EP0718550A1 - Gicleur - Google Patents

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Publication number
EP0718550A1
EP0718550A1 EP95810745A EP95810745A EP0718550A1 EP 0718550 A1 EP0718550 A1 EP 0718550A1 EP 95810745 A EP95810745 A EP 95810745A EP 95810745 A EP95810745 A EP 95810745A EP 0718550 A1 EP0718550 A1 EP 0718550A1
Authority
EP
European Patent Office
Prior art keywords
injection nozzle
fuel
channel
injection
nozzle 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
EP95810745A
Other languages
German (de)
English (en)
Other versions
EP0718550B1 (fr
Inventor
Robin T.D. Mcmillan
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 AG Germany
Original Assignee
ABB Management 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 ABB Management AG filed Critical ABB Management AG
Publication of EP0718550A1 publication Critical patent/EP0718550A1/fr
Application granted granted Critical
Publication of EP0718550B1 publication Critical patent/EP0718550B1/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
    • 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 invention relates to an injection nozzle for injecting fuels into compressed gaseous media, for example for use in premix burners, the injection nozzle mainly consisting of a fuel line and a duct branching off from the fuel line, the fuel line extending longitudinally essentially perpendicular to the injection direction of the fuel and the channel extends parallel to the direction of injection of the fuel.
  • Such injection nozzles are known from EP-A1-0 433 790. They are used there for premix burners, which are constructed as so-called double-cone burners in a cone shape from several shells. When using a medium calorific gas as fuel, the injection nozzles prevent the mixture from igniting prematurely and enable the mixing process to be stabilized. Liquid fuel is fed into the combustion chamber via a nozzle arranged in the tip of the premix burner injected. However, the atomizing performance of these nozzles is generally insufficient. In addition, a good mixing of combustion air and fuel before the ignition can usually not be achieved because the atomized fuel does not come into contact with the entire combustion air. When using liquid fuels, this leads to relatively high exhaust gas emissions, in particular to high nitrogen oxide emissions. The injection of demineralized water into the combustion chamber is necessary to reduce nitrogen oxide emissions.
  • the invention has for its object to provide a possibility in an injection nozzle of the type mentioned in order to improve the mixing of liquid fuel with the combustion air prior to ignition and thus to reduce the exhaust gas emissions.
  • this is achieved in that the fuel is guided via slots in the fuel line by means of the channel to an atomizing edge, the interior of the channel being built up from distribution plates, between which distribution pins are arranged.
  • the advantages of the invention can be seen, inter alia, in the fact that the injection nozzle is of simple and robust construction. It is possible to work with a low fuel pressure, since the momentum of the air flow is used for atomization.
  • the injection nozzle is used in a premix burner, for example in a double-cone burner, the fuel is distributed along the air inlet slots. Thereby there is a uniform and good mixing with the combustion air before ignition. This results in low pollutant emissions.
  • Fig. 1 50 is a jacketed plenum, which generally receives the combustion air delivered by a compressor, not shown, and feeds it to a combustion chamber 60. It can be a single combustion chamber or an annular combustion chamber.
  • a dome 55 is placed at the head end of the combustion chamber, whose combustion chamber is encased by a combustion chamber wall 63 and delimited by a front plate 54.
  • a burner 10 is arranged in this dome in such a way that the burner outlet 18 is at least approximately flush with the front plate 54.
  • the combustion air flows from the plenum 50 into the interior of the dome via the dome wall perforated at its outer end and acts on the burner.
  • the fuel is fed to the burner via a fuel lance 20 which penetrates the dome and plenum walls.
  • the schematically illustrated premix burner 10 is a so-called double-cone burner, as is known, for example, from EP-A1-0 433 790 mentioned at the beginning.
  • it essentially consists of two hollow, conical partial bodies 11, 12 which are nested one inside the other in the direction of flow.
  • the respective central axes 13, 14 of the two partial bodies are offset from one another.
  • the adjacent walls of the two partial bodies form in their longitudinal extent tangential slots 19 for the combustion air, which in this way reaches the interior of the burner.
  • the burner is operated with liquid fuel.
  • injection nozzles 1 running along these slots are arranged in the region of the tangential slots 19.
  • the injector extends essentially over the full length of the tangential slot 19 (Fig. 1).
  • the exit plane of the fuel from the injection nozzle 1 is usually arranged in the area where the highest combustion air velocities prevail, in the exemplary embodiment shown in the center of the tangential slot 19.
  • the injection nozzles 1 are designed aerodynamically, drop-shaped, on the outside so as to reduce the flow of the combustion air as little as possible possible to disturb.
  • the injection nozzle 1 consists of a fuel line 2 which has a slot 6 along its length.
  • a channel 7 branches off from the slot 6 and leads to an atomizing edge 5.
  • the liquid fuel is fed from the fuel lance 20 to the fuel line 2 of the injection nozzle 1 via feed lines (not shown).
  • the fuel is passed through the slots 6 to distribution plates 3, which form the channel 7.
  • the arrangement and size of these distribution plates 3 can be adjusted by means of intermediate pieces 8. This is done by including the flow of the combustion air through the tangential slots 19 and must be adapted to the respective burner 10.
  • the distribution plate 3 can extend over the entire length of the injection nozzle 1.
  • Rhombus-shaped distribution pins 4 are arranged on the distribution plate.
  • the distribution pins 4 distribute the fuel evenly in the direction of flow in front of the atomizing edge 5.
  • the thickness of the fuel film produced in this way is determined by the gap width t of the channel 7 of the injection nozzle 1 at the atomizing edge 5.
  • the pulse of the combustion air flowing in at high pressure is used for atomization.
  • the liquid fuel can therefore be introduced into the injection nozzle at a relatively low pressure.
  • the size of the fuel droplets after atomization can be adjusted by means of the gap width t and thus the thickness of the fuel film.
  • the gap width t is less than half a millimeter chosen to achieve an optimal mixing between fuel and combustion air.
  • a fuel concentration that is as homogeneous as possible is established over the applied annular cross section.
  • a defined dome-shaped recirculation zone 21 is formed at the burner outlet, at the tip of which the ignition takes place. The flame itself is stabilized by the recirculation zone in front of the burner without the need for a mechanical flame holder.
  • the invention is not limited to the exemplary embodiment shown and described.
  • the shape and number of the distribution pins is essentially arbitrary, the only decisive factor is the regular distribution of the fuel.
  • the extension of the injection nozzles in the tangential slot and the position of the intermediate pieces must be adapted to the air flow through the tangential slot.
  • the burner can also be operated with gaseous fuel.
  • gas inflow openings distributed in the longitudinal direction in the form of nozzles are then provided in the region of the tangential slots in the walls of the two partial bodies.
  • the mixture formation with the combustion air also begins in the zone of the tangential inlet slots.
  • FIG. 5 shows a conventional burner with swirl body 30, consisting essentially of a tube 32, a plurality of deflecting bodies 31 with a wing profile and a fuel lance 34 arranged in the middle.
  • the injection nozzles 1 described above can of course also be installed in the swirl body 30 between the deflecting bodies 31. This will make an optimal one Mixing between fuel and combustion air previously reached the ignition.
  • the number of injection nozzles 1 can, of course, deviate from FIG. 6 as desired and be adapted to the respective circumstances.
  • the injection nozzles 1 can be supplied with fuel directly from the fuel lance 34 via lines (not shown). 7 there is the possibility of integrating the injection nozzle directly into the deflection body 31a.
  • This integrated nozzle la is functionally identical to the injection nozzle 1.
  • the fuel line 2a is simply adapted to the spatial conditions in the deflection body 31a.
  • the fuel supply can of course also take place here through the fuel lance 34.
  • the shape and number of the distribution pins is essentially arbitrary.
  • the injectors can also be used in other arrangements. Sufficiently high energies of the gaseous media into which the liquid working fluid is injected are essential. So the injector can be used in any kind of premix burner.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP95810745A 1994-12-19 1995-11-29 Gicleur Expired - Lifetime EP0718550B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4445279A DE4445279A1 (de) 1994-12-19 1994-12-19 Einspritzdüse
DE4445279 1994-12-19

Publications (2)

Publication Number Publication Date
EP0718550A1 true EP0718550A1 (fr) 1996-06-26
EP0718550B1 EP0718550B1 (fr) 2000-03-01

Family

ID=6536262

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810745A Expired - Lifetime EP0718550B1 (fr) 1994-12-19 1995-11-29 Gicleur

Country Status (5)

Country Link
US (1) US5588824A (fr)
EP (1) EP0718550B1 (fr)
JP (1) JPH08226620A (fr)
CN (1) CN1133419A (fr)
DE (2) DE4445279A1 (fr)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59710380D1 (de) * 1997-11-21 2003-08-07 Alstom Brenner für den Betrieb eines Wärmeerzeugers
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
EP0981019A1 (fr) * 1998-08-20 2000-02-23 Asea Brown Boveri AG Procédé et brûleur pour la combustion des combustibles liquides
US6883332B2 (en) * 1999-05-07 2005-04-26 Parker-Hannifin Corporation Fuel nozzle for turbine combustion engines having aerodynamic turning vanes
US6460344B1 (en) 1999-05-07 2002-10-08 Parker-Hannifin Corporation Fuel atomization method for turbine combustion engines having aerodynamic turning vanes
GB2368386A (en) * 2000-10-23 2002-05-01 Alstom Power Nv Gas turbine engine combustion system
FR2824625B1 (fr) * 2001-05-10 2003-08-15 Inst Francais Du Petrole Dispositif et procede d'injection d'un combustible liquide dans un flux d'air pour une chambre de combustion
KR100830316B1 (ko) * 2002-08-09 2008-05-19 제이에프이 스틸 가부시키가이샤 관상화염버너, 그 연소제어방법 및 장치
DE102005015152A1 (de) 2005-03-31 2006-10-05 Alstom Technology Ltd. Vormischbrenner für eine Gasturbinenbrennkammer
EP1734306B1 (fr) * 2005-06-17 2010-09-08 Alstom Technology Ltd Brûleur pour combustion à prémélange
EP1843098A1 (fr) * 2006-04-07 2007-10-10 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
US8408896B2 (en) * 2007-07-25 2013-04-02 Lummus Technology Inc. Method, system and apparatus for firing control
DE102009045950A1 (de) 2009-10-23 2011-04-28 Man Diesel & Turbo Se Drallerzeuger
KR101760978B1 (ko) * 2010-11-16 2017-07-24 가부시키가이샤 닛신 세이훈 구루프혼샤 분체 분배 장치
EP3056819B1 (fr) * 2015-02-11 2020-04-01 Ansaldo Energia Switzerland AG Dispositif d'injection de carburant pour une turbine à gaz

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2222670A (en) * 1988-09-01 1990-03-14 Mtu Muenchen Gmbh Turboramjet engine full speed
EP0433790A1 (fr) 1989-12-22 1991-06-26 Asea Brown Boveri Ag BrÀ»leur
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
US5244380A (en) * 1991-03-12 1993-09-14 Asea Brown Boveri Ltd. Burner for premixing combustion of a liquid and/or gaseous fuel
EP0641971A2 (fr) * 1993-09-06 1995-03-08 Abb Research Ltd. Procédé pour commander un brûleur à prémélange

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2464791A (en) * 1943-11-05 1949-03-22 Claude A Bonvillian Apparatus for the combustion of fuel
GB1048968A (en) * 1964-05-08 1966-11-23 Rolls Royce Combustion chamber for a gas turbine engine
DE1751929C3 (de) * 1968-08-20 1975-08-28 Joseph Lucas (Industries) Ltd., Birmingham (Grossbritannien) Zerstäuberdüse zur Aufbereitung von flüssigem Brennstoff für Gasturbinen
US4269583A (en) * 1978-05-22 1981-05-26 Combustion Unlimited Incorporated Pilots for flare stacks

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2222670A (en) * 1988-09-01 1990-03-14 Mtu Muenchen Gmbh Turboramjet engine full speed
EP0433790A1 (fr) 1989-12-22 1991-06-26 Asea Brown Boveri Ag BrÀ»leur
US5244380A (en) * 1991-03-12 1993-09-14 Asea Brown Boveri Ltd. Burner for premixing combustion of a liquid and/or gaseous fuel
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
EP0641971A2 (fr) * 1993-09-06 1995-03-08 Abb Research Ltd. Procédé pour commander un brûleur à prémélange

Also Published As

Publication number Publication date
DE4445279A1 (de) 1996-06-20
JPH08226620A (ja) 1996-09-03
EP0718550B1 (fr) 2000-03-01
CN1133419A (zh) 1996-10-16
DE59507901D1 (de) 2000-04-06
US5588824A (en) 1996-12-31

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