EP0902233A1 - Buse de pulvérisation par pression combinée - Google Patents

Buse de pulvérisation par pression combinée Download PDF

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Publication number
EP0902233A1
EP0902233A1 EP97810662A EP97810662A EP0902233A1 EP 0902233 A1 EP0902233 A1 EP 0902233A1 EP 97810662 A EP97810662 A EP 97810662A EP 97810662 A EP97810662 A EP 97810662A EP 0902233 A1 EP0902233 A1 EP 0902233A1
Authority
EP
European Patent Office
Prior art keywords
feed channel
fuel
atomizing nozzle
nozzle
pressure atomizing
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
EP97810662A
Other languages
German (de)
English (en)
Other versions
EP0902233B1 (fr
Inventor
Franz Büchi
Uwe Hoferer
Peter Dr. Jansohn
Christian Dr. Steinbach
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Switzerland GmbH
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by ABB Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Priority to EP97810662A priority Critical patent/EP0902233B1/fr
Priority to DE59709510T priority patent/DE59709510D1/de
Priority to JP26027598A priority patent/JP4124296B2/ja
Priority to US09/152,515 priority patent/US6378787B1/en
Priority to CNB981192742A priority patent/CN1153922C/zh
Publication of EP0902233A1 publication Critical patent/EP0902233A1/fr
Application granted granted Critical
Publication of EP0902233B1 publication Critical patent/EP0902233B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • F23L7/002—Supplying water
    • 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
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • F23D11/26—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space with provision for varying the rate at which the fuel is sprayed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means

Definitions

  • the invention relates to a combined pressure atomizer nozzle operated with liquid fuel for gas turbine burners, according to the preamble of claim 1.
  • the penetration depth of the fuel spray into the combustion air is mainly due to influences the ratio of the pulse flows of combustion air and fuel. This ratio changes with the operating conditions, i.e. as a result of changes in the fuel mass flow, in the fuel pressure and in the temperature and the pressure of the burner air.
  • the evaporation time of the fuel depends essentially of the atomization quality, the relative speed between Fuel and air as well as the ambient conditions such as temperature and pressure off. While the latter for the different load conditions the gas turbine process are specified, the atomization quality and the relative speed is mainly determined by the atomizing nozzle.
  • DE-PS 862 599 is a combined two- or multi-stage swirl atomizer is known, but an impulse behavior unsuitable for gas turbine burners having.
  • the resulting swirl spray does indeed produce very fine atomization reached, but the fuel pulse is too small to distribute sufficiently the fuel droplets in the combustion air and thus a good premix to achieve.
  • the invention tries to avoid these disadvantages. It is based on the task to create a combined pressure atomizing nozzle for gas turbine burners, with an improved adjustment of the atomization quality of liquids to the respective load conditions, i.e. a good premix throughout Load range can be realized.
  • the second feed channel at least two outlet openings to the outside space.
  • the combined pressure atomizer nozzle designed as a multi-hole orifice nozzle with a simple, central nozzle, which besides the fine atomization of the liquid fuel also one high fuel pulse guaranteed.
  • both rapid evaporation of the liquid fuel as well as a good premix of the fuel spray can be achieved with the combustion air, which is why the inventive Pressure atomizer nozzle, especially for gas turbine burners suitable is.
  • a relatively simple pressure atomizer nozzle created with a small footprint, the two-tier only by the additional Introducing the outlet openings of the second feed channel is realized.
  • outlet openings of the second feed channel are evenly distributed on the circumference of the nozzle body. This arrangement ensures a uniform fuel concentration in the reaction zone and therefore prevents the increased formation of nitrogen oxides.
  • the first feed channel is inside a first tube and the second feed channel formed inside a second tube. Both tubes are concentric arranged to each other and are downstream from a cover to the outside completed. The cover and the first tube are made in one piece. As a result, the pressure atomizing nozzle can be installed relatively easily, by placing the second tube up to its stop on the lid on the first tube is postponed. Then the second tube and the lid become firm connected to one another, for example by welding.
  • a turbulence chamber is formed.
  • the Turbulence chamber is from the second feed channel separated by a partition. In the partition are off-center arranged at least two turbulence generator openings of the second feed channel.
  • the turbulence generator openings are particularly advantageously offset from the outlet openings arranged of the second feed channel.
  • the displacement is preferably with four turbulence generator openings or outlet openings about 45 °, so the arrangement of the turbulence openings takes place exactly in the middle between the outlet openings. This leads to a more intense, small-scale and turbulent structure, i.e. to a very fine fuel spray.
  • the pressure atomizing nozzle with the additional turbulence chamber can also be installed relatively easily.
  • the lid is the first
  • the tube and the partition are made in one piece, so that these components together, to some extent as an insert, are inserted into the second tube can.
  • the first tube and the lid for example by welding, firmly connected.
  • An alternative to a simple, central nozzle is between the first feed channel and the outlet opening either a swirl chamber or a turbulence chamber educated.
  • a swirl spray is used generated with a relatively wide spray cone, so that even at partial load high fuel concentration in the center of the burner and sufficient Evaporation of the fuel can be achieved.
  • This also enables in the partial load range the gas turbine has a stable burner operation.
  • becomes a turbulence nozzle used as a central nozzle it can with good atomization a narrower spray angle of the liquid fuel can be realized. On in this way the fuel concentration in the center of the burner can be further increased and thereby the burner operation can be additionally stabilized at partial load.
  • the pressure atomizer nozzle for example, is not shown Gas turbine burner.
  • the direction of flow of the work equipment is indicated by arrows.
  • the gas turbine burner, not shown, which receives the pressure atomizing nozzle is designed, for example, as a double cone burner, as it is from the EP-B1-0 321 809 is known.
  • the pressure atomizer nozzle is in principle also suitable for other gas turbine burners, e.g. for the from the EP-A2-0 704 657 known, from a swirl generator with a subsequent mixing section existing burner.
  • the pressure atomizing nozzle has a nozzle body 1 two concentrically arranged tubes 2, 3, which are downstream of one conical cover 4 to an outside space 5 can be completed.
  • the nozzle body 1 has a longitudinal axis 6, which with the longitudinal axis of the gas turbine burner, not shown, coincides.
  • the first, inner tube 2 encloses a first, inner feed channel 7 to which connects a swirl chamber 8 downstream.
  • the swirl chamber 8 is on the outside from inner tube 2, downstream of the cover 4 and upstream by an insert 9 (Fig. 1). It stands with the inner feed channel 7 above, arranged in the insert 9, tangential swirl channels 10 (FIG. 2) and with the outer space 5 via an outlet opening 11 in connection.
  • the outlet opening 11 is in the Longitudinal axis 6 of the nozzle body 1 is arranged.
  • the second, outer tube 3 has a larger diameter than the inner tube 2, so that between two tubes 3, 2, a second, outer and designed as an annular feed channel 12 is arranged. The latter is via four outlet openings located in the cover 4 13 also connected to the outside space 5.
  • the outlet openings 13 are evenly distributed over the circumference of the nozzle body 1 (FIG. 3) and so aligned that they are in the wake of the swirl generator of the not shown Inject the burner.
  • the exact orientation depends on the boundary conditions of the Gas turbine. It should be noted that the number of outlet openings 13 is not set to four, however, must be for even fuel distribution at least two outlet openings 13 are present.
  • Pressure atomizer nozzle is particularly suitable for swirl generators with a conical shape suitable.
  • the cover 4 and the inner tube 2 of the nozzle body 1 are formed in one piece. As a result, the entire pressure atomizing nozzle can be assembled relatively easily be by the outer tube 3 up to its stop on the lid 4 on the inner tube 2 is pushed on. Then the outer tube 3 and the lid 4 welded together.
  • the pressure atomizing nozzle When operating the gas turbine burner, the pressure atomizing nozzle is considered to be atomized Liquid 14 is a liquid fuel, for example fuel oil.
  • the Liquid fuel 14 to the gas turbine burner either via the outer feed channel 12 or via the inner feed channel 7 of the pressure atomizing nozzle.
  • the Nozzle body 1 thus has two different nozzles, namely an outer one Multi-hole orifice nozzle and a central swirl nozzle.
  • the liquid fuel 14 is in the inner feed channel 7 of the nozzle body 1 introduced from where it swirls through the swirl channels 10 into the swirl chamber 8 arrives.
  • the liquid fuel 14 is then passed through the outlet opening 11 injected into the outer space 5, the swirl nozzle being a swirl spray 15 generated with a relatively wide spray cone 16 (Fig. 4).
  • This also applies to Partial load a high fuel concentration in the center of the burner and a sufficient evaporation of the fuel is achieved. This also enables in Partial load range of the gas turbine stable burner operation.
  • the liquid fuel is supplied centrally 14 over the center and completely from the outer feed channel 12 surrounded, inner feed channel 7.
  • the inner feed channel 7 also arranged off-center and / or only partially from the outside Supply channel 12 are surrounded so that the liquid fuel 14 is decentralized, however reaches the swirl nozzle with the same effect (not shown).
  • the injection pressure should be up to 100 bar.
  • the maximum mass flow of liquid fuel 14 will be covered depending on Load range of the gas turbine selected and is usually less than 50% of the mass flow at full load.
  • the gas turbine burner can also Work part load of the gas turbine in premix mode.
  • the liquid fuel 14 is at full load in the outer feed channel 12 of the nozzle body 1 is inserted and passes through its outlet openings 13 into the outside space 5.
  • the multi-hole orifice nozzle several fuel sprays corresponding to the number of outlet openings 13 17 each with a relatively narrow spray cone 18 (Fig. 1).
  • the separate fuel sprays 17 have a high momentum and also have a high relative speed of the liquid fuel 14 to the combustion air. Therefore the multi-hole orifice nozzle atomizes the liquid fuel well 14.
  • the liquid fuel 14 reaches a high depth of penetration into the combustion air, which leads to a significantly improved mixing quality.
  • the now improved penetration depth of the liquid fuel 14 in full load operation there are no problems with partial load from wall application of Droplets of fuel oil, because then it is switched to the central swirl nozzle.
  • Gas turbine burners can both use several different liquid fuels 31 as well as with a liquid fuel 31 and with water 29, with only a liquid fuel 31 or with liquid fuel-water mixtures operate. They therefore allow a relatively wide range of applications and can be adapted to changing operating conditions.
  • the central swirl nozzle is in operation of the multi-hole orifice nozzle constantly by the latter flows around the liquid 14, 31. Therefore, when switching from Full to partial load, such as e.g. in the event of a loss of load, no cooling of the Swirl nozzle required so that a quick load change can be guaranteed can.
  • a turbulence chamber 32 is formed.
  • the turbulence chamber 32 is from the outer feed channel 12 through an intermediate wall 33 separated.
  • In the intermediate wall 33 are eccentric of the outer Feed channel 12 formed four turbulence generator openings 34 (Fig. 7).
  • the turbulence generator openings are 34, based on the main flow direction of the liquid fuel 14, at an angle of 45 ° to the outlet openings 13 of the outer feed channel 12 is arranged.
  • This is one of the turbulence generator openings 34 in the middle between two adjacent outlet openings 13 arranged.
  • the turbulent structure of the Liquid fuel 14 on the one hand more intensive and on the other hand small-scale. Therefore a turbulent, rapidly disintegrating free jet emerges from the multi-hole orifice nozzle out.
  • a number other than four outlet openings 13 can also be used or turbulence generator openings 34 can be realized, in which case the described Angle changes accordingly.
  • the cover 4, the inner tube 2 and the intermediate wall 33 of the nozzle body 1 are formed in one piece (Fig. 7). This also enables this pressure atomizing nozzle can be assembled relatively easily by the outer tube 3 up to its Stop on the cover 4 is pushed onto the inner tube 2. Subsequently the outer tube 3 with both the cover 4 and the partition 33 welded.
  • the outlet openings 13 have of the outer feed channel 12 has a radial outlet direction 35 (FIG. 10, FIG. 11), which is particularly suitable for axial swirl generators.
  • a radial outlet direction 35 (FIG. 10, FIG. 11)
  • axially parallel Inflow to the pressure atomizing nozzle leads to a very high Penetration depth of the fuel spray 17 into the combustion air and thus to one additional improvement of the premixing of the gas turbine burner.
  • Embodiment turbulence channels 36 arranged in the insert 9. These lead to into a turbulence chamber 37, which in turn is connected via the outlet opening 11 is connected to the outside space 5 (FIG. 12). During partial load operation, this is off a multi-hole orifice and a central turbulence nozzle Pressure atomizer nozzle becomes a rapidly disintegrating fuel spray 38 with a particularly narrow spray cone 39 generated. This can reduce the fuel concentration further increased in the center of the burner even at part load of the gas turbine become.
  • the pressure atomizing nozzle can also be designed without an insert 9 so that the first feed channel 7 extends directly to the cover 4 (FIG. 13).
  • a particularly simple, central nozzle with a small one is created Space requirements and an essentially analogous function to that of the central one Nozzles of the exemplary embodiments described above.
  • a third Pipe 40 arranged, which ends upstream of the outlet opening 11 and the inner feed channel 7 receives.
  • the first and the third tube 2, 40 are from each other spaced, so that between them a space designed as an air duct 41 arises.
  • the air duct 41 widens downstream of the third pipe 40 to a mixing space 42 into which the feed channel 7 opens (FIG. 14).
  • this central nozzle is via a feed line, not shown, and the Air duct 41 air 43 brought up.
  • the air 43 hits the liquid fuel 14, which leads to its air-assisted injection into the outside space 5 of the pressure atomizing nozzle, i.e. into the interior of the gas turbine burner, is coming. This makes the required atomization quality independent of current fuel throughput is reached, which is particularly the case with partial load operation of Advantage is.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP97810662A 1997-09-15 1997-09-15 Buse de pulvérisation par pression combinée Expired - Lifetime EP0902233B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP97810662A EP0902233B1 (fr) 1997-09-15 1997-09-15 Buse de pulvérisation par pression combinée
DE59709510T DE59709510D1 (de) 1997-09-15 1997-09-15 Kombinierte Druckzerstäuberdüse
JP26027598A JP4124296B2 (ja) 1997-09-15 1998-09-14 ガスタービンバーナ用の複合式圧力噴霧ノズル
US09/152,515 US6378787B1 (en) 1997-09-15 1998-09-14 Combined pressure atomizing nozzle
CNB981192742A CN1153922C (zh) 1997-09-15 1998-09-15 组合式压力雾化喷嘴

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810662A EP0902233B1 (fr) 1997-09-15 1997-09-15 Buse de pulvérisation par pression combinée

Publications (2)

Publication Number Publication Date
EP0902233A1 true EP0902233A1 (fr) 1999-03-17
EP0902233B1 EP0902233B1 (fr) 2003-03-12

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810662A Expired - Lifetime EP0902233B1 (fr) 1997-09-15 1997-09-15 Buse de pulvérisation par pression combinée

Country Status (5)

Country Link
US (1) US6378787B1 (fr)
EP (1) EP0902233B1 (fr)
JP (1) JP4124296B2 (fr)
CN (1) CN1153922C (fr)
DE (1) DE59709510D1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2347205A (en) * 1998-12-30 2000-08-30 Abb Alstom Power Ch Ag Atomizing device
WO2006042796A2 (fr) * 2004-10-18 2006-04-27 Alstom Technology Ltd Bruleur pour turbine a gaz
DE102010009051A1 (de) * 2010-02-23 2011-08-25 Deutsches Zentrum für Luft- und Raumfahrt e.V., 51147 Brennstoffzuführungseinrichtung
DE102011116317A1 (de) * 2011-10-18 2013-04-18 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner eines Fluggasturbinentriebwerks
AT521116A1 (de) * 2018-04-10 2019-10-15 Cs Comb Solutions Gmbh Zerstäubungsdüse
CN111878848A (zh) * 2020-08-11 2020-11-03 新奥能源动力科技（上海）有限公司 一种喷嘴及燃烧室

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WO2007051705A1 (fr) * 2005-11-04 2007-05-10 Alstom Technology Ltd Lance à combustible
US8500044B2 (en) * 2007-05-04 2013-08-06 S.C. Johnson & Son, Inc. Multiple nozzle differential fluid delivery head
FR2914397B1 (fr) * 2007-03-26 2009-05-01 Saint Gobain Emballage Sa Injecteur a jet creux de combustible liquide.
DE102007021927A1 (de) * 2007-05-10 2008-11-20 Siemens Ag Ölvergasungsbrenner für aschefreien Flüssigbrennstoff
US8820664B2 (en) 2007-05-16 2014-09-02 S.C. Johnson & Son, Inc. Multiple nozzle differential fluid delivery head
US9242256B2 (en) * 2007-07-17 2016-01-26 S.C. Johnson & Son, Inc. Aerosol dispenser assembly having VOC-free propellant and dispensing mechanism therefor
GB0803959D0 (en) * 2008-03-03 2008-04-09 Pursuit Dynamics Plc An improved mist generating apparatus
US8272218B2 (en) * 2008-09-24 2012-09-25 Siemens Energy, Inc. Spiral cooled fuel nozzle
US8161751B2 (en) * 2009-04-30 2012-04-24 General Electric Company High volume fuel nozzles for a turbine engine
US8783585B2 (en) * 2009-05-20 2014-07-22 General Electric Company Methods and systems for mixing reactor feed
US8196408B2 (en) * 2009-10-09 2012-06-12 General Electric Company System and method for distributing fuel in a turbomachine
CN101982243B (zh) * 2010-10-22 2014-07-23 合肥辰泰安全设备有限责任公司 一种旋射流雾化喷头
US9217570B2 (en) * 2012-01-20 2015-12-22 General Electric Company Axial flow fuel nozzle with a stepped center body
DE102012201178B3 (de) * 2012-01-27 2013-02-14 Aptar Radolfzell Gmbh Düseneinheit und Spender mit einer solchen
CN102580866A (zh) * 2012-03-29 2012-07-18 李燕 一种高压喷嘴及具有该高压喷嘴的用水清洗油污的喷头
CN103316793B (zh) * 2013-06-19 2016-07-06 安徽艾可蓝节能环保科技有限公司 一种气助式雾化喷嘴
CN105705863B (zh) * 2013-11-08 2019-03-15 通用电气公司 用于燃料喷嘴的液体燃料筒
CN103623946B (zh) * 2013-11-29 2016-06-01 柳州化工股份有限公司 粉煤气化耐高温吹灰喷头及制作方法
JP6452298B2 (ja) * 2014-03-25 2019-01-16 三菱日立パワーシステムズ株式会社 噴射ノズル、ガスタービン燃焼器及びガスタービン
EP3180565B1 (fr) 2014-08-14 2019-04-17 Siemens Aktiengesellschaft Injecteur de carburant multifonctionnel avec un atomiseur à orifice double
WO2016024977A1 (fr) * 2014-08-14 2016-02-18 Siemens Aktiengesellschaft Injecteur de carburant multifonction muni d'un ensemble de pulvérisateurs
JP6100295B2 (ja) * 2015-03-02 2017-03-22 三菱日立パワーシステムズ株式会社 燃料ノズル、これを備えた燃焼器及びガスタービン
EP3088802A1 (fr) * 2015-04-29 2016-11-02 General Electric Technology GmbH Buse pour un lobe de combustion de turbine a gaz
KR101853464B1 (ko) * 2015-06-22 2018-06-04 두산중공업 주식회사 실링구조를 포함하는 연료공급노즐.
DE102017101167A1 (de) * 2017-01-23 2018-07-26 Man Diesel & Turbo Se Brennkammer einer Gasturbine, Gasturbine und Verfahren zum Betreiben derselben
DE102017114362A1 (de) * 2017-06-28 2019-01-03 Man Diesel & Turbo Se Brennkammer einer Gasturbine, Gasturbine und Verfahren zum Betreiben derselben
KR102046457B1 (ko) 2017-11-09 2019-11-19 두산중공업 주식회사 연소기 및 이를 포함하는 가스 터빈
WO2020049861A1 (fr) * 2018-09-06 2020-03-12 株式会社Ihi Injecteur de combustible liquide
CN109833985B (zh) * 2019-03-14 2020-09-04 重庆川仪调节阀有限公司 减温阀的雾化喷嘴结构

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EP0704657A2 (fr) 1994-10-01 1996-04-03 ABB Management AG Brûleur
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Publication number Priority date Publication date Assignee Title
DE324589C (de) * 1916-11-19 1920-09-01 Rudolf Wagner Dr Schleuderzerstaeuberkopf
DE862599C (de) 1950-11-03 1953-01-12 Paul Lechler Fa Zerstaeuber zum gleichzeitigen Zerstaeuben mehrerer Stoffe
US3785570A (en) * 1972-08-30 1974-01-15 Us Army Dual orifice fuel nozzle with air-assisted primary at low flow rates
FR2234931A1 (fr) * 1973-06-27 1975-01-24 Shell Int Research
FR2403517A1 (fr) * 1977-09-16 1979-04-13 Charmilles Sa Ateliers Injecteur pour la pulverisation sous pression de combustible liquide
EP0321809B1 (fr) 1987-12-21 1991-05-15 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
EP0704657A2 (fr) 1994-10-01 1996-04-03 ABB Management AG Brûleur
EP0711953A2 (fr) 1994-11-12 1996-05-15 Abb Research Ltd. Brûleur à prémélange

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2347205A (en) * 1998-12-30 2000-08-30 Abb Alstom Power Ch Ag Atomizing device
GB2347205B (en) * 1998-12-30 2003-03-19 Abb Alstom Power Ch Ag Atomizing device
WO2006042796A2 (fr) * 2004-10-18 2006-04-27 Alstom Technology Ltd Bruleur pour turbine a gaz
WO2006042796A3 (fr) * 2004-10-18 2006-08-10 Alstom Technology Ltd Bruleur pour turbine a gaz
US7520745B2 (en) 2004-10-18 2009-04-21 Alstom Technology Ltd. Burner for a gas turbine
DE102010009051A1 (de) * 2010-02-23 2011-08-25 Deutsches Zentrum für Luft- und Raumfahrt e.V., 51147 Brennstoffzuführungseinrichtung
DE102011116317A1 (de) * 2011-10-18 2013-04-18 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner eines Fluggasturbinentriebwerks
AT521116A1 (de) * 2018-04-10 2019-10-15 Cs Comb Solutions Gmbh Zerstäubungsdüse
AT521116B1 (de) * 2018-04-10 2020-03-15 Cs Comb Solutions Gmbh Zerstäubungsdüse
CN111878848A (zh) * 2020-08-11 2020-11-03 新奥能源动力科技（上海）有限公司 一种喷嘴及燃烧室

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Publication number Publication date
CN1211703A (zh) 1999-03-24
DE59709510D1 (de) 2003-04-17
US6378787B1 (en) 2002-04-30
JP4124296B2 (ja) 2008-07-23
JPH11159757A (ja) 1999-06-15
EP0902233B1 (fr) 2003-03-12
CN1153922C (zh) 2004-06-16

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