EP0095788B1 - Brennkammer einer Gasturbine und Verfahren zu deren Betrieb - Google Patents

Brennkammer einer Gasturbine und Verfahren zu deren Betrieb Download PDF

Info

Publication number
EP0095788B1
EP0095788B1 EP83200492A EP83200492A EP0095788B1 EP 0095788 B1 EP0095788 B1 EP 0095788B1 EP 83200492 A EP83200492 A EP 83200492A EP 83200492 A EP83200492 A EP 83200492A EP 0095788 B1 EP0095788 B1 EP 0095788B1
Authority
EP
European Patent Office
Prior art keywords
fuel
combustion
elements
diffusion
approximately
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.)
Expired
Application number
EP83200492A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0095788A1 (de
Inventor
Eduard Brühwiler
Hans Koch
Gerald A. Roffe
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.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
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 BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0095788A1 publication Critical patent/EP0095788A1/de
Application granted granted Critical
Publication of EP0095788B1 publication Critical patent/EP0095788B1/de
Expired legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D23/00—Assemblies of two or more burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • 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
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners

Definitions

  • the invention relates to the combustion chamber of a gas turbine according to the preamble of claim 1. It also relates to a method for starting and loading such a combustion chamber.
  • a combustion chamber of the type mentioned at the outset without water or steam injection is known from DE-A No. 2950535.
  • this optimization process can be driven in the direction of even lower NO x values in such a way that the space for combustion and after-reactions is kept much longer than would be necessary for the actual combustion.
  • This allows a larger excess air number to be selected, which initially produces larger amounts of CO, but can react further to CO 2 , so that ultimately the CO emissions remain small.
  • due to the large excess of air little additional NO is formed. Since several tubular elements take over the pre-mixing / pre-evaporation, only so many elements are operated with fuel in the load control that the optimum excess air number results for the respective operating phase (start, partial load, etc.).
  • the invention seeks to remedy this.
  • the object of the invention is to raise the stability limit in the entire operating range in a combustion chamber of the type mentioned at the outset in such a way that extinguishing of the flame is avoided with certainty.
  • the inventive solution to this problem is characterized in claim 1.
  • the advantage of the invention can essentially be seen in the fact that a means is provided in a relatively simple manner to keep the combustion at all times within the ignition limits by appropriately distributing the fuel to the premixing or diffusion nozzles.
  • the fact that the use of previous pilot burners can be dispensed with also has a particularly favorable effect.
  • combustion chamber is driven according to a fuel control curve, as defined in claims 4 or 6, and if the burners are gradually ignited from the inside to the outside, there is a combustion in addition to the required flame stability, in which the CO emissions are far greater have better values than can be achieved, for example, with the combustion chamber mentioned at the beginning.
  • FIG. 1 shows, in a highly simplified manner, the design of a combustion chamber with the fuel supply according to the invention.
  • a larger number of tubular elements 2 are arranged in the upper area of the combustion chamber casing 1, which optimally fill the available space.
  • FIG. 2 An example of such an arrangement is shown in which 36 tubular elements 2 are arranged around a central pilot burner 5. The number is not mandatory, however, because it depends on the size of the combustion chamber, which in turn is dependent on the desired combustion output.
  • a support bridge 27, with which the tubular elements 2 are connected by means of suitable means, is anchored to a support rib 23.
  • the tubular elements 2 are guided laterally in the middle of their longitudinal extent by means of a guide plate 6.
  • the tubular elements 2 can also be anchored differently than with the support bridge 27 shown; In such cases, however, it will always be necessary to ensure that the selected anchorage is placed as far as possible from the combustion chamber 7 so that the thermal expansions cannot develop a disruptive effect.
  • the greater part of the compressed air quantity flows through the openings 9 into a distribution chamber 19 provided in the combustion chamber shell, which is delimited downwards by the support bridge 27 and upwards by the cover 35 flanged by the flange rib 38 becomes. From this distribution chamber 19, the compressed air then flows through the air funnels 14 into the individual tubular elements 2.
  • the fuel supply is provided for each tubular element 2 by a fuel line 4, a fuel nozzle 15 ′ projecting into the tubular element 2 providing the atomization of the oil and a fuel nozzle 15 ′′ blowing gas.
  • the fuel mixes with the inflowing compressed air in such a way that A pre-mixing / pre-evaporation process takes place in the tubular element 2.
  • the fuel evaporates and mixes with the air.
  • the degree of evaporation is stronger, the greater the temperature and the residence time and the smaller the drop size of the atomized fuel.
  • the critical time until the mixture self-ignites decreases, so that the length of the tubular elements 2 is coordinated in such a way that the best possible evaporation results for the shortest possible time.
  • gas there is no evaporation; the gas only needs to be distributed evenly with the air.
  • the flame holder 3 which forms the end of the downstream part of the tubular elements 2, has the task of preventing the flame from reigniting from the combustion chamber 7 into the interior of the tubular element 2. It is preferably provided with a swirl body 28, the mixture of which is directed to the combustion chamber 7 in a swirling manner through its openings.
  • the swirl body 28 favors a stable flame and good heat distribution due to the backflow occurring downstream in its center, which results in a homogeneous temperature and speed distribution after the combustion chamber 7 with the effect that the turbine, not shown, is acted upon uniformly. So far combustion chambers are known.
  • a diffusion nozzle 8 is now arranged within the flame holder 3 of each element 2 and injects the fuel directly into the combustion chamber 7.
  • This nozzle 8 is intended for both oil and gas operation. It is designed in such a way that the start-up in oil operation can only be carried out with diffusion combustion, i.e. it can process the entire amount of oil supplied to element 2. Because of the different volume ratios in gas operation, it is only possible to process about 50% of the total amount of gas supplied to an element 2 with the flow cross-section of the nozzle 8 unchanged.
  • FIG. 3 A simplified schematic diagram of the fuel supply is shown in FIG. 3.
  • the fuel depending on the operating mode oil or gas, is fed into a swirl chamber 11 via a central line 10.
  • the atomizing air is guided in an annular space 12 enveloping the central line 10 and reaches the chamber 11 via openings 13.
  • the mixture is injected into the combustion chamber 7 via a commercially available diffusion nozzle 8.
  • the diffusion nozzle is cooled by an air flow which is removed from the annular space 12 upstream of the swirl chamber 11 via a bore 16 and is guided in an annular chamber 17 which is delimited on the outside by a sleeve 18.
  • the swirl bodies 28 of the flame holder 3 are fastened to this sleeve 18.
  • separate fuel nozzles 15 ′ are each provided for gas and oil operation. respectively 15 ".
  • the decisive factor here is that the oil is expediently introduced into the mixing chamber against the direction of air inflow, while the gas is introduced into or across the direction of the air.
  • a ring line 20 for the fuel oil is arranged around the central line 10 and communicates with an outlet chamber 24 via a bore 21, approximately at half the chamber height.
  • the atomizing air is guided in this area in longitudinal bores 26 which are evenly distributed over the circumference and which open into the annular space 12 already mentioned at their lower end.
  • this annular space 12 communicates with the lower, closed end of the outlet chamber 24 via a bore 29.
  • the outlet chamber 24 is provided at its upper end with an annular nozzle 15 ', via which the mixture against the combustion air in the actual mixing and Evaporation space is injected.
  • the gas premix system is arranged above the oil premix system.
  • the atomizing air that is not required in this area is in turn guided in an annular chamber 30 concentrically surrounding the channels 12 and 20.
  • This annular chamber 30 is surrounded on the outside by a gas chamber 31, from which the fuel gas is blown under pressure into the mixing chamber via the nozzles 15 ′′, perpendicular to the direction of flow of the combustion air.
  • the nozzles 15 'and 15 are dimensioned in such a way that they can process the entire amount of fuel supplied to an element 2.
  • the element arrangement shown in FIG. 2 is taken as a basis and the assumption is made that the elements 2 are only switched on or off in groups.
  • the machine speed n is plotted on the abscissa in [%] and the excess air number ⁇ is plotted on the ordinate.
  • the parameters K z4 , K, a , K 15 , K 12 , K s and K s each represent a number of 24.18 ... 6 elements. It is the optimal switching curve when starting the combustion chamber in oil operation. It goes without saying that premix combustion cannot be carried out here, since when starting the air coming from the compressor is still too cold to cause oil evaporation within the elements 2. The starting process and the low load range are therefore carried out with pure diffusion combustion. Since an excess air ratio of at least 1 is required for combustion, the diagram shows that at least 18 elements are required for starting.
  • the actual switching curve is drawn with a thick line.
  • the combustion chamber is started up with 18 elements.
  • the groups u, v and w are in operation.
  • group w is switched off at 60% speed. This means that the same amount of fuel is now burned in just 15 elements, which lowers the excess air figure.
  • group v is switched off at approx. 92% speed, which causes the excess air figure to drop to 1.2.
  • the fact that the curves in this area do not run continuously is due to the fact that the usual blowing off of compressor air is interrupted here.
  • the NO x limit value can easily be fallen below, but then the stability limit S M is low because of the low flame temperature.
  • the range between ignitability and extinguishing is too narrow to be able to safely run the gas turbine in the full load range.
  • the invention is therefore based on a mixed driving style with diffusion and premix combustion in the load range. That is in each case Proportional oil quantity ratio selected so that a driving style with a sufficient distance from the resulting stability limit S DM is possible. Tests have shown that this is best achieved when 90 to 95% of the fuel is burned according to the premix principle and 5 to 10% of the fuel is burned according to the diffusion principle.
  • the diagram shows a mixed driving style with a 10% diffusion percentage. From idle to 15% load, 1/4 of the available elements are used, ie only with group u in pure diffusion mode. Due to the increase in the fuel oil supply, ⁇ has become so low at 15% load that the element group v has to be switched on again. At 20% load, the premixing system is then put into operation for all elements of groups u and v, which leads to a division of the fuel oil in the above-mentioned ratio. The reduction in fuel at the diffusion nozzles while the amount of air remains the same, causing the excess air figure to rise steeply, as shown in dashed lines.
  • the commissioning of the premix can be represented by reducing the excess air from the value oo (infinite) to the value shown at 20% load, as is shown in dash-dot lines. With this measure, the stability limit falls to the displayed value S DM at 20% load.
  • the further control curve for the load increase is now determined in such a way that the excess air figure is constantly between 1.5 and 2.
  • the diagram in Fig. 6 deals with the optimal fuel control curve in the load range for gas combustion. All sizes shown from 20% load. correspond to those in Fig. 5. Gas operation differs from oil operation only in the starting phase and in the lower load range.
  • the starting process from 20% engine speed to idling (not shown) is already carried out with mixed diffusion / premix combustion and it has proven to be advantageous if the process is carried out with 50% premix and 50% diffusion combustion. This is possible because evaporation and the air temperature required for this are not necessary.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)
  • Spray-Type Burners (AREA)
EP83200492A 1982-05-28 1983-04-07 Brennkammer einer Gasturbine und Verfahren zu deren Betrieb Expired EP0095788B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH329582 1982-05-28
CH3295/82 1982-05-28

Publications (2)

Publication Number Publication Date
EP0095788A1 EP0095788A1 (de) 1983-12-07
EP0095788B1 true EP0095788B1 (de) 1985-12-18

Family

ID=4252890

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83200492A Expired EP0095788B1 (de) 1982-05-28 1983-04-07 Brennkammer einer Gasturbine und Verfahren zu deren Betrieb

Country Status (4)

Country Link
US (1) US4967561A (enrdf_load_stackoverflow)
EP (1) EP0095788B1 (enrdf_load_stackoverflow)
JP (1) JPS58219329A (enrdf_load_stackoverflow)
DE (1) DE3361535D1 (enrdf_load_stackoverflow)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4412315A1 (de) * 1994-04-11 1995-10-12 Abb Management Ag Verfahren und Vorrichtung zum Betreiben der Brennkammer einer Gasturbine

Families Citing this family (80)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60207820A (ja) * 1984-03-26 1985-10-19 ザ　ギヤレツト　コーポレーシヨン 燃料を噴出し霧化する方法およびその装置
EP0193029B1 (de) * 1985-02-26 1988-11-17 BBC Brown Boveri AG Brennkammer für Gasturbinen
EP0204553B1 (en) * 1985-06-07 1989-06-07 Ruston Gas Turbines Limited Combustor for gas turbine engine
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
US4982570A (en) * 1986-11-25 1991-01-08 General Electric Company Premixed pilot nozzle for dry low Nox combustor
DE3766807D1 (de) * 1986-11-25 1991-01-31 Gen Electric Kombinierter diffusions- und vormischpilotbrenner.
CH672541A5 (enrdf_load_stackoverflow) * 1986-12-11 1989-11-30 Bbc Brown Boveri & Cie
JP2528894B2 (ja) * 1987-09-04 1996-08-28 株式会社日立製作所 ガスタ―ビン燃焼器
US5339635A (en) * 1987-09-04 1994-08-23 Hitachi, Ltd. Gas turbine combustor of the completely premixed combustion type
CH680946A5 (enrdf_load_stackoverflow) * 1989-12-19 1992-12-15 Asea Brown Boveri
US5199265A (en) * 1991-04-03 1993-04-06 General Electric Company Two stage (premixed/diffusion) gas only secondary fuel nozzle
US5235814A (en) * 1991-08-01 1993-08-17 General Electric Company Flashback resistant fuel staged premixed combustor
US5261226A (en) * 1991-08-23 1993-11-16 Westinghouse Electric Corp. Topping combustor for an indirect fired gas turbine
US5263325A (en) * 1991-12-16 1993-11-23 United Technologies Corporation Low NOx combustion
US5274991A (en) * 1992-03-30 1994-01-04 General Electric Company Dry low NOx multi-nozzle combustion liner cap assembly
DE4223828A1 (de) * 1992-05-27 1993-12-02 Asea Brown Boveri Verfahren zum Betrieb einer Brennkammer einer Gasturbine
US5410884A (en) * 1992-10-19 1995-05-02 Mitsubishi Jukogyo Kabushiki Kaisha Combustor for gas turbines with diverging pilot nozzle cone
US5323604A (en) * 1992-11-16 1994-06-28 General Electric Company Triple annular combustor for gas turbine engine
US5408825A (en) * 1993-12-03 1995-04-25 Westinghouse Electric Corporation Dual fuel gas turbine combustor
JP2580527B2 (ja) * 1993-12-27 1997-02-12 工業技術院長 液化ｌｐガスを用いるガスタービン燃焼器
IT1273369B (it) * 1994-03-04 1997-07-08 Nuovo Pignone Spa Sistema perfezionato combustione a basse emissioni inquinanti per turbine a gas
US5491970A (en) 1994-06-10 1996-02-20 General Electric Co. Method for staging fuel in a turbine between diffusion and premixed operations
DE69625744T2 (de) * 1995-06-05 2003-10-16 Rolls-Royce Corp., Indianapolis Magervormischbrenner mit niedrigem NOx-Ausstoss für industrielle Gasturbinen
US5822992A (en) * 1995-10-19 1998-10-20 General Electric Company Low emissions combustor premixer
GB2307980B (en) * 1995-12-06 2000-07-05 Europ Gas Turbines Ltd A fuel injector arrangement; a method of operating a fuel injector arrangement
US5881756A (en) * 1995-12-22 1999-03-16 Institute Of Gas Technology Process and apparatus for homogeneous mixing of gaseous fluids
US5797268A (en) * 1996-07-05 1998-08-25 Westinghouse Electric Corporation Partially swirled multi-swirl combustor plate and chimneys
SE514341C2 (sv) * 1998-06-18 2001-02-12 Abb Ab Förfarande för start av en brännaranordning till en gasturbin
JP4339519B2 (ja) 1998-08-31 2009-10-07 シーメンス アクチエンゲゼルシヤフト ガスタービンの運転方法及びガスタービン
IT1313547B1 (it) * 1999-09-23 2002-07-24 Nuovo Pignone Spa Camera di premiscelamento per turbine a gas
EP1199523A1 (de) * 2000-10-20 2002-04-24 Siemens Aktiengesellschaft Verfahren zur Beaufschlagung von Brennern in einer Brennkammer sowie Brennkammer mit einer Anzahl von Brennern
US6813889B2 (en) * 2001-08-29 2004-11-09 Hitachi, Ltd. Gas turbine combustor and operating method thereof
US6928823B2 (en) * 2001-08-29 2005-08-16 Hitachi, Ltd. Gas turbine combustor and operating method thereof
US6962055B2 (en) * 2002-09-27 2005-11-08 United Technologies Corporation Multi-point staging strategy for low emission and stable combustion
US6931853B2 (en) * 2002-11-19 2005-08-23 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
US7546740B2 (en) * 2004-05-11 2009-06-16 United Technologies Corporation Nozzle
US7350357B2 (en) * 2004-05-11 2008-04-01 United Technologies Corporation Nozzle
US7900435B1 (en) * 2007-05-23 2011-03-08 Xcor Aerospace Micro-coaxial injector for rocket engine
US8087228B2 (en) * 2008-09-11 2012-01-03 General Electric Company Segmented combustor cap
US8327642B2 (en) * 2008-10-21 2012-12-11 General Electric Company Multiple tube premixing device
US9140454B2 (en) 2009-01-23 2015-09-22 General Electric Company Bundled multi-tube nozzle for a turbomachine
EP2430362A1 (en) * 2009-05-07 2012-03-21 General Electric Company Multi-premixer fuel nozzle
US8402763B2 (en) * 2009-10-26 2013-03-26 General Electric Company Combustor headend guide vanes to reduce flow maldistribution into multi-nozzle arrangement
US8511092B2 (en) * 2010-08-13 2013-08-20 General Electric Company Dimpled/grooved face on a fuel injection nozzle body for flame stabilization and related method
US9033699B2 (en) * 2011-11-11 2015-05-19 General Electric Company Combustor
US9134023B2 (en) * 2012-01-06 2015-09-15 General Electric Company Combustor and method for distributing fuel in the combustor
US20130199189A1 (en) * 2012-02-08 2013-08-08 Jong Ho Uhm Fuel injection assembly for use in turbine engines and method of assembling same
US20130199190A1 (en) * 2012-02-08 2013-08-08 Jong Ho Uhm Fuel injection assembly for use in turbine engines and method of assembling same
US8511086B1 (en) * 2012-03-01 2013-08-20 General Electric Company System and method for reducing combustion dynamics in a combustor
US9366445B2 (en) * 2012-04-05 2016-06-14 General Electric Company System and method for supporting fuel nozzles inside a combustor
US20130283810A1 (en) * 2012-04-30 2013-10-31 General Electric Company Combustion nozzle and a related method thereof
US9261279B2 (en) * 2012-05-25 2016-02-16 General Electric Company Liquid cartridge with passively fueled premixed air blast circuit for gas operation
US9267690B2 (en) 2012-05-29 2016-02-23 General Electric Company Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same
US20130318976A1 (en) * 2012-05-29 2013-12-05 General Electric Company Turbomachine combustor nozzle and method of forming the same
US20140109582A1 (en) * 2012-10-23 2014-04-24 General Electric Company Self-stabilized micromixer
US9353950B2 (en) * 2012-12-10 2016-05-31 General Electric Company System for reducing combustion dynamics and NOx in a combustor
CN107420943B (zh) * 2013-10-18 2019-12-06 三菱重工业株式会社 燃料喷射器
US10107499B2 (en) * 2014-07-31 2018-10-23 General Electric Company Fuel plenum for a fuel nozzle and method of making same
JP6440433B2 (ja) * 2014-09-29 2018-12-19 川崎重工業株式会社 燃料噴射ノズル、燃料噴射モジュール、及びガスタービン
RU2015156419A (ru) 2015-12-28 2017-07-04 Дженерал Электрик Компани Узел топливной форсунки, выполненный со стабилизатором пламени предварительно перемешанной смеси
US11226092B2 (en) 2016-09-22 2022-01-18 Utilization Technology Development, Nfp Low NOx combustion devices and methods
US10295190B2 (en) 2016-11-04 2019-05-21 General Electric Company Centerbody injector mini mixer fuel nozzle assembly
US10465909B2 (en) 2016-11-04 2019-11-05 General Electric Company Mini mixing fuel nozzle assembly with mixing sleeve
US10724740B2 (en) 2016-11-04 2020-07-28 General Electric Company Fuel nozzle assembly with impingement purge
US10352569B2 (en) 2016-11-04 2019-07-16 General Electric Company Multi-point centerbody injector mini mixing fuel nozzle assembly
US10393382B2 (en) 2016-11-04 2019-08-27 General Electric Company Multi-point injection mini mixing fuel nozzle assembly
US10634353B2 (en) 2017-01-12 2020-04-28 General Electric Company Fuel nozzle assembly with micro channel cooling
WO2019117467A1 (ko) * 2017-12-11 2019-06-20 (주)넥스트가스이노베이션 Lpg 직접 분사 연소장치
US10890329B2 (en) 2018-03-01 2021-01-12 General Electric Company Fuel injector assembly for gas turbine engine
DE102018114870B3 (de) * 2018-06-20 2019-11-28 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennersystem und Verfahren zur Erzeugung von Heißgas in einer Gasturbinenanlage
WO2019008304A2 (fr) * 2018-10-05 2019-01-10 Fives Pillard Bruleur et procede de combustion pour bruleur
US10935245B2 (en) 2018-11-20 2021-03-02 General Electric Company Annular concentric fuel nozzle assembly with annular depression and radial inlet ports
US11073114B2 (en) 2018-12-12 2021-07-27 General Electric Company Fuel injector assembly for a heat engine
US11286884B2 (en) 2018-12-12 2022-03-29 General Electric Company Combustion section and fuel injector assembly for a heat engine
US11156360B2 (en) 2019-02-18 2021-10-26 General Electric Company Fuel nozzle assembly
DE102020119619A1 (de) * 2020-07-24 2022-01-27 Friedrich-Alexander-Universität Erlangen-Nürnberg Düsencluster
US12331932B2 (en) 2022-01-31 2025-06-17 General Electric Company Turbine engine fuel mixer
KR102583225B1 (ko) * 2022-02-07 2023-09-25 두산에너빌리티 주식회사 마이크로 믹서 및 이를 포함하는 가스 터빈
US12215866B2 (en) 2022-02-18 2025-02-04 General Electric Company Combustor for a turbine engine having a fuel-air mixer including a set of mixing passages
CN116678012B (zh) * 2023-07-07 2025-06-13 北京航空航天大学 一种油气分离式一体化火焰稳定器系统及变循环发动机

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH305532A (de) * 1951-06-25 1955-02-28 Parsons & Co Ltd C A Gasturbinenanlage.
CH303030A (de) * 1952-08-15 1954-11-15 Bbc Brown Boveri & Cie Gasbrenner, vorzugsweise für Brennkammern von Gasturbinenanlagen.
DE1074920B (de) * 1955-07-07 1960-02-04 Ing habil Fritz A F Schmidt Murnau Dr (Obb) Verfahren und \ orrichtung zur Regelung von Gas turbmenbrennkammern mit unterteilter Verbrennung und mehreren Druckstufen
CH388022A (de) * 1960-10-07 1965-02-15 Maschf Augsburg Nuernberg Ag Brennkammer für die gleichzeitige Verbrennung gasförmiger und nichtgasförmiger Brennstoffe, insbesondere für Gasturbinenanlagen
GB1284439A (en) * 1969-12-09 1972-08-09 Rolls Royce Fuel injector for a gas turbine engine
US3630024A (en) * 1970-02-02 1971-12-28 Gen Electric Air swirler for gas turbine combustor
US3777983A (en) * 1971-12-16 1973-12-11 Gen Electric Gas cooled dual fuel air atomized fuel nozzle
US3904119A (en) * 1973-12-05 1975-09-09 Avco Corp Air-fuel spray nozzle
US3886728A (en) * 1974-05-01 1975-06-03 Gen Motors Corp Combustor prechamber
GB1559779A (en) * 1975-11-07 1980-01-23 Lucas Industries Ltd Combustion assembly
US4134719A (en) * 1976-09-27 1979-01-16 Velie Wallace W Multi-flame fuel burner for liquid and gaseous fuels
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
US4155220A (en) * 1977-01-21 1979-05-22 Westinghouse Electric Corp. Combustion apparatus for a gas turbine engine
US4327547A (en) * 1978-11-23 1982-05-04 Rolls-Royce Limited Fuel injectors
US4288980A (en) * 1979-06-20 1981-09-15 Brown Boveri Turbomachinery, Inc. Combustor for use with gas turbines
DE2950535A1 (de) * 1979-11-23 1981-06-11 BBC AG Brown, Boveri & Cie., Baden, Aargau Brennkammer einer gasturbine mit vormisch/vorverdampf-elementen
HU181665B (en) * 1979-11-28 1983-10-28 Chinoin Gyogyszer Es Vegyeszet Plant protective composition containing carbofurane with increased growth promoting and insecticide effect
DE2949388A1 (de) * 1979-12-07 1981-06-11 Kraftwerk Union AG, 4330 Mülheim Brennkammer fuer gasturbinen und verfahren zum betrieb der brennkammer
US4356698A (en) * 1980-10-02 1982-11-02 United Technologies Corporation Staged combustor having aerodynamically separated combustion zones

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4412315A1 (de) * 1994-04-11 1995-10-12 Abb Management Ag Verfahren und Vorrichtung zum Betreiben der Brennkammer einer Gasturbine
DE4412315B4 (de) * 1994-04-11 2005-12-15 Alstom Verfahren und Vorrichtung zum Betreiben der Brennkammer einer Gasturbine

Also Published As

Publication number Publication date
JPH0356369B2 (enrdf_load_stackoverflow) 1991-08-28
US4967561A (en) 1990-11-06
EP0095788A1 (de) 1983-12-07
DE3361535D1 (en) 1986-01-30
JPS58219329A (ja) 1983-12-20

Similar Documents

Publication Publication Date Title
EP0095788B1 (de) Brennkammer einer Gasturbine und Verfahren zu deren Betrieb
EP0576697B1 (de) Brennkammer einer Gasturbine
EP0029619B1 (de) Brennkammer einer Gasturbine mit Vormisch/Vorverdampf-Elementen
EP0571782B1 (de) Verfahren zum Betrieb einer Brennkammer einer Gasturbine
DE69828916T2 (de) Emissionsarmes Verbrennungssystem für Gasturbinentriebwerke
EP0274630B1 (de) Brenneranordnung
DE69506142T2 (de) Verbesserte Verbrennungsanlage mit niedriger Schadstoffemission für Gasturbinen
EP0503319B1 (de) Brenner für eine Vormischverbrennung eines flüssigen und/oder gasförmigen Brennstoffes
DE4446945B4 (de) Gasbetriebener Vormischbrenner
DE2417147C2 (de) Brennkammeranordnung für Gasturbinen
DE69010973T2 (de) Brenner.
DE10050248A1 (de) Brenner
EP0481111B1 (de) Brennkammer einer Gasturbine
EP0321809A1 (de) Verfahren für die Verbrennung von flüssigem Brennstoff in einem Brenner
EP0401529A1 (de) Brennkammer einer Gasturbine
EP0801268A2 (de) Gasturbinenbrennkammer
DE4320212A1 (de) Feuerungsanlage
EP0394800B1 (de) Vormischbrenner für die Heissgaserzeugung
EP0816759B1 (de) Vormischbrenner und Verfahren zum Betrieb des Brenners
DE60125892T2 (de) Brennkammer
EP0483554B1 (de) Verfahren zur Minimierung der NOx-Emissionen aus einer Verbrennung
DE4412315B4 (de) Verfahren und Vorrichtung zum Betreiben der Brennkammer einer Gasturbine
DE2705647A1 (de) Brenner fuer gasfoermigen oder fluessigen brennstoff
DE4242003A1 (de) Prozesswärmeerzeuger
DE4422535A1 (de) Verfahren zum Betrieb einer Feuerungsanlage

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

AK Designated contracting states

Designated state(s): CH DE FR GB LI NL

17P Request for examination filed

Effective date: 19840209

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Designated state(s): CH DE FR GB LI NL

REF Corresponds to:

Ref document number: 3361535

Country of ref document: DE

Date of ref document: 19860130

ET Fr: translation filed
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
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 19930706

Year of fee payment: 11

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

Ref country code: LI

Effective date: 19940430

Ref country code: CH

Effective date: 19940430

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: GB

Payment date: 20010316

Year of fee payment: 19

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

Ref country code: NL

Payment date: 20010329

Year of fee payment: 19

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

Ref country code: DE

Payment date: 20010421

Year of fee payment: 19

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

Ref country code: FR

Payment date: 20010427

Year of fee payment: 19

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

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: 20020407

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

Ref country code: NL

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

Effective date: 20021101

Ref country code: DE

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

Effective date: 20021101

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

Effective date: 20020407

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: 20021231

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee

Effective date: 20021101

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST