EP2037172A2 - Brûleur maigre de turbine à gaz doté d'une buse à carburant ayant une homogénéité de carburant contrôlée - Google Patents

Brûleur maigre de turbine à gaz doté d'une buse à carburant ayant une homogénéité de carburant contrôlée Download PDF

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Publication number
EP2037172A2
EP2037172A2 EP08015722A EP08015722A EP2037172A2 EP 2037172 A2 EP2037172 A2 EP 2037172A2 EP 08015722 A EP08015722 A EP 08015722A EP 08015722 A EP08015722 A EP 08015722A EP 2037172 A2 EP2037172 A2 EP 2037172A2
Authority
EP
European Patent Office
Prior art keywords
fuel
der
gasturbinenmagerbrenner
gas turbine
burner
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
EP08015722A
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German (de)
English (en)
Other versions
EP2037172B1 (fr
EP2037172A3 (fr
Inventor
Leif Rackwitz
Imon-Kalyan Bagchi
Thomas Dörr
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
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Publication date
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Publication of EP2037172A2 publication Critical patent/EP2037172A2/fr
Publication of EP2037172A3 publication Critical patent/EP2037172A3/fr
Application granted granted Critical
Publication of EP2037172B1 publication Critical patent/EP2037172B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • 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

Definitions

  • the invention relates to a gas turbine lean burn burner according to the features of the preamble of claim 1.
  • the invention relates to a fuel nozzle with controlled fuel inhomogeneity, which provides the opportunity to introduce the fuel in an optimal manner for combustion.
  • the main stage of the known so-called lean burners is often designed as a so-called film depositor ( US 2006/0248898 A1 ).
  • some injection methods with single-jet injection are known which are intended to ensure a high degree of homogenization of the initial fuel distribution and / or a high penetration depth of the injected fuel ( US 2004/0040311 A1 ).
  • bluff body geometries which may be designed as baffle plates or V-shaped stabilizers arranged (eg US 4445339 and WO 10/860659 ).
  • the local fuel-air mixture is not controlled adjustable.
  • the problem is that with a desired homogeneous axial and circumferential loading of the fuel on the film layer
  • a very good air-fuel mixture with average low combustion temperatures and thus low NOx emissions can be achieved, however the homogeneous mixture formation aimed at under high load conditions under partial load conditions as a result of insufficient fuel loading on the film former lead to a significant deterioration of the combustion chamber burnout (cf. Fig. 6 ).
  • the background is the reduced heat release associated with lean mixtures as well as the property for local flame extinction with successive reduction of the fuel and low combustion chamber pressure and temperature.
  • Another flow form is characterized by a so-called "unfolding" of the flow and the formation of a recirculation area on the burner axis (see Fig. 4 ).
  • an attenuated recirculation area in the wake of the stabilizer is additionally present in this variant of the flame stabilizer.
  • the invention has for its object to provide a Gasturbinenmagerbrenner of the type mentioned, which has a low structure while avoiding the disadvantages of the prior art low pollutant emissions, improved flame stability and a high Brennttingausbrand.
  • a burner operated with excess air having a pilot 17 and a main fuel injection 18.
  • the aim is to set a targeted inhomogeneity of the fuel-air mixture.
  • the goal is to create a load-dependent variation of fuel placement in the main stage of the fuel in order to influence the degree of local fuel-air mixture.
  • the background is that a high mixture homogenization on the one hand favors the formation of low NOx emissions, on the other hand, a reduced mixture homogenization by targeted formation of locally rich mixture zones advantageous for achieving a high burnout of the combustion chamber, especially at partial load conditions.
  • the partially competing properties are to be optimized by the method of load-dependent fuel inhomogeneity.
  • the burner is characterized by a novel flame stabilizer between the inner and middle flow channel, which should lead to improved flow control within the combustion chamber, in particular with regard to the interaction of the pilot and main flow in addition to the method for local load-dependent fuel enrichment.
  • An essential feature of the present invention is that the outlet openings of the discrete fuel injections are set in the circumferential direction ( see FIGS. 10, 12 ).
  • the angle of attack of the fuel jets in the circumferential direction should be in the range between 10 ° ⁇ ⁇ 2 ⁇ 60 °. This can be by a - in relation to the twisted air flow of the central air passage 15 - the same direction or opposite directions.
  • the fuel jets may be at individual angles ⁇ 2.
  • the fuel jets can continue to be employed with respect to the burner axis 4 in the axial direction.
  • the preferred axial angle of attack of the fuel jets is in the range between -10 ° ⁇ ⁇ 1 ⁇ 90 °.
  • the fuel jets can be set at individual angles ⁇ 1.
  • the recesses can also be made individually (both with respect to ⁇ 1 and ⁇ 2).
  • the first method is to meter the main fuel through discrete fuel bores upstream of the main fuel passage exit face and directly adjust a circumferentially controlled inhomogeneous fuel-air mixture. This can be achieved by a suitable choice of the number, arrangement and adjustment of the fuel bores and by ensuring a low interaction of the injected fuel jets with the wall element already described within the fuel level. This means that the fuel jets injected into the middle flow channel still have a defined velocity pulse.
  • the short run length of the main fuel between the inner surface of the main stage 19, 38 and the location of the holes 41 is a load-dependent penetration depth of a more or less closed fuel film, albeit reduced or to a fuel film approximated fuel entry adjustable.
  • a "subsequent" local enrichment of the fuel film in the circumferential direction is proposed when using a fuel film ( Fig. 19 ).
  • These inhomogeneities in the fuel distribution can be achieved by different measures, for example of turbulators placed on the film laying surface, a suitable design of the trailing edge of the film layer (eg corrugated arrangement, lamella shape).
  • the said methods for local adjustment of inhomogeneities for the fuel film can be located both within the middle flow channel both upstream and / or downstream of the film gap.
  • turbulators on the surface of the film layer as follows: upstream or downstream of the film gap, then each 1-row or multi-row, with / without circumferential position, but also a circumferentially closed ring geometry of the turbulator (eg circumferential edge / step).
  • a specific contouring, both in the axial and in the circumferential direction, of the flame stabilizer is proposed.
  • An embodiment with a flower-shaped geometry for the outlet cross-section of a flame stabilizer is in Fig. 14 shown.
  • the diameter of the exit surface varies between a minimum diameter A1, which can lead to a pronounced decentralized recirculation in the wake of the V-shaped flame stabilizer, and a maximum diameter A2, which favors the formation of a central recirculation on the burner axis.
  • a minimum diameter A1 which can lead to a pronounced decentralized recirculation in the wake of the V-shaped flame stabilizer
  • a maximum diameter A2 which favors the formation of a central recirculation on the burner axis.
  • Fig. 14 illustrated variant for a contoured flame stabilizer with 8 so-called “flowers” are proposed further variants, the proposed geometries between 2 and 20 "flowers” may have.
  • Fig. 15 Another version is shown for a slightly more contoured flame stabilizer with 8 "flowers” in which the diameter A1 is reduced and at the same time the diameter A2 is increased.
  • the flow locally undergoes a flow acceleration or delay, resulting in a highly three-dimensional flow area with both centralized and decentralized recirculation (see Fig. 5 ).
  • a further embodiment provides for the circumferential alignment of the 3D wave geometry (contours) of the flame stabilizer at the effective helix angle of the deflected air flow for the inner pilot stage and / or the effective helix angle of the deflected air flow for the radially outer main stage.
  • Fig. 16 another embodiment of the contoured flame stabilizer is shown.
  • the contouring of the inner leg of the flame holder has 5 flowers, whereby by the number and arrangement of the flowers a diameter variation is achieved with a controlled asymmetry in the flow guidance of the pilot flow.
  • both a strong flow acceleration as well as due to the cross-sectional widening a deflection and flow delay is implemented in a sectional plane.
  • Fig. 17 another embodiment of a flame stabilizer with an eccentric positioning shown.
  • An additional option for contouring 25 is a sawtooth profile.
  • bimetal elements can be integrated into the front part of the flame stabilizer or at the trailing edge of the flame stabilizer to achieve a desired change in exit geometry.
  • Another advantage of the invention is the possibility of controlled adjustment of a "mixed" flow field with distinct central and decentralized recirculation areas. It is expected that the presence of a central recirculation on the one hand, the NOx emissions can be significantly reduced and can be achieved by setting a sufficient sudströmzone in the wake of the flame stabilizer very high flame stability against lean burn. Furthermore, it is expected that the interaction between the pilot and main flame can be more controlled, since depending on the 3D contour of the flame stabilizer there is the possibility to generate different flow states with more or less strong interaction of the pilot and main flow. With the help of this targeted generation of a "mixed" flow form, the operating range of the lean burn burner can be significantly extended between low and full load.
  • Another advantage of the invention is expected in the field of ignition of the pilot stage. Due to the contoured geometry of the exit surface with locally increased pitch diameters A2, a radial expansion (dispersion) of the pilot spray is generated, which can lead to improved mixture preparation. This increases the likelihood that a greater part of the pilot spray can be brought into the vicinity of the combustion chamber wall in the region of the spark plug and thus - depending on the local fuel-air mixture - the ignition characteristics of the burner can be improved.
  • Another advantage of the three-dimensional contouring of the flame stabilizer is an equalization of the flow and thus the reduction of the occurrence of possible flow instabilities, which can often form in the wake of bluff bodies - especially in the shear layer.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP08015722.5A 2007-09-13 2008-09-05 Brûleur maigre de turbine à gaz doté d'une buse à carburant ayant une homogénéité de carburant contrôlée Not-in-force EP2037172B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102007043626A DE102007043626A1 (de) 2007-09-13 2007-09-13 Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität

Publications (3)

Publication Number Publication Date
EP2037172A2 true EP2037172A2 (fr) 2009-03-18
EP2037172A3 EP2037172A3 (fr) 2012-09-26
EP2037172B1 EP2037172B1 (fr) 2014-04-02

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EP08015722.5A Not-in-force EP2037172B1 (fr) 2007-09-13 2008-09-05 Brûleur maigre de turbine à gaz doté d'une buse à carburant ayant une homogénéité de carburant contrôlée

Country Status (3)

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US (2) US20090139240A1 (fr)
EP (1) EP2037172B1 (fr)
DE (1) DE102007043626A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102639939A (zh) * 2009-11-30 2012-08-15 西门子公司 燃烧器装置
EP2549183A1 (fr) * 2011-07-20 2013-01-23 Rolls-Royce plc Injecteur de carburant
EP2703720A3 (fr) * 2012-08-28 2017-12-27 Rolls-Royce Deutschland Ltd & Co KG Procédé de fonctionnement d'un brûleur à prémélange maigre d'une turbine à gaz pour l'aéronautique et dispositif permettant de réaliser le procédé
CN116624890A (zh) * 2023-06-21 2023-08-22 清华大学 火焰稳定器、燃烧室及火焰稳定方法

Families Citing this family (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2107306A1 (fr) * 2008-03-31 2009-10-07 Siemens Aktiengesellschaft Boîtier de chambre de combustion
FR2971038B1 (fr) * 2011-01-31 2013-02-08 Snecma Dispositif d'injection pour une chambre de combustion de turbomachine
US8925325B2 (en) * 2011-03-18 2015-01-06 Delavan Inc. Recirculating product injection nozzle
US9291102B2 (en) * 2011-09-07 2016-03-22 Siemens Energy, Inc. Interface ring for gas turbine fuel nozzle assemblies
DE102012217263B4 (de) * 2012-09-25 2023-02-02 Deutsches Zentrum für Luft- und Raumfahrt e.V. Drallbrenner und Verfahren zum Betrieb eines Drallbrenners
US20140144152A1 (en) * 2012-11-26 2014-05-29 General Electric Company Premixer With Fuel Tubes Having Chevron Outlets
US20140144141A1 (en) * 2012-11-26 2014-05-29 General Electric Company Premixer with diluent fluid and fuel tubes having chevron outlets
US10281146B1 (en) * 2013-04-18 2019-05-07 Astec, Inc. Apparatus and method for a center fuel stabilization bluff body
WO2015178149A1 (fr) * 2014-05-23 2015-11-26 三菱日立パワーシステムズ株式会社 Dispositif de combustion de turbine à gaz et turbine à gaz
JP6351071B2 (ja) 2014-08-18 2018-07-04 川崎重工業株式会社 燃料噴射装置
US20160061452A1 (en) * 2014-08-26 2016-03-03 General Electric Company Corrugated cyclone mixer assembly to facilitate reduced nox emissions and improve operability in a combustor system
US10252270B2 (en) * 2014-09-08 2019-04-09 Arizona Board Of Regents On Behalf Of Arizona State University Nozzle apparatus and methods for use thereof
WO2016059200A1 (fr) * 2014-10-17 2016-04-21 Nuovo Pignone Srl Procédé pour la réduction des émissions de nox dans une turbine à gaz, mélangeur air-carburant, turbine à gaz et dispositif de tourbillonnement
US9638477B1 (en) * 2015-10-13 2017-05-02 Caterpillar, Inc. Sealless cooling device having manifold and turbulator
EP3184898A1 (fr) * 2015-12-23 2017-06-28 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
JP6723768B2 (ja) * 2016-03-07 2020-07-15 三菱重工業株式会社 バーナアセンブリ、燃焼器、及びガスタービン
US10352570B2 (en) 2016-03-31 2019-07-16 General Electric Company Turbine engine fuel injection system and methods of assembling the same
US10801728B2 (en) * 2016-12-07 2020-10-13 Raytheon Technologies Corporation Gas turbine engine combustor main mixer with vane supported centerbody
US11149952B2 (en) * 2016-12-07 2021-10-19 Raytheon Technologies Corporation Main mixer in an axial staged combustor for a gas turbine engine
US11561008B2 (en) * 2017-08-23 2023-01-24 General Electric Company Fuel nozzle assembly for high fuel/air ratio and reduced combustion dynamics
GB2568981A (en) * 2017-12-01 2019-06-05 Rolls Royce Plc Fuel spray nozzle
CN108844097B (zh) * 2018-03-16 2020-04-24 南京航空航天大学 一种多点贫油直接喷射的低污染燃烧室
JP6692847B2 (ja) 2018-03-26 2020-05-13 三菱重工業株式会社 ガスタービン燃焼器及びこれを備えたガスタービン機関
DE102020106842A1 (de) * 2020-03-12 2021-09-16 Rolls-Royce Deutschland Ltd & Co Kg Düse mit Strahlerzeugerkanal für in eine Brennkammer eines Triebwerks einzuspritzenden Kraftstoff
GB202019222D0 (en) 2020-12-07 2021-01-20 Rolls Royce Plc Lean burn combustor
GB202019219D0 (en) * 2020-12-07 2021-01-20 Rolls Royce Plc Lean burn combustor
CN113551262B (zh) * 2021-07-19 2022-06-14 南昌航空大学 一种带新月沙丘型面的支板火焰稳定器
CN113551261B (zh) * 2021-07-19 2022-06-14 南昌航空大学 一种波浪形v型火焰稳定器
CN114526497B (zh) * 2022-01-07 2023-02-07 清华大学 双缩口组合旋流式中心分级高温升燃烧室
CN120488311B (zh) * 2025-07-14 2025-10-10 中国人民解放军国防科技大学 无凹腔、支板的超燃冲压燃烧室及燃烧稳定性增强方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4445339A (en) 1980-11-24 1984-05-01 General Electric Co. Wingtip vortex flame stabilizer for gas turbine combustor flame holder
US6272840B1 (en) 2000-01-13 2001-08-14 Cfd Research Corporation Piloted airblast lean direct fuel injector
US6543235B1 (en) 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
US20040040311A1 (en) 2002-04-30 2004-03-04 Thomas Doerr Gas turbine combustion chamber with defined fuel input for the improvement of the homogeneity of the fuel-air mixture
WO2005028526A1 (fr) 2003-08-13 2005-03-31 Societe De Technologie Michelin Système catalytique pour l'obtention de copolymères diène(s) conjugué(s) / mono-oléfine(s) et ces copolymères
US20060248898A1 (en) 2005-05-04 2006-11-09 Delavan Inc And Rolls-Royce Plc Lean direct injection atomizer for gas turbine engines

Family Cites Families (128)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3091283A (en) * 1960-02-24 1963-05-28 Babcock & Wilcox Co Liquid fuel burner
GB1275255A (en) * 1968-07-18 1972-05-24 Lucas Industries Ltd Liquid atomising devices
US3568650A (en) * 1968-12-05 1971-03-09 Sonic Air Inc Supercharger and fuel injector assembly for internal combustion engines
US3699773A (en) * 1968-12-23 1972-10-24 Gen Electric Fuel cooled fuel injectors
US3713588A (en) * 1970-11-27 1973-01-30 Gen Motors Corp Liquid fuel spray nozzles with air atomization
US3703259A (en) * 1971-05-03 1972-11-21 Gen Electric Air blast fuel atomizer
US3955361A (en) * 1971-12-15 1976-05-11 Phillips Petroleum Company Gas turbine combustor with controlled fuel mixing
SE371685B (fr) 1972-04-21 1974-11-25 Stal Laval Turbin Ab
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
US3808803A (en) * 1973-03-15 1974-05-07 Us Navy Anticarbon device for the scroll fuel carburetor
US3919840A (en) * 1973-04-18 1975-11-18 United Technologies Corp Combustion chamber for dissimilar fluids in swirling flow relationship
US3930369A (en) * 1974-02-04 1976-01-06 General Motors Corporation Lean prechamber outflow combustor with two sets of primary air entrances
US3980233A (en) * 1974-10-07 1976-09-14 Parker-Hannifin Corporation Air-atomizing fuel nozzle
GB1537671A (en) 1975-04-25 1979-01-04 Rolls Royce Fuel injectors for gas turbine engines
US4170108A (en) * 1975-04-25 1979-10-09 Rolls-Royce Limited Fuel injectors for gas turbine engines
DE2529701A1 (de) * 1975-07-03 1977-01-27 Bosch Gmbh Robert Kraftstoffeinspritzanlage
US3977186A (en) * 1975-07-24 1976-08-31 General Motors Corporation Impinging air jet combustion apparatus
GB1597968A (en) * 1977-06-10 1981-09-16 Rolls Royce Fuel burners for gas turbine engines
US4141213A (en) * 1977-06-23 1979-02-27 General Motors Corporation Pilot flame tube
GB2012415B (en) 1978-01-04 1982-03-03 Secr Defence Fuel mixers
US4175380A (en) * 1978-03-24 1979-11-27 Baycura Orestes M Low noise gas turbine
IT1111808B (it) * 1978-03-28 1986-01-13 Rolls Royce Perfezionamenti apportati ai dispositivi di combustione di motori a turbina a gas
US4218020A (en) * 1979-02-23 1980-08-19 General Motors Corporation Elliptical airblast nozzle
US4425755A (en) * 1980-09-16 1984-01-17 Rolls-Royce Limited Gas turbine dual fuel burners
US4519958A (en) * 1982-06-14 1985-05-28 Kenna Research Corporation Fuel flow metering apparatus
CH670296A5 (en) 1986-02-24 1989-05-31 Bbc Brown Boveri & Cie Gas turbine fuel nozzle - has externally-supported premixing chamber for liq. fuel and air
CA1306873C (fr) * 1987-04-27 1992-09-01 Jack R. Taylor Injecteur de combustible a faible teneur en coke, pour turbine a gaz
US4845952A (en) * 1987-10-23 1989-07-11 General Electric Company Multiple venturi tube gas fuel injector for catalytic combustor
US4920740A (en) * 1987-11-23 1990-05-01 Sundstrand Corporation Starting of turbine engines
US4854127A (en) * 1988-01-14 1989-08-08 General Electric Company Bimodal swirler injector for a gas turbine combustor
DE3819898A1 (de) 1988-06-11 1989-12-14 Daimler Benz Ag Brennkammer fuer eine thermische stroemungsmaschine
CH680084A5 (fr) * 1989-06-06 1992-06-15 Asea Brown Boveri
US5165241A (en) * 1991-02-22 1992-11-24 General Electric Company Air fuel mixer for gas turbine combustor
JP2839777B2 (ja) 1991-12-24 1998-12-16 株式会社東芝 ガスタービン燃焼器用燃料噴射ノズル
DE4203775C2 (de) * 1992-02-10 1993-11-18 Erno Raumfahrttechnik Gmbh Triebwerk auf der Basis der katalytischen Zersetzung
US5267851A (en) 1992-03-16 1993-12-07 General Electric Company Swirl gutters for isolating flow fields for combustion enhancement at non-baseload operating conditions
DE4228816C2 (de) * 1992-08-29 1998-08-06 Mtu Muenchen Gmbh Brenner für Gasturbinentriebwerke
US5251447A (en) * 1992-10-01 1993-10-12 General Electric Company Air fuel mixer for gas turbine combustor
US5505045A (en) * 1992-11-09 1996-04-09 Fuel Systems Textron, Inc. Fuel injector assembly with first and second fuel injectors and inner, outer, and intermediate air discharge chambers
FR2698157B1 (fr) * 1992-11-18 1994-12-16 Snecma Système d'injection aérodynamique de chambre de combustion.
US5303554A (en) * 1992-11-27 1994-04-19 Solar Turbines Incorporated Low NOx injector with central air swirling and angled fuel inlets
DE4304213A1 (de) * 1993-02-12 1994-08-18 Abb Research Ltd Brenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
JPH06272862A (ja) * 1993-03-18 1994-09-27 Hitachi Ltd 燃料空気混合方法およびその混合装置
DE4316474A1 (de) * 1993-05-17 1994-11-24 Abb Management Ag Vormischbrenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
US5479781A (en) * 1993-09-02 1996-01-02 General Electric Company Low emission combustor having tangential lean direct injection
US5351477A (en) * 1993-12-21 1994-10-04 General Electric Company Dual fuel mixer for gas turbine combustor
US5511375A (en) * 1994-09-12 1996-04-30 General Electric Company Dual fuel mixer for gas turbine combustor
US5590529A (en) * 1994-09-26 1997-01-07 General Electric Company Air fuel mixer for gas turbine combustor
DE4446611A1 (de) * 1994-12-24 1996-06-27 Abb Management Ag Brennkammer
US5701732A (en) * 1995-01-24 1997-12-30 Delavan Inc. Method and apparatus for purging of gas turbine injectors
EP0747635B1 (fr) * 1995-06-05 2003-01-15 Rolls-Royce Corporation Brûleur à prémélange pauvre avec faible production de NOx pour turbines à gaz industrielles
DE19527453B4 (de) 1995-07-27 2009-05-07 Alstom Vormischbrenner
US5735117A (en) * 1995-08-18 1998-04-07 Fuel Systems Textron, Inc. Staged fuel injection system with shuttle valve and fuel injector therefor
DE19532264C2 (de) 1995-09-01 2001-09-06 Mtu Aero Engines Gmbh Einrichtung zur Aufbereitung eines Gemisches aus Brennstoff und Luft an Brennkammern für Gasturbinentriebwerke
DE19535370B4 (de) 1995-09-25 2006-05-11 Alstom Verfahren zur schadstoffarmen Vormischverbrennung in Gasturbinenbrennkammern
US5822992A (en) * 1995-10-19 1998-10-20 General Electric Company Low emissions combustor premixer
US5647215A (en) * 1995-11-07 1997-07-15 Westinghouse Electric Corporation Gas turbine combustor with turbulence enhanced mixing fuel injectors
US5778676A (en) * 1996-01-02 1998-07-14 General Electric Company Dual fuel mixer for gas turbine combustor
US6067790A (en) * 1996-01-05 2000-05-30 Choi; Kyung J. Lean direct wall fuel injection method and devices
FR2751054B1 (fr) * 1996-07-11 1998-09-18 Snecma Chambre de combustion anti-nox a injection de carburant de type annulaire
US5916142A (en) * 1996-10-21 1999-06-29 General Electric Company Self-aligning swirler with ball joint
US5927076A (en) * 1996-10-22 1999-07-27 Westinghouse Electric Corporation Multiple venturi ultra-low nox combustor
GB2319078B (en) * 1996-11-08 1999-11-03 Europ Gas Turbines Ltd Combustor arrangement
JP3619626B2 (ja) * 1996-11-29 2005-02-09 株式会社東芝 ガスタービン燃焼器の運転方法
US5961646A (en) 1997-01-02 1999-10-05 Level One Communications, Inc. Method and apparatus employing an invalid symbol security jam for communications network security
US5816049A (en) * 1997-01-02 1998-10-06 General Electric Company Dual fuel mixer for gas turbine combustor
US5899075A (en) * 1997-03-17 1999-05-04 General Electric Company Turbine engine combustor with fuel-air mixer
GB2324147B (en) * 1997-04-10 2001-09-05 Europ Gas Turbines Ltd Fuel-injection arrangement for a gas turbine combuster
EP1009952A4 (fr) * 1997-05-13 2001-05-02 Maxon Corp Bruleur industriel a emissions reduites
EP0986717A1 (fr) * 1997-06-02 2000-03-22 Solar Turbines Incorporated Procede et dispositif d'injection d'un systeme de carburation mixte
WO1999006767A1 (fr) * 1997-07-31 1999-02-11 Siemens Aktiengesellschaft Brûleur
JP3448190B2 (ja) * 1997-08-29 2003-09-16 三菱重工業株式会社 ガスタービンの燃焼器
US6502399B2 (en) * 1997-09-10 2003-01-07 Mitsubishi Heavy Industries, Ltd. Three-dimensional swirler in a gas turbine combustor
US5966937A (en) * 1997-10-09 1999-10-19 United Technologies Corporation Radial inlet swirler with twisted vanes for fuel injector
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
GB9726697D0 (en) * 1997-12-18 1998-02-18 Secr Defence Fuel injector
DE19757189B4 (de) 1997-12-22 2008-05-08 Alstom Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
US6122916A (en) * 1998-01-02 2000-09-26 Siemens Westinghouse Power Corporation Pilot cones for dry low-NOx combustors
US6141967A (en) * 1998-01-09 2000-11-07 General Electric Company Air fuel mixer for gas turbine combustor
GB2333832A (en) * 1998-01-31 1999-08-04 Europ Gas Turbines Ltd Multi-fuel gas turbine engine combustor
DE59810159D1 (de) * 1998-02-26 2003-12-18 Alstom Switzerland Ltd Verfahren zum sicheren Entfernen von Flüssigbrennstoff aus dem Brennstoffsystem einer Gasturbine sowie Vorrichtung zur Durchführung des Verfahrens
US6082113A (en) * 1998-05-22 2000-07-04 Pratt & Whitney Canada Corp. Gas turbine fuel injector
US6289676B1 (en) * 1998-06-26 2001-09-18 Pratt & Whitney Canada Corp. Simplex and duplex injector having primary and secondary annular lud channels and primary and secondary lud nozzles
US6119459A (en) * 1998-08-18 2000-09-19 Alliedsignal Inc. Elliptical axial combustor swirler
EP0994300B1 (fr) 1998-10-14 2003-11-26 ALSTOM (Switzerland) Ltd Brûleur pour la conduite d'un générateur de chaleur
ITMI991204A1 (it) * 1999-05-31 2000-12-01 Nuovo Pignone Spa Iniettore di combustibile liquido per bruciatori in turbine a gas
JP3364169B2 (ja) * 1999-06-09 2003-01-08 三菱重工業株式会社 ガスタービン及びその燃焼器
IT1313547B1 (it) * 1999-09-23 2002-07-24 Nuovo Pignone Spa Camera di premiscelamento per turbine a gas
EP1096201A1 (fr) * 1999-10-29 2001-05-02 Siemens Aktiengesellschaft Brûleur
JP2001263143A (ja) * 2000-03-16 2001-09-26 Hitachi Ltd 内燃機関の制御装置
US6481209B1 (en) * 2000-06-28 2002-11-19 General Electric Company Methods and apparatus for decreasing combustor emissions with swirl stabilized mixer
JP2002031343A (ja) 2000-07-13 2002-01-31 Mitsubishi Heavy Ind Ltd 燃料噴出部材、バーナ、燃焼器の予混合ノズル、燃焼器、ガスタービン及びジェットエンジン
US6367262B1 (en) * 2000-09-29 2002-04-09 General Electric Company Multiple annular swirler
US6675583B2 (en) * 2000-10-04 2004-01-13 Capstone Turbine Corporation Combustion method
US6460345B1 (en) * 2000-11-14 2002-10-08 General Electric Company Catalytic combustor flow conditioner and method for providing uniform gasvelocity distribution
DE10056243A1 (de) * 2000-11-14 2002-05-23 Alstom Switzerland Ltd Brennkammer und Verfahren zum Betrieb dieser Brennkammer
US6453660B1 (en) * 2001-01-18 2002-09-24 General Electric Company Combustor mixer having plasma generating nozzle
US6539724B2 (en) * 2001-03-30 2003-04-01 Delavan Inc Airblast fuel atomization system
US20020162333A1 (en) * 2001-05-02 2002-11-07 Honeywell International, Inc., Law Dept. Ab2 Partial premix dual circuit fuel injector
GB2375601A (en) 2001-05-18 2002-11-20 Siemens Ag Burner apparatus for reducing combustion vibrations
US6418726B1 (en) * 2001-05-31 2002-07-16 General Electric Company Method and apparatus for controlling combustor emissions
US6655145B2 (en) * 2001-12-20 2003-12-02 Solar Turbings Inc Fuel nozzle for a gas turbine engine
FR2836986B1 (fr) 2002-03-07 2004-11-19 Snecma Moteurs Systeme d'injection multi-modes d'un melange air/carburant dans une chambre de combustion
EP1499800B1 (fr) * 2002-04-26 2011-06-29 Rolls-Royce Corporation Module de premelange de combustible pour chambre de combustion de turbine a gaz
DE50313028D1 (de) * 2002-05-02 2010-10-14 Alstom Technology Ltd Katalytischer Brenner
DE50307654D1 (de) * 2002-05-16 2007-08-23 Alstom Technology Ltd Vormischbrenner
US6735949B1 (en) 2002-06-11 2004-05-18 General Electric Company Gas turbine engine combustor can with trapped vortex cavity
US6675581B1 (en) * 2002-07-15 2004-01-13 Power Systems Mfg, Llc Fully premixed secondary fuel nozzle
US6722132B2 (en) 2002-07-15 2004-04-20 Power Systems Mfg, Llc Fully premixed secondary fuel nozzle with improved stability and dual fuel capability
US6691516B2 (en) 2002-07-15 2004-02-17 Power Systems Mfg, Llc Fully premixed secondary fuel nozzle with improved stability
GB0219461D0 (en) 2002-08-21 2002-09-25 Rolls Royce Plc Fuel injection arrangement
US6705087B1 (en) 2002-09-13 2004-03-16 Siemens Westinghouse Power Corporation Swirler assembly with improved vibrational response
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
ES2309128T3 (es) 2002-09-20 2008-12-16 Siemens Aktiengesellschaft Quemador premezclado con corriente masica de aire perfilada, turbina de gas y procedimiento para quemar combustible en aire.
US6986255B2 (en) 2002-10-24 2006-01-17 Rolls-Royce Plc Piloted airblast lean direct fuel injector with modified air splitter
US6866503B2 (en) 2003-01-29 2005-03-15 Air Products And Chemicals, Inc. Slotted injection nozzle and low NOx burner assembly
US6898926B2 (en) 2003-01-31 2005-05-31 General Electric Company Cooled purging fuel injectors
DE10326720A1 (de) 2003-06-06 2004-12-23 Rolls-Royce Deutschland Ltd & Co Kg Brenner für eine Gasturbinenbrennkammer
JP4065947B2 (ja) 2003-08-05 2008-03-26 独立行政法人 宇宙航空研究開発機構 ガスタービン燃焼器用燃料・空気プレミキサー
DE10340826A1 (de) * 2003-09-04 2005-03-31 Rolls-Royce Deutschland Ltd & Co Kg Homogene Gemischbildung durch verdrallte Einspritzung des Kraftstoffs
DE502005003648D1 (de) * 2004-02-12 2008-05-21 Alstom Technology Ltd Vormischbrenneranordnung zum betreiben einer brennkammer sowie verfahren zum betreiben einer brennkammer
DE112004002704B4 (de) * 2004-03-03 2011-04-07 Mitsubishi Heavy Industries, Ltd. Verbrennungsanlage
US7065972B2 (en) 2004-05-21 2006-06-27 Honeywell International, Inc. Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions
US6993916B2 (en) 2004-06-08 2006-02-07 General Electric Company Burner tube and method for mixing air and gas in a gas turbine engine
US6968255B1 (en) 2004-10-22 2005-11-22 Pulse Microsystems, Ltd. Method and system for automatically deriving stippling stitch designs in embroidery patterns
DE102005062079A1 (de) * 2005-12-22 2007-07-12 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner mit einer Zerstäuberlippe
DE102007015311A1 (de) 2006-03-31 2007-10-04 Alstom Technology Ltd. Verfahren zum Betrieb einer Gasturbine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4445339A (en) 1980-11-24 1984-05-01 General Electric Co. Wingtip vortex flame stabilizer for gas turbine combustor flame holder
US6272840B1 (en) 2000-01-13 2001-08-14 Cfd Research Corporation Piloted airblast lean direct fuel injector
US20020011064A1 (en) 2000-01-13 2002-01-31 Crocker David S. Fuel injector with bifurcated recirculation zone
US6543235B1 (en) 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
US20040040311A1 (en) 2002-04-30 2004-03-04 Thomas Doerr Gas turbine combustion chamber with defined fuel input for the improvement of the homogeneity of the fuel-air mixture
WO2005028526A1 (fr) 2003-08-13 2005-03-31 Societe De Technologie Michelin Système catalytique pour l'obtention de copolymères diène(s) conjugué(s) / mono-oléfine(s) et ces copolymères
US20060248898A1 (en) 2005-05-04 2006-11-09 Delavan Inc And Rolls-Royce Plc Lean direct injection atomizer for gas turbine engines

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102639939A (zh) * 2009-11-30 2012-08-15 西门子公司 燃烧器装置
CN102639939B (zh) * 2009-11-30 2014-11-12 西门子公司 燃烧器装置
US9103552B2 (en) 2009-11-30 2015-08-11 Siemens Aktiengesellschaft Burner assembly including a fuel distribution ring with a slot and recess
EP2549183A1 (fr) * 2011-07-20 2013-01-23 Rolls-Royce plc Injecteur de carburant
US9285122B2 (en) 2011-07-20 2016-03-15 Rolls-Royce Plc Fuel injector
EP2703720A3 (fr) * 2012-08-28 2017-12-27 Rolls-Royce Deutschland Ltd & Co KG Procédé de fonctionnement d'un brûleur à prémélange maigre d'une turbine à gaz pour l'aéronautique et dispositif permettant de réaliser le procédé
CN116624890A (zh) * 2023-06-21 2023-08-22 清华大学 火焰稳定器、燃烧室及火焰稳定方法

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US20090139240A1 (en) 2009-06-04
DE102007043626A1 (de) 2009-03-19
US8646275B2 (en) 2014-02-11
EP2037172B1 (fr) 2014-04-02
EP2037172A3 (fr) 2012-09-26

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