EP0987493B1 - Brûleur pour générateur de chaleur - Google Patents

Brûleur pour générateur de chaleur Download PDF

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Publication number
EP0987493B1
EP0987493B1 EP98810922A EP98810922A EP0987493B1 EP 0987493 B1 EP0987493 B1 EP 0987493B1 EP 98810922 A EP98810922 A EP 98810922A EP 98810922 A EP98810922 A EP 98810922A EP 0987493 B1 EP0987493 B1 EP 0987493B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
combustion
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.)
Expired - Lifetime
Application number
EP98810922A
Other languages
German (de)
English (en)
Other versions
EP0987493A1 (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 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 has to be stopped, inspected and repaired, which leads to immense costs. It has been shown that there is a high risk in this regard, in particular in the case of prototype gas turbines with new combustion technology or the combustion of fuels containing hydrogen (MBtu or LBtu gases).
  • MBtu or LBtu gases fuels containing hydrogen
  • EP-A-0 816 760 describes a burner for operating a gas turbine with several in the premixing section downstream of the fuel injection Glass fiber are arranged, which via optical sensors with the Control system of the gas turbine are connected.
  • 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.
  • 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.
  • 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.
  • the fuel supply is to keep the turbine output constant.
  • 3 shows the qualitative sequence of the fuel control over time, the flushing out at the extreme points of this control 84 of the retarded flame takes place.
  • 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 socket 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 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 established.
  • 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 already mentioned transition geometry form, 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 accordingly 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 amount of air 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 Annular chamber 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 therefore forms Bore 306 a pilot burner acting in the combustion chamber 30, which one guaranteed stable operation.
  • An ignition device becomes through the air-circulating ring chamber 302 311 passed through, which in the downstream annular chamber 308 Ignition of the mixture formed there. For one thing, it takes for this passage of the ignition device 311 no further constructive Measures, and on the other hand, this ignition device 311 is constantly by the air 304 flowing there is cooled anyway. This is very important because when using it temperature 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, 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 also eliminated avoided.
  • additional fuel injectors 170 which contains a certain amount of preferably a gaseous fuel enter the respective amount of air 160 in such a way that a sets uniform fuel concentration 150 over the flow cross-section, as the representation in the figure symbolizes.
  • Fuel concentration 150 especially the strong concentration the burner axis 60 ensures that the flame front is stabilized at the burner outlet, especially when using a central one Injection with liquid fuel, resulting in combustion chamber pulsations be avoided.
  • 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 will be 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 conical sub-bodies 101, 102 each have a fuel line 108, 109, 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.
  • 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 Flue gas or exhaust gas enriched, this supports the evaporation sustainably 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 when liquid lines 108, 109 Fuels should be supplied.
  • 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, 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. 4 is constructed.
  • the down in the flow direction running surface of the individual transition channels 201 has a flow direction spiral shape, which has a crescent shape Course describes, corresponding to the fact that the flow cross-section is present of the transition piece 200 flared in the flow direction.
  • 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 entry still has a sufficient distance to be perfect Premix with the injected fuel. Furthermore increased the axial speed due to 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 cause a significant increase the axial velocity profile towards the center of the mixing tube, see above that the danger of early ignition is decisively counteracted.
  • the tear-off edge A runs inside the tube 20 and thus forms a tear-off step S opposite the front point of the tear-off edge A, whose depth> 3 mm is.
  • this can be parallel to the exit plane of the tube 20 running edge based on a curved course back to the exit level to be brought.
  • the angle ⁇ ' which is between the tangent of the tear-off edge A and perpendicular to the exit plane of the tube 20 is the same as large as angle ⁇ .
  • Another Design of the tear-off edge for the same purpose can be done with the combustion chamber achieve toroidal notches. This publication is inclusive the scope of protection there regarding the tear-off edge is an integrating one Part of this description.

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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)
  • Spray-Type Burners (AREA)

Claims (15)

  1. Brûleur servant à faire fonctionner un générateur de chaleur, le brûleur consistant en amont de la chambre de combustion (30) en au moins une section de pré-mélange (220), laquelle section de pré-mélange présente des moyens (100) permettant de créer un flux tourbillonnant d'air de combustion et laquelle section de pré-mélange étant équipée d'au moins un injecteur de carburant (103, 117), étant disposé en aval de l'injecteur de carburant au moins un capteur (400) qui détecte un retour de la flamme de pré-mélange hors de la chambre de combustion vers l'intérieur du brûleur et déclenche un réglage du carburant.
  2. Brûleur selon la revendication 1, caractérisé en ce que le brûleur consiste substantiellement en un générateur de tourbillon pour un flux d'air de combustion, en moyens d'injection d'au moins un carburant dans le flux d'air de combustion afin de former une flamme de pré-mélange, étant disposée en aval du générateur de tourbillon une section de mélange qui présente, à l'intérieur d'une première partie de section dans le sens du flux, un certain nombre de canaux de transition servant à transférer un flux formé dans le générateur de tourbillon dans un tuyau mélangeur adjoint installé en aval de ces canaux de transition, que dans la zone inférieure du tuyau mélangeur (20) est disposé un système de brûleur pilote (300) agissant dans la chambre de combustion (30) adjointe au tuyau mélangeur (20).
  3. Brûleur selon la revendication 2, caractérisé en ce que le générateur de tourbillon (100) consiste en au moins deux corps partiels creux de forme conique emboítés l'un dans l'autre dans le sens du flux (101, 102 ; 130, 131, 132, 133 ; 140, 141, 142, 143), que les axes respectifs de symétrie longitudinale (101b, 102b ; 130a, 131a, 132a, 133a ; 140a, 141a, 142a, 143a) de ces corps partiels sont orientés décalés les uns par rapport aux autres, de manière à ce que les parois voisines des corps partiels forment dans leur extension longitudinale des canaux tangentiels (119, 120) pour un flux d'air de combustion (115), et qu'au moins une buse de carburant (103) est susceptible d'agir dans l'espace intérieur (114) constitué par les corps partiels.
  4. Brûleur selon la revendication 2, caractérisé en ce que le système de brûleur pilote (300) est refroidi et peut être actionné à l'aide d'au moins un dispositif d'allumage (311).
  5. Brûleur selon la revendication 2, caractérisé en ce que le système de brûleur pilote (300) consiste en au moins deux chambres de guidage de produit (301, 302) et en une autre chambre commune adjointe (308), que, dans cette chambre adjointe (308), les produits (303, 304) provenant des deux autres chambres (301, 302) peuvent être mélangés, et que la chambre adjointe (308) présente des moyens servant à la constitution de brûleurs pilotes (306) agissant dans la chambre de combustion (30) pouvant fonctionner avec le mélange des deux produits (303, 304).
  6. Brûleur selon les revendications 2 et 5, caractérisé en ce qu'ils sont constitués en forme annulaire par les chambres de guidage du produit (301, 303) et coordonnés, qu'à travers la première chambre annulaire (301) un carburant gazeux (303) et à travers la deuxième chambre annulaire (302) une quantité d'air (304) affluent, que dans la deuxième chambre annulaire (302) sont intégrés des moyens (305) grâce auxquels l'air s'y écoulant (304) assure un refroidissement par rebond sur une tôle de protection contre la chaleur (307) disposée du côté de l'extrémité du système de brûleur pilote (300), et que le dispositif d'allumage (311) est dirigé à travers la deuxième chambre annulaire (302).
  7. Brûleur selon la revendication 6, caractérisé en ce que le moyen servant à assurer le refroidissement par rebond est une plaque perforée (305) formant le fond dans la chambre annulaire coordonnée (302).
  8. Brûleur selon la revendication 2, caractérisé en ce que le front à brûleur du tuyau mélangeur (20) vers la chambre de combustion adjointe (30) est conformé avec un bord sectionné (A).
  9. Brûleur selon la revendication 2, caractérisé en ce que le nombre de canaux de transition (201) dans la section de mélange (220) équivaut au nombre de flux partiels formés par le générateur de tourbillon (100).
  10. Brûleur selon la revendication 2, caractérisé en ce que le tuyau mélangeur (20) adjoint aux canaux de transition (201) est muni dans le sens du flux et périphérique d'orifices (21) servant à injecter un flux d'air à l'intérieur du tuyau mélangeur (20).
  11. Brûleur selon la revendication 2, caractérisé en ce qu'en aval de la section de mélange (220) est disposée une chambre de combustion (30), qu'entre la section de mélange (220) et la chambre de combustion (30) se trouve un saut de section transversale qui induit la section transversale du flux de départ de la chambre de combustion (30) et qu'une flamme de pré-mélange se constitue avec une zone de reflux (50) dans la zone de ce saut de section transversale.
  12. Brûleur selon la revendication 1, caractérisé en ce que la section de pré-mélange consiste en amont de la chambre de combustion (30) en un générateur de tourbillon (100), lequel générateur de tourbillon consiste en au moins deux corps partiels creux de forme conique emboítés l'un dans l'autre dans le sens du flux (101, 102 ; 130, 131, 132, 133 ; 140, 141, 142, 143), que les axes respectifs de symétrie longitudinale (101b, 102b ; 130a, 131a, 132a, 133a ; 140a, 141a, 142a, 143a) de ces corps partiels sont orientés décalés les uns par rapport aux autres de manière à ce que les parois voisines des corps partiels forment dans leur extension longitudinale des canaux tangentiels (119, 120) pour un flux d'air de combustion (115), et qu'au moins une buse de carburant (103) est susceptible d'agir dans l'espace intérieur formé par les corps partiels (114).
  13. Brûleur selon les revendications 2 ou 12, caractérisé en ce que, dans la zone des canaux tangentiels (119, 120) sont disposés, dans l'extension longitudinale de ceux-ci, d'autres injecteurs de carburant (117).
  14. Brûleur selon la revendication 15, caractérisé en ce que les corps partiels (140, 141, 142, 143) présentent en section transversale un profilage en forme de pelle.
  15. Procédé de fonctionnement d'un brûleur selon les revendications 1 et 2 ou 1 et 12, caractérisé en ce qu'un retour de la flamme est détecté par le capteur installé dans le brûleur (400), qu'ensuite la quantité de carburant de cette flamme est réduite du moins temporairement et qu'en même temps la quantité de carburant pilote est augmentée de manière à maintenir à un niveau constant la quantité totale de carburant et donc le rendement de la turbine.
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 EP0987493A1 (fr) 2000-03-22
EP0987493B1 true EP0987493B1 (fr) 2003-08-06

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EP98810922A Expired - Lifetime EP0987493B1 (fr) 1998-09-16 1998-09-16 Brûleur pour générateur de chaleur

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

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6357216B1 (en) * 2000-09-27 2002-03-19 Honeywell International, Inc. Flashback control for a gas turbine engine combustor having an air bypass system
CN1556876B (zh) * 2001-08-31 2012-01-18 Nano-C公司 富勒烯的燃烧合成方法
EP1389713A1 (fr) * 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Brûleur pilote annulaire pour sortie de brûleur à prémélange
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EP0987493A1 (fr) 2000-03-22
US6210152B1 (en) 2001-04-03
JP2000097407A (ja) 2000-04-04
CA2282153A1 (fr) 2000-03-16
DE59809222D1 (de) 2003-09-11
JP4344049B2 (ja) 2009-10-14

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