EP1456583B1 - Procédé d'injection d'un mélange air/carburant dans une chambre de combustion - Google Patents

Procédé d'injection d'un mélange air/carburant dans une chambre de combustion Download PDF

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Publication number
EP1456583B1
EP1456583B1 EP02781042A EP02781042A EP1456583B1 EP 1456583 B1 EP1456583 B1 EP 1456583B1 EP 02781042 A EP02781042 A EP 02781042A EP 02781042 A EP02781042 A EP 02781042A EP 1456583 B1 EP1456583 B1 EP 1456583B1
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EP
European Patent Office
Prior art keywords
fuel
lance
tube
cavity
purge air
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
EP02781042A
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German (de)
English (en)
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EP1456583A1 (fr
Inventor
Stefano Bernero
Weiqun Geng
Christian Steinbach
Peter Stuber
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Filing date
Publication date
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Publication of EP1456583A1 publication Critical patent/EP1456583A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • 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
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/76—Protecting flame and burner parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

  • the present invention relates to a method for injecting a fuel air mixture into a combustion chamber according to the preamble of claim 1. Such a method is known from the document US-A-6038863 known.
  • Premix burners allow, depending on premix quality, a significant reduction in NOx emissions from gas turbines.
  • the problem is the relatively narrow operating range of premix burners.
  • vortex breakdown swirl stabilization such as in double cone burners, as they are US 4,932,861 are known, or in double-cone burners with downstream mixing section, as shown for example in the EP 0704657 described, an additional flame for the part-load operation is required.
  • This partial load flame or pilot flame is usually diffusion-like and ideally should have as close as possible contact with the (premix) main flame.
  • aerodynamic measures a recirculation of fuel mixture in the pilot fuel system during the premix operation, as this can ignite and thus can lead to overheating of the fuel lines.
  • DE-A1-44 24 597 discloses a combustion device.
  • This combustion device is particularly suitable for a gas turbine and comprises a combustion chamber with a plurality of burners operating in parallel. These burners are supplied by means of exchangeable inserted fuel lances from the outside liquid or gaseous fuel via corresponding liquid fuel supply channels or gas supply channels. For easy tuning of the fuel distribution changeable throttle points are provided in the liquid fuel supply channels or gas supply channels of the individual fuel lances of the burner.
  • DE-A1-195 45 310 discloses a premix burner.
  • This premix burner for mixing fuel and combustion air consists essentially of at least two partial cone shells with associated pitch cone axes and inlet channels for the combustion air.
  • the premix burner is essentially formed from a straight hollow cone which is delimited by an outer conical surface and an inner conical surface and in which at least two inlet channels are arranged tangentially to the inner conical surface and along a straight conical surface line of the conical surface.
  • the pitch cone axes of the part cone shells formed thereby lie on a common cone axis.
  • US-A-5,782,626 discloses an atomizer nozzle.
  • this airblast atomizer nozzle for operating a liquid and gaseous fuel powered burner, the intermediate wall between the inner and outer air duct is held by inner and outer support members, which have a sliding seat and can be designed as swirl blades.
  • the atomizer edges of the airblast nozzle are angled in the direction of the nozzle axis.
  • the nozzle is characterized by small dimensions, low pressure loss and low coking tendency.
  • the combustion chamber should be able to be operated simultaneously or alternatively with the two fuels, without the risk of re-ignition or coking (in the case of liquid fuel) occurs.
  • the solution of the problem can be found in the characterizing part of the main claim.
  • the solution is that the liquid fuel injected at the injection in radially outward and directed to the flow of scavenging air in the form of a revolving, the lance tip hollow hollow truncated cone is injected and the gaseous fuel at Eindüsungsort in radially inward and on the stream the scavenging air is injected in a directed manner.
  • the essence of the invention thus consists in that the scavenging air, which is likewise guided to the lance tip, is guided in such a way between the fuels injected into the combustion chamber at the lance tip that a "protective shield" of purging air prevents the two fuels from crossing one another. In particular, it can thus be prevented during operation of the lance with only one fuel that fuel enters that fuel channel, which is currently not driven by fuel.
  • the two channels for the fuels and the channel for the scavenging air are formed as substantially concentric cylindrical tubes of different diameters, wherein the three media are guided in the resulting hollow cylindrical or cylindrical spaces to Eindüsungsort.
  • This construction is simple and particularly suitable with regard to the thermal loads in a burner.
  • the fuel systems are a liquid fuel system and a gaseous fuel system.
  • the gaseous fuel is used for the partial load range in the gas mode
  • the liquid fuel for. B. in the form of an oil for the entire load range in oil operation.
  • the liquid fuel is passed through a central, inner tube with the smallest diameter to the lance tip, said inner tube is surrounded by two other, concentrically arranged with the inner tubes and the gaseous fuel, and the scavenging air in the thus formed hollow cylindrical spaces to the lance tip is led to the Eindüsungsort, and further wherein immediately downstream of the injection site, the scavenging air flows in the cavity between the central, inner tube and the middle tube. This ensures that the purge air at the point of injection effectively between the two Fuel flows and in the sense of a shielding shell and the two fuel streams decoupled from each other.
  • the fuel lance is further characterized in that the purging air is injected into the combustion chamber in a substantially axial and circumferential manner, in the sense of a hollow cylinder at Eindüsungsort.
  • the purge air enters the zone of combustion parallel to the burner axis.
  • the injection of the liquid fuel takes place in a slightly radially outward direction and in the axial purge air flow direction, i. E. in the form of a circumferential hollow circular truncated cone opening to the tip of the spear.
  • the liquid fuel can also be injected at this point through a Hohtkegel swirl nozzle or through a multi-hole nozzle.
  • the gaseous fuel is injected in a slightly radially inward direction and in the purge air flow direction, d. H. in the form of a circular hollow circular truncated cone closing to the tip of the lance.
  • Another preferred embodiment of the inventive method is characterized in that the liquid and the gaseous fuel at the lance base in the inner tube respectively in the cavity between the inner tube and the middle tube are guided, and the purging air in the cavity between the middle tube and the outer Tube is guided.
  • the scavenging air can be diverted into the cavity between the inner tube and the middle tube, while the gaseous fuel is passed into the cavity between the middle tube and the outer tube, wherein particularly preferably the introduction of the scavenging air in the middle cavity is made by arranged in corresponding radial segments slots or holes. Since usually the lance tip on the lance base can have a larger diameter, this design allows higher flows of purge air and gaseous fuel.
  • it relates to the use of a method as described above.
  • it relates to such use for the pilot operation of a premix burner, in particular a double-cone burner with or without a downstream mixing section, in which case the fuel lance is arranged on the axis of the premix burner.
  • the lance extends substantially over a length of 3/4 of the total length of the double-cone burner with or without a downstream mixing section, the total length being the length of the conical region of the double-cone burner.
  • Fig. 1 shows the lance tip 1 of a fuel lance in an axial section.
  • the fuel lance consists of an outermost lance tube 2, the lance in the case of.
  • Use in a double-cone burner, as z. B. off US 4,932,861 is known, usually about 3/4 of the length of the burner protrudes into the cavity between the conical Operakörpem.
  • the fuel lance usually has a circular cross-section.
  • a middle tube 4 In the cylindrical outermost tube 2 is located coaxially with the outermost tube 2, a middle tube 4, and another, inner tube, the oil tube 3, with the smallest diameter.
  • liquid fuel that is oil 6, Gasoline, or the like in the oil guide 5 to the lance tip 1 when the fuel lance with liquid fuel 6 is operated.
  • a central insert 7 At the tip of the oil pipe 3 is a central insert 7, which is arranged substantially on the axis of the burner lance, and which causes the flow of oil at the lance tip 1 is deflected radially outwards.
  • the liquid fuel does not occur in the direction of the axis of the fuel lance in the combustion chamber or the cavity in which the combustion is to take place, but in the form of a circular cone-shaped spray cone, which may be closed all around, ie formed circumferentially.
  • the liquid fuel may also be injected at this point through a hollow cone swirl nozzle (not shown in the figures) or through a multi-hole nozzle.
  • gaseous fuel 11 flows to the lance tip 1.
  • the outer tube 2 has at its outermost end directed in the direction of the axis of the fuel lance, circumferential curvature, i. Constriction, which causes the gas flow is deflected just before emerging from the fuel lance in the direction of the axis of the fuel lance. In other words, a conical hollow gas cone is created.
  • scavenging air 9 now flows according to the invention to the spearhead 1.
  • This scavenging air 9 flows essentially axially, ie. H. forming a cylindrical air jacket at the lance tip 1 from.
  • the scavenging air 9 flows between the two fuels used.
  • both the gaseous fuel 11 and the liquid fuel 6 are directed onto this cylindrical air mantle of purging air 9.
  • This particular arrangement allows a mode of operation in which due to the shielding of the fuel streams by the scavenging air 9, the lance can be operated either with one of the two fuels 6,11, or with both, without causing z. B. when operating with only one fuel would be the danger that fuels 6,11 can get from the controlled fuel channel in the non-operated channel (no fuel reflux).
  • such a fuel lance has an outer diameter in the range of 20 to 40 millimeters (outer diameter of the outermost tube 2)
  • the middle tube 4 has an outer diameter of about 2/3 of that of the outermost tube 2
  • the oil tube 3 has a diameter of At the lance base 17 of the lance this usually has a larger outer diameter of in the range of 30 to 60 millimeters.
  • the tubes are advantageously made of nickel-based alloys with a wall thickness in the range of 1 to 3 millimeters.
  • the outer tube 2 which has an inward bend in the foremost region, is tapered there over a length of 10 millimeters in the range of 40%, which causes a deflection of the pilot gas 11 in the direction of the central axis of the fuel lance and whereby the outlet opening of the fuel lance Pilot gas 11 comes to rest so that the shielding effect of the scavenging air 9 is maximum.
  • such a fuel lance is used for pilot operation of premix burners. If possible, only gaseous fuel 11 is used in pilot operation, wherein typically the fuel lance is used up to approximately 50% load, ie. H. until the premix flame is sufficiently stabilized. If the premix flame is sufficiently stabilized, normally the fuel lance is no longer fueled, but only the fuel nozzles at the inlet slots of the premix burner.
  • the fuel lance according to the invention alternatively allows burner operation using liquid fuel 6.
  • This alternative usability is possible because the purging air 9 prevents that when operating with only one fuel this fuel in the not operated channel into it, and leads there to reignitions.
  • the coat of scavenging air 9 also has the advantage of liquid fuel 6 that coking can be avoided.
  • FIG. 2 shows a lance in its entire length. Since usually the liquid and the gaseous fuel 6, 11 are supplied to the lance base 17 of the burner in a pilot gas-15 and an oil inlet 16, there is basically the problem, the purge air 9 to lead between these two fuel channels.
  • FIG. 2 representing the possibility in which the two fuels are first guided in concentric tubes from the lance base 17 into the area of the lance tip 1, and the purging air 9 is arranged in a further intermediate space between the lances middle pipe 4 and an outer tube 2 is guided to this area.
  • the scavenging air 9 is thereby introduced in the region of the lance base 17 at 14 through openings in the intermediate space between the central tube 4 and the outermost tube 2.
  • This scavenging air 9 is usually sucked from an area behind the burner.
  • the inlet openings can be designed as slots, but to prevent the entry of dirt particles, it proves to be advantageous to perform these openings as holes, usually with a diameter in the range of 2 to 4 millimeters.
  • the pilot gas guide 10 is now guided on the one hand in the radially outermost space by the two outer channels are crossed in a region 12.
  • the scavenging air 9 guided in the outermost space between the pipes 2 and 4 is guided into the middle gap 8 between the middle pipe 4 and the inner oil pipe 3.
  • This mutual deflection takes place in segments (with respect to the cross section perpendicular to the axis of symmetry 18 of the fuel lance), three segments for the gas guide and three segments for the scavenging air guide, the segments typically having the same cross section.
  • the guide of the scavenging air 9 shown in FIG. 2 in the outermost interspace up to the region of the lance tip 1 has the advantage that the lance thereby has good cooling through this purging air channel.
  • this lance is particularly suitable when it comes to burners, which have a certain risk of kickback.
  • FIG 3 shows another exemplary embodiment of a fuel lance for pilot operation, in which the intersection 19, 20 of the two channels of purging air and pilot gas does not take place at the lance tip 1 but already at the lance base 17.
  • the introduced scavenging air 9 is guided into the space between the middle tube 4 and the oil pipe 3, and accordingly the pilot gas inlet 15 is already guided at the lance base 17 into the space between the middle pipe 4 and the outermost pipe 2.
  • the inlet 14 of the scavenging air 9 takes place through slots or holes in three segments while in another three segments, the pilot gas is fed into the outermost channel.
  • the embodiment according to FIG. 3 has the advantage that as a result of the larger diameter of the fuel lance at its lance base 17, larger flow cross sections for the pilot gas and the purging air are made possible than when the intersection takes place at the lance tip. Accordingly, in such a fuel lance, higher flows of purge air 9 and pilot gas 11 can be realized.

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

Abstract

L'invention concerne une lance pour combustibles à l'aide de laquelle des combustibles (6,11) peuvent être injectés en alternance ou simultanément, dans une chambre de combustion, par l'intermédiaire d'au moins deux canaux (5, 10) séparés l'un de l'autre, en un point d'injection disposé sensiblement au niveau de la pointe de la lance (1). L'invention vise à parvenir à un mode de fonctionnement fiable sans risque de retour de flamme et en évitant les phénomènes de calamine. A cet effet, outre du combustible, la lance pour combustibles achemine de l'air de balayage (9) jusqu'au point d'injection et l'air de balayage (9) est guidé au point d'injection entre les deux systèmes de combustible (6, 11), de sorte que ces derniers soient protégés l'un par rapport à l'autre par l'air de balayage (9).

Claims (6)

  1. Procédé d'injection d'un mélange de combustible et d'air dans une chambre de combustion,
    - dans lequel au moyen d'une lance à combustible qui présente une pointe (1) de lance et deux canaux à combustible (6, 11) ainsi qu'un canal pour l'air de balayage (9), un combustible liquide et un combustible gazeux (6, 11) et de l'air de balayage (9) sont injectés dans la chambre de combustion en alternance ou simultanément,
    - le combustible liquide (6) étant amené par un tube intérieur central (3) de plus petit diamètre jusqu'à la pointe (1) de la lance, ce tube intérieur (3) étant entouré par deux autres tubes (2, 4) disposés concentriquement par rapport au tube intérieur et
    - l'air de balayage (9) s'écoulant entre le tube intérieur central (3) et le tube (4) du milieu et étant amené à l'emplacement d'injection d'une manière essentiellement axiale et périphérique, à la manière d'un cylindre creux, entre le combustible liquide et les combustibles gazeux (6, 11), de telle sorte que ces derniers restent séparés l'un de l'autre par l'air de balayage (9),
    caractérisé en ce que
    - le combustible liquide (6) est injecté à l'emplacement d'injection d'une manière orientée radialement vers l'extérieur et vers l'écoulement d'air de balayage (9), sous la forme d'un tronc de cône circulaire creux périphérique qui s'ouvre en direction de la pointe (1) de la lance et
    - le combustible gazeux (11) est injecté à l'emplacement d'injection d'une manière orientée radialement vers l'intérieur et vers l'écoulement d'air de balayage (9).
  2. Procédé selon la revendication 1, caractérisé en ce que le combustible liquide et le combustible gazeux (6, 11) sont amenés à la base (17) de la lance dans le tube intérieur (3) respectivement dans l'espace creux entre le tube intérieur (3) et dans le tube du milieu (4), l'air de balayage (9) étant amené dans l'espace creux situé entre le tube du milieu (4) et le tube extérieur (2).
  3. Procédé selon la revendication 2, caractérisé en ce que directement à la base de la lance (17), l'air de balayage (9) est dévié dans l'espace creux situé entre le tube intérieur (3) et le tube du milieu (4) tandis que le combustible gazeux (6) est amené dans l'espace creux situé entre le tube du milieu (4) et le tube extérieur (2), l'injection d'air de balayage (9) dans l'espace creux du milieu s'effectuant de façon particulièrement préférable par des fentes ou des alésages disposés dans des segments radiaux correspondants.
  4. Procédé selon la revendication 2, caractérisé en ce que l'air de balayage (9) est amené vers la pointe (1) de la lance dans l'espace creux situé entre le tube du milieu (4) et le tube extérieur (2), l'air de balayage (9) étant dévié dans l'espace creux du milieu situé entre le tube d'intérieur (3) et le tube du milieu (4) dans la zone de la pointe (1) de la lance, tandis que le combustible gazeux (11) est amené dans l'espace creux extérieur (10) situé entre le tube du milieu (4) et le tube extérieur (2).
  5. Procédé selon l'une des revendications précédentes, caractérisé en ce que la lance à combustible est disposée sur l'axe d'un brûleur à prémélange et en ce que le procédé est utilisé pour le fonctionnement pilote du brûleur à prémélange, en particulier d'un brûleur à double cône avec ou sans parcours de mélange aval.
  6. Procédé selon la revendication 5, caractérisé en ce que la lance à combustible a une longueur qui correspond essentiellement à 3/4 de la longueur totale du brûleur à double cône et est utilisée pour le fonctionnement pilote du brûleur à prémélange.
EP02781042A 2001-12-20 2002-12-06 Procédé d'injection d'un mélange air/carburant dans une chambre de combustion Expired - Lifetime EP1456583B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH233101 2001-12-20
CH23312001 2001-12-20
PCT/CH2002/000675 WO2003054447A1 (fr) 2001-12-20 2002-12-06 Lance pour combustibles

Publications (2)

Publication Number Publication Date
EP1456583A1 EP1456583A1 (fr) 2004-09-15
EP1456583B1 true EP1456583B1 (fr) 2007-10-10

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Application Number Title Priority Date Filing Date
EP02781042A Expired - Lifetime EP1456583B1 (fr) 2001-12-20 2002-12-06 Procédé d'injection d'un mélange air/carburant dans une chambre de combustion

Country Status (8)

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US (2) US7082768B2 (fr)
EP (1) EP1456583B1 (fr)
JP (1) JP4246067B2 (fr)
CN (1) CN1320307C (fr)
AU (1) AU2002349248A1 (fr)
DE (1) DE50211068D1 (fr)
ES (1) ES2295423T3 (fr)
WO (1) WO2003054447A1 (fr)

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Also Published As

Publication number Publication date
JP4246067B2 (ja) 2009-04-02
WO2003054447A1 (fr) 2003-07-03
CN1620579A (zh) 2005-05-25
CN1320307C (zh) 2007-06-06
JP2005513399A (ja) 2005-05-12
EP1456583A1 (fr) 2004-09-15
DE50211068D1 (de) 2007-11-22
US7406827B2 (en) 2008-08-05
US7082768B2 (en) 2006-08-01
ES2295423T3 (es) 2008-04-16
US20050028532A1 (en) 2005-02-10
US20080163626A1 (en) 2008-07-10
AU2002349248A1 (en) 2003-07-09

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