EP2263044B1 - Grössenskalierung eines brenners - Google Patents

Grössenskalierung eines brenners Download PDF

Info

Publication number
EP2263044B1
EP2263044B1 EP09728642.1A EP09728642A EP2263044B1 EP 2263044 B1 EP2263044 B1 EP 2263044B1 EP 09728642 A EP09728642 A EP 09728642A EP 2263044 B1 EP2263044 B1 EP 2263044B1
Authority
EP
European Patent Office
Prior art keywords
quarl
burner
section
fuel
flame
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.)
Not-in-force
Application number
EP09728642.1A
Other languages
English (en)
French (fr)
Other versions
EP2263044A1 (de
Inventor
Vladimir Milosavljevic
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP09728642.1A priority Critical patent/EP2263044B1/de
Publication of EP2263044A1 publication Critical patent/EP2263044A1/de
Application granted granted Critical
Publication of EP2263044B1 publication Critical patent/EP2263044B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00016—Retrofitting in general, e.g. to respect new regulations on pollution
    • 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
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • the small pilot combustor combined with very hot cooling air (above 750 °C) premixed with fuel act as a flameless burner, where reactants (oxygen & fuel) are premixed with products of combustion and a distributed flame is established at the forward stagnation point of the swirl induced recirculation zone.
  • the burner utilizes aerodynamics stabilization of the flame and confines the flame stabilization zone - the recirculation zone - in the multiple quarl arrangement.
  • the multiple quarl arrangement is an important feature of the design of the provided burner for the following reasons.
  • the quarl (or also called diffuser):
  • FIG 1 the burner is depicted with the burner 1 having a housing 2 enclosing the burner components.
  • Figure 2 shows for the sake of clarity a cross sectional view of the burner above a rotational symmetry axis.
  • the main parts of the burner are the radial swirler 3, the multi quarl 4a, 4b, 4c and the pilot combustor 5.
  • the burner loperates according to the principle of "supplying" heat and high concentration of free radicals from the a pilot combustor 5 exhaust 6 to a main flame 7 burning in a lean premixed air/fuel swirl emerging from a first exit 8 of a first lean premixing channel 10 and from a second exit 9 of a second lean premixing channel 11, whereby a rapid and stable combustion of the main lean premixed flame 7 is supported.
  • Said first lean premixing channel 10 is formed by and between the walls 4a and 4b of the multi quarl.
  • the second lean premixing channel 11 is formed by and between the walls 4b and 4c of the multi quarl.
  • the outermost rotational symmetric wall 4c of the multi quarl is provided with an extension 4c1 to provide for the optimal length of the multi quarl arrangement.
  • the first 10 and second 11 lean premixing channels are provided with swirler wings forming the swirler 3 to impart rotation to the air/fuel mixture passing through the channels.
  • Air 12 is provided to the first 10 and second 11 channels at the inlet 13 of said first and second channels.
  • the swirler 3 is located close to the inlet 13 of the first and second channels.
  • fuel 14 is introduced to the air/fuel swirl through a tube 15 provided with small diffusor holes 15b located at the air 12 inlet 13 between the swirler 3 wings, whereby the fuel is distributed into the air flow through said holes as a spray and effectively mixed with the air flow. Additional fuel can be added through a second tube 16 emerging into the first channel 10.
  • the pilot combustor 5 supplies heat and supplements a high concentration of free radicals directly to a forward stagnation point P and the shear layer 18 of the main swirl induced recirculation zone 20, where the main lean premixed flow is mixed with hot gases products of combustion provided by the pilot combustor 5.
  • the pilot combustor 5 is provided with walls 21 enclosing a combustion room for a pilot combustion zone 22. Air is supplied to the combustion room through fuel channel 23 and air channel 24.
  • a distributor plate 25 provided with holes over the surface of the plate. Said distributor plate 25 is separated a certain distance from said walls 21 forming a cooling space layer 25a. Cooling air 26 is taken in through a cooling inlet 27 and meets the outside of said distributor plate 25, whereupon the cooling air 26 is distributed across the walls 21 of the pilot combustor to effectively cool said walls 21.
  • the cooling air 26 is after said cooling let out through a second swirler 28 arranged around a pilot quarl 29 of the pilot combustor 5.
  • Further fuel can be added to the combustion in the main lean flame 7 by supplying fuel in a duct 30 arranged around and outside the cooling space layer 25a. Said further fuel is then let out and into the second swirler 28, where the now hot cooling air 26 and the fuel added through duct 30 is effectively premixed.
  • Recirculating products which are: source of heat and active species (symbolized by means of arrows 1a and 1b), located within the recirculation zone 20, have to be stationary in space and time downstream from the mixing section of the burner 1 to enable pyrolysis of the incoming mixture of fuel and air. If a steady combustion process is not prevailing, thermo-acoustics instabilities will occur.
  • a premixed or turbulent diffusion combustion swirl provides an effective way of premixing fuel and air.
  • the entrainiment of the fuel/air mixture into the shear layer of the recirculation zone 20 is proportional to the strength of the recirculation zone, the swirl number and the characteristics recirculation zone velocity URZ.
  • the process is initiated and stabilized by means of transporting heat and free radicals 31 from the previously combusted fuel and air, back upstream towards the flame front 7.
  • the combustion process is very lean, as is the case in lean-partially premixed combustion systems, and as a result the combustion temperature is low, the equilibrium levels of free radicals is also very low.
  • the free radicals produced by the combustion process quickly relax, see Fig. 6 , to the equilibrium level that corresponds to the temperature of the combustion products. This is due to the fact that the rate of this relaxation of the free radicals to equilibrium increases exponentially with increase in pressure, while on the other hand the equilibrium level of free radicals decreases exponentially with temperature decrease.
  • the relaxation time of the free radicals can be short compared to the "transport" time required for the free radicals (symbolized by arrows 31) to be convected downstream, from the point where they were produced in the shear layer 18 of the main recirculation zone 20, back upstream, towards the flame front 7 and the forward stagnation point P of the main recirculation zone 20.
  • This invention utilizes high non-equilibrium levels of free radicals 32 to stabilize the main lean combustion 7.
  • the scale of the small pilot combustor 5 is kept small and most of the combustion of fuel occurs in the lean premixed main combustor (at 7 and 18), and not in the small pilot combustor 5.
  • the small pilot combustor 5, can be kept small, because the free radicals 32 are released near the forward stagnation point P of the main recirculation zone 20. This is generally the most efficient location to supply additional heat and free radicals to swirl stabilized combustion (7).
  • the time scale between quench and utilization of free radicals 32 is very short not allowing free radicals 32 to relax to low equilibrium levels.
  • the forward stagnation point P of the main-lean re-circulating zone 20 is maintained and aerodynamically stabilized in the quarl (4a), at the exit 6 of the small pilot combustor 5.
  • zone 22 the exit of the small pilot combustor 5 is positioned on the centerline and at the small pilot combustor 5 throat 33.
  • the burner utilizes aerodynamics stabilization of the flame and confines the flame stabilization zone - recirculation zone (5), in the multiple quarl arrangement (4a, 4b and 4c).
  • the multiple quarl (the term multiple quarl is herein sometimes used for multiple quarl sections defining the completed quarl of the burner) arrangement is an important feature of the disclosed burner design for the reasons listed below.
  • the quarl (or sometimes called the diffuser):
  • the quarl (or diffuser) and the imparted swirl provides a possibility of a simple scaling of the disclosed burner geometry for different burner powers.
  • the igniter 34 as in prior art burners, is placed in the outer recirculation zone, which is illustrated in Figure 4b , the fuel/air mixture entering this region must often be made rich in order to make the flame temperature sufficiently hot to sustain stable combustion in this region.
  • the flame then often cannot be propagated to the main recirculation until the main premixed fuel and airflow becomes sufficiently rich, hot and has a sufficient pool of free radicals, which occurs at higher fuel flow rates.
  • the flame cannot propagate from the outer recirculation zone to the inner main recirculation zone shortly after ignition, it must propagate at higher pressure after the engine speed begins to increase.
  • the combustion - flame front 7 also expands outwards in a conical shape from this forward stagnation point P, as illustrated in Figure 2 .
  • This conical expansion downstream allows the heat and free radicals 32 generated upstream to support the combustion downstream allowing the flame front 7 to widen as it moves downstream.
  • the quarl (4a, 4b, 4c), illustrated in Figure 2 compared to swirl stabilized combustion without the quarl, shows how the quarl shapes the flame to be more conical and less hemispheric in nature.
  • a more conical flame front allows for a point source of heat to initiate combustion of the whole flow field effectively.
  • the combustion process within the burner 1 is staged.
  • lean flame 35 is initiated in the small pilot combustor 5 by adding fuel 23 mixed with air 24 and igniting the mixture utilizing ignitor 34.
  • ignition equivalence ratio of the flame 35 in the small pilot combustor 5 is adjusted at either lean (below equivalence ratio 1, and at approximately equivalence ratio of 0,8) or rich conditions (above equivalence ratio 1, and at approximately equivalence ratio between 1,4 and 1,6).
  • lean low equivalence ratio 1, and at approximately equivalence ratio of 0,8
  • rich conditions above equivalence ratio 1, and at approximately equivalence ratio between 1,4 and 1,6.
  • the reason why the equivalence ratio within the small pilot combustor 5 is at rich conditions in the range between 1,4 and 1,6 is emission levels.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Claims (4)

  1. Verfahren zum Skalieren der Größe eines Brenners (1) einer Gasturbinenmaschine, die ein Brennergehäuse (2) umfasst, wobei der Brenner Folgendes aufweist:
    - sich axial gegenüberliegende stromaufwärts gelegene und stromabwärts gelegene Endabschnitte;
    - an einem stromaufwärts gelegenen Ende des Brenners (1) Brennstoff (14) und Luft (12), die als eine Mischung aus Luft und Brennstoff aus einem Ausgang (8) eines Vormischkanals (10) bereitgestellt werden, um eine Hauptflamme (7) an dem stromabwärts gelegenen Ende des Brenners (1) zu unterhalten;
    - wobei der Vormischkanal (10) an seinen Ausgängen (8) durch eine runde Innenwand, die von einem inneren Brennersteinabschnitt (4a) gebildet ist, und eine runde Außenwand, die von einem äußeren Brennersteinabschnitt (4b) gebildet ist, definiert ist.
    - dadurch gekennzeichnet, dass das Verfahren die folgenden Schritte umfasst:
    - Erhöhen der Größe des Brenners (1) durch Hinzufügen eines Brennersteinabschnitts (4c) außerhalb des und umlaufend um den vorher äußersten Brennersteinabschnitt (4b) und dadurch in einem ringförmigen Raum zwischen dem hinzugefügten Brennersteinabschnitt (4c) und dem bestehenden äußeren Brennersteinabschnitt (4b) Bilden eines zusätzlichen Vormischkanals (11), der an seinen Ausgängen (9) durch eine runde Innenwand, die durch den vorher äußersten Brennersteinabschnitt (4b) gebildet ist, und eine runde Außenwand, die durch den hinzugefügten Brennersteinabschnitt (4c) gebildet ist, definiert ist;
    - wobei die Brennersteinabschnitte (4a, 4b, 4c) einen Verbrennungsraum zum Aufnehmen der Hauptflamme (7) des Brenners (1) definieren, wobei ein äußerer Brennersteinabschnitt (4c, 4b) einen größeren Durchmesser aufweist als ein benachbarter innerer Brennersteinabschnitt (4b, 4a) und sich in einem größeren Abstand stromabwärts als der benachbarte innere Brennersteinabschnitt (4b, 4a) erstreckt, wobei jeder Brennersteinabschnitt (4a, 4b, 4c) die Konfiguration des konischen Mantels eines Kegelstumpfs aufweist und aufeinanderfolgend einer nach dem anderen in der stromabwärts gelegenen Richtung des Brenners (1) angeordnet ist, wobei der engste Teil des Mantels eines stromabwärts gelegenen Brennersteinabschnitts (4b) den weitesten Teil des Mantels des nächstgelegenen stromaufwärts gelegenen Brennersteinabschnitts (4a) umgibt.
  2. Verfahren nach Anspruch 1, das ferner die folgenden Schritte umfasst:
    - Erhöhen der Größe des Brenners (1) durch Hinzufügen eines Brennersteinabschnitts (4d) außerhalb des und umlaufend um den vorher äußersten Brennersteinabschnitt (4c) und dadurch in einem ringförmigen Raum zwischen dem hinzugefügten Brennersteinabschnitt (4d) und dem bestehenden äußeren Brennersteinabschnitt (4c) Bilden eines zusätzlichen Vormischkanals (11b), der an seinem Ausgang durch eine runde Innenwand, die durch den vorher äußersten Brennersteinabschnitt (4c) gebildet ist, und eine runde Außenwand, die durch den hinzugefügten Brennersteinabschnitt (4d) gebildet ist, definiert ist;
    - wobei die Brennersteinabschnitte (4a, 4b, 4c, 4d) einen Verbrennungsraum zum Aufnehmen der Hauptflamme (7) des Brenners (1) definieren, wobei ein äußerer Brennersteinabschnitt (4d, 4c, 4b) einen größeren Durchmesser aufweist als ein benachbarter innerer Brennersteinabschnitt (4c, 4b, 4a) und sich in einem größeren Abstand stromabwärts als sein benachbarter innerer Brennersteinabschnitt (4c, 4b, 4a) erstreckt.
  3. Verfahren nach Anspruch 2, das ferner den folgenden Schritt umfasst:
    - Anordnen der Wirbelanzahlen der Luft/Brennstoff-Mischung, die den Kanälen (10, 11, 11b) zur Verfügung gestellt wird, um die Wirbelanzahlen gemäß SN,10 > SN, 11 > SN, 11b zu halten, wobei jedoch die Wirbelanzahlen alle oberhalb SN = 0,6 und nicht größer als SN = 0,8 sein sollten.
  4. Größenskalierbarer Brennerstein in einem Brenner (1) für eine Gasturbinenmaschine, wobei
    - der Brenner (1) sich axial gegenüberliegende stromaufwärts gelegene und stromabwärts gelegene Endabschnitte aufweist;
    - Brennstoff und Luft gemischt und dem Brenner (1) zur Verfügung gestellt werden, woraufhin der Brennstoff in einer Hauptflamme (7) des Brenners (1) verbrannt wird,
    - ein Brennerstein (4a, 4b, 4c) angeordnet ist, um die Hauptflamme (7) aufzunehmen,
    dadurch gekennzeichnet, dass
    - der skalierbare Brennerstein aus mehreren Brennersteinabschnitten (4a, 4b, 4c) gebildet ist, wobei jeder Brennersteinabschnitt (4a, 4b, 4c) die Konfiguration des konischen Mantels eines Kegelstumpfs aufweist und aufeinanderfolgend einer nach dem anderen in der stromabwärts gelegenen Richtung des Brenners (1) angeordnet ist, wobei der engste Teil des Mantels eines stromabwärts gelegenen Brennersteinabschnitts (4b) den weitesten Teil des Mantels des nächstgelegenen stromaufwärts gelegenen Brennersteinabschnitts (4a) umgibt,
    - ein ringförmiger Kanal (10, 11) für vorgemischte Luft und Brennstoff zwischen zwei aufeinanderfolgenden Brennersteinabschnitten (4a, 4b) angeordnet ist,
    - der Brennerstein angeordnet ist, so dass weitere Brennersteinabschnitte (4c, 4d) zu einer bestehenden Anzahl von wenigstens zwei Brennersteinabschnitten (4a, 4b) hinzugefügt werden können, und
    - der Brennerstein angeordnet ist, so dass hinzugefügte Brennersteinabschnitte (4d, 4c) entfernt werden können, bis ein Minimum von zwei Brennersteinabschnitten (4a, 4b) verbleibt.
EP09728642.1A 2008-04-01 2009-03-26 Grössenskalierung eines brenners Not-in-force EP2263044B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09728642.1A EP2263044B1 (de) 2008-04-01 2009-03-26 Grössenskalierung eines brenners

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08006666A EP2107311A1 (de) 2008-04-01 2008-04-01 Größenskalierung eines Brenners
EP09728642.1A EP2263044B1 (de) 2008-04-01 2009-03-26 Grössenskalierung eines brenners
PCT/EP2009/053555 WO2009121776A1 (en) 2008-04-01 2009-03-26 Size scaling of a burner

Publications (2)

Publication Number Publication Date
EP2263044A1 EP2263044A1 (de) 2010-12-22
EP2263044B1 true EP2263044B1 (de) 2013-05-15

Family

ID=39810145

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08006666A Withdrawn EP2107311A1 (de) 2008-04-01 2008-04-01 Größenskalierung eines Brenners
EP09728642.1A Not-in-force EP2263044B1 (de) 2008-04-01 2009-03-26 Grössenskalierung eines brenners

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08006666A Withdrawn EP2107311A1 (de) 2008-04-01 2008-04-01 Größenskalierung eines Brenners

Country Status (6)

Country Link
US (1) US20110027728A1 (de)
EP (2) EP2107311A1 (de)
CN (1) CN101981379B (de)
ES (1) ES2417158T3 (de)
RU (1) RU2455570C1 (de)
WO (1) WO2009121776A1 (de)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20122154A1 (it) * 2012-12-17 2014-06-18 Ansaldo Energia Spa Gruppo bruciatore, camera di combustione comprendente detto gruppo bruciatore e metodo per alimentare detto gruppo bruciatore
US9366443B2 (en) * 2013-01-11 2016-06-14 Siemens Energy, Inc. Lean-rich axial stage combustion in a can-annular gas turbine engine
US8794217B1 (en) 2013-02-07 2014-08-05 Thrival Tech, LLC Coherent-structure fuel treatment systems and methods
JP6086860B2 (ja) * 2013-11-29 2017-03-01 三菱日立パワーシステムズ株式会社 ノズル、燃焼器、及びガスタービン
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
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
GB202013274D0 (en) * 2020-08-25 2020-10-07 Siemens Gas And Power Gmbh & Co Kg Combuster for a gas turbine

Family Cites Families (50)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2787120A (en) * 1950-08-05 1957-04-02 Leduc Rene Plural annular coaxial combustion chambers
FR1150640A (fr) * 1956-05-18 1958-01-16 Perfectionnements aux chambres de combustion notamment pour aéronefs
GB1048968A (en) * 1964-05-08 1966-11-23 Rolls Royce Combustion chamber for a gas turbine engine
GB1421399A (en) * 1972-11-13 1976-01-14 Snecma Fuel injectors
US3866413A (en) * 1973-01-22 1975-02-18 Parker Hannifin Corp Air blast fuel atomizer
DE2460740C3 (de) * 1974-12-21 1980-09-18 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Brennkammer für Gasturbinentriebwerke
US4204402A (en) * 1976-05-07 1980-05-27 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reduction of nitric oxide emissions from a combustor
US4845940A (en) * 1981-02-27 1989-07-11 Westinghouse Electric Corp. Low NOx rich-lean combustor especially useful in gas turbines
EP0114062A3 (de) * 1983-01-18 1986-02-19 Stubinen Utveckling AB Verfahren und Vorrichtung zum Verbrennen fester Brennstoffe, insbesondere Kohle, Torf oder dergleichen, in pulverisierter Form
ATE42821T1 (de) * 1985-03-04 1989-05-15 Siemens Ag Brenneranordnung fuer feuerungsanlagen, insbesondere fuer brennkammern von gasturbinenanlagen sowie verfahren zu ihrem betrieb.
JP2644745B2 (ja) * 1987-03-06 1997-08-25 株式会社日立製作所 ガスタービン用燃焼器
JPH01114623A (ja) * 1987-10-27 1989-05-08 Toshiba Corp ガスタービン燃焼器
JPH0684817B2 (ja) * 1988-08-08 1994-10-26 株式会社日立製作所 ガスタービン燃焼器及びその運転方法
US5040371A (en) * 1988-12-12 1991-08-20 Sundstrand Corporation Fuel injectors for use with combustors
CH678757A5 (de) * 1989-03-15 1991-10-31 Asea Brown Boveri
US5094082A (en) * 1989-12-22 1992-03-10 Sundstrand Corporation Stored energy combustor
DE69129858T2 (de) * 1990-10-05 1998-12-03 Massachusetts Inst Technology Verbrennungsanlage mit vermindertem ausstoss von stickstoffoxiden
GB9023004D0 (en) * 1990-10-23 1990-12-05 Rolls Royce Plc A gas turbine engine combustion chamber and a method of operating a gas turbine engine combustion chamber
EP0540167A1 (de) * 1991-09-27 1993-05-05 General Electric Company Gestufte Vormischbrennkammer mit niedrigem NOx-Ausstoss
US5131334A (en) * 1991-10-31 1992-07-21 Monro Richard J Flame stabilizer for solid fuel burner
GB2262981B (en) * 1991-12-30 1995-08-09 Ind Tech Res Inst Dual fuel low nox burner
US5284438A (en) * 1992-01-07 1994-02-08 Koch Engineering Company, Inc. Multiple purpose burner process and apparatus
JPH05203148A (ja) * 1992-01-13 1993-08-10 Hitachi Ltd ガスタービン燃焼装置及びその制御方法
US5237812A (en) * 1992-10-07 1993-08-24 Westinghouse Electric Corp. Auto-ignition system for premixed gas turbine combustors
US5407347A (en) * 1993-07-16 1995-04-18 Radian Corporation Apparatus and method for reducing NOx, CO and hydrocarbon emissions when burning gaseous fuels
US5394688A (en) * 1993-10-27 1995-03-07 Westinghouse Electric Corporation Gas turbine combustor swirl vane arrangement
US5477685A (en) * 1993-11-12 1995-12-26 The Regents Of The University Of California Lean burn injector for gas turbine combustor
GB2284884B (en) * 1993-12-16 1997-12-10 Rolls Royce Plc A gas turbine engine combustion chamber
JP2950720B2 (ja) * 1994-02-24 1999-09-20 株式会社東芝 ガスタービン燃焼装置およびその燃焼制御方法
US5647215A (en) * 1995-11-07 1997-07-15 Westinghouse Electric Corporation Gas turbine combustor with turbulence enhanced mixing fuel injectors
US6201029B1 (en) * 1996-02-13 2001-03-13 Marathon Oil Company Staged combustion of a low heating value fuel gas for driving a gas turbine
JP3673009B2 (ja) * 1996-03-28 2005-07-20 株式会社東芝 ガスタービン燃焼器
GB2311596B (en) * 1996-03-29 2000-07-12 Europ Gas Turbines Ltd Combustor for gas - or liquid - fuelled turbine
US5983642A (en) * 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
US6109038A (en) * 1998-01-21 2000-08-29 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel assembly
US6354072B1 (en) * 1999-12-10 2002-03-12 General Electric Company Methods and apparatus for decreasing combustor emissions
AU1736401A (en) * 1999-12-15 2001-06-25 Osaka Gas Co., Ltd. Fluid distributor, burner device, gas turbine engine, and cogeneration system
US6272840B1 (en) * 2000-01-13 2001-08-14 Cfd Research Corporation Piloted airblast lean direct fuel injector
JP4625609B2 (ja) * 2000-06-15 2011-02-02 アルストム テクノロジー リミテッド バーナーの運転方法と段階的予混合ガス噴射バーナー
US6488496B1 (en) * 2001-09-06 2002-12-03 Hauck Manufacturing Co. Compact combination burner with adjustable spin section
UA68446C2 (en) * 2002-02-18 2004-08-16 Res And Production Complex Of Combustion chamber of gas turbine of power unit
US6820411B2 (en) * 2002-09-13 2004-11-23 The Boeing Company Compact, lightweight high-performance lift thruster incorporating swirl-augmented oxidizer/fuel injection, mixing and combustion
US6969249B2 (en) * 2003-05-02 2005-11-29 Hauck Manufacturing, Inc. Aggregate dryer burner with compressed air oil atomizer
DE10326720A1 (de) * 2003-06-06 2004-12-23 Rolls-Royce Deutschland Ltd & Co Kg Brenner für eine Gasturbinenbrennkammer
JP3940705B2 (ja) * 2003-06-19 2007-07-04 株式会社日立製作所 ガスタービン燃焼器及びその燃料供給方法
KR101178195B1 (ko) * 2003-09-05 2012-08-30 지멘스 악티엔게젤샤프트 가스 터빈 엔진에서의 연소 안정화 장치
DE112005001695A5 (de) * 2004-08-27 2007-11-22 Alstom Technology Ltd. Mischeranordnung
EP1659339A1 (de) * 2004-11-18 2006-05-24 Siemens Aktiengesellschaft Verfahren zum Anfahren eines Brenners
US20080083224A1 (en) * 2006-10-05 2008-04-10 Balachandar Varatharajan Method and apparatus for reducing gas turbine engine emissions
EP2107300A1 (de) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Dralleinrichtung mit Gasinjektor

Also Published As

Publication number Publication date
EP2263044A1 (de) 2010-12-22
RU2010144571A (ru) 2012-05-10
RU2455570C1 (ru) 2012-07-10
CN101981379A (zh) 2011-02-23
ES2417158T3 (es) 2013-08-06
EP2107311A1 (de) 2009-10-07
US20110027728A1 (en) 2011-02-03
CN101981379B (zh) 2012-06-20
WO2009121776A1 (en) 2009-10-08

Similar Documents

Publication Publication Date Title
EP2257743B1 (de) Brenner
EP2107301B1 (de) Gaseinspritzung in einem Brenner
EP2263043B1 (de) Brennersteine in einem brenner
US8033112B2 (en) Swirler with gas injectors
EP2107312A1 (de) Pilotverbrennkammer in einem Brenner
EP2107313A1 (de) Gestufte Brennstoffversorgung in einem Brenner
EP2263044B1 (de) Grössenskalierung eines brenners
EP2434218A1 (de) Brenner mit geringen NOx-Emissionen

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20100827

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA RS

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 612357

Country of ref document: AT

Kind code of ref document: T

Effective date: 20130615

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602009015728

Country of ref document: DE

Effective date: 20130711

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2417158

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20130806

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 612357

Country of ref document: AT

Kind code of ref document: T

Effective date: 20130515

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20130515

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130816

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130916

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130815

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130915

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130815

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

Ref country code: BE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20140218

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20140313

Year of fee payment: 6

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602009015728

Country of ref document: DE

Effective date: 20140218

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20140328

Year of fee payment: 6

Ref country code: FR

Payment date: 20140317

Year of fee payment: 6

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20140312

Year of fee payment: 6

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20140519

Year of fee payment: 6

Ref country code: ES

Payment date: 20140411

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140326

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140331

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140326

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140331

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602009015728

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20150326

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150327

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150326

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20151130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150326

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20151001

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150331

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20090326

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150327

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20180622

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130515