EP1439349A1 - Procédé de combustion et brûleur pour sa mise en oeuvre - Google Patents

Procédé de combustion et brûleur pour sa mise en oeuvre Download PDF

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Publication number
EP1439349A1
EP1439349A1 EP03104559A EP03104559A EP1439349A1 EP 1439349 A1 EP1439349 A1 EP 1439349A1 EP 03104559 A EP03104559 A EP 03104559A EP 03104559 A EP03104559 A EP 03104559A EP 1439349 A1 EP1439349 A1 EP 1439349A1
Authority
EP
European Patent Office
Prior art keywords
fuel
catalytic converter
burner
exhaust gas
catalyst
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Withdrawn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
EP03104559A
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German (de)
English (en)
Inventor
Richard Carroni
Peter Flohr
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.)
Ansaldo Energia Switzerland AG
Original Assignee
Alstom Technology 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 Technology AG filed Critical Alstom Technology AG
Publication of EP1439349A1 publication Critical patent/EP1439349A1/fr
Withdrawn legal-status Critical Current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 
    • F23C13/00—Apparatus in which combustion takes place in the presence of catalytic material
    • 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
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means

Definitions

  • the present invention relates to the field of combustion technology. It relates to a combustion process according to the preamble of claim 1 and a burner to carry out the process.
  • Catalytic combustion is a process that can be applied to gas turbines to increase the stability of the combustion process and reduce emissions (see, for example, US-B1-6,339,925).
  • Limits in the material load and operating conditions require that the catalysts used convert only a part (typically up to 60%) of the total fuel flowing through the burner. The resulting gas temperature may therefore not be increased enough to burn the fuel remaining at the outlet of the catalyst (a homogeneous mixture of fuel O 2 , N 2 , CO, CO 2 and H 2 O at temperatures between 600 ° C and 950 ° C) stabilize thermally. Aerodynamic stabilization is therefore necessary.
  • a simplified vortex generator element also known as a SEV vortex generator is referred to and by reduced pressure losses distinguished has been disclosed in US-A-5,577,378. It has proven to be suitable proven for sequential combustion or combustion with afterburning. The effect of the device is based on an exhaust gas temperature at the outlet of the first burner, which is above the autoignition temperature of the im second burner injected fuel; the combustion chamber for afterburning is a burnerless room with a number of vortex generating elements, the purpose of which is to mix the second stage fuel with the Mix exhaust gas of the first stage before auto-ignition.
  • the degree of Circulation and the shape of the axial velocity profile can be determined by the Choice of the geometric parameters of the vortex generating element (length, Height, flow angle) can be tailored to the needs and can be in In extreme cases, even lead to a free-standing vertebral collapse like him sometimes observed in planes with delta wings at large angles of attack becomes.
  • Catalyst in the first combustion stage indicate which one is simple and safe is to be carried out and leads to lower pressure losses, as well as a burner to specify to carry out the procedure.
  • the essence of the invention is in a combustion in which in the second combustion stage of unburned fuel from the first, with a Combustion-equipped combustion stage, which is burned in the second stage to generate aerodynamically stabilized homogeneous flame by the fuel-containing exhaust gas from the catalyst between the outlet the catalyst and the homogeneous flame is passed through devices, which aerodynamically stabilize the homogeneous flame.
  • aerodynamic stabilizing devices used vortex generating elements, which are arranged at the outlet of the catalyst.
  • aerodynamic stabilizing device additionally a step-like extension in Flow channel uses which between the vortex generating elements and the homogeneous flame is arranged.
  • the exhaust gas at the outlet of the catalyst contains, in addition to the unburned fuel, O 2 , N 2 , CO, CO 2 and H 2 O, exits the catalyst at a flow rate of less than or equal to 50 m / s and has a temperature between 600 ° C and 950 ° C.
  • a preferred embodiment of the burner according to the invention is thereby characterized that additionally downstream of the vortex generating elements a step-like expansion of the flow channel is provided.
  • the formation of the vortex generating elements depends on whether the vortex generating elements are mainly a mixture or cause a breakdown of vertebrae.
  • SEV vortex generation elements are also advantageous because for these elements already extensive experience regarding their interpretation (regarding cooling, fatigue, flame position, pulsations, speed and temperature distributions) are present in high-temperature burners have been made with afterburning, and directly on burners with catalytic Elements can be applied.
  • the degree of circulation and the shape of the axial velocity profile by suitable choice of parameters (length L, height h, Inlet angle ⁇ , and the angle ⁇ ) derived from these three quantities Desire to be set. Depending on the exact requirements these parameters can be set so that only one mixture (lowest Pressure drop) or a mixture and a collapse of the vertebrae (higher Pressure loss due to the formation of a recirculation zone in the wake) results. In any case, there will be a pair of counter-rotating flow vortices generated.
  • the vortex generating elements can be designed so that the homogeneous flames are prevented from returning to the elements themselves attach.
  • the catalyst can also include a pilot burner that produces its own combustion products (e.g. an enriched fuel / air mixture or syngas), which then also is added to the main gas stream.
  • a pilot burner that produces its own combustion products (e.g. an enriched fuel / air mixture or syngas), which then also is added to the main gas stream.
  • This is an important consideration because the Combustion of inhomogeneous mixtures leads to high local temperatures and thereby increasing emissions.
  • the vortex generating elements are of their nature according to also mixing devices and therefore ensure that the gas mixtures be mixed well before homogeneous combustion.
  • the vortex generating elements 16 are sufficiently steep, i.e. if the approach angle is large, they can have recirculation zones in their post-currents cause.
  • the recirculation zones can be undesirable because they become one Anchor the homogeneous flame to the vortex generating elements could. Such anchoring would be significant on the devices cause thermal stress and reduce the service life.
  • FIG. 3 differs differs from the burner 12 shown in FIG. 2 mainly in that between the vortex generating elements 16 and the homogeneous flame 17 one step-like extension 19 is provided in the cross section of the flow channel 13 is. This step-like extension 19 reliably prevents the flame 17 from the elements 16 is anchored and endangered them.
EP03104559A 2003-01-14 2003-12-05 Procédé de combustion et brûleur pour sa mise en oeuvre Withdrawn EP1439349A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH462003 2003-01-14
CH462003 2003-01-14

Publications (1)

Publication Number Publication Date
EP1439349A1 true EP1439349A1 (fr) 2004-07-21

Family

ID=32514186

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03104559A Withdrawn EP1439349A1 (fr) 2003-01-14 2003-12-05 Procédé de combustion et brûleur pour sa mise en oeuvre

Country Status (3)

Country Link
US (1) US6896509B2 (fr)
EP (1) EP1439349A1 (fr)
JP (1) JP2004219066A (fr)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10330023A1 (de) * 2002-07-20 2004-02-05 Alstom (Switzerland) Ltd. Wirbelgenerator mit kontrollierter Nachlaufströmung
KR100754013B1 (ko) 2006-11-06 2007-09-03 한국항공우주연구원 스월자극혼합기
US8812582B2 (en) * 2006-11-30 2014-08-19 Red Hat, Inc. Automated screen saver with shared media
US8408872B2 (en) * 2009-09-24 2013-04-02 General Electric Company Fastback turbulator structure and turbine nozzle incorporating same
US8881500B2 (en) * 2010-08-31 2014-11-11 General Electric Company Duplex tab obstacles for enhancement of deflagration-to-detonation transition
JP5584260B2 (ja) * 2012-08-08 2014-09-03 日野自動車株式会社 排気浄化装置用バーナー
US10436445B2 (en) 2013-03-18 2019-10-08 General Electric Company Assembly for controlling clearance between a liner and stationary nozzle within a gas turbine
US9316396B2 (en) 2013-03-18 2016-04-19 General Electric Company Hot gas path duct for a combustor of a gas turbine
US9383104B2 (en) 2013-03-18 2016-07-05 General Electric Company Continuous combustion liner for a combustor of a gas turbine
US9316155B2 (en) 2013-03-18 2016-04-19 General Electric Company System for providing fuel to a combustor
US9631812B2 (en) 2013-03-18 2017-04-25 General Electric Company Support frame and method for assembly of a combustion module of a gas turbine
US9400114B2 (en) 2013-03-18 2016-07-26 General Electric Company Combustor support assembly for mounting a combustion module of a gas turbine
US9360217B2 (en) 2013-03-18 2016-06-07 General Electric Company Flow sleeve for a combustion module of a gas turbine
US9322556B2 (en) 2013-03-18 2016-04-26 General Electric Company Flow sleeve assembly for a combustion module of a gas turbine combustor
WO2015184294A1 (fr) 2014-05-29 2015-12-03 General Electric Company Générateur de turbulence fastback
US10364684B2 (en) 2014-05-29 2019-07-30 General Electric Company Fastback vorticor pin
US10280785B2 (en) 2014-10-31 2019-05-07 General Electric Company Shroud assembly for a turbine engine
US10233775B2 (en) 2014-10-31 2019-03-19 General Electric Company Engine component for a gas turbine engine
US11371709B2 (en) 2020-06-30 2022-06-28 General Electric Company Combustor air flow path
CN114110658A (zh) * 2021-11-19 2022-03-01 上海交通大学 氢燃料分级无焰燃烧方法及燃烧装置

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4731989A (en) 1983-12-07 1988-03-22 Kabushiki Kaisha Toshiba Nitrogen oxides decreasing combustion method
DE4202018C1 (en) * 1992-01-25 1993-04-29 Abb Patent Gmbh, 6800 Mannheim, De Combustion chamber for gas turbine plant - has two catalyst holders consisting of honeycomb segments with flame holder downstream of them.
US5518697A (en) * 1994-03-02 1996-05-21 Catalytica, Inc. Process and catalyst structure employing intergal heat exchange with optional downstream flameholder
US5577378A (en) 1993-04-08 1996-11-26 Abb Management Ag Gas turbine group with reheat combustor
US5626017A (en) 1994-07-25 1997-05-06 Abb Research Ltd. Combustion chamber for gas turbine engine
WO2002068867A2 (fr) * 2001-01-16 2002-09-06 Catalytica Energy Systems, Inc. Strategie antipollution pour un systeme de combustion catalytique flexible
EP1255077A2 (fr) * 2001-04-30 2002-11-06 ALSTOM (Switzerland) Ltd Dispositif pour la combustion d'un mélange gazeux de combustible et comburant

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US3914090A (en) * 1971-05-13 1975-10-21 Engelhard Min & Chem Method and furnace apparatus
US3729285A (en) * 1972-05-22 1973-04-24 G Schwedersky Burner and method of operating it to control the production of nitrogen oxides
US3868211A (en) * 1974-01-11 1975-02-25 Aqua Chem Inc Pollutant reduction with selective gas stack recirculation
US5277578A (en) * 1992-12-08 1994-01-11 Gaz Metropolitain & Co., Ltd. And Ptnr. Gas burner having tangential counter-rotation air injectors and axial gas injector tube
CH687831A5 (de) 1993-04-08 1997-02-28 Asea Brown Boveri Vormischbrenner.
DE4435266A1 (de) 1994-10-01 1996-04-04 Abb Management Ag Brenner
SE9602688L (sv) * 1996-07-08 1998-01-09 Volvo Ab Katalytisk brännkammare, samt förfarande för tändning och reglering av den katalytiska brännkammaren
US6339925B1 (en) 1998-11-02 2002-01-22 General Electric Company Hybrid catalytic combustor
US6652265B2 (en) * 2000-12-06 2003-11-25 North American Manufacturing Company Burner apparatus and method

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4731989A (en) 1983-12-07 1988-03-22 Kabushiki Kaisha Toshiba Nitrogen oxides decreasing combustion method
DE4202018C1 (en) * 1992-01-25 1993-04-29 Abb Patent Gmbh, 6800 Mannheim, De Combustion chamber for gas turbine plant - has two catalyst holders consisting of honeycomb segments with flame holder downstream of them.
US5577378A (en) 1993-04-08 1996-11-26 Abb Management Ag Gas turbine group with reheat combustor
US5518697A (en) * 1994-03-02 1996-05-21 Catalytica, Inc. Process and catalyst structure employing intergal heat exchange with optional downstream flameholder
US5626017A (en) 1994-07-25 1997-05-06 Abb Research Ltd. Combustion chamber for gas turbine engine
WO2002068867A2 (fr) * 2001-01-16 2002-09-06 Catalytica Energy Systems, Inc. Strategie antipollution pour un systeme de combustion catalytique flexible
EP1255077A2 (fr) * 2001-04-30 2002-11-06 ALSTOM (Switzerland) Ltd Dispositif pour la combustion d'un mélange gazeux de combustible et comburant

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US20040146820A1 (en) 2004-07-29
US6896509B2 (en) 2005-05-24
JP2004219066A (ja) 2004-08-05

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