EP1070915A1 - Brûleur à prémélange - Google Patents

Brûleur à prémélange Download PDF

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Publication number
EP1070915A1
EP1070915A1 EP99114377A EP99114377A EP1070915A1 EP 1070915 A1 EP1070915 A1 EP 1070915A1 EP 99114377 A EP99114377 A EP 99114377A EP 99114377 A EP99114377 A EP 99114377A EP 1070915 A1 EP1070915 A1 EP 1070915A1
Authority
EP
European Patent Office
Prior art keywords
premix burner
swirl generator
burner according
support structure
premix
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.)
Granted
Application number
EP99114377A
Other languages
German (de)
English (en)
Other versions
EP1070915B1 (fr
Inventor
Bettina Dr. Paikert
Richard Strässle
Christian Dr. Steinbach
Dieter Winkler
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.)
General Electric Technology GmbH
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to DE59909531T priority Critical patent/DE59909531D1/de
Priority to EP99114377A priority patent/EP1070915B1/fr
Publication of EP1070915A1 publication Critical patent/EP1070915A1/fr
Application granted granted Critical
Publication of EP1070915B1 publication Critical patent/EP1070915B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • 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
    • 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
    • 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
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23D2211/00—Thermal dilatation prevention or compensation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2214/00—Cooling

Definitions

  • the invention relates to premix burners according to the preamble of independent claim.
  • each Premix burner for operation with gaseous and / or liquid fuels become known who have essential characteristics in common. So closes each a swirl generator with tangential air inlet openings a cavity a whose cross-sectional area widens in the axial flow direction.
  • this is realized by the swirl generator is conical, while the completely equivalent in WO 93/17279 proposed solution is that the swirl generator itself is cylindrical build, and inside the cavity a conical, extending in axial Use flow tapering displacement body. Fuel is supplied to the swirl flow within the swirl generator.
  • Burners of the type known from EP 0 321 809 have been in use for years practical application in gas turbines and atmospheric Firing systems proven. That from EP 0 321 809 and from EP 0 780 629 well-known burners have been continuously developed, and Suggestions for improvement can be found in a large number of published Documents.
  • the task is one Premix burner of the type mentioned in particular in the area of Set up supply lines for gaseous fuel in such a way that Relative shifts of the individual components of the burner due to thermal expansion unhindered.
  • the essence of the invention is therefore the supply of gaseous fuel for Decouple the premix operation mechanically from the swirl generator.
  • one Fuel line with a variety of gas holes in the swirl generator too integrate the swirl generator with a series of openings, and Fuel lines for gas premixing are called pipelines executed through those openings into the interior of the swirl generator protrude and there the swirled flow of combustion air supply gaseous fuel.
  • Preferred is per tangential inlet slot the swirl generator arranged at least one gas supply pipe.
  • the open ones The ends of the gas lines are advantageously designed as nozzles. The one with high Gas escaping at a speed prevents fuel gas from flowing back through the openings of the swirl generator.
  • the front end facing the combustion chamber with a heat shield the hot combustion gases and the heat radiation in the combustion chamber protected, and it will also be a good one in this area Relative movement of components ensured that strong in operation are exposed to different temperatures, or their materials are strong have different coefficients of thermal expansion.
  • the Front part of the burner built in two parts, from one Support structure on which the swirl generator or one of the swirl generator downstream mixing tube is arranged, and a heat shield. Due to the heat protection shield, the support structure is excessive Heat input is protected and the temperature of the support structure is in operation comparable to that of the components attached to it. Can continue here materials with compatible coefficients of thermal expansion are used become.
  • the swirl generator or a mixing tube can be fixed on the Support structure can be arranged without thermal Differential strains stresses are induced in the component.
  • the heat shield is advantageously attached to the support structure in such a way that relative displacements of the support structure and the heat shield in the Framework of the expected thermal differential expansions if be hindered as little as possible.
  • Preferred swirl generator geometries result in connection with the invention itself from the subclaims.
  • the invention can be implemented at the same time Premix burners with or without the swirl generator downstream Mixing section.
  • a first preferred embodiment of an inventive Premix burner can be found in Fig. 1. It is essentially around the premix burner known from EP 0 321 809, the Swirl generator consisting of nested conical half-bodies 101, 102 consists. The burner is shown partially cut. The partial body 101, 102 enclose a cavity 14, the cross section of which is axial Extended direction of the burner to the combustion chamber 22. A gaseous one Oxidation medium - generally air or another oxygen-containing Gas - 15 flows through tangential slots 19 which extend in the axial direction of the Insert the burner into this cavity. A forms in the cavity 14 Swirl flow out.
  • the swirl flow within the Cavity 14 admixed at least one fuel.
  • the partial bodies 101, 102 of the swirl generator are provided with openings 31. By these openings are passed through pipes 32.
  • Fig. 2 the same burner is shown without a section. For the better The liquid fuel supply is not shown for clarity. In Fig. 2 is easy to see how a hammer supply pipe 32 from the outside through the Opening 31 of the swirl generator body 101 is passed.
  • the external bracket of the gas supply pipe 32 without attachment to the Components of the swirl generator, has when using the burner appropriate thermal conditions significant advantages.
  • the Combustion air 15 reaches temperatures of several 100 ° C. 500 ° C from today's perspective, more on the conservative side while in connection with higher pressure ratios of the working processes of gas turbines and external ones Combustion air preheating temperatures around 700 ° C can be discussed.
  • a possible preheating temperature of the gaseous fuels is up for example 150 ° C or 200 ° C limited.
  • the swirl generator partial bodies thus have and the gas supply pipes 32 are very different in operation Temperatures and thermal expansions. If a gas supply is now firmly connected to a swirl generator body, in the Operation strong due to disabled thermal expansion Thermal stresses that are at least the life of the burner shorten.
  • FIG. 1 as in FIG. 2 it can be seen that the combustion chamber 22 facing Front part of the burner is constructed in two parts.
  • the swirl generator is on a support structure 42 held while a heat shield 41 without direct large-area contact with the support structure 42 before this protects direct contact with hot gas within the combustion chamber 22.
  • the Support structure for your part is provided with a number of holes 11, through which a cooling medium 18, preferably the oxidation medium, into one formed as a cooling channel space between the support structure and the heat shield flows.
  • the support structure thus serves as Perforated plate for an impingement cooling of the heat shield, and is by itself the coolant 18 flowing through is cooled.
  • the cooling duct is in turn through a circumferential web 411 in the circumferential direction of the burner in radial direction divided, both on the heat shield and on the Support structure can be arranged. Through this subdivision damaging radial currents, due to which hot gases enter the cooling channel can penetrate avoided.
  • the heat protection shield is attached to the by means of bolts Carrier structure attached, which is not shown in the illustration Fig. 1 and Fig. 2 are.
  • the relatively soft attachment using a few bolts ensures one at least partial compensation of different thermal expansions, which is why they do not lead to pronounced mechanical stresses.
  • the support structure on which the swirl generator is mounted is in front excessive heat input protected. This makes it different Temperature is only marginally different from that of the swirl generator part, which is why also at the junction between the swirl generator and the Support structure stress increases due to different thermal expansion can be avoided.
  • the burner shown in perspective in FIGS. 1 and 2 is in one in FIG Longitudinal section shown.
  • the configuration is particularly important in this representation the front of the burner is clearly visible.
  • the swirl generator is firmly on the Support structure 42 mounted.
  • Heat shield 41 mounted between the support structure and the Heat protection shield has a circumferential web 411. The bolt connection can be made so soft that a relative shift only slightly hindered between the support structure and the heat protection shield becomes.
  • the premix burner according to the invention can of course also be used without the heat protection shield can be realized.
  • the carrier structure is not directly on the Fixed combustion chamber wall, but this is by means of tubes or rods 33 also attached to the combustion chamber wall so that relative movements are only slightly hampered here due to thermal expansion.
  • supports are designed as tubes, which extended at the front of the support structure towards the combustion chamber and through the heat shield is passed through.
  • These tubes 33 can for Supply of a gaseous fuel 16 for the so-called pilot operation be used. If the burner air ratio is very high, the amount is sufficient of a gaseous fuel no longer, um, when supplied via the Premix gas supply 32 to ensure a stable premix flame. In Such an operating state is the amount of gas as a so-called pilot gas 16 supplied via lines 33, and then burns in a diffusion flame. On the one hand, this generates significantly more nitrogen oxides, but it is at high levels Burner air ratios far more stable than a premix flame.
  • Fig. 4 shows a burner according to the invention with an alternative, but completely equivalent design of the swirl generator.
  • the swirl generator 100 namely not conical but cylindrical.
  • the extension the flow cross section of the burner cavity 14 is in this type achieved by creating a conical inside the burner Displacement body 8 is located, which tapers in the axial flow direction.
  • there is also one expanding swirl generator can be combined with a displacement body.
  • there could even be a taper in the axial flow direction Swirl generators are used, in which an even more tapered Displacer is used: Enlarged with the appropriate design the cross section of the cavity 14 in the swirl generator yet.
  • a liquid fuel nozzle 3 can be arranged in this displacement body be arranged, the arrangement shown here directly on the Cone tip is by no means imperative.
  • a gaseous fuel 17 for the Premix operation here also via lines 32 into the swirled combustion air 15 introduced which lines have no rigid connection with the Have swirl generator 100.
  • the tangential entry slot 19 is in this Example does not continue immediately to the mouth of the burner; it can are said to be downstream to the burner mouth connects a mixing section to the swirl generator. This point is below discussed in more detail.
  • the design also bursts on the burner with cylindrical swirl generator premixed swirl flow at sudden cross-section transition from Burner interior to the combustion chamber 22, and thus forms the backflow zone 6 which ultimately stabilizes a flame.
  • FIG. 5 Another preferred embodiment of a burner with a cylindrical Swirl generator is shown in Fig. 5.
  • Displacer fully used for the fuel supply.
  • a line 35 conducts a liquid fuel 12 through the displacer 8 to a liquid fuel nozzle 3.
  • At a downstream end is the Displacement body completed.
  • a gaseous fuel 17 for the premix operation supplied via a number of openings 37 in the displacement body swirled combustion air 15 is added.
  • there are thermal tensions in the area of the premix gas supply not perfectly avoided, but are significantly lower than according to the state of the Technology.
  • the axial shape of the swirl body contour in Combination with an inner displacement body in one Burner according to the invention can be varied within wide limits.
  • the displacement body can also have a number of different contours Have direction of the burner longitudinal axis without the invention in your To influence beings. It is crucial that in the interaction of the Swirl generator and the displacement body which flowed axially Cross section of the interior of the swirl generator increases.
  • the structure of the swirl generator in cross section can be broad Certain conditions, for example fluid dynamic, reaction kinetic or manufacturing requirements, adapted become.
  • Figures 6 to 9 give a small insight into the multitude possible geometries.
  • the swirl generator consists of two in Cross-section of semicircular partial bodies 101, 102, each with an inlet guide section. The central axes 101a and 102a of the two partial bodies are different from one another, as a result of which the tangential inlet openings 19 arise.
  • the partial body can of course also instead of semicircular be spiral or elliptical, or even oval, by which choice the Fine structure of the swirl flow in the swirl generator cavity is influenced.
  • the swirl generator can also consist of more than two against each other offset partial bodies exist, as shown in Fig. 7. 8 is a Swirl generator shown in cross section, consisting of four aerodynamic Bucket profiles 101, 102, 103, 104, which are arranged so that tangential inlet openings 19 also arise.
  • a Swirl generator shown in cross section, consisting of four aerodynamic Bucket profiles 101, 102, 103, 104, which are arranged so that tangential inlet openings 19 also arise.
  • a swirl generator 100 a mixing section 220 for an improved Mixing of fuel and combustion air in the axial direction of flow downstream of the burner.
  • the swirl generator is a conical swirl generator, consisting of four swirl generator parts shown, of which in selected section two partial bodies 101 and 102 completely and the partial body 103 are partially visible. Again each sub-body contains one Implementation 31 for a premix gas line 32, through which a gaseous Fuel 17 for the gas premix operation of the burner can be supplied.
  • the total of four premix gas lines are in the selected illustration only two visible, namely those through the partial bodies 101 and 102 are passed through. Again, these lines are light at the end designed nozzle-shaped.
  • a backflow of fuel through the Feed-through openings 31 is the via a central fuel nozzle 3 Burner can still be operated with liquid fuel.
  • Downstream of the swirl generator is followed by a transition piece 200, which is even larger in FIG. 11 is shown.
  • the wall geometry is on the inner wall of the transition piece designed in such a way that the swirl flow 50 formed in the swirl generator is possible is transferred without loss into a mixing tube 20. Therefore, in the Transition piece 200 also has a number of transfer channels 201 incorporated which is the flow coming from each tangential entry slot 19 flows into the burner interior 14, avoiding Discontinuities in the wall contour from the swirl generator leads to the mixing tube.
  • the Transition piece is installed in a mounting ring 10, which is the swirl generator 100, the transition piece 200 and the mixing tube 20 carries.
  • the mixing tube itself are tangential wall holes 21 through which an amount of air 151 flows into the mixing tube. This additional air prevents that there is an ignitable mixture in the flow boundary layer close to the wall is in which due to the locally low flow velocity A flame could re-ignite into the mixing tube.
  • the Mixing tube opens with a small transition radius and a tear-off edge 212 into the combustion chamber 22. Radially outside the tear-off edge is one circumferential groove incorporated in the front of the burner. Based on these A special configuration forms a detachment bubble 6 with a comparatively large radial, but a very small axial extent.
  • the front part of the burner shown as an example is, as already above discussed in detail, again provided with a heat shield.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP99114377A 1999-07-22 1999-07-22 Brûleur à prémélange Expired - Lifetime EP1070915B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE59909531T DE59909531D1 (de) 1999-07-22 1999-07-22 Vormischbrenner
EP99114377A EP1070915B1 (fr) 1999-07-22 1999-07-22 Brûleur à prémélange

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP99114377A EP1070915B1 (fr) 1999-07-22 1999-07-22 Brûleur à prémélange

Publications (2)

Publication Number Publication Date
EP1070915A1 true EP1070915A1 (fr) 2001-01-24
EP1070915B1 EP1070915B1 (fr) 2004-05-19

Family

ID=8238645

Family Applications (1)

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EP99114377A Expired - Lifetime EP1070915B1 (fr) 1999-07-22 1999-07-22 Brûleur à prémélange

Country Status (2)

Country Link
EP (1) EP1070915B1 (fr)
DE (1) DE59909531D1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003036167A1 (fr) * 2001-10-19 2003-05-01 Alstom Technology Ltd Bruleur a gaz de synthese
EP1321715A2 (fr) * 2001-12-21 2003-06-25 Nuovo Pignone Holding S.P.A. Chambre de prémélange et chambre de combustion pour turbines à gaz à faible émission de polluants fonctionnant avec combustible liquide et/ou gazeux
US7013648B2 (en) 2002-05-16 2006-03-21 Alstom Technology Ltd. Premix burner
WO2006094922A1 (fr) * 2005-03-09 2006-09-14 Alstom Technology Ltd Bruleur de premelange destine a produire un melange carburant-air inflammable
EP2058590A1 (fr) 2007-11-09 2009-05-13 ALSTOM Technology Ltd Procédé de fonctionnement d'un brûleur
WO2009068424A1 (fr) 2007-11-27 2009-06-04 Alstom Technology Ltd Procédé et dispositif pour la combustion d'hydrogène dans un brûleur à prémélange
US7610761B2 (en) 2005-03-23 2009-11-03 Alstom Technology Ltd. Method and device for the combustion of hydrogen in a premix burner
US7871262B2 (en) 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner
WO2011032935A2 (fr) 2009-09-17 2011-03-24 Alstom Technology Ltd. Procédé pour brûler des combustibles gazeux, riches en hydrogène, dans un brûleur ainsi que brûleur pour la mise en oeuvre du procédé
US10837643B2 (en) 2018-08-06 2020-11-17 General Electric Company Mixer assembly for a combustor

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809A1 (fr) 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
US5129231A (en) * 1990-03-12 1992-07-14 United Technologies Corporation Cooled combustor dome heatshield
WO1993017279A1 (fr) 1992-02-26 1993-09-02 United Technologies Corporation Bruleur de gaz a premelange
US5363643A (en) * 1993-02-08 1994-11-15 General Electric Company Segmented combustor
EP0780629A2 (fr) 1995-12-21 1997-06-25 ABB Research Ltd. Brûleur pour un générateur de chaleur
EP0908671A1 (fr) * 1997-10-08 1999-04-14 Abb Research Ltd. Procédé de combustion des combustibles gazeux, liquides et combustibles à moyen et bas pouvoir calorifique dans un brûleur
EP0918190A1 (fr) * 1997-11-21 1999-05-26 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809A1 (fr) 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
US5129231A (en) * 1990-03-12 1992-07-14 United Technologies Corporation Cooled combustor dome heatshield
WO1993017279A1 (fr) 1992-02-26 1993-09-02 United Technologies Corporation Bruleur de gaz a premelange
US5307634A (en) * 1992-02-26 1994-05-03 United Technologies Corporation Premix gas nozzle
US5363643A (en) * 1993-02-08 1994-11-15 General Electric Company Segmented combustor
EP0780629A2 (fr) 1995-12-21 1997-06-25 ABB Research Ltd. Brûleur pour un générateur de chaleur
EP0908671A1 (fr) * 1997-10-08 1999-04-14 Abb Research Ltd. Procédé de combustion des combustibles gazeux, liquides et combustibles à moyen et bas pouvoir calorifique dans un brûleur
EP0918190A1 (fr) * 1997-11-21 1999-05-26 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003036167A1 (fr) * 2001-10-19 2003-05-01 Alstom Technology Ltd Bruleur a gaz de synthese
US7003957B2 (en) 2001-10-19 2006-02-28 Alstom Technology Ltd Burner for synthesis gas
EP1321715A2 (fr) * 2001-12-21 2003-06-25 Nuovo Pignone Holding S.P.A. Chambre de prémélange et chambre de combustion pour turbines à gaz à faible émission de polluants fonctionnant avec combustible liquide et/ou gazeux
EP1321715A3 (fr) * 2001-12-21 2004-01-14 Nuovo Pignone Holding S.P.A. Chambre de prémélange et chambre de combustion pour turbines à gaz à faible émission de polluants fonctionnant avec combustible liquide et/ou gazeux
US6880339B2 (en) 2001-12-21 2005-04-19 Nuovo Pignone S.P.A. Combination of a premixing chamber and a combustion chamber, with low emission of pollutants, for gas turbines running on liquid and/or gas fuel
US7013648B2 (en) 2002-05-16 2006-03-21 Alstom Technology Ltd. Premix burner
US7871262B2 (en) 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner
WO2006094922A1 (fr) * 2005-03-09 2006-09-14 Alstom Technology Ltd Bruleur de premelange destine a produire un melange carburant-air inflammable
US8007273B2 (en) 2005-03-09 2011-08-30 Alstom Technology Ltd. Premixing burner for generating an ignitable fuel/air mixture
US7610761B2 (en) 2005-03-23 2009-11-03 Alstom Technology Ltd. Method and device for the combustion of hydrogen in a premix burner
EP2058590A1 (fr) 2007-11-09 2009-05-13 ALSTOM Technology Ltd Procédé de fonctionnement d'un brûleur
JP2009121806A (ja) * 2007-11-09 2009-06-04 Alstom Technology Ltd バーナー操作方法
US9103547B2 (en) 2007-11-09 2015-08-11 Alstom Technology Ltd Method for operating a burner
WO2009068424A1 (fr) 2007-11-27 2009-06-04 Alstom Technology Ltd Procédé et dispositif pour la combustion d'hydrogène dans un brûleur à prémélange
US8066509B2 (en) 2007-11-27 2011-11-29 Alstom Technology Ltd. Method and device for combusting hydrogen in a premix burner
US8549860B2 (en) 2009-09-17 2013-10-08 Alstom Technology Ltd Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method
WO2011032935A2 (fr) 2009-09-17 2011-03-24 Alstom Technology Ltd. Procédé pour brûler des combustibles gazeux, riches en hydrogène, dans un brûleur ainsi que brûleur pour la mise en oeuvre du procédé
DE112010003677B4 (de) 2009-09-17 2023-10-26 Ansaldo Energia Switzerland AG Verfahren zum verbrennen wasserstoffreicher, gasförmiger brennstoffe in einem brenner sowie brenner zur durchführung des verfahrens
US10837643B2 (en) 2018-08-06 2020-11-17 General Electric Company Mixer assembly for a combustor

Also Published As

Publication number Publication date
DE59909531D1 (de) 2004-06-24
EP1070915B1 (fr) 2004-05-19

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