EP1734306A1 - Brûleur pour combustion à prémélange - Google Patents

Brûleur pour combustion à prémélange Download PDF

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Publication number
EP1734306A1
EP1734306A1 EP06115305A EP06115305A EP1734306A1 EP 1734306 A1 EP1734306 A1 EP 1734306A1 EP 06115305 A EP06115305 A EP 06115305A EP 06115305 A EP06115305 A EP 06115305A EP 1734306 A1 EP1734306 A1 EP 1734306A1
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
air inlet
premix
outlet openings
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
EP06115305A
Other languages
German (de)
English (en)
Other versions
EP1734306B1 (fr
Inventor
Eroglu Adnan
Toqan Majed
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
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1734306A1 publication Critical patent/EP1734306A1/fr
Application granted granted Critical
Publication of EP1734306B1 publication Critical patent/EP1734306B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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 
    • 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
    • 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 
    • 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 invention relates to a burner for premixing combustion according to claim 1 and a method for operating a burner according to claim 23.
  • a preferred arrangement are burners in the form of conical hollow body having tangential air inlet slots. Combustion air flows through the air inlet slots into the conical burner cavity. Via fuel outlet openings at the edges of the air inlet slots fuel, in particular gaseous fuel, is supplied to the combustion air flow. In addition, liquid fuel is introduced at the apex of the cone in the burner cavity, in particular sprayed. The combustion takes place at the exit of the conical burner cavity.
  • the EP 0 321 809 A1 describes a method for the premix-type combustion of liquid fuel, in which a conical liquid fuel column forms inside the conical cavity, which is enclosed by a rotating combustion air flow flowing tangentially into the burner.
  • the ignition of the mixture takes place at the outlet of the burner, whereby a flame stabilization is established in the region of the burner mouth by the formation of a backflow zone.
  • a corresponding burner the two offset part cone body to form a conical burner cavity, a centrally between the mutually offset longitudinal axes of symmetry Part cone body attached fuel injection and having tangential air inlet slots.
  • the fuel exit openings for introducing the premix fuel are attached to the edges of the air inlet slots.
  • the EP 0 981 016 B1 describes a burner, which also has the above-described conical structure with tangential air inlet slots for the introduction of a combustion air flow.
  • This burner also has an injection device for injecting fuel into the combustion air flow.
  • This injection device is arranged centrally in the combustion air flow in front of the air inlet slots in order to inject the fuel in a parallel flow direction to the combustion air flow.
  • the WO 01/96785 A1 describes a burner and a corresponding method for operating a burner, in which two or more fuel feeds are provided with arranged substantially in the direction of the burner axis fuel outlet openings, which can separately introduce premix fuel in the burner chamber. Thereby, a stepped injection of fuel into the burner chamber can be achieved, which adapts to the changing conditions in the operation of the burner, resulting for example from different loads, gas qualities or gas preheating temperatures.
  • the DE 100 49 205 A1 describes a method and apparatus for fueling a premix burner, in which the Premix fuel supply is performed over at least two spatially axially separate areas along the burner, so that for the startup of the turbine and for the further start-up of the load up to full load, a gradual or continuous redistribution of the supply of the premix fuel between the areas.
  • the object of the present invention is therefore to propose a burner for premix-type combustion and a method for operating a burner, which enable a stable premix-type combustion with as homogeneous as possible mixing of the premix fuel with the combustion air with reduced pollutant emissions.
  • An essential idea of the invention is that the means mounted centrally in the inflow region of the combustion air flow for injection of premix fuel into the tangential air inlet slots of a burner cavity are designed so that they relative to a cross-sectional plane perpendicular to the burner axis the premix fuel not only centrally but also more as a point in the combustion air flow to achieve the most homogeneous possible mixing of the premix fuel with the combustion air.
  • a high pollutant emissions, in particular nitrogen oxides avoided due to insufficient premixing.
  • the invention now concretely relates to a burner for premix-type combustion, which has a cavity which has at least one tangential one An air inlet slot for supplying a combustion air flow, means for injecting fuel into the cavity, which are mounted in the region of a burner axis, and means for injection of premix fuel in the at least one air inlet slot, which are mounted centrally in the inflow region of the combustion air flow comprises.
  • the means for injection of premix fuel in the at least one air inlet slots have at least one fuel supply, the fuel outlet openings are arranged such that the premix fuel is introduced on both sides of the at least one fuel supply relative to a cross-sectional plane perpendicular to the burner axis in the combustion air flow.
  • the pressure for injecting the premix fuel into the relatively high velocity incoming combustion air stream can be reduced as compared to a one-sided injection from the edge of the air inlet slot.
  • the burner is designed such that the cavity is formed from at least two complementary to a body cone bodies forming a conical cavity whose longitudinal axes of symmetry are radially offset from one another and include at least two tangential air inlet slots for the supply of a combustion air flow.
  • the burner can be designed such that the cavity is formed from at least two complementary to a body body parts, which form a cylinder cavity whose longitudinal axes of symmetry are radially offset from one another and include at least two tangential air inlet slots for the supply of a combustion air flow.
  • tulip or cup-shaped formations of the cavity are possible.
  • the burner may have a mixing section located downstream of the cavity for transferring a flow generated in the cavity having a fuel mixture in a combustion chamber. This can increase the stability of flameless combustion.
  • the fuel outlet openings have a common, along the respective tangential air inlet slot mounted fuel supply.
  • the number of fuel feeds may depend on the number of air inlet slots, which in turn depends on whether the cavity is formed by two or more partial bodies.
  • the fuel outlet openings are formed as a pair of slot nozzles extending along the entire length of the fuel supply.
  • the combustion air flow premix fuel can be supplied evenly distributed over the entire length of the tangential air inlet slot.
  • the fuel outlet openings may have circular or oval cross sections.
  • a different penetration depth of the premix fuel into the combustion air flow can be achieved so as to be able to realize different mixture distributions.
  • the fuel outlet openings can be distributed in pairs evenly over the entire length of the tangential air inlet slot. The arrangement, distribution and design of the fuel outlet openings affects the fuel distribution within the burner and thus its quality of combustion.
  • the fuel outlet openings may be arranged grouped such that a first group of fuel outlet openings distributed uniformly over the entire length of the tangential air inlet slot and having a first common fuel supply and that a second group of fuel outlet openings along a portion of the entire length of the tangential air inlet slot distributed and at least a second common fuel supply.
  • the fuel outlets are arranged in such a group that a first group of fuel outlets is evenly distributed over a first portion of the entire length of the tangential air inlet slot and has a first common fuel supply and at least one second group is longitudinal a further portion of the entire length of the tangential air inlet slot distributed and having at least a second common fuel supply.
  • a stepped supply of premix fuel may be advantageous when starting the gas turbine if the entire premix fuel supply is to take place preferably via the first, upstream group of fuel outlets.
  • the premix fuel supply can be routed step by step or continuously to the second, downstream group of fuel outlets on further startup of the gas turbine to full load.
  • the subregions do not overlap. Depending on the operating mode of the burner, however, it may also be desirable for at least two partial areas to overlap.
  • the fuel outlet openings of two or more Groups have different cross-sections.
  • the group of fuel outlets which is to inject smaller amounts of premix fuel, have smaller injection cross-sections and vice versa.
  • the fuel feeds may have a streamlined profile with respect to a cross-sectional plane perpendicular to the burner axis.
  • the fuel feeds may be mounted in front of the air inlet slots with respect to the direction of the combustion air flow. Thus, they may be disposed in a region of a lower velocity of the combustion air flow than directly in the air inlet slots. Aerodynamic losses and the required pressure for the premix fuel injection can thus be reduced.
  • the fuel feeds may comprise means for regulating the mass flow of the premix fuel.
  • the fuel feeds to the groups of fuel outlet openings means for regulating the mass flow of Vormischbrennstoffs to impinge independently on fuel or the penetration depth of Vormischbrunstoffs in the combustion air flow and thus the mixing quality influence. Under certain circumstances, it is even possible to dispense with the additional supply of a pilot fuel for starting the gas turbine or in low load operation in the central fuel injection at the burner axis.
  • the means for injecting premix fuel in the air inlet slots are designed as a single component.
  • the unitary component may comprise means for attachment to a burner.
  • Such a construction can not only increase the flexibility in use of said burners, but also simplify the manufacture of the molded cone bodies, since the integration of the fuel feeds and the fuel outlets into the cast part cone body is eliminated.
  • the means for injecting fuel into the cavity which are mounted in the region of the burner axis, designed as a jet pipe, in addition to a central outlet nozzle for liquid fuel fuel outlet openings for the supply of premix fuel in a from the combustion chamber end remote Part of the beam tube along the burner axis having an associated fuel supply.
  • jet nozzle applications that protrude into the cavity longer have proven to be advantageous in terms of combustion stability, as they may, for example, prevent undesirable interference between pilot fuel and premix fuel.
  • the means for injecting fuel into the cavity which are mounted in the region of the burner axis, be designed as a conical body, the apex of which is oriented downstream and having a fuel outlet nozzle.
  • the burner can be arranged together with a secondary burner as a hybrid burner.
  • the invention further relates to a method of operating a burner, comprising a cavity having at least one tangential air inlet slot for supplying a combustion air stream, means for injecting fuel into the cavity, which are mounted in the region of a burner axis, and means for injection of Vormischbrennstoff in the air inlet slots, which are mounted centrally in the inflow region of the combustion air flow includes.
  • the means for injection of premix fuel into the air inlet slots bring the premix fuel on both sides of fuel supply to a cross-sectional plane perpendicular to the burner axis in the combustion air flow.
  • the penetration depth and interference of the premix fuel jet may affect the mixing quality of the premix fuel and the combustion air and thus the fuel distribution at the burner throat. These in turn can be crucial for the combustion stability and the level of pollutant emissions, especially nitrogen emissions.
  • gaseous fuels can be introduced into the combustion air flow on both sides of the fuel feeds, with reference to a cross-sectional plane perpendicular to the burner axis.
  • the premix fuel can be introduced uniformly over the entire length of the tangential air inlet slot. Good mixing of the fuels is the prerequisite for low levels of nitrogen oxide emissions during combustion in such premix burners.
  • the premix fuel can be introduced separately over at least two subregions of the entire length of the tangential air inlet slot.
  • the burner can be operated stably even with a changed load or fuel quality with low nitrogen emission values.
  • the premix fuel may be introduced in front of the air inlet slots with respect to the direction of the combustion air flow and thus in a lower velocity region of the combustion air flow than directly into the air inlet slots.
  • the feed of the premix fuel to the individual fuel outlet openings can be carried out controllably.
  • the premix fuel may also be introduced as a function of measured pressure fluctuations, pollutant emission values or material temperatures of the burner in order to ensure stable combustion.
  • the means for injecting fuel into the cavity which are mounted in the region of the burner axis and are designed as a jet pipe, in addition to the introduction of a liquid fuel through a central Eject premix fuel via a portion of the jet pipe remote from the combustion chamber end along the burner axis. So can the Incorporation of the premix fuel in the cavity are even better graded and a better adaptation of the combustion to different operating conditions can be achieved.
  • FIG. 1 shows a longitudinal cross-section of a conical burner 1 according to the prior art, as shown for example in the EP 0 321 809 A1 is described.
  • FIG. 2 shows a cross section along the line AA of the burner shown in FIG.
  • the conical cavity 8 of the burner 1 is formed by two part cone bodies 7 displaced radially relative to one another.
  • tangential air inlet slots 11 are formed, through which the mixed with Vormischbrennstoff 3 combustion air 12 flows into the conical cavity 8.
  • the burner axis 10 is located centrally and on a line between the longitudinal axes of symmetry 9 of the part cone body 7.
  • a jet pipe 2 is mounted to inject liquid fuel 4 into the burner chamber 8.
  • pilot fuel 6 is introduced into the conical cavity. Air is introduced to the shield 5 between the pilot fuel 6 and the liquid fuel 4 to prevent premature mixing of liquid fuel 4 and pilot fuel 6 and thus premature ignition of the fuels.
  • the liquid fuel 4 injected through the jet pipe 2 forms a conical fuel column which is surrounded by the rotating combustion air 12 mixed with premix fuel 3.
  • the strength of the rotation depends on the design of the cone angle and the number and width of the air inlet slots 11. With a suitable selection of these parameters, the ignition of the fuel mixture takes place at the output of the burner 1, wherein in the region of the burner port 13, a flame stabilization by the Forming a backflow adjusts.
  • the fuel outlet openings 15 for introducing the premix fuel 3 are attached to the edges of the air inlet slots 11.
  • a high pressure for the injection of the premix fuel 3 in the incoming at high velocity combustion air stream 12 is required.
  • the injection occurs from one side of the air inlet slot 11.
  • the fuel feeds 14, which are integrated in the partial cone bodies 7, are exposed to high thermal loads due to the contact on the one hand with cold fuel and on the other hand with hot combustion air, which can lead to a shorter service life of these components. Since the fuel feeds 14 and the fuel outlet openings 15 are an integral part of the cast part cone bodies 7, it is necessary to replace the entire burner 1 when using a different fuel. In addition, the integration of the fuel supply lines 14 and the fuel outlet openings 15 in the cast part cone body 7 is technically complex and expensive.
  • Fig. 3 shows a longitudinal cross-section of a conical burner 1 with the centrally mounted in the inflow region of the combustion air flow 12 means for injection of premix fuel 3 in the air inlet slots 11.
  • Fig. 4 shows a corresponding cross section along the line B-B of the burner shown in Fig. 3. Reference will now be made to reference numerals of both FIG. 3 and FIG. 4.
  • the burner 1 shown in FIGS. 3 and 4 has fuel feeds 14 that are not components of the partial cone body 7. They are designed as an independent component, which is arranged centrally in the inflow region of the combustion air flow 12. Furthermore, on both sides of the fuel supply 14 relative to a cross-sectional plane perpendicular to the burner axis 10 fuel outlet openings 15, the Introduce premix fuel 3 into the combustion air stream 12.
  • the fuel outlet openings 15 have a circular cross-section. In other embodiments, the fuel exit openings may have oval or slot-shaped cross sections.
  • the fuel outlet openings 15 of a tangential air inlet slot 11 are supplied with premix fuel 3 via a common fuel feed 14.
  • the fuel supply 14 may be provided with means which regulate the mass flow of the fuel in order to adapt it to the current operating conditions of the burner.
  • the fuel supply 14 is arranged spatially in front of the air inlet slots 11, that is to say in a region of a lower velocity of the combustion air stream 12 than directly in the air inlet slots. This reduces aerodynamic losses and the required pressure for the injection of premix fuel 3.
  • the fuel feeds 14 have a streamlined profile with respect to a cross-sectional plane perpendicular to the burner axis 10 in order to reduce the pressure loss during the inflow of the combustion air 12.
  • premix fuel 3 is introduced into the combustion air flow 12 centrally and on both sides of the fuel feed 14, a relatively homogeneous mixing of premix fuel 3 and combustion air 12 results, which leads to combustion in the burner 1 with low nitrogen emissions.
  • the premix fuel supply as an independent component, not the entire burner 1 must be replaced when using a different fuel, but only the component for the Vormischbrennstoffzu operation. It is also possible to retrofit other burners with such a device. Furthermore, the technical Producing the cast part cone body less expensive, since the integration of the fuel supply lines 14 and the fuel outlet openings 15 is omitted in the cast part cone body 7. The thermal load of the burner or the partial cone body, which occurs in the burner mentioned in the prior art due to the different temperatures of one hand, cold fuel and hot combustion air, decreases because the direct contact with the cold fuel supplying fuel supply is eliminated.
  • FIG. 5 shows a longitudinal cross section of a conical burner 1 with two groups of fuel outlet openings 15.1, 15.2, which are distributed along two partial areas 16, 17 of the entire length of the tangential air inlet slot 11.
  • FIG. 6 illustrates two cross sections along the lines C-C and D-D of the burner 1 shown in FIG. 5.
  • the fuel supply of the tangential air inlet slot 11 shown here is divided into two separate fuel supply lines 14.1 and 14.2.
  • premix fuel 3 is introduced into the combustion air stream 12 through the fuel outlet openings 15.2, which is supplied via the fuel supply 14.2.
  • premix fuel 3 is introduced into the combustion air flow 12 in the second partial region 17 of the entire length of the air inlet slot 11 via the fuel outlet openings 15.1, which fuel is supplied via the fuel feed 14.1.
  • premix fuel 3 in the combustion air stream 12 allows an optimized adjustment of the burner behavior when starting the gas turbine, for example, or when operating in different load ranges. That's one Supply of premix fuel 3 in separate sections along the burner axis 10 advantageous when starting the gas turbine, if the entire premix fuel supply is preferably carried out in the upstream portion 16.
  • the premix fuel supply can be laid stepwise or continuously to the downstream portion 17 during further startup of the gas turbine to full load.
  • Means for regulating the mass flow of the premix fuel which are not shown here, prove to be particularly advantageous in order to independently apply premix fuel 3 to the fuel feeds 14.1, 14.2 and to regulate the mass flow of premix fuel 3 within a fuel feed 14.1, 14.2.
  • Fig. 7 shows a longitudinal cross-section of a cylindrical UTC burner 1 (referred to as burners of the United Technologies Corporation, for example, one of these UTC burners is shown in Figs WO 93/17279 shown; the WO 93/17279 is hereby considered to be fully incorporated in the description) with a burner port 13 and the means centrally located in the inflow region of the combustion air stream for injecting premix fuel 3 into the air inlet slots 11.
  • the means for injecting fuel 18 into the cavity of the burner 1 are as a conical body are executed, the apex of which is aligned downstream and a plurality of annularly arranged on the apex outlet nozzles 19 for the pilot fuel 6 has.
  • the illustrated burner 1 fuel feeds 14, which are not components of the part cylinder body. They are designed as independent components which are arranged centrally in the inflow region of the combustion air flow, that is in the air inlet slots 11.
  • the fuel feeds 14 have fuel outlet openings 15, which introduce the premix fuel 3 in the combustion air flow.
  • the fuel outlet openings 15 have a circular cross-section. Alternatively, the fuel outlet openings may also have oval or slot-shaped cross sections.

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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)
EP06115305A 2005-06-17 2006-06-12 Brûleur pour combustion à prémélange Not-in-force EP1734306B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH10312005 2005-06-17

Publications (2)

Publication Number Publication Date
EP1734306A1 true EP1734306A1 (fr) 2006-12-20
EP1734306B1 EP1734306B1 (fr) 2010-09-08

Family

ID=34975044

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06115305A Not-in-force EP1734306B1 (fr) 2005-06-17 2006-06-12 Brûleur pour combustion à prémélange

Country Status (6)

Country Link
US (1) US7975486B2 (fr)
EP (1) EP1734306B1 (fr)
CN (1) CN1880848A (fr)
AT (1) ATE480737T1 (fr)
DE (1) DE502006007811D1 (fr)
ES (1) ES2352679T3 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009127240A1 (fr) * 2008-04-16 2009-10-22 Man Turbo Ag Procédé de fonctionnement d'un brûleur à pré-mélange et brûleur à prémélange approprié pour mettre ledit procédé en oeuvre
US9062886B2 (en) 2010-01-26 2015-06-23 Alstom Technology Ltd. Sequential combustor gas turbine including a plurality of gaseous fuel injection nozzles and method for operating the same

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* Cited by examiner, † Cited by third party
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CH701905A1 (de) * 2009-09-17 2011-03-31 Alstom Technology Ltd Verfahren zum Verbrennen wasserstoffreicher, gasförmiger Brennstoffe in einem Brenner sowie Brenner zur Durchführung des Verfahrens.
US20110173983A1 (en) * 2010-01-15 2011-07-21 General Electric Company Premix fuel nozzle internal flow path enhancement
WO2014179956A1 (fr) * 2013-05-09 2014-11-13 Zheng Shi Système et procédé destinés à la combustion à petite échelle de combustibles solides pulvérisés
CN105090955B (zh) * 2014-05-20 2018-10-26 林内株式会社 扁平燃烧器
USD842981S1 (en) * 2017-05-24 2019-03-12 Hamworthy Combustion Engineering Limited Atomizer
CN107036100B (zh) * 2017-05-31 2019-02-22 北京理工大学 一种带扩张段的轴切多旋流气液固多相流燃烧器
JP7446077B2 (ja) * 2019-10-04 2024-03-08 三菱重工業株式会社 ガスタービン用燃焼器、ガスタービン及び油燃料の燃焼方法
CN113654804B (zh) * 2021-07-15 2022-09-16 哈尔滨工程大学 多成分气体高速混合的定容弹进气系统及其使用方法
CN113551864B (zh) * 2021-08-30 2023-05-09 重庆大学 一种主动旋转式气流场试验系统

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Publication number Priority date Publication date Assignee Title
US5244380A (en) * 1991-03-12 1993-09-14 Asea Brown Boveri Ltd. Burner for premixing combustion of a liquid and/or gaseous fuel
US5489203A (en) * 1993-09-06 1996-02-06 Abb Research Ltd. Method of operating a premixing burner
US5588824A (en) * 1994-12-19 1996-12-31 Abb Management Ag Injection nozzle
EP0981016A1 (fr) * 1998-08-19 2000-02-23 Asea Brown Boveri AG Brûleur et procédé de fonctionnement d'un moteur à combustion interne
WO2001096785A1 (fr) * 2000-06-15 2001-12-20 Alstom (Switzerland) Ltd Procede pour l'exploitation d'un bruleur et bruleur a injection etagee de gaz premelange

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CH674561A5 (fr) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
CH680467A5 (fr) * 1989-12-22 1992-08-31 Asea Brown Boveri
DE19736902A1 (de) * 1997-08-25 1999-03-04 Abb Research Ltd Brenner für einen Wärmeerzeuger
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
DE10049205A1 (de) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Verfahren und Vorrichtung zur Brennstoffversorgung eines Vormischbrenners

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5244380A (en) * 1991-03-12 1993-09-14 Asea Brown Boveri Ltd. Burner for premixing combustion of a liquid and/or gaseous fuel
US5489203A (en) * 1993-09-06 1996-02-06 Abb Research Ltd. Method of operating a premixing burner
US5588824A (en) * 1994-12-19 1996-12-31 Abb Management Ag Injection nozzle
EP0981016A1 (fr) * 1998-08-19 2000-02-23 Asea Brown Boveri AG Brûleur et procédé de fonctionnement d'un moteur à combustion interne
WO2001096785A1 (fr) * 2000-06-15 2001-12-20 Alstom (Switzerland) Ltd Procede pour l'exploitation d'un bruleur et bruleur a injection etagee de gaz premelange

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009127240A1 (fr) * 2008-04-16 2009-10-22 Man Turbo Ag Procédé de fonctionnement d'un brûleur à pré-mélange et brûleur à prémélange approprié pour mettre ledit procédé en oeuvre
US10557634B2 (en) 2008-04-16 2020-02-11 Man Energy Solutions Se Method for operating a premix burner, and a premix burner for carving out the method
US9062886B2 (en) 2010-01-26 2015-06-23 Alstom Technology Ltd. Sequential combustor gas turbine including a plurality of gaseous fuel injection nozzles and method for operating the same
DE102011008009B4 (de) * 2010-01-26 2019-07-18 Ansaldo Energia Switzerland AG Verfahren zum Betreiben einer Gasturbine und Gasturbine

Also Published As

Publication number Publication date
US20070026353A1 (en) 2007-02-01
ATE480737T1 (de) 2010-09-15
EP1734306B1 (fr) 2010-09-08
ES2352679T3 (es) 2011-02-22
DE502006007811D1 (de) 2010-10-21
US7975486B2 (en) 2011-07-12
CN1880848A (zh) 2006-12-20

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