EP0029619B1 - Brennkammer einer Gasturbine mit Vormisch/Vorverdampf-Elementen - Google Patents

Brennkammer einer Gasturbine mit Vormisch/Vorverdampf-Elementen Download PDF

Info

Publication number
EP0029619B1
EP0029619B1 EP80200979A EP80200979A EP0029619B1 EP 0029619 B1 EP0029619 B1 EP 0029619B1 EP 80200979 A EP80200979 A EP 80200979A EP 80200979 A EP80200979 A EP 80200979A EP 0029619 B1 EP0029619 B1 EP 0029619B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
orifices
elements
flame retention
flame
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP80200979A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0029619A1 (de
Inventor
Eduard Brühwiler
Hans Koch
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=4363297&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP0029619(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0029619A1 publication Critical patent/EP0029619A1/de
Application granted granted Critical
Publication of EP0029619B1 publication Critical patent/EP0029619B1/de
Expired legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/10—Flame flashback

Definitions

  • the invention relates to the combustion chamber of a gas turbine according to the preamble of claim 1.
  • Gas turbines are increasingly subject to the stringent environmental regulations in many countries regarding exhaust gas composition. Above all, compliance with the regulations on the maximum permitted NO x emissions is extremely difficult when operating a gas turbine.
  • a combustion chamber of the type mentioned at the outset for the purpose of reducing the pollutants liberated during combustion is known from US-A-4 100 733. It is aimed there that the emission values of pollutants without the injection of aids such as water or steam into the combustion chamber under the allowable values fall from the emission regulations. This is achieved by adding a pre-mixing / pre-evaporation phase to the actual combustion process. For this purpose, the pre-mixing / pre-evaporation is carried out in several tubular elements, the fuel being mixed with air from the compressor with a large excess of air.
  • This known combustion chamber is designed in two stages and is operated in such a way that the first stage is operated at low load, i. H. that about half of the tubular elements are used in terms of fuel. The second stage is only operated at higher loads. The aim here is that the mixture in the first stage is always rich enough to ensure stable combustion. This can be achieved either by changing the resistance at the air inlets on the distribution chamber side or by using fuel injectors of different sizes.
  • the present invention is based on the object of improving a combustion chamber of the type mentioned in such a way that first of all a reliable ignition of all elements is ensured and that then a re-ignition of the Flame from the combustion chamber into the interior of the tubular elements is prevented.
  • pilot elements are used in the present invention, it is expedient to distribute them geometrically evenly among the tubular elements used. If these are still put into operation by initial ignition, then one does not apply to the elements which are put into operation later: the flame jumps from the pilot elements to the surrounding ones, favored by the fact that the flame holders of these pilot elements are provided either with swirl bodies or with oblique holes, so that divergent tongues of flame are generated, which additionally promote good caloric and air-jet mixing, which is reflected in a more uniform temperature and speed distribution after the combustion chamber.
  • both the oblique openings and the openings in the flame holder parallel to the axis of the flame holder have a length of at least 1.5 opening diameters. Through this opening, the air-fuel oil vapor mixture or the air-fuel gas mixture flows to the combustion chamber at an increased speed, as a result of which flame back ignition is avoided.
  • a further embodiment in order to avoid a flashback, is to design the openings in the flame holder as injectors, so that air is introduced into the boundary layer of the openings.
  • Another configuration of the openings in the flame holder is to design them as diffusers. With this solution, a higher speed is possible with the same pressure loss. The higher speed offers more security against the flame reigniting from the combustion chamber. To ensure the safe operation of the diffuser, it is necessary to add a cylindrical section with a minimum length of 1.5 diameter.
  • FIG. 1 shows schematically the concept of such a combustion chamber.
  • 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 FIG. 2, in which thirty-seven tubular elements 2 are arranged. However, this number is not mandatory, because it depends on the size of the combustion chamber, which in turn is dependent on the desired combustion output.
  • a support bridge 27, on which the tubular elements 2 are connected by means of end nuts 5, is anchored to a support rib 23. In order to connect the tubular elements 2 to the support bridge 27, other types of connection can of course also be used.
  • the tubular elements 2 are guided laterally in the lower region by means of a guide plate 6.
  • the tubular elements 2 can also be guided individually, as can be seen in FIG. 16, in which case no guide plate is then used, but individual guide rings 25 take on this task.
  • the guide rings 25 are also carried here by support elements 22 which are firmly connected to the support bridge 27.
  • the tubular elements 2 can also be anchored differently than with the support bridge 27 shown, but in such cases it will always be necessary to ensure that the chosen anchoring is placed as far away from the combustion chamber 7 as possible so that the thermal expansions cannot have a disruptive effect.
  • the greater part of the compressed air which is provided in the compressor (not shown), flows through the openings 9 into a distribution chamber 19 provided in the combustion chamber casing I, which distributes downwards through the support bridge 27 and upwards through the cover 35 flanged on the flange rib 38 is narrowed down. 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 means of a fuel line 4, a fuel nozzle 15, which projects into the tubular element 2 and has one or more fuel openings (not shown), atomizing the fuel against the air inflow direction. The fuel does not necessarily have to be injected against the air flow.
  • fuel gas natural gas
  • the gas is blown in in the direction of air inflow. It is also possible to input and burn oil and gas at the same time.
  • fuel oil to achieve finer atomization, the smallest possible amount of compressed air can be added through the nozzle 15, which has an overpressure compared to the process pressure.
  • the fuel therefore mixes with the incoming compressed air in such a way that a pre-mixing nor evaporation process takes place in the tubular element 2.
  • This process can be intensified due to the turbulence which arises by inserting a flange 34 at the air inlet of the tubular element 2, as can be seen in FIG. 16.
  • the fuel injection or fuel injection through the fuel nozzle 15 must be carried out at an optimal distance from the mouth 34, but still in the region of the turbulence that has arisen.
  • 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.
  • a remaining amount of compressed air does not flow into the distribution chamber 19, but into the combustion chamber casing I through the openings 26, is distributed between the tubular elements 2 and flows through the openings 18 recessed in the flame holder edge 13 (FIG. 2) to the combustion chamber, as a result of which the outer part of the flame holder 3 is cooled in such a way that the risk of burning, which is latent especially when producing divergent flame tongues, is counteracted.
  • the combustion of the mixture is aimed at with the largest possible excess of air, which is given by the fact that the flame is still burning and further by the fact that not too much CO is produced.
  • a good optimization can be present, for example, if the air content of the mixture is kept at 1.8 times the stoichiometric value.
  • the lower terminating rib 24 prevents free convection of the hot air from the combustion chamber 7, the terminating rib 24 also being cooled with the same residual air flowing in through the openings 26, which then flows out through the openings 18 of the adjacent flame shader edges 13 to the combustion chamber 7.
  • the flame holder 3 which forms the end of the downstream part of the tubular element 2, has the task of preventing the flame from reigniting from the combustion chamber 7 into the interior of the tubular element 2.
  • the inner wall of the combustion chamber casing 1 is provided with a cooling system (not shown) in the area of the combustion chamber 7, that is to say from the flame heater 3.
  • the flame holder 3 shown has a number of cylindrical holes 21 which run parallel to the axis of the tubular element 2. If additional divergent flame tongues are to be produced, as can be seen in FIGS. 4 and 5, the holes 30 in the flame holder 3, with the exception of the central hole, can be made obliquely in radial planes of the flame holder 3, the angle 38 from the center to the periphery of the flame holder 3 steadily increases or remains the same.
  • the length of both the parallel holes 21 and the oblique holes 30, 31 must be at least 1.5 hole diameter.
  • the resulting increased mixture speed in the holes 21, 30, 31 and the length of the holes counteract flame reignition from the combustion chamber 7.
  • the number of holes 21, 30, 31 must be adapted to the given conditions. In the example shown in FIG. 7, there are for example twenty-one holes 31.
  • the flame holder 3 consists of an upper plate 3a and a lower plate 3b, between which a channel 10 connected to the openings 8 runs.
  • the openings 8 provided in the flame holder 3 are each lined with two slightly conical bushes 11, 12, these overlapping in the region of the channel 10 telescopically and with play 16. Burning back of the flame from the combustion chamber 7, in particular in the boundary layer along the wall of the sleeve 12, is counteracted by introducing compressed air through the channel 10, which flows through the play 16 along the endangered wall of the sleeve 12 with the mixture . Flow separations, which would favor reignition, are prevented by the conical shape of the openings 8.
  • the flame holder 3 shown in FIG. 11 has sixteen openings 8, which are fed symmetrically from two channels 10 with compressed air.
  • the supply of the openings 8 made in the flame holder 3 with compressed air can be fulfilled by other channel configurations.
  • the openings 8 in the flame holder 3 are designed as diffusers 39.
  • an initial cylindrical bore 32 is followed by a section formed as a diffuser 40, which is followed by a cylindrical bore 33 of larger diameter than the inlet bore 32, which has a length of at least 1.5 bore diameter.
  • a higher speed at the narrowest point is possible with the same pressure loss, which is reflected in greater safety against flame reignition from the combustion chamber 7.
  • the beginning of the flame in the combustion chamber 7 is brought into a corresponding distance from the diffuser 40 through the cylindrical bore 33.
  • the flow in the subsequent cylindrical part 33 will again rest against the wall.
  • the flame holder 3 can, as shown in FIG. 9 10 and 10, can be provided with a swirl body 28, the mixture being directed to the combustion chamber 7 in a swirling manner through its openings 41, for example fourteen in number.
  • the swirl body 28 promotes good air-jet mixing of the fuel / air mixture and good heat distribution, 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.
  • tubular elements 2 and the individual flame holder 3 itself in combination according to Figures 3, 4/5, 6/7/8, 9/10, 11/15 or 14 can be formed.
  • the combustion chamber casing 1 is optimally filled with a larger number of tubular elements 2. As shown in FIG. 2, among the thirty-seven tubular elements 2 used, thirteen pilot elements 17 are geometrically evenly distributed. When the combustion chamber is started, pilot elements 17 are initially put into operation by an initial ignition unit (not shown). When the load increases, the flame jumps from the pilot elements 17 to the surrounding ones, which have just been put into operation.
  • the openings 8 in the flame holder 3 of the pilot elements 17 can optionally be formed after the holes 30 and / or after the holes 31.
  • the use of swirl bodies 28 can also be provided for the pilot elements 17, which, like the holes 30, 31, also produce divergent flame tongues and thus favor the ignition of the surrounding tubular elements 2.
  • the flame holder 3 is hexagonal 20 in the circumferential direction. From these figures it can also be seen that the openings 18 made in the flame holder base 13 are evenly distributed between the hexagonal shape 20 and the tubular element. A polygon game 29 absorbs the thermal expansion in this area.
  • an orifice 34 is used, which in this area, that is to say directly around the fuel nozzle 15, generates turbulence which is suitable for this purpose; to intensify the premixing, atomization and pre-evaporation process in addition to the measures described above, that is to say in particular by the fine injection of the fuel against the direction of air inflow.
  • turbulence amplifiers can also be used instead of the on-board mouth 34.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
EP80200979A 1979-11-23 1980-10-16 Brennkammer einer Gasturbine mit Vormisch/Vorverdampf-Elementen Expired EP0029619B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH1044479 1979-11-23
CH10444/79 1979-11-23

Publications (2)

Publication Number Publication Date
EP0029619A1 EP0029619A1 (de) 1981-06-03
EP0029619B1 true EP0029619B1 (de) 1983-06-01

Family

ID=4363297

Family Applications (1)

Application Number Title Priority Date Filing Date
EP80200979A Expired EP0029619B1 (de) 1979-11-23 1980-10-16 Brennkammer einer Gasturbine mit Vormisch/Vorverdampf-Elementen

Country Status (5)

Country Link
US (1) US4408461A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
EP (1) EP0029619B1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
JP (1) JPS5691132A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
CA (1) CA1157280A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
DE (2) DE2950535A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0095788A1 (de) * 1982-05-28 1983-12-07 BBC Aktiengesellschaft Brown, Boveri & Cie. Brennkammer einer Gasturbine und Verfahren zu deren Betrieb
US4539811A (en) * 1982-01-27 1985-09-10 The United States Of America As Represented By The Secretary Of The Navy Multi-port dump combustor
EP0526152A1 (en) * 1991-08-01 1993-02-03 General Electric Company Flashback resistant fuel staged premixed combustor
FR2695460A1 (fr) * 1992-09-09 1994-03-11 Snecma Chambre de combustion de turbomachine à plusieurs injecteurs.
US5412938A (en) * 1992-06-29 1995-05-09 Abb Research Ltd. Combustion chamber of a gas turbine having premixing and catalytic burners
US5713206A (en) * 1993-04-15 1998-02-03 Westinghouse Electric Corporation Gas turbine ultra low NOx combustor

Families Citing this family (129)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS57207711A (en) * 1981-06-15 1982-12-20 Hitachi Ltd Premixture and revolving burner
DE3241162A1 (de) * 1982-11-08 1984-05-10 Kraftwerk Union AG, 4330 Mülheim Vormischbrenner mit integriertem diffusionsbrenner
DE3318863A1 (de) * 1983-05-25 1984-12-13 Erich 8480 Weiden Bielefeldt Kraftmaschine mit gasturbine
US5165241A (en) * 1991-02-22 1992-11-24 General Electric Company Air fuel mixer for gas turbine combustor
US5891584A (en) * 1991-03-25 1999-04-06 General Electric Company Coated article for hot hydrocarbon fluid and method of preventing fuel thermal degradation deposits
US5805973A (en) * 1991-03-25 1998-09-08 General Electric Company Coated articles and method for the prevention of fuel thermal degradation deposits
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
JPH0579631A (ja) * 1991-09-19 1993-03-30 Hitachi Ltd 燃焼器設備
JPH05203146A (ja) * 1992-01-29 1993-08-10 Hitachi Ltd ガスタービン燃焼器及びガスタービン発電装置
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
US5247792A (en) * 1992-07-27 1993-09-28 General Electric Company Reducing thermal deposits in propulsion systems
US5251447A (en) * 1992-10-01 1993-10-12 General Electric Company Air fuel mixer for gas turbine combustor
DE59209209D1 (de) * 1992-10-16 1998-04-02 Asea Brown Boveri Gasbetriebener Vormischbrenner
US5444982A (en) * 1994-01-12 1995-08-29 General Electric Company Cyclonic prechamber with a centerbody
DE4408136A1 (de) * 1994-03-10 1995-09-14 Bmw Rolls Royce Gmbh Verfahren und Vorrichtung zur Kraftstoff-Aufbereitung für eine Gasturbinen-Brennkammer
US5636510A (en) * 1994-05-25 1997-06-10 Westinghouse Electric Corporation Gas turbine topping combustor
DE4444125A1 (de) * 1994-12-12 1996-06-13 Abb Research Ltd Verfahren zur schadstoffarmen Verbrennung
WO1997040316A1 (en) * 1996-04-19 1997-10-30 Westinghouse Electric Corporation Premixed combustor with flashback arrestors
RU2138661C1 (ru) * 1996-05-22 1999-09-27 Акционерное общество "Авиадвигатель" Газотурбинный двигатель, работающий на криогенном топливе
US5797268A (en) * 1996-07-05 1998-08-25 Westinghouse Electric Corporation Partially swirled multi-swirl combustor plate and chimneys
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
US6298667B1 (en) * 2000-06-22 2001-10-09 General Electric Company Modular combustor dome
US6672073B2 (en) * 2002-05-22 2004-01-06 Siemens Westinghouse Power Corporation System and method for supporting fuel nozzles in a gas turbine combustor utilizing a support plate
US6996991B2 (en) * 2003-08-15 2006-02-14 Siemens Westinghouse Power Corporation Fuel injection system for a turbine engine
US6923002B2 (en) * 2003-08-28 2005-08-02 General Electric Company Combustion liner cap assembly for combustion dynamics reduction
EP2041494B8 (en) * 2005-12-14 2015-05-27 Industrial Turbine Company (UK) Limited Gas turbine engine premix injectors
JP4854613B2 (ja) * 2007-07-09 2012-01-18 株式会社日立製作所 燃焼装置及びガスタービン燃焼器
JP4922878B2 (ja) * 2007-09-19 2012-04-25 株式会社日立製作所 ガスタービン燃焼器
JP4872992B2 (ja) 2008-09-12 2012-02-08 株式会社日立製作所 燃焼器，燃焼器の燃料供給方法及び燃焼器の改造方法
US7886991B2 (en) * 2008-10-03 2011-02-15 General Electric Company Premixed direct injection nozzle
US9140454B2 (en) 2009-01-23 2015-09-22 General Electric Company Bundled multi-tube nozzle for a turbomachine
US20120031097A1 (en) * 2009-05-07 2012-02-09 General Electric Company Multi-premixer fuel nozzle
US8522555B2 (en) 2009-05-20 2013-09-03 General Electric Company Multi-premixer fuel nozzle support system
US8402763B2 (en) * 2009-10-26 2013-03-26 General Electric Company Combustor headend guide vanes to reduce flow maldistribution into multi-nozzle arrangement
EP2436983A1 (de) * 2010-10-04 2012-04-04 Siemens Aktiengesellschaft Strahlbrenner
EP2442029A1 (de) * 2010-10-12 2012-04-18 Siemens Aktiengesellschaft Prallgekühlte Kopfplatte mit thermischer Entkopplung für einen Strahlpiloten
EP2442030A1 (de) * 2010-10-13 2012-04-18 Siemens Aktiengesellschaft Axiale Stufe für einen strahlstabilisierten Brenner
US9506654B2 (en) * 2011-08-19 2016-11-29 General Electric Company System and method for reducing combustion dynamics in a combustor
US9243803B2 (en) * 2011-10-06 2016-01-26 General Electric Company System for cooling a multi-tube fuel nozzle
US9004912B2 (en) * 2011-11-11 2015-04-14 General Electric Company Combustor and method for supplying fuel to a combustor
US9033699B2 (en) * 2011-11-11 2015-05-19 General Electric Company Combustor
JP5762558B2 (ja) * 2011-11-16 2015-08-12 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器
US9366440B2 (en) * 2012-01-04 2016-06-14 General Electric Company Fuel nozzles with mixing tubes surrounding a liquid fuel cartridge for injecting fuel in a gas turbine 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
US20130219899A1 (en) * 2012-02-27 2013-08-29 General Electric Company Annular premixed pilot in fuel nozzle
US9121612B2 (en) * 2012-03-01 2015-09-01 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
US20130283802A1 (en) * 2012-04-27 2013-10-31 General Electric Company Combustor
US20130283810A1 (en) * 2012-04-30 2013-10-31 General Electric Company Combustion nozzle and a related method thereof
US20130318976A1 (en) * 2012-05-29 2013-12-05 General Electric Company Turbomachine combustor nozzle and method of forming the same
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
US9291103B2 (en) * 2012-12-05 2016-03-22 General Electric Company Fuel nozzle for a combustor of a gas turbine engine
WO2015042615A1 (en) 2013-09-23 2015-03-26 Clearsign Combustion Corporation Horizontally fired burner with a perforated flame holder
US9857076B2 (en) 2013-02-14 2018-01-02 Clearsign Combustion Corporation Perforated flame holder and burner including a perforated flame holder
US10125983B2 (en) 2013-02-14 2018-11-13 Clearsign Combustion Corporation High output porous tile burner
US10571124B2 (en) 2013-02-14 2020-02-25 Clearsign Combustion Corporation Selectable dilution low NOx burner
CA2892236A1 (en) 2013-02-14 2014-08-21 Clearsign Combustion Corporation Fuel combustion system with a perforated reaction holder
US11460188B2 (en) 2013-02-14 2022-10-04 Clearsign Technologies Corporation Ultra low emissions firetube boiler burner
US10119704B2 (en) 2013-02-14 2018-11-06 Clearsign Combustion Corporation Burner system including a non-planar perforated flame holder
US10386062B2 (en) 2013-02-14 2019-08-20 Clearsign Combustion Corporation Method for operating a combustion system including a perforated flame holder
US20140251483A1 (en) * 2013-03-07 2014-09-11 General Electric Company Tube assembly for use in fuel injection assemblies and methods of assembling same
US9650959B2 (en) 2013-03-12 2017-05-16 General Electric Company Fuel-air mixing system with mixing chambers of various lengths for gas turbine system
US9366439B2 (en) 2013-03-12 2016-06-14 General Electric Company Combustor end cover with fuel plenums
US9347668B2 (en) * 2013-03-12 2016-05-24 General Electric Company End cover configuration and assembly
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9765973B2 (en) 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9759425B2 (en) 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
DE102013204309A1 (de) * 2013-03-13 2014-09-18 Siemens Aktiengesellschaft Strahlbrenner
WO2014160836A1 (en) 2013-03-27 2014-10-02 Clearsign Combustion Corporation Electrically controlled combustion fluid flow
US10125979B2 (en) 2013-05-10 2018-11-13 Clearsign Combustion Corporation Combustion system and method for electrically assisted start-up
US9371997B2 (en) * 2013-07-01 2016-06-21 General Electric Company System for supporting a bundled tube fuel injector within a combustor
US9322555B2 (en) 2013-07-01 2016-04-26 General Electric Company Cap assembly for a bundled tube fuel injector
US9273868B2 (en) * 2013-08-06 2016-03-01 General Electric Company System for supporting bundled tube segments within a combustor
WO2015042614A1 (en) 2013-09-23 2015-03-26 Clearsign Combustion Corporation Burner system employing multiple perforated flame holders, and method of operation
WO2015057740A1 (en) 2013-10-14 2015-04-23 Clearsign Combustion Corporation Flame visualization control for electrodynamic combustion control
WO2015070188A1 (en) 2013-11-08 2015-05-14 Clearsign Combustion Corporation Combustion system with flame location actuation
EP3097365A4 (en) 2014-01-24 2017-10-25 Clearsign Combustion Corporation LOW NOx FIRE TUBE BOILER
CN106103338B (zh) 2014-02-14 2018-04-20 克利尔赛恩燃烧公司 具有有孔火焰保持器的顶烧式燃烧器
US9885496B2 (en) 2014-07-28 2018-02-06 Clearsign Combustion Corporation Fluid heater with perforated flame holder
US9828288B2 (en) 2014-08-13 2017-11-28 Clearsign Combustion Corporation Perforated burner for a rotary kiln
CN107110496A (zh) * 2014-12-24 2017-08-29 克利尔赛恩燃烧公司 具有燃料和氧化剂再循环的火焰稳定器、包括此类火焰稳定器的燃烧系统，以及相关方法
WO2016133936A1 (en) 2015-02-17 2016-08-25 Clearsign Combustion Corporation Prefabricated integrated combustion assemblies and methods of installing the same into a combustion system
WO2016134068A1 (en) * 2015-02-17 2016-08-25 Clearsign Combustion Corporation Burner system with a perforated flame holder and a plurality of fuel sources
US12247733B2 (en) 2015-02-17 2025-03-11 Clearsign Technologies Corporation Prefabricated integrated combustion assemblies and methods of installing the same into a combustion system
WO2016134061A1 (en) 2015-02-17 2016-08-25 Clearsign Combustion Corporation Perforated flame holder with adjustable fuel nozzle
WO2016133934A1 (en) 2015-02-17 2016-08-25 Clearsign Combustion Corporation Methods of upgrading a conventional combustion system to include a perforated flame holder
US10006715B2 (en) 2015-02-17 2018-06-26 Clearsign Combustion Corporation Tunnel burner including a perforated flame holder
WO2016160010A1 (en) * 2015-04-01 2016-10-06 Siemens Energy, Inc. Pre-mixing based fuel nozzle for use in a combustion turbine engine
RU2015156419A (ru) 2015-12-28 2017-07-04 Дженерал Электрик Компани Узел топливной форсунки, выполненный со стабилизатором пламени предварительно перемешанной смеси
US10088153B2 (en) 2015-12-29 2018-10-02 Clearsign Combustion Corporation Radiant wall burner including perforated flame holders
CN112432166B (zh) 2016-01-13 2023-10-27 美一蓝技术公司 瓷砖组之间具有间隙的穿孔火焰保持器
US10551058B2 (en) 2016-03-18 2020-02-04 Clearsign Technologies Corporation Multi-nozzle combustion assemblies including perforated flame holder, combustion systems including the combustion assemblies, and related methods
EP3449183B1 (en) 2016-04-29 2023-12-06 ClearSign Technologies Corporation Burner system with discrete transverse flame stabilizers
US10408455B2 (en) * 2016-06-14 2019-09-10 General Electric Company Fuel nozzle assembly with fuel inlet slots
US10514165B2 (en) 2016-07-29 2019-12-24 Clearsign Combustion Corporation Perforated flame holder and system including protection from abrasive or corrosive fuel
US10539326B2 (en) 2016-09-07 2020-01-21 Clearsign Combustion Corporation Duplex burner with velocity-compensated mesh and thickness
US10295190B2 (en) 2016-11-04 2019-05-21 General Electric Company Centerbody injector mini mixer fuel nozzle assembly
US10352569B2 (en) 2016-11-04 2019-07-16 General Electric Company Multi-point centerbody injector mini mixing fuel nozzle assembly
US10724740B2 (en) 2016-11-04 2020-07-28 General Electric Company Fuel nozzle assembly with impingement purge
US10465909B2 (en) 2016-11-04 2019-11-05 General Electric Company Mini mixing fuel nozzle assembly with mixing sleeve
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
US10669942B2 (en) * 2017-02-23 2020-06-02 General Electric Company Endcover assembly for a combustor
US10273913B2 (en) * 2017-05-25 2019-04-30 The United States Of America, As Represented By The Secretary Of The Navy Multi-mode thermoacoustic actuator
US11525578B2 (en) * 2017-08-16 2022-12-13 General Electric Company Dynamics-mitigating adapter for bundled tube fuel nozzle
KR102046455B1 (ko) * 2017-10-30 2019-11-19 두산중공업 주식회사 연료 노즐, 이를 포함하는 연소기 및 가스 터빈
JP2019128125A (ja) * 2018-01-26 2019-08-01 川崎重工業株式会社 バーナ装置
US10890329B2 (en) 2018-03-01 2021-01-12 General Electric Company Fuel injector assembly for gas turbine engine
JP7044669B2 (ja) * 2018-09-05 2022-03-30 三菱重工業株式会社 ガスタービン燃焼器
US10935245B2 (en) 2018-11-20 2021-03-02 General Electric Company Annular concentric fuel nozzle assembly with annular depression and radial inlet ports
US11286884B2 (en) 2018-12-12 2022-03-29 General Electric Company Combustion section and fuel injector assembly for a heat engine
US11073114B2 (en) 2018-12-12 2021-07-27 General Electric Company Fuel injector assembly for a heat engine
US11156360B2 (en) 2019-02-18 2021-10-26 General Electric Company Fuel nozzle assembly
EP4027059A1 (en) * 2021-01-12 2022-07-13 Crosstown Power GmbH Burner, combustor, and method for retrofitting a combustion appliance
US20230408097A1 (en) * 2021-11-03 2023-12-21 Power Systems Mfg., Llc Multitube pilot injector having a flame anchor for a gas tubine engine
AU2022421994A1 (en) * 2021-12-21 2024-06-27 Spark Thermionics, Inc. Burner system and method of operation
US12359813B2 (en) 2021-12-29 2025-07-15 General Electric Company Engine fuel nozzle and swirler
US12331932B2 (en) 2022-01-31 2025-06-17 General Electric Company Turbine engine fuel mixer
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
US20230266003A1 (en) * 2022-02-22 2023-08-24 Honeywell International Inc. Ultra-low nox multi-port burner apparatus
CN116642202B (zh) * 2023-02-28 2025-09-02 中山大学 一种带有定向调控燃油喷射的火焰稳定器
US12339006B1 (en) 2023-12-22 2025-06-24 General Electric Company Turbine engine having a combustion section with a fuel nozzle assembly

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1020491B (de) * 1941-01-24 1957-12-05 Bayerische Motoren Werke Ag Strahltriebwerk mit aufladbarer Brennkammer und nachgeschalteter Gasturbine oder Treibstrahlduese oder Gasturbine und Treibstrahlduese
DE805463C (de) * 1946-12-04 1951-05-21 Armstrong Siddeley Motors Ltd Brennkammer fuer fluessigen Brennstoff
DE806613C (de) * 1947-02-24 1951-06-14 Cem Comp Electro Mec Anordnung der Verbrennungskammern von Gasturbinen
GB657789A (en) * 1949-01-13 1951-09-26 Rolls Royce Improvements relating to liquid fuel combustion equipment for gas-turbine engines
US2565843A (en) * 1949-06-02 1951-08-28 Elliott Co Multiple tubular combustion chamber
DE1855295U (de) * 1961-03-06 1962-07-19 David Budworth Ltd Brennstoff-verdampfungsbrenner.
CH577627A5 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) * 1974-04-03 1976-07-15 Bbc Sulzer Turbomaschinen
GB1559779A (en) * 1975-11-07 1980-01-23 Lucas Industries Ltd Combustion assembly
US4052144A (en) * 1976-03-31 1977-10-04 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Fuel combustor
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
US4262482A (en) * 1977-11-17 1981-04-21 Roffe Gerald A Apparatus for the premixed gas phase combustion of liquid fuels
GB2012413B (en) * 1977-12-05 1982-03-24 Secr Defence Evaproative fuel injectors
GB2012415B (en) * 1978-01-04 1982-03-03 Secr Defence Fuel mixers
US4222232A (en) * 1978-01-19 1980-09-16 United Technologies Corporation Method and apparatus for reducing nitrous oxide emissions from combustors
US4215535A (en) * 1978-01-19 1980-08-05 United Technologies Corporation Method and apparatus for reducing nitrous oxide emissions from combustors

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4539811A (en) * 1982-01-27 1985-09-10 The United States Of America As Represented By The Secretary Of The Navy Multi-port dump combustor
EP0095788A1 (de) * 1982-05-28 1983-12-07 BBC Aktiengesellschaft Brown, Boveri & Cie. Brennkammer einer Gasturbine und Verfahren zu deren Betrieb
US4967561A (en) * 1982-05-28 1990-11-06 Asea Brown Boveri Ag Combustion chamber of a gas turbine and method of operating it
EP0526152A1 (en) * 1991-08-01 1993-02-03 General Electric Company Flashback resistant fuel staged premixed combustor
US5412938A (en) * 1992-06-29 1995-05-09 Abb Research Ltd. Combustion chamber of a gas turbine having premixing and catalytic burners
FR2695460A1 (fr) * 1992-09-09 1994-03-11 Snecma Chambre de combustion de turbomachine à plusieurs injecteurs.
US5713206A (en) * 1993-04-15 1998-02-03 Westinghouse Electric Corporation Gas turbine ultra low NOx combustor

Also Published As

Publication number Publication date
DE2950535A1 (de) 1981-06-11
CA1157280A (en) 1983-11-22
EP0029619A1 (de) 1981-06-03
US4408461A (en) 1983-10-11
DE3063624D1 (en) 1983-07-07
JPS5691132A (en) 1981-07-23
JPH0130055B2 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1989-06-15

Similar Documents

Publication Publication Date Title
EP0029619B1 (de) Brennkammer einer Gasturbine mit Vormisch/Vorverdampf-Elementen
EP2156095B1 (de) Drallfreie stabilisierung der flamme eines vormischbrenners
DE3222347C2 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
DE69024081T2 (de) Verfahren zur Verbrennung mit Gasvormischung und eine Verbrennungsvorrichtung zur Durchführung des Verfahrens
DE69513542T2 (de) Brennstoffdüse
DE69409428T2 (de) Zweistoffbrenner mit sehr niedrigem NOx-Ausstoss
DE69405281T2 (de) Vormischbrennkammer mit konzentrischen Ringkanälen
DE69632111T2 (de) Vormischbrenner für eine Gasturbinen-Brennkammer mit niedriger Schadstoffemission
DE69218576T2 (de) Brennkammer einer Gasturbine
DE69412484T2 (de) Verbrennungskammer eines gasturbinenmotors
DE60007946T2 (de) Eine Brennkammer
DE69822984T2 (de) Kraftstoffleitung
DE60215351T2 (de) Vormischungskammer für turbinenverbrennungskammer
EP0918191B1 (de) Brenner für den Betrieb eines Wärmeerzeugers
EP0924470B1 (de) Vormischbrennkammer für eine Gasturbine
DE69525920T2 (de) Brennstoffeinspritzeinrictung für mit gasförmigem oder flüssigem Brennstoff betriebene Turbine
EP0059490A1 (de) Ringbrennkammer mit Ringbrenner für Gasturbinen
CH698007A2 (de) Gestufte Mehrringdüse mit radialem Einlauf für mageres Vorgemisch und Zweistoff-Ringrohr-Brennkammer.
DE2731562A1 (de) Brenner fuer fluessige und/oder gasfoermige brennstoffe
WO2003098110A1 (de) Vormischbrenner
EP1436546A1 (de) Brenner für synthesegas
DE69910106T2 (de) Brennkammer
EP0481111A1 (de) Brennkammer einer Gasturbine
EP1645802A2 (de) Vormischbrenner
EP1730448B1 (de) Mehrfachbrenneranordnung zum betrieb einer brennkammer sowie verfahren zum betreiben der mehrfachbrenneranordnung

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 NL SE

17P Request for examination filed

Effective date: 19810725

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

Owner name: BBC AKTIENGESELLSCHAFT BROWN, BOVERI & CIE.

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

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

REF Corresponds to:

Ref document number: 3063624

Country of ref document: DE

Date of ref document: 19830707

ET Fr: translation filed
PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

26 Opposition filed

Opponent name: KRAFTWERK UNION AKTIENGESELLSCHAFT

Effective date: 19840301

PLBN Opposition rejected

Free format text: ORIGINAL CODE: 0009273

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

Free format text: STATUS: OPPOSITION REJECTED

27O Opposition rejected

Effective date: 19850502

NLR2 Nl: decision of opposition
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 19930127

Year of fee payment: 13

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

Ref country code: SE

Payment date: 19930915

Year of fee payment: 14

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

Ref country code: LI

Effective date: 19931031

Ref country code: CH

Effective date: 19931031

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: SE

Effective date: 19941017

EAL Se: european patent in force in sweden

Ref document number: 80200979.5

EUG Se: european patent has lapsed

Ref document number: 80200979.5

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

Ref country code: NL

Payment date: 19970919

Year of fee payment: 18

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: 19990501

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

Effective date: 19990501

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

Ref country code: GB

Payment date: 19990913

Year of fee payment: 20

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

Ref country code: DE

Payment date: 19990927

Year of fee payment: 20

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

Ref country code: FR

Payment date: 19990929

Year of fee payment: 20

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 EXPIRATION OF PROTECTION

Effective date: 20001015

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Effective date: 20001015

PLAB Opposition data, opponent's data or that of the opponent's representative modified

Free format text: ORIGINAL CODE: 0009299OPPO