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EP1265029A2 - Ensemble brûleur - Google Patents

Ensemble brûleur Download PDF

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Publication number
EP1265029A2
EP1265029A2 EP02405361A EP02405361A EP1265029A2 EP 1265029 A2 EP1265029 A2 EP 1265029A2 EP 02405361 A EP02405361 A EP 02405361A EP 02405361 A EP02405361 A EP 02405361A EP 1265029 A2 EP1265029 A2 EP 1265029A2
Authority
EP
European Patent Office
Prior art keywords
flow
flow channel
combustion chamber
burner
section
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Withdrawn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
EP02405361A
Other languages
German (de)
English (en)
Other versions
EP1265029A3 (fr
Inventor
Adnan Dr. Eroglu
Klaus Dr. Knapp
Bettina Dr. Paikert
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 Technology GmbH
Original Assignee
Alstom Technology AG
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 Technology AG, Alstom Schweiz AG filed Critical Alstom Technology AG
Publication of EP1265029A2 publication Critical patent/EP1265029A2/fr
Publication of EP1265029A3 publication Critical patent/EP1265029A3/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Withdrawn legal-status Critical Current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 
    • 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
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • 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
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/70—Baffles or like flow-disturbing devices
    • 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
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03341—Sequential combustion chambers or burners

Definitions

  • the invention relates to a burner system with a premix burner, in which is provided at least one vortex generator, the one of the Air-containing, gaseous air flowing through the premix burner Main flow is interspersed in the gaseous downstream of the vortex generator and / or liquid fuel as a secondary flow for generating a fuel / air mixture is injected, as well as with a combustion chamber, which is downstream of the Premix burner connects to this and a combustion chamber cross section which is larger than that limited by the premix burner Flow cross section immediately upstream of the combustion chamber.
  • FIG. 3 shown schematically.
  • the known burner system has a premix burner 1, through which a supply air flow ZL flows axially.
  • the usually supply air ZL compressed by a compressor stage first flows through one Vortex generator 2, for example of the type described in EP 0 619 133 B1 described vortex generator.
  • the vortex generator 2 typically consists of four tetrahedral vertebral bodies, which are equally distributed in Are arranged circumferentially within the flow channel.
  • Such a thing vortex generator 2 is capable of four vortex flow pairs generate that downstream within the subsequent premix burner 1 spread.
  • gaseous or liquid fuel is centralized in the swirled supply air ZL injected.
  • the fuel mixes along the downstream one Mixing section 4 largely uniformly with the swirled supply air ZL Fuel / air mixture, which finally flows in the direction of flow Premix burner 1 subsequent combustion chamber 5 enters and is ignited.
  • the flow transition within the burner system shown in Fig. 3 is in per se known step-shaped, i.e. the by the Premixing burner 1 in the mixing area 4 limits the flow cross section C1 directly over a sharp-edged step 6 to the widened Combustion chamber cross section C2.
  • This erratic transition between Premix burner 1 and combustion chamber 5 are fluidically within the axially propagating fuel / air mixture to so-called, downstream to the sharp-edged step 6 spreading separation vortex 7, which is a considerable have vertebral strength oriented transversely to the direction of propagation and form a periodic sequence.
  • thermoacoustic Vibrations are basically resonant phenomena, which can be found in certain Train operating states of the burner system more or less, however especially in the case of lower inlet or flame temperatures Appearance.
  • Burner system to improve the combustion process is optimized within the combustion chamber.
  • Combustion chamber volume almost completely for combustion of the in the combustion chamber to use entering fuel / air mixture.
  • thermoacoustic vibrations The ones to be met Precautions should on the one hand be possible with the simplest possible means and raise only low costs. It is also important to take precautions in existing ones to integrate burner systems in operation.
  • a burner system is designed in accordance with the preamble of claim 1, that a flow channel is provided between the premix burner and the combustion chamber and is delimited by side walls which create a gradual transition between the flow cross section (C1) and the combustion chamber cross section (C2), and that at least one flow stall structure is provided upstream, inside and / or downstream of the flow channel, through which the fuel / air mixture passing through the flow channel is locally detached from the side wall of the flow channel.
  • a gradual transition between the Premix burner and the combustion chamber which is preferably rounded is trained.
  • the term gradual transition basically means everyone To understand transition geometry that the flow cross section within the Premix burner, which is smaller than that inside the combustion chamber, gradually expanded to the cross-section of the combustion chamber.
  • the Transition to a funnel-shaped contour with which the flow cross-section within the premix burner to the combustion chamber cross-section evenly is expanded. It is also possible to make the transition area conical, i.e. with straight, obliquely inclined to the direction of flow side walls. Also a segmented series of straight lines Sidewall sections or multi-step transition structures are basically conceivable.
  • the stall structure is attached to the side wall of the flow channel and has a tear-off edge, which is preferably at the flow outlet of the Flow channel is arranged. Upstream to the tear-off edge Flow stall structure on aerodynamically favorable surface parts, which are upstream nestle the side wall of the flow channel.
  • Fig. 1 is a schematic longitudinal section through an inventive trained burner system shown as a connector between the Premix burner 1 and combustion chamber 5 provide a flow channel 10, whose side walls make a gradual transition between the Flow cross-section C1 within the premix burner and the Create combustion chamber cross section C2.
  • the side walls of the flow channel 10 are evenly curved, like a funnel, and allow thus a continuous flow cross-sectional expansion.
  • the re-application point 9 moves upstream in the direction of the Premix burner 1, whereby the slipstream-related dead space 8 is considerable is reduced.
  • the shear layer containing the transverse vertebrae 7 is also significantly shortened trained with considerably weaker vertebrae.
  • FIGS. 2a-c an advantageously designed one is shown in several view variants
  • Flow channel 10 shown which as a single component already in module existing burner systems can be integrated.
  • Fig. 2a shows a view of the flow channel 10 upstream in the direction of Premix burner 1. Immediately at the flow outlet shown in Fig. 2a of the flow channel 10 there are four flow separation structures 11 each associated tear-off edges 12.
  • 2b which shows a perspective oblique view of the flow channel 10
  • the stall structures 11 are more clearly visible in their spatial shape.
  • Flow separation structures 11, which are upstream of the separation edge 12 in each case have aerodynamic surface parts 13 through which the through Flow channel 10 flowing through continuously from the side walls is distracted locally.
  • An actual flow separation takes place along the Tear-off edge 12 of the respective stall structures.
  • 2c is one Sectional view along the section AA shown in Fig. 2a. On the corresponding reference numbers already mentioned will be here directed.
  • the burnout behavior can be arranged symmetrically around the flow channel of a generic burner system can be decisively optimized. at the same time the measure according to the invention serves decisively for damping itself combustion chamber pulsations forming within the burner system.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP02405361A 2001-06-09 2002-05-03 Ensemble brûleur Withdrawn EP1265029A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10128063A DE10128063A1 (de) 2001-06-09 2001-06-09 Brennersystem
DE10128063 2001-06-09

Publications (2)

Publication Number Publication Date
EP1265029A2 true EP1265029A2 (fr) 2002-12-11
EP1265029A3 EP1265029A3 (fr) 2003-11-12

Family

ID=7687770

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02405361A Withdrawn EP1265029A3 (fr) 2001-06-09 2002-05-03 Ensemble brûleur

Country Status (4)

Country Link
US (1) US6572366B2 (fr)
EP (1) EP1265029A3 (fr)
KR (1) KR100850659B1 (fr)
DE (1) DE10128063A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1429075A1 (fr) * 2002-12-04 2004-06-16 Alstom Technology Ltd Système de combustion
EP1975506A1 (fr) * 2007-03-30 2008-10-01 Siemens Aktiengesellschaft Pré-chambre de combustion
US7632472B2 (en) 2003-06-27 2009-12-15 Alstom Technology Ltd. Catalytic reactor and associated operating method
EP2169303A2 (fr) * 2008-09-30 2010-03-31 Alstom Technology Ltd Chambre de combustion de turbine à gaz
EP2420731A1 (fr) * 2010-08-16 2012-02-22 Alstom Technology Ltd Brûleur post-combustion

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007036953B3 (de) * 2007-08-04 2009-04-02 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brenner
EP2116767B1 (fr) 2008-05-09 2015-11-18 Alstom Technology Ltd Brûleur avec lance
EP2496880B1 (fr) 2009-11-07 2018-12-05 Ansaldo Energia Switzerland AG Système d'injection pour brûleur de réchauffage
EP2496885B1 (fr) 2009-11-07 2019-05-29 Ansaldo Energia Switzerland AG Brûleur avec un système de refroidissement permettant d'accroître le rendement d'une turbine à gaz
WO2011054757A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection pour brûleur de réchauffage avec lances à combustible
WO2011054771A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Brûleur à prémélange pour chambre de combustion de turbine à gaz
WO2011054766A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection de brûleur de postcombustion
EP2420730B1 (fr) * 2010-08-16 2018-03-07 Ansaldo Energia IP UK Limited Brûleur de post-combustion
EP2522912B1 (fr) 2011-05-11 2019-03-27 Ansaldo Energia Switzerland AG Redresseur de flux et mélangeur
RU2550370C2 (ru) 2011-05-11 2015-05-10 Альстом Текнолоджи Лтд Центробежная форсунка с выступающими частями
CA2830031C (fr) 2012-10-23 2016-03-15 Alstom Technology Ltd. Bruleur pour chambre de combustion tubulaire unique
EP2725302A1 (fr) 2012-10-25 2014-04-30 Alstom Technology Ltd Agencement de brûleur de postcombustion
EP2728258A1 (fr) * 2012-11-02 2014-05-07 Alstom Technology Ltd Turbine à gaz
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
EP2735798B1 (fr) * 2012-11-23 2020-07-29 IHI Power Systems Co., Ltd. Chambre de combustion de turbine à gaz
EP2837883B1 (fr) 2013-08-16 2018-04-04 Ansaldo Energia Switzerland AG Chambre de combustion tubulaire pré-mélangée ayant des aubes ondulées pour le deuxième étage d'une turbine à gaz séquentielle
EP2933559A1 (fr) 2014-04-16 2015-10-21 Alstom Technology Ltd Agencement de mélange de carburant et chambre de combustion avec un tel agencement
EP3023696B1 (fr) 2014-11-20 2019-08-28 Ansaldo Energia Switzerland AG Lance à lobes pour chambre de combustion d'une turbine à gaz
EP3029378B1 (fr) 2014-12-04 2019-08-28 Ansaldo Energia Switzerland AG Brûleur séquentiel pour une turbine à gaz axiale
EP3354984B1 (fr) 2017-01-31 2020-09-09 Ansaldo Energia Switzerland AG Injecteur à lobes pour une chambre de combustion de turbine à gaz
US11898755B2 (en) 2022-06-08 2024-02-13 General Electric Company Combustor with a variable volume primary zone combustion chamber

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5638682A (en) * 1994-09-23 1997-06-17 General Electric Company Air fuel mixer for gas turbine combustor having slots at downstream end of mixing duct
US5791891A (en) * 1995-09-30 1998-08-11 Abb Research Ltd. Method and device for burning fuels
US5829967A (en) * 1995-03-24 1998-11-03 Asea Brown Boveri Ag Combustion chamber with two-stage combustion
DE19859829A1 (de) * 1998-12-23 2000-06-29 Abb Alstom Power Ch Ag Brenner zum Betrieb eines Wärmeerzeugers
US6152726A (en) * 1998-10-14 2000-11-28 Asea Brown Boveri Ag Burner for operating a heat generator

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0619133B1 (fr) 1993-04-08 1996-11-13 ABB Management AG Chambre de mélanges
CH687831A5 (de) * 1993-04-08 1997-02-28 Asea Brown Boveri Vormischbrenner.
DE59402803D1 (de) 1993-04-08 1997-06-26 Asea Brown Boveri Brennkammer
DE4417538A1 (de) * 1994-05-19 1995-11-23 Abb Management Ag Brennkammer mit Selbstzündung
US5943866A (en) * 1994-10-03 1999-08-31 General Electric Company Dynamically uncoupled low NOx combustor having multiple premixers with axial staging
DE19639301A1 (de) * 1996-09-25 1998-03-26 Abb Research Ltd Brenner zum Betrieb einer Brennkammer
DE19640198A1 (de) * 1996-09-30 1998-04-02 Abb Research Ltd Vormischbrenner
DE19736902A1 (de) * 1997-08-25 1999-03-04 Abb Research Ltd Brenner für einen Wärmeerzeuger
US6141967A (en) * 1998-01-09 2000-11-07 General Electric Company Air fuel mixer for gas turbine combustor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5638682A (en) * 1994-09-23 1997-06-17 General Electric Company Air fuel mixer for gas turbine combustor having slots at downstream end of mixing duct
US5829967A (en) * 1995-03-24 1998-11-03 Asea Brown Boveri Ag Combustion chamber with two-stage combustion
US5791891A (en) * 1995-09-30 1998-08-11 Abb Research Ltd. Method and device for burning fuels
US6152726A (en) * 1998-10-14 2000-11-28 Asea Brown Boveri Ag Burner for operating a heat generator
DE19859829A1 (de) * 1998-12-23 2000-06-29 Abb Alstom Power Ch Ag Brenner zum Betrieb eines Wärmeerzeugers

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1429075A1 (fr) * 2002-12-04 2004-06-16 Alstom Technology Ltd Système de combustion
US7632472B2 (en) 2003-06-27 2009-12-15 Alstom Technology Ltd. Catalytic reactor and associated operating method
EP1975506A1 (fr) * 2007-03-30 2008-10-01 Siemens Aktiengesellschaft Pré-chambre de combustion
WO2008119737A1 (fr) * 2007-03-30 2008-10-09 Siemens Aktiengesellschaft Préchambre de combustion
EP2169303A2 (fr) * 2008-09-30 2010-03-31 Alstom Technology Ltd Chambre de combustion de turbine à gaz
EP2169303A3 (fr) * 2008-09-30 2014-12-24 Alstom Technology Ltd Chambre de combustion de turbine à gaz
EP2420731A1 (fr) * 2010-08-16 2012-02-22 Alstom Technology Ltd Brûleur post-combustion
US9057518B2 (en) 2010-08-16 2015-06-16 Alstom Technology Ltd. Reheat burner

Also Published As

Publication number Publication date
US6572366B2 (en) 2003-06-03
US20020187448A1 (en) 2002-12-12
KR100850659B1 (ko) 2008-08-07
DE10128063A1 (de) 2003-01-23
EP1265029A3 (fr) 2003-11-12
KR20020095094A (ko) 2002-12-20

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