EP1456583A1 - Lance pour combustibles - Google Patents

Lance pour combustibles

Info

Publication number
EP1456583A1
EP1456583A1 EP02781042A EP02781042A EP1456583A1 EP 1456583 A1 EP1456583 A1 EP 1456583A1 EP 02781042 A EP02781042 A EP 02781042A EP 02781042 A EP02781042 A EP 02781042A EP 1456583 A1 EP1456583 A1 EP 1456583A1
Authority
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.)
Granted
Application number
EP02781042A
Other languages
German (de)
English (en)
Other versions
EP1456583B1 (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
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 Technology AG filed Critical Alstom Technology AG
Publication of EP1456583A1 publication Critical patent/EP1456583A1/fr
Application granted granted Critical
Publication of EP1456583B1 publication Critical patent/EP1456583B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D17/00Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00Combustion apparatus characterised by arrangements for air supply
    • F23C7/002Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D11/00Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36Details, e.g. burner cooling means, noise reduction means
    • F23D11/40Mixing tubes or chambers; Burner heads
    • F23D11/402Mixing chambers downstream of the nozzle
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D14/00Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46Details, e.g. noise reduction means
    • F23D14/72Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/76Protecting flame and burner parts
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D2900/00Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D2900/00Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

  • the present invention relates to a fuel lance according to the preamble of claim 1 and to the use of such a fuel lance in a double-cone burner according to claim 11.
  • premix burners allow a significant reduction in NOx emissions from gas turbines.
  • the relatively narrow operating range of premix burners is problematic.
  • swirl stabilization with vortex breakdown such as in double-cone burners as described in US 4,932,861, or in double-cone burners with a downstream mixing section as described for example in EP 0704657
  • an additional flame is required for part-load operation.
  • This partial load flame or pilot flame is usually diffusion-like and should ideally have as close contact as possible with the (premix) main flame.
  • the fuel lance should be able to be operated simultaneously or alternatively with the two fuels without the risk of reignition or coking (in the case of liquid fuel).
  • the solution to the problem can be found in the characterizing part of the main claim.
  • the solution is that the fuel lance, in addition to fuel, also leads purge air to the injection location, and that the purge air at the injection location is conducted between the two fuel systems in such a way that the purge air shields them from one another.
  • the essence of the invention is therefore that the scavenging air, which is also led to the tip of the lance, is guided between the fuels injected into the combustion chamber at the tip of the lance in such a way that a “protective screen” of scavenging air prevents the two fuels from crossing.
  • a “protective screen” of scavenging air prevents the two fuels from crossing.
  • the two channels for the fuels and the channel for the scavenging air are designed as essentially concentric cylindrical tubes of different diameters, the three media being guided to the injection site in the hollow cylindrical or cylindrical gaps that are created.
  • This design is simple and particularly suitable in relation to the thermal loads in a burner.
  • the fuel systems are a system with liquid fuel and a system with gaseous fuel.
  • Partial load range used in gas operation and the liquid fuel, e.g. B. in the form of a
  • the liquid fuel is preferably led to the lance tip via a central, inner tube with the smallest diameter, this inner tube being arranged by two further tubes which are arranged concentrically with the inner one
  • Pipes is surrounded and the gaseous fuel and the scavenging air are guided in the hollow cylindrical spaces thus formed to the lance tip to the injection site, and the scavenging air continues directly at the injection site
  • Cavity flows between the central, inner tube and the middle tube. This will ensure that the purge air is effectively between the two at the point of injection Fuel flows and flows in the sense of a shielding jacket and decouples the two fuel flows from each other.
  • the scavenging air is injected into the combustion chamber in an essentially axial and circumferential manner, in the sense of a hollow cylinder, at the injection location.
  • the purge air enters the combustion zone parallel to the burner axis.
  • the liquid fuel can moreover preferably be at the injection point in a slightly radially outward direction and in a manner directed towards the axial purge air flow, i.e. in the form of an encircling hollow circular truncated cone opening towards the tip of the lance.
  • the liquid fuel can also be injected through a hollow-cone swirl nozzle or through a multi-hole nozzle.
  • the gaseous fuel can take place in a slightly radially inward direction and in a manner directed towards the purge air flow, ie. H. in the form of a circular circular frustum of a cone that closes at the tip of the lance.
  • Another preferred embodiment is characterized in that the liquid and the gaseous fuel are guided at the lance base in the inner tube and in the cavity between the inner tube and the middle tube, respectively, and the purge air is guided in the cavity between the middle tube and the outer tube ,
  • the purging air can either be diverted directly to the lance base into the cavity between the inner tube and the middle tube, while the gaseous fuel is directed into the cavity between the middle tube and the outer tube, with the purging air being particularly preferably introduced into the middle cavity through slots or holes arranged in corresponding radial segments. Since usually the lance tip can have a larger diameter at the lance base, this design allows higher flows of purge air and gaseous fuel.
  • the present invention relates to the use of a fuel lance as described above.
  • it relates to such a use for the pilot operation of a premix burner, in particular a double-cone burner with or without a downstream mixing section, the fuel lance being arranged on the axis of the premix burner.
  • the lance extends essentially 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 an axial section through a fuel lance according to the invention
  • FIG. 2 shows an axial section through an entire fuel lance according to the invention, in which the crossing is arranged at the tip of the lance;
  • Fig. 3 shows an axial section through a fuel lance according to the invention, in which the crossing is arranged on the lance base.
  • Fig. 1 shows the 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 it is for. B. is described in US 4,932,861, usually about 3/4 of the length of the burner protrudes into the cavity between the conical partial bodies.
  • the fuel lance usually has a circular cross section.
  • the oil tube in the cylindrical outermost tube 2, coaxially arranged with the outermost tube 2, there is a middle tube 4 and another inner tube 3, the oil tube, with the smallest diameter.
  • Liquid fuel that is to say oil, flows through the oil pipe 3, Petrol, or the like in the oil guide 5 to the lance tip if the lance is to be operated with liquid fuel.
  • a central insert 7 At the tip of the oil pipe 3 there is a central insert 7, which is arranged essentially on the axis of the burner lance and which leads to the oil flow at the tip of the lance being deflected radially outwards.
  • the liquid fuel does not enter the combustion chamber or the cavity in which the combustion is to take place in the direction of the axis of the fuel lance, but rather in the form of a circular cone-shaped spray cone which can be closed all around, that is to say it can run all the way around.
  • the liquid fuel can also be injected through a hollow-cone swirl nozzle (not shown in the figures) or through a multi-hole nozzle.
  • gaseous fuel usually flows at the lance tip 1.
  • the outer tube 2 has at its outermost end a circumferential curvature directed in the direction of the axis of the fuel lance, i.e. Constriction, which leads to the gas stream 11 being deflected in the direction of the axis of the fuel lance shortly before it emerges from the fuel lance.
  • Constriction a circumferential curvature directed in the direction of the axis of the fuel lance, i.e. Constriction, which leads to the gas stream 11 being deflected in the direction of the axis of the fuel lance shortly before it emerges from the fuel lance.
  • a tapered hollow gas cone is created.
  • purge air 9 now flows according to the invention at the lance tip 1.
  • This purge air now flows essentially axially, ie with the formation of a cylindrical air jacket at the lance tip 1.
  • the purge air 9 flows between the two fuels used.
  • both the gaseous fuel stream 11 and the liquid fuel stream 6 are directed onto this cylindrical air jacket made of purge air.
  • This particular arrangement allows an operation in which, as a result of the shielding of the fuel flows through the purge air, the lance can either be operated with one of the two fuels or with both without z.
  • such a fuel lance has an outside diameter in the range of 20 to 40 millimeters (outside diameter of the outermost pipe 2), the middle pipe 4 has an outside diameter of about 2/3 of that of the outermost pipe 2, and the oil pipe 3 has a diameter of something 1/3 that of the outermost tube 2. At the foot 17 of the lance, this usually has a larger outside 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 curvature in the foremost region, is there tapered over a length of 10 millimeters by in the region of 40%, which causes a deflection of the pilot gas 11 in the direction of the central axis of the fuel lance and thereby the outlet opening of the Pilot gas comes to lie so that the shielding effect of the purge air is at a maximum.
  • a fuel lance is usually used for the pilot operation of premix burners. If possible, only gaseous fuel is used in pilot operation, with the fuel lance typically being used up to about 50% load, ie until the premix flame is sufficiently stabilized. If the premix flame is sufficiently stabilized, the fuel lance is normally no longer activated with fuel, 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.
  • This alternative usability is possible because the purge air prevents this fuel from getting into the non-operated channel when operating with only one fuel, and causing reignitions there.
  • the purge air jacket also has the advantage with liquid fuel that coking is avoided.
  • Fig. 2 shows a lance in its entire length. Since the liquid 16 and the gaseous 15 fuel are usually supplied at the base 17 of the burner in two concentrically arranged pipes, there is basically the problem of guiding the purge air 9 between these two fuel channels. This can be done in two different ways, FIG.
  • the pilot gas guide 10 is now guided into the radially outermost space on one side by crossing the two outer channels in an area 12.
  • the purge air 9 guided in the outermost space between the pipes 2 and 4 is guided into the middle space between the middle pipe 4 and the inner oil pipe 3.
  • This mutual deflection takes place segment by segment (with respect to the cross section perpendicular to the axis 18 of the fuel lance), three segments being sufficient for the gas duct and three segments for the scavenging air duct, the segments typically having the same cross section.
  • the area of the lance tip has the advantage that the lance has good cooling through this purge air channel. This makes this lance particularly suitable when it comes to burners with a certain risk of kickback.
  • FIG. 3 shows another exemplary embodiment of a fuel lance for pilot operation, in which the two channels of purge air and pilot gas do not cross at the lance tip, but already at the lance base 17.
  • the introduced purge air 14 is already guided on the lance base 17 into the space between the middle pipe 4 and the oil pipe 3, and accordingly the pilot gas supply 15 is already guided on the lance base 17 into the space between the middle pipe 4 and the outer pipe 2.
  • this takes place in segments, that is to say the supply 14 of the purge air takes place through slots or bores in three segments, while in a further three segments the pilot gas is led into the outermost channel.
  • the embodiment according to FIG. 3 has the advantage that, owing to the larger diameter of the fuel lance at its base 17, larger flow cross-sections for the pilot gas and the purge air are also possible than when the intersection takes place at the tip of the lance. Accordingly, higher flows of purge air and pilot gas can be realized with such a fuel lance.

Landscapes

  • 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).
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
CH23312001 2001-12-20
CH233101 2001-12-20
PCT/CH2002/000675 WO2003054447A1 (fr) 2001-12-20 2002-12-06 Lance pour combustibles

Publications (2)

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

Family

ID=4568627

Family Applications (1)

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)

Country Link
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
US7406827B2 (en) 2008-08-05
AU2002349248A1 (en) 2003-07-09
ES2295423T3 (es) 2008-04-16
EP1456583B1 (fr) 2007-10-10
JP4246067B2 (ja) 2009-04-02
CN1620579A (zh) 2005-05-25
US7082768B2 (en) 2006-08-01
JP2005513399A (ja) 2005-05-12
US20080163626A1 (en) 2008-07-10
CN1320307C (zh) 2007-06-06
DE50211068D1 (de) 2007-11-22
WO2003054447A1 (fr) 2003-07-03
US20050028532A1 (en) 2005-02-10

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