EP0899508A1 - Brûleur pour un dispositif à chaleur - Google Patents

Brûleur pour un dispositif à chaleur Download PDF

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Publication number
EP0899508A1
EP0899508A1 EP98810651A EP98810651A EP0899508A1 EP 0899508 A1 EP0899508 A1 EP 0899508A1 EP 98810651 A EP98810651 A EP 98810651A EP 98810651 A EP98810651 A EP 98810651A EP 0899508 A1 EP0899508 A1 EP 0899508A1
Authority
EP
European Patent Office
Prior art keywords
burner according
swirl generator
flow
burner
fuel
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
EP98810651A
Other languages
German (de)
English (en)
Other versions
EP0899508B1 (fr
Inventor
Klaus Dr. Döbbeling
Christian Dr. Steinbach
Thomas Ruck
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 Switzerland GmbH
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Publication of EP0899508A1 publication Critical patent/EP0899508A1/fr
Application granted granted Critical
Publication of EP0899508B1 publication Critical patent/EP0899508B1/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
    • 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
    • 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
    • F23D11/38—Nozzles; Cleaning devices therefor
    • 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
    • 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
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the present invention relates to a burner for a heat generator according to Preamble of claim 1.
  • the invention seeks to remedy this.
  • the invention as set out in the claims is characterized, the task is based on a burner at the beginning to propose precautions by which a perfect premix of the fuel used is guaranteed, while maintaining an operationally reliable and optimal flame positioning.
  • the injection of the fuel is proposed on a certain radius from the burner axis.
  • the main advantages of the invention are that enrichment the central zone is prevented, and the fuel drops increasing radius within the premixing section a stronger radial acceleration are exposed in such a way that they enter into the Can mix in combustion air well.
  • the number of injection points is adapted to the burner design, at least one injection per bowl or scoop is to be provided.
  • Fig. 1 shows the overall structure of a burner.
  • a swirl generator 100 effective, the design of which is shown in more detail in the following FIGS. 2-5 is shown and described.
  • This swirl generator 100 is a cone-shaped structure that tangentially inflows several times from a tangentially Combustion air flow 115 is applied.
  • the one forming here Flow is provided based on a swirl generator 100 downstream Transition geometry seamlessly transferred into a transition piece 200, that no separation areas can occur there.
  • the configuration of this Transition geometry is described in more detail in FIG. 6.
  • This transition piece 200 is on the outflow side of the transition geometry through a pipe 20 extended, both parts of the actual mixing tube 220, also mixing section called, form the burner.
  • the mixing tube 220 can be made from one consist of only one piece, i.e. then that the transition piece 200 and Tube 20 are fused into a single coherent structure, keeping the characteristics of each part. Become a transition piece 200 and tube 20 created from two parts, so these are by one Socket ring 10 connected, this head side as an anchoring surface for serves the swirl generator 100. Such a sleeve ring 10 also has the Advantage that different mixing tubes can be used. Outflow side of the tube 20 is the actual combustion chamber 30, which is here is only symbolized by the flame tube.
  • the mixing tube 220 fulfills that Condition that a defined mixing section is provided downstream of the swirl generator 100 in which a perfect premixing of different fuelskind is achieved.
  • This mixing section ie the mixing tube 220, enables the further a loss-free flow control, so that there is also an operative connection cannot initially form a backflow zone with the transition geometry, with which over the length of the mixing tube 220 to the quality of the mixture for all types of fuel Influence can be exercised.
  • This mixing tube 220 has another another property, which then is that in the mixing tube 220 itself Axial velocity profile has a pronounced maximum on the axis, so that the flame cannot be re-ignited from the combustion chamber. Indeed it is correct that with such a configuration this axial speed drops to the wall.
  • the mixing tube 220 becomes a number in the flow and circumferential directions regularly or irregularly distributed holes 21 different Provide cross sections and directions through which an amount of air enters the interior of the mixing tube 220 flows, and along the wall in the manner of a film induce an increase in speed.
  • the flow cross section of the Mixing tube 220 downstream of the transition channels 201 which are already mentioned transition geometry form, undergoes a narrowing, whereby the entire speed level within the mixing tube 220 is raised becomes.
  • these bores 21 run at an acute angle the burner axis 60.
  • the outlet corresponds to the transition channels 201 the narrowest flow cross section of the mixing tube 220.
  • transition channels 201 therefore bridge the respective cross-sectional difference, without negatively influencing the flow formed. If the chosen precaution in guiding the pipe flow 40 along the Mixing tube 220 triggers an intolerable pressure loss, can counteract this Remedy can be created by not at the end of the mixing tube in the figure shown diffuser is provided. At the end of the mixing tube 220 closes a combustion chamber 30, wherein between the two flow cross sections a cross-sectional jump is present. Only here does a central backflow zone form 50, which has the properties of a flame holder. Forms there is a flow within this cross-sectional jump during operation Edge zone, in which by the prevailing negative pressure Vertebral detachments occur, this leads to an increased ring stabilization the backflow zone 50.
  • the combustion chamber 30 has a number of openings at the end 31 through which an amount of air jumps directly into the cross section flows, and there lower others help that the ring stabilization of the Backflow zone 50 is strengthened.
  • the Generation of a stable backflow zone 50 also a sufficiently high one Twist number in a pipe required. If this is initially undesirable, you can stable return flow zones through the supply of small, strongly swirled air flows generated at the end of the tube, for example by tangential openings become. It is assumed here that the amount of air required for this in is about 5-20% of the total air volume.
  • Fig. 2-5 The configuration of the tear-off edge at the end of the mixing tube 220 is shown in FIG. 7 described in more detail.
  • the first part of the burner according to FIG. 1 forms the swirl generator shown in FIG. 2 100.
  • This consists of two hollow conical partial bodies 101, 102, which are nested in a staggered manner.
  • the number of conical Partial body can of course be larger than two, like the examples 4 and 5 show.
  • the number of conical partial bodies depends in each case depends on which operating mode is used. It is with certain operating constellations not ruled out a single spiral Provide swirl generator.
  • the offset of the respective central axis or longitudinal symmetry axes 201b, 202b of the tapered partial bodies 101, 102 to one another creates a mirror image of the neighboring wall, one tangential channel each, i.e. an air inlet slot 119, 120 (FIG.
  • the cone shape of the partial body shown 101, 102 in the flow direction has a certain fixed angle.
  • the partial bodies 101, 102 in Flow direction have an increasing or decreasing cone inclination, similar to a trumpet or Tulip. The latter two forms are not recorded in the drawing, since they can be easily understood by the expert are.
  • the two conical partial bodies 101, 102 each have a cylindrical one Initial part 101a, 102a, which also, analogous to the conical partial bodies 101, 102, run offset from one another, so that the tangential air inlet slots 119, 120 are present over the entire length of the swirl generator 100.
  • a main nozzle 103 In the area of the cylindrical initial part is a main nozzle 103, preferably for one liquid fuel 112 housed.
  • the fuel is introduced into the cone cavity 114 here a decentralized injection, which is carried out by a number of nozzle pipes 104 becomes.
  • the angle of the fuel jet formed from these nozzle tubes 104 105 compared to the burner axis corresponds approximately the tapered course of the partial bodies 101, 102. If the swirl generator is characterized by an in blade configuration acting on a plane, the angle corresponds the fuel jet 105 the angle of attack of the blades compared to the Combustion chamber axis. In this connection, reference is made to FIG. 8.
  • the preferably to be provided injection position of the fuel jet 105 with respect the inflow level of the combustion air 115 is closer to Fig. 3-5 explained.
  • the injection capacity and injection type of the individual nozzle pipes 104 depends on the given parameters of the respective burner. Each depending on the burner size, turbulence-assisted Provide pressure atomization nozzle for the individual nozzle tubes 104, the Injection pressure to achieve good atomization qualities be around 100 bar should.
  • the length of the nozzle tubes 104 is the required injection radius adjust, but should not be more than 1/4 of the partial body, respectively. Blade length (Fig. 8), otherwise there is an inherent risk that during operation with gaseous fuels, the nozzle tubes 104 act as a flame holder. For long partial body or blades (Fig. 8) a decentralized injection must be provided, in which the nozzle tubes 104 directly from the partial body, respectively. Shovels (Fig. 8) emerges in the wake flow.
  • the fuel can be targeted Zones of high air velocity are sprayed.
  • a company can also be operated Maintained with minimized pollutant emissions without the addition of water gets along. It is then essential that the fine atomization is connected with a high fuel pulse, good conditions for rapid evaporation of fuel as well as maximized premix.
  • the swirl generator 100 can be purely conical, that is to say without a cylindrical one Initial parts 101a, 102a.
  • the tapered partial bodies 101, 102 have furthermore each have a fuel line 108, 109 which runs along the tangential Air inlet slots 119, 120 arranged and with injection openings 117 are provided, by means of which a gaseous fuel 113 in preferably the combustion air 115 flowing through there is injected, as is the case with the arrows 116 want to symbolize.
  • These fuel lines 108, 109 are preferred at the latest at the end of the tangential inflow, before entering the cone cavity 114, placed this in order to obtain an optimal air / fuel mixture.
  • the fuel 112 fed through the main nozzle 103 is concerned as mentioned, it is normally a liquid fuel, one of which is Mixture formation with another medium is easily possible.
  • the combustion air 115 additionally preheated, or for example with a recycled flue gas or exhaust gas enriched, this supports sustainably the vaporization of the liquid fuel 112 within the length of the burner pre-mixing section before this mixture in the downstream Combustion stage flows.
  • liquid fuels should be supplied via lines 108, 109.
  • a reduction in tangential air inlet slots 119, 120 the faster formation of a backflow zone already in the area of the swirl generator favored.
  • the axial speed within the swirl generator 100 can be by a corresponding supply of an axial combustion air flow 115a change, this air inflow being held so that the Fuel jet 105 is not affected or negatively influenced.
  • a corresponding Swirl generation prevents the formation of flow separations within the the mixing tube 100 downstream of the swirl generator.
  • the construction of the swirl generator 100 is also excellent, the size of the tangential Air inlet slots 119, 120 to change, so without changing the overall length of the swirl generator 100 a relatively large operational bandwidth can be detected can.
  • the partial bodies 101, 102 are also in another Plane can be shifted towards each other, which even overlaps them can be provided. It is also possible to use the partial bodies 101, 102 can be nested spirally in one another by a counter-rotating movement. Thus, it is possible to change the shape, size and configuration of the tangential Air inlet slots 119, 120 to vary as desired, with which the swirl generator 100 can be used universally without changing its overall length.
  • FIG. 3 now shows the geometric configuration of the guide plates 121a, 121b. They have a flow introduction function, and this, accordingly their length, the respective end of the tapered partial body 101, 102 in the direction of flow extend towards the combustion air 115.
  • the channeling the combustion air 115 into the cone cavity 114 can be opened or closing the guide plates 121a, 121b by one in the area of the entrance thereof Channel in the cone cavity 114 pivot point 123 are optimized, this is particularly necessary if the original gap size of the tangential Air inlet slots 119, 120 are to be changed dynamically.
  • these dynamic arrangements can also be provided statically, by making required baffles an integral part with the tapered Form partial bodies 101, 102.
  • the swirl generator 100 can also be used without Baffles are operated, or other aids can be provided for this become.
  • the swirl generator 100 now consists of four partial bodies 130, 131, 132, 133 is constructed.
  • the associated longitudinal symmetry axes for each sub-body are marked with the letter a. To this Configuration is to be said that it is due to the lower generated with it Twist strength and in cooperation with a correspondingly enlarged Slot width is best suited, the bursting of the vortex flow on the downstream side to prevent the swirl generator in the mixing tube, thus causing the mixing tube to can fulfill the intended role.
  • FIG. 5 differs from FIG. 4 in that the partial body 140, 141, 142, 143 have a blade profile shape which is used to provide a certain Flow is provided. Otherwise, the mode of operation of the swirl generator stayed the same.
  • the admixture of fuel 116 in the combustion air flow 115 happens from inside the blade profiles, i.e. the fuel line 108 is now integrated in the individual blades.
  • FIGS. 3-5 that is within the flow cross section positioned one-tip positions of the fuel jet 105, which of the Flow of the combustion air corresponds to the opposite sides.
  • a nozzle tube is provided for each combustion air inflow, one such Assignment is not essential.
  • the individual fuel jets 105 are positioned in such a way that, in compliance with the procedure shown in FIG underlying angle of the fuel jet, along the leeward side of the partial body 101 and 102, 130-133, 140-143, as can be seen from FIGS. 3-5, respectively. of the guide vanes act in a configuration of the swirl generator according to FIG. 8. There the drop spray is exposed to lower aerodynamic forces, so that it is better mixed radially into the combustion air 115.
  • the transition geometry is corresponding for a swirl generator 100 with four partial bodies 4 or 5, built. Accordingly, the transition geometry as a natural extension of the upstream partial bodies, four transition channels 201 on, whereby the conical quarter area of said partial body is extended until the wall of the tube 20 resp. of the mixing tube 220 cuts.
  • the same considerations also apply if the swirl generator comes from another Principle, as that described under Fig. 2, is constructed.
  • the down area of the individual transition channels 201 running in the direction of flow has a spiral shape in the flow direction, which has a describes crescent-shaped course, corresponding to the fact that present the flow cross section of the transition piece 200 in the flow direction flared.
  • the swirl angle of the transition channels 201 in the flow direction is selected so that the pipe flow then up to the cross-sectional jump there is still a sufficiently large distance at the combustion chamber inlet, to achieve a perfect premix with the injected fuel. Furthermore, the measures mentioned above also increase the axial speed on the mixing tube wall downstream of the swirl generator. The Transition geometry and the measures in the area of the mixing tube a significant increase in the axial speed profile towards the center of the mixing tube, so that the risk of early ignition is decisively counteracted becomes.
  • the flow cross section of the tube 20 receives one in this area Transition radius R, the size of which basically depends on the flow within of the tube 20 depends.
  • This radius R is chosen so that the Applies flow to the wall and so the swirl number increases sharply.
  • the size of the radius R can be defined so that it is> 10% of the inside diameter d of the tube is 20.
  • the backflow bladder 50 increases enormously.
  • This radius R runs to the exit plane of the tube 20, the angle ⁇ between the beginning and end of curvature is ⁇ 90 °.
  • FIG. 8 shows a swirl generator 150 which uses swirl blading 151 is constructed.
  • a swirl generator Concentric to the central main nozzle powered by fuel 112 103 a swirl generator is scheduled, which consists of a swirl blading 151 exists, i.e. the blades arranged in a ring effect here a swirl, analogous to that of Fig. 2.
  • the combustion air supplied 115 can take place here using an annular channel, not shown in more detail, which extends upstream of the swirl blading 151.
  • the central main fuel nozzle 103 Downstream of the swirl blading 151, the central main fuel nozzle 103 has a number of nozzle pipes 104, whose fuel jet 105 is the angle of attack of the swirl blades 151 relative to the burner axis 60 respectively.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Spray-Type Burners (AREA)
EP98810651A 1997-08-25 1998-07-08 Brûleur pour un dispositif à chaleur Expired - Lifetime EP0899508B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19736902A DE19736902A1 (de) 1997-08-25 1997-08-25 Brenner für einen Wärmeerzeuger
DE19736902 1997-08-25

Publications (2)

Publication Number Publication Date
EP0899508A1 true EP0899508A1 (fr) 1999-03-03
EP0899508B1 EP0899508B1 (fr) 2004-01-28

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Family Applications (1)

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EP98810651A Expired - Lifetime EP0899508B1 (fr) 1997-08-25 1998-07-08 Brûleur pour un dispositif à chaleur

Country Status (5)

Country Link
US (1) US6102692A (fr)
EP (1) EP0899508B1 (fr)
JP (1) JP4442940B2 (fr)
CN (1) CN1318797C (fr)
DE (2) DE19736902A1 (fr)

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WO2006042796A2 (fr) * 2004-10-18 2006-04-27 Alstom Technology Ltd Bruleur pour turbine a gaz
WO2007135691A1 (fr) * 2006-05-22 2007-11-29 Spray Engineering Devices Limited buse d'éjection AMéLIORée pour condensateur à pulvérisations et à jets multiples
CN104456553B (zh) * 2014-11-24 2016-08-10 浙江大学 适用于研究液体燃料燃烧特性的锥形火焰燃烧器及其方法
CN111503659A (zh) * 2020-04-28 2020-08-07 中国航发湖南动力机械研究所 火焰筒、微型涡喷发动机及火焰筒的制备工艺

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DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
DE50110801D1 (de) 2000-12-23 2006-10-05 Alstom Technology Ltd Brenner zur Erzeugung eines Heissgases
EP1262714A1 (fr) * 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
DE10128063A1 (de) * 2001-06-09 2003-01-23 Alstom Switzerland Ltd Brennersystem
DE502005005999D1 (de) * 2004-01-20 2009-01-02 Alstom Technology Ltd Vormischbrenneranordnung sowie Verfahren zum Betreiben einer Brennkammer
WO2005078348A1 (fr) * 2004-02-12 2005-08-25 Alstom Technology Ltd Systeme de bruleur de premelange pour faire fonctionner une chambre de combustion, et procede pour faire fonctionner une chambre de combustion
WO2006058843A1 (fr) * 2004-11-30 2006-06-08 Alstom Technology Ltd Procede et dispositif de combustion d'hydrogene dans un bruleur a premelange
DE502006007811D1 (de) * 2005-06-17 2010-10-21 Alstom Technology Ltd Brenner zur vormischartigen Verbrennung
FR2889292B1 (fr) * 2005-07-26 2015-01-30 Optimise Procede et installation de combustion sans soutien de gaz combustible pauvre a l'aide d'un bruleur et bruleur associe
CA2515923A1 (fr) * 2005-08-05 2007-02-05 Mark A. Dupuis Gicleur
CN101235969B (zh) * 2007-01-31 2014-11-26 通用电气公司 具有同轴燃料-空气通道的逆流喷射机构
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DE102009060844A1 (de) 2009-12-29 2011-06-30 Friedrichs, Arno, 95326 Verfahren zur Herstellung eines Kanäle aufweisenden Kraftstoffeinspritzelementes sowie Kraftstoffeinspritzelement
KR101190128B1 (ko) * 2010-09-15 2012-10-12 강원석 세척용 분사노즐
US8365534B2 (en) 2011-03-15 2013-02-05 General Electric Company Gas turbine combustor having a fuel nozzle for flame anchoring
RU2011115528A (ru) 2011-04-21 2012-10-27 Дженерал Электрик Компани (US) Топливная форсунка, камера сгорания и способ работы камеры сгорания
EP2650612A1 (fr) * 2012-04-10 2013-10-16 Siemens Aktiengesellschaft Brûleur
EP2693117A1 (fr) 2012-07-30 2014-02-05 Alstom Technology Ltd Brûleur de postcombustion et procédé de mélange de carburant/flux d'air porteur dans un brûleur de postcombustion
CN107620958B (zh) * 2017-09-23 2019-02-15 武汉富世达能源科技股份有限公司 一种聚能预热燃烧器
CN108019741A (zh) * 2017-12-10 2018-05-11 罗碧婉 旋涡式锅炉炉膛
CN108036306A (zh) * 2017-12-10 2018-05-15 罗碧婉 旋涡式锅炉烟气燃烧室
FR3099547B1 (fr) * 2019-07-29 2021-10-08 Safran Aircraft Engines Nez d'injecteur de carburant pour turbomachine comprenant une chambre de mise en rotation intérieurement délimitée par un pion
CN115163667B (zh) * 2022-07-27 2024-06-14 合肥工业大学 一种涡旋型出气的平面静压气浮轴承

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WO1995002789A1 (fr) * 1993-07-16 1995-01-26 Radian Corporation APPAREIL ET PROCEDE DESTINES A REDUIRE LES REJETS DE NOx, DE CO ET D'HYDROCARBURES LORS DE LA COMBUSTION DE COMBUSTIBLES GAZEUX
EP0704657A2 (fr) * 1994-10-01 1996-04-03 ABB Management AG Brûleur
US5586878A (en) * 1994-11-12 1996-12-24 Abb Research Ltd. Premixing burner
EP0797051A2 (fr) * 1996-03-20 1997-09-24 Abb Research Ltd. Brûleur pour un générateur de chaleur

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FR2698156B1 (fr) * 1992-11-16 1995-01-27 Rhone Poulenc Chimie Procédé de traitement thermique d'un effluent comprenant des matières organiques polluantes ou un composé inorganique.
DE19547912A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE19547913A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger

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
WO1995002789A1 (fr) * 1993-07-16 1995-01-26 Radian Corporation APPAREIL ET PROCEDE DESTINES A REDUIRE LES REJETS DE NOx, DE CO ET D'HYDROCARBURES LORS DE LA COMBUSTION DE COMBUSTIBLES GAZEUX
EP0704657A2 (fr) * 1994-10-01 1996-04-03 ABB Management AG Brûleur
US5586878A (en) * 1994-11-12 1996-12-24 Abb Research Ltd. Premixing burner
EP0797051A2 (fr) * 1996-03-20 1997-09-24 Abb Research Ltd. Brûleur pour un générateur de chaleur

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006042796A2 (fr) * 2004-10-18 2006-04-27 Alstom Technology Ltd Bruleur pour turbine a gaz
WO2006042796A3 (fr) * 2004-10-18 2006-08-10 Alstom Technology Ltd Bruleur pour turbine a gaz
US7520745B2 (en) 2004-10-18 2009-04-21 Alstom Technology Ltd. Burner for a gas turbine
WO2007135691A1 (fr) * 2006-05-22 2007-11-29 Spray Engineering Devices Limited buse d'éjection AMéLIORée pour condensateur à pulvérisations et à jets multiples
CN104456553B (zh) * 2014-11-24 2016-08-10 浙江大学 适用于研究液体燃料燃烧特性的锥形火焰燃烧器及其方法
CN111503659A (zh) * 2020-04-28 2020-08-07 中国航发湖南动力机械研究所 火焰筒、微型涡喷发动机及火焰筒的制备工艺
CN111503659B (zh) * 2020-04-28 2021-11-09 中国航发湖南动力机械研究所 火焰筒、微型涡喷发动机及火焰筒的制备工艺

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DE19736902A1 (de) 1999-03-04
JP4442940B2 (ja) 2010-03-31
EP0899508B1 (fr) 2004-01-28
CN1318797C (zh) 2007-05-30
US6102692A (en) 2000-08-15
CN1209521A (zh) 1999-03-03
DE59810650D1 (de) 2004-03-04
JPH11118108A (ja) 1999-04-30

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