EP2023041A1 - Vormischbrenner und Verfahren zum Betrieb eines Vormischbrenners - Google Patents

Vormischbrenner und Verfahren zum Betrieb eines Vormischbrenners Download PDF

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Publication number
EP2023041A1
EP2023041A1 EP07014820A EP07014820A EP2023041A1 EP 2023041 A1 EP2023041 A1 EP 2023041A1 EP 07014820 A EP07014820 A EP 07014820A EP 07014820 A EP07014820 A EP 07014820A EP 2023041 A1 EP2023041 A1 EP 2023041A1
Authority
EP
European Patent Office
Prior art keywords
fuel
injected
premixing zone
air
zone
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.)
Withdrawn
Application number
EP07014820A
Other languages
German (de)
English (en)
French (fr)
Inventor
Berthold Köstlin
Martin Lenze
Bernd Dr. Prade
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP07014820A priority Critical patent/EP2023041A1/de
Priority to JP2010517396A priority patent/JP2010534782A/ja
Priority to EP08786350A priority patent/EP2171353A1/de
Priority to US12/669,971 priority patent/US20100183991A1/en
Priority to PCT/EP2008/059658 priority patent/WO2009016079A1/de
Priority to CN2008801005344A priority patent/CN101765742B/zh
Publication of EP2023041A1 publication Critical patent/EP2023041A1/de
Withdrawn legal-status Critical Current

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Classifications

    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07002—Injecting inert gas, other than steam or evaporated water, into the combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07009—Injection of steam into the combustion chamber

Definitions

  • the present invention relates to a premix burner, in particular a synthesis gas premix burner, and a method of operating a premix burner.
  • Premix burners typically include a premix zone in which air and fuel are mixed before passing the mixture into a combustion chamber. There, the mixture burns, producing a hot gas under elevated pressure. This hot gas is forwarded to the turbine. In connection with the operation of premix burners, it is particularly important to keep the nitrogen oxide emissions low and to avoid a flashback.
  • Synthesis gas premix burners are characterized by the fact that synthesis gases are used as fuel in them. Compared with the traditional turbine fuels natural gas and petroleum, which consist essentially of hydrocarbon compounds, the combustible components of the synthesis gas are essentially carbon monoxide and hydrogen. Depending on the gasification process and the overall plant concept, the calorific value of the synthesis gas is about 5 to 10 times smaller than that of natural gas.
  • the quality of the mixture between synthesis gas and air at the flame front is an important influencing factor for avoiding temperature peaks and thus for minimizing the formation of thermal nitrogen oxides.
  • the main constituents of the synthesis gas are not only carbon monoxide and hydrogen but also inert fractions.
  • the inert fractions are nitrogen and / or water vapor and optionally carbon dioxide. Due to the low Heat value must therefore be introduced into the combustion chamber high volume flows of fuel gas. As a result, significantly larger injection cross sections are required for the combustion of low-calorie fuels, such as synthesis gases, than with conventional high-calorie combustion gases.
  • the air mass flow introduced into the combustion chamber is typically twisted by means of an air swirl generator.
  • the fuel is injected via one or more juxtaposed or successively arranged circular rows of holes.
  • EP 1 614 963 A1 In order to reduce nitrogen oxide emissions and to prevent flashbacks in the combustion of low calorific fuels for the operation of a gas turbine, a method is proposed in which a low calorific fuel is premixed with air in stages.
  • EP 1 507 120 A1 Specially designed to prevent flashbacks in EP 1 507 120 A1 proposed a gas turbine with an annular combustion chamber, in which a swirl grating is arranged in a combustion air inlet region around the entire circumference of the annular combustion chamber, whereby a higher flow rate of the incoming combustion air is achieved compared to individual air inlet regions, each with a swirl grating. This results in a higher safety against flashbacks and a lower tendency to form combustion oscillations.
  • the method of the invention relates to a premix burner comprising a premix zone.
  • a premix zone In the combustion chamber, an air mass flow and fuel is injected, whereby a potential H adoptedgas Wegström which can form.
  • the inventive method is characterized in that a non-fuel-containing fluid is injected downstream of the fuel injection in the premixing zone.
  • the fluid can be injected into the premixing zone along the surface of the premixing zone in the main flow direction which is located in the potential hot gas backflow region.
  • the injection of a fluid along the component surface in the main flow direction prevents the actual formation of the H.gas Wegström capablees and / or diluted and cools the local fuel-air mixture from such that no ignition conditions prevail.
  • the fuel can in particular be injected perpendicular to the main flow direction of the air mass flow in the premixing zone, which is advantageous in terms of a thorough mixing of air and fuel.
  • the fuel can be injected via at least one swirl blade into the premixing zone.
  • the fuel may in particular also be a synthesis gas.
  • the fluid injected into the premixing zone along the surface located in the potential hot gas return flow region can be, for example, air or an inert gas.
  • Inert gases are gases that are very slow to react, meaning they participate in only a few chemical reactions.
  • carbon dioxide, water vapor, nitrogen, but also all noble gases can be used as the inert gas.
  • the use of an inert gas is particularly suitable if ignition conditions for highly flammable fuels should be avoided.
  • air of the air mass flow which is in any case supplied to the premixing zone.
  • a proportion of 10% of the total air supplied to the premixing zone can be branched off and injected into it along the surface of the premixing zone located in the potential hot gas backflow region.
  • the proportion of along The surface of the premixing zone located in the potential hot gas return flow area can be selected as desired.
  • the height of the preferably used portion of the air depends on the geometry of the premixing zone, on the velocity of the air mass flow and the velocity of the injected fuel.
  • the premix burner of the present invention includes a premix zone, an air swirler with an air supply, and one or more fuel nozzles.
  • the fuel can be injected through the fuel nozzles into a mass air flow that is twisted by the air swirler in the premixing zone, whereby a potential hot gas backflow region can form.
  • the premix burner according to the invention is characterized in that the premix zone surface in the potential H disclosegasgurström which has at least one opening through which a fluid can be injected into the premixing zone. In particular, there may be openings arranged so that the fluid can be injected in the main flow direction of the burner along the surface of the premixing zone.
  • the premixing zone surface has a plurality of openings in the hot gas backflow region.
  • the opening or the openings can advantageously be connected via a fluid channel with the leading to the air swirler air supply so be that through the opening part of the air can be injected as fluid into the combustion chamber.
  • the fuel nozzles may be located on the cone side and / or on the hub side of the premix zone.
  • the fuel nozzles are arranged in one or more consecutive rows downstream of the air swirler. This allows a graduated fuel injection.
  • the fuel nozzles and / or the openings may be located in the air swirler, preferably in at least one swirl vane.
  • the individual fuel nozzles can be designed, for example, as round bores. Another possibility is to design the fuel nozzles so that the fuel can be injected perpendicular to the main flow direction of the air mass flow into the combustion chamber, which promotes the mixing. Of course, the fuel can be injected at any other angle to the air mass flow.
  • the fuel used may in particular be a synthesis gas.
  • FIG. 1 1 schematically shows a section through a part of a conventional premix burner 1.
  • the premix burner 1 comprises inter alia a housing 7, a premix zone 2, an air swirler 10 and one or more fuel nozzles 11.
  • the premix zone 2 is arranged radially symmetrically about the center axis 12.
  • the outer side of the premixing zone 2 seen from the center axis 12 is referred to below as the cone side 3.
  • the side of the premixing zone 2 facing the center axis 12 is referred to below as the hub side 4.
  • an air mass flow 5 reaches the air swirler 10.
  • the air swirler 10 swirls the air mass flow 5 and forwards it into the premixing zone 2. From there, the air mass flow in the main flow direction 9 to the combustion chamber (not shown) forwarded.
  • One or more fuel nozzles 11 are located on the hub side 4 of the premixing zone 2.
  • fuel 6 directs fuel 6 perpendicular to the main flow direction 9 of the air mass flow 5 into the premixing zone 2. Downstream of the fuel nozzle 11 in the main flow direction 9 now forms a H disclosegasgurström which 8 from. Instead of a vertical injection to the main flow direction 9 of the air mass flow 5, the fuel 6 can be injected at any other angle to the main flow direction 9.
  • the flow direction of the injected fuel is indicated by arrows 6, the flow direction of the supplied air mass flow is indicated by arrows 5.
  • the Main flow direction in the interior of the premixing zone 2 is marked by arrows 9.
  • FIG. 2 the flow conditions in the interior of the premixing zone 2 are sketched schematically. You can see in FIG. 2 a plan view of the fuel nozzles 11 from the interior of the premixing zone 2 from.
  • the main flow direction of the air mass flow flowing past the fuel nozzles is indicated by arrows 9. Downstream of the fuel nozzles 11 in the main flow direction 9 now form H thoroughlygasgurström whiche 8 from.
  • the flow direction of the flowing back hot gas is indicated by arrows 13.
  • FIG. 3 schematically shows a section through a part of a premix burner according to the invention 1.
  • the premix burner 1 shown substantially corresponds to that or of the in connection with the in FIG. 1 shown premix burner.
  • the premix burner according to the invention comprises one or more fluid inlet openings 14 which are located downstream of the fuel nozzle or nozzles 11 in the main flow direction 9.
  • the fluid inlet openings 14 open into the premixing zone 2.
  • a fluid for example air or an inert gas
  • the direction of flow of the injected fluid is indicated by arrows 15. It runs within the premixing zone 2 substantially parallel to the main flow direction 9.
  • the injected fluid prevents the formation of a H disclosegas Wegström capablees, as in the associated with FIG. 1 described premix burner occurs.
  • FIG. 4 are the flow conditions inside the in FIG. 3 shown schematically schematically. you looks in FIG. 4 a plan view of the fuel nozzles 11 and the fluid inlet openings 14 seen from the premixing zone 2 from.
  • the main flow direction of the air flowing from the swirl generator 10 in the direction of the fuel nozzles 11 and the fluid inlet openings 14 is indicated by arrows 9.
  • the direction of flow of the fluid injected through the fluid inlet openings 14 is indicated by arrows 15.
  • the hot gas 13 is entrained in the main flow direction 9. A backflow of the hot gas 13 against the main flow direction 9 is effectively prevented in this way.
  • the fluid injected via the fluid inlet openings 14 is air which is connected to the air mass flow 5 via a fluid channel and branched off from it. It has been found favorable with regard to avoiding the hot gas backflow to supply about 5% to 20%, preferably 10%, of the total air supplied to the premix zone 2 via the fluid inlet openings 14 of the premix zone 2.
  • an inert gas for example carbon dioxide, water vapor or nitrogen, can alternatively be injected into the premixing zone 2 via the fluid inlet openings 14. But also the injection of a noble gas is possible in principle.
  • the fuel can optionally be injected perpendicular to the main flow direction 9 of the air mass flow 5 in the premixing zone 2, as in connection with FIG. 1 and FIG. 3 described or the fuel can be injected at any angle to the main flow direction 9 of the air mass flow in the premixing zone 2.
  • the fuel nozzles 11 can be located both on the cone side 3 and on the hub side 4 of the premixing zone 2 or in the swirl blades 17. In the event that the fuel nozzles 11 are located on the cone side 3 of the premixing zone 2, it is advantageous to place the fluid inlet openings 14 correspondingly on the cone side 3 as well.
  • the fluid inlet ports 14 should turn in the main flow direction 9 downstream of the fuel nozzles and allow injection of the fluid in the main flow direction 9.
  • the fuel nozzles 11 may be disposed in one or more rows one behind the other downstream of the air swirler 10. They can advantageously be designed as round holes.
  • the fuel injected by it may in particular also be a synthesis gas.
  • FIG. 5 schematically a section through a swirl blade 17 is shown.
  • the swirl blade 17 has in its interior a fuel flow channel 18 and a downstream of the main flow direction 9 fluid flow channel 19.
  • the fuel 6 is injected via the fuel flow channel 18 through fuel nozzles 11 from the swirl blade 17 into the premixing zone 2.
  • the fluid 15, which is preferably an inert gas, is injected via the fluid flow channel 19 through fluid inlet openings 20, 21, 22 into the premixing zone 2.
  • the fluid inlet openings 20, 21, 22 are located downstream of the fuel nozzles 11 in the main flow direction 9.
  • part of the fluid 15 is injected into the premixing zone 2 through fluid inlet openings 20, which are arranged downstream of the fuel nozzles 11, substantially in the direction opposite to the main flow direction 9.
  • fluid inlet openings 21 arranged further downstream of the fluid inlet openings 20
  • part of the fluid 15 is injected into the premixing zone 2 almost perpendicular to the main flow direction 9.
  • Downstream of the fluid inlet openings 21 further fluid inlet openings 22 are arranged through which a portion of the fluid 15 is injected into the premixing zone 2 substantially in the main flow direction 9.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP07014820A 2007-07-27 2007-07-27 Vormischbrenner und Verfahren zum Betrieb eines Vormischbrenners Withdrawn EP2023041A1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP07014820A EP2023041A1 (de) 2007-07-27 2007-07-27 Vormischbrenner und Verfahren zum Betrieb eines Vormischbrenners
JP2010517396A JP2010534782A (ja) 2007-07-27 2008-07-23 予混合バーナとその運転方法
EP08786350A EP2171353A1 (de) 2007-07-27 2008-07-23 Vormischbrenner und verfahren zum betrieb eines vormischbrenners
US12/669,971 US20100183991A1 (en) 2007-07-27 2008-07-23 Premixing burner and method for operating a premixing burner
PCT/EP2008/059658 WO2009016079A1 (de) 2007-07-27 2008-07-23 Vormischbrenner und verfahren zum betrieb eines vormischbrenners
CN2008801005344A CN101765742B (zh) 2007-07-27 2008-07-23 用于运行预混合式燃烧器的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07014820A EP2023041A1 (de) 2007-07-27 2007-07-27 Vormischbrenner und Verfahren zum Betrieb eines Vormischbrenners

Publications (1)

Publication Number Publication Date
EP2023041A1 true EP2023041A1 (de) 2009-02-11

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP07014820A Withdrawn EP2023041A1 (de) 2007-07-27 2007-07-27 Vormischbrenner und Verfahren zum Betrieb eines Vormischbrenners
EP08786350A Withdrawn EP2171353A1 (de) 2007-07-27 2008-07-23 Vormischbrenner und verfahren zum betrieb eines vormischbrenners

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08786350A Withdrawn EP2171353A1 (de) 2007-07-27 2008-07-23 Vormischbrenner und verfahren zum betrieb eines vormischbrenners

Country Status (5)

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US (1) US20100183991A1 (zh)
EP (2) EP2023041A1 (zh)
JP (1) JP2010534782A (zh)
CN (1) CN101765742B (zh)
WO (1) WO2009016079A1 (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101881454A (zh) * 2009-05-05 2010-11-10 通用电气公司 由惰性气体或较低反应性燃料层进行燃料覆盖

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110005189A1 (en) * 2009-07-08 2011-01-13 General Electric Company Active Control of Flame Holding and Flashback in Turbine Combustor Fuel Nozzle
IT1399989B1 (it) * 2010-05-05 2013-05-09 Avio Spa Gruppo di iniezione per un combustore di una turbina a gas
US20120085834A1 (en) * 2010-10-07 2012-04-12 Abdul Rafey Khan Flame Tolerant Primary Nozzle Design
US8978384B2 (en) * 2011-11-23 2015-03-17 General Electric Company Swirler assembly with compressor discharge injection to vane surface
US9217570B2 (en) * 2012-01-20 2015-12-22 General Electric Company Axial flow fuel nozzle with a stepped center body
US9441835B2 (en) * 2012-10-08 2016-09-13 General Electric Company System and method for fuel and steam injection within a combustor
US10288291B2 (en) * 2014-08-15 2019-05-14 General Electric Company Air-shielded fuel injection assembly to facilitate reduced NOx emissions in a combustor system
US10234142B2 (en) * 2016-04-15 2019-03-19 Solar Turbines Incorporated Fuel delivery methods in combustion engine using wide range of gaseous fuels
EP3301368A1 (en) 2016-09-28 2018-04-04 Siemens Aktiengesellschaft Swirler, combustor assembly, and gas turbine with improved fuel/air mixing
US10393030B2 (en) * 2016-10-03 2019-08-27 United Technologies Corporation Pilot injector fuel shifting in an axial staged combustor for a gas turbine engine
CN112128975B (zh) * 2020-09-25 2021-11-09 郑州釜鼎热能技术有限公司 一种空煤气上喷卷吸高温烟气蓄热体中燃烧与传热的热风炉

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5778676A (en) * 1996-01-02 1998-07-14 General Electric Company Dual fuel mixer for gas turbine combustor
US6050096A (en) * 1995-09-25 2000-04-18 European Gas Turbines Ltd. Fuel injector arrangement for a combustion apparatus
EP1058063A1 (en) * 1999-05-31 2000-12-06 Nuovo Pignone Holding S.P.A. Liquid fuel injector for burners in gas turbines
EP1821035A1 (en) * 2006-02-15 2007-08-22 Siemens Aktiengesellschaft Gas turbine burner and method of mixing fuel and air in a swirling area of a gas turbine burner

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2135778A5 (zh) * 1971-04-28 1972-12-22 Sourdillon Matricage Robinette
US4199936A (en) * 1975-12-24 1980-04-29 The Boeing Company Gas turbine engine combustion noise suppressor
US4198815A (en) * 1975-12-24 1980-04-22 General Electric Company Central injection fuel carburetor
JPH0269256A (ja) * 1988-09-05 1990-03-08 Matsushita Electric Ind Co Ltd サーマルヘッドおよびその製造方法
US5251447A (en) * 1992-10-01 1993-10-12 General Electric Company Air fuel mixer for gas turbine combustor
US5408830A (en) * 1994-02-10 1995-04-25 General Electric Company Multi-stage fuel nozzle for reducing combustion instabilities in low NOX gas turbines
JP2666117B2 (ja) * 1994-06-10 1997-10-22 財団法人石油産業活性化センター 予蒸発予混合燃焼器
JP3456268B2 (ja) * 1994-09-02 2003-10-14 日産自動車株式会社 ガスタービンの燃焼器
JPH08135969A (ja) * 1994-11-08 1996-05-31 Hitachi Ltd ガスタービン燃焼器の空気流量調節器
US5724805A (en) * 1995-08-21 1998-03-10 University Of Massachusetts-Lowell Power plant with carbon dioxide capture and zero pollutant emissions
GB2311596B (en) * 1996-03-29 2000-07-12 Europ Gas Turbines Ltd Combustor for gas - or liquid - fuelled turbine
JPH10252497A (ja) * 1997-03-12 1998-09-22 Mitsubishi Heavy Ind Ltd ２流体ガスタービン
WO1999004196A1 (de) * 1997-07-17 1999-01-28 Siemens Aktiengesellschaft Brenneranordnung für eine feuerungsanlage, insbesondere eine gasturbinenbrennkammer
US6145319A (en) * 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner
JP3620776B2 (ja) * 1998-10-23 2005-02-16 財団法人電力中央研究所 ガス化発電プラント用ガスタービン燃焼器
JP2002181330A (ja) * 2000-12-14 2002-06-26 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
GB2375601A (en) * 2001-05-18 2002-11-20 Siemens Ag Burner apparatus for reducing combustion vibrations
US7360363B2 (en) * 2001-07-10 2008-04-22 Mitsubishi Heavy Industries, Ltd. Premixing nozzle, combustor, and gas turbine
EP1400751A1 (de) * 2002-09-17 2004-03-24 Siemens Aktiengesellschaft Brennkammer für eine Gasturbine
AU2005207563B2 (en) * 2004-01-12 2011-04-07 Combustion Science & Engineering, Inc. System and method for flame stabilization and control

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6050096A (en) * 1995-09-25 2000-04-18 European Gas Turbines Ltd. Fuel injector arrangement for a combustion apparatus
US5778676A (en) * 1996-01-02 1998-07-14 General Electric Company Dual fuel mixer for gas turbine combustor
EP1058063A1 (en) * 1999-05-31 2000-12-06 Nuovo Pignone Holding S.P.A. Liquid fuel injector for burners in gas turbines
EP1821035A1 (en) * 2006-02-15 2007-08-22 Siemens Aktiengesellschaft Gas turbine burner and method of mixing fuel and air in a swirling area of a gas turbine burner

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101881454A (zh) * 2009-05-05 2010-11-10 通用电气公司 由惰性气体或较低反应性燃料层进行燃料覆盖
EP2251604A1 (en) * 2009-05-05 2010-11-17 General Electric Company Fuel blanketing by inert gas or less reactive fuel layer to prevent flame holding in premixers

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US20100183991A1 (en) 2010-07-22
EP2171353A1 (de) 2010-04-07
CN101765742A (zh) 2010-06-30
WO2009016079A1 (de) 2009-02-05
JP2010534782A (ja) 2010-11-11
CN101765742B (zh) 2012-04-25

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