EP0694730B1 - Bruleur - Google Patents

Bruleur Download PDF

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Publication number
EP0694730B1
EP0694730B1 EP95810443A EP95810443A EP0694730B1 EP 0694730 B1 EP0694730 B1 EP 0694730B1 EP 95810443 A EP95810443 A EP 95810443A EP 95810443 A EP95810443 A EP 95810443A EP 0694730 B1 EP0694730 B1 EP 0694730B1
Authority
EP
European Patent Office
Prior art keywords
flow
burner
tangential
sectional bodies
burner according
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.)
Expired - Lifetime
Application number
EP95810443A
Other languages
German (de)
English (en)
Other versions
EP0694730A2 (fr
EP0694730A3 (fr
Inventor
Klaus Dr. Döbbeling
Hans Peter Knöpfel
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.)
Alstom SA
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 EP0694730A2 publication Critical patent/EP0694730A2/fr
Publication of EP0694730A3 publication Critical patent/EP0694730A3/fr
Application granted granted Critical
Publication of EP0694730B1 publication Critical patent/EP0694730B1/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
    • 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
    • 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
    • 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 according to the preamble of claim 1.
  • EP-A1-0 321 809 is a premix burner of double cone Design known, which consists essentially of two hollow, conical, nested in the direction of flow Partial bodies exist, their respective axes of longitudinal symmetry run offset from each other. These against each other running dislocation forms along adjacent walls the partial body in the longitudinal extent tangential channels or Air inlet slots through which a combustion air flow flows into the cone cavity. In this cone cavity there is at least a fuel nozzle housed. That burner contrasts with the previous state of the art Flame stabilization, efficiency and pollutant emissions represents a leap in quality.
  • the invention seeks to remedy this.
  • the invention how it is characterized in the claims, the task lies precautions for a burner of the type mentioned at the beginning to propose which flame stability also in guaranteed transient load range.
  • the main advantages of the invention can be seen in that with it a better flame stability over the whole To achieve load range, especially in the lower load range is. As soon as the flame front remains 100% stable, one is possible overheating of the burner by migration of the flame no longer to fear upstream.
  • the burner also less susceptible to vibrations, for example stimulated by combustion processes via the combustion chamber and fireplace system can be reinforced.
  • Another important advantage of the invention is that see that a restriction of the load range no longer must be considered.
  • FIG. 1 Cuts according to Figures 2-4 are used, if necessary also Fig. 5.
  • Fig. 1 are to be designed in it according to Figures 2-4 schematically shown guide plates 121a, 121b only hinted been recorded. The following is in the description of Fig. 1 referred to the remaining figures as required.
  • the premix burner 100 consists of two hollow ones conical partial bodies 101, 102 which are offset from one another are nested.
  • the transfer of the respective Center axis or longitudinal axis of symmetry 201b, 202b of the conical Partial body 101, 102 creates each other on both sides, in mirror image arrangement, each with a tangential air inlet slot 119, 120 free (Fig. 2-4), through which the Combustion air 115 in the interior of the premix burner 100, i.e. flows into the cone cavity 114.
  • the flow cross section this air inlet slots 119, 120 takes in the direction of flow from, the course continuously conical or can be intermittent.
  • FIG. 5 shows what the conical As far as the course of the air inlet slots 119, 120 is concerned, such a configuration.
  • the cone shape of the partial body shown 101, 102 has a certain direction of flow fixed angle.
  • the partial body 101, 102 in the direction of flow have an increasing or decreasing taper, similar a trumpet resp. Tulip.
  • the two tapered Partial bodies 101, 102 each have a cylindrical initial part 101a, 102a, which also, analogous to the tapered Partial bodies 101, 102, offset from one another, so that the tangential air inlet slots 119, 120 via the entire length of the premix burner 100 are present.
  • a nozzle 103 is accommodated in the cylindrical starting part, the injection 104 of approximately the narrowest cross section that formed by the tapered body 101, 102 Cone cavity 114 coincides.
  • the injection capacity and the type of this nozzle 103 depends on the given Parameters of the respective premix burner 100.
  • the premix burner can be purely conical, i.e.
  • the conical partial bodies 101, 102 each have one Fuel line 108, 109 on which along the tangential Entry slots 119, 120 arranged and with injection openings 117 are provided, by which preferably a gaseous fuel 113 into the one flowing through there Combustion air 115 is injected, as shown by arrows 116 want to symbolize.
  • These fuel lines 108, 109 are preferably at the latest at the end of the tangential inflow, before entering the cone cavity 114, placed, this to get an optimal air / fuel mixture.
  • the outlet opening of the premix burner is on the combustion chamber side 122 100 into a front wall 110, in which a number Bores 110a are present.
  • Fuel is a liquid fuel 112, which is enriched at most with a recirculated exhaust gas can be. This fuel 112 is under one acute angle injected into the cone cavity 114. From the Nozzle 103 thus forms a conical fuel profile 105, the rotating combustion air flowing in tangentially 115 is enclosed.
  • the concentration of fuel 112 continuously through the incoming combustion air 115 for optimal mixing reduced. If the premix burner 100 has a gaseous one Operated fuel 113, this is preferably done via opening nozzles 117, the formation of this Fuel / air mixture directly at the end of the air inlet slots 119, 120 comes about.
  • the optimal, homogeneous fuel concentration reached across the cross section. The ignition takes place at the top of the backflow zone 106. Only at this A stable flame front 107 can arise in this place.
  • the swirl number which is the ratio between the tangential and axial velocity components defined along the tangential air inlet slots compared to a uniform flow cross-section a steeper course.
  • the combustion air 115 is additionally preheated or enriched with a recirculated exhaust gas, so supported this is the vaporization of the liquid fuel 112 sustainable before the combustion zone is reached.
  • the same considerations also apply when using the lines 108, 109 supplied instead of gaseous, liquid fuels become.
  • the tangential Air inlet slots 119, 120 can be generally determined that the once-fixed backflow zone 106 per se is stable in position, because the swirl number increases in the direction of flow in the area of the cone shape of the premix burner 100 to what is additionally due to the decreasing flow cross section the tangential air inlet slots 119, 120 in Flow direction is supported, which is particularly positive in the transient area.
  • the axial speed within the premix burner 100 further by a corresponding supply, not shown axial combustion air flow, i.e. in favor a stabilization of the backflow zone 106 at the burner outlet can increase this axial flow become.
  • the design of the premix burner 100 is suitable Furthermore, the size and the course of the adjust tangential air inlet slots 119, 120, with what without changing the overall length of the premix burner 100 a relatively large operational bandwidth can be captured.
  • the partial bodies 101, 102 are also in one another level slidable to each other, creating even a Overlap of the same can be controlled. It is even if necessary, the partial body 101, 102 by an opposing to interleave rotating movement in a spiral.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Claims (7)

  1. Brûleur (100) constitué d'au moins deux corps partiels (101, 102) creux, en forme de cône, emboítés l'un dans l'autre dans la direction d'écoulement, dont les axes respectifs de symétrie longitudinale (101b, 102b) sont décalés l'un par rapport à l'autre de telle sorte que les parois voisines des corps partiels forment dans leur extension longitudinale des canaux tangentiels (119, 120) pour un flux d'air de combustion, au moins un gicleur de combustible (117) étant présent dans l'espace conique creux (114) formé par les corps partiels, caractérisé en ce que la section transversale d'écoulement des canaux tangentiels (119, 120) diminue dans la direction d'écoulement du brûleur (100).
  2. Brûleur selon la revendication 1, caractérisé en ce que dans la zone des canaux tangentiels (119, 120), d'autres gicleurs à combustible (117) sont disposés dans leur extension longitudinale.
  3. Brûleur selon la revendication 1, caractérisé en ce que la section transversale d'écoulement des canaux tangentiels (119, 120) évolue coniquement dans la direction d'écoulement du brûleur (100).
  4. Brûleur selon la revendication 1, caractérisé en ce que les corps partiels (101, 102) s'évasent en forme de cônes à angle fixe dans la direction d'écoulement.
  5. Brûleur selon la revendication 1, caractérisé en ce que les corps partiels (101, 102) présentent une pente de cône croissante dans la direction d'écoulement.
  6. Brûleur selon la revendication 1, caractérisé en ce que les corps partiels (101, 102) présentent une pente de cône décroissante dans la direction d'écoulement.
  7. Brûleur selon la revendication 1, caractérisé en ce que les corps partiels (101, 102) sont emboítés l'un dans l'autre en spirale.
EP95810443A 1994-07-25 1995-07-05 Bruleur Expired - Lifetime EP0694730B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4426353 1994-07-25
DE4426353A DE4426353A1 (de) 1994-07-25 1994-07-25 Brenner

Publications (3)

Publication Number Publication Date
EP0694730A2 EP0694730A2 (fr) 1996-01-31
EP0694730A3 EP0694730A3 (fr) 1998-05-06
EP0694730B1 true EP0694730B1 (fr) 2001-12-19

Family

ID=6524115

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810443A Expired - Lifetime EP0694730B1 (fr) 1994-07-25 1995-07-05 Bruleur

Country Status (5)

Country Link
US (1) US5562441A (fr)
EP (1) EP0694730B1 (fr)
JP (1) JPH08189611A (fr)
CN (1) CN1118859A (fr)
DE (2) DE4426353A1 (fr)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19547914A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Vormischbrenner für einen Wärmeerzeuger
DE19548851A1 (de) * 1995-12-27 1997-07-03 Asea Brown Boveri Vormischbrenner
DE19548853A1 (de) * 1995-12-27 1997-07-03 Abb Research Ltd Kegelbrenner
DE19610930A1 (de) * 1996-03-20 1997-09-25 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE19654741A1 (de) * 1996-12-30 1998-07-02 Abb Research Ltd Kesselanlage für eine Wärmeerzeugung
DE59708077D1 (de) * 1997-12-22 2002-10-02 Alstom Brenner
DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
EP1279898B1 (fr) 2001-07-26 2008-09-10 ALSTOM Technology Ltd Brûleur à prémélange offrant une haute stabilité de flamme
WO2006058843A1 (fr) * 2004-11-30 2006-06-08 Alstom Technology Ltd Procede et dispositif de combustion d'hydrogene dans un bruleur a premelange
EP1843098A1 (fr) * 2006-04-07 2007-10-10 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
CN102224379B (zh) * 2008-09-22 2014-09-24 达塞尔·卡尔灵顿 空气流动控制后壳体构件
EP2722591A1 (fr) * 2012-10-22 2014-04-23 Alstom Technology Ltd Brûleur à multiples cones pour une turbine à gaz

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1069243A (en) * 1912-03-13 1913-08-05 George L Fogler Furnace-burner.
DE3662462D1 (en) * 1985-07-30 1989-04-20 Bbc Brown Boveri & Cie Dual combustor
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
EP0518072A1 (fr) * 1991-06-14 1992-12-16 Asea Brown Boveri Ag Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation pour turbine à gaz ou un foyer
CH684962A5 (de) * 1991-07-03 1995-02-15 Asea Brown Boveri Brenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder einer Feuerungsanlage.
DE59209209D1 (de) * 1992-10-16 1998-04-02 Asea Brown Boveri Gasbetriebener Vormischbrenner
DE4237187A1 (de) * 1992-11-04 1994-05-05 Raimund Prof Dr Ruderich Wirbelerzeuger für einen Brenner

Also Published As

Publication number Publication date
EP0694730A2 (fr) 1996-01-31
CN1118859A (zh) 1996-03-20
DE4426353A1 (de) 1996-02-01
JPH08189611A (ja) 1996-07-23
DE59509959D1 (de) 2002-01-31
EP0694730A3 (fr) 1998-05-06
US5562441A (en) 1996-10-08

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