EP0919768B1 - 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
EP0919768B1
EP0919768B1 EP97810907A EP97810907A EP0919768B1 EP 0919768 B1 EP0919768 B1 EP 0919768B1 EP 97810907 A EP97810907 A EP 97810907A EP 97810907 A EP97810907 A EP 97810907A EP 0919768 B1 EP0919768 B1 EP 0919768B1
Authority
EP
European Patent Office
Prior art keywords
burner according
burner
radius
flow
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.)
Expired - Lifetime
Application number
EP97810907A
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German (de)
English (en)
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EP0919768A1 (fr
Inventor
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
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Alstom SA
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 Alstom SA filed Critical Alstom SA
Priority to AT97810907T priority Critical patent/ATE232282T1/de
Priority to EP97810907A priority patent/EP0919768B1/fr
Priority to DE59709281T priority patent/DE59709281D1/de
Priority to US09/196,115 priority patent/US5954490A/en
Publication of EP0919768A1 publication Critical patent/EP0919768A1/fr
Application granted granted Critical
Publication of EP0919768B1 publication Critical patent/EP0919768B1/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
    • 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
    • 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
    • F23D11/40—Mixing tubes; 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
    • F23D14/46—Details
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/74—Preventing flame lift-off
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion simultaneously or alternately 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

Definitions

  • the present invention relates to a burner for operating a heat generator according to claim 1.
  • a further premix burner has become known, in which Measures are taken to move the backflow bubble further downstream, this to get a longer premixing and evaporation distance.
  • a swirl generator acting on the head side of the premix burner which is based here on the premix burner according to EP-0 312 809 B1, a mixing tube downstream, with a transition geometry between the swirl generator and the mixing tube which is switched from transition channels to non-detachable Transfer of the swirl flow from the swirl generator into the mixing tube.
  • transition channels are arranged sectorally according to the number the inflow channels acting in the swirl generator.
  • the design of the burner outlet at the end of the mixing tube with a tear-off edge has a significant improvement in terms of Strengthening flame stability, lower pollutant emissions, lower Pulsations, complete burnout, large operating range, good cross-ignition between the different burners, compact design, improved Mixture, etc., triggered.
  • further strengthening the flame stability and an improved adaptation of the flame to the specified one Combustion chamber geometry for smooth operation at the highest Level is required in the premix combustion of the newer generation.
  • 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 precautions which strengthen the flame stability and an adaptation of the flame to the given combustion chamber geometry effect without the other benefits of this burner in any way reduce.
  • a radius is attached to the end of the mixing tube
  • the size is chosen so that the flow contacts the wall of the mixing tube and so the swirl number increases. Opposite a flow without a radius Now the backflow zone increases enormously.
  • Fig. 1 shows the overall structure of a burner operated as a premix burner becomes.
  • a swirl generator 100 is effective, the design of which is shown in FIGS the following Fig. 3-6 is shown and described in more detail. It is about in this swirl generator 100 around a conical structure, the tangential multiple is acted upon by an inflowing combustion air flow 115.
  • the flow formed here is based on a downstream of the swirl generator 100 provided transition geometry seamlessly into a transition piece 200 transferred in such a way that no detachment areas can occur there.
  • the Configuration of this transition geometry is described in more detail in FIG. 6.
  • This transition piece 200 is on the outflow side of the transition geometry extended by a mixing tube 20, both parts of the actual mixing section Form 220.
  • the mixing section 220 can be made from a single one Consist of pieces, i.e. then that the transition piece 200 and the mixing tube 20 merge into a single coherent structure, but the Characteristics of each part are retained.
  • a 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 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 is the actual combustion chamber 30 one 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 mixed route so primarily the mixing tube 20, also allows lossless Flow guidance, so that it is also in operative connection with the transition geometry initially cannot form a backflow zone or backflow bubble, with which over the length of the mixing section 220 to the mixing quality for all types of fuel Influence can be exercised.
  • this mixing section 220 still has one another property, which is that in itself the axial velocity profile has a pronounced maximum on the axis, so that backfire the flame from the combustion chamber is not possible. However, it is correct that with such a configuration this axial velocity towards the wall drops.
  • the mixing tube 20 in the flow and circumferential direction with a number of regular or irregular distributed holes 21 of various cross sections and directions provided, through which an amount of air flows into the interior of the mixing tube 20, and along the wall in the sense of a filming an increase in the flow rate induce.
  • These holes 21 can also be designed that at least additionally on the inner wall of the mixing tube 20 sets an effusion cooling.
  • these bores 21 are also possible. It is also possible for the mixing tube 20 to be intermittent to provide such holes, for example at the beginning and end of the same. These bores 21 are preferably distributed around the circumference of the mixing tube. Furthermore, the outlet of the transition channels 201 corresponds to the narrowest Flow cross-section of the mixing tube 20. The above-mentioned transition channels 201 bridging the respective cross-sectional difference without the to influence the flow formed. If the precaution chosen at the guidance of the pipe flow 40 along the mixing pipe 20 an intolerable If pressure loss triggers, this can be remedied by At the end of this mixing tube 20, a diffuser, not shown in the figure, is provided becomes.
  • a combustion chamber then closes at the end of the mixing tube 20 30 (combustion chamber), with a through between the two flow cross-sections there is a cross-sectional jump formed in the burner front. Only here does it form a central flame front with a backflow zone 50, which is opposite the Flame front has the properties of a disembodied flame holder. forms there is a flow within this cross-sectional jump during operation Edge zone, in which by the prevailing negative pressure Vortex detachments arise, this leads to an increased ring stabilization of the Backflow zone 50. It should also be mentioned that the generation of a stable backflow zone 50 also a sufficiently high swirl number in one Tube required.
  • FIG. 2 shows a schematic view of the burner according to FIG. 1, in particular here to the washing around a centrally arranged fuel nozzle 103 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 are described in more detail in the following figures.
  • the fuel nozzle 103 is encased with a spaced ring 190, in which has a number of holes 161 arranged in the circumferential direction, through which an amount of air 160 flows into an annular chamber 180 and there rinsing the fuel nozzle 103. These holes 161 are slanted forward so that an adequate axial component arises on the burner axis 60.
  • additional fuel injectors 170 are provided, which have a specific one Amount of preferably a gaseous fuel in the respective amount of air Feed 160 such that there is a uniform fuel concentration in the mixing tube 20 150 sets over the flow cross-section, as the illustration wants to symbolize in the figure.
  • Exactly this uniform fuel concentration 150, especially the strong concentration on the burner axis 60 provides that there is a stabilization of the flame front at the exit of the burner sets, thus avoiding occurring combustion chamber pulsations.
  • FIG. 4 is used at the same time as FIG. 3.
  • 3 is referred to the other figures as required in the description of FIG. 3,
  • the first part of the burner according to FIG. 1 forms the swirl generator shown in FIG. 3 100.
  • 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 Figures 5 and 6 demonstrate; this depends on how they are explained in more detail below depends on the operating mode of the entire burner. It is with certain operating constellations not excluded, a single spiral Provide swirl generator.
  • the displacement of the respective central axis or Longitudinal symmetry axes 101b, 102b (see FIG. 4) of the tapered partial bodies 101, 102 creates each other in the neighboring wall, in a mirror-image arrangement, one tangential inflow channel each, i.e.
  • the cone shape of the Part body 101, 102 shown in the flow direction has a certain fixed Angle on.
  • the partial bodies 101, 102 have an increasing or decreasing cone inclination in the direction of flow, similar to a trumpet or Tulip. The latter two forms are not recorded in the drawing, since they can be easily understood by the expert are.
  • the two conical partial bodies 101, 102 each have a cylindrical one annular starting part 101a. In the area of this cylindrical initial part the fuel nozzle 103 already mentioned under FIG. 2 is accommodated, which is preferably operated with a liquid fuel 112.
  • the injection 104 of this fuel 112 falls approximately with the narrowest cross section of the formed by the conical part body 101, 102 cone cavity 114 together.
  • the injection capacity and the type of this fuel nozzle 103 are determined according to the given parameters of the respective burner.
  • the tapered body 101, 102 also each have a fuel line 108, 109, which arranged along the tangential air inlet slots 119, 120 and with injection openings 117 are provided, through which preferably a gaseous Fuel 113 is injected into the combustion air 115 flowing through there, as arrows 116 symbolize this.
  • These fuel lines 108, 109 are preferably at the latest at the end of the tangential inflow, before entering the cone cavity 114, arranged for an optimal air / fuel mixture to obtain.
  • fuel 112 is normally a liquid Fuel, forming a mixture with another medium, for example with a recirculated flue gas, is easily possible. That fuel 112 is inserted into the cone cavity 114 at a preferably very acute angle injected. A conical fuel spray thus forms from the fuel nozzle 103 105, from the rotating combustion air flowing in tangentially 115 enclosed and dismantled. The concentration is then in the axial direction of the injected fuel 112 continuously through the inflowing combustion air 115 degraded to mix in the direction of evaporation.
  • a gaseous fuel 113 is introduced via the opening nozzles 117 the formation of the fuel / air mixture directly at the end of the air inlet slots 119, 120.
  • the combustion air 115 additionally preheated, or for example enriched with a recirculated flue gas or exhaust gas, so supported this sustained the vaporization of the liquid fuel 112 before this mixture flows into the downstream stage, here into the transition piece 200 (See Figures 1 and 7).
  • the same considerations also apply when talking about the Lines 108, 109 liquid fuels should be supplied.
  • the tangential air inlet slots 119, 120 are strict limits to be observed, so that the desired flow field of the combustion air 115 at the exit of the swirl generator 100 can adjust. Generally it can be said that a Reduction of the tangential air inlet slots 119, 120 the faster formation a backflow zone already favored in the area of the swirl generator.
  • the axial speed within the swirl generator 100 can be by a corresponding increase supply of air as described in Fig. 2 (item 160) or stabilize.
  • a corresponding swirl generation in operative connection with the downstream transition piece 200 prevents formation of flow separation within the swirl generator 100 downstream Mixing tube.
  • the construction of the swirl generator 100 is suitable further excellent, the size of the tangential air inlet slots 119, 120 to change, with which without changing the overall length of the swirl generator 100 relatively large operational bandwidth can be captured.
  • the partial bodies 101, 102 can also be displaced relative to one another in another plane, as a result of which even an overlap of the same can be provided. It is the further possible, the partial body 101, 102 by a counter-rotating movement to nest in a spiral.
  • FIG. 4 shows, among other things, the geometric configuration of optional ones Baffles 121a, 121b. They have a flow initiation function these, according to their length, the respective end of the tapered partial body 101, 102 extend in the direction of flow towards the combustion air 115.
  • the channeling of the combustion air 115 into the cone cavity 114 can by opening or closing the guide plates 121a, 121b by one in the area the point of entry of this channel into the cone cavity 114 123 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 arrangements can also be provided statically, by using required baffles form an integral part with the tapered 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.
  • this configuration is to be said that they are due to the lower generated with it Twist strength and in cooperation with a correspondingly enlarged slot width ideally suited, the bursting of the vortex flow on the downstream side of the To prevent swirl generator in the mixing tube, with which the mixing tube the intended Role.
  • FIG. 6 differs from FIG. 5 in that the partial bodies 140 here 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 points as Natural extension of the upstream part of the four transition channels 201, whereby the conical quarter area of the partial bodies is extended, until it cuts the wall of the mixing tube.
  • the same considerations apply even if the swirl generator is based on a principle other than that described under FIG. 3, is constructed.
  • the downward flow area of the individual transition channels 201 has a spiral shape in the flow direction running shape, which describes a crescent shape, accordingly the fact that in the present case the flow cross-section of the transition piece 200 flared in the direction of flow.
  • the twist angle of the Transition channels 201 in the flow direction are selected so that the pipe flow then another one up to the cross-sectional jump at the combustion chamber inlet enough distance remains to allow a perfect premix with the injected To accomplish fuel. It also increases by the above Measures also include the axial speed on the mixing tube wall downstream of the swirl generator. The transition geometry and the measures in the area of the mixing tube cause a significant increase in the axial speed profile towards the center of the mixing tube, so there is a risk of early ignition is decisively counteracted.
  • FIG. 8 shows the geometric design of the burner outlet at the end of the mixing tube 20 already mentioned for spatial stabilization of the backflow zone.
  • the flow cross-section of the tube 20 receives in this area a first transition radius R 1 which is convex with respect to the burner axis 60, the size of which basically depends on the respective flow within the mixing tube 20.
  • the size of this radius R 1 is accordingly chosen so that the flow is applied to the wall and the swirl number can increase sharply.
  • the size of the radius R 1 can be defined quantitatively such that it is> 10% of the inner diameter d of the mixing tube 20. Compared to a flow without a radius, the backflow zone 50 now increases enormously.
  • This radius R 1 then merges into a second radius R 2 , which is concave with respect to the burner axis 60 up to the exit plane 70 of the mixing tube 20, the size of this radius R 2 being > 10% of the inside diameter d of the mixing tube 20.
  • This second radius R 2 ensures that the edge flow is aligned axially in such a way that the flame does not appear on the combustion chamber wall when the combustion chamber is of small radial dimension.
  • the sectorial angles ⁇ 1 and ⁇ 2 of the two radii R 1 , R 2 are complementary angles, the maximum sum of which is 90 °. Depending on the number of swirls and the axial orientation of the flow, the two angles mentioned are adapted accordingly, which is interdependent on the size of the two radii.
  • the exit plane 70 of the mixing tube 20 is further provided with a step S of> 3 mm depth in the radial direction from the end edge of the second radius R 2 , this step performing the function of a stall stage.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Sorption Type Refrigeration Machines (AREA)
  • Combustion Of Fluid Fuel (AREA)

Claims (15)

  1. Brûleur pour faire fonctionner un générateur de chaleur, le brûleur étant constitué essentiellement d'un générateur (100) de tourbillons pour un courant d'air de combustion, de moyens (117) d'injection d'au moins un combustible dans le courant d'air de combustion, une zone (220) de mélange étant disposée en aval du générateur de tourbillons et comportant dans une première partie dans la direction du courant un certain nombre de canaux (201) de raccordement pour faire passer un courant formé dans ce générateur de tourbillons dans un tube (20) de mélange en aval de ces canaux de raccordement, l'extrémité du tube (20) de mélange ayant dans sa zone de sortie menant à une chambre (30) de combustion en aval un premier rayon (R1) s'étendant de manière convexe par rapport à l'axe (60) du brûleur, ce rayon (R1) se transformant en un deuxième rayon (R2) allant jusqu'au plan (70) de sortie du tube (20) de mélange et s'étendant de manière concave par rapport à l'axe (60) du brûleur et le secteur (β1 + β2) recouvert par les deux rayons (R1 R2) est ≤ 90°.
  2. Brûleur suivant la revendication 1, caractérisé en ce que les deux rayons (R1 R2) sont respectivement > 10 % du diamètre (d) intérieur du tube (20) de mélange.
  3. Brûleur suivant la revendication 1, caractérisé en ce que le plan (70) de sortie est muni à partir du bord d'extrémité du deuxième rayon (R2) en direction radiale d'une partie (S) en retrait.
  4. Brûleur suivant la revendication 3, caractérisé en ce que la partie (S) en retrait a une profondeur > 3 mm.
  5. Brûleur suivant la revendication 1, caractérisé en ce que le générateur (100) de tourbillons est constitué d'au moins deux sous-pièces (101, 102, 130, 131, 132, 133, 140, 141, 142, 143) creuses, coniques et emboítées l'une dans l'autre dans la direction du courant, en ce que les axes (101b, 102b; 130a, 131a, 132a, 133a; 140a, 141a, 142a, 143a) respectifs de symétrie longitudinale de ces sous-pièces s'étendent en étant décalés l'un par rapport à l'autre, de façon à ce que les parois voisines des sous-pièces forment dans leur étendue longitudinale des canaux (119, 120) tangentiels pour un courant (115) d'air de combustion et en ce qu'il est prévu au moins une buse (103) pour du combustible dans la chambre (114) intérieure formée par les sous-pièces.
  6. Brûleur suivant la revendication 5, caractérisé en ce que d'autres buses (117) pour du combustible sont disposées dans la région des canaux (119, 120) tangentiels dans leur étendue longitudinale.
  7. Brûleur suivant la revendication 5, caractérisé en ce que les sous-pièces (140, 141, 142, 143) ont en coupe transversale un profilage en forme d'aube.
  8. Brûleur suivant la revendication 5, caractérisé en ce que les sous-pièces ont dans la direction du courant un angle de cône qui est fixe ou une inclinaison de cône qui est croissante ou une inclinaison de cône qui est décroissante.
  9. Brûleur suivant la revendication 5, caractérisé en ce que les pièces partielles s'emboitent l'une dans l'autre en forme de spirale.
  10. Brûleur suivant les revendications 1 et 5, caractérisé en ce que le nombre de canaux de raccordement (201) dans la zone (220) de mélange correspond au nombre de sous-courants formés par le générateur (100) de tourbillons.
  11. Brûleur suivant la revendication 1, caractérisé en ce que le tube (20) de mélange est muni à l'intérieur dans la direction du courant et dans la direction périphérique de trous (21) d'injection d'un courant d'air à l'intérieur.
  12. Brûleur suivant la revendication 11, caractérisé en ce que les trous (21) font un angle aigu avec l'axe du tube (20) de mélange.
  13. Brûleur suivant la revendication 1, caractérisé en ce que la section transversale de passage du tube (20) de mélange est en aval des canaux (201) de raccordement plus petite, égale ou plus grande que la section transversale du courant (40) formé dans le générateur (100) de tourbillons.
  14. Brûleur suivant la revendication 1, caractérisé en ce qu'il est prévu entre la zone (220) de mélange et la chambre (30) de combustion un saut de section transversale, qui induit la section transversale initiale du courant de la chambre de combustion et en ce qu'une zone (50) de reflux peut agir dans la région de ce saut de section transversale.
  15. Brûleur suivant la revendication 1, caractérisé en ce qu'il est prévu en amont du premier rayon (R1) un diffuseur et/ou une zone de venturi.
EP97810907A 1997-11-25 1997-11-25 Brûleur pour la mise en oeuvre d'un générateur de chaleur Expired - Lifetime EP0919768B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
AT97810907T ATE232282T1 (de) 1997-11-25 1997-11-25 Brenner zum betrieb eines wärmeerzeugers
EP97810907A EP0919768B1 (fr) 1997-11-25 1997-11-25 Brûleur pour la mise en oeuvre d'un générateur de chaleur
DE59709281T DE59709281D1 (de) 1997-11-25 1997-11-25 Brenner zum Betrieb eines Wärmeerzeugers
US09/196,115 US5954490A (en) 1997-11-25 1998-11-20 Burner for operating a heat generator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810907A EP0919768B1 (fr) 1997-11-25 1997-11-25 Brûleur pour la mise en oeuvre d'un générateur de chaleur

Publications (2)

Publication Number Publication Date
EP0919768A1 EP0919768A1 (fr) 1999-06-02
EP0919768B1 true EP0919768B1 (fr) 2003-02-05

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US (1) US5954490A (fr)
EP (1) EP0919768B1 (fr)
AT (1) ATE232282T1 (fr)
DE (1) DE59709281D1 (fr)

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DE19859829A1 (de) * 1998-12-23 2000-06-29 Abb Alstom Power Ch Ag Brenner zum Betrieb eines Wärmeerzeugers
EP1070914B1 (fr) * 1999-07-22 2003-12-03 ALSTOM (Switzerland) Ltd Brûleur à prémélange
DE10026122A1 (de) * 2000-05-26 2001-11-29 Abb Alstom Power Nv Brenner für einen Wärmeerzeuger
DE10056243A1 (de) * 2000-11-14 2002-05-23 Alstom Switzerland Ltd Brennkammer und Verfahren zum Betrieb dieser Brennkammer
DE10064259B4 (de) * 2000-12-22 2012-02-02 Alstom Technology Ltd. Brenner mit hoher Flammenstabilität
EP1262714A1 (fr) * 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
US6889523B2 (en) * 2003-03-07 2005-05-10 Elkcorp LNG production in cryogenic natural gas processing plants
WO2006058843A1 (fr) * 2004-11-30 2006-06-08 Alstom Technology Ltd Procede et dispositif de combustion d'hydrogene dans un bruleur a premelange
EP1843098A1 (fr) * 2006-04-07 2007-10-10 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
CH701905A1 (de) * 2009-09-17 2011-03-31 Alstom Technology Ltd Verfahren zum Verbrennen wasserstoffreicher, gasförmiger Brennstoffe in einem Brenner sowie Brenner zur Durchführung des Verfahrens.

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US2762428A (en) * 1953-02-05 1956-09-11 Selas Corp Of America Gas-fueled radiant burner
US3083759A (en) * 1957-08-13 1963-04-02 Selas Corp Of America Radiant cup gas burner
US4416620A (en) * 1981-06-08 1983-11-22 Selas Corporation Of America Larger capacity Vortex burner
CH674561A5 (fr) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
NL8902963A (nl) * 1989-12-01 1991-07-01 Int Flame Research Foundation Werkwijze voor het verbranden van brandstof met een laag nox-gehalte in de verbrandingsgassen door middel van getrapte brandstoftoevoer en brander te gebruiken daarbij.
US5454712A (en) * 1993-09-15 1995-10-03 The Boc Group, Inc. Air-oxy-fuel burner method and apparatus
DE19547913A1 (de) 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger

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EP0919768A1 (fr) 1999-06-02
DE59709281D1 (de) 2003-03-13
US5954490A (en) 1999-09-21
ATE232282T1 (de) 2003-02-15

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