EP1484553A2 - Brûleur pour une chambre de combustion de turbine à gaz - Google Patents

Brûleur pour une chambre de combustion de turbine à gaz Download PDF

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Publication number
EP1484553A2
EP1484553A2 EP04090216A EP04090216A EP1484553A2 EP 1484553 A2 EP1484553 A2 EP 1484553A2 EP 04090216 A EP04090216 A EP 04090216A EP 04090216 A EP04090216 A EP 04090216A EP 1484553 A2 EP1484553 A2 EP 1484553A2
Authority
EP
European Patent Office
Prior art keywords
burner
air
ring
burner according
gas turbine
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
EP04090216A
Other languages
German (de)
English (en)
Other versions
EP1484553A3 (fr
EP1484553B1 (fr
Inventor
Ralf Sebastian Von Der Bank
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1484553A2 publication Critical patent/EP1484553A2/fr
Publication of EP1484553A3 publication Critical patent/EP1484553A3/fr
Application granted granted Critical
Publication of EP1484553B1 publication Critical patent/EP1484553B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • 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
    • F23D2209/00—Safety arrangements
    • F23D2209/20—Flame lift-off / stability
    • 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
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • 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
    • F23D2900/00018—Means for protecting parts of the burner, e.g. ceramic lining outside of the flame tube

Definitions

  • the invention relates to a burner for a gas turbine combustor, in particular for an aircraft gas turbine, the a lean premix burner with centrically integrated support burner includes.
  • Magervormischbrennern known to be an ignition or support burner associated with the case of an air-fuel mixture with higher fuel content (rich mixture) a high combustion temperature is generated to that of the lean burn burner or main burner produced lean, a low Combustion temperature supplying air-fuel mixture, too at low air temperature and correspondingly unfavorable To ignite the evaporation behavior of the liquid fuel and to ensure the flame stability.
  • combustion chamber is for lean premix burners trained with support measures, each master / lean burn burner in a lateral gradation respectively a support burner is assigned separately. Except for the complicated construction, the high number of parts, the high Manufacturing costs and high weight, is also the cooling the large surfaces associated with a considerable effort.
  • combustion chamber concepts are commonly referred to as “axially staged combustion chambers” or “double-annealed combustion chambers” designated.
  • a burner combination of the type mentioned above, the one Main burner and one in this centric integrated Supporting burner has, for example, in EP 0 660 038 B1 described.
  • This burner includes a main burner with an annular outer fuel-air mixing duct for generating a to be introduced into the combustion chamber Fuel-air mixture and one in an axially extending Channel of a central body trained, that is centrically mounted in the main burner support burner, sprayed at the discharge fuel and with a Core air mixed in the gas turbine combustor registered becomes.
  • a stable flame training in every operating condition can not be achieved with this burner design.
  • the invention is based on the object, a burner of be formed in the way mentioned above that over the entire Operating range of a gas turbine engine a stable Flame formation in the combustion chamber and one at any time safe function of the gas turbine is guaranteed.
  • the basic idea of the invention is a lean premix burner supplied via a main air ring channel lean air-fuel mixture and one in the lean premix burner centrically integrated support burner with a surrounded by the main air ring channel core air ring channel and a arranged at the outflow atomizer for fuel in that in the contiguous Mouth area of the concentrically arranged annular channels flame stabilizing ring highly heated by the combustion process is arranged, the Heilleitflanken the Main air-fuel mixture to the outside and the core air flow to lead inwards.
  • the flame stabilizing ring By the one with the hot flame stabilizing ring generated gas flow forms one of the Flame stabilizing ring outgoing hot, about hollow cylindrical to barrel-shaped, stationary recirculation zone or hot gas zone, which together with the stabilizing ring acts as an ignition element and in which of the Support burner discharged fuel and completely absorbed is burned.
  • the flame stabilizing ring manages, in every operating condition one with a lean premix burner and integrated support burner Equipped gas turbine, and also by external Conditions of reduced air temperature, a stable, not to provide extinguishing flame and thus the To ensure functional safety of the gas turbine engine.
  • the Flame stabilization ring designed as a cone ring, the one enclosed by two legs, towards the combustion chamber having open groove.
  • the legs form at the to Burner side facing the leading edges for the inside flowing core air or the outward flowing air-fuel mixture.
  • the groove or the legs of the conical ring whose required cooling guaranteed against overheating. The cooling takes place at the Heilleitflanken the relatively thin-walled legs of Flame stabilizing ring with the supplied core air or main air.
  • the cone ring (Flame stabilizing ring) made of a heat-resistant or heat-resistant or flame-resistant heat-resistant coated Material.
  • the cone ring is with the tip on the Attached end face of the central body, the core air ring channel separates from the main air ring channel.
  • the burner 1 has a housing 2 and a central body 3 with a main air annular channel 4 formed between them for a main or lean premix burner, the one Combustion chamber 5 is associated with a (aircraft) -Gasturbine.
  • the main air ring channel 4 of the lean premix burner through which flow about 90% of the total burner air, are Main air swirl generator 6 integrated, the main air flow - Arrow A - put in a rotary motion.
  • the Main air flow becomes more fluid after swirl generation
  • Fuel injected which deals with the hot air flow mixed and partially evaporated in this. That in the Combustion chamber 5 introduced - lean - fuel-air mixture has a high proportion of air and burns in the combustion chamber. 5 with a correspondingly low combustion temperature, so that the nitrogen oxide emission and consequently the air pollution is extremely low.
  • Channel 7 is formed for receiving a support burner, the an atomizer consisting of atomizer fins 18, one Fuel line 8, an adjoining this atomizer carrier tube 9 and one opening into the combustion chamber 5 Atomizer nozzle 10, and one at the periphery of the atomizer trained core air ring channel 11 includes.
  • core air passes through the core air ring channel eleventh and a core air swirl generator 12 for generating a axial rotational movement of the core air into the gas turbine combustor 5, there to create a stable flame with the sprayed from the atomizer nozzle 10 fuel Fuel-air mixture with a high fuel content for To make available.
  • the direction of rotation of the main air flow and the core air flow is preferably in the same direction.
  • An essential component of the present lean burn burner with centrically integrated support burner is on the central body 3 in the mouth region of the core air-annular channel 11 and the main air-annular channel 4 subsequent Flame stabilization ring, which is used as a cone ring 13 with the Central body 3 subsequent tip and one of a annular Kern Kunststoffleitflanke 14 and an annular Hauptluftleitflanke 15 formed to the interior of the combustion chamber 5 facing groove 16 is executed.
  • hot recirculation zone 17 can cause the cold air intake due unfavorable weather conditions so far not evaporated Fuel mist coming from the atomizer nozzle 10 in this Penetrate area, or fuel-air mixtures at high Temperature stay sufficiently long and largely evaporate to a good combustible and ignitable fuel-air mixture to form in the combustion chamber.
  • the fuel outlet angle from the atomizer nozzle 10 is set that the fuel droplets on the very hot, dormant Rezirkulationszone 17 meet and be burned there and not beyond this area to the combustion chamber walls can reach.
  • the Cone ring 13 On the formation of the domed hollow cylindrical hot recirculation zone 17 contributes significantly to the warming of the Coving 16 having conical ring 13, at whose due to the lying there flame root hot surface the fuel or the fuel-air mixture also ignited to sustain combustion.
  • the Cone ring 13 is made of heat-resistant steel, optionally with ceramic protective coating on the flame side, or also completely made of a ceramic material (advantageous: fiber-ceramic composites).
  • Overheating of the Cone ring 13 is made by suitable choice of materials and the good heat transfer to the relatively thin-walled core and Hauptluftleitflanken 14, 15 of the cone ring 13 and at the rear side as a cooling medium flowing main air (air-fuel mixture) or core air prevented.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
EP04090216A 2003-06-06 2004-06-02 Brûleur pour une chambre de combustion de turbine à gaz Expired - Fee Related EP1484553B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10326720A DE10326720A1 (de) 2003-06-06 2003-06-06 Brenner für eine Gasturbinenbrennkammer
DE10326720 2003-06-06

Publications (3)

Publication Number Publication Date
EP1484553A2 true EP1484553A2 (fr) 2004-12-08
EP1484553A3 EP1484553A3 (fr) 2006-11-29
EP1484553B1 EP1484553B1 (fr) 2011-09-28

Family

ID=33154610

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04090216A Expired - Fee Related EP1484553B1 (fr) 2003-06-06 2004-06-02 Brûleur pour une chambre de combustion de turbine à gaz

Country Status (3)

Country Link
US (1) US7621131B2 (fr)
EP (1) EP1484553B1 (fr)
DE (1) DE10326720A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010008633A2 (fr) * 2008-04-11 2010-01-21 General Electric Company Mélangeur pour chambre de combustion et procédé pour sa fabrication
CN101514815B (zh) * 2008-02-21 2013-04-10 通用电气公司 燃气涡轮机燃烧器火焰稳定器
US10190774B2 (en) 2013-12-23 2019-01-29 General Electric Company Fuel nozzle with flexible support structures
US10288293B2 (en) 2013-11-27 2019-05-14 General Electric Company Fuel nozzle with fluid lock and purge apparatus
US10451282B2 (en) 2013-12-23 2019-10-22 General Electric Company Fuel nozzle structure for air assist injection

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US6986255B2 (en) * 2002-10-24 2006-01-17 Rolls-Royce Plc Piloted airblast lean direct fuel injector with modified air splitter
AU2003253274A1 (en) * 2003-07-25 2005-02-14 Ansaldo Energia S.P.A. Gas turbine burner
US7308793B2 (en) * 2005-01-07 2007-12-18 Power Systems Mfg., Llc Apparatus and method for reducing carbon monoxide emissions
US7779636B2 (en) * 2005-05-04 2010-08-24 Delavan Inc Lean direct injection atomizer for gas turbine engines
US7624576B2 (en) * 2005-07-18 2009-12-01 Pratt & Whitney Canada Corporation Low smoke and emissions fuel nozzle
US8062027B2 (en) * 2005-08-11 2011-11-22 Elster Gmbh Industrial burner and method for operating an industrial burner
DE102005062079A1 (de) 2005-12-22 2007-07-12 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner mit einer Zerstäuberlippe
US7836677B2 (en) * 2006-04-07 2010-11-23 Siemens Energy, Inc. At least one combustion apparatus and duct structure for a gas turbine engine
US7631499B2 (en) * 2006-08-03 2009-12-15 Siemens Energy, Inc. Axially staged combustion system for a gas turbine engine
US8393891B2 (en) * 2006-09-18 2013-03-12 General Electric Company Distributed-jet combustion nozzle
DE102006051286A1 (de) * 2006-10-26 2008-04-30 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennervorrichtung
DE102007043626A1 (de) 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität
EP2107313A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Alimentation étagée de combustible dans un brûleur
EP2107311A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Mise à l'échelle de taille dans un brûleur
US8683804B2 (en) * 2009-11-13 2014-04-01 General Electric Company Premixing apparatus for fuel injection in a turbine engine
US9027350B2 (en) * 2009-12-30 2015-05-12 Rolls-Royce Corporation Gas turbine engine having dome panel assembly with bifurcated swirler flow
DE102010019773A1 (de) * 2010-05-07 2011-11-10 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner eines Gasturbinentriebwerks mit Strömungsleitelement
US9920932B2 (en) 2011-01-26 2018-03-20 United Technologies Corporation Mixer assembly for a gas turbine engine
US8312724B2 (en) 2011-01-26 2012-11-20 United Technologies Corporation Mixer assembly for a gas turbine engine having a pilot mixer with a corner flame stabilizing recirculation zone
US8973368B2 (en) 2011-01-26 2015-03-10 United Technologies Corporation Mixer assembly for a gas turbine engine
JP5773342B2 (ja) * 2011-06-03 2015-09-02 川崎重工業株式会社 燃料噴射装置
JP5772245B2 (ja) 2011-06-03 2015-09-02 川崎重工業株式会社 燃料噴射装置
DE102012017065A1 (de) * 2012-08-28 2014-03-27 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zum Betrieb eines Magervormischbrenners einer Fluggasturbine sowie Vorrichtung zur Durchführung des Verfahrens
JP6203371B2 (ja) 2013-03-13 2017-09-27 インダストリアル タービン カンパニー （ユーケイ） リミテッドＩｎｄｕｓｔｒｉａｌ Ｔｕｒｂｉｎｅ Ｃｏｍｐａｎｙ （ＵＫ） Ｌｉｍｉｔｅｄ リーン方位角炎燃焼器
DE102013206014A1 (de) * 2013-04-05 2014-10-09 Dürr Systems GmbH Energiewandler-System und Baugruppen hierfür
US10281146B1 (en) * 2013-04-18 2019-05-07 Astec, Inc. Apparatus and method for a center fuel stabilization bluff body
EP3022492A4 (fr) * 2013-07-15 2017-02-22 Hamilton Sundstrand Corporation Système, appareil et procédé de combustion
DE102017118166A1 (de) * 2017-08-09 2019-02-14 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR) Brennerkopf, Brennersystem und Verwendung des Brennersystems

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101514815B (zh) * 2008-02-21 2013-04-10 通用电气公司 燃气涡轮机燃烧器火焰稳定器
WO2010008633A2 (fr) * 2008-04-11 2010-01-21 General Electric Company Mélangeur pour chambre de combustion et procédé pour sa fabrication
WO2010008633A3 (fr) * 2008-04-11 2013-01-17 General Electric Company Mélangeur pour chambre de combustion et procédé pour sa fabrication
US10288293B2 (en) 2013-11-27 2019-05-14 General Electric Company Fuel nozzle with fluid lock and purge apparatus
US10190774B2 (en) 2013-12-23 2019-01-29 General Electric Company Fuel nozzle with flexible support structures
US10451282B2 (en) 2013-12-23 2019-10-22 General Electric Company Fuel nozzle structure for air assist injection

Also Published As

Publication number Publication date
US7621131B2 (en) 2009-11-24
EP1484553A3 (fr) 2006-11-29
EP1484553B1 (fr) 2011-09-28
US20050028526A1 (en) 2005-02-10
DE10326720A1 (de) 2004-12-23

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