US20090249789A1 - Burner tube premixer and method for mixing air and gas in a gas turbine engine - Google Patents
Burner tube premixer and method for mixing air and gas in a gas turbine engine Download PDFInfo
- Publication number
- US20090249789A1 US20090249789A1 US12/099,241 US9924108A US2009249789A1 US 20090249789 A1 US20090249789 A1 US 20090249789A1 US 9924108 A US9924108 A US 9924108A US 2009249789 A1 US2009249789 A1 US 2009249789A1
- Authority
- US
- United States
- Prior art keywords
- fuel
- burner
- burner tube
- air
- slots
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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Classifications
-
- 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
-
- 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
- F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
Definitions
- the present invention relates to an air fuel mixer for the combustor of a gas turbine engine, and to a method for mixing air and fuel.
- the primary air polluting emissions usually produced by gas turbines burning conventional hydrocarbon fuels are oxides of nitrogen, carbon monoxide, and unburned hydrocarbons.
- the oxidation of molecular nitrogen in air breathing engines is highly dependent upon the maximum hot gas temperature in the combustion system reaction zone.
- the rate of chemical reactions forming oxides of nitrogen (NOx) is an exponential function of temperature. If the temperature of the combustion chamber hot gas is controlled to a sufficiently low level, thermal NOx will not be produced.
- One method of controlling the temperature of the reaction zone of a combustor below the level at which thermal NOx is formed is to premix fuel and air to a lean mixture prior to combustion.
- the thermal mass of the excess air present in the reaction zone of a lean premixed combustor absorbs heat and reduces the temperature rise of the products of combustion to a level where thermal NOx is not formed.
- the mixture of fuel and air exiting the premixer and entering the reaction zone of the combustor must be very uniform to achieve the desired emissions performance. If regions in the flow field exist where fuel/air mixture strength is significantly richer than average, the products of combustion in these regions will reach a higher temperature than average, and thermal NOx will be formed. This can result in failure to meet NOx emissions objectives depending upon the combination of temperature and residence time. If regions in the flow field exist where the fuel/air mixture strength is significantly leaner than average, then quenching may occur with failure to oxidize hydrocarbons and/or carbon monoxide to equilibrium levels. This can result in failure to meet carbon monoxide (CO) and/or unburned hydrocarbon (UHC) emissions objectives.
- CO carbon monoxide
- UHC unburned hydrocarbon
- a burner for use in a gas turbine engine comprises a burner tube having an inlet end and an outlet end; a plurality of slots formed in the burner tube and configured to introduce air flows tangentially into the burner tube and impart swirl to the air flows; a plurality of fuel passages extending axially along the burner tube; and a plurality of fuel injection holes provided to each fuel passage. At least one of the fuel injection holes of each fuel passage is configured to inject a fuel flow tangentially into the burner tube between air flows of adjacent slots to form a fuel and air co-flow.
- a method of mixing air and fuel in a burner of a gas turbine includes a burner tube comprising a plurality of slots formed in the burner tube.
- the method comprises introducing air flows tangentially into the burner tube through the slots and imparting swirl to the air flows; and injecting fuel between air flows of adjacent slots to form fuel and air co-flows.
- FIG. 1 schematically depicts a perspective of a burner according to an embodiment of the invention
- FIG. 2 schematically depicts a cross section of the burner of FIG. 1 along 2 - 2 ;
- FIG. 3 schematically depicts a cross section of the burner of FIG. 1 along 3 - 3 .
- a burner 2 comprises a burner tube 4 having an inlet end 6 and an outlet end 8 .
- a flange 10 is provided to the burner tube 4 for mounting the burner 2 into a gas turbine engine. It should be appreciated that the flange 10 may be integrally formed with the burner tube 4 , or may be provided separately. It should also be appreciated that other mounting arrangements may be provided for the burner 2 .
- a plurality of slots 12 are formed in the burner tube 4 . Air is introduced tangentially into the burner tube 4 through the slots 12 . Each slot 12 has a spiral, or swirling, configuration to impart swirl to combustion air entering the slot 12 .
- the burner tube 4 comprises a plurality of fuel passages 14 that extend axially along the burner tube 4 .
- a plurality of fuel injection holes 16 are provided to inject fuel tangentially into the burner tube 4 from the fuel passages 14 .
- the fuel passages 14 are formed in the burner tube 4 between an exterior wall 36 and an interior wall 30 .
- a converging central body 18 is provided in the burner tube 4 to accelerate the mixture of air and fuel along the axis of the burner tube 4 and to maintain no flow separation at the surface of the central body 18 .
- the central body 18 has a central body tip 32 adjacent to the outlet end 8 of the burner tube 4 .
- the central body 18 also comprises a central passage 20 to allow purge air to flow through the central body 18 to prevent flame holding at the central body 18 , for example at the central body tip 32 .
- the slots 12 each have a slot end 22 that is tangential to the axis 34 of the burner tube 4 to minimize disturbance in the mixing of the air and fuel.
- the injected fuel 24 is sandwiched between an air flow 26 from a slot 12 and air flow 28 from another slot 12 .
- the injected fuel 24 co-flows with the air flows 26 , 28 and is prevented from contacting the interior wall 30 of the burner tube 4 . This will eliminate jet cross flow, which tends to cause flame holding.
- the tangentially entered fuel and air co-flow layers then flow down axially with quick mixing and dump to the combustor for a stable premixed combustion.
- the fuel and air co-flows 24 , 26 , 28 radially enter the burner tube 4 .
- the radial entry of the co-flows 24 , 26 , 28 generates no wake domain inside the burner tube 4 and eliminates any potential flame holding spots.
- the radial fuel and air co-flows 24 , 26 , 28 also provide axial vortex breaking to ensure good fuel and air mixing.
- the slot ends 22 are configured to allow the air flows 26 , 28 to enter the burner tube 4 tangentially to the burner tube axis 34 and radially.
- the central body 18 prevents flame flashback at the center of the burner tube 4 and stabilizes the flame near the central body tip 32 .
- the burner 2 has simple geometry and may be manufactured at low cost.
- the burner 2 also provides high efficiency and low emission.
- the interior wall 30 of the burner tube 4 may also be protected by pure air or an air purge.
- the burner 2 also provides low air and fuel pressure drop and the gradual axial fuel injection avoids dynamics.
- the burner 2 may also be used with high hydrogen fuel and syngas.
- the length and width of the slots 12 , the number of fuel injection holes 16 , the diameter of the fuel injection holes 16 , the locations of the fuel injection holes 16 , and the surface profile of the central body 18 may be designed using Computational Fluid Dynamics (CFD) to provide desired, or enhanced, air/fuel mixing and to avoid autoignition and flame holding in the burner. It should also be appreciated that although the burner has been shown as including, for example, four slots, that any plural number of slots may be provided.
- CFD Computational Fluid Dynamics
Abstract
Description
- This invention was made with Government support under Contract No. DE-FC26-05NT42643 awarded by the Department of Energy. The Government has certain rights in this invention.
- The present invention relates to an air fuel mixer for the combustor of a gas turbine engine, and to a method for mixing air and fuel.
- Gas turbine manufacturers are regularly involved in research and engineering programs to produce new gas turbines that will operate at high efficiency without producing undesirable air polluting emissions. The primary air polluting emissions usually produced by gas turbines burning conventional hydrocarbon fuels are oxides of nitrogen, carbon monoxide, and unburned hydrocarbons. The oxidation of molecular nitrogen in air breathing engines is highly dependent upon the maximum hot gas temperature in the combustion system reaction zone. The rate of chemical reactions forming oxides of nitrogen (NOx) is an exponential function of temperature. If the temperature of the combustion chamber hot gas is controlled to a sufficiently low level, thermal NOx will not be produced.
- One method of controlling the temperature of the reaction zone of a combustor below the level at which thermal NOx is formed is to premix fuel and air to a lean mixture prior to combustion. The thermal mass of the excess air present in the reaction zone of a lean premixed combustor absorbs heat and reduces the temperature rise of the products of combustion to a level where thermal NOx is not formed.
- There are several problems associated with dry low emissions combustors operating with lean premixing of fuel and air in which flammable mixtures of fuel and air exist within the premixing section of the combustor, which is external to the reaction zone of the combustor. There is a tendency for combustion to occur within the premixing section due to flashback, which occurs when flame propagates from the combustor reaction zone into the premixing section and causes the flame to hold inside the wake flows behind the fuel injection columns (jet cross flow) or vane trailing edges, or autoignition, which occurs when the dwell time and temperature for the fuel/air mixture in the premixing section are sufficient for combustion to be initiated without an igniter. The consequences of combustion in the premixing section are degradation of emissions performance and/or overheating and damage to the premixing section, which is typically not designed to withstand the heat of combustion. Therefore, a problem to be solved is to prevent flashback or autoignition resulting in combustion within the premixer.
- In addition, the mixture of fuel and air exiting the premixer and entering the reaction zone of the combustor must be very uniform to achieve the desired emissions performance. If regions in the flow field exist where fuel/air mixture strength is significantly richer than average, the products of combustion in these regions will reach a higher temperature than average, and thermal NOx will be formed. This can result in failure to meet NOx emissions objectives depending upon the combination of temperature and residence time. If regions in the flow field exist where the fuel/air mixture strength is significantly leaner than average, then quenching may occur with failure to oxidize hydrocarbons and/or carbon monoxide to equilibrium levels. This can result in failure to meet carbon monoxide (CO) and/or unburned hydrocarbon (UHC) emissions objectives. Thus, another problem to be solved is to produce a fuel/air mixture strength distribution, exiting the premixer, which is sufficiently uniform to meet emissions performance objectives.
- Still further, in order to meet the emissions performance objectives imposed upon the gas turbine in many applications, it is necessary to reduce the fuel/air mixture strength to a level that is close to the lean flammability limit for most hydrocarbon fuels. This results in a reduction in flame propagation speed as well as emissions. As a consequence, lean premixing combustors tend to be less stable than more conventional diffusion flame combustors, and high level combustion driven dynamic pressure fluctuation (dynamics) often results. Dynamics can have adverse consequences such as combustor and turbine hardware damage due to wear or fatigue, flashback or blow out. Accordingly, another problem to be solved is to control the combustion dynamics to an acceptably low level.
- Lean, premixing fuel injectors for emissions abatement are in use throughout the industry, having been reduced to practice in heavy duty industrial gas turbines for more than two decades. A representative example of such a device is described in U.S. Pat. No. 5,259,184. Such devices have achieved progress in the area of gas turbine exhaust emissions abatement. Reduction of oxides of nitrogen, NOx, emissions by an order of magnitude or more relative to the diffusion flame burners of the prior art have been achieved without the use of diluent injection such as steam or water.
- As noted above, however, these gains in emissions performance have been made at the risk of incurring several problems. In particular, flashback and flame holding within the premixing section of the device result in degradation of emissions performance and/or hardware damage due to overheating. In addition, increased levels of combustion driven dynamic pressure activity results in a reduction in the useful life of combustion system parts and/or other parts of the gas turbine due to wear or high cycle fatigue failures. Still further, gas turbine operational complexity is increased and/or operating restrictions on the gas turbine are necessary in order to avoid conditions leading to high-level dynamic pressure activity, flashback, or blow out.
- In addition to these problems, conventional lean premixed combustors have not achieved maximum emission reductions possible with perfectly uniform premixing of fuel and air.
- According to one embodiment of the invention, a burner for use in a gas turbine engine comprises a burner tube having an inlet end and an outlet end; a plurality of slots formed in the burner tube and configured to introduce air flows tangentially into the burner tube and impart swirl to the air flows; a plurality of fuel passages extending axially along the burner tube; and a plurality of fuel injection holes provided to each fuel passage. At least one of the fuel injection holes of each fuel passage is configured to inject a fuel flow tangentially into the burner tube between air flows of adjacent slots to form a fuel and air co-flow.
- According to another embodiment of the invention, a method of mixing air and fuel in a burner of a gas turbine is provided. The burner includes a burner tube comprising a plurality of slots formed in the burner tube. The method comprises introducing air flows tangentially into the burner tube through the slots and imparting swirl to the air flows; and injecting fuel between air flows of adjacent slots to form fuel and air co-flows.
-
FIG. 1 schematically depicts a perspective of a burner according to an embodiment of the invention; -
FIG. 2 schematically depicts a cross section of the burner ofFIG. 1 along 2-2; and -
FIG. 3 schematically depicts a cross section of the burner ofFIG. 1 along 3-3. - Referring to
FIGS. 1-3 , aburner 2 comprises aburner tube 4 having aninlet end 6 and anoutlet end 8. Aflange 10 is provided to theburner tube 4 for mounting theburner 2 into a gas turbine engine. It should be appreciated that theflange 10 may be integrally formed with theburner tube 4, or may be provided separately. It should also be appreciated that other mounting arrangements may be provided for theburner 2. - A plurality of
slots 12 are formed in theburner tube 4. Air is introduced tangentially into theburner tube 4 through theslots 12. Eachslot 12 has a spiral, or swirling, configuration to impart swirl to combustion air entering theslot 12. As shown inFIG. 2 , theburner tube 4 comprises a plurality offuel passages 14 that extend axially along theburner tube 4. A plurality offuel injection holes 16 are provided to inject fuel tangentially into theburner tube 4 from thefuel passages 14. Thefuel passages 14 are formed in theburner tube 4 between anexterior wall 36 and aninterior wall 30. - Referring to
FIGS. 2 and 3 , a convergingcentral body 18 is provided in theburner tube 4 to accelerate the mixture of air and fuel along the axis of theburner tube 4 and to maintain no flow separation at the surface of thecentral body 18. Thecentral body 18 has acentral body tip 32 adjacent to theoutlet end 8 of theburner tube 4. Thecentral body 18 also comprises acentral passage 20 to allow purge air to flow through thecentral body 18 to prevent flame holding at thecentral body 18, for example at thecentral body tip 32. - Referring to
FIG. 3 , theslots 12 each have aslot end 22 that is tangential to theaxis 34 of theburner tube 4 to minimize disturbance in the mixing of the air and fuel. As shown inFIG. 2 , the injectedfuel 24 is sandwiched between anair flow 26 from aslot 12 andair flow 28 from anotherslot 12. The injectedfuel 24 co-flows with the air flows 26, 28 and is prevented from contacting theinterior wall 30 of theburner tube 4. This will eliminate jet cross flow, which tends to cause flame holding. The tangentially entered fuel and air co-flow layers then flow down axially with quick mixing and dump to the combustor for a stable premixed combustion. - The fuel and
air co-flows burner tube 4. The radial entry of the co-flows 24, 26, 28 generates no wake domain inside theburner tube 4 and eliminates any potential flame holding spots. The radial fuel andair co-flows burner tube 4 tangentially to theburner tube axis 34 and radially. Thecentral body 18 prevents flame flashback at the center of theburner tube 4 and stabilizes the flame near thecentral body tip 32. - The
burner 2 has simple geometry and may be manufactured at low cost. Theburner 2 also provides high efficiency and low emission. Theinterior wall 30 of theburner tube 4 may also be protected by pure air or an air purge. Theburner 2 also provides low air and fuel pressure drop and the gradual axial fuel injection avoids dynamics. Theburner 2 may also be used with high hydrogen fuel and syngas. - The length and width of the
slots 12, the number of fuel injection holes 16, the diameter of the fuel injection holes 16, the locations of the fuel injection holes 16, and the surface profile of thecentral body 18 may be designed using Computational Fluid Dynamics (CFD) to provide desired, or enhanced, air/fuel mixing and to avoid autoignition and flame holding in the burner. It should also be appreciated that although the burner has been shown as including, for example, four slots, that any plural number of slots may be provided. - While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (19)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/099,241 US20090249789A1 (en) | 2008-04-08 | 2008-04-08 | Burner tube premixer and method for mixing air and gas in a gas turbine engine |
JP2009024707A JP2009250604A (en) | 2008-04-08 | 2009-02-05 | Burner tube premixer and method for mixing air with gas in gas turbine engine |
FR0950762A FR2929688A1 (en) | 2008-04-08 | 2009-02-06 | BURNER TUBE PREMELANGER AND METHOD FOR MIXING AIR AND GAS IN A GAS TURBINE. |
DE102009003453A DE102009003453A1 (en) | 2008-04-08 | 2009-02-06 | Combustion tube premixer and method for gas / air mixture formation in a gas turbine |
CNA2009101307158A CN101556043A (en) | 2008-04-08 | 2009-02-09 | Burner tube premixer and method for mixing air and gas in a gas turbine engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/099,241 US20090249789A1 (en) | 2008-04-08 | 2008-04-08 | Burner tube premixer and method for mixing air and gas in a gas turbine engine |
Publications (1)
Publication Number | Publication Date |
---|---|
US20090249789A1 true US20090249789A1 (en) | 2009-10-08 |
Family
ID=41060748
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/099,241 Abandoned US20090249789A1 (en) | 2008-04-08 | 2008-04-08 | Burner tube premixer and method for mixing air and gas in a gas turbine engine |
Country Status (5)
Country | Link |
---|---|
US (1) | US20090249789A1 (en) |
JP (1) | JP2009250604A (en) |
CN (1) | CN101556043A (en) |
DE (1) | DE102009003453A1 (en) |
FR (1) | FR2929688A1 (en) |
Cited By (14)
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US20100175381A1 (en) * | 2007-04-23 | 2010-07-15 | Nigel Wilbraham | Swirler |
US20100180600A1 (en) * | 2009-01-22 | 2010-07-22 | General Electric Company | Nozzle for a turbomachine |
US20100186413A1 (en) * | 2009-01-23 | 2010-07-29 | General Electric Company | Bundled multi-tube nozzle for a turbomachine |
US20100192581A1 (en) * | 2009-02-04 | 2010-08-05 | General Electricity Company | Premixed direct injection nozzle |
CN102628593A (en) * | 2011-02-03 | 2012-08-08 | 通用电气公司 | Apparatus for mixing fuel in a gas turbine |
EP2808611A1 (en) * | 2013-05-31 | 2014-12-03 | Siemens Aktiengesellschaft | Injector for introducing a fuel-air mixture into a combustion chamber |
US8959921B2 (en) | 2010-07-13 | 2015-02-24 | General Electric Company | Flame tolerant secondary fuel nozzle |
US20150198095A1 (en) * | 2014-01-15 | 2015-07-16 | Delavan Inc. | Offset stem fuel distributor |
CN105318328A (en) * | 2015-01-15 | 2016-02-10 | 上海凌云瑞升燃烧设备有限公司 | Internal circulation multi-flame low nitrogen oxide (NOX) fuel gas burner |
US9267690B2 (en) | 2012-05-29 | 2016-02-23 | General Electric Company | Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same |
US20160290652A1 (en) * | 2013-11-12 | 2016-10-06 | Hanwha Techwin Co., Ltd. | Swirler assembly |
EP2719952A3 (en) * | 2012-10-09 | 2017-12-20 | General Electric Company | Fuel nozzle and method of assembling the same |
US11015808B2 (en) | 2011-12-13 | 2021-05-25 | General Electric Company | Aerodynamically enhanced premixer with purge slots for reduced emissions |
US20230130173A1 (en) * | 2020-07-17 | 2023-04-27 | Siemens Energy Global GmbH & Co. KG | Premixer injector assembly in gas turbine engine |
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US20110173983A1 (en) * | 2010-01-15 | 2011-07-21 | General Electric Company | Premix fuel nozzle internal flow path enhancement |
FR2955375B1 (en) * | 2010-01-18 | 2012-06-15 | Turbomeca | INJECTION DEVICE AND TURBOMACHINE COMBUSTION CHAMBER EQUIPPED WITH SUCH AN INJECTION DEVICE |
US8590311B2 (en) * | 2010-04-28 | 2013-11-26 | General Electric Company | Pocketed air and fuel mixing tube |
US20120058437A1 (en) * | 2010-09-08 | 2012-03-08 | General Electric Company | Apparatus and method for mixing fuel in a gas turbine nozzle |
JP6934359B2 (en) * | 2017-08-21 | 2021-09-15 | 三菱パワー株式会社 | Combustor and gas turbine with the combustor |
CN107631323B (en) * | 2017-09-05 | 2019-12-06 | 中国联合重型燃气轮机技术有限公司 | Nozzle for gas turbine |
CN109237472A (en) * | 2018-06-26 | 2019-01-18 | 天时燃烧设备(苏州)有限责任公司 | Tube assembly of burning and burner |
KR102607177B1 (en) * | 2022-01-28 | 2023-11-29 | 두산에너빌리티 주식회사 | Nozzle for combustor, combustor, and gas turbine including the same |
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- 2009-02-06 FR FR0950762A patent/FR2929688A1/en not_active Withdrawn
- 2009-02-06 DE DE102009003453A patent/DE102009003453A1/en not_active Withdrawn
- 2009-02-09 CN CNA2009101307158A patent/CN101556043A/en active Pending
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Cited By (21)
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US20100175381A1 (en) * | 2007-04-23 | 2010-07-15 | Nigel Wilbraham | Swirler |
US8297059B2 (en) | 2009-01-22 | 2012-10-30 | General Electric Company | Nozzle for a turbomachine |
US20100180600A1 (en) * | 2009-01-22 | 2010-07-22 | General Electric Company | Nozzle for a turbomachine |
US9140454B2 (en) | 2009-01-23 | 2015-09-22 | General Electric Company | Bundled multi-tube nozzle for a turbomachine |
US20100186413A1 (en) * | 2009-01-23 | 2010-07-29 | General Electric Company | Bundled multi-tube nozzle for a turbomachine |
US20100192581A1 (en) * | 2009-02-04 | 2010-08-05 | General Electricity Company | Premixed direct injection nozzle |
US8539773B2 (en) | 2009-02-04 | 2013-09-24 | General Electric Company | Premixed direct injection nozzle for highly reactive fuels |
US8959921B2 (en) | 2010-07-13 | 2015-02-24 | General Electric Company | Flame tolerant secondary fuel nozzle |
CN102628593A (en) * | 2011-02-03 | 2012-08-08 | 通用电气公司 | Apparatus for mixing fuel in a gas turbine |
US11015808B2 (en) | 2011-12-13 | 2021-05-25 | General Electric Company | Aerodynamically enhanced premixer with purge slots for reduced emissions |
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US11421884B2 (en) | 2011-12-13 | 2022-08-23 | General Electric Company | System for aerodynamically enhanced premixer for reduced emissions |
US9267690B2 (en) | 2012-05-29 | 2016-02-23 | General Electric Company | Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same |
EP2719952A3 (en) * | 2012-10-09 | 2017-12-20 | General Electric Company | Fuel nozzle and method of assembling the same |
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Also Published As
Publication number | Publication date |
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CN101556043A (en) | 2009-10-14 |
JP2009250604A (en) | 2009-10-29 |
DE102009003453A1 (en) | 2009-10-15 |
FR2929688A1 (en) | 2009-10-09 |
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