EP1286112A1 - Brûleur à prémélange et procédé opératoire dudit brûleur - Google Patents

Brûleur à prémélange et procédé opératoire dudit brûleur Download PDF

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Publication number
EP1286112A1
EP1286112A1 EP01119249A EP01119249A EP1286112A1 EP 1286112 A1 EP1286112 A1 EP 1286112A1 EP 01119249 A EP01119249 A EP 01119249A EP 01119249 A EP01119249 A EP 01119249A EP 1286112 A1 EP1286112 A1 EP 1286112A1
Authority
EP
European Patent Office
Prior art keywords
burner
combustion
premix
pilot
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.)
Withdrawn
Application number
EP01119249A
Other languages
German (de)
English (en)
Inventor
Karsten Jordan
Holger Dr. Streb
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP01119249A priority Critical patent/EP1286112A1/fr
Priority to PCT/EP2002/008354 priority patent/WO2003014621A1/fr
Priority to JP2003519311A priority patent/JP4354810B2/ja
Priority to EP02760280A priority patent/EP1415112A1/fr
Publication of EP1286112A1 publication Critical patent/EP1286112A1/fr
Priority to US10/764,290 priority patent/US7029272B2/en
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2203/00—Gaseous fuel burners
    • F23D2203/10—Flame diffusing means
    • F23D2203/105—Porous plates

Definitions

  • the invention relates to a premix burner, in particular for a gas turbine, with a main burner and a den Main burner stabilizing pilot burner. It continues to affect a method of operating a premix burner.
  • a burner for a gas turbine is known from US 6202401.
  • This burner designed as a hybrid burner, works optionally as a diffusion or premix burner. While at the diffusion combustion fuel and combustion air in the flame is mixed in the premix combustion first the combustion air with the fuel intensive mixed and this mixture then fed to the combustion. This is particularly advantageous in terms of Nitrogen oxide emissions, because in the premix flame due to the homogeneous mixture a uniform flame temperature prevails. The nitrogen oxide formation increases exponentially with the Flame temperature.
  • a fuel delivery system a main burner and one pilot burner igniting the main burner.
  • the pilot burner flame is monitored by means of a piston in which a Porous material is arranged to absorb a analyzing gas is used.
  • EP 1062461 A1 shows a combustion chamber with a lining from heat shield elements.
  • a heat shield element is as run a burner heat shield element, the combustion air and fuel is supplied.
  • the heat shield element is designed as a pore burner. The combustion reaction takes place here at least partly in a porous material. This will cause the combustion stabilized and the tendency to form combustion vibrations reduced.
  • EP 0576697 B1 describes a gas turbine in which in addition to classic burner types, also catalytic ones Burners are used.
  • the classic burner types are Premix burners with which the main combustion is carried out becomes.
  • catalytic burners a simpler regulation with changing load conditions the gas turbine.
  • the invention has for its object a premix burner to be specified in which combustion is particularly low in nitrogen oxides with a low tendency to instability in combustion is possible. Furthermore, a corresponding Method for operating a premix burner and a gas turbine with low nitrogen oxide emissions and low inclination to Burn instabilities can be specified.
  • the above-mentioned object is achieved by the features of claim 1. These are for mixing from combustion air with fuel to a fuel gas mixture and for the subsequent combustion of the fuel gas mixture a main burner for most of the combustion air and a pilot burner to stabilize a lean Combustion is provided in the main burner, the pilot burner designed as a pore burner with a burner material which has a fine-pored structure.
  • the invention is based on the consideration of the pilot burner a premix burner as a pore burner.
  • the pilot burner is the unstable premix combustion of the main burner should be stabilized. Indeed but it could be shown through tests that sufficient by heating the burner material Stabilization through the pilot burner designed as a pore burner is possible.
  • the pore burner is then successful can be used if the mass flow rate of the fuel / Air mixture is set correctly.
  • the pressure conditions are set so that not by a too high mass flow rate the combustion reaction from the Pore body is expelled.
  • the mass throughput but also not be so low that the danger a flashback occurs.
  • the nitrogen oxide emissions are caused by a strong heating and thus reduces heat radiation from the burner material, because the flame temperature drops as a result. Furthermore, also the reaction density in the entire burner flame consistent performance is reduced as part of the response in the porous burner material. Furthermore, the combustion due to the particularly low susceptibility of the pore burner stabilized against air or gas fluctuations, whereby especially low susceptibility to Combustion vibrations result.
  • the fine-pored structure is expedient by foaming of a basic material. Foaming and subsequent hardening of the base material results in easier Way to a fine-pored structure.
  • the burner material is preferably ceramic.
  • a ceramic Burner material is particularly characterized by a high Temperature resistance.
  • the burner material shows expediently on zirconium oxide or silicon carbide.
  • the burner material is a nickel or cobalt based superalloy or a high-temperature steel.
  • Even such metallic ones Materials can be used as metal foams, for example Execute fine pores and have a high temperature resistance good processability. Is possible also a metal mesh version.
  • the main burner encloses the pilot burner with an annular duct for the combustion air.
  • the premix burner is in an appropriate further training in one Gas turbine, in particular a stationary gas turbine, used.
  • a stationary gas turbine like this is used to generate electrical energy, there is a reduction in environmental pollution and compliance statutory emissions regulations to a low Nitrogen oxide emission.
  • combustion vibrations are in such gas turbines due to high power releases the risk of mechanical damage.
  • the gas turbine preferably has an annular combustion chamber.
  • an annular combustion chamber it can be done by coupling all Burners for combustion vibrations of particularly high amplitude come. Because of the complex geometry, these are vibrations also practically not to be calculated in advance.
  • Figure 1 shows a premix burner 1 with a main burner 3 and with a pilot burner 5.
  • the main burner 3 has one Ring channel 7, which surrounds the pilot burner 5 concentrically.
  • Swirl blades 9 are arranged in the ring channel 7.
  • Combustion air 11 is guided through ring channel 7.
  • the combustion air 11 is about not shown hollow Swirl blades mixed with fuel 13 from the swirl blades the fuel 13 is skipped.
  • the fuel 13 mixes intensively with the combustion air 11 before it is burned in a main flame 15.
  • the main burner is used to reduce nitrogen oxide emissions 3 operated with an excess air of combustion air 11, so that a lean mixture is created.
  • the premixing ensures that the mixture is largely homogeneous and thus there is a uniform flame temperature.
  • This skinny Premix combustion is difficult to regulate and goes out easily. It is accordingly susceptible to combustion instabilities, through acoustic coupling with the Environment, such as a combustion chamber wall, to create a stable combustion vibration can lead. Such combustion vibrations lead to high noise pollution or even damage to the combustion system.
  • the pilot burner is used to stabilize the main flame 15 5. It has a pilot air duct 21 through which combustion air 11 is supplied. Furthermore, the pilot burner points 5 a pilot fuel channel 23 through which the fuel 13 is fed. The combustion air 11 and the fuel 13 are passed through a fine-pored burner material 41.
  • the Pilot burner 5 is thereby designed as a pore burner. Before entering the burner material 41, one finds Mixing of the combustion air 11 and the fuel 13 instead of. A combustion reaction is already taking place in the burner material 41. By a pilot flame 25 at the outlet of the Pilot burner 5, the main flame 15 is stabilized.
  • the Burner material 41 reduced by equalization and Flame temperature lowering the nitrogen oxide emissions. Farther results in particular from the heating of the burner material 41 a stable, against air or gas fluctuations very insensitive combustion and thus a reduced Tendency to develop combustion vibrations.
  • the pilot fuel channel is in the pilot burner 5 shown in FIG 23 from a gas lance 23 and an additional channel 35 composed, which corresponds to the pilot fuel demand more adaptable supply of fuel 13 results.
  • the burner material 41 is arranged following an opening 39 of the gas lance 23, one Mouth 39 of the additional duct 37 and the pilot air duct 21 . It is made of a ceramic Foamed material and has a corresponding fine-pored structure. The burner material would also be conceivable 41 to form from a material mixture, one or then removed several components of this mixture that the fine-pored structure of the burner material 41 remains.
  • the gas turbine 51 shown in FIG. 3 has one Compressor 53, an annular combustion chamber 55 and a turbine part 57 on.
  • the combustion air 11 is in the compressor 53 highly compressed and fed to the ring combustion chamber 55.
  • Premix burner 1 of the type described above will be there burned with fuel 13 to a hot gas 59 which is the turbine part 57 drives.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP01119249A 2001-08-09 2001-08-09 Brûleur à prémélange et procédé opératoire dudit brûleur Withdrawn EP1286112A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP01119249A EP1286112A1 (fr) 2001-08-09 2001-08-09 Brûleur à prémélange et procédé opératoire dudit brûleur
PCT/EP2002/008354 WO2003014621A1 (fr) 2001-08-09 2002-07-26 Bruleur a melange prealable et procede permettant de le faire fonctionner
JP2003519311A JP4354810B2 (ja) 2001-08-09 2002-07-26 予混合バーナとその運転方法
EP02760280A EP1415112A1 (fr) 2001-08-09 2002-07-26 Bruleur a melange prealable et procede permettant de le faire fonctionner
US10/764,290 US7029272B2 (en) 2001-08-09 2004-01-23 Premix burner and method for operation thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01119249A EP1286112A1 (fr) 2001-08-09 2001-08-09 Brûleur à prémélange et procédé opératoire dudit brûleur

Publications (1)

Publication Number Publication Date
EP1286112A1 true EP1286112A1 (fr) 2003-02-26

Family

ID=8178283

Family Applications (2)

Application Number Title Priority Date Filing Date
EP01119249A Withdrawn EP1286112A1 (fr) 2001-08-09 2001-08-09 Brûleur à prémélange et procédé opératoire dudit brûleur
EP02760280A Withdrawn EP1415112A1 (fr) 2001-08-09 2002-07-26 Bruleur a melange prealable et procede permettant de le faire fonctionner

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP02760280A Withdrawn EP1415112A1 (fr) 2001-08-09 2002-07-26 Bruleur a melange prealable et procede permettant de le faire fonctionner

Country Status (4)

Country Link
US (1) US7029272B2 (fr)
EP (2) EP1286112A1 (fr)
JP (1) JP4354810B2 (fr)
WO (1) WO2003014621A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10341610B4 (de) * 2003-09-10 2007-06-06 Lurgi Lentjes Ag Verfahren zur Verbrennung von festen Abfällen
US7568907B2 (en) 2005-12-22 2009-08-04 Alstom Technology Ltd. Combustion chamber with burner and associated operating method
EP2930430A1 (fr) * 2014-04-07 2015-10-14 Siemens Aktiengesellschaft Bec de brûleur et brûleur d'une turbine à gaz

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1645805A1 (fr) * 2004-10-11 2006-04-12 Siemens Aktiengesellschaft brûleur pour combustible fluide et procédé pour uriliser un tel brûleur
US8393891B2 (en) * 2006-09-18 2013-03-12 General Electric Company Distributed-jet combustion nozzle
US8413445B2 (en) * 2007-05-11 2013-04-09 General Electric Company Method and system for porous flame holder for hydrogen and syngas combustion
US8529249B2 (en) * 2007-09-25 2013-09-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Flame holder system
CN102200280A (zh) * 2011-05-25 2011-09-28 朱复定 一种陶瓷窑二次进风预混燃气燃烧器

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1377648A (en) * 1971-11-05 1974-12-18 Penny R N Flame-tube for a combustion chamber of a gas turbine engine
EP0193838A2 (fr) * 1985-03-04 1986-09-10 Siemens Aktiengesellschaft Disposition de brûleur pour installations de combustion, en particulier pour chambres de combustion d'installations de turbines à gaz ainsi que procédé de sa mise en oeuvre
US5022849A (en) * 1988-07-18 1991-06-11 Hitachi, Ltd. Low NOx burning method and low NOx burner apparatus
EP0710797A2 (fr) * 1994-11-05 1996-05-08 Abb Research Ltd. Procédé et dispositif de mise en oeuvre d'un brûleur à prémélange
DE19637727A1 (de) * 1996-09-16 1998-03-19 Siemens Ag Verfahren zur katalytischen Verbrennung eines fossilen Brennstoffs in einer Verbrennungsanlage und Anordnung zur Durchführung dieses Verfahrens

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3954384A (en) 1974-02-20 1976-05-04 Robertshaw Controls Company Burner system
US5080577A (en) * 1990-07-18 1992-01-14 Bell Ronald D Combustion method and apparatus for staged combustion within porous matrix elements
WO1993013360A1 (fr) * 1991-12-30 1993-07-08 Bowin Designs Pty. Ltd. Dispositif de chauffage au gaz comprenant des bruleurs fonctionnant sans air secondaire
EP0576697B1 (fr) 1992-06-29 1997-08-27 Abb Research Ltd. Chambre de combustion pour turbine à gaz
US5879154A (en) * 1996-11-18 1999-03-09 Rheem Manufacturing Company Flame spreader-type fuel burner with lowered NOx emissions
EP1062461B1 (fr) 1998-03-10 2003-12-03 Siemens Aktiengesellschaft Chambre de combustion et mode de fonctionnement d'une chambre de combustion
DE19904921C2 (de) * 1999-02-06 2000-12-07 Bosch Gmbh Robert Erhitzer für Flüssigkeiten

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1377648A (en) * 1971-11-05 1974-12-18 Penny R N Flame-tube for a combustion chamber of a gas turbine engine
EP0193838A2 (fr) * 1985-03-04 1986-09-10 Siemens Aktiengesellschaft Disposition de brûleur pour installations de combustion, en particulier pour chambres de combustion d'installations de turbines à gaz ainsi que procédé de sa mise en oeuvre
US5022849A (en) * 1988-07-18 1991-06-11 Hitachi, Ltd. Low NOx burning method and low NOx burner apparatus
EP0710797A2 (fr) * 1994-11-05 1996-05-08 Abb Research Ltd. Procédé et dispositif de mise en oeuvre d'un brûleur à prémélange
DE19637727A1 (de) * 1996-09-16 1998-03-19 Siemens Ag Verfahren zur katalytischen Verbrennung eines fossilen Brennstoffs in einer Verbrennungsanlage und Anordnung zur Durchführung dieses Verfahrens

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10341610B4 (de) * 2003-09-10 2007-06-06 Lurgi Lentjes Ag Verfahren zur Verbrennung von festen Abfällen
DE10341610B8 (de) * 2003-09-10 2007-09-27 Lentjes Gmbh Verfahren zur Verbrennung von festen Abfällen
US7568907B2 (en) 2005-12-22 2009-08-04 Alstom Technology Ltd. Combustion chamber with burner and associated operating method
DE102005061486B4 (de) * 2005-12-22 2018-07-12 Ansaldo Energia Switzerland AG Verfahren zum Betreiben einer Brennkammer einer Gasturbine
EP2930430A1 (fr) * 2014-04-07 2015-10-14 Siemens Aktiengesellschaft Bec de brûleur et brûleur d'une turbine à gaz
WO2015154902A1 (fr) * 2014-04-07 2015-10-15 Siemens Aktiengesellschaft Bec de brûleur et brûleur pour une turbine à gaz
US10125982B2 (en) 2014-04-07 2018-11-13 Siemens Aktiengesellschaft Burner tip and a burner for a gas turbine

Also Published As

Publication number Publication date
JP4354810B2 (ja) 2009-10-28
EP1415112A1 (fr) 2004-05-06
US20050079464A1 (en) 2005-04-14
WO2003014621A1 (fr) 2003-02-20
US7029272B2 (en) 2006-04-18
JP2004537707A (ja) 2004-12-16

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