefied petroleum gas), VAM, a gas in which a large amount of hydrogen is mixed with natural gas, etc., the composition differs from natural gas, that is, the main component or element content is Use different fuels.
- hydrogen gas and LPG are main components are different
- VAM is the main component is the same with methane, such as rich in CO 2, which differences containing chamber of carbon and hydrogen.
- the combustion cylinder 9 is provided with a plurality of cylindrical introduction pipes 25 for introducing the air A into the combustion chamber 10 from the air passage 22 outside the combustion cylinder 9. Has been inserted.
- the air A flows from the outside of the combustion cylinder 9 toward the internal combustion chamber 10 through the gap between the reheating burner 20 and the inner peripheral surface of the introduction pipe 25.
- the main burner 12 is disposed so as to surround the outer periphery of the pilot burner 13.
- the main burner 12 has an annular outer wall 121 and an inner wall 122 having an L-shaped cross section, and a premixing passage 14 is formed between the outer wall 121 and the inner wall 122.
- the upstream end of the premixing passage 14 opens outward in the radial direction, and a plurality of main fuel nozzles 17 are equidistantly spaced in the circumferential direction of the main burner 12 outward of the opened annular air inlet 14a. Is arranged in.
- a plurality of fuel injection holes (not shown) for injecting the first fuel F1 toward the air intake port 14a are formed in a portion of the main fuel nozzle 17 facing the air intake port 14a, and the air intake port 14a. Is provided with a swirler 21 that swirls the inflowing air to promote premixing with the first fuel F1.
- the diffusion combustion type pilot burner 13 is disposed in the inner space of the outer wall 121.
- the first fuel F1 supplied from the first fuel supply source 18 is injected from the main fuel nozzle 17 toward the air intake port 14a of the premixing passage 14 after the flow rate is adjusted by the first fuel control valve 23. .
- the injected first fuel F1 is introduced into the premixing passage 14 while being swirled by the swirler 21 together with the compressed air A flowing from the air passage 22 into the air intake port 14a.
- a premixed gas outlet 2 that is premixed while flowing 4 is injected into the combustion chamber 10 as a premixed gas M.
- the first fuel control valve 23 When the gas turbine engine GT is started, the first fuel control valve 23 is closed, only the second fuel control valve 27 is opened, and the first fuel F1 of the first fuel supply source 18 turns the second fuel control valve 27 on.
- the fuel is injected from the pilot burner 13 into the combustion chamber 10 and diffused and burned by ignition by a spark plug (not shown).
- the premixed gas M injected from the main burner 12 into the combustion chamber 10 is premixed and combusted using the flame as a seed flame, In the upstream portion of the combustion chamber 10, a first combustion region S1 is formed.
- the main burner 12 and the pilot burner 13 are controlled so that the air-fuel ratio (air flow rate / fuel flow rate) becomes a preferable predetermined value.
- the premix characteristic range includes a combustion speed range in which no backfire occurs in the relatively long premix passage 14 and a heat generation range in which combustion at a small amount and overheating at a large amount do not occur. Both are included.
- the range of the burning rate Mcp is about 32 to 39 cm / s
- the range of the calorific value is about 29 to 42 MJ / m 3 N.
- the second fuel F ⁇ b> 2 supplied from the second fuel supply source 19 and injected from the refueling burner 20 is diffusely burned, thereby causing the second combustion.
- Region S2 is formed. Since the second fuel F2 is directly injected from the diffusion combustion type reheating burner 20 and is diffusively burned, even if the flow rate fluctuates, backfire or the like into the premixing passage 14 does not occur. Even if a fuel having a characteristic out of the premix characteristic range of the first fuel F1 is used as the second fuel F2, no problem occurs.
- the second fuel F2 can be used even if it has a component that changes or is of low quality.
- the second combustion region S2 is formed in order to expand the operating range to the high output side according to the fluctuation of the operating load of the gas turbine engine GT, and as shown in FIG. 3, the operation of the gas turbine engine GT is performed.
- the third fuel control valve 28 in FIG. Two fuels F ⁇ b> 2 are supplied to the reheating burner 20 through the mixer 29 and the third fuel control valve 28.
- the amount of use of the second fuel F2 increases as the operating load of the engine GT increases, so that the combustor removes hydrogen gas or the like that is not fully utilized at that time under a high load. 2 can be used in large quantities as fuel.
- the flame holding performance of the first combustion region S1 is ensured by the main burner 12 and the pilot burner 13 regardless of the amount of the second fuel F2 supplied in the second combustion region S2.
- the fourth fuel control valve 30 is opened and the first fuel F 1 of the first fuel supply source 18 is supplied to the second fuel supply source 19 side through the check valve 31. Then, the first fuel F 1 and the second fuel F 2 from the second fuel supply source 19 are mixed by the mixer 29 and supplied to the reheating burner 20. The second fuel F2 is prevented from flowing into the first fuel F1 by the check valve 31.
- the concentration of hydrogen from the reheating burner 20 is reduced to become a lean combustion state, and the combustion temperature is lowered.
- the amount of NOx generated can be suppressed. Since the hydrogen gas is diluted with air, the reduction action is weak, but the amount of NOx generated in the first combustion region S1 in which premixed combustion is performed is small, so the effect of reducing NOx due to the reduction action of hydrogen gas is expected. Not done. Even if the introduction pipe 25 is not used, at least one air introduction hole for introducing the compressed air A in the air passage 22 into the combustion chamber 10 is formed in the vicinity of the reheating burner 20 in the combustion cylinder 9. In this way, lean combustion can be realized.
- FIG. 4 shows a second embodiment of the present invention.
- the gas turbine combustor 2A of the second embodiment is different from the gas turbine combustor of FIG. 2 in that an additional reheating burner is provided in the vicinity of the normal reheating burner 20 in the combustion cylinder 9 of the first embodiment. 33 is provided.
- a fuel supply system branched from the fuel supply system to the main burner 12 and provided with the fifth fuel control valve 34 is connected to the reheating burner 33. Then, if necessary, the fifth fuel control valve 34 is opened, and the first fuel F1 of the fuel supply system of the main burner 12 is injected from the additional combustion burner 33 into the second combustion region S2.
- the same number of additional burner burners 33 as the normal burner burners 20 are provided, and are provided at equal intervals so that the positions of the normal burner burners 20 and the circumferential direction are alternately arranged.
- the four additional burner burners 20 provided on the same circle at intervals of 90 degrees are arranged upstream or downstream.
- four additional burner burners 33 are arranged at 90 ° intervals on the same circle with a 45 ° phase shift.
- hydrogen gas as the second fuel F2 is used due to the operation stop of the chemical plant or the like.
- the fifth fuel control valve 34 is opened, and the first fuel F1 diverted from the fuel supply system of the main burner 12 is injected into the combustion chamber 10 through the additional burner 33.
- the second combustion region S2 can be stably maintained.
- both the normal reheating burner 20 and the additional reheating burner 33 are operated to supply the first fuel F1 and the second fuel F2 into the combustion chamber 10.
- the ordinary reheating burner 20 When natural gas is used as the first fuel, the ordinary reheating burner 20 is set to a small burner diameter corresponding to natural gas having a small volume.
- the volume per unit calorie of hydrogen gas is larger than that of natural gas, the required amount cannot be injected when the ordinary reheating burner 20 is used for the injection of hydrogen gas.
- the additional burner 33 for hydrogen gas since the additional burner 33 for hydrogen gas is provided, by setting the additional burner 33 to a large burner diameter corresponding to the volume of hydrogen gas, When the hydrogen gas as the second fuel F2 is injected, a necessary amount can be injected.
- the second fuel F2 that does not adversely affect the low emission performance of the main burner 12 is shown.
- the ratio is about 30% of the whole in terms of calorie.
- the second fuel F2 injected from the ordinary reheating burner 20 is 100% hydrogen gas, and the calorific value of the hydrogen gas is natural gas that is the first fuel F1.
- the volume ratio of the first fuel F1 (natural gas) to the second fuel F2 (hydrogen gas) is 7:12 in terms of volumetric flow rate distribution. That is, the first fuel F1 is 36.84% (7/19) and the second fuel F2 is 63.15% (12/19).
- the upper limit of the mixing ratio of the second fuel F2 is considered in order to avoid backfire and abnormal combustion.
- more than 60% of the total fuel can be covered with hydrogen gas of the second fuel F2. Therefore, a large amount of hydrogen gas that could not be sufficiently used in the past can be effectively used as the second fuel of the gas turbine combustor 2A.
Abstract
Description
4から予混合気Mとして燃焼室10内に噴出される。
12 メインバーナ
13 パイロットバーナ
20 追焚きバーナ
25 導入パイプ
33 追加の追焚きバーナ
S1 第1燃焼領域
S2 第2燃焼領域
M 予混合気
Claims (7)
- 燃焼室内の第1燃焼領域に予混合用の第1燃料を含む予混合気を供給して予混合燃焼させるメインバーナと、
前記燃焼室内の前記第1燃焼領域よりも下流の第2燃焼領域に、前記第1燃料とは異なる組成の追焚き用の第2燃料を供給して拡散燃焼させる追焚きバーナとを備え、
前記第1燃料は、予混合気を生成するのに適した予混合特性範囲を有し、前記第2燃料は前記予混合特性範囲から外れた特性を有するガスタービン燃焼器。 - 請求項1に記載のガスタービン燃焼器において、さらに、前記第1燃料を前記第1燃焼領域に噴射して拡散燃焼させるパイロットバーナを備えたガスタービン燃焼器。
- 請求項1または2に記載のガスタービン燃焼器において、さらに、前記第1燃料を前記第2燃焼領域に供給して燃焼させる追加の追焚き用バーナを備えたガスタービン燃焼器。
- 請求項1から3のいずれか一項に記載のガスタービン燃焼器において、前記第2燃料は水素であるガスタービン燃焼器。
- 請求項1から3のいずれか一項に記載のガスタービン燃焼器において、前記第1燃料は天然ガスであり、前記第2燃料は水素または水素含有ガスであるガスタービン燃焼器。
- 請求項4または5に記載のガスタービン燃焼器において、前記燃焼室を形成する燃焼筒と、前記燃焼筒に設けられて前記燃焼筒の外部から内部の燃焼室に空気を導入する導入パイプとを備え、
前記追焚きバーナは、前記導入パイプの中空部に挿入されているガスタービン燃焼器。 - 請求項1から6のいずれか一項に記載のガスタービン燃焼器において、前記追焚き用の第2燃料は前記第2燃焼領域において稀薄燃焼されるガスタービン燃焼器。
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JP2014552101A JP6033887B2 (ja) | 2012-12-13 | 2013-12-13 | マルチ燃料対応のガスタービン燃焼器 |
CN201380065296.9A CN104870902A (zh) | 2012-12-13 | 2013-12-13 | 适合多种燃料的燃气轮机燃烧器 |
EP13862678.3A EP2933561A4 (en) | 2012-12-13 | 2013-12-13 | MULTI-FACTORY GAS TURBINE CHAMBER |
CA2894643A CA2894643A1 (en) | 2012-12-13 | 2013-12-13 | Multi-fuel-capable gas turbine combustor |
US14/736,571 US20150275755A1 (en) | 2012-12-13 | 2015-06-11 | Multi-fuel-capable gas turbine combustor |
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US14/736,571 Continuation US20150275755A1 (en) | 2012-12-13 | 2015-06-11 | Multi-fuel-capable gas turbine combustor |
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Also Published As
Publication number | Publication date |
---|---|
US20150275755A1 (en) | 2015-10-01 |
EP2933561A1 (en) | 2015-10-21 |
JP6033887B2 (ja) | 2016-11-30 |
CA2894643A1 (en) | 2014-06-19 |
EP2933561A4 (en) | 2016-08-24 |
CN104870902A (zh) | 2015-08-26 |
JPWO2014092185A1 (ja) | 2017-01-12 |
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