EP0911583B1 - Procédé de mise en oeuvre d'un brûleur à prémélange - Google Patents

Procédé de mise en oeuvre d'un brûleur à prémélange Download PDF

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Publication number
EP0911583B1
EP0911583B1 EP97810800A EP97810800A EP0911583B1 EP 0911583 B1 EP0911583 B1 EP 0911583B1 EP 97810800 A EP97810800 A EP 97810800A EP 97810800 A EP97810800 A EP 97810800A EP 0911583 B1 EP0911583 B1 EP 0911583B1
Authority
EP
European Patent Office
Prior art keywords
fuel
premix burner
burner
liquid
inner chamber
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
EP97810800A
Other languages
German (de)
English (en)
Other versions
EP0911583A1 (fr
Inventor
Adnan Dr. Eroglu
Jaan Dr. Hellat
Jakob Prof. Dr. Keller
Robin Mcmillan
Roger Suter
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 Switzerland GmbH
Original Assignee
Alstom Schweiz 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 Schweiz AG filed Critical Alstom Schweiz AG
Priority to AT97810800T priority Critical patent/ATE234444T1/de
Priority to EP97810800A priority patent/EP0911583B1/fr
Priority to JP10303862A priority patent/JPH11304111A/ja
Priority to US09/179,460 priority patent/US6270338B1/en
Publication of EP0911583A1 publication Critical patent/EP0911583A1/fr
Application granted granted Critical
Publication of EP0911583B1 publication Critical patent/EP0911583B1/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
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • 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
    • F23D11/38—Nozzles; Cleaning devices therefor
    • 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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the invention relates to a method for operating a premix burner according to Claim 1 and a corresponding premix burner to carry out the procedure.
  • Combustion chambers have long been available for stationary gas turbines in power plants with pre-mix burners designed as so-called double-cone burners proven, where the fuel from the outside by insertable fuel lances is fed.
  • the lance is usually designed as a two-fuel lance, i.e. optionally gaseous fuel, e.g. Pilot gas, and / or more liquid Fuel, for example an oil-water mixture, are supplied.
  • a liquid fuel pipe an atomizing air pipe and a pilot gas pipe arranged concentrically.
  • the tubes each form a channel for the Liquid fuel, the atomizing air and the pilot gas, which at the lance head in end of a central fuel nozzle.
  • the fuel lance is stuck with its lance head in a corresponding inner tube of the double-cone burner, so that the escaping fuel in the middle of the burner interior connected to the inner tube arrives (see DE 43 06 956 A1, EP0 794 383 A).
  • a double cone burner which is used for intended for use in a combustion chamber connected to a gas turbine is.
  • This burner consists of two hollow, complementary to the double cone burner Partial bodies that are arranged radially offset from each other. He owns one with hollow cone-shaped interior enlarging in the direction of flow tangential air inlet slots.
  • the fuel supply for the double-cone burner takes place from the outside via the fuel lance, which goes into the central liquid fuel nozzle empties.
  • the latter forms a hollow cone-shaped fuel spray consisting of liquid fuel and air, in which most fuel droplets at the outer end of the conical spray pattern are concentrated.
  • full jet atomizers are used downstream with pre-mix burners equipped combustion chambers of gas turbine plants, however not used because the liquid fuel is atomized quickly shall be.
  • the described full jet atomizer is for many combustion applications not very suitable because it tends to drop the fuel to concentrate in a small area immediately downstream of the nozzle. Especially under the unfavorable conditions of a low air / fuel ratio and at low air speed, atomization cannot be sufficient be achieved.
  • the invention has for its object a method for operating a premix burner to create which is improved in certain operating modes Has functional reliability and functionality.
  • a corresponding Premix burners for performing the method can be specified.
  • this is achieved by using an operating method a premix burner, at least one liquid fuel in a full jet and with an injection angle ⁇ injected into the interior of the premix burner of less than 10 ° becomes.
  • the liquid fuel nozzle is provided with a simple injection opening, which has a guide length I and a diameter d.
  • the one through the Injection opening axially injected liquid fuel into the interior of the premix burner forms a full jet due to the influence of the opening Injection angle is less than 10 ° and is therefore relatively small.
  • the act Fuel jet and the combustion air flow inside the premix burner together. Mainly due to the shear forces between the fuel jet and the swirled combustion air, is in the downstream area of the premix burner achieved good atomization, resulting in combustion suitable, fine droplets are generated. Because of the small injection angle and the concentration of the axial pulse of the injected fuel in the burner axis, the influence of the swirl flow on the fuel droplets significantly reduced.
  • the liquid fuel nozzle used is particularly simple, robust and reliable, which also helps to reduce costs.
  • Your main parameters are the diameter d, the guide length I and the shape of the injection opening.
  • the degree of turbulence is also decisive for the atomization Fuel flow, which is mainly due to the conditions upstream Injection opening and defined by the aforementioned axial guide length is.
  • the injection opening particularly advantageously has a ratio of the guide length to the diameter of 4 ⁇ l / d ⁇ 6.
  • a ratio of the guide length to the diameter of the injection opening is determined by the textbook “Atomization and sprays "by A. Lefebvre, West Lafayette, Indiana 1989, pp. 155-161, In particular in Fig. 5.4., which results are shown on the basis of test results Influence the ratio of the guide length to the diameter of the injection opening on the injection coefficient, i.e. on the ratio of the current to the theoretical flow rate through the injection opening.
  • Quotient l / d examined up to 10 and found that the greatest injection coefficient is reached with a quotient l / d of approx. 2.
  • this compact liquid fuel spray is in such an atomizer nozzle or a suitably equipped premix burner on the burner head there is no fully prepared fuel mixture yet. Therefore, a pulsation-free operation over a wide load range and also with different ones Amount of water reached.
  • the compact liquid fuel spray also hits not on the burner walls, causing the premix burner to overheat and the combustion chamber can be prevented as well as coking inside of the premix burner.
  • Another, which is exclusively within the liquid fuel spray located in the combustion air flow The advantage is good ignition and partial load capability without an additional injection stage. As a result, both the fuel lance and the driving concept are the entire combustion chamber easier and cheaper. After all, that too Retrofitting existing pre-mix burners possible with minimal costs.
  • the fuel lance consists of a central liquid fuel pipe, which is coaxially surrounded by an air tube. Because the liquid Full jet in this process or through the corresponding device is surrounded by an air flow, the liquid fuel spray remains small Mass flow in the center of the interior of the burner. So that is stability of liquid fuel, especially at low liquid flow rates, i.e. improved in ignition and partial load of the gas turbine, both improved ignition performance and higher part-load combustion performance become. With large liquid flow rates, however, the dominates Liquid flow. In addition, the injection opening and the area of the Burner head by the air flow against fuel deposits and consequently protected against coking.
  • the screen airflow is at a speed from 5 to 60 m / s and with a mass of 0.1 to 2.0% of the total air mass flow is injected into the interior of the premix burner.
  • this serves Shield air flow not for atomizing the liquid fuel, which is about 5 to 10% of the total air mass flow would be required. Rather, it will Small amount of axially injected air to control the aerodynamics in the area near the injection port, i.e. to improve the flow conditions of the Premix burner used.
  • the air prevents that from Cross-sectional jump downstream of the injection opening caused suction of the Liquid jet on the inner wall of the premix burner and on the other one local twist count too high.
  • the air flow also increases axial penetration of the full jet of liquid emerging from the liquid fuel nozzle.
  • the premix burner In a further embodiment of the invention, it is located in the interior of the premix burner, full jet of one spreading in the flow direction rotating combustion air stream flowing tangentially into the burner.
  • the ignition of the combustion mixture that takes place takes place in the Area of the burner mouth instead, the flame in this area by a Backflow zone is stabilized.
  • the premix burner consists of at least two hollow partial cone bodies, radially offset from each other, with a hollow cone-shaped interior that increases in the direction of flow.
  • the burner has tangential air inlet slots and the liquid fuel nozzle is connected to a fuel lance used to supply fuel.
  • this method provides a form of liquid spray with a small injection angle, which with the small opening angle of the premix burner interacts optimally. This creates ideal conditions for the Combustion of liquid fuel by means of a premix burner designed in this way created.
  • FIG. 1 two exemplary embodiments of the invention are shown in FIG the premix burner used in the combustion chamber of a gas turbine system represented a liquid fuel nozzle according to the invention.
  • the gas turbine system for example, does not show the compressor and the gas turbine.
  • the direction of flow of the work equipment is indicated by arrows.
  • the gas turbine plant consists of a compressor, one Gas turbine and a combustion chamber 1.
  • the combustion chamber 1 there are several both for operation with liquid fuel 2 as well as with gaseous fuel 3 suitable and designed as a double-cone pre-mix burner 4.
  • the double-cone burners 4 each consist of two half, hollow partial cone bodies 5, 6, each with an inner wall 7, 8. Close both inner walls 7, 8 a hollow conical interior 9 that increases in the direction of flow a (Fig. 1).
  • the partial cone bodies 5, 6 each have an offset to the other arranged central axis 10, 11.
  • Both partial cone bodies 5, 6 each have a cylindrical one Initial part 15, 16.
  • the initial parts 15, 16 are analogous to the partial cone bodies 5, 6 staggered.
  • Fuel lance 18 arranged (Fig. 1).
  • the liquid fuel nozzle 17 has one simple, circular injection opening 19 (Fig. 2).
  • This injection opening 19 has a diameter d and a guide length l, the quotient of the Guide length l and the diameter d is 4 (Fig. 3).
  • the injection opening 19 can correspond to the specific operating conditions the double cone burner 4 also another suitable shape and the quotient of guide length and diameter is an amount up to 6 to have.
  • the double-cone burner 4 can be purely conical, i.e. without the cylindrical starting parts 15, 16 are formed (not shown).
  • Both partial cone bodies each have a fuel line provided with openings 20 21, 22, which at the end of the tangential air inlet slots 12, 13 is appropriate.
  • openings 20 21, 22 Through the fuel lines 21, 22, the gaseous fuel 3 fed and through the openings 20 into the tangential air inlet slots 12, 13 initiated. Mixing of the gaseous fuel 3 takes place there with the combustion air 14 flowing in from the outside.
  • Combustion chamber side 1 the double cone burner 4 has a collar-shaped, as anchoring for the Partial cone body 5, 6 serving end plate 23 with a number of holes 24 (Fig. 1). If necessary, the combustion chamber 1 can pass through these bores 24 Cooling air 25 are supplied.
  • the double-cone burner 4 is also used as a liquid fuel via the fuel lance 18 2 fuel oil used.
  • the fuel oil 2 is through the central Injection opening 19 of the liquid fuel nozzle 17 with an injection angle ⁇ injected smaller than 10 ° into the interior 9. Because of this narrow injection angle initially arises in the interior 9 of the double-cone burner 4 compact full jet 26, which only opens downstream and in which the fuel droplets are evenly distributed over the entire cross-section.
  • a full jet 26 has sufficient fuel spray in its center axial impulses so that the fuel droplets do not hit the inner walls 7, 8 of the partial cone body 5, 6 are worn. It can also have this effect due to a relatively high injection speed of the fuel oil 2 of 20 to 60 m / s to be reinforced.
  • the full jet 26 spreads in the interior 9 of the double-cone burner 4 in the direction of flow evenly and ultimately takes on a conical shape Shape.
  • the resulting fuel mixture is ignited in the area of the burner orifice, whereby a flame front 27 is formed, which in turn is in the area the burner mouth is stabilized by a backflow zone 28.
  • the pulse of the full jet 26 can also be regulated that depending on the premix burner 4 used and the current one Load state of the combustion chamber 1 required penetration depth of the fuel drops is achieved.
  • the fuel lance 18 consists of a central liquid fuel tube 29, which is coaxially surrounded by an air tube 30 (Fig. 4).
  • the double-cone burner 4 is therefore simultaneous with the injection of the Fuel oil 2, but radially outside and concentric with fuel oil 2 Shield air flow 31 introduced into the interior 9 of the double-cone burner 4.
  • This screen air flow 31 is injected at a speed of approx. 30 m / s and a mass of 0.1 to 2.0% of the total air mass flow of the double-cone burner 4.
  • an even more compact full jet 26 'generated which bursts only at the end of the burner (Fig. 5). Cools and at the same time protects the air tube 30 into the interior 9 of the double-cone burner 4 arriving screen air flow 31 the liquid fuel pipe 29. All other processes take place essentially analogously to the first embodiment.

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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)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Claims (10)

  1. Procédé de mise en oeuvre d'un brûleur à prémélange comprenant une buse pour combustible liquide (17) débouchant centralement dans un espace interne (9) du brûleur à prémélange (4), au moins un combustible liquide (2) étant injecté dans un jet complet (26, 26') dans l'espace interne (9) du brûleur à prémélange (4) avec un angle d'injection • inférieur à 10°.
  2. Procédé selon la revendication 1, caractérisé en ce qu'un courant d'air écran (31) est introduit dans l'espace interne (9) radialement à l'extérieur ainsi que concentriquement à au moins un combustible liquide (2).
  3. Procédé selon la revendication 2, caractérisé en ce que le courant d'air écran (31) est introduit avec une faible masse dans l'espace interne (9).
  4. Procédé selon la revendication 3, caractérisé en ce que le courant d'air écran (31) vaut environ 0,1 + 2,0% du débit massique d'air total du brûleur à prémélange (4).
  5. Procédé selon la revendication 4, caractérisé en ce que le courant d'air écran (31) est introduit dans l'espace interne (9) avec une vitesse de 5 à 60 m/s.
  6. Procédé selon l'une quelconque des revendications 1 à 5, caractérisé en ce que le jet complet (26, 26') s'étalant dans l'espace interne (9) du brûleur à prémélange (4) dans la direction de l'écoulement est entouré par un courant d'air de combustion (14) rotatif, s'écoulant tangentiellement dans le brûleur à prémélange (4), l'allumage du mélange s'effectuant dans la région de l'embouchure du brûleur et le front de flamme (27) se stabilisant dans cette région par une zone de reflux (28).
  7. Brûleur à prémélange pour mettre en oeuvre le procédé selon l'une quelconque des revendications 1 à 6, dans lequel la buse pour combustible liquide (17) possède une ouverture d'injection (19) simple, réalisée avec une longueur de guidage (1) ainsi qu'un diamètre (d).
  8. Brûleur à prémélange selon la revendication 7, caractérisé en ce que l'ouverture d'injection (19) présente un rapport longueur de guidage (1) à diamètre (d) de 4 ≤ l/d ≤ 6.
  9. Brûleur à prémélange selon la revendication 8, caractérisé en ce que le brûleur à prémélange (4) se compose d'au moins deux corps coniques partiels creux (5, 6), décalés radialement l'un par rapport à l'autre, avec un espace interne (9) en forme de cône creux s'élargissant dans la direction de l'écoulement et présente des fentes d'entrée d'air tangentielles (12, 13) et la buse pour combustible liquide (17) est connectée à une lance de combustible (18) servant à l'alimentation en combustible.
  10. Brûleur à prémélange selon la revendication 9, caractérisé en ce que la lance de combustible (18) se compose d'un tube de combustible liquide (29) central, qui est entouré coaxialement par un tube d'air (30).
EP97810800A 1997-10-27 1997-10-27 Procédé de mise en oeuvre d'un brûleur à prémélange Expired - Lifetime EP0911583B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
AT97810800T ATE234444T1 (de) 1997-10-27 1997-10-27 Verfahren zum betrieb eines vormischbrenners
EP97810800A EP0911583B1 (fr) 1997-10-27 1997-10-27 Procédé de mise en oeuvre d'un brûleur à prémélange
JP10303862A JPH11304111A (ja) 1997-10-27 1998-10-26 予混合バーナを運転する方法
US09/179,460 US6270338B1 (en) 1997-10-27 1998-10-27 Method for operating a premix burner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810800A EP0911583B1 (fr) 1997-10-27 1997-10-27 Procédé de mise en oeuvre d'un brûleur à prémélange

Publications (2)

Publication Number Publication Date
EP0911583A1 EP0911583A1 (fr) 1999-04-28
EP0911583B1 true EP0911583B1 (fr) 2003-03-12

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EP97810800A Expired - Lifetime EP0911583B1 (fr) 1997-10-27 1997-10-27 Procédé de mise en oeuvre d'un brûleur à prémélange

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US (1) US6270338B1 (fr)
EP (1) EP0911583B1 (fr)
JP (1) JPH11304111A (fr)
AT (1) ATE234444T1 (fr)

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CN111156544A (zh) * 2019-12-27 2020-05-15 成立航空技术有限公司 并联式双油路离心喷嘴主副喷口相对位置的确定方法

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Publication number Priority date Publication date Assignee Title
CN111156544A (zh) * 2019-12-27 2020-05-15 成立航空技术有限公司 并联式双油路离心喷嘴主副喷口相对位置的确定方法

Also Published As

Publication number Publication date
EP0911583A1 (fr) 1999-04-28
ATE234444T1 (de) 2003-03-15
US6270338B1 (en) 2001-08-07
JPH11304111A (ja) 1999-11-05

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