EP0903540B1 - Brenner für den Betrieb eines Wärmeerzeugers - Google Patents

Brenner für den Betrieb eines Wärmeerzeugers Download PDF

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Publication number
EP0903540B1
EP0903540B1 EP97810687A EP97810687A EP0903540B1 EP 0903540 B1 EP0903540 B1 EP 0903540B1 EP 97810687 A EP97810687 A EP 97810687A EP 97810687 A EP97810687 A EP 97810687A EP 0903540 B1 EP0903540 B1 EP 0903540B1
Authority
EP
European Patent Office
Prior art keywords
burner
flow
section
burner according
swirl generator
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
EP97810687A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0903540A1 (de
Inventor
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
Alstom Schweiz 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 Schweiz AG filed Critical Alstom Schweiz AG
Priority to EP97810687A priority Critical patent/EP0903540B1/de
Priority to DE59709791T priority patent/DE59709791D1/de
Priority to US09/153,269 priority patent/US5944511A/en
Priority to CNB981192939A priority patent/CN1143077C/zh
Priority to JP26681698A priority patent/JP4155635B2/ja
Publication of EP0903540A1 publication Critical patent/EP0903540A1/de
Application granted granted Critical
Publication of EP0903540B1 publication Critical patent/EP0903540B1/de
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
    • 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
    • F23D2210/00—Noise abatement

Definitions

  • the invention relates to a burner for the operation of a heat generator according to Preamble of claim 1.
  • a burner which on the inflow side a swirl generator, the flow formed therein seamlessly into one Mixing section is transferred. This is done using one at the beginning of the mixing section flow geometry formed for this purpose, which consists of transition channels exists, which is sectoral, according to the number of acting partial bodies of the swirl generator, capture the end face of the mixing section and in the direction of flow twist.
  • the outflow side of these transition channels has the Mixing section on a number of filming holes, which increase the Ensure flow velocity along the pipe wall. Then follows a combustion chamber, the transition between the mixing section and the Combustion chamber is formed by a cross-sectional jump, in the plane of which forms a backflow zone or backflow bubble.
  • the swirl strength in the swirl generator is selected so that the bursting of the Vortex not within the mixing section, but further downstream, as above executed in the area of the cross-sectional jump.
  • the length of the mixing section is like this dimensioned to ensure sufficient mix quality for all types of fuel is.
  • the invention seeks to remedy this.
  • the invention as set out in the claims is characterized, the task is based on a burner of the type mentioned To propose kind of precautions which strengthen the flame stability and an adaptation of the flame to the given combustion chamber geometry effect without diminishing in any way the other advantages of this burner.
  • the one acting on the head and the swirl generator of the burner belonging fuel nozzle which is preferably on the axis of the swirl generator or the burner and which is usually with a liquid Fuel is fed, surrounded by an annular spaced jacket, in which holes are made in the circumferential direction, through which a Air volume flows around the fuel nozzle.
  • additional injectors which are preferably with a gaseous Fuel operated. A small amount of fuel is generated by this Injectors injected into the air volume for flushing around the fuel nozzle, in such a way that the center of the burner flow, which is important for the stability of the flame, always is supplied to the right extent.
  • Another advantage of the invention is the fact that the purge air through the above Openings in the area of the fuel nozzle wetting the inner wall of the conical swirl generator prevented by the injected liquid fuel.
  • Fig. 1 shows the overall structure of a burner.
  • a swirl generator is 100 effective, the design of which is shown in more detail in the following FIGS. 3-6 and is described.
  • This swirl generator 100 is a conical one Formation that is tangential multiple times from a tangentially flowing combustion air flow 115 is applied.
  • the current that forms here is based on a transition geometry provided downstream of the swirl generator 100 transitioned seamlessly into a transition piece 200 such that there are none Detachment areas can occur.
  • the configuration of this transition geometry is described in more detail in Fig. 6.
  • This transition piece 200 is on the outflow side the transition geometry extended by a mixing tube 20, both Parts form the actual mixing section 220.
  • the mixing section 220 consist of a single piece, i.e.
  • transition piece 200 and the mixing tube 20 into a single continuous structure merge, maintaining the characteristics of each part.
  • Transition piece 200 and mixing tube 20 created from two parts so these are connected by a bushing ring 10, the same bushing ring 10 on the head side serves as anchoring surface for the swirl generator 100.
  • Such a bushing ring 10 also has the advantage that different mixing tubes are used can.
  • the actual combustion chamber is located on the outflow side of the mixing tube 20 30, which is only symbolized here by a flame tube.
  • the Mixing section 220 largely fulfills the task that is downstream of the swirl generator 100 a defined route is provided, in which a perfect premix of different types of fuel can be achieved.
  • This mixing section so ostensibly the mixing tube 20, furthermore enables lossless flow guidance, so that it is also in operative connection with the transition geometry cannot initially form a backflow zone or backflow bubble, which means that Length of the mixing section 220 influences the quality of the mixture for all types of fuel can be exercised.
  • This mixing section 220 has yet another property, which is that the axial velocity profile is in it itself has a pronounced maximum on the axis, so that the Flame from the combustion chamber is not possible. However, it is correct that at in such a configuration, this axial velocity drops towards the wall.
  • the mixing tube 20 in Flow and circumferential direction with a number of regular or irregular distributed holes 21 of different cross-sections and directions, through which an amount of air flows into the interior of the mixing tube 20, and along the wall in the sense of a filming an increase in the flow rate induce.
  • These holes 21 can also be designed in such a way that the inner wall of the mixing tube 20 at least additionally an effusion cooling established.
  • Another possibility is to increase the speed of the mixture To achieve within the mixing tube 20 is that Flow cross-section on the outflow side of the transition channels 201, which already have the called transition geometry form, undergoes a narrowing, whereby the entire speed level within the mixing tube 20 is raised.
  • these bores 21 run at an acute angle with respect to the Burner axis 60.
  • the outlet corresponds to the transition channels 201 the narrowest flow cross-section of the mixing tube 20.
  • the transition channels mentioned 201 accordingly bridge the respective cross-sectional difference, without negatively influencing the flow formed. If the chosen one Precautions when guiding the pipe flow 40 along the mixing pipe 20 causes intolerable pressure loss, this can be remedied, by a diffuser not shown in the figure at the end of this mixing tube is provided.
  • a combustion chamber then closes at the end of the mixing tube 20 30 on, with a through a Burner front 70 formed cross-sectional jump is present.
  • FIG. 2 shows a schematic view of the burner according to FIG. 1, with particular reference being made to the flushing of a centrally arranged fuel nozzle 103 and to the effect of fuel injectors 170.
  • the mode of operation of the remaining main components of the burner, namely swirl generator 100 and transition piece 200, are described in more detail in the following figures.
  • the fuel nozzle 103 is encased with a spaced ring 190, in which a number of bores 161 arranged in the circumferential direction are laid, through which a quantity of air 160 flows into an annular chamber 180 and carries out the purging of the fuel lance there.
  • These bores 161 are made obliquely forward so that an appropriate axial component is created on the burner axis 60.
  • additional fuel injectors 170 are provided, which enter a certain amount, preferably a gaseous fuel, into the respective air amount 160 in such a way that a uniform fuel concentration 150 is established in the mixing tube 20 over the flow cross-section, as shown in FIG Figure symbolizes. It is precisely this uniform fuel concentration 150, in particular the strong concentration on the burner axis 60, that the flame front is stabilized at the outlet of the burner, thus avoiding combustion chamber pulsations.
  • FIG. 4 is used at the same time as FIG. 3. The following will in the description of Fig. 3 referred to the other figures as needed.
  • the first part of the burner according to FIG. 1 forms the swirl generator shown in FIG. 3 100.
  • This consists of two hollow conical partial bodies 101, 102 which are nested staggered.
  • the number of conical part bodies can of course be greater than two, as shown in Figures 5 and 6; this depends on, as will be explained in more detail below the operating mode of the entire burner. It is with certain operating constellations not excluded, a swirl generator consisting of a single spiral provided.
  • the offset of the respective central axis or longitudinal symmetry axes 101b, 102b (see FIG. 4) of the conical partial bodies 101, 102 to one another creates one on each of the neighboring walls in a mirror-image arrangement tangential channel, i.e.
  • the conical shape of the partial bodies 101, 102 shown in Flow direction has a certain fixed angle. Of course, ever after operational use, the partial bodies 101, 102 can increase in the direction of flow or have decreasing cone inclination, similar to a trumpet resp. Tulip. The last two forms are not included in the drawing as they are for the expert can be easily understood.
  • the two conical partial bodies 101, 102 each have a cylindrical annular starting part 101a. In the area this cylindrical initial part is the fuel nozzle already mentioned in FIG. 2 103 housed, which preferably with a liquid fuel 112 is operated.
  • the injection 104 of this fuel 112 coincides with that narrowest cross section of the conical cavity formed by the conical partial bodies 101, 102 114 together.
  • the injection capacity and the type of this fuel nozzle 103 depends on the specified parameters of the respective burner.
  • the tapered partial bodies 101, 102 furthermore each have a fuel line 108, 109, which are arranged along the tangential air inlet slots 119, 120 and are provided with injection openings 117, through which preferably a gaseous fuel 113 is injected into the combustion air 115 flowing through there is how the arrows 116 symbolize this.
  • fuel lines 108, 109 are preferably at the latest at the end of the tangential inflow Entry into the cone cavity 114, arranged to do this for an optimal Obtain air / fuel mixture.
  • fuel 112 is normally a liquid Fuel, forming a mixture with another medium, for example with a recirculated flue gas, is easily possible. That fuel 112 is in the cone cavity at a preferably very acute angle 114 injected. A conical fuel spray thus forms from the fuel nozzle 103 105, from the rotating combustion air flowing in tangentially 115 enclosed and dismantled.
  • the concentration is then in the axial direction of the injected fuel 112 continuously through the inflowing combustion air 115 degraded to mix in the direction of evaporation.
  • the combustion air 115 additionally preheated, or for example with a recycled flue gas or exhaust gas enriched, this supports sustainably the evaporation of the liquid fuel 112 before this mixture into the downstream stage flows, here in the transition piece 200 (see FIGS. 1 and 7).
  • the construction of the swirl generator 100 is furthermore excellently suitable, the size of the tangential Air inlet slots 119, 120 to change, so without changing the overall length of the swirl generator 100 covers a relatively large operational bandwidth can be.
  • the partial bodies 101, 102 are also in another Plane can be moved relative to one another, which even provides an overlap thereof can be. It is also possible to pass through the partial bodies 101, 102 to interleave a counter-rotating movement in a spiral. Consequently 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 is unchanged its overall length can be used universally.
  • FIG. 4 shows, among other things, the geometric configuration of optional ones Baffles 121a, 121b. They have a flow initiation function these, according to their length, the respective end of the tapered partial body 101, 102 extend in the direction of flow towards the combustion air 115.
  • the channeling of the combustion air 115 into the cone cavity 114 can be done by Open or close the guide plates 121a, 121b by one in the area of the entrance of this channel in the cone cavity 114 pivot point 123 optimized this is particularly necessary if the original gap size of the tangential air inlet slots 119, 120 should be changed dynamically, for example to change the speed of the combustion air 115 to reach.
  • these dynamic arrangements can also be static can be provided by using a fixed component as required form the tapered partial body 101, 102.
  • FIG. 5 shows, compared to FIG. 4, that 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.
  • this configuration can be said that they are due to the lower twist strength generated with it and in combination with a correspondingly enlarged slot width suitable, the bursting of the vortex flow on the downstream side of the swirl generator To prevent the mixing tube, so that the mixing tube best fulfills its intended role can meet.
  • FIG. 6 differs from FIG. 5 in that the partial bodies 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 is remained the same.
  • the admixture of fuel 116 in the combustion air flow 115 happens from the inside of the blade profiles, i.e. the fuel line 108 is now integrated in the individual blades. They are here too Longitudinal axes of symmetry to the individual partial bodies marked with the letter a.
  • the transition geometry is corresponding for a swirl generator 100 with four partial bodies 5 or 6, built. Accordingly, the transition geometry points as Natural extension of the upstream part of the four transition channels 201 on, whereby the conical quarter surface of said partial body is extended until it cuts the wall of the mixing tube.
  • the same considerations also apply if the swirl generator is based on a principle other than that described under FIG. 3, is constructed.
  • the downward surface of the individual Transition channels 201 have a spiral path in the direction of flow Form, which describes a crescent-shaped course, according to the The fact that in the present case the flow cross section of the transition piece 200 flared in the direction of flow.
  • the twist angle of the transition channels 201 in the flow direction is selected so that the pipe flow then up to for the cross-sectional jump at the combustion chamber inlet there is still a sufficiently large distance remains to achieve a perfect premix with the injected fuel.
  • 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 cause one significant increase in the axial speed profile to the center of the mixing tube so that the danger of early ignition is decisively counteracted.
  • the flow cross-section of the tube 20 receives a transition radius in this area R, the size of which basically depends on the flow within the Tube 20 depends.
  • This radius R is chosen so that the flow adjusts to the Puts on the wall and so the swirl number increases sharply. It can be quantified Define the size of the radius R so that it is> 10% of the inner diameter d of the tube is 20. Compared to a flow without a radius increases now the backflow bladder 50 tremendous.
  • This radius R extends to the exit plane of the tube 20, the angle ⁇ between the beginning and end of the curvature ⁇ 90 ° is.
  • the tear-off edge A ins runs along one leg of the angle ⁇ Interior of the tube 20 and thus forms a demolition step S compared to the front Point of the tear-off edge A, the depth of which is> 3 mm.
  • the angle ⁇ ' the between the tangent of the tear-off edge A and perpendicular to the exit plane of the pipe 20 is the same size as the angle ⁇ .
  • the benefits of this training this tear-off edge go from EP-0 780 629 A2 under the chapter "Representation of the invention ".
  • Another configuration of the tear-off edge for the same purpose can be achieved with toroid-like notches on the combustion chamber side.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
EP97810687A 1997-09-19 1997-09-19 Brenner für den Betrieb eines Wärmeerzeugers Expired - Lifetime EP0903540B1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP97810687A EP0903540B1 (de) 1997-09-19 1997-09-19 Brenner für den Betrieb eines Wärmeerzeugers
DE59709791T DE59709791D1 (de) 1997-09-19 1997-09-19 Brenner für den Betrieb eines Wärmeerzeugers
US09/153,269 US5944511A (en) 1997-09-19 1998-09-14 Burner for operating a heat generator
CNB981192939A CN1143077C (zh) 1997-09-19 1998-09-18 用于运行热发生器的燃烧器
JP26681698A JP4155635B2 (ja) 1997-09-19 1998-09-21 熱発生器を稼働させるためのバーナ

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810687A EP0903540B1 (de) 1997-09-19 1997-09-19 Brenner für den Betrieb eines Wärmeerzeugers

Publications (2)

Publication Number Publication Date
EP0903540A1 EP0903540A1 (de) 1999-03-24
EP0903540B1 true EP0903540B1 (de) 2003-04-09

Family

ID=8230395

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810687A Expired - Lifetime EP0903540B1 (de) 1997-09-19 1997-09-19 Brenner für den Betrieb eines Wärmeerzeugers

Country Status (5)

Country Link
US (1) US5944511A (zh)
EP (1) EP0903540B1 (zh)
JP (1) JP4155635B2 (zh)
CN (1) CN1143077C (zh)
DE (1) DE59709791D1 (zh)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE244380T1 (de) * 1997-11-21 2003-07-15 Alstom Brenner für den betrieb eines wärmeerzeugers
EP0931980B1 (de) * 1998-01-23 2003-04-09 ALSTOM (Switzerland) Ltd Brenner für den Betrieb eines Wärmeerzeugers
DE19914666B4 (de) * 1999-03-31 2009-08-20 Alstom Brenner für einen Wärmeerzeuger
US20030143638A1 (en) * 2000-04-07 2003-07-31 Mahito Hirai Antibody/carrier complex, process for producing the same, method of controlling antigen-antibody reaction by using the same and immunoassay method
WO2001096785A1 (de) * 2000-06-15 2001-12-20 Alstom (Switzerland) Ltd Verfahren zum betrieb eines brenners sowie brenner mit gestufter vormischgas-eindüsung
DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
US20050065136A1 (en) * 2003-08-13 2005-03-24 Roby Russell R. Methods and compositions for the treatment of infertility using dilute hormone solutions
WO2005105106A2 (en) * 2004-04-21 2005-11-10 Roby Russell R Hormone treatment of macular degeneration
US20060025390A1 (en) * 2004-07-28 2006-02-02 Roby Russell R Treatment of hormone allergy and related symptoms and disorders
US9441543B2 (en) * 2012-11-20 2016-09-13 Niigata Power Systems Co., Ltd. Gas turbine combustor including a premixing chamber having an inner diameter enlarging portion
US9261852B2 (en) 2014-02-27 2016-02-16 Ricoh Company, Ltd. Acoustic device, and electronic device and image forming apparatus incorporating same

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5461865A (en) * 1994-02-24 1995-10-31 United Technologies Corporation Tangential entry fuel nozzle
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner
DE4439619A1 (de) * 1994-11-05 1996-05-09 Abb Research Ltd Verfahren und Vorrichtung zum Betrieb eines Vormischbrenners
DE19545309A1 (de) * 1995-12-05 1997-06-12 Asea Brown Boveri Vormischbrenner
DE19547914A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Vormischbrenner für einen Wärmeerzeuger
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
DE19548851A1 (de) * 1995-12-27 1997-07-03 Asea Brown Boveri Vormischbrenner

Also Published As

Publication number Publication date
JP4155635B2 (ja) 2008-09-24
CN1212347A (zh) 1999-03-31
JPH11148618A (ja) 1999-06-02
US5944511A (en) 1999-08-31
CN1143077C (zh) 2004-03-24
EP0903540A1 (de) 1999-03-24
DE59709791D1 (de) 2003-05-15

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