EP0638769B1 - Injecteur de combustible pour des combustibles liquides et gazeux et procédé de sa mise en oeuvre - Google Patents

Injecteur de combustible pour des combustibles liquides et gazeux et procédé de sa mise en oeuvre Download PDF

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Publication number
EP0638769B1
EP0638769B1 EP94110938A EP94110938A EP0638769B1 EP 0638769 B1 EP0638769 B1 EP 0638769B1 EP 94110938 A EP94110938 A EP 94110938A EP 94110938 A EP94110938 A EP 94110938A EP 0638769 B1 EP0638769 B1 EP 0638769B1
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EP
European Patent Office
Prior art keywords
fuel
air
nozzle
lance
gas
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
EP94110938A
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German (de)
English (en)
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EP0638769A3 (fr
EP0638769A2 (fr
Inventor
Adnan Dr. Eroglu
Franz Joos
Peter Novacek
Peter Dr. Senior
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 AG Germany
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0638769A2 publication Critical patent/EP0638769A2/fr
Publication of EP0638769A3 publication Critical patent/EP0638769A3/fr
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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
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
    • 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
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • 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
    • F23D14/78—Cooling burner parts
    • 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

Definitions

  • the present invention relates to the field of Combustion technology. It concerns a fuel lance for liquid and / or gaseous fuels for use in a Combustion chamber, as used for example in gas turbines finds.
  • a fuel lance of the type mentioned is known from GB-A-2021 254.
  • the air jet surrounds the fuel jets. While the fuel is through If separate pipe systems are inserted into the lance from the outside, the air Removed combustion chamber. As a result, there is no possibility of the lance outside as well as to cool the internal fuel channels and those from the nozzles protect escaping fuel from early ignition.
  • the task is for a fuel lance for liquid and / or gaseous Fuels for use in the combustion chamber of a premix burner characterizing features of claim 1 solved.
  • the essence of the invention is that for cooling the lance and for distributing the fuel through the air duct air with a temperature up to several 100 ° C, but preferably less than 600 ° C, to the air / fuel nozzle led and there as a sheath flow surrounding the fuel flow in the Combustion chamber is blown. This also ensures safe cooling of the lance at higher temperatures of the combustion air flowing past the lance or combustion gases reached.
  • a first preferred embodiment of the invention Fuel lance is characterized in that the least an air / fuel nozzle and the at least one gas nozzle circular and one behind the other common nozzle axis are arranged, and the diameter the gas nozzle is smaller than the diameter of the Air / fuel nozzle.
  • the gas flow emerging from the gas nozzle will pass through the Air / fuel nozzle surrounded by a jacket-shaped air flow. This ensures on the one hand that for the gaseous fuel gives practically the same injection route as for the liquid fuel. On the other hand supports the air flow largely independent of the amount of gas the gas injection, so that even with small gas flows the aerodynamic conditions in the combustion chamber hardly change.
  • a further preferred embodiment of the invention is thereby characterized that the gas pipe and the liquid fuel pipe in the flow direction before the at least one Air / fuel nozzle ends that the gas nozzle and liquid fuel nozzle arranged at the end of each tube and are oriented parallel to the lance axis, and that for each Air / fuel nozzle and the other nozzles a scoop-shaped Baffle is provided, which from the other Gas or liquid flows emerging through nozzles by approximately 90 ° deflects and introduces into the respective air / fuel nozzle.
  • This will help distribute and mix the liquid fuel an air powered atomizer realized in Anglo-Saxon literature as a "prefilming atomizer" is known (see also A. H. Lefebvre, Airblast Atomization, Prog.Energy Combust. Sci., Vol. 6, pp. 233-261 (1980)).
  • Fuel lance is the air duct around the downstream led around the end of the fuel lance, and in this end at least one, largely parallel to the lance axis oriented auxiliary nozzle provided through which air can flow out of the air duct into the combustion chamber.
  • auxiliary nozzle will fuel-free air in the room behind the The tip of the lance was injected to the critical point Formation of fuel-containing after-runs and / or recirculation zones to prevent.
  • Fig. 1 is a possible arrangement of a side view exemplary fuel lance according to the invention in one by a housing 3 limited combustion chamber 2 of a gas turbine or the like. (Only a partial section is shown the chamber).
  • the fuel lance 1 is in this Example with their lance axis 5 in the central axis of the Combustion chamber 2 is arranged and (as by the three long Arrows is indicated in Fig. 1) of hot combustion air flows around.
  • the fuel lance 1 is therefore the aerodynamic Conditions in the combustion chamber 2 adapted and streamlined designed. It is of an elongated lance coat 11 surrounded and on a laterally outgoing arm 4 on Housing 3 attached.
  • the support arm 4 is also streamlined designed and can in the cross section shown Have wing-like support arm profile 14.
  • the tubes include one in the axial direction internal liquid fuel pipe 7 and a the liquid fuel tube 7 concentrically in one Distance surrounding gas pipe 9.
  • the gas pipe 9 is in turn surrounded at a distance by the lance jacket 11. Due to the concentric and spaced arrangement of pipes and jacket three channels are formed, the inner liquid fuel channel 6, the gas duct 8 and the air duct 10. Die Channels take over depending on the operating mode of the fuel lance 1 different functions, based on three preferred exemplary embodiments illustrated in FIGS. 2 to 4 are to be explained in more detail.
  • Fig. 2 shows for the first embodiment in longitudinal section the lance tip used to explain various Operating cases along the lance axis 5 in two separate Halves has been divided.
  • the top half refers with the drawn currents (marked by arrows) to the operating case with exclusively gaseous fuel, the lower half to the operating case with exclusively liquid fuel.
  • a corresponding two-part Representation is the same for the other reasons Figures 3 and 4 have been chosen.
  • the inner liquid fuel tube ends in the tip of the lance 7, the gas pipe 9 and the lance jacket 11.
  • the gas pipe 9 ends up in a hemispherical pipe head 17 above, which closes the pipe.
  • the Liquid fuel pipe 7 is blunt on the inner surface of the Pipe head 17 welded (or soldered) and in this way completed at the end.
  • the lance jacket 11 encloses the pipe head 17 at a distance in the form of a hemispherical shell, so that the formed between lance jacket 11 and gas pipe 9 Air duct 10 extends into the immediate tip of the lance and encloses the pipe head 17 on the outside.
  • Each nozzle set includes one in Liquid fuel pipe 7 embedded liquid fuel nozzle 18, a gas nozzle 15 embedded in the gas pipe and one in the lance jacket 11 recessed air / fuel nozzle 12.
  • Each of the Nozzles 12, 15 and 18 are preferably circular. Your diameter are graduated with the inner liquid fuel nozzle 18 the smallest and the outer air / fuel nozzle largest diameter.
  • Number and diameter of the Liquid fuel nozzles 18 are based on that in the normal case flow rate of the liquid fuel occurring. It is make sure that the nozzle diameter is not too large the nozzles become small when solid deposits are formed do not clog. Otherwise, the number of jets of fuel injected into the combustion chamber through the nozzles not be too big, so that the aerodynamics are not around the fuel lance 1 is disturbed so far that increasingly form fuel-containing wakes behind the lance.
  • the inner liquid fuel channel 6 not used at all.
  • the flammable Gas flows through the gas channel 8 and the gas nozzle 15 and forms there a radially outward gas jet, the enters the combustion chamber 2 through the air / fuel nozzle 12.
  • cooling air with a Temperature up to several 100 ° C, but preferably less than 600 ° C, which is also sent out of the air / fuel nozzle radially emerges into the combustion chamber and the gas jet initially surrounds it as a jacket-shaped stream.
  • the cooling air has several functions: First, it cools the lance jacket 11 and forms a thermal protective jacket for the fuel channels further inside.
  • a liquid fuel usually an oil-water emulsion
  • the liquid fuel nozzle 18 out and there radially as a liquid jet ejected outside.
  • the gas channel 8 Introduced air that exits through the gas nozzle 15 and in Interaction with that also through the gas nozzle 15 penetrating liquid jet a fine atomization of the Liquid fuel in small droplets ("plain-jet airblast atomization").
  • the atomizing jet is then at the air / fuel nozzle 12 in the same way as described above, surrounded by a cooling air jacket (the also contributes to atomization) and finally into the combustion chamber 2 injected.
  • the auxiliary air in the gas duct 8 provided a further thermal shielding stage. This allows the liquid fuel in the liquid fuel channel 6 be kept at temperatures at which solid deposits be safely avoided.
  • the cooling or Auxiliary air in the lance functions: (i) It cools the lance and protects the inside Fuel channels from too high temperatures. (ii) It cools the fuel jets during injection and delays them thus heating them up, so that before self-ignition a there is sufficient mixing with the combustion air can. (iii) As auxiliary air, it drives the necessary Atomization of a liquid fuel. (iv) supports you when exiting through the air / fuel nozzles 12 as a jacket stream the mixing of the fuel jet in the combustion chamber. (v) It gets that even with low fuel flows jet system emerging from the nozzle sets upright.
  • the special arrangement of the nozzles 12, 15 and 18 achieves that, regardless of whether gaseous or liquid fuel is used, always gives the same aerodynamic configuration, i.e. that Fuel jets are injected into the combustion chamber 2 in the same way become. Because of the stable connection of the pipes 7, 9 with each other and with the lance jacket 11, the uniaxial remains Arrangement of the nozzle sets and thus the aerodynamic Receive configuration even if by different Temperature distributions thermal tensions in the lance available.
  • the air from the air duct 10 can advantageously still perform another function: in the flow direction behind
  • the tip of the lance can change for fluidic reasons basically form fuel-containing wakes that too Flashbacks or thermoacoustic vibrations (Pulsations). Such phenomena are intolerable, because they put a strain on the combustion chamber and, above all, too lead to increased pollutant emissions.
  • For their prevention is preferably a centrally in the Lance axis 5 arranged auxiliary nozzle 13 through which a fuel-free air flow from the air duct 10 in the part of the combustion chamber located behind the tip becomes. At the same time, this measure also ensures that the fuel lance 1 cooled to the foremost tip becomes.
  • FIG. 3 is another preferred embodiment reproduced for a fuel lance according to the invention.
  • 3A corresponds in its form of representation to FIG. 2;
  • Figure 3B is a partial cross section through the lance along line A-A of Fig. 3A, the area with the Liquid fuel nozzles 18 in FIG. 3A about the lance axis 5 is shown rotated.
  • the embodiment shown gives way of the Fig. 2 especially with regard to the arrangement of the Liquid fuel nozzles 18 from:
  • the nozzles 18 are not here longer with the other nozzles 12 and 15 together on a common one Nozzle axis 24 arranged, but from the lance tip moved backwards and at the same time around the Lance axis 5 rotated (Fig.
  • FIG. 3A In the upper part of FIG. 3A, as in FIG. 2, is the operating case represented with gaseous fuel in which the Liquid fuel pipe 7 is empty and is not used.
  • the injection jet is formed here completely analogously to Fig. 2.
  • the liquid fuel occurs as Jet from the liquid fuel nozzle 18 is by in Gas channel 8 led auxiliary air on the inner wall of the gas pipe 9 entrained along to the gas nozzle 15 and together there blown off with the auxiliary air through the guide tube 19, wherein atomization takes place simultaneously ("air assist atomizer").
  • Additional ring plates 20 on both sides of the liquid fuel nozzles 18 improve the flow conditions.
  • FIG. 4A again corresponds to FIG. 2 or FIG. 3A, while in FIG. 4B the special shape of the used baffles and their interaction with the nozzles will be shown.
  • 4 are the Air / fuel nozzles 12 arranged in the same place as in the exemplary embodiments from FIGS. 2 and 3.
  • the Gas pipe 9 and the liquid fuel pipe 7 end in the direction of flow even before the air / fuel nozzles 12.
  • everyone Air / fuel nozzle 12 associated gas nozzle 15 and liquid fuel nozzle 18 are at the end of each tube (9 and 7) and are oriented parallel to the lance axis 5.
  • a blade-shaped guide plate 22 is provided, which the gas exiting from the associated nozzles 15, 18 or liquid flows deflected by about 90 ° and into the respective Air / fuel nozzle 12 initiates.
  • the baffles 22 are cloverleaf around the lance axis 5 arranged around.
  • Each baffle 22 preferably runs in the area of Air / fuel nozzle 12 in a closed sheet metal ring 23 whose diameter is smaller than the diameter of the Air / fuel nozzle 12.
  • the redirected streams from the assigned Nozzles 15, 18 are so when leaving the Air / fuel nozzle 12, in turn, in the form of a jacket from an air stream surround.
  • an additional Guide tube 19 can be fitted to a safe deflection of the To ensure gas flows through the baffles 22.
  • the Baffles 22 are in the area of the nozzles (12, 15, 18) with the Lance jacket 11 firmly connected so that they are relative to Air / fuel nozzle 12 can not move.
  • the connection takes place via a tubular head 21 in the form of a hemispherical shell, the position of the pipe head 17 from FIG. 2 or FIG. 3 occupies and by means of the connecting webs already mentioned 16 is anchored to the lance jacket 11.
  • FIG. 5 Another preferred embodiment of a fuel lance according to the invention is shown in FIG. 5.
  • the gas nozzles 15 are independently in Flow direction placed in front of the other nozzles 12, 18.
  • in the Case of gas operation mixes the gas in front of the air / fuel nozzle 12 in the air duct 10 intensive with the cooling air.
  • the gas-air mixture occurs then through the air / fuel nozzle 12 into the combustion chamber out.
  • the liquid fuel flows from the liquid fuel nozzle accommodated in the tube head 17 18 past the air tube 20 directly into the air / fuel nozzle 12, where it is in the manner already described with the cooling air cooperates from the air duct 10.
  • the invention results in a fuel lance, which in the same aerodynamic configuration are gaseous and can inject liquid fuels, even at high combustion gas temperatures works safely, optimal atomization of liquid fuels allowed and by an extended Mixing process enables very low pollutant emissions.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Nozzles (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Claims (17)

  1. Injecteur de combustible pour des combustibles liquides et/ou gazeux à employer dans une chambre de combustion (2), comprenant
    (a) un tuyau de combustible liquide (7) disposé suivant un axe de l'injecteur (5), qui entoure un canal de combustible liquide (6) pour conduire un combustible liquide;
    (b) un tuyau de gaz (9) entourant le tuyau de combustible liquide (7), qui forme entre lui-même et le tuyau de combustible liquide (7) un canal de gaz pour conduire un combustible gazeux;
    (c) une enveloppe de l'injecteur (11) entourant le tuyau de gaz (9), qui forme entre elle-même et le tuyau de gaz (9) un canal d'air (10) pour conduire de l'air de refroidissement, respectivement de pulvérisation;
    (d) au moins un gicleur à air/combustible (12) dans l'enveloppe de l'injecteur (11), prévu latéralement dans l'extrémité aval de l'injecteur de combustible (1), par lequel l'air venant du canal d'air (10) peut sortir dans la chambre de combustion (2) entourant l'injecteur de combustible (1); dans lequel
    (e) au moins un gicleur à gaz (15) est disposé dans le tuyau de gaz (9), par lequel du gaz venant du canal de gaz (8) peut, par le canal d'air (10) et le au moins un gicleur à air/combustible (12), sortir avec l'air dans la chambre de combustion (2); et dans lequel
    (f) au moins un gicleur à combustible liquide (18) est disposé dans le tuyau de combustible liquide (7), par lequel du combustible liquide venant du canal de combustible liquide (6) peut, par le canal d'air (10) et le au moins un gicleur à air/combustible (12), sortir avec l'air dans la chambre de combustion (2),
    caractérisé en ce que
    (g) pour le refroidissement de l'injecteur et pour la répartition du combustible à travers le canal d'air (10), de l'air avec une température pouvant atteindre plusieurs centaines de degrés centigrades, de préférence toutefois inférieure à 600°C, est conduit au gicleur à air/combustible (12) et y est insufflé dans la chambre de combustion (2) sous la forme d'un courant gainant entourant le courant de combustible.
  2. Injecteur de combustible suivant la revendication 1, caractérisé en ce que le au moins un gicleur à air/combustible (12) et le au moins un gicleur à gaz (15) sont de forme circulaire et sont disposés l'un derrière l'autre sur un axe des gicleurs commun (24), et en ce que le diamètre du gicleur à gaz (15) est plus petit que le diamètre du gicleur à air/combustible (12).
  3. Injecteur de combustible suivant la revendication 2, caractérisé en ce qu'un tube de guidage (19) est inséré dans le gicleur à gaz (15), allant du gicleur à gaz (15) au gicleur à air/combustible (12) en traversant le canal d'air (10), d'une façon telle qu'un courant de gaz circulant à travers le tube de guidage (19) soit entouré par un courant d'air formant une gaine à la sortie du gicleur à air/combustible (12).
  4. Injecteur de combustible suivant l'une quelconque des revendications 2 et 3, caractérisé en ce que le gicleur à combustible liquide (18) est également disposé avec les deux autres gicleurs (12, 15) sur l'axe des gicleurs commun (24), et en ce que le diamètre du gicleur à combustible liquide (18) est plus petit que le diamètre du gicleur à gaz (15).
  5. Injecteur de combustible suivant la revendication 4, caractérisé en ce que le tuyau de combustible liquide (7) et le tuyau de gaz (9) sont solidement assemblés à l'enveloppe de l'injecteur (11) dans la région des gicleurs (12, 15, 18).
  6. Injecteur de combustible suivant l'une quelconque des revendications 2 et 3, caractérisé en ce que le gicleur à combustible liquide (18) est déplacé latéralement hors de l'axe des gicleurs (24) par rapport au gicleur à gaz (15), et en ce que le tuyau de gaz (9) est solidement assemblé à l'enveloppe de l'injecteur (11) dans la région des gicleurs (12, 15, 18).
  7. Injecteur de combustible suivant l'une quelconque des revendications 5 et 6, caractérisé en ce que le tuyau de gaz (9) se transforme, à l'extrémité aval de l'injecteur de combustible (1), en une tête de tuyau (17) fermée arrondie, qui est entourée par le canal d'air (10) et l'enveloppe de l'injecteur (11) et qui est fixée à l'enveloppe de l'injecteur (11) au moyen d'une pluralité de nervures de liaison (16) traversant le canal d'air (10).
  8. Injecteur de combustible suivant la revendication 1, caractérisé en ce que le tuyau de gaz (9) et le tuyau de combustible liquide (7) se terminent avant le au moins un gicleur à air/combustible (12), dans le sens de l'écoulement, en ce que le gicleur à gaz (15) et le gicleur à combustible liquide (18) sont disposés à l'extrémité du tuyau respectif (9, respectivement 7) et sont orientés parallèlement à l'axe de l'injecteur (5), et en ce que, pour chaque gicleur à air/combustible (12) et pour les autres gicleurs (15, 18), il est prévu un déflecteur en forme d'aube (22), qui dévie d'environ 90° les courants de gaz, respectivement de combustible liquide, sortant des autres gicleurs (15, 18) et les introduit dans le gicleur à air/combustible (12) respectif.
  9. Injecteur de combustible suivant la revendication 8, caractérisé en ce que le déflecteur se transforme, dans la région du gicleur à air/combustible (12), en un anneau de tôle fermé (23), dont le diamètre est plus petit que le diamètre du gicleur à air/combustible (12), d'une façon telle que les courants déviés venant des autres gicleurs (15, 18) soient entourés par un courant d'air formant une gaine à la sortie du gicleur à air/combustible (12).
  10. Injecteur de combustible suivant l'une quelconque des revendications 8 et 9, caractérisé en ce qu'un tube de guidage (19) est inséré en plus dans le gicleur à gaz (15), et en ce que le déflecteur (22) est solidement assemblé à l'enveloppe de l'injecteur (11) dans la région des gicleurs (12, 15, 18).
  11. Injecteur de combustible suivant l'une quelconque des revendications 1 à 10, caractérisé en ce qu'une pluralité de gicleurs, de préférence 4, sont disposés sur la périphérie de l'injecteur de combustible (1), avec une répartition dépendant de l'écoulement qui entoure l'injecteur de combustible (1).
  12. Injecteur de combustible suivant l'une quelconque des revendications 1 à 11, caractérisé en ce que le canal d'air (10) est mené autour de l'extrémité aval de l'injecteur de combustible (1), et en ce qu'il est prévu, dans cette extrémité, au moins un gicleur auxiliaire (13), orienté largement parallèlement à l'axe de l'injecteur (5), par lequel l'air venant du canal d'air (10) peut sortir dans la chambre de combustion (2).
  13. Injecteur de combustible suivant l'une quelconque des revendications 1 à 12, caractérisé en ce que l'injecteur de combustible (1) est fixé à un corps (3) entourant la chambre de combustion (2), au moyen d'un bras porteur latéral (4) présentant un profil de bras porteur (14) favorable à l'écoulement, et en ce que les tuyaux (7,9) sont conduits hors de la chambre de combustion (2) à l'interieur du bras porteur (4).
  14. Injecteur de combustible suivant la revendication 1, caractérisé en ce que le au moins un gicleur à gaz (15) est disposé avant les autres gicleurs (12, 18), dans le sens de l'écoulement.
  15. Injecteur de combustible suivant la revendication 14, caractérisé en ce qu'il est prévu, à l'extrémité aval de l'injecteur de combustible (1), au moins un gicleur auxiliaire (13), orienté largement parallèlement à l'axe de l'injecteur (5), par lequel l'air venant du canal d'air (10) peut sortir dans la chambre de combustion (2), et en ce qu'il est prévu des tuyaux d'air (20), par lesquels de l'air de refroidissement libre de combustible peut être conduit au gicleur auxiliaire (13) en évitant le gicleur à gaz (15).
  16. Procédé pour la conduite d'un injecteur de combustible suivant l'une quelconque des revendications 1 à 13, caractérisé en ce que le gaz est conduit à travers le canal de gaz (8) et le gicleur à gaz (15) jusqu'au gicleur à air/combustible (12) et y est mélangé avec le courant d'air, tandis que le canal de combustible liquide (6) reste inutilisé.
  17. Procédé pour la conduite d'un injecteur de combustible suivant la revendication 1, caractérisé en ce que le combustible liquide, sous la forme d'une émulsion, est conduit à travers le canal de combustible liquide (6) et le gicleur à combustible liquide (18) jusqu'au gicleur à air/combustible (12) et y est mélangé avec le courant d'air, et en ce que de l'air est en outre conduit à travers le canal de gaz (8) jusqu'au gicleur à air/combustible (12) pour une meilleure répartition et un refroidissement supplémentaire du combustible liquide.
EP94110938A 1993-08-10 1994-07-14 Injecteur de combustible pour des combustibles liquides et gazeux et procédé de sa mise en oeuvre Expired - Lifetime EP0638769B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4326802 1993-08-10
DE4326802A DE4326802A1 (de) 1993-08-10 1993-08-10 Brennstofflanze für flüssige und/oder gasförmige Brennstoffe sowie Verfahren zu deren Betrieb

Publications (3)

Publication Number Publication Date
EP0638769A2 EP0638769A2 (fr) 1995-02-15
EP0638769A3 EP0638769A3 (fr) 1995-08-16
EP0638769B1 true EP0638769B1 (fr) 1999-05-26

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EP94110938A Expired - Lifetime EP0638769B1 (fr) 1993-08-10 1994-07-14 Injecteur de combustible pour des combustibles liquides et gazeux et procédé de sa mise en oeuvre

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Country Link
US (1) US5487659A (fr)
EP (1) EP0638769B1 (fr)
JP (1) JP3672597B2 (fr)
DE (2) DE4326802A1 (fr)

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DE19535370B4 (de) * 1995-09-25 2006-05-11 Alstom Verfahren zur schadstoffarmen Vormischverbrennung in Gasturbinenbrennkammern
DE19545309A1 (de) * 1995-12-05 1997-06-12 Asea Brown Boveri Vormischbrenner
GB2307980B (en) * 1995-12-06 2000-07-05 Europ Gas Turbines Ltd A fuel injector arrangement; a method of operating a fuel injector arrangement
US5857419A (en) * 1996-06-20 1999-01-12 Selas Corporation Of America Converging burner tip
DE19730617A1 (de) * 1997-07-17 1999-01-21 Abb Research Ltd Druckzerstäuberdüse
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US5487659A (en) 1996-01-30
JPH0777316A (ja) 1995-03-20
DE59408303D1 (de) 1999-07-01
JP3672597B2 (ja) 2005-07-20
DE4326802A1 (de) 1995-02-16
EP0638769A3 (fr) 1995-08-16
EP0638769A2 (fr) 1995-02-15

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