EP0918191A1 - Brûleur pour la mise en oeuvre d'un générateur de chaleur - Google Patents

Brûleur pour la mise en oeuvre d'un générateur de chaleur Download PDF

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Publication number
EP0918191A1
EP0918191A1 EP97810894A EP97810894A EP0918191A1 EP 0918191 A1 EP0918191 A1 EP 0918191A1 EP 97810894 A EP97810894 A EP 97810894A EP 97810894 A EP97810894 A EP 97810894A EP 0918191 A1 EP0918191 A1 EP 0918191A1
Authority
EP
European Patent Office
Prior art keywords
fuel
flow
burner according
burner
swirl generator
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
EP97810894A
Other languages
German (de)
English (en)
Other versions
EP0918191B1 (fr
Inventor
Klaus Dr. Döbbeling
Hans Peter Knöpfel
Thomas Ruck
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.)
Alstom SA
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 AT97810894T priority Critical patent/ATE244380T1/de
Priority to DE59710380T priority patent/DE59710380D1/de
Priority to EP97810894A priority patent/EP0918191B1/fr
Priority to US09/192,531 priority patent/US6155820A/en
Priority to JP33132098A priority patent/JP4130716B2/ja
Publication of EP0918191A1 publication Critical patent/EP0918191A1/fr
Application granted granted Critical
Publication of EP0918191B1 publication Critical patent/EP0918191B1/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
    • 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
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • 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
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air

Definitions

  • the invention relates to a burner for operating a heat generator according to Preamble of claim 1.
  • the upstream side consists of a swirl generator, the flow formed therein seamlessly in a mixing section is transferred. This is done using one at the beginning of the Mixing section flow geometry formed for this purpose, which consists of transition channels exists, which is sectoral, according to the number of those acting Partial body of the swirl generator, capture the end face of the mixing section and in Flow direction swirl. Downstream of these transition channels the mixing section has a number of filming holes, which one Ensure an increase in the flow velocity along the pipe wall. This is followed by a combustion chamber, the transition between the Mixing section and the combustion chamber formed by a cross-sectional jump in whose plane a backflow zone or backflow bubble forms.
  • the Twist strength in the swirl generator is selected so that the bursting of the Vortex does not occur within the mixing section, but further downstream, as executed above, in the area of the cross-sectional jump.
  • the swirl generator fulfills here the function of a premix section. This consists of at least two hollow, conical, nested partial bodies in the direction of flow, the respective axes of longitudinal symmetry of the individual partial bodies relative to one another run away. As a result, the adjacent walls of the partial body form in the longitudinal extension tangential inflow channels for a combustion air flow, at least in the interior formed by the partial bodies a fuel nozzle works.
  • the burner changes to a diffusion mode, which then inevitably leads to high NO x emissions.
  • the burner threatens to overheat or even burn parts of it.
  • the fuel is therefore injected as far downstream as possible so that the flame cannot strike back upstream.
  • the fuel is diluted with water vapor or nitrogen, but in both cases the efficiency is reduced.
  • the invention seeks to remedy this.
  • the invention as set out in the claims is characterized, the task is based on a burner at the beginning to propose the above-mentioned type of precautions which ensure good mixing when Use of a low-calorie fuel with minimized pollutant emissions and ensure maximum efficiency.
  • the swirl generator receives one in addition to the air inlet channels second independent fuel guide, preferably designed as a channel which the low calorific fuel is brought in. This will then be more adequate Way mixed with the combustion air flow, so that it too A partial mixture of the two media comes before it enters the wider interior of the swirl generator flow.
  • Burner can now be used for any fuel.
  • the inventive Burner operated for example with a liquid fuel, so the nozzle arranged at the head is preferably used, its mode of operation emerges from the publication mentioned at the beginning.
  • the fuel nozzles come with a gaseous fuel with a higher calorific value to be used, which along the tangential inflow channels transition to the interior are arranged.
  • the expansion according to the invention comes into play when the heating value is low. This Expansion of the operation of the burner with a low-calorie fuel is possible because it is injected into the combustion air a distance happens upstream of the transition to the interior of the swirl generator.
  • Another advantage of the invention is that the fuel is isokinetic can be injected, with which high turbulence between the injected Fuel and the combustion air flow is prevented, with a kickback the flame is permanently suppressed.
  • Fig. 1 shows the overall structure of a burner. Initially there is a swirl generator 100 effective, the design of which can be seen in more detail in connection with FIG. 2 is.
  • the swirl flow that forms in this swirl generator 100 is determined using a transition geometry provided downstream seamlessly into a transition piece 200 transferred, such that there are no detachment areas in this zone can form.
  • the configuration of this transition geometry is described in more detail in FIG. 3.
  • the swirl generator 100 is described below using FIG. 2.
  • This consists of four hollow, conical partial bodies 101, 102, 103, 104 (See Fig. 2), which are nested offset from one another.
  • the dislocation of the respective central axis 101a-104a (see FIG. 2) to each other creates on each Side a tangential inflow duct 101b-104b (see FIG. 2), through which combustion air 115 flows into interior 118 of swirl generator 100.
  • the conical shape of the partial bodies 101-104 shown in the flow direction has one certain fixed angle. Of course, depending on the operational use, you can the partial bodies 101-104 are increasing or decreasing in the direction of flow Show cone inclination, similar to a trumpet. Tulip.
  • the partial body 101-104 have a cylindrical Initial part, the design of which is described in more detail in FIG. 5.
  • the swirl generator 100 can be purely conical, ie without the cylindrical one Initial part to be formed.
  • the partial bodies 101-104 each have one channel 121, 122, 123, displaced inward and also tangentially guided 124 (see also FIG. 2), through which a gaseous fuel 117 is introduced which is in each case via an axially extending inflow slot 131, which extends parallel or quasi-parallel to the course of the partial bodies 101-104, into the tangential combustion air inlet channels 101b-104b is injected.
  • the flow cross section and the course of this inflow slot 131 is the pressure and the amount of fuel to be introduced 117 adjusted.
  • the two streams namely the combustion air 115 and the gaseous fuel 117, until their first mixing, before the Inflow into the interior 118 occurs independently.
  • the fuel 117 is upstream of the combustion air 115 for a distance the transition of the tangential inflow channels 101b-104b into the interior 118 mixed. It is thereby achieved that the two media by Have already mixed entry into the interior 118. Can be constructively achieve this by the fuel-carrying channels 121-124 the respective Part body 101-104 are set up as independent guides.
  • the flow openings of the two media 115, 117 up to the level of their mixing designed so that they flow through an approximately equal mass flow allow, which is always necessary if the burner with an LBTU or MBTU gas is operated.
  • the gaseous fuel 117 flows out the gas-carrying channels 121-124, as already mentioned, via the inflow slots 131 on the inside of the combustion air flow 115.
  • the mixing level is, as mentioned, a distance upstream of the crossing of the tangential inflow channels 101b-104b into the interior 118. In the interior 118 thus flows in a premixed mixture 130.
  • the flow guidance of the media 115, 117 can be interchanged be.
  • the mixing of these two media before entering the interior 118 takes place through the mutually forming shear forces, which is quite intense Partial mixing results.
  • the further premixing section in the swirl generator 100 then ensures the final provision of an optimal homogeneous mixture between the two media 115, 117.
  • the combustion air 115 is additional preheated or enriched with a recirculated exhaust gas, so supported this sustainably the degree of mixing of the two media.
  • the swirl generator 100 is further provided with a central fuel nozzle 105, which acts as a head step.
  • This fuel nozzle is preferably included a liquid fuel 106 operated. However, it is also possible to do this To operate the nozzle with a gaseous fuel.
  • a liquid fuel 106 When introducing a liquid fuel 106 through the nozzle 105 forms in the cone cavity 118 conical fuel profile 107, which flows in from the tangential and swirl Combustion air 115 is encased.
  • the combustion air flowing in here 115 can be replaced by the mixture 115/117 described above Direction, the concentration of the fuel 106 is continuously increased by the inflowing Combustion air 115 is broken down into a mixture.
  • the swirl generator 100 also has along the tangential inflow channels 101b-104b each have a fuel line 111-114 through which a fuel 116 flows, this fuel at the transition to the interior 118 over into the Fuel line integrated openings injected into the combustion air flow 115 becomes. Operation of the burner with fuel from lines 111-114 can be accomplished because the tangential fuel channels 121-124 do not extend to the transition into the interior 118 of the swirl generator 100.
  • the number of the conical partial bodies 101-104 is not limited to four. Swirl generators with only two tangential inflow channels are also possible.
  • the transition piece 200 is on the outflow side of the transition geometry (cf. Fig. 3) extended by a mixing tube 20, both parts of the actual Form mixing section 220.
  • the mixing section 220 can consist of one consist of only one piece, i.e. then that the transition piece 200 and that Mix the mixing tube 20 into a single coherent structure, keeping the characteristics of each part.
  • a transition piece 200 and mixing tube 20 made of two parts these are through a socket ring 10 connected, the same socket ring 10 on the head side as Anchoring surface for the swirl generator 100 is used.
  • Such a bushing ring 10 also has the advantage that different mixing tubes are used can, without having to change anything in the basic configuration.
  • the Mixing section 220 largely fulfills the task that is downstream of the swirl generator 100 a defined route is provided, in which a perfect premix of different types of fuel can be achieved.
  • This mixing section so primarily the mixing tube 20, also allows lossless Flow guidance, so that it is also in operative connection with the transition geometry initially do not form a backflow zone or backflow bubble can, thus over the length of the mixing section 220 to the mixing quality for all Fuel types influence can be exerted.
  • this mixing section 220 has yet another property, which consists in the fact that it contains the axial velocity profile has a pronounced maximum on the axis, so that back-ignition of the flame from the combustion chamber is not possible. Indeed it is correct that with such a configuration this axial speed is used for Wall falls down.
  • These holes 21 can also be so be designed that at least on the inner wall of the mixing tube 20 additionally sets an effusion cooling.
  • Transition channels 201 which form the transition geometry already mentioned, undergoes a constriction, causing the overall speed level to be within of the mixing tube 20 is raised.
  • These holes run in the figure 21 at an acute angle with respect to the burner axis 60.
  • the outlet of the transition channels 201 corresponds to the narrowest flow cross-section of the mixing tube 20. Bridge the mentioned transition channels 201 accordingly the respective cross-sectional difference without the formed To influence flow negatively.
  • a diffuser not shown in the figure, is provided at the end of this mixing tube becomes.
  • a combustion chamber then closes at the end of the mixing tube 20 (Combustion chamber 30), with a between the two flow cross-sections there is a cross-sectional jump formed by a burner front 70. Only here a central flame front is formed with a backflow zone 50 which is opposite the flame front has the characteristics of a disembodied flame holder having.
  • the transition geometry is corresponding for a swirl generator 100 with four partial bodies 1, 2 constructed. Accordingly, the transition geometry points as Natural extension of the upstream part of the four transition channels 201 on, whereby the conical quarter area of said partial body is extended until it cuts the wall of the mixing tube.
  • the same considerations also apply if the swirl generator is based on a principle other than the one below Fig. 1, 2 described, is constructed.
  • the one running downward in the direction of flow The surface of the individual transition channels 201 has one in the flow direction spiral shape, which has a crescent shape describes, in accordance with the fact that in the present case the flow cross-section of the transition piece 200 flared in the flow direction.
  • the helix angle of the transition channels 201 in the flow direction is selected such that the pipe flow then up to the cross-sectional jump at the combustion chamber inlet there is still a long enough distance to make a perfect premix with the injected fuel. Furthermore, increases the axial speed at the Mixing tube wall downstream of the swirl generator.
  • the transition geometry and the Measures in the area of the mixing tube result in a significant increase in Axial velocity profile towards the center of the mixing tube, so that the Danger of early ignition is decisively counteracted.
  • Fig. 4 shows the tear-off edge already mentioned, which exits at the burner is formed.
  • the flow cross section of the tube 20 receives one in this area Transition radius R, the size of which basically depends on the flow within of the tube 20 depends.
  • This radius R is chosen so that the Applies flow to the wall and so the swirl number increases sharply.
  • the size of the radius R can be defined so that it is> 10% of the inside diameter d of the tube is 20.
  • the backflow bladder 50 increases enormously.
  • This radius R runs to the exit plane of the tube 20, the angle ⁇ between the beginning and end of curvature is ⁇ 90 °.
  • FIG. 5 shows a schematic view of the burner according to FIG. 1, here in particular the flushing of a centrally arranged fuel nozzle 105 and the effect of fuel injectors 170 is pointed out.
  • the mode of action the remaining main components of the burner, namely swirl generator 100 and transition piece 200 has been described in more detail above.
  • the Fuel nozzle 105 is encased with a spaced ring 190 in which a number of holes 161, which are arranged in the circumferential direction, through which an amount of air 160 flows into an annular chamber 180 and there rinsing the fuel lance. These holes 161 are oblique laid out forward so that an adequate axial component is on the burner axis 60 is formed.
  • Additional fuel injectors 170 are provided, which have a certain amount preferably enter a gaseous fuel into the respective air volume 160, such that there is a uniform fuel concentration in the mixing tube 20 150 over the flow cross-section, as shown in the Figure symbolizes. Exactly this even fuel concentration 150, in particular the strong concentration on the burner axis 60 ensures that the flame front stabilizes at the burner outlet, thus avoiding combustion chamber pulsations.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Gas Burners (AREA)
  • Sorption Type Refrigeration Machines (AREA)
EP97810894A 1997-11-21 1997-11-21 Brûleur pour la mise en oeuvre d'un générateur de chaleur Expired - Lifetime EP0918191B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
AT97810894T ATE244380T1 (de) 1997-11-21 1997-11-21 Brenner für den betrieb eines wärmeerzeugers
DE59710380T DE59710380D1 (de) 1997-11-21 1997-11-21 Brenner für den Betrieb eines Wärmeerzeugers
EP97810894A EP0918191B1 (fr) 1997-11-21 1997-11-21 Brûleur pour la mise en oeuvre d'un générateur de chaleur
US09/192,531 US6155820A (en) 1997-11-21 1998-11-17 Burner for operating a heat generator
JP33132098A JP4130716B2 (ja) 1997-11-21 1998-11-20 熱発生器を稼働するためのバーナ

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810894A EP0918191B1 (fr) 1997-11-21 1997-11-21 Brûleur pour la mise en oeuvre d'un générateur de chaleur

Publications (2)

Publication Number Publication Date
EP0918191A1 true EP0918191A1 (fr) 1999-05-26
EP0918191B1 EP0918191B1 (fr) 2003-07-02

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EP97810894A Expired - Lifetime EP0918191B1 (fr) 1997-11-21 1997-11-21 Brûleur pour la mise en oeuvre d'un générateur de chaleur

Country Status (5)

Country Link
US (1) US6155820A (fr)
EP (1) EP0918191B1 (fr)
JP (1) JP4130716B2 (fr)
AT (1) ATE244380T1 (fr)
DE (1) DE59710380D1 (fr)

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DE10029607A1 (de) * 2000-06-15 2001-12-20 Alstom Power Nv Brenner mit gestufter Vormischgas-Eindüsung
WO2001096785A1 (fr) * 2000-06-15 2001-12-20 Alstom (Switzerland) Ltd Procede pour l'exploitation d'un bruleur et bruleur a injection etagee de gaz premelange
EP1201995A2 (fr) * 2000-10-23 2002-05-02 ALSTOM Power N.V. Sytème de combustion pour turbine à gaz
US7520745B2 (en) 2004-10-18 2009-04-21 Alstom Technology Ltd. Burner for a gas turbine
EP2685161A1 (fr) * 2012-07-10 2014-01-15 Alstom Technology Ltd Agencement de chambre de combustion, en particulier pour turbine à gaz
EP2722591A1 (fr) * 2012-10-22 2014-04-23 Alstom Technology Ltd Brûleur à multiples cones pour une turbine à gaz

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US7681104B1 (en) * 2004-08-09 2010-03-16 Bakbone Software, Inc. Method for erasure coding data across a plurality of data stores in a network
US7421843B2 (en) * 2005-01-15 2008-09-09 Siemens Power Generation, Inc. Catalytic combustor having fuel flow control responsive to measured combustion parameters
CN101137869A (zh) * 2005-03-09 2008-03-05 阿尔斯托姆科技有限公司 用于使燃烧室运转的预混燃烧器
CN101137868A (zh) * 2005-03-09 2008-03-05 阿尔斯通技术有限公司 用于产生可燃燃料/气体混合物的预混燃烧器
CA2537685C (fr) * 2006-02-24 2013-05-14 9131-9277 Quebec Inc. Injecteur de combustible, bruleur et methode d'injection
EP1985924A1 (fr) * 2007-04-23 2008-10-29 Siemens Aktiengesellschaft Dispositif de tourbillonnement
US8650881B2 (en) * 2009-06-30 2014-02-18 General Electric Company Methods and apparatus for combustor fuel circuit for ultra low calorific fuels
EP2685163B1 (fr) 2012-07-10 2020-03-25 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
EP2685160B1 (fr) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
US20150211462A1 (en) * 2012-08-01 2015-07-30 3M Innovative Properties Company Fuel injector nozzles with at least one multiple inlet port and/or multiple outlet port
JP5584260B2 (ja) * 2012-08-08 2014-09-03 日野自動車株式会社 排気浄化装置用バーナー
CA2830031C (fr) 2012-10-23 2016-03-15 Alstom Technology Ltd. Bruleur pour chambre de combustion tubulaire unique
USD787041S1 (en) * 2015-09-17 2017-05-16 Whirlpool Corporation Gas burner
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US11777190B2 (en) 2015-12-29 2023-10-03 Whirlpool Corporation Appliance including an antenna using a portion of appliance as a ground plane
US10145568B2 (en) 2016-06-27 2018-12-04 Whirlpool Corporation High efficiency high power inner flame burner
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US10660162B2 (en) 2017-03-16 2020-05-19 Whirlpool Corporation Power delivery system for an induction cooktop with multi-output inverters
PL422320A1 (pl) * 2017-07-24 2019-01-28 Instytut Lotnictwa Wtryskiwacz przebogaconej mieszanki paliwowo-powietrznej do komory spalania silników spalinowych
US10627116B2 (en) 2018-06-26 2020-04-21 Whirlpool Corporation Ventilation system for cooking appliance
US10619862B2 (en) 2018-06-28 2020-04-14 Whirlpool Corporation Frontal cooling towers for a ventilation system of a cooking appliance
US10837652B2 (en) 2018-07-18 2020-11-17 Whirlpool Corporation Appliance secondary door
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures

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Publication number Priority date Publication date Assignee Title
EP0433790A1 (fr) * 1989-12-22 1991-06-26 Asea Brown Boveri Ag BrÀ»leur
EP0710797A2 (fr) * 1994-11-05 1996-05-08 Abb Research Ltd. Procédé et dispositif de mise en oeuvre d'un brûleur à prémélange
EP0724114A2 (fr) * 1995-01-30 1996-07-31 ABB Management AG Brûleur
EP0747635A2 (fr) * 1995-06-05 1996-12-11 Allison Engine Company, Inc. Brûleur à prémélange pauvre avec faible production de NOx pour turbines à gaz industrielles
DE19545310A1 (de) * 1995-12-05 1997-06-12 Asea Brown Boveri Vormischbrenner
EP0780629A2 (fr) 1995-12-21 1997-06-25 ABB Research Ltd. Brûleur pour un générateur de chaleur
DE19548851A1 (de) * 1995-12-27 1997-07-03 Asea Brown Boveri Vormischbrenner
EP0807787A2 (fr) * 1996-05-17 1997-11-19 Abb Research Ltd. Brûleur

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10029607A1 (de) * 2000-06-15 2001-12-20 Alstom Power Nv Brenner mit gestufter Vormischgas-Eindüsung
WO2001096785A1 (fr) * 2000-06-15 2001-12-20 Alstom (Switzerland) Ltd Procede pour l'exploitation d'un bruleur et bruleur a injection etagee de gaz premelange
US6769903B2 (en) 2000-06-15 2004-08-03 Alstom Technology Ltd Method for operating a burner and burner with stepped premix gas injection
EP1201995A2 (fr) * 2000-10-23 2002-05-02 ALSTOM Power N.V. Sytème de combustion pour turbine à gaz
EP1201995A3 (fr) * 2000-10-23 2002-07-24 ALSTOM Power N.V. Sytème de combustion pour turbine à gaz
US6684640B2 (en) 2000-10-23 2004-02-03 Alstom Power N.V. Gas turbine engine combustion system
US7520745B2 (en) 2004-10-18 2009-04-21 Alstom Technology Ltd. Burner for a gas turbine
EP2685161A1 (fr) * 2012-07-10 2014-01-15 Alstom Technology Ltd Agencement de chambre de combustion, en particulier pour turbine à gaz
JP2014016150A (ja) * 2012-07-10 2014-01-30 Alstom Technology Ltd 特にガスタービン用の燃焼器配列
US9933163B2 (en) 2012-07-10 2018-04-03 Ansaldo Energia Switzerland AG Combustor arrangement with slidable multi-cone premix burner
EP2722591A1 (fr) * 2012-10-22 2014-04-23 Alstom Technology Ltd Brûleur à multiples cones pour une turbine à gaz
US9464810B2 (en) 2012-10-22 2016-10-11 General Electric Technology Gmbh Burner including a swirl chamber with slots having different widths

Also Published As

Publication number Publication date
ATE244380T1 (de) 2003-07-15
DE59710380D1 (de) 2003-08-07
JPH11223306A (ja) 1999-08-17
US6155820A (en) 2000-12-05
JP4130716B2 (ja) 2008-08-06
EP0918191B1 (fr) 2003-07-02

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