WO2003054447A1 - Brennstofflanze - Google Patents
Brennstofflanze Download PDFInfo
- Publication number
- WO2003054447A1 WO2003054447A1 PCT/CH2002/000675 CH0200675W WO03054447A1 WO 2003054447 A1 WO2003054447 A1 WO 2003054447A1 CH 0200675 W CH0200675 W CH 0200675W WO 03054447 A1 WO03054447 A1 WO 03054447A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- fuel
- lance
- tube
- cavity
- purge air
- Prior art date
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 124
- 238000002347 injection Methods 0.000 claims abstract description 21
- 239000007924 injection Substances 0.000 claims abstract description 21
- 238000010926 purge Methods 0.000 claims description 51
- 239000007788 liquid Substances 0.000 claims description 19
- 230000002000 scavenging effect Effects 0.000 claims description 12
- 238000002485 combustion reaction Methods 0.000 claims description 8
- 238000005507 spraying Methods 0.000 claims description 2
- 238000004939 coking Methods 0.000 abstract description 3
- 238000011010 flushing procedure Methods 0.000 abstract 3
- 230000015556 catabolic process Effects 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000001419 dependent effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
- F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
-
- 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
-
- 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
- F23D11/40—Mixing tubes or chambers; Burner heads
- F23D11/402—Mixing chambers downstream of the nozzle
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/76—Protecting flame and burner parts
-
- 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
-
- 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
- F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
-
- 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
- F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon
Definitions
- the present invention relates to a fuel lance according to the preamble of claim 1 and to the use of such a fuel lance in a double-cone burner according to claim 11.
- premix burners allow a significant reduction in NOx emissions from gas turbines.
- the relatively narrow operating range of premix burners is problematic.
- swirl stabilization with vortex breakdown such as in double-cone burners as described in US 4,932,861, or in double-cone burners with a downstream mixing section as described for example in EP 0704657
- an additional flame is required for part-load operation.
- This partial load flame or pilot flame is usually diffusion-like and should ideally have as close contact as possible with the (premix) main flame.
- the fuel lance should be able to be operated simultaneously or alternatively with the two fuels without the risk of reignition or coking (in the case of liquid fuel).
- the solution to the problem can be found in the characterizing part of the main claim.
- the solution is that the fuel lance, in addition to fuel, also leads purge air to the injection location, and that the purge air at the injection location is conducted between the two fuel systems in such a way that the purge air shields them from one another.
- the essence of the invention is therefore that the scavenging air, which is also led to the tip of the lance, is guided between the fuels injected into the combustion chamber at the tip of the lance in such a way that a “protective screen” of scavenging air prevents the two fuels from crossing.
- a “protective screen” of scavenging air prevents the two fuels from crossing.
- the two channels for the fuels and the channel for the scavenging air are designed as essentially concentric cylindrical tubes of different diameters, the three media being guided to the injection site in the hollow cylindrical or cylindrical gaps that are created.
- This design is simple and particularly suitable in relation to the thermal loads in a burner.
- the fuel systems are a system with liquid fuel and a system with gaseous fuel.
- Partial load range used in gas operation and the liquid fuel, e.g. B. in the form of a
- the liquid fuel is preferably led to the lance tip via a central, inner tube with the smallest diameter, this inner tube being arranged by two further tubes which are arranged concentrically with the inner one
- Pipes is surrounded and the gaseous fuel and the scavenging air are guided in the hollow cylindrical spaces thus formed to the lance tip to the injection site, and the scavenging air continues directly at the injection site
- Cavity flows between the central, inner tube and the middle tube. This will ensure that the purge air is effectively between the two at the point of injection Fuel flows and flows in the sense of a shielding jacket and decouples the two fuel flows from each other.
- the scavenging air is injected into the combustion chamber in an essentially axial and circumferential manner, in the sense of a hollow cylinder, at the injection location.
- the purge air enters the combustion zone parallel to the burner axis.
- the liquid fuel can moreover preferably be at the injection point in a slightly radially outward direction and in a manner directed towards the axial purge air flow, i.e. in the form of an encircling hollow circular truncated cone opening towards the tip of the lance.
- the liquid fuel can also be injected through a hollow-cone swirl nozzle or through a multi-hole nozzle.
- the gaseous fuel can take place in a slightly radially inward direction and in a manner directed towards the purge air flow, ie. H. in the form of a circular circular frustum of a cone that closes at the tip of the lance.
- Another preferred embodiment is characterized in that the liquid and the gaseous fuel are guided at the lance base in the inner tube and in the cavity between the inner tube and the middle tube, respectively, and the purge air is guided in the cavity between the middle tube and the outer tube ,
- the purging air can either be diverted directly to the lance base into the cavity between the inner tube and the middle tube, while the gaseous fuel is directed into the cavity between the middle tube and the outer tube, with the purging air being particularly preferably introduced into the middle cavity through slots or holes arranged in corresponding radial segments. Since usually the lance tip can have a larger diameter at the lance base, this design allows higher flows of purge air and gaseous fuel.
- the present invention relates to the use of a fuel lance as described above.
- it relates to such a use for the pilot operation of a premix burner, in particular a double-cone burner with or without a downstream mixing section, the fuel lance being arranged on the axis of the premix burner.
- the lance extends essentially over a length of 3/4 of the total length of the double-cone burner with or without a downstream mixing section, the total length being the length of the conical region of the double-cone burner.
- FIG. 1 shows an axial section through a fuel lance according to the invention
- FIG. 2 shows an axial section through an entire fuel lance according to the invention, in which the crossing is arranged at the tip of the lance;
- Fig. 3 shows an axial section through a fuel lance according to the invention, in which the crossing is arranged on the lance base.
- Fig. 1 shows the tip 1 of a fuel lance in an axial section.
- the fuel lance consists of an outermost lance tube 2, the lance in the case of use in a double-cone burner, as it is for. B. is described in US 4,932,861, usually about 3/4 of the length of the burner protrudes into the cavity between the conical partial bodies.
- the fuel lance usually has a circular cross section.
- the oil tube in the cylindrical outermost tube 2, coaxially arranged with the outermost tube 2, there is a middle tube 4 and another inner tube 3, the oil tube, with the smallest diameter.
- Liquid fuel that is to say oil, flows through the oil pipe 3, Petrol, or the like in the oil guide 5 to the lance tip if the lance is to be operated with liquid fuel.
- a central insert 7 At the tip of the oil pipe 3 there is a central insert 7, which is arranged essentially on the axis of the burner lance and which leads to the oil flow at the tip of the lance being deflected radially outwards.
- the liquid fuel does not enter the combustion chamber or the cavity in which the combustion is to take place in the direction of the axis of the fuel lance, but rather in the form of a circular cone-shaped spray cone which can be closed all around, that is to say it can run all the way around.
- the liquid fuel can also be injected through a hollow-cone swirl nozzle (not shown in the figures) or through a multi-hole nozzle.
- gaseous fuel usually flows at the lance tip 1.
- the outer tube 2 has at its outermost end a circumferential curvature directed in the direction of the axis of the fuel lance, i.e. Constriction, which leads to the gas stream 11 being deflected in the direction of the axis of the fuel lance shortly before it emerges from the fuel lance.
- Constriction a circumferential curvature directed in the direction of the axis of the fuel lance, i.e. Constriction, which leads to the gas stream 11 being deflected in the direction of the axis of the fuel lance shortly before it emerges from the fuel lance.
- a tapered hollow gas cone is created.
- purge air 9 now flows according to the invention at the lance tip 1.
- This purge air now flows essentially axially, ie with the formation of a cylindrical air jacket at the lance tip 1.
- the purge air 9 flows between the two fuels used.
- both the gaseous fuel stream 11 and the liquid fuel stream 6 are directed onto this cylindrical air jacket made of purge air.
- This particular arrangement allows an operation in which, as a result of the shielding of the fuel flows through the purge air, the lance can either be operated with one of the two fuels or with both without z.
- such a fuel lance has an outside diameter in the range of 20 to 40 millimeters (outside diameter of the outermost pipe 2), the middle pipe 4 has an outside diameter of about 2/3 of that of the outermost pipe 2, and the oil pipe 3 has a diameter of something 1/3 that of the outermost tube 2. At the foot 17 of the lance, this usually has a larger outside diameter of in the range of 30 to 60 millimeters.
- the tubes are advantageously made of nickel-based alloys with a wall thickness in the range of 1 to 3 millimeters.
- the outer tube 2 which has an inward curvature in the foremost region, is there tapered over a length of 10 millimeters by in the region of 40%, which causes a deflection of the pilot gas 11 in the direction of the central axis of the fuel lance and thereby the outlet opening of the Pilot gas comes to lie so that the shielding effect of the purge air is at a maximum.
- a fuel lance is usually used for the pilot operation of premix burners. If possible, only gaseous fuel is used in pilot operation, with the fuel lance typically being used up to about 50% load, ie until the premix flame is sufficiently stabilized. If the premix flame is sufficiently stabilized, the fuel lance is normally no longer activated with fuel, but only the fuel nozzles at the inlet slots of the premix burner.
- the fuel lance according to the invention alternatively allows burner operation using liquid fuel.
- This alternative usability is possible because the purge air prevents this fuel from getting into the non-operated channel when operating with only one fuel, and causing reignitions there.
- the purge air jacket also has the advantage with liquid fuel that coking is avoided.
- Fig. 2 shows a lance in its entire length. Since the liquid 16 and the gaseous 15 fuel are usually supplied at the base 17 of the burner in two concentrically arranged pipes, there is basically the problem of guiding the purge air 9 between these two fuel channels. This can be done in two different ways, FIG.
- the pilot gas guide 10 is now guided into the radially outermost space on one side by crossing the two outer channels in an area 12.
- the purge air 9 guided in the outermost space between the pipes 2 and 4 is guided into the middle space between the middle pipe 4 and the inner oil pipe 3.
- This mutual deflection takes place segment by segment (with respect to the cross section perpendicular to the axis 18 of the fuel lance), three segments being sufficient for the gas duct and three segments for the scavenging air duct, the segments typically having the same cross section.
- the area of the lance tip has the advantage that the lance has good cooling through this purge air channel. This makes this lance particularly suitable when it comes to burners with a certain risk of kickback.
- FIG. 3 shows another exemplary embodiment of a fuel lance for pilot operation, in which the two channels of purge air and pilot gas do not cross at the lance tip, but already at the lance base 17.
- the introduced purge air 14 is already guided on the lance base 17 into the space between the middle pipe 4 and the oil pipe 3, and accordingly the pilot gas supply 15 is already guided on the lance base 17 into the space between the middle pipe 4 and the outer pipe 2.
- this takes place in segments, that is to say the supply 14 of the purge air takes place through slots or bores in three segments, while in a further three segments the pilot gas is led into the outermost channel.
- the embodiment according to FIG. 3 has the advantage that, owing to the larger diameter of the fuel lance at its base 17, larger flow cross-sections for the pilot gas and the purge air are also possible than when the intersection takes place at the tip of the lance. Accordingly, higher flows of purge air and pilot gas can be realized with such a fuel lance.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Spray-Type Burners (AREA)
- Gas Burners (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AU2002349248A AU2002349248A1 (en) | 2001-12-20 | 2002-12-06 | Fuel lance |
JP2003555122A JP4246067B2 (ja) | 2001-12-20 | 2002-12-06 | 燃料ランス |
EP02781042A EP1456583B1 (de) | 2001-12-20 | 2002-12-06 | Verfahren zum Eindüsen eines Brennstoff-/Luftgemisches in eine Brennkammer |
DE50211068T DE50211068D1 (de) | 2001-12-20 | 2002-12-06 | Verfahren zum Eindüsen eines Brennstoff-/Luftgemisches in eine Brennkammer |
US10/869,942 US7082768B2 (en) | 2001-12-20 | 2004-06-18 | Method for injecting a fuel-air mixture into a combustion chamber |
US11/426,924 US7406827B2 (en) | 2001-12-20 | 2006-06-27 | Apparatus for injecting a fuel-air mixture into a combustion chamber |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH2331/01 | 2001-12-20 | ||
CH23312001 | 2001-12-20 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/869,942 Continuation US7082768B2 (en) | 2001-12-20 | 2004-06-18 | Method for injecting a fuel-air mixture into a combustion chamber |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2003054447A1 true WO2003054447A1 (de) | 2003-07-03 |
Family
ID=4568627
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/CH2002/000675 WO2003054447A1 (de) | 2001-12-20 | 2002-12-06 | Brennstofflanze |
Country Status (8)
Country | Link |
---|---|
US (2) | US7082768B2 (de) |
EP (1) | EP1456583B1 (de) |
JP (1) | JP4246067B2 (de) |
CN (1) | CN1320307C (de) |
AU (1) | AU2002349248A1 (de) |
DE (1) | DE50211068D1 (de) |
ES (1) | ES2295423T3 (de) |
WO (1) | WO2003054447A1 (de) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2010080604A1 (en) * | 2008-12-18 | 2010-07-15 | Solar Turbines Incorporated | Low-cross-talk gas turbine fuel injector |
EP2208927A1 (de) * | 2009-01-15 | 2010-07-21 | ALSTOM Technology Ltd | Brenner einer Gasturbine |
EP1770333B1 (de) * | 2005-09-28 | 2010-07-21 | Snecma | Anti-Verkokungsinjektorarm |
EP2282115A1 (de) * | 2009-07-30 | 2011-02-09 | Alstom Technology Ltd | Brenner einer Gasturbine |
DE102006005130B4 (de) * | 2005-02-05 | 2015-03-19 | Alstom Technology Ltd. | Brennstoffeinspritzsystem und Verfahren zur Überwachung eines Brennstoffeinspritzsystems |
Families Citing this family (19)
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US8062027B2 (en) * | 2005-08-11 | 2011-11-22 | Elster Gmbh | Industrial burner and method for operating an industrial burner |
FR2915989B1 (fr) * | 2007-05-10 | 2011-05-20 | Saint Gobain Emballage | Injecteur mixte a bas nox |
US7926282B2 (en) * | 2008-03-04 | 2011-04-19 | Delavan Inc | Pure air blast fuel injector |
US8347631B2 (en) * | 2009-03-03 | 2013-01-08 | General Electric Company | Fuel nozzle liquid cartridge including a fuel insert |
US8468831B2 (en) * | 2009-07-13 | 2013-06-25 | General Electric Company | Lean direct injection for premixed pilot application |
JP5558168B2 (ja) * | 2010-03-30 | 2014-07-23 | 三菱重工業株式会社 | 燃焼器及びガスタービン |
US8893500B2 (en) | 2011-05-18 | 2014-11-25 | Solar Turbines Inc. | Lean direct fuel injector |
US8919132B2 (en) | 2011-05-18 | 2014-12-30 | Solar Turbines Inc. | Method of operating a gas turbine engine |
CN102287825A (zh) * | 2011-07-15 | 2011-12-21 | 马鞍山科达洁能股份有限公司 | 燃烧喷嘴及煤气化炉 |
US9182124B2 (en) | 2011-12-15 | 2015-11-10 | Solar Turbines Incorporated | Gas turbine and fuel injector for the same |
JP5618337B2 (ja) * | 2012-02-28 | 2014-11-05 | 三菱日立パワーシステムズ株式会社 | ガスタービン燃焼器 |
US20130269351A1 (en) * | 2012-04-17 | 2013-10-17 | General Electric Company | Micromixer assembly of a turbine system and method of assembly |
US9086017B2 (en) * | 2012-04-26 | 2015-07-21 | Solar Turbines Incorporated | Fuel injector with purged insulating air cavity |
US9261279B2 (en) * | 2012-05-25 | 2016-02-16 | General Electric Company | Liquid cartridge with passively fueled premixed air blast circuit for gas operation |
JP6018714B2 (ja) * | 2012-11-21 | 2016-11-02 | ゼネラル・エレクトリック・カンパニイ | コーキング防止液体燃料カートリッジ |
EP2743582A1 (de) * | 2012-12-14 | 2014-06-18 | Siemens Aktiengesellschaft | Brennerspitze und Brenner |
US11555612B2 (en) * | 2017-11-29 | 2023-01-17 | Babcock Power Services, Inc. | Dual fuel direct ignition burners |
GB2592267A (en) * | 2020-02-24 | 2021-08-25 | Altair Uk Ltd | Pulse nozzle for filter cleaning systems |
CN116928698A (zh) * | 2023-07-17 | 2023-10-24 | 中国航发燃气轮机有限公司 | 一种喷嘴头、双燃料喷嘴及燃烧室 |
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-
2002
- 2002-12-06 EP EP02781042A patent/EP1456583B1/de not_active Expired - Lifetime
- 2002-12-06 WO PCT/CH2002/000675 patent/WO2003054447A1/de active IP Right Grant
- 2002-12-06 CN CNB028282736A patent/CN1320307C/zh not_active Expired - Fee Related
- 2002-12-06 DE DE50211068T patent/DE50211068D1/de not_active Expired - Lifetime
- 2002-12-06 AU AU2002349248A patent/AU2002349248A1/en not_active Abandoned
- 2002-12-06 ES ES02781042T patent/ES2295423T3/es not_active Expired - Lifetime
- 2002-12-06 JP JP2003555122A patent/JP4246067B2/ja not_active Expired - Fee Related
-
2004
- 2004-06-18 US US10/869,942 patent/US7082768B2/en not_active Expired - Lifetime
-
2006
- 2006-06-27 US US11/426,924 patent/US7406827B2/en not_active Expired - Lifetime
Patent Citations (4)
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US4798330A (en) * | 1986-02-14 | 1989-01-17 | Fuel Systems Textron Inc. | Reduced coking of fuel nozzles |
DE4424597A1 (de) * | 1994-07-13 | 1996-01-18 | Abb Management Ag | Verbrennungsvorrichtung |
DE19545310A1 (de) * | 1995-12-05 | 1997-06-12 | Asea Brown Boveri | Vormischbrenner |
US6038863A (en) * | 1996-12-19 | 2000-03-21 | Asea Brown Boveri Ag | Burner arrangement for a gas turbine for preventing the ingress of fluids into a fuel passage |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102006005130B4 (de) * | 2005-02-05 | 2015-03-19 | Alstom Technology Ltd. | Brennstoffeinspritzsystem und Verfahren zur Überwachung eines Brennstoffeinspritzsystems |
EP1770333B1 (de) * | 2005-09-28 | 2010-07-21 | Snecma | Anti-Verkokungsinjektorarm |
WO2010080604A1 (en) * | 2008-12-18 | 2010-07-15 | Solar Turbines Incorporated | Low-cross-talk gas turbine fuel injector |
US8099940B2 (en) | 2008-12-18 | 2012-01-24 | Solar Turbines Inc. | Low cross-talk gas turbine fuel injector |
CN102317690B (zh) * | 2008-12-18 | 2014-07-02 | 索拉透平公司 | 低串扰的燃气轮机燃料喷射器引燃组件及降低串扰的方法 |
EP2208927A1 (de) * | 2009-01-15 | 2010-07-21 | ALSTOM Technology Ltd | Brenner einer Gasturbine |
US8601818B2 (en) | 2009-01-15 | 2013-12-10 | Alstom Technology Ltd | Conical gas turbine burner having a fuel lance with inclined side nozzles |
EP2282115A1 (de) * | 2009-07-30 | 2011-02-09 | Alstom Technology Ltd | Brenner einer Gasturbine |
EP2284441A2 (de) | 2009-07-30 | 2011-02-16 | Alstom Technology Ltd | Brenner einer Gasturbine |
EP2284441A3 (de) * | 2009-07-30 | 2014-12-17 | Alstom Technology Ltd | Brenner einer Gasturbine |
US9435532B2 (en) | 2009-07-30 | 2016-09-06 | General Electric Technology Gmbh | Burner of a gas turbine |
Also Published As
Publication number | Publication date |
---|---|
CN1620579A (zh) | 2005-05-25 |
US7406827B2 (en) | 2008-08-05 |
EP1456583A1 (de) | 2004-09-15 |
CN1320307C (zh) | 2007-06-06 |
US20050028532A1 (en) | 2005-02-10 |
JP2005513399A (ja) | 2005-05-12 |
JP4246067B2 (ja) | 2009-04-02 |
ES2295423T3 (es) | 2008-04-16 |
DE50211068D1 (de) | 2007-11-22 |
US7082768B2 (en) | 2006-08-01 |
EP1456583B1 (de) | 2007-10-10 |
AU2002349248A1 (en) | 2003-07-09 |
US20080163626A1 (en) | 2008-07-10 |
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