EP0610722A1 - Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation à turbine à gaz ou un foyer - Google Patents

Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation à turbine à gaz ou un foyer Download PDF

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Publication number
EP0610722A1
EP0610722A1 EP94101142A EP94101142A EP0610722A1 EP 0610722 A1 EP0610722 A1 EP 0610722A1 EP 94101142 A EP94101142 A EP 94101142A EP 94101142 A EP94101142 A EP 94101142A EP 0610722 A1 EP0610722 A1 EP 0610722A1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
nozzles
gaseous
fuels
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
EP94101142A
Other languages
German (de)
English (en)
Other versions
EP0610722B1 (fr
Inventor
Klaus Dr. Döbbeling
Hans Peter Knöpfel
Wolfgang Dr. Polifke
Thomas Dr. Sattelmayer
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
ABB Research Ltd Sweden
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 EP0610722A1 publication Critical patent/EP0610722A1/fr
Application granted granted Critical
Publication of EP0610722B1 publication Critical patent/EP0610722B1/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
    • 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

Definitions

  • the invention relates to a burner for operating an internal combustion engine, a combustion chamber of a gas turbine group or firing system which, in addition to the usual oil or natural gas firing, can also be used for the combustion of gaseous fuels containing highly reactive components with an average calorific value.
  • the gasification product consists largely of hydrogen and carbon monoxide with a maximum volume ratio of H2 to CO of 0.9.
  • Double cone burners known from EP 0518072 and EP 0521325 for low-emission combustion have so far only been possible to burn liquid fuels and gaseous fuels of low reactivity.
  • the invention tries to avoid all these disadvantages. It is based on the task of creating a burner and a method for operating the burner of an internal combustion engine, a combustion chamber of a gas turbine group or firing system, in which, in addition to the conventional oil or natural gas firing, gaseous fuels containing highly reactive components with an average calorific value can be used without having to be diluted with water vapor and nitrogen before combustion.
  • this is achieved in a burner according to the preamble of claim 1 in that for the gaseous fuel containing highly reactive components average calorific value near the burner outlet at a distance from the burner outlet of up to 30% of the nominal burner diameter, at least one row of nozzles is attached to the circumference of the partial cone bodies and there is a fuel line and a distribution channel for the highly reactive fuel placed in the area of the nozzles, the two of which Systems for the injection of the gaseous fuels are arranged independently of one another.
  • this is achieved in a method for operating the above-mentioned.
  • the burner is achieved by injecting the highly reactive fuel at high speed near the burner outlet into the zones of high air speed and coordinating the depth of penetration and direction of the fuel jets so that the ignition only takes place behind the burner after the mixture has been mixed.
  • the advantages of the invention can be seen, inter alia, in the elimination of the need to dilute the gaseous fuel containing highly reactive components with nitrogen and water vapor before the combustion, and in the compression of the dilution media to the combustion chamber pressure. Furthermore, a stable and low-pollutant combustion of the fuels is achieved under gas turbine conditions. Since the fuel systems in the burner are arranged independently of one another, the burner is still fully functional even in the known natural gas and oil operation.
  • the diameter of the individual nozzles is less than 1% of the nominal diameter of the burner.
  • the burner is operated in mixed operation with both types of gas injection with one or two different gaseous fuels or alternatively with a liquid fuel.
  • FIG. 1 An embodiment of the invention is shown.
  • the single figure shows a perspective view of the burner, the partial section particularly showing the tangential air feeds.
  • the burner body consists of two half hollow partial cone bodies 1 and 2, which are offset from one another. Due to this geometric structure, one can speak of a double-cone burner.
  • the offset of the respective central axes of the partial cone bodies 1, 2 to one another creates a tangential air inlet slots 4 and 5 on both sides of the partial cone bodies 1, 2, through which the combustion air 12 flows into the interior of the double-cone burner, ie into the cone cavity 6.
  • the two partial cone bodies 1, 2 each have a cylindrical initial part 1a, 2a, which likewise run offset to one another analogously to the partial cone bodies 1, 2, so that the tangential air inlet slots 4, 5 are present from the start.
  • a nozzle 3 is accommodated, which ensures the supply of the liquid fuel 13.
  • the double-cone burner can of course also be designed without the cylindrical starting parts 1a, 2a.
  • the two partial cone bodies 1, 2 each have a fuel line 7, 8, which are provided with fuel nozzles 9 through which the gaseous fuel 14 flows, which is mixed with the combustion air 12 flowing through the tangential air inlet slots 4, 5.
  • the fuel lines 7, 8 are arranged at the end of the tangential air inlet slots 4, 5, so that the admixture of the fuel 14 with the inflowing combustion air 12 can take place there.
  • the double-cone burner has a front plate 16 at the burner outlet.
  • the liquid fuel 13 flowing through the nozzle 3 is injected into the cone cavity 6 at an acute angle.
  • the conical liquid fuel profile is then surrounded in a rotating manner by the combustion air 12 flowing in tangentially. If gaseous fuel 14 is injected, the mixture is formed with the combustion air 12 directly at the end of the tangential air inlet slots 4, 5.
  • the liquid fuel 13 is injected, the optimal homogeneous fuel distribution is achieved in the region of the return flow zone.
  • the ignition itself takes place at the top of the backflow zone outside the burner. This operation of the double-cone burner with natural gas and oil just described is already known.
  • injection points (nozzles 10) for the gaseous fuel 15 containing highly reactive components are included medium calorific value.
  • the fuel 15 is fed via the fuel line 11 to the distribution channel 17, which is placed in the area of the nozzles 10 on the circumference of the partial cone bodies 1, 2. It then flows through the nozzles 10 into the cone cavity 6 and is mixed there with the combustion air.
  • the nozzles 10 are arranged in a row and aligned in the radial direction.
  • these nozzles 10 can also be arranged in several rows.
  • the positioning of the nozzles 10 in the axial and azimuthal direction can also be advantageous.
  • the nozzles 10 should, if possible, be oriented in such a way that they are completely mixed with all the air available.
  • nozzles 10 are required on the circumference of the partial cone bodies 1, 2.
  • the diameter of a nozzle 10 is less than 1% of the nominal burner diameter, so that one can speak of a microflame burner.
  • the two systems for injecting the gaseous fuels 14, 15 are arranged separately from one another.
  • the double-cone burner according to the invention with microflames is therefore operated in such a way that the highly reactive fuel 15 is injected at high speed through the nozzles 10 arranged near the burner outlet into zones of high air speed, the depth of penetration and the direction of the fuel jets being coordinated such that the ignition and stabilization of the flame only takes place behind the burner outlet after mixing is complete.
  • fuels 14 with a high calorific value and low reactivity and on the other hand fuels 15 with a high reactivity and medium calorific value can be carried.
  • the double-cone burner can be operated in mixed operation with both types of injection with one or two different gaseous fuels 14, 15 or alternatively with a liquid fuel 13.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
EP94101142A 1993-02-12 1994-01-27 Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation à turbine à gaz ou un foyer Expired - Lifetime EP0610722B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4304213 1993-02-12
DE4304213A DE4304213A1 (de) 1993-02-12 1993-02-12 Brenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage

Publications (2)

Publication Number Publication Date
EP0610722A1 true EP0610722A1 (fr) 1994-08-17
EP0610722B1 EP0610722B1 (fr) 1997-05-21

Family

ID=6480298

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94101142A Expired - Lifetime EP0610722B1 (fr) 1993-02-12 1994-01-27 Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation à turbine à gaz ou un foyer

Country Status (4)

Country Link
US (1) US5375995A (fr)
EP (1) EP0610722B1 (fr)
JP (1) JP3512455B2 (fr)
DE (2) DE4304213A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19619873A1 (de) * 1996-05-17 1997-11-20 Abb Research Ltd Brenner
DE19626240A1 (de) * 1996-06-29 1998-01-02 Abb Research Ltd Vormischbrenner und Verfahren zum Betrieb des Brenners
EP0849451A2 (fr) * 1996-12-21 1998-06-24 Abb Research Ltd. Méthode de stabilisation de combustion dans installation à turbine à gaz
EP0908671A1 (fr) * 1997-10-08 1999-04-14 Abb Research Ltd. Procédé de combustion des combustibles gazeux, liquides et combustibles à moyen et bas pouvoir calorifique dans un brûleur
WO2003098110A1 (fr) * 2002-05-16 2003-11-27 Alstom Technology Ltd Bruleur a premelange
US7003957B2 (en) 2001-10-19 2006-02-28 Alstom Technology Ltd Burner for synthesis gas
WO2006058843A1 (fr) * 2004-11-30 2006-06-08 Alstom Technology Ltd Procede et dispositif de combustion d'hydrogene dans un bruleur a premelange
WO2009068427A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Dispositif et procédé d'utilisation d'une installation de turbine à gaz par recours à un deuxième carburant riche en hydrogène
ITTV20120075A1 (it) * 2012-05-08 2013-11-09 Mirko Dencic Bruciatore a vortice.
CN106062481A (zh) * 2013-11-25 2016-10-26 特-可再生能源企业有限公司 用于点燃和燃烧合成气的设备

Families Citing this family (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4316474A1 (de) * 1993-05-17 1994-11-24 Abb Management Ag Vormischbrenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
US5479773A (en) * 1994-10-13 1996-01-02 United Technologies Corporation Tangential air entry fuel nozzle
DE19536837B4 (de) * 1995-10-02 2006-01-26 Alstom Vorrichtung und Verfahren zum Einspritzen von Brennstoffen in komprimierte gasförmige Medien
US5761897A (en) * 1996-12-20 1998-06-09 United Technologies Corporation Method of combustion with a two stream tangential entry nozzle
ATE244380T1 (de) * 1997-11-21 2003-07-15 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
DE59810551D1 (de) * 1998-08-19 2004-02-12 Alstom Switzerland Ltd Brenner zum Betrieb einer Brennkammer
DE59810347D1 (de) 1998-09-10 2004-01-15 Alstom Switzerland Ltd Schwingungsdämpfung in Brennkammern
DE59811961D1 (de) * 1998-11-09 2004-10-21 Alstom Technology Ltd Baden Brenner
EP1002992B1 (fr) * 1998-11-18 2004-09-29 ALSTOM Technology Ltd Brûleur
DE19948674B4 (de) * 1999-10-08 2012-04-12 Alstom Verbrennungseinrichtung, insbesondere für den Antrieb von Gasturbinen
DE10029607A1 (de) * 2000-06-15 2001-12-20 Alstom Power Nv Brenner mit gestufter Vormischgas-Eindüsung
AU2001272682A1 (en) 2000-06-15 2001-12-24 Alstom Power N.V. Method for operating a burner and burner with stepped premix gas injection
DE10040869A1 (de) * 2000-08-21 2002-03-07 Alstom Power Nv Verfahren und Vorrichtung zur Unterdrückung von Strömungswirbeln innerhalb einer Strömungskraftmaschine
DE10049203A1 (de) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Verfahren zur Brennstoffeinleitung in einen Vormischbrenner
DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
US6360776B1 (en) 2000-11-01 2002-03-26 Rolls-Royce Corporation Apparatus for premixing in a gas turbine engine
DE10055408A1 (de) * 2000-11-09 2002-05-23 Alstom Switzerland Ltd Verfahren zur Brenstoffeinspritzung in einen Brenner
DE10056124A1 (de) * 2000-11-13 2002-05-23 Alstom Switzerland Ltd Brennersystem mit gestufter Brennstoff-Eindüsung und Verfahren zum Betrieb
DE10164099A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeinspritzung
DE10219354A1 (de) * 2002-04-30 2003-11-13 Rolls Royce Deutschland Gasturbinenbrennkammer mit gezielter Kraftstoffeinbringung zur Verbesserung der Homogenität des Kraftstoff-Luft-Gemisches
US6928822B2 (en) * 2002-05-28 2005-08-16 Lytesyde, Llc Turbine engine apparatus and method
US6935117B2 (en) * 2003-10-23 2005-08-30 United Technologies Corporation Turbine engine fuel injector
CN100590355C (zh) * 2004-02-12 2010-02-17 阿尔斯通技术有限公司 具有限定圆锥形涡旋室的涡旋发生器的、传感器监视的预混合燃烧器
CN101243287B (zh) * 2004-12-23 2013-03-27 阿尔斯托姆科技有限公司 具有混合段的预混燃烧器
GB0510021D0 (en) * 2005-05-17 2005-06-22 Roscoe Keith Liquid injection into gas stream
JP4728176B2 (ja) * 2005-06-24 2011-07-20 株式会社日立製作所 バーナ、ガスタービン燃焼器及びバーナの冷却方法
DE102007043626A1 (de) * 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität
EP2058590B1 (fr) * 2007-11-09 2016-03-23 Alstom Technology Ltd Procédé de fonctionnement d'un brûleur
JP5242135B2 (ja) 2007-11-12 2013-07-24 株式会社ノヴァエネルギー 水流発電装置
JP5574969B2 (ja) * 2007-11-27 2014-08-20 アルストム テクノロジー リミテッド 予混合バーナ内で水素を燃焼させるための方法および装置
CH701905A1 (de) * 2009-09-17 2011-03-31 Alstom Technology Ltd Verfahren zum Verbrennen wasserstoffreicher, gasförmiger Brennstoffe in einem Brenner sowie Brenner zur Durchführung des Verfahrens.
US9187699B2 (en) * 2011-11-08 2015-11-17 Exxonmobil Chemical Patents Inc. Hydrocarbon pyrolysis process
US9194604B2 (en) 2012-03-09 2015-11-24 The Gsi Group, Llc Burner for gas-fired air heater
EP2685160B1 (fr) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2509436A1 (fr) * 1981-07-07 1983-01-14 Sred Az V Bruleur a canaux annulaires pour la combustion simultanee et separee de plusieurs combustibles
EP0433790A1 (fr) * 1989-12-22 1991-06-26 Asea Brown Boveri Ag BrÀ»leur
EP0521325A1 (fr) * 1991-07-03 1993-01-07 Asea Brown Boveri Ag Chambre de combustion

Family Cites Families (4)

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US3529917A (en) * 1968-07-23 1970-09-22 Eng Co The Air-mixing device for fuel burner
DE3317035A1 (de) * 1983-05-10 1984-11-15 BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau Mehrstoffbrenner
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

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2509436A1 (fr) * 1981-07-07 1983-01-14 Sred Az V Bruleur a canaux annulaires pour la combustion simultanee et separee de plusieurs combustibles
EP0433790A1 (fr) * 1989-12-22 1991-06-26 Asea Brown Boveri Ag BrÀ»leur
EP0521325A1 (fr) * 1991-07-03 1993-01-07 Asea Brown Boveri Ag Chambre de combustion

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19619873A1 (de) * 1996-05-17 1997-11-20 Abb Research Ltd Brenner
US5921766A (en) * 1996-05-17 1999-07-13 Abb Research Ltd. Burner
DE19626240A1 (de) * 1996-06-29 1998-01-02 Abb Research Ltd Vormischbrenner und Verfahren zum Betrieb des Brenners
US5782627A (en) * 1996-06-29 1998-07-21 Abb Research Ltd. Premix burner and method of operating the burner
EP0849451A2 (fr) * 1996-12-21 1998-06-24 Abb Research Ltd. Méthode de stabilisation de combustion dans installation à turbine à gaz
EP0849451B1 (fr) * 1996-12-21 2003-05-07 ALSTOM (Switzerland) Ltd Méthode de stabilisation de combustion dans installation à turbine à gaz
EP0908671A1 (fr) * 1997-10-08 1999-04-14 Abb Research Ltd. Procédé de combustion des combustibles gazeux, liquides et combustibles à moyen et bas pouvoir calorifique dans un brûleur
US7003957B2 (en) 2001-10-19 2006-02-28 Alstom Technology Ltd Burner for synthesis gas
WO2003098110A1 (fr) * 2002-05-16 2003-11-27 Alstom Technology Ltd Bruleur a premelange
US7013648B2 (en) 2002-05-16 2006-03-21 Alstom Technology Ltd. Premix burner
WO2006058843A1 (fr) * 2004-11-30 2006-06-08 Alstom Technology Ltd Procede et dispositif de combustion d'hydrogene dans un bruleur a premelange
US7871262B2 (en) 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner
CN101069039B (zh) * 2004-11-30 2011-10-19 阿尔斯托姆科技有限公司 用于在预混合燃烧器中燃烧氢气的方法和设备
WO2009068427A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Dispositif et procédé d'utilisation d'une installation de turbine à gaz par recours à un deuxième carburant riche en hydrogène
US10208960B2 (en) 2007-11-27 2019-02-19 Ansaldo Energia Switzerland AG Method for operating a gas turbine installation and equipment for carrying out the method
ITTV20120075A1 (it) * 2012-05-08 2013-11-09 Mirko Dencic Bruciatore a vortice.
CN106062481A (zh) * 2013-11-25 2016-10-26 特-可再生能源企业有限公司 用于点燃和燃烧合成气的设备
CN106062481B (zh) * 2013-11-25 2018-10-09 一特-可再生能源企业有限公司 用于点燃和燃烧合成气的设备
US10393372B2 (en) 2013-11-25 2019-08-27 Entech-Renewable Energy Solutions Pty.Ltd. Apparatus for firing and combustion of syngas

Also Published As

Publication number Publication date
JPH06241423A (ja) 1994-08-30
DE4304213A1 (de) 1994-08-18
DE59402785D1 (de) 1997-06-26
JP3512455B2 (ja) 2004-03-29
EP0610722B1 (fr) 1997-05-21
US5375995A (en) 1994-12-27

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