EP0987493A1 - Brûleur pour générateur de chaleur - Google Patents

Brûleur pour générateur de chaleur Download PDF

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Publication number
EP0987493A1
EP0987493A1 EP98810922A EP98810922A EP0987493A1 EP 0987493 A1 EP0987493 A1 EP 0987493A1 EP 98810922 A EP98810922 A EP 98810922A EP 98810922 A EP98810922 A EP 98810922A EP 0987493 A1 EP0987493 A1 EP 0987493A1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
downstream
flow
burner according
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
EP98810922A
Other languages
German (de)
English (en)
Other versions
EP0987493B1 (fr
Inventor
Ken Haffner
Matthias Dr. Höbel
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.)
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 EP98810922A priority Critical patent/EP0987493B1/fr
Priority to DE59809222T priority patent/DE59809222D1/de
Priority to US09/379,470 priority patent/US6210152B1/en
Priority to JP24760699A priority patent/JP4344049B2/ja
Priority to CA002282153A priority patent/CA2282153A1/fr
Publication of EP0987493A1 publication Critical patent/EP0987493A1/fr
Application granted granted Critical
Publication of EP0987493B1 publication Critical patent/EP0987493B1/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
    • 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
    • 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
    • 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
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/82—Preventing flashback or blowback
    • 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
    • F23D—BURNERS
    • F23D23/00—Assemblies of two or more burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/02—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium
    • F23N5/08—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium using light-sensitive elements
    • F23N5/082—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium using light-sensitive elements using electronic means
    • 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
    • F23D2209/00—Safety arrangements
    • F23D2209/10—Flame flashback

Definitions

  • the present invention relates to a burner for a heat generator according to Preamble of claim 1. It also relates to a method of operation of such a burner.
  • premix burners are used in premix mode hazards.
  • Such premix burners are from EP-B1-0 321 809 and from DE-195 47 913.0 became known. Thanks to the upstream fuel injection such premix burners, the fuel is premixed with the air before the Combustion takes place. This will make it ignitable within the burner Mixture provided for further combustion.
  • the flame may become unstable. If the one that has jumped back can then stabilize within the burner, it burns as a diffusion flame at a very high temperature, approx. 1900 ° C. Within a short time in the range of 10 to max. 30 seconds, the burner overheats and is destroyed. The subsequent turbine blades may then be damaged; in any case, the gas turbine must be stopped, inspected and repaired, which leads to immense costs. It has been shown that there is a high risk in this regard, particularly in the case of prototype gas turbines with new combustion technology or the combustion of fuels containing hydrogen (MBtu or LBtu gases).
  • the invention seeks to remedy this.
  • the invention as set out in the claims is characterized, the task is based on one burner and one Propose measures of the type mentioned at the outset, by means of which stabilization of the flame in the burner is maximized.
  • the burner be fitted at a suitable point compact non-contact flame detector.
  • the main advantages of the invention are the fact that the burner attached sensor reports a flame back. Then the Reduced the amount of premix fuel and at the same time increased the amount of pilot fuel so that the total amount of fuel and thus the turbine power is constant remains. By which a reduction, i.e. the amount of premix fuel, is able the retracted flame no longer stabilizes in the burner, it is inevitably flushed out of the burner. This allows the destruction prevent the burner.
  • Such a sensor or flame monitor can be help of high temperature resistant Realize glass fibers.
  • the fibers are arranged in such a way that their control field endangered areas, but not the normal burning pilot and premix flame.
  • the UV component (approx. 300-330 nm) of the radiation detected by the sensor Spectrally analyzed with suitable filters. About the ratio of intensity Different wavelengths can be flashback in the burner within milliseconds be recognized. If the combustion chamber consists of a number of burners, suitable data acquisition can be used to determine which one Burner of flashback has occurred and suitable ones can be used Measures to remedy the causes are taken.
  • Fig. 1 shows a schematic overview of a premix burner, the Formation of such a burner is described in detail in Figs. 4-11.
  • this premix burner consists of a swirl generator 100 a mixing section 220 connected downstream of this swirl generator, in which the Mixing section 220 downstream combustion chamber 30 a system of pilot burners 300 acts with corresponding pilot flames 70.
  • the fuel injectors 116 is always observed to reignite from the combustion chamber 30 comes to the fuel injectors 116.
  • At least one sensor 400 becomes immediate placed downstream of the fuel injectors 116 and should not be the premix flame 50 still the pilot flames 70, but only the areas at risk to capture.
  • Such a sensor 400 preferably consists of high-temperature resistant ones Glass fibers, which are arranged so that their viewing angle 402 just that only the areas at risk are recorded.
  • the radiation detected by the sensor is forwarded 401 and spectrally analyzed with suitable filters. About the relationship The intensities at different wavelengths can cause a flashback can be recognized in the burner within milliseconds.
  • Data acquisition can be determined for which burner in the network the flashback has taken place, taking appropriate measures can be taken to remedy the cause.
  • Fig. 3 shows which measures are initiated after a flashback become.
  • a control 82 directly accesses the fuel quantity for the premix flame 50, which is immediately reduced according to certain criteria.
  • a second control 83 which determines the amount of fuel for the pilot burner system 300, i.e. for the pilot flame 70, increased. Aim this opposite The fuel supply is to keep the turbine output constant.
  • the Reduction of the amount of fuel for the premix flame 50 can be the struck back Do not stabilize the flame in the burner anymore, it will burn out washed out, which safely prevents the inevitable destruction of the burner becomes.
  • 3 shows the qualitative sequence of the fuel control over time, the flushing out at the extreme points of this control 84 the flame retreated.
  • Fig. 4 shows the overall structure of a burner that can be operated by swirl flow.
  • a swirl generator 100 is effective, the design of which follows in the following Fig. 5-8 is shown and described in more detail. It is about this swirl generator 100 around a cone-shaped structure, the multiple of one tangentially flowing combustion air flow 115 is applied.
  • the flow that forms here is based on a flow downstream of the swirl generator 100 provided transition geometry seamlessly transferred into a transition piece 200, in such a way that no separation areas can occur there.
  • This Transition piece 200 is through on the outflow side of the transition geometry a mixing tube 20 extends, both parts of the actual mixing section 220 form.
  • the mixing section 220 can be made from a single piece exist, i.e. then that the transition piece 200 and the mixing tube 20 into one single contiguous entities merge, the characteristics of each part are preserved.
  • transition piece 200 and Mixing tube 20 created from two parts these are through a sleeve ring 10 connected, the same sleeve ring 10 on the head side as an anchoring surface serves for the swirl generator 100.
  • Such a sleeve ring 10 also has the advantage that different mixing tubes can be used.
  • Outflow side of the mixing tube 20 there is the actual combustion chamber 30 Combustion chamber, which is only symbolized here by a flame tube.
  • 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 is that in it the axial velocity profile has a pronounced maximum on the axis, so that reignition of the flame from the combustion chamber itself is prevented should. However, it is correct that with such a configuration this Axial velocity drops towards the wall.
  • the mixing tube 20 in the flow and circumferential direction with a number of regularly or irregularly distributed holes Provide 21 different cross sections and directions, through which one Air flow into the interior of the mixing tube 20, and along the wall in the In the sense of filming, induce an increase in the flow rate.
  • These holes 21 can also be designed so that on the inner wall of the mixing tube 20 at least additionally an effusion cooling sets.
  • Another possibility is to increase the speed of the mixture To achieve within the mixing tube 20 is that Flow cross section downstream of the transition channels 201, which the form already mentioned transition geometry, undergoes a narrowing, whereby the entire speed level within the mixing tube 20 is raised becomes.
  • these bores 21 run at an acute angle the burner axis 60.
  • the outlet corresponds to the transition channels 201 the narrowest flow cross section of the mixing tube 20. Die named transition channels 201 therefore bridge the respective cross-sectional difference, without negatively influencing the flow formed.
  • a pilot burner system becomes concentric with the mixing tube 20 in the area of its outlet 300 provided.
  • This consists of an inner annular chamber 301, in which flows in a fuel, preferably a gaseous fuel 303.
  • a second annular chamber Dispatched 302 In addition to this inner annular chamber 301 is a second annular chamber Dispatched 302, into which an air quantity 304 flows.
  • Both annular chambers 301, 302 have individually designed through openings, such that the individual media 303, 304 functionally in a common downstream Flow ring chamber 308. Transfer of gaseous fuel 303 from the annular chamber 301 into the downstream annular chamber 308 by a Number of openings 309 arranged in the circumferential direction.
  • the Through geometry of these openings 309 is designed so that the gaseous Fuel 303 with a large mixing potential in the downstream Annulus 308 flows.
  • the other annular chamber 302 closes with one perforated plate 305, the holes 310 provided here designed so are that the amount of air 304 flowing through there is an impact cooling on the base plate 307 of the downstream ring chamber 308.
  • This base plate has the Function of a heat protection plate against the caloric load from the Combustion chamber 30, so that this impingement cooling must be extremely efficient here.
  • this air mixes within this annular chamber 308 with the inflowing gaseous fuel 303 from the openings 309 of the upstream annular chamber 301 before this mixture through a number of bores 306 arranged on the combustion chamber side into the combustion chamber 30 flows out.
  • the mixture flowing out burns as a premixed diffusion flame with minimized pollutant emissions and forms accordingly Bore 306 a pilot burner acting in the combustion chamber 30, which one guaranteed stable operation.
  • the secondary annular chamber 302 through which air flows is an ignition device 311 passed through, which in the downstream annular chamber 308 Ignition of the mixture formed there.
  • this ignition device 311 is constantly by the air 304 flowing there is cooled anyway. This is very important because when using it temperatures of approx. 1000 ° C can be reached with a glow plug. However, since there is only a low voltage for the operation proposed here, high current is required, the susceptibility of the ignition device is therefore eliminated against condensation water. Due to the arrangement of the glow plug, whereby the use of a spark plug is also possible within of the burner, the respective ignition device 311 is thermally slightly loaded, which means that no additional cooling is required and leakages are eliminated avoided.
  • FIG. 5 shows a schematic view of the burner according to FIG. 4, here in particular the flushing of a centrally arranged fuel nozzle 103 (See FIG. 6) and the effect of fuel injectors 170 is pointed out.
  • the mode of operation of the remaining main components of the burner, namely swirl generator 100 and transition piece 200 are among the following figures described in more detail.
  • the fuel nozzle 103 is spaced apart Ring 190 encased, in which a number arranged in the circumferential direction Bores 161 are placed through which an amount of air 160 in an annular Chamber 180 flows and rinses the fuel lance there. This Bores 161 are slanted forward so that it is adequate axial component arises on the burner axis 60.
  • FIG. 7 is used at the same time as FIG. 6.
  • 6 is referred to the other figures as required in the description of FIG. 6.
  • the first part of the burner according to FIG. 4 forms the swirl generator shown in FIG. 6 100.
  • This consists of two hollow conical partial bodies 101, 102, which are nested in a staggered manner.
  • the number of conical Partial body can of course be larger than two, like the figures 5 and 6 show; this depends in each case, as explained in more detail below will depend on the operating mode of the entire burner. It is with certain Operating constellations are not excluded, one from a single spiral to provide existing swirl generator.
  • the offset of the respective central axis or longitudinal symmetry axes 101b, 102b (see FIG. 7) of the conical partial bodies 101, 102 creates each other in the adjacent wall, in mirror image Arrangement, each a tangential channel, i.e.
  • the cone shape the partial body 101, 102 shown in the flow direction has a certain one fixed angle.
  • the partial bodies can 101, 102 an increasing or decreasing cone inclination in the flow direction have, similar to a diffuser or confuser.
  • the latter two Shapes are not recorded in the drawing, as they are without for the specialist are further sensitive.
  • the two conical partial bodies 101, 102 have each have a cylindrical annular starting part 101a in the area of this cylindrical Initially, the fuel nozzle 103 already mentioned under FIG.
  • the tapered partial bodies 101, 102 also each have a fuel direction 108, 109 to which along the tangential air inlet slots 119, 120 are arranged and provided with injection openings 117 through which preferably a gaseous fuel 113 in the combustion air flowing through there 115 is injected, as the arrows 116 want to symbolize.
  • fuel lines 108, 109 are preferably at the end of the latest tangential inflow, before entering the cone cavity 114, this to get an optimal air / fuel mixture.
  • fuel 112 is, as mentioned, in Normally a liquid fuel, whereby a mixture formation with a other medium, for example with a recirculated flue gas, without further ado is possible.
  • This fuel 112 is preferably very pointed under one Angle injected into the cone cavity 114.
  • the concentration of the injected fuel 112 then becomes axial continuously through the incoming combustion air 115 for mixing Degraded towards evaporation. If a gaseous fuel 113 over the Introduced opening nozzles 117, the fuel / air mixture is formed directly at the end of the air inlet slots 119, 120. Is the combustion air 115 additionally preheated, or for example with a recirculated Enriched with flue gas or exhaust gas, this sustainably supports evaporation of liquid fuel 112 before this mixture is downstream Stage flows, here in the transition piece 200 (see FIGS. 4 and 10). The same Considerations also apply if liquid lines 108, 109 Fuels should be supplied.
  • the construction of the swirl generator 100 is furthermore particularly suitable, change the size of the tangential air inlet slots 119, 120, which is a relatively large one without changing the overall length of the swirl generator 100 operational bandwidth can be recorded.
  • the partial bodies 101, 102 can also be moved relative to each other in another plane, which even an overlap of the same can be provided. It is further possible, the partial body 101, 102 by a counter-rotating movement spiral to nest into each other. So it is possible, the shape, the size and to vary the configuration of the tangential air inlet slots 119, 120 as desired, which makes the swirl generator 100 universal without changing its overall length can be used.
  • FIG. 7 shows, among other things, the geometric configuration of optional ones Baffles 121a, 121b. They have a flow initiation function which, according to their length, the respective end of the tapered Partial bodies 101, 102 in the flow direction with respect to the combustion air 115 extend.
  • the channeling of the combustion air 115 into the cone cavity 114 can be opened or closed by one of the baffles 121a, 121b Area of entry of this channel into the fulcrum 114 placed cone cavity 123 can be optimized, especially if the original Gap size of the tangential air inlet slots 119, 120 changed dynamically should be, for example, to change the speed of the combustion air 115 to achieve.
  • these can be dynamic Precautions can also be provided statically by using baffles as needed form a fixed component with the conical partial bodies 101, 102.
  • the swirl generator 100 now consists of four partial bodies 130, 131, 132, 133 is constructed.
  • the associated longitudinal symmetry axes for each sub-body are marked with the letter a. To this Configuration is to be said that it is due to the lower generated with it Twist strength and in cooperation with a correspondingly enlarged Slot width is best suited, the bursting of the vortex flow on the downstream side to prevent the swirl generator in the mixing tube, thus causing the mixing tube to can fulfill the intended role.
  • FIG. 9 differs from FIG. 8 in that the partial body 140, 141, 142, 143 have a blade profile shape which is used to provide a certain Flow is provided. Otherwise, the mode of operation of the swirl generator stayed the same.
  • the admixture of fuel 116 in the combustion air flow 115 happens from inside the blade profiles, i.e. the fuel line 108 is now integrated in the individual blades.
  • the transition geometry is corresponding for a swirl generator 100 with four partial bodies 5 or 6, built. Accordingly, the transition geometry as a natural extension of the upstream partial bodies, four transition channels 201 on which extends the conical quarter area of the partial bodies mentioned until it cuts the wall of the mixing tube.
  • the swirl generator is based on a principle other than the one below Fig. 4, is constructed.
  • the down in the direction of flow running surface of the individual transition channels 201 has a flow direction spiral shape on which a crescent shape Course describes, corresponding to the fact that the flow cross-section is present of the transition piece 200 is flared in the direction of flow
  • the swirl angle of the transition channels 201 in the flow direction is so chosen that the pipe flow then up to the cross-sectional jump on Combustion chamber entrance still has a sufficient distance to be perfect Premix with the injected fuel.
  • Further increases the axial speed is also affected by the above-mentioned measures on the mixing tube wall downstream of the swirl generator.
  • the transition geometry and the measures in the area of the mixing tube bring about a significant increase of the axial velocity profile towards the center of the mixing tube, see above that the danger of early ignition is decisively counteracted.
  • Fig. 11 shows the tear-off edge already mentioned, which emerges 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 °.
EP98810922A 1998-09-16 1998-09-16 Brûleur pour générateur de chaleur Expired - Lifetime EP0987493B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP98810922A EP0987493B1 (fr) 1998-09-16 1998-09-16 Brûleur pour générateur de chaleur
DE59809222T DE59809222D1 (de) 1998-09-16 1998-09-16 Brenner für einen Wärmeerzeuger
US09/379,470 US6210152B1 (en) 1998-09-16 1999-08-24 Burner for a heat generator and method for operating the same
JP24760699A JP4344049B2 (ja) 1998-09-16 1999-09-01 熱発生器用のバーナ
CA002282153A CA2282153A1 (fr) 1998-09-16 1999-09-13 Bruleur pour generateur thermique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98810922A EP0987493B1 (fr) 1998-09-16 1998-09-16 Brûleur pour générateur de chaleur

Publications (2)

Publication Number Publication Date
EP0987493A1 true EP0987493A1 (fr) 2000-03-22
EP0987493B1 EP0987493B1 (fr) 2003-08-06

Family

ID=8236324

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810922A Expired - Lifetime EP0987493B1 (fr) 1998-09-16 1998-09-16 Brûleur pour générateur de chaleur

Country Status (5)

Country Link
US (1) US6210152B1 (fr)
EP (1) EP0987493B1 (fr)
JP (1) JP4344049B2 (fr)
CA (1) CA2282153A1 (fr)
DE (1) DE59809222D1 (fr)

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EP2669577A1 (fr) * 2012-05-30 2013-12-04 General Electric Company Détection de flamme dans une région non ignifuge de turbine à gaz

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US6357216B1 (en) * 2000-09-27 2002-03-19 Honeywell International, Inc. Flashback control for a gas turbine engine combustor having an air bypass system
EP1423561B1 (fr) * 2001-08-31 2018-06-27 Nano-C, Inc. Procede de synthese par combustion de fullerenes
EP1389713A1 (fr) * 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Brûleur pilote annulaire pour sortie de brûleur à prémélange
US7303388B2 (en) * 2004-07-01 2007-12-04 Air Products And Chemicals, Inc. Staged combustion system with ignition-assisted fuel lances
WO2006048405A1 (fr) * 2004-11-03 2006-05-11 Alstom Technology Ltd Bruleur a premelange
US7546737B2 (en) * 2006-01-24 2009-06-16 Honeywell International Inc. Segmented effusion cooled gas turbine engine combustor
US7789659B2 (en) * 2006-02-24 2010-09-07 9131-9277 Quebec Inc. Fuel injector, burner and method of injecting fuel
EP1999410B1 (fr) * 2006-03-27 2015-12-02 Alstom Technology Ltd Bruleur pour le fonctionnement d'un generateur de chaleur
US8617811B2 (en) * 2008-01-28 2013-12-31 Complete Genomics, Inc. Methods and compositions for efficient base calling in sequencing reactions
US20090249789A1 (en) * 2008-04-08 2009-10-08 Baifang Zuo Burner tube premixer and method for mixing air and gas in a gas turbine engine
EP2110601A1 (fr) * 2008-04-15 2009-10-21 Siemens Aktiengesellschaft Brûleur
US9353947B2 (en) * 2009-06-11 2016-05-31 General Electric Company Combustor flashback/flame holding detection via temperature sensing
EP2423591B1 (fr) * 2010-08-24 2018-10-31 Ansaldo Energia IP UK Limited Procédé de fonctionnement d'une chambre de combustion
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
EP3290804A1 (fr) * 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Brûleur avec alimentation d'air et de carburant incorporée dans une paroi du brûleur
EP3617599A1 (fr) * 2018-09-03 2020-03-04 Siemens Aktiengesellschaft Brûleur à mélange air-carburant amélioré
EP4202308A1 (fr) * 2021-12-21 2023-06-28 Ansaldo Energia Switzerland AG Brûleur de prémélange pour un ensemble de turbine à gaz de centrale électrique adapté pour être alimenté avec des combustibles communs et très réactifs, son procédé de fonctionnement et ensemble de turbine à gaz de centrale électrique comprenant ce brûleur
CN114234190B (zh) * 2021-12-24 2023-07-04 中科卓异环境科技(东莞)有限公司 一种多孔介质燃烧器及燃烧方法

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EP0816760A1 (fr) * 1996-06-24 1998-01-07 General Electric Company Détection de retour de flamme par fibre optique
WO1998021450A1 (fr) * 1996-11-12 1998-05-22 Siemens Westinghouse Power Corporation Dispositif combustor avec systeme de retour de flamme

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2669577A1 (fr) * 2012-05-30 2013-12-04 General Electric Company Détection de flamme dans une région non ignifuge de turbine à gaz
US9335046B2 (en) 2012-05-30 2016-05-10 General Electric Company Flame detection in a region upstream from fuel nozzle

Also Published As

Publication number Publication date
DE59809222D1 (de) 2003-09-11
CA2282153A1 (fr) 2000-03-16
EP0987493B1 (fr) 2003-08-06
JP2000097407A (ja) 2000-04-04
US6210152B1 (en) 2001-04-03
JP4344049B2 (ja) 2009-10-14

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