EP0694730A2 - Bruleur - Google Patents

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Publication number
EP0694730A2
EP0694730A2 EP95810443A EP95810443A EP0694730A2 EP 0694730 A2 EP0694730 A2 EP 0694730A2 EP 95810443 A EP95810443 A EP 95810443A EP 95810443 A EP95810443 A EP 95810443A EP 0694730 A2 EP0694730 A2 EP 0694730A2
Authority
EP
European Patent Office
Prior art keywords
burner
flow
bodies
tangential
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.)
Granted
Application number
EP95810443A
Other languages
German (de)
English (en)
Other versions
EP0694730B1 (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.
  • the invention seeks to remedy this.
  • the invention as characterized in the claims, is based on the object of proposing precautions for a burner of the type mentioned at the outset, which ensures flame stability even in the transient load range.
  • the geometry of the tangential channels undergoes a change: These run conically in the direction of flow towards the burner outlet, with the flow cross-section increasing upstream from the burner outlet.
  • the swirl number which defines the relationship between the tangential and axial speed components, experiences a steeper course along the tangential channels compared to a uniform flow cross section.
  • the flow cross-section there has the original size, which is usually used as a basis.
  • the main advantages of the invention can be seen in the fact that better flame stability can be achieved over the entire load range, in particular in the lower load range. As soon as the flame front remains 100% stable, there is no longer any risk of the burner overheating due to the flame traveling upstream.
  • This maximized flame stabilization also makes the burner less susceptible to vibrations, which can be amplified, for example, by combustion processes via the combustion chamber and chimney system.
  • Another important advantage of the invention is that a restriction of the load range no longer has to be taken into account.
  • FIGS. 2-4 In order to better understand the structure of the premix burner 100, it is advantageous if the individual cuts according to FIGS. 2-4 are used simultaneously with FIG. 1, if necessary also FIG. 5. Furthermore, in order to avoid unnecessary confusion in FIG. 1 shape, the baffles 121a, 121b shown schematically in FIGS. 2-4 have only been hinted at in it. In the description of FIG. 1, reference is made below to the remaining figures as required.
  • the premix burner 100 consists of two hollow, conical partial bodies 101, 102 which are nested in one another offset from one another.
  • the offset of the respective central axis or longitudinal axis of symmetry 201b, 202b of the conical partial bodies 101, 102 to one another creates a tangential air inlet slot 119, 120 on both sides, in a mirror-image arrangement (FIGS. 2-4), through which the combustion air 115 enters the interior of the Premix burner 100, ie flows into the cone cavity 114.
  • the flow cross section of these air inlet slots 119, 120 decreases in the direction of flow, it being possible for the course to be continuously conical or intermittent.
  • FIG. 5 shows such a configuration as far as the conical shape of the air inlet slots 119, 120 is concerned.
  • the conical shape of the partial bodies 101, 102 shown in the flow direction has a specific fixed angle.
  • the partial bodies 101, 102 can have an increasing or decreasing cone inclination in the direction of flow, similar to a trumpet or. Tulip.
  • the above-mentioned shapes are not included in the drawing, since they can easily be reproduced.
  • the two tapered partial bodies 101, 102 each have a cylindrical starting part 101a, 102a, which, similarly to the tapered partial bodies 101, 102, also run offset from one another, so that the tangential air inlet slots 119, 120 are present over the entire length of the premix burner 100.
  • a nozzle 103 is accommodated, the injection 104 of which coincides approximately with the narrowest cross section of the conical cavity 114 formed by the conical partial bodies 101, 102.
  • the injection capacity and the type of this nozzle 103 depend on the specified parameters of the respective premix burner 100.
  • the premix burner can be of a purely conical design, that is to say without cylindrical starting parts 101a, 102a.
  • the conical sub-bodies 101, 102 further each have a fuel line 108, 109, which are arranged along the tangential inlet slots 119, 120 and are provided with injection openings 117, through which a gaseous fuel 113 is preferably injected into the combustion air 115 flowing through there, such as arrows 116 symbolize this.
  • These fuel lines 108, 109 are preferably placed at the latest at the end of the tangential inflow, before entering the cone cavity 114, in order to obtain an optimal air / fuel mixture.
  • the outlet opening of the premix burner 100 merges into a front wall 110, in which a number of bores 110a are provided.
  • the latter come into operation when necessary and ensure that dilution air or cooling air 110b is supplied to the front part of the combustion chamber 122.
  • this air supply ensures flame stabilization at the outlet of the premix burner 100. This flame stabilization becomes important when it comes to supporting the compactness of the flame due to a radial flattening.
  • the fuel supplied through the nozzle 103 is a liquid fuel 112, which may be enriched with a recirculated exhaust gas. This fuel 112 is injected into the cone cavity 114 at an acute angle.
  • a conical fuel profile 105 is thus formed from the nozzle 103 and is enclosed by the rotating combustion air 115 flowing in tangentially.
  • the concentration of the fuel 112 is continuously reduced to an optimal mixing by the incoming combustion air 115.
  • the premix burner 100 is operated with a gaseous fuel 113, this is preferably done via opening nozzles 117, the formation of this fuel / air mixture taking place directly at the end of the air inlet slots 119, 120.
  • the optimal, homogeneous fuel concentration over the cross section is achieved in the region of the vortex run, that is to say in the region of the backflow zone 106 at the end of the premix burner 100.
  • the ignition takes place at the tip of the backflow zone 106. Only at this point can a stable flame front 107 arise. A flashback of the flame into the interior of the premix burner 100, as is latently the case with known premixing sections, while remedial measures are sought there with complicated flame holders, is not to be feared here.
  • the design of the air inlet slots 119, 120 makes a lasting contribution to this: the flow cross section of these air inlet slots 119, 120 decreases in the direction of flow, that is, from the burner head to the burner outlet in the sense of a conical shape, as can be seen particularly well from FIG. 5.
  • the other FIGS. 2-4 also show the decreasing cross section of the air inlet slots 119, 120 very well in the direction of flow.
  • the swirl number which defines the ratio between the tangential and axial speed components, experiences a steeper course along the tangential air inlet slots compared to a uniform flow cross section.
  • the flow cross section of the tangential air inlet slots 119, 120 must in any case be kept within narrow limits so that the desired flow field of the combustion air 115 with the return flow zone 106 can be set at the outlet of the premix burner 100.
  • the decreasing flow cross-section of the tangential air inlet slots 119, 120 in the flow direction increases the persistence of the flame front in the area of the burner outlet.
  • the backflow zone 106 once fixed, is inherently position-stable, because the swirl number increases in the direction of flow in the region of the cone shape of the premix burner 100, which is additionally due to the decreasing flow cross section of the tangential ones Air inlet slots 119, 120 is supported in the direction of flow, which is particularly noticeable in the transient area.
  • the axial speed within the premix burner 100 can also be changed by a corresponding supply, not shown, of an axial combustion air flow, ie, in order to stabilize the backflow zone 106 at the burner outlet, this axial flow can be amplified.
  • the design of the premix burner 100 is furthermore particularly suitable for adapting the size and the course of the tangential air inlet slots 119, 120, with which A relatively large operating bandwidth can be recorded without changing the overall length of the premix burner 100.
  • the partial bodies 101, 102 can also be displaced relative to one another in another plane, as a result of which even an overlap thereof can be controlled. It is even possible, if necessary, to interleave the partial bodies 101, 102 in a spiral manner by counter-rotating movement.
  • FIG. 2-4 now shows the geometrical configuration of the guide plates 121a, 121b. They have a flow introduction function, which, depending on their length, extend the respective end of the tapered partial bodies 101, 102 in the direction of flow relative to the combustion air 115.
  • the channeling of the combustion air 115 into the cone cavity 114 can be optimized by opening or closing the guide plates 121a, 121b about a pivot point 123 located in the region of the entry of this channel into the cone cavity 114, in particular this can be necessary if the flow cross section of the tangential air inlet slots 119, 120 in the sense of Figures 2-4.
  • these dynamic arrangements can also be provided statically, in that guide baffles as required form a fixed component with the tapered partial bodies 101, 102.
  • the premix burner 100 can also be operated without baffles, or other aids can be provided for this.
  • FIG. 5 which has already been tapped several times, shows schematically how the course of the tangential air inlet slots 119, 120 should preferably be provided.
  • a certain alternative to the effect of the decreasing flow cross-section of the tangential air inlet slots 119, 120 can be achieved by forming the partial bodies 101, 102 of the premix burner 100 according to the trumpet shape already recognized.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)
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 true EP0694730A2 (fr) 1996-01-31
EP0694730A3 EP0694730A3 (fr) 1998-05-06
EP0694730B1 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)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0786626A1 (fr) * 1995-12-27 1997-07-30 Asea Brown Boveri Ag Brûleur à prémélange
EP0797051A2 (fr) * 1996-03-20 1997-09-24 Abb Research Ltd. Brûleur pour un générateur de chaleur
EP0780628A3 (fr) * 1995-12-21 1997-10-22 Abb Research Ltd Brûleur à prémélange pour un générateur de chaleur
EP0783089A3 (fr) * 1995-12-27 1998-11-11 Abb Research Ltd. Brûleur sous forme d'un cÔne
EP0851176A3 (fr) * 1996-12-30 1999-01-20 Abb Research Ltd. Chaudière pour un générateur de chaleur
US6834504B2 (en) 2001-07-26 2004-12-28 Alstom Technology Ltd Premix burner with high flame stability having a net-like structure within the mixing section
EP2722592A1 (fr) * 2012-10-22 2014-04-23 Alstom Technology Ltd Brûleur à multiples cones pour une turbine à gaz

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
JP4913746B2 (ja) * 2004-11-30 2012-04-11 アルストム テクノロジー リミテッド 予混合バーナー内の水素を燃焼する方法及び装置
EP1843098A1 (fr) * 2006-04-07 2007-10-10 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
AU2009295221A1 (en) * 2008-09-22 2010-03-25 Darsell Karringten Burner

Citations (1)

* 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

Family Cites Families (6)

* 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
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

Patent Citations (1)

* 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

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0780628A3 (fr) * 1995-12-21 1997-10-22 Abb Research Ltd Brûleur à prémélange pour un générateur de chaleur
EP0786626A1 (fr) * 1995-12-27 1997-07-30 Asea Brown Boveri Ag Brûleur à prémélange
EP0783089A3 (fr) * 1995-12-27 1998-11-11 Abb Research Ltd. Brûleur sous forme d'un cÔne
EP0797051A2 (fr) * 1996-03-20 1997-09-24 Abb Research Ltd. Brûleur pour un générateur de chaleur
EP0797051A3 (fr) * 1996-03-20 1998-05-20 Abb Research Ltd. Brûleur pour un générateur de chaleur
EP0851176A3 (fr) * 1996-12-30 1999-01-20 Abb Research Ltd. Chaudière pour un générateur de chaleur
US6834504B2 (en) 2001-07-26 2004-12-28 Alstom Technology Ltd Premix burner with high flame stability having a net-like structure within the mixing section
EP2722592A1 (fr) * 2012-10-22 2014-04-23 Alstom Technology Ltd Brûleur à multiples cones pour une turbine à gaz
US9464810B2 (en) 2012-10-22 2016-10-11 General Electric Technology Gmbh Burner including a swirl chamber with slots having different widths

Also Published As

Publication number Publication date
DE59509959D1 (de) 2002-01-31
EP0694730B1 (fr) 2001-12-19
JPH08189611A (ja) 1996-07-23
DE4426353A1 (de) 1996-02-01
EP0694730A3 (fr) 1998-05-06
CN1118859A (zh) 1996-03-20
US5562441A (en) 1996-10-08

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