EP0833105A2 - Brûleur à prémélange - Google Patents

Brûleur à prémélange Download PDF

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Publication number
EP0833105A2
EP0833105A2 EP97810622A EP97810622A EP0833105A2 EP 0833105 A2 EP0833105 A2 EP 0833105A2 EP 97810622 A EP97810622 A EP 97810622A EP 97810622 A EP97810622 A EP 97810622A EP 0833105 A2 EP0833105 A2 EP 0833105A2
Authority
EP
European Patent Office
Prior art keywords
premix burner
burner according
flow
interior
mixing tube
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
EP97810622A
Other languages
German (de)
English (en)
Other versions
EP0833105B1 (fr
EP0833105A3 (fr
Inventor
Hans Peter Knöpfel
Giacomo F. Bolis
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 Switzerland GmbH
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 EP0833105A2 publication Critical patent/EP0833105A2/fr
Publication of EP0833105A3 publication Critical patent/EP0833105A3/fr
Application granted granted Critical
Publication of EP0833105B1 publication Critical patent/EP0833105B1/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
    • 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
    • F23D2209/00—Safety arrangements
    • F23D2209/10—Flame flashback

Definitions

  • the present invention relates to a premix burner according to the preamble of claim 1.
  • Lean premixed combustion is a common procedure to achieve low pollutant emissions, in particular Nitrogen oxide emissions when burning fuels with a low content of nitrogen compounds. From publications has become known that with experimental burners by improving the mixing quality of air and fuel a further reduction in nitrogen oxide emissions, in particular when burning under high pressure like this The latest generation of gas turbines is possible. A transfer of such experimental burners to machine technology is however not easily possible because here high demands regarding flame stabilization and Pre-ignition safety exists. Conventional spin-stabilized and machine-compatible premix burners mix the fuel into the combustion air just before the flame zone.
  • a burner which in consists essentially of a cylindrical chamber, which in turn has several tangentially arranged slots, through which the combustion air inside the chamber flows.
  • these slots at the transition to the interior the chamber, act in the axial direction a number of Fuel nozzles, through which preferably a gaseous Fuel mixed with the combustion air flowing through there becomes.
  • the interior of the chamber is also with provided a conical body, which is in the direction of flow tapered, being conical in the area of the tip Body more fuel nozzles for one preferably liquid fuel are provided. Downstream of the The cone tip of this body becomes the combustion air for ignition brought. Around the flame outside the premixing section To keep the burner stable, the flow in the chamber must resp.
  • Premix section itself should be supercritical, i.e. the Twist count must be so small here that there is no vortex burst is coming.
  • the critical swirl number can be Reach three parameters in the right place: Through a change the width of the tangential slots, and on the other hand by adjusting the angle of the tapered body in the Interior of the chamber as well as by adding a central one Support air, be it swirled or unswirled. Through the Fuel injection in the area of the slots are in their Interpretation but very limited. In addition, leaves optimal homogeneous mixing of air and fuel not reach immediately, this applies in particular to those fuel injections that are at the end of the burner are located in the immediate area of the Flame front are located, with which this proximity also a there is a latent risk of reignition. Furthermore, the both gaseous as well as liquid fuel due to the short Distance between injection to flame not good with the Air mixes, which results in local fat zones in the Flames result in high NOx emissions and higher Cause pulsations.
  • the invention seeks to remedy this.
  • the invention how it is characterized in the claims, the task lies the basis for a premix burner of the type mentioned Art to remedy the disadvantages mentioned above.
  • the flow at the exit of the swirl generator is chosen so is that there is no vortex burst. That the Swirl generator downstream mixing tube ensures that the Flame zone is shifted further downstream and that Air / fuel mixture better mixed.
  • An exit radius with a tear-off edge which is on the combustion chamber side is attached in the burner front, ensures by an enlargement of the backflow bladder to strengthen the Flame zone and thus better flame stability.
  • the size of the radius depends on the flow inside the mixing tube from. It is chosen so that the flow adjusts to the Applies to the wall and thus the swirl number increases sharply. Across from In a flow without a radius, the backflow bubble now increases tremendous, which maximizes stabilization of the Flame front causes.
  • Another advantage of the invention is that the enlargement of the backflow bubble by others Measures can be achieved within the burner front, preferably due to toroidal recesses in the burner front.
  • FIG. 1 To better understand the structure of the premix burner, is it is advantageous if at the same time as FIG. 1 and FIG. 2 is used. Furthermore, not unnecessary to Fig. 1 The tangential air supply ducts are to be confusing has only been shown schematically. Hereinafter 1 is referred to FIG. 2 pointed out.
  • the swirl generator 10 consists of two hollow partial shells 11, 12 which are nested in one another offset from one another (cf. FIG. 2). .
  • the offset of the respective central axis or longitudinal axis of symmetry 11b, 12b (see FIG. 2) to one another creates a tangential air inlet duct 11a, 12a on both sides, in a mirror-image arrangement, through which a combustion air 16 or a fuel / air mixture into one flows from the partial shells 11, 12 formed interior 18.
  • Said longitudinal symmetry axes preferably run parallel to one another, whereupon the tangential air inlet ducts 11a, 12a have a constant flow cross section. If necessary, the flow cross-section in the axial direction can be regularly or irregularly reduced or increased by a corresponding course of the longitudinal symmetry axes.
  • the shells 11, 12 themselves are preferably cylindrical in the direction of flow. However, they can have a different geometrical configuration which directly induce the flow cross section of the interior 18.
  • the shells 11, 12 can be designed as a Venturi tube.
  • the design options mentioned are not shown in detail in the drawing, since they can be easily understood by the person skilled in the art.
  • the number of shells that form the swirl generator 10 they are not limited to two, as can be seen from the exemplary embodiment.
  • a larger number of tangentially arranged air inlet ducts is easily possible depending on the operation.
  • the individual shells arranged offset from one another can easily be replaced by a coherent tube, the tube wall of which is provided with tangentially arranged slots which then form the tangential air inflow channels.
  • a conical inner body 13 is arranged in the interior 18, which tapers in the direction of flow and tapers out largely in a tip shape.
  • the conical configuration of this inner body 13, which has approximately the length of the tangential air inlet ducts, is not limited to the shape shown: An outer shape of this inner body 13 as a diffuser or confuser is also possible.
  • the measure for the design of this inner body 13 in interdependency with the tangentially flowing combustion air 16 is the achievement of a certain number of swirls at the output of the swirl generator.
  • the inner body 13 has a central bore 19 through which a fuel lance 14 is passed, which in turn extends to approximately the tip of the inner body.
  • a liquid fuel is preferably introduced through this fuel lance 14, the injection into the interior 18 via a fuel nozzle 17, which generates a fuel spray angle indicated for operation.
  • This fuel nozzle 17 thus forms the actual head stage of the premix burner.
  • the fuel lance 14 is encased with a supporting air 15, which triggers at least one axial pulse to stabilize the flame front 30 that forms in the combustion chamber 30.
  • this supporting air 15 contributes to enhancing the optimization of the premixing process, in particular the local stabilization of the flame front, whereby this supporting air can also be enriched by a partial amount of a recirculated exhaust gas.
  • This support air can also be replaced by another air / fuel mixture. So that a backflow bubble cannot form at the end of the swirl generator 10, it is important that the swirl formed by the tangential flow remains subcritical. This can be achieved by various measures, one of which relates to the flow cross section of the tangential air inlet ducts 11a, 12a, another is directed to the number of these ducts, the conical shape of the inner body 13 playing an interdependent role with the measures mentioned.
  • the swirl flow consisting of an air / fuel mixture 23 therefore flows into a backflow zone without formation a downstream of the swirl generator 10 connected Mixing section 20, which essentially consists of a mixing tube 21 exists.
  • This mixing tube 21 fulfills the condition that a defined mixture downstream of the swirl generator 10 is provided in which a perfect premix of A wide variety of fuels is achieved.
  • the mixing tube 21, i.e. its length also enables lossless Flow guidance, this being a pronounced maximum of the axial velocity profile on the axis 24, so that the flame does not reignite from the combustion chamber 30 is possible.
  • the axial velocity to the wall of the mixing tube 21 drops.
  • the mixing tube 21 is in flow and circumferential direction with a number of regular or irregular distributed flow openings 22 which are different are designed in cross-section and flow direction.
  • This flow openings 22 flows an amount of air into the Inside of the mixing tube, and along the inside wall in the sense a filming an increase in the axial speed prevailing there induce and the mixture in this Lean area.
  • Another configuration around the same To achieve effect is to cross-section the Mixing tube 21 to be provided with a constriction, whereby the total speed level within this flow path is increased.
  • the flow openings are in the figure 22 formed as bores, which point under a Angle with respect to the burner axis 24. If someone the precautions taken when guiding the swirl flow 23 along the mixing tube 21 an intolerable Loss of pressure causes a remedy be by a at the end of the mixing tube 21 in the figure not visible diffuser is provided.
  • the combustion chamber 30 closes at the end of the mixing tube 21 , which is indicated schematically by a flame tube 31, the transition between the two flow cross sections is characterized by a cross-sectional jump.
  • This The transition is further made by a front wall 25 formed, which is arranged on the front side of the combustion chamber and has a number of openings through which an amount of air flows directly into the edge zones of the cross-sectional jump.
  • a flow Edge zone in which by the predominant there This leads to negative pressure vortex detachments to a strengthened ring stabilization of the backflow zone 32.
  • FIG. 2 shows the configuration in a schematic representation the nested partial shells 11, 12.
  • these partial shells are also mutually above this level movable, i.e. it is easily possible to have one Overlap of these in the area of the tangential air inlet slots 11a, 12a to accomplish.
  • the partial shells 11, 12 by an opposing to interleave rotating movement in a spiral. This allows the shape and size of the tangential Vary air inlet slots lla, 12a so that the swirl number and swirl strength from the swirl generator 10 each Conditions can be adjusted.
  • the tangential air inlet slots lla, 12a each form the outlet opening a feed channel, not shown in detail.
  • FIG. 3 shows the tear-off edge A already mentioned, which is formed in the front wall 25.
  • transitional transition radius R At the end of the flow cross section of the mixing tube 21 is in the front wall 25 transitional transition radius R provided, its size basically from the flow within the mixing tube 21 depends.
  • This radius R is chosen so that the flow lays against the wall and the swirl number increases sharply leaves.
  • the size of the radius R can be quantified in this way define that this is> 10% of the flow diameter d of the mixing tube 21.
  • Opposite a current without Radius now increases the backflow zone enormously. This Radius extends to the outlet level of the mixing tube 21, the arc angle ⁇ between the beginning and end of the Curvature is ⁇ 90 °.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Spray-Type Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
EP97810622A 1996-09-30 1997-09-02 Brûleur à prémélange Expired - Lifetime EP0833105B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19640198 1996-09-30
DE19640198A DE19640198A1 (de) 1996-09-30 1996-09-30 Vormischbrenner

Publications (3)

Publication Number Publication Date
EP0833105A2 true EP0833105A2 (fr) 1998-04-01
EP0833105A3 EP0833105A3 (fr) 1998-10-21
EP0833105B1 EP0833105B1 (fr) 2003-03-19

Family

ID=7807366

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810622A Expired - Lifetime EP0833105B1 (fr) 1996-09-30 1997-09-02 Brûleur à prémélange

Country Status (5)

Country Link
US (1) US6126439A (fr)
EP (1) EP0833105B1 (fr)
JP (1) JP3904685B2 (fr)
CN (1) CN1115515C (fr)
DE (2) DE19640198A1 (fr)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1213541A1 (fr) * 2000-12-11 2002-06-12 ALSTOM Power N.V. Brûleur à prémélange avec combustion catalytique et procédé de fonctionnement
EP1255077A2 (fr) 2001-04-30 2002-11-06 ALSTOM (Switzerland) Ltd Dispositif pour la combustion d'un mélange gazeux de combustible et comburant
US6609905B2 (en) 2001-04-30 2003-08-26 Alstom (Switzerland) Ltd. Catalytic burner
US6672863B2 (en) 2001-06-01 2004-01-06 Alstom Technology Ltd Burner with exhaust gas recirculation
US7241138B2 (en) 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
WO2007115989A1 (fr) * 2006-04-07 2007-10-18 Siemens Aktiengesellschaft Bruleur de turbine a gaz
EP2058590A1 (fr) * 2007-11-09 2009-05-13 ALSTOM Technology Ltd Procédé de fonctionnement d'un brûleur
WO2009068425A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Brûleur à prémélange pour une turbine à gaz
WO2009068424A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Procédé et dispositif pour la combustion d'hydrogène dans un brûleur à prémélange
WO2009109454A1 (fr) * 2008-03-07 2009-09-11 Alstom Technology Ltd Procédé et ensemble brûleur servant à produire du gaz chaud et utilisation dudit procédé
WO2009109452A1 (fr) * 2008-03-07 2009-09-11 Alstom Technology Ltd Ensemble brûleur et son utilisation
WO2009109448A1 (fr) * 2008-03-07 2009-09-11 Alstom Technology Ltd Ensemble brûleur et son utilisation
EP2299178A1 (fr) * 2009-09-17 2011-03-23 Alstom Technology Ltd Procédé et système de combustion de turbine à gaz pour mélanger sans danger des carburants riches en H2 avec de l'air
EP2735798A1 (fr) * 2012-11-23 2014-05-28 Niigata Power Systems Co., Ltd. Chambre de combustion de 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
EP2179222B2 (fr) † 2007-08-07 2021-12-01 Ansaldo Energia IP UK Limited Brûleur pour une chambre de combustion d'un turbogroupe

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6672862B2 (en) 2000-03-24 2004-01-06 North American Manufacturing Company Premix burner with integral mixers and supplementary burner system
DE10050248A1 (de) 2000-10-11 2002-04-18 Alstom Switzerland Ltd Brenner
DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
DE10128063A1 (de) * 2001-06-09 2003-01-23 Alstom Switzerland Ltd Brennersystem
DE10233161B4 (de) * 2002-07-22 2012-01-05 Alstom Technology Ltd. Brenner und Pilotbrenner
AU2003240374A1 (en) * 2002-08-30 2004-03-19 Alstom Technology Ltd Hybrid burner and corresponding operating method
DE10329162A1 (de) * 2003-06-27 2005-01-13 Alstom Technology Ltd Katalytischer Reaktor und zugehöriges Betriebsverfahren
JP4913746B2 (ja) * 2004-11-30 2012-04-11 アルストム テクノロジー リミテッド 予混合バーナー内の水素を燃焼する方法及び装置
EP2041494B8 (fr) * 2005-12-14 2015-05-27 Industrial Turbine Company (UK) Limited Injecteurs de prémélange de turbine à gaz
US7628606B1 (en) * 2008-05-19 2009-12-08 Browning James A Method and apparatus for combusting fuel employing vortex stabilization
EP2650612A1 (fr) * 2012-04-10 2013-10-16 Siemens Aktiengesellschaft Brûleur
EP2703721B1 (fr) * 2012-08-31 2019-05-22 Ansaldo Energia IP UK Limited Brûleur à prémélange
CN104406414B (zh) * 2014-10-27 2016-06-22 云南铜业科技发展股份有限公司 一种浸没式管束混合顶吹喷枪
DE102018121946A1 (de) * 2018-09-07 2020-03-12 Andreas Dequis Feuerungseinrichtung
DE202018006638U1 (de) 2018-09-07 2021-09-29 Andreas Dequis Feuerungseinrichtung
CN114772698B (zh) * 2022-03-31 2024-01-05 深圳市华尔信环保科技有限公司 一种有机废液超临界水氧化系统
WO2024047123A1 (fr) * 2022-08-30 2024-03-07 Katholieke Universiteit Leuven Réacteur à effet tourbillonnaire

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EP0321809A1 (fr) 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
WO1993017279A1 (fr) 1992-02-26 1993-09-02 United Technologies Corporation Bruleur de gaz a premelange

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US4271675A (en) * 1977-10-21 1981-06-09 Rolls-Royce Limited Combustion apparatus for gas turbine engines
FR2698156B1 (fr) * 1992-11-16 1995-01-27 Rhone Poulenc Chimie Procédé de traitement thermique d'un effluent comprenant des matières organiques polluantes ou un composé inorganique.
GB9326367D0 (en) * 1993-12-23 1994-02-23 Rolls Royce Plc Fuel injection apparatus
JPH07190308A (ja) * 1993-12-28 1995-07-28 Hitachi Ltd 旋回型バーナ
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner
DE19545026A1 (de) * 1995-12-02 1997-06-05 Abb Research Ltd Vormischbrenner
DE19547912A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809A1 (fr) 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
WO1993017279A1 (fr) 1992-02-26 1993-09-02 United Technologies Corporation Bruleur de gaz a premelange

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6625988B2 (en) 2000-12-11 2003-09-30 Alstom (Switzerland) Ltd Premix burner arrangement with catalytic combustion and method for its operation
EP1213541A1 (fr) * 2000-12-11 2002-06-12 ALSTOM Power N.V. Brûleur à prémélange avec combustion catalytique et procédé de fonctionnement
US6638055B2 (en) 2001-04-30 2003-10-28 Alstom (Switzerland) Ltd Device for burning a gaseous fuel/oxidant mixture
US6609905B2 (en) 2001-04-30 2003-08-26 Alstom (Switzerland) Ltd. Catalytic burner
EP1255077A2 (fr) 2001-04-30 2002-11-06 ALSTOM (Switzerland) Ltd Dispositif pour la combustion d'un mélange gazeux de combustible et comburant
US6672863B2 (en) 2001-06-01 2004-01-06 Alstom Technology Ltd Burner with exhaust gas recirculation
US7241138B2 (en) 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
WO2007115989A1 (fr) * 2006-04-07 2007-10-18 Siemens Aktiengesellschaft Bruleur de turbine a gaz
US8596074B2 (en) 2006-04-07 2013-12-03 Siemens Aktiengesellschaft Gas turbine combustor
EP2179222B2 (fr) † 2007-08-07 2021-12-01 Ansaldo Energia IP UK Limited Brûleur pour une chambre de combustion d'un turbogroupe
EP2058590A1 (fr) * 2007-11-09 2009-05-13 ALSTOM Technology Ltd Procédé de fonctionnement d'un brûleur
US9103547B2 (en) 2007-11-09 2015-08-11 Alstom Technology Ltd Method for operating a burner
WO2009068425A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Brûleur à prémélange pour une turbine à gaz
WO2009068424A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Procédé et dispositif pour la combustion d'hydrogène dans un brûleur à prémélange
US8033821B2 (en) 2007-11-27 2011-10-11 Alstom Technology Ltd. Premix burner for a gas turbine
US8066509B2 (en) 2007-11-27 2011-11-29 Alstom Technology Ltd. Method and device for combusting hydrogen in a premix burner
WO2009109452A1 (fr) * 2008-03-07 2009-09-11 Alstom Technology Ltd Ensemble brûleur et son utilisation
US8459985B2 (en) 2008-03-07 2013-06-11 Alstom Technology Ltd Method and burner arrangement for the production of hot gas, and use of said method
US8468833B2 (en) 2008-03-07 2013-06-25 Alstom Technology Ltd Burner arrangement, and use of such a burner arrangement
WO2009109448A1 (fr) * 2008-03-07 2009-09-11 Alstom Technology Ltd Ensemble brûleur et son utilisation
WO2009109454A1 (fr) * 2008-03-07 2009-09-11 Alstom Technology Ltd Procédé et ensemble brûleur servant à produire du gaz chaud et utilisation dudit procédé
WO2011032839A1 (fr) * 2009-09-17 2011-03-24 Alstom Technology Ltd Procédé et système de combustion de turbine à gaz pour mélanger de manière sûre des combustibles riches en h2 avec de l'air
EP2299178A1 (fr) * 2009-09-17 2011-03-23 Alstom Technology Ltd Procédé et système de combustion de turbine à gaz pour mélanger sans danger des carburants riches en H2 avec de l'air
US10208958B2 (en) 2009-09-17 2019-02-19 Ansaldo Energia Switzerland AG Method and gas turbine combustion system for safely mixing H2-rich fuels with air
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
EP2735798A1 (fr) * 2012-11-23 2014-05-28 Niigata Power Systems Co., Ltd. Chambre de combustion de turbine à gaz

Also Published As

Publication number Publication date
JPH10110912A (ja) 1998-04-28
CN1115515C (zh) 2003-07-23
CN1185561A (zh) 1998-06-24
DE59709549D1 (de) 2003-04-24
EP0833105B1 (fr) 2003-03-19
EP0833105A3 (fr) 1998-10-21
JP3904685B2 (ja) 2007-04-11
US6126439A (en) 2000-10-03
DE19640198A1 (de) 1998-04-02

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