EP0833104A2 - Brûleur pour le fonctionnement d'une chambre de combustion - Google Patents

Brûleur pour le fonctionnement d'une chambre de combustion Download PDF

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Publication number
EP0833104A2
EP0833104A2 EP97810621A EP97810621A EP0833104A2 EP 0833104 A2 EP0833104 A2 EP 0833104A2 EP 97810621 A EP97810621 A EP 97810621A EP 97810621 A EP97810621 A EP 97810621A EP 0833104 A2 EP0833104 A2 EP 0833104A2
Authority
EP
European Patent Office
Prior art keywords
burner
flow
burner according
section
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
EP97810621A
Other languages
German (de)
English (en)
Other versions
EP0833104B1 (fr
EP0833104A3 (fr
Inventor
Klaus Dr. Döbbeling
Hans Peter Knöpfel
Donald Frank Walker
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.)
ABB Research Ltd Switzerland
Original Assignee
ABB Research Ltd Switzerland
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 filed Critical ABB Research Ltd Switzerland
Publication of EP0833104A2 publication Critical patent/EP0833104A2/fr
Publication of EP0833104A3 publication Critical patent/EP0833104A3/fr
Application granted granted Critical
Publication of EP0833104B1 publication Critical patent/EP0833104B1/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
    • F23D11/40—Mixing tubes; 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 simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion simultaneously or alternately 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 
    • F23C2202/00—Fluegas recirculation
    • F23C2202/40—Inducing local whirls around flame
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/20—Flame lift-off / stability
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2214/00—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability

Definitions

  • the present invention relates to a burner according to the preamble of claim 1.
  • the upstream side consists of a swirl generator
  • Transition channels exist, which are sectoral, according to the Number of acting partial bodies of the swirl generator, the end face the mixing section and in the direction of flow twisted.
  • the mixing section has a number of filming holes on what an increase in flow velocity ensure along the pipe wall.
  • a combustion chamber the transition between the mixing section and the combustion chamber through a cross-sectional jump is formed, in the plane of which is a backflow zone or Backflow bubble forms.
  • the swirl strength in the swirl generator is selected so that that the swirl does not burst within the mixing section, but continues downstream, as stated above in the area of the cross-sectional jump.
  • the length of the mixing section is dimensioned so that an adequate Mixing quality is guaranteed for all types of fuel.
  • the invention seeks to remedy this.
  • the invention how it is characterized in the claims, the task lies based on precautions for a burner of the type mentioned propose which a strengthening of flame stability and an adaptation of the flame to the given one Combustion chamber geometry does this without the other advantages To diminish Brenners in any way.
  • the burner front is at the end of the mixing section in the plane of the cross-sectional jump on the combustion chamber side formed with a torus or torus-like notch.
  • This configuration means that the Mixing section flowing combustion air to the in the torus creating flow, with which the swirl number of the main flow rises sharply.
  • Another embodiment of the invention relates to the relocation the head-side fuel nozzle opposite the inflow the combustion air in a conical shape Swirl generator with tangential air inlet slots.
  • This misalignment leads to the mouth of the fuel nozzle upstream of the inflow area, so that Fuel spray from the fuel nozzle with a larger one Spray radius can be injected into the main flow.
  • This precaution is achieved in that the fuel spray first contact with the combustion air from a film has decayed into drops, and the conical surface of this Fuel sprays in this area increased by a factor has what improves the spread of the fuel spray and does not hinder the inflow of combustion air.
  • Another advantage of the invention is that the purge air through the openings in the area of the mouth Fuel nozzle wetting the inner wall of the conical Swirl generator prevented.
  • Fig. 1 shows the overall structure of a burner.
  • a swirl generator 100 effective, the design of which in the following Fig. 2-5 shown and described in more detail becomes.
  • This swirl generator 100 is a conical structure, the tangential multiple of a tangential inflowing combustion air flow 115 is applied becomes.
  • the flow that forms here is based on a transition geometry provided downstream of the swirl generator 100 transitioned seamlessly into a transition piece 200, in such a way that no separation areas can occur there.
  • the configuration of this transition geometry is under Fig. 6 described in more detail.
  • This transition piece is 200 downstream of the transition geometry through a mixing tube 20 extended, both parts of the actual mixing section Form 220.
  • the mixing section 220 can consist of a single piece, i.e.
  • a transition piece 200 and mixing tube 20 created from two parts so are these are connected by a socket ring 10, the same Socket ring 10 on the head side as anchoring surface for the Swirl generator 100 is used.
  • Such a sleeve ring 10 has it also the advantage that different mixing tubes are used can be.
  • Downstream side of the mixing tube 20 is the actual combustion chamber 30, which is here is only symbolized by a flame tube.
  • the Mixing section 220 largely fulfills the task that downstream of the swirl generator 100 provided a defined distance in which a perfect premix of fuels different types can be achieved.
  • This mixing section so primarily the mixing tube 20, further allows a loss-free flow, so that even in Active connection with the transition geometry initially none Backflow zone or backflow bubble can form, with which over the Length of the mixing section 220 to the mix quality for all Fuel types influence can be exerted.
  • This mixing section 220 has yet another property, which is that in it itself the axial velocity profile has a pronounced maximum on the axis, so that the flame does not reignite from the combustion chamber is possible. However, it is true that with such Configuration this axial velocity towards the wall falls off.
  • the mixing tube 20 in the flow and circumferential direction with a number of regularly or irregularly distributed Provide holes 21 of different cross-sections and directions, through which an amount of air into the interior of the mixing tube 20 flows, and along the wall like a film induce an increase in speed.
  • Combustion chamber 30 has an end face Number of openings 31 through which an amount of air directly flows into the cross-sectional jump, and there bottom others contributes to the ring stabilization of the backflow zone 50 is strengthened.
  • the creation of a stable backflow zone 50 is also sufficient requires a high number of twists in a tube. Is a such undesirable at first, so stable backflow zones by supplying small, strongly swirled air flows on the Pipe end, for example through tangential openings, be generated. It is assumed here that the Air volume required for this is approximately 5-20% of the total air volume is.
  • the design of the burner front 70 in the end of the mixing tube 20 to stabilize the backflow zone or Backflow bladder 50 relates to the description below Fig. 8-11 referenced.
  • FIG. 2 In order to better understand the structure of the swirl generator 100 it is advantageous if, at the same time as FIG. 2, at least FIG. 3 is used. Furthermore, this Fig. 2 is not unnecessary to be confusing, they are those according to the Figure 3 schematically shown guide plates 121a, 121b only hinted been recorded. In the following, the Description of Fig. 2 as required on the figures mentioned pointed out.
  • the first part of the burner according to FIG. 1 forms the one according to FIG. 2 shown swirl generator 100.
  • This consists of two hollow conical partial bodies 101, 102 which are offset from one another are nested.
  • the number of conical Partial body can of course be larger than two, such as Figures 4 and 5 show; this depends on how each further will be explained in more detail below, depending on the type of debt collection of the whole burner. It is with certain operating constellations not excluded one from one single spiral existing 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 Arrangement, each a tangential channel, i.e.
  • the cone shape of the one shown Partial body 101, 102 has a flow direction certain fixed angle. Of course, depending on the operational use, can the partial body 101, 102 in the direction of flow have an increasing or decreasing taper similar to a trumpet or Tulip. The latter two Shapes are not included in the drawing as they are for the expert can be easily understood.
  • 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 swirl generator 100 are present.
  • a nozzle 103 is preferred for a liquid fuel 112, the injection of which 104 with the narrowest cross section of the through conical partial body 101, 102 formed conical cavity 114 coincides.
  • the injection capacity and the type of this Nozzle 103 depends on the specified parameters of the respective burner.
  • the swirl generator can 100 purely conical, i.e. without cylindrical starting parts 101a, 102a.
  • the tapered body 101, 102 also each have a fuel line 108, 109 on which along the tangential air inlet slots 119, 120 arranged and provided with injection openings 117 are, by which preferably a gaseous fuel 113 injected into the combustion air 115 flowing through there is how the arrows 116 symbolize this.
  • This Fuel lines 108, 109 are preferably at the latest End of tangential inflow, before entering the cone cavity 114, placed, this for an optimal Obtain air / fuel mixture.
  • fuel introduced 112 normally a liquid fuel, whereby a mixture formation with another medium without any problems is possible. This fuel 112 will tip under one Angle injected into the cone cavity 114.
  • the construction of the swirl generator 100 is also excellent, the size to change the tangential air inlet slots 119, 120, with which without changing the overall length of the swirl generator 100 a relatively wide range of operations can be covered can.
  • the partial bodies 101, 102 are also in another level slidable to each other, which even an overlap of the same can be provided. It is further possible, the partial body 101, 102 by an opposite to interleave rotating movement in a spiral. So it is possible to change the shape, size and the configuration of the tangential air inlet slots 119, 120 to vary arbitrarily, with which the swirl generator 100 without Changing its overall length is universally applicable.
  • FIG Baffles 121a, 121b The geometric configuration of FIG Baffles 121a, 121b. They have a flow initiation function these, according to 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 by opening or closing the guide plates 121a, 121b by one in the area of the entry of this channel into the Cone cavity 114 placed pivot point 123 can be optimized, this is particularly necessary if the original gap size of the tangential air inlet slots 119, 120 dynamic should be changed.
  • you can dynamic arrangements can also be provided statically by required guide plates with a fixed component form the tapered partial bodies 101, 102.
  • the can also Swirl generator 100 can also be operated without baffles, or other aids can be provided for this.
  • FIG. 4 shows that the swirl generator 100 now made up of four partial bodies 130, 131, 132, 133 is.
  • the associated longitudinal symmetry axes for each partial body are marked with the letter a.
  • This configuration can be said that because of the generated lower twist strength and in cooperation with one suitably suitably enlarged slot width, the bursting of the vortex flow on the downstream side of the To prevent swirl in the mixing tube, making the mixing tube can best fulfill the role intended for him.
  • Fig. 5 differs from Fig. 4 in so far as here the partial bodies 140, 141, 142, 143 have a blade profile shape, which is intended to provide a certain flow becomes. 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 the inside the blade profiles out, i.e. the fuel line 108 is now integrated in the individual blades. Also here are the longitudinal axes of symmetry to the individual partial bodies marked with the letter a.
  • the transition geometry is for a swirl generator 100 with four partial bodies, corresponding to FIG. 4 or 5, built up. Accordingly, the transition geometry points as natural extension of the upstream parts four transition channels 201 on, making up the cone quarter area the partial body mentioned is extended until it hits the wall of the mixing tube cuts.
  • the same considerations apply also if the swirl generator is based on a principle other than that described under Fig. 2 is constructed.
  • the down surface of the individual transition channels running in the direction of flow 201 has a spiral shape in the flow direction running shape, which has a crescent shape describes, according to the fact that present the flow cross section of the transition piece 200 in the flow direction flared.
  • the twist angle of the transition channels 201 in the flow direction is selected so that the Pipe flow then up to the cross-sectional jump on Combustion chamber entrance still has a sufficiently large distance, for a perfect premix with the injected To accomplish fuel. It also increases through above-mentioned measures also the axial speed the mixing tube wall downstream of the swirl generator. The transition geometry and the measures in the area of the mixing tube cause a significant increase in the axial speed profile towards the center of the mixing tube so that the Danger of early ignition is decisively counteracted.
  • FIG. 7 shows a schematic illustration of a swirl generator 100a, that closer to the previous Fig. 2-5 has been described.
  • 7 is essential Representation of the fuel nozzle 103a placed in the middle, which compared to the beginning 125 of the conical flow cross-section is set back upstream, the distance 126 from depends on the chosen spray angle 105, and it is approx long as the diameter of the cross section there. By this displacement comes the mouth 104 of the fuel nozzle 103a in the area of the fixed casing 101a on the head side, 102a to stand.
  • openings 124 are provided, through which a purge air in the size of the fuel nozzle 103a induced cross-section flows.
  • the flow cross section of these openings 124 is chosen such that in gas operation the air mass flow flowing through these openings not sufficient to cover the backflow zone (see Fig. 1) to move further downstream.
  • the fuel spray 105 acts practically as a jet pump, with which the air mass flow through the openings mentioned 124 increased. This causes a larger axial momentum the backflow zone moves further downstream, which is good Measures against flame reignition are effective.
  • conical partial bodies 101, 102 is discussed in more detail in Fig. 2-5.
  • Fig. 8 shows how at the end of the mixing tube 20, along the radial end edge, which forms the burner front 70, On the combustion chamber side, a torus 71 is left out.
  • the size of this torus depends on the main flow 40 within the mixing tube 20 belonging to the mixing section: the Torus 71 is selected so that the main flow 40 turns on creates a torus flow 72 formed by it, with which the Swirl number increases sharply.
  • the Torus 71 is selected so that the main flow 40 turns on creates a torus flow 72 formed by it, with which the Swirl number increases sharply.
  • an inclined to the burner axis 60 deflected main flow 73 which is tangential to the Torus flow 72 developed. This is caused by the torus 71 induced flow dynamics is responsible for that the backflow bladder 50 against a flow without Torus increased enormously, as this is indicated in Fig.
  • FIG. 9 shows a further embodiment of the torus. This is now of quarter circle 74 and then goes in a radial terminating edge 75 over which of the original Burner front 70 is deposed according to FIG. 8. Here too there is a strong increase in the number of twists, and from above reasons set out to strengthen the backflow bladder 50.
  • the Training of the toruses can be various. Important is that the torus flow 72 through the main flow 40 is driven, and then the latter in the sense of Images is redirected.
  • FIG. 11 is another embodiment of FIG. 10, wherein here a basic possibility is shown, as in A pilot stage in connection with the formation of the torus flow 72 77 can be integrated.
  • One to pilot level 77 proper and axially extending channel brings fuel in the torus flow 72 and ensures fuel piloting, this channel roughly at the highest point of the Toruses 71 flows into.

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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)
  • Spray-Type Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
EP97810621A 1996-09-25 1997-09-02 Brûleur pour le fonctionnement d'une chambre de combustion Expired - Lifetime EP0833104B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19639301 1996-09-25
DE19639301A DE19639301A1 (de) 1996-09-25 1996-09-25 Brenner zum Betrieb einer Brennkammer

Publications (3)

Publication Number Publication Date
EP0833104A2 true EP0833104A2 (fr) 1998-04-01
EP0833104A3 EP0833104A3 (fr) 1998-07-29
EP0833104B1 EP0833104B1 (fr) 2001-04-11

Family

ID=7806802

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810621A Expired - Lifetime EP0833104B1 (fr) 1996-09-25 1997-09-02 Brûleur pour le fonctionnement d'une chambre de combustion

Country Status (4)

Country Link
EP (1) EP0833104B1 (fr)
JP (1) JP3904684B2 (fr)
CN (1) CN1109843C (fr)
DE (2) DE19639301A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19859829A1 (de) * 1998-12-23 2000-06-29 Abb Alstom Power Ch Ag Brenner zum Betrieb eines Wärmeerzeugers
EP1087178A1 (fr) * 1999-09-23 2001-03-28 Nuovo Pignone Holding S.P.A. Chambre de prémélange pour turbines à gaz
RU2166695C2 (ru) * 1998-05-18 2001-05-10 Юнайтед Текнолоджиз Корпорейшн Форсунка и способ предварительного смешения с использованием этой форсунки
EP1389713A1 (fr) * 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Brûleur pilote annulaire pour sortie de brûleur à prémélange
US7871262B2 (en) * 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10128063A1 (de) 2001-06-09 2003-01-23 Alstom Switzerland Ltd Brennersystem
DE10233161B4 (de) 2002-07-22 2012-01-05 Alstom Technology Ltd. Brenner und Pilotbrenner
EP2703721B1 (fr) 2012-08-31 2019-05-22 Ansaldo Energia IP UK Limited Brûleur à prémélange
JP7711469B2 (ja) * 2021-07-26 2025-07-23 株式会社豊田自動織機 燃焼器
CN115059917B (zh) * 2022-06-24 2024-06-18 北京理工大学 一种带收缩段的高速多相射流燃烧器

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0704657A2 (fr) 1994-10-01 1996-04-03 ABB Management AG Brûleur

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2806517A (en) * 1950-11-16 1957-09-17 Shell Dev Oil atomizing double vortex burner
US4373325A (en) * 1980-03-07 1983-02-15 International Harvester Company Combustors
US4561841A (en) * 1980-11-21 1985-12-31 Donald Korenyi Combustion apparatus
JPH07190308A (ja) * 1993-12-28 1995-07-28 Hitachi Ltd 旋回型バーナ
DE19547912A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0704657A2 (fr) 1994-10-01 1996-04-03 ABB Management AG Brûleur

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2166695C2 (ru) * 1998-05-18 2001-05-10 Юнайтед Текнолоджиз Корпорейшн Форсунка и способ предварительного смешения с использованием этой форсунки
DE19859829A1 (de) * 1998-12-23 2000-06-29 Abb Alstom Power Ch Ag Brenner zum Betrieb eines Wärmeerzeugers
US6702574B1 (en) 1998-12-23 2004-03-09 Alstom (Schweiz) Ag Burner for heat generator
EP1087178A1 (fr) * 1999-09-23 2001-03-28 Nuovo Pignone Holding S.P.A. Chambre de prémélange pour turbines à gaz
US6363725B1 (en) 1999-09-23 2002-04-02 Nuovo Pignone Holding S.P.A. Pre-mixing chamber for gas turbines
EP1389713A1 (fr) * 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Brûleur pilote annulaire pour sortie de brûleur à prémélange
WO2004015332A1 (fr) * 2002-08-12 2004-02-19 Alstom Technology Ltd Veilleuse d'anneau de sortie premelangee
US7140183B2 (en) 2002-08-12 2006-11-28 Alstom Technology Ltd. Premixed exit ring pilot burner
US7871262B2 (en) * 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner

Also Published As

Publication number Publication date
EP0833104B1 (fr) 2001-04-11
JPH10103620A (ja) 1998-04-21
DE59703346D1 (de) 2001-05-17
CN1109843C (zh) 2003-05-28
EP0833104A3 (fr) 1998-07-29
DE19639301A1 (de) 1998-03-26
CN1185559A (zh) 1998-06-24
JP3904684B2 (ja) 2007-04-11

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