EP0801268A2 - Chambre de combustion pour turbine à gaz - Google Patents

Chambre de combustion pour turbine à gaz Download PDF

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Publication number
EP0801268A2
EP0801268A2 EP97810159A EP97810159A EP0801268A2 EP 0801268 A2 EP0801268 A2 EP 0801268A2 EP 97810159 A EP97810159 A EP 97810159A EP 97810159 A EP97810159 A EP 97810159A EP 0801268 A2 EP0801268 A2 EP 0801268A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
section
mixing section
cross
flow
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
EP97810159A
Other languages
German (de)
English (en)
Other versions
EP0801268A3 (fr
EP0801268B1 (fr
Inventor
Klaus Dr. Döbbeling
Timothy Griffin
Hans Peter Knöpfel
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
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 EP0801268A2 publication Critical patent/EP0801268A2/fr
Publication of EP0801268A3 publication Critical patent/EP0801268A3/fr
Application granted granted Critical
Publication of EP0801268B1 publication Critical patent/EP0801268B1/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
    • 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
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability

Definitions

  • the present invention relates to a combustion chamber according to the preamble of claim 1.
  • Lean-operated premix burners are used in modern combustion chambers of gas turbines in order to minimize the pollutant components, in particular NOx and CO, from the combustion. Basically, it is nowadays assumed that very low NOx emission values, below 10 vppm at 15% 02, must be guaranteed even with very high flame temperatures. In order to achieve such low pollutant emissions when operating a gas turbine over a load range of approx. 40-100%, a perfectly premixed burner must be ensured over a wide flame temperature range, typically approx. 1650-1850 ° K.
  • Such burners are characterized in that, after a conventional air / fuel premixing section, a combustion chamber is connected, the flow cross section of which, over an essentially immediate cross-sectional jump, is a multiple of the exit cross section of the mixing section exceeds. Because of this configuration, outer recirculation zones are formed in the combustion chamber, in the area of the level of this transition, which in themselves induce a stabilization of the premix flame. The stabilizing effect of these recirculation zones with respect to the premixing flame, i.e.
  • the backflow zone formed in the plane of the outlet cross section of the mixing section depends essentially on the extent to which the hot gases from the combustion flow back into these recirculation zones during the course of operation and the supply to a self-igniting or at least there can maintain a stable burning combustion zone.
  • the backflow of the hot gases into the recirculation zones can take place irregularly, so that their effect on the outflowing mixture is prevented.
  • the stabilizing effect on the outflowing mixture that comes from the recirculation zones is lost, which can result in extremely damaging flame extinguishing and deflagrations.
  • the invention seeks to remedy this.
  • the invention is based on the object of proposing measures in a combustion chamber of the type mentioned at the outset, which ensure effective combustion-related stabilization of the premixing flame over the course of the entire operation over all load ranges.
  • part of the air / fuel mixture formed here is branched off and mixed into the outer recirculation zones.
  • the location of this interference is chosen so that complete mixing of that part of the branched mixture within the outer Recirculation zones with the recirculating hot gas flow from the combustion within the combustion chamber are reached before the outer recirculation zones come into contact with the remaining part of the air / fuel mixture from the mixing section.
  • the result of this is that an advantageous mixture ratio of air / fuel mixture and hot gas is established in the recirculation zones, and the branched-off air / fuel mixture in the manner of a self-igniting pilot flame significantly improves the stability of the flame front.
  • the division of the air / fuel mixture from the mixing section into a main flow and a secondary flow divided into small partial flows results in a greatly increased contact area between the air / fuel mixture and recirculating hot gas within the combustion chamber.
  • the total cross-sectional area of the main and secondary flow of the air / fuel mixture is kept approximately constant. This is achieved by providing a small contraction at the end of the mixing section.
  • the number of branches for the partial flow, the respective flow cross-section and the flow guidance are influenced to the appropriate extent.
  • the reason for the advantage under a) is to be seen in the fact that, compared to a conventional mixture by shear layers between the air / fuel mixture and recirculating hot gas, which leads to a maximum of the probability density distribution of the volume ratio between the two media mentioned at approximately 50%, the inventive addition of the air / fuel mixture into the outer recirculation zones ensures such an approx. 30%. Measurements of the correlated autoignition times for the different probability density distributions for the different media have shown that a distribution with a maximum at 30% air / fuel mixture within the outer recirculation zones results in an ignition delay time that is an order of magnitude shorter than that with one Distribution with a maximum at 50%.
  • the only figure shows a combustion chamber, the final phase of a mixing section with a subsequent combustion chamber.
  • the figure shows, as can be seen from the schematically drawn shaft axis 15, a combustion chamber designed as an annular combustion chamber 1, which essentially consists of a coherent annular or quasi-annular cylinder.
  • the combustion chamber can, however, also consist of a number of combustion chambers which are arranged axially, quasi-axially or helically about the said axis and are individually self-contained.
  • a combustion chamber consisting of a single combustion chamber in the form shown is also possible.
  • the present annular combustion chamber 1 is arranged downstream of a mixing section 2, wherein this mixing section can easily be part of a premix burner, as described, for example, in EP-0 321 809 B1. This publication is therefore declared an integral part of this description.
  • the mixing section 2 shown in the figure can be part of a mixing tube which acts, for example, downstream of the premixing burner mentioned.
  • this mixing section 2 in the narrower or broader sense, it is about the formation of an air / fuel mixture for the subsequent combustion in such a way that this combustion then takes place with minimized pollutant emissions, in particular as far as the NOx emissions are concerned.
  • a combustion chamber 3 connects to the end of the mixing section 2, such that the transition between the two flow sections is formed by a radial cross-sectional jump 5, which initially induces the flow cross section of the combustion chamber 3, this flow cross section being 2-10 times the outlet cross section of the mixing section 2 is.
  • a part 9 of the entire air / fuel mixture 8 is branched off at the transition of the mixing section 2 into the combustion chamber 3 and mixed into the outer recirculation zones 10.
  • This branched-off part 9 of preferably 10-30% of the entire mixture 8 is introduced via flow channels 4 into the outer recirculation zones 10 mentioned, the location of the intermixing being selected such that it is completely mixed with a recirculating hot gas 17 in the region of the vortex separations 11 is reached before the outer recirculation zones 10 come into contact with the main stream 16 of the air / fuel mixture 8.
  • the diameter of the Flow channels 4 which run approximately at an angle of 30-60 °, preferably 45 °, with respect to the shaft axis 15 so that they run approximately parallel to the wall flow lines of the swirl flow, are 3-8%, preferably 5% of the hydraulic diameter the mixing section 2.
  • the number of flow channels 4 results from the mass flow ratio between the main flow and the secondary flow of the air / fuel mixture, the mass flow ratio roughly corresponding to the area ratio of the two flows.
  • the distance between the flow channels 4 and the mixing section is preferably approximately 10% of the hydraulic diameter of the mixing section 2.
  • the air / fuel mixture 9 via the flow channels 4 can be enriched with an additional fuel 6, for example by means of a ring line 19 provided with bores 18
  • the aforementioned fuel 6 is introduced into each flow channel 4, as a result of which a reinforced and safe pilot flame then acts in the outer recirculation zones 10, with the result that a lower lean extinguishing limit can be targeted even in the transient areas with minimized pollutant emissions, accordingly the operating range of lean premix burners can also be extended to load ranges below 40%.
  • the hot gases 13 act on a downstream turbine 14, which is not shown in detail, it being possible for the combustion chamber 1 shown here to be easily arranged on the low-pressure side of a gas turbine group based on sequential combustion and can be operated using an auto-ignition method.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)
EP97810159A 1996-04-09 1997-03-18 Méthode d'exploitation d'une chambre de combustion pour turbine à gaz Expired - Lifetime EP0801268B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19614001A DE19614001A1 (de) 1996-04-09 1996-04-09 Brennkammer
DE19614001 1996-04-09

Publications (3)

Publication Number Publication Date
EP0801268A2 true EP0801268A2 (fr) 1997-10-15
EP0801268A3 EP0801268A3 (fr) 1999-07-14
EP0801268B1 EP0801268B1 (fr) 2003-12-10

Family

ID=7790796

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810159A Expired - Lifetime EP0801268B1 (fr) 1996-04-09 1997-03-18 Méthode d'exploitation d'une chambre de combustion pour turbine à gaz

Country Status (5)

Country Link
US (1) US5885068A (fr)
EP (1) EP0801268B1 (fr)
JP (1) JP3907779B2 (fr)
CN (1) CN1165937A (fr)
DE (2) DE19614001A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0985882A1 (fr) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Amortissement des vibrations dans des combusteurs
EP0994300A1 (fr) * 1998-10-14 2000-04-19 Abb Research Ltd. Brûleur pour la conduite d'un générateur de chaleur
WO2010079276A1 (fr) 2009-01-08 2010-07-15 Augier Procede et systeme de transmission de l'energie electrique
US8057224B2 (en) * 2004-12-23 2011-11-15 Alstom Technology Ltd. Premix burner with mixing section
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19855034A1 (de) * 1998-11-28 2000-05-31 Abb Patent Gmbh Verfahren zum Beschicken eines Brenners für Gasturbinen mit Pilotgas
US6286298B1 (en) * 1998-12-18 2001-09-11 General Electric Company Apparatus and method for rich-quench-lean (RQL) concept in a gas turbine engine combustor having trapped vortex cavity
US6295801B1 (en) * 1998-12-18 2001-10-02 General Electric Company Fuel injector bar for gas turbine engine combustor having trapped vortex cavity
DE10297365B4 (de) * 2001-10-26 2017-06-22 General Electric Technology Gmbh Gasturbine
AU2003240374A1 (en) * 2002-08-30 2004-03-19 Alstom Technology Ltd Hybrid burner and corresponding operating method
ITMI20032621A1 (it) * 2003-12-30 2005-06-30 Nuovo Pignone Spa Sistema di combustione a basse emissioni inquinanti
US20060107667A1 (en) * 2004-11-22 2006-05-25 Haynes Joel M Trapped vortex combustor cavity manifold for gas turbine engine
US20070204624A1 (en) * 2006-03-01 2007-09-06 Smith Kenneth O Fuel injector for a turbine engine
DE102006041955A1 (de) * 2006-08-30 2008-03-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren zur Steuerung der Verbrennung in einer Brennkammer und Brennkammervorrichtung
EP1950494A1 (fr) * 2007-01-29 2008-07-30 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
EP2107312A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Chambre de combustion pilote dans un brûleur
CN101776283B (zh) * 2009-01-13 2012-06-20 北京航空航天大学 带射流注入的火焰稳定装置
CN102877984B (zh) * 2012-10-24 2014-12-03 北京航空航天大学 一种带前缘气缝结构的超燃冲压发动机火焰稳定装置
EP2889542B1 (fr) * 2013-12-24 2019-11-13 Ansaldo Energia Switzerland AG Procédé pour le fonctionnement d'une chambre de combustion pour turbine à gaz et chambre de combustion
CN104566460A (zh) * 2014-12-26 2015-04-29 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种具有突扩通道的燃料空气混合器
CN108006695B (zh) * 2016-11-01 2019-12-06 北京华清燃气轮机与煤气化联合循环工程技术有限公司 优化用于燃气轮机的预混合燃料喷嘴的方法
FR3099546B1 (fr) * 2019-07-29 2021-08-06 Safran Aircraft Engines Chambre de combustion comportant des systèmes d'injection secondaires injectant de l'air et du carburant directement dans des zones de recirculation de coin, turbomachine la comprenant, et procédé d'alimentation en carburant de celle-ci
CN112128975B (zh) * 2020-09-25 2021-11-09 郑州釜鼎热能技术有限公司 一种空煤气上喷卷吸高温烟气蓄热体中燃烧与传热的热风炉
CN112984500B (zh) * 2021-01-27 2022-12-06 杭州聚能环保科技股份有限公司 一种卧式单炉胆煤粉锅炉
CN113279857B (zh) * 2021-05-27 2022-03-15 中国科学院工程热物理研究所 一种适用于无人飞行器的高推重比燃气涡轮发生器

Citations (6)

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Publication number Priority date Publication date Assignee Title
US3879939A (en) * 1973-04-18 1975-04-29 United Aircraft Corp Combustion inlet diffuser employing boundary layer flow straightening vanes
US4062182A (en) * 1974-12-21 1977-12-13 Mtu Motoren-Und Turbinen-Union Gmbh Combustion chamber for gas turbine engines
US4488869A (en) * 1982-07-06 1984-12-18 Coen Company, Inc. High efficiency, low NOX emitting, staged combustion burner
US5359847A (en) * 1993-06-01 1994-11-01 Westinghouse Electric Corporation Dual fuel ultra-low NOX combustor
DE4426351A1 (de) * 1994-07-25 1996-02-01 Abb Research Ltd Brennkammer
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

Family Cites Families (4)

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US4395223A (en) * 1978-06-09 1983-07-26 Hitachi Shipbuilding & Engineering Co., Ltd. Multi-stage combustion method for inhibiting formation of nitrogen oxides
JPS6057131A (ja) * 1983-09-08 1985-04-02 Hitachi Ltd ガスタ−ビン燃焼器の燃料供給方法
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
DE4408136A1 (de) * 1994-03-10 1995-09-14 Bmw Rolls Royce Gmbh Verfahren und Vorrichtung zur Kraftstoff-Aufbereitung für eine Gasturbinen-Brennkammer

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3879939A (en) * 1973-04-18 1975-04-29 United Aircraft Corp Combustion inlet diffuser employing boundary layer flow straightening vanes
US4062182A (en) * 1974-12-21 1977-12-13 Mtu Motoren-Und Turbinen-Union Gmbh Combustion chamber for gas turbine engines
US4488869A (en) * 1982-07-06 1984-12-18 Coen Company, Inc. High efficiency, low NOX emitting, staged combustion burner
US5359847A (en) * 1993-06-01 1994-11-01 Westinghouse Electric Corporation Dual fuel ultra-low NOX combustor
US5359847B1 (en) * 1993-06-01 1996-04-09 Westinghouse Electric Corp Dual fuel ultra-flow nox combustor
DE4426351A1 (de) * 1994-07-25 1996-02-01 Abb Research Ltd Brennkammer
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

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0985882A1 (fr) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Amortissement des vibrations dans des combusteurs
US6430933B1 (en) 1998-09-10 2002-08-13 Alstom Oscillation attenuation in combustors
EP0994300A1 (fr) * 1998-10-14 2000-04-19 Abb Research Ltd. Brûleur pour la conduite d'un générateur de chaleur
US6152726A (en) * 1998-10-14 2000-11-28 Asea Brown Boveri Ag Burner for operating a heat generator
US8057224B2 (en) * 2004-12-23 2011-11-15 Alstom Technology Ltd. Premix burner with mixing section
WO2010079276A1 (fr) 2009-01-08 2010-07-15 Augier Procede et systeme de transmission de l'energie electrique
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

Also Published As

Publication number Publication date
DE59711087D1 (de) 2004-01-22
EP0801268A3 (fr) 1999-07-14
JP3907779B2 (ja) 2007-04-18
EP0801268B1 (fr) 2003-12-10
CN1165937A (zh) 1997-11-26
DE19614001A1 (de) 1997-10-16
US5885068A (en) 1999-03-23
JPH1038275A (ja) 1998-02-13

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