EP2006606A1 - Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange - Google Patents

Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange Download PDF

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Publication number
EP2006606A1
EP2006606A1 EP07012207A EP07012207A EP2006606A1 EP 2006606 A1 EP2006606 A1 EP 2006606A1 EP 07012207 A EP07012207 A EP 07012207A EP 07012207 A EP07012207 A EP 07012207A EP 2006606 A1 EP2006606 A1 EP 2006606A1
Authority
EP
European Patent Office
Prior art keywords
premix
burner
fuel
air
pilot
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.)
Withdrawn
Application number
EP07012207A
Other languages
German (de)
English (en)
Inventor
Mariano Cano Dr. Wolf
Patrick Ronald Flohr
Matthias Dr. Hase
Martin Lenze
Jürgen Dr. Meisl
Paul Pixner
Uwe Remlinger
Kai-Uwe Dr. Schildmacher
Thomas Alexis Schneider
Jaap Dr. Van Kampen
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP07012207A priority Critical patent/EP2006606A1/fr
Priority to EP08774139.3A priority patent/EP2156095B1/fr
Priority to US12/663,886 priority patent/US20100192583A1/en
Priority to PCT/EP2008/057757 priority patent/WO2008155373A1/fr
Publication of EP2006606A1 publication Critical patent/EP2006606A1/fr
Withdrawn legal-status Critical Current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 
    • F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
    • F23C9/006—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber the recirculation taking place in the combustion chamber
    • 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
    • F23D11/102—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 in an internal mixing chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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 
    • F23C2202/00—Fluegas recirculation
    • F23C2202/40—Inducing local whirls around flame
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2203/00—Gaseous fuel burners
    • F23D2203/007—Mixing tubes, air supply regulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation

Definitions

  • the present invention relates to a method for stabilizing the flame of a premix burner.
  • Combustion of fuel or an air-fuel mixture in combustors of gas turbines can cause combustion oscillations. These are characterized by greatly increased pressure amplitudes at different frequencies. Combustion vibrations can occur in the combustion chamber itself, but also in the adjacent components of the gas turbine and can be measured there. In general, combustion oscillations are undesirable because they adversely affect the combustion and can damage the entire combustion system. Combustion vibrations occur primarily in premix combustion systems, that is, in systems where the fuel is mixed with air prior to ignition. They occur preferably when the flame is limited to a relatively small location, so the reaction density is very high. Such a compact flame with a small local extent are associated with so-called delay times. If the delay times are within a certain narrow range, interactions with the acoustics of the combustion chamber may occur. This combustion oscillations can occur.
  • pilot flames An additional, common way to stabilize the flame is the use of pilot flames. This is particularly important in a partial load operation of a gas turbine.
  • the method according to the invention for stabilizing the flame of a premix burner comprising a reaction space containing a fluid, such as the combustion gases, is characterized in that an air-fuel mixture is injected into the reaction space at a rate different from that in the reaction space differs located fluid.
  • the velocity is set such that vortices form at the forming interface between the fuel or air-fuel mixture and the fluid surrounding it.
  • the eddies that form can be characterized in particular by the fact that the axes of the vertebrae are perpendicular to the propagation direction of the air-fuel mixture are. This distinguishes them from the vortexes that arise in the premix combustion systems already mentioned, in which an air-fuel mixture is twisted.
  • the axes of the vortex which primarily arise as a result of the twisting of the air-fuel mixture, lie parallel to the propagation direction of the air-fuel mixture.
  • recirculation vortices also form whose axes are perpendicular to the propagation direction of the air-fuel mixture.
  • the vortices arising in connection with the present invention are characterized in that no vortices with axes parallel to the propagation direction of the air-fuel mixture occur.
  • An advantage of the present invention is that a complex twisting of the air-fuel mixture is not required, but nevertheless a mixing of air and fuel by turbulence is achieved.
  • the recirculation also causes mixing of the air-fuel mixture with the hot combustion gas produced during combustion. This stabilizes the burner since it achieves continuous ignition.
  • the air-fuel mixture may preferably be formed by, in a premix jet nozzle, injecting the fuel into an oxidant at a rate higher than that of the oxidant.
  • the fuel can be injected parallel to the flow direction of the oxidizing agent in this.
  • the oxidizing agent in particular air, i. the atmospheric oxygen, serve.
  • pilot fuel for flame stabilization fuel or an air-fuel mixture can be injected as a pilot fuel in the reaction space.
  • the pilot fuel can be injected parallel or anti-parallel offset to the air-fuel mixture in the reaction space.
  • inject the pilot fuel in anti-parallel offset to the air-fuel mixture in the reaction space since the hot gases of the pilot flame are the Vormischstrahlen provided for the hot gas intake available. This reliably stabilizes the combustion reaction of the jets.
  • the discharge of the hot gases from the combustion chamber takes place counter to the Vormischstrahlraum, virtually all of the hot gas is available for the ignition and the stabilization of the premixing jets available.
  • the side of the reaction space at which the pilot burner is located can be cooled with an oxidizing agent, which is then fed to the pilot fuel when injected into the reaction space.
  • the oxidizing agent may be, for example, air.
  • the inventive method in particular the just described principle of anti-parallel injection of pilot fuel and air-fuel mixture, is applicable both for tube combustion chamber systems and for annular combustion chamber systems.
  • the pilot burner used may be a spin-stabilized burner or a jet burner.
  • the antiparallel injection is particularly advantageous when annularly arranged jet burners are used as the main burner.
  • a stabilization of several annular arranged jet flames through a centrally located pilot flame with parallel to the jet flame flow direction causes the main flow direction of the pilot flame of a recirculation flow is directed around the jet flames around, which can lead to disadvantages in the ignition.
  • the reason for this is that not the entire pilot flame is available for igniting and stabilizing the jet flames.
  • the stronger the recirculation the worse the pilot flame can ignite and stabilize.
  • a strong recirculation of the hot combustion gases is absolutely necessary for stable operation of the jet flames in order to allow hot gas to be drawn into the jets.
  • the hot gas intake into the jets ignites the jet flames and ensures continuous combustion.
  • the exit velocity of the air-fuel mixture from the Vormischstrahldüse into the reaction chamber or the combustion chamber is greater than the flame speed.
  • the laminar flame velocity is the rate at which the fresh gas flows into the flame front under laminar flow conditions during flame reactions.
  • the flame front In laminar flames on burners, the flame front is stationary, in turbulent, as occurs in most technical combustion processes, the flame front fluctuates around a central location.
  • the flame speed of the turbulent flame is a multiple of the speed of the laminar flame.
  • the premix burner according to the invention comprises inter alia a reaction space and at least one premix jet nozzle which opens into the reaction space. It is characterized in that the premix jet nozzle is designed such that an air-fuel mixture can be injected into the reaction space at a speed which differs from that of the surrounding fluid. The speed is adjusted so that form at the forming interface between the air-fuel mixture and the surrounding fluid vortex.
  • the premix burner according to the invention offers in Essentially the advantages already described in relation to the inventive method.
  • the air-fuel mixture is injected in the form of an untwisted jet into a reaction space.
  • the jet entry speed may preferably be above the flame speed.
  • the jet entrance velocity may preferably be higher than the velocity of the fluid surrounding the steel.
  • the free jet of each nozzle penetrates into the reaction space and absorbs surrounding fluid by entrainment, primarily already combusted air-fuel mixture. This backflow stabilizes the flame.
  • the speed and extent of the free jet determine the flame length, ensuring that all the fuel burns within the reaction space.
  • the premix jet nozzle of the premix burner according to the invention may preferably comprise a fuel nozzle.
  • the premix jet nozzle can be designed such that the fuel is injected through the fuel nozzle parallel to the flow direction of an oxidant present in the premix jet nozzle, for example compressor air.
  • the premix jet nozzle can be configured such that the fuel nozzle has at least one injection opening which allows the fuel to be injected at an angle between 0 ° and 90 ° to the flow direction of an oxidant present in the premix jet nozzle.
  • the inlet opening of the premix jet nozzle opening into the reaction chamber and / or the opening of the fuel nozzle opening into the premix jet nozzle can have a round, oval, rectangular or square shape or be designed as a slot.
  • the premix jet nozzle may also include an element which adjusts the oxidant entrance velocity allows.
  • This element for adjusting the oxidant inlet velocity may be, for example, a valve or a perforated plate.
  • the premix burner according to the invention may comprise at least one pilot burner.
  • the pilot burner may be a spin-stabilized burner or a jet burner.
  • several premix jet nozzles can be arranged to form one ring or several concentric rings around a respective pilot burner.
  • the premix jet nozzles of the various rings are arranged offset from one another.
  • the pilot burner can in particular also be arranged such that the flow direction of the pilot flame runs anti-parallel to the jet direction of the jet flames.
  • premix jet nozzles can also be arranged in one or more rows. Again, it is advantageous to arrange the premix jet nozzles of different rows offset from each other. In any case, it is additionally possible for the directions of irradiation of the premix jet nozzles to have an angle between 0 ° and 90 ° relative to each other.
  • a pilot burner is arranged between two premix jet nozzles.
  • the premix jet nozzles or the premix jet nozzle can be arranged opposite to the pilot burner and offset therefrom.
  • the premix burner may be surrounded by a fluid channel which is connected to a cooling fluid supply.
  • the cooling fluid supply may in particular be an air supply.
  • the advantage of the present invention lies in the non-twisted injection of an air-fuel mixture via nozzles into the reaction space, wherein an optimal distribution of heat release in the entire reaction space is achieved by a targeted design of the air inlets and the gas mixture within the mixing channels.
  • the resulting better distribution of heat release through individual penetration depths allows a higher combustion stability compared to conventional systems. As a result, combustion oscillations are avoided.
  • the center line 2 indicates the axis of symmetry of the premix burner 1.
  • the premix burner 1 comprises a housing 3, a pilot burner 4, a reaction space 5 and a premix jet nozzle 6.
  • the premix jet nozzle 6 has a Inlet opening 13, which opens into the reaction chamber 5.
  • the pilot burner 4, which in the present embodiment is a spin-stabilized burner, is located in the middle of the rear wall of the premix burner 1. It is surrounded concentrically by a plurality of premix jet nozzles 6, which are likewise located on the rear wall of the premix burner 1.
  • the premix jet nozzle 6 includes a fuel nozzle 8 surrounded by an air intake passage 37.
  • the air inlet channel 37 and the pilot burner 4 open into the reaction space 5.
  • Inside the air inlet channel 37 is a perforated plate 14.
  • the perforated plate 14 serves to regulate the speed of the incoming oxidant, which is compressor air in the present embodiment.
  • the flow direction of the air flowing through the air inlet passage 37 is indicated by arrows 7.
  • the incoming air mixes with the incoming through the fuel nozzle 8 Fuel.
  • Fuel Through the inlet opening 13 of this mixture is injected into the reaction chamber 5.
  • an interface 11 between the gas located in the reaction space 5, in the present embodiment already at least partially burned air-fuel mixture, and the injected air-fuel mixture.
  • This interface 11 arise due to the difference in velocity between the mixture located in the reaction chamber 5 and the injected air-fuel mixture vortices 10. These vortices cause mixing of the injected air-fuel mixture with the gas mixture in the reaction chamber, which contains in particular hot combustion gases, which contribute to the stabilization of the flame.
  • the air is injected through the air inlet passage 37 at a lower velocity into the front part of the premix jet nozzle 6 than the velocity of the fuel injected through the fuel nozzle 8 into the front part of the premix jet nozzle 6.
  • the air is entrained by the fuel, which promotes the mixing of air and fuel due to the so-called Entrainments.
  • the air can in particular be injected parallel to the fuel in the reaction chamber 5.
  • FIG. 2 schematically outlined by the inventive method vortex 10 is sketched.
  • the FIG. 2 shows the direction of propagation 31, synonymous with the main flow direction of the air-fuel mixture in the reaction chamber 5 and, by way of example, a resulting vortex 10.
  • the axis 32 of the vortex 10 is outlined.
  • the vortex axis 32 of the resulting vortex 10 in this case runs perpendicular to the propagation direction 31 of the air-fuel mixture. This distinguishes the vortices arising in the context of the method according to the invention from the vortices, which are primarily caused by twisting.
  • FIG. 3 are outlined for comparison vertebrae 33 and 44, which was caused by twisting.
  • the axis of the vortex 33 generated primarily by the twisting is characterized by the fact that it is largely parallel to the also in FIG. 3 sketched propagation direction 31 of the twisted air-fuel mixture is.
  • the twisting additionally causes the formation of recirculation vortices 44 whose axes are perpendicular to the propagation direction 31 of the air-fuel mixture, as shown in the FIG. 3 is shown schematically.
  • FIG. 4 schematically shows the upper half-plane of a section along the IV-IV sectional plane through the rear wall of the in FIG. 1 premix burner 1.
  • the in FIG. 4 indicated by the reference numeral 26 center line is perpendicular to the in FIG. 1 denoted by reference numeral 2 symmetry axis.
  • the first inlet openings 13 are arranged on a concentric circle around the pilot burner 4.
  • the second inlet openings 15 are also arranged on a circle lying concentrically around the pilot burner 4, wherein the second inlet openings 15 are located at a greater distance from the pilot burner 4 than the first inlet openings 13.
  • the second inlet openings 15 are also arranged offset from the first inlet openings 13 , Alternatively, any number of inlet openings may also be arranged on only one circle around the pilot burner 4.
  • pilot burners may be arranged on a circle whose radius is different from the radius of the circles on which the first and second inlet openings 13 and 15 are arranged.
  • the first inlet openings 13, the second inlet openings 15 and / or the pilot burners can be arranged axially offset from one another.
  • FIGS FIG. 5 described in more detail. Elements which correspond to the elements described in the first embodiment are given the same reference numerals and will not be described again.
  • FIG. 5 shows schematically the cross section through a part of the rear wall of a largely rotationally symmetrical premix burner.
  • a pilot burner 4 which is formed as a spin-stabilized premix burner as in the first embodiment and is surrounded concentrically by Vormischstrahldüsen 6.
  • fuel nozzles 8 are surrounded by air inlet channels 37. With the aid of the inlet openings 13 and 15, fuel and air 16 is injected into the reaction space 5.
  • fuel is first sprayed through the fuel nozzle 8 into the front part of the premix jet nozzles 6 where it is mixed with air 16 from the air inlet channels 37, and then passed on or injected into the reaction space 5.
  • the fuel nozzles 8 are characterized in that they have openings 34 on their sides facing the reaction space 5, which allow the fuel to exit obliquely to the flow direction of the air flowing in through the air inlet ducts 37.
  • the flow direction of the fuel is in FIG. 5 indicated by arrows 9, the flow direction of the air flowing through the air inlet channels 37 is indicated by arrows 7.
  • an angle between the direction of flow of the exiting fuel 9 and the flow direction of the incoming air 7 between 0 ° and 45 ° makes sense.
  • the fuel is injected into the air intake passages 37 at a higher rate than air. This promotes penetration of the fuel into the air flow and thus the mixing of fuel and air.
  • the air-fuel mixture is injected in the present embodiment through first inlet openings 13 parallel to the center line 2 in the reaction chamber 5.
  • the injection of the air-fuel mixture into the reaction space 5 takes place through second inlet openings 15 at an angle to the center line 2.
  • At the interfaces 11 between the injected air-fuel mixture and the air located in the reaction chamber 5 again vortex form 10. These vortices 10th have the properties described in the previous embodiment.
  • FIGS FIG. 6 described in more detail. Elements corresponding to the elements described in the first two embodiments are given the same reference numerals and will not be described again.
  • the premix burner of the third embodiment is characterized by a different arrangement of inlet openings and pilot burners in comparison to the first two embodiments.
  • the FIG. 6 schematically shows one to FIG. 4 alternative arrangement of inlet openings and pilot burners. You can see in FIG. 6 a top view 17 on the back of the reaction chamber 5 viewed from the reaction space. Both the pilot burner. 4 and the inlet openings 18 are arranged concentrically around the center of the rear wall of the reaction space 5. The pilot burner 4 and the inlet openings 18 have the same distance from the center. The four pilot burners shown and the eight in FIG. 6 shown inlet openings 18 are arranged so that the inlet openings 18 are each adjacent to a pilot burner 4.
  • the inlet openings 18 are further distinguished by the fact that they are not round in contrast to the previously described embodiments, but are designed as rectangular slots with rounded corners. Of course, instead of four pilot burners 4 and eight intake ports 18, any number of pilot burners and intake ports may be used.
  • the arrangement described has the advantage that the ignition paths are smaller by the arrangement of a plurality of pilot burners than in the previously described embodiments with a central pilot burner. Another advantage is that the plurality of pilot burners allows flexible control of the burnup of the air-fuel mixture. In addition, the individual flames can be specifically stabilized with the help of the various pilot burners.
  • FIGS FIG. 7 described in more detail. Elements which correspond to the elements described in the first three embodiments are given the same reference numerals and will not be described again.
  • FIG. 7 shows schematically the cross section through a premix burner in the longitudinal direction.
  • the in FIG. 7 The premix burner shown contains in its interior a reaction space 5, which has an outlet 35 directed towards the turbine for the combustion gases.
  • the reaction space 5 is surrounded by a circumferential channel 19.
  • a pilot burner 4 At the end of the reaction space 5 facing away from the output 35 is a pilot burner 4.
  • the output 35 of the reaction chamber 5 is annularly surrounded by inlet openings 13 of Vormischstrahldüsen 6.
  • the inlet openings 13 are the pilot burner 4 opposite lying and arranged offset radially to this.
  • the pilot burner 4 which in the present exemplary embodiment is designed as a spin-stabilized burner, is supplied with pilot fuel by a pilot fuel supply 36.
  • the flow direction of the pilot fuel is indicated by an arrow 20.
  • the pilot fuel is injected via the pilot burner 4 in the reaction chamber 5 and burned there.
  • the pilot burner is also supplied with air from the circulating channel 19. A portion of this air is passed from there to the pilot burner 4, another part of the air passes through the circumferential channel 19 to the inlet openings 13.
  • the direction of flow of the air coming from the compressor is through the arrows 24 marked.
  • the air flowing on to the pilot burner 4 is indicated by the arrows 23.
  • the air entering the premix jet nozzles 6 is indicated by the arrows 25.
  • the air flowing to the pilot burner 4 simultaneously cools the rear side 21 of the reaction space 5.
  • the rear side 21 is exposed to stronger thermal loads compared to conventional burners due to the inlet openings 13 opposite it through which an air-fuel mixture is injected into the reaction space 5 at high speed. A corresponding cooling is therefore advantageous.
  • Each premix jet 6 in FIG. 7 comprises a fuel nozzle 8.
  • the fuel nozzle 8 opens into the front part of the premix jet nozzle 6, which in turn opens into the reaction space 5 via an inlet opening 13.
  • fuel nozzle 8 fuel is passed.
  • the flow direction of the fuel is indicated by arrows 27.
  • the fuel is injected via the fuel nozzle 8 in the front part of the Vormischstrahldüse 6.
  • the fuel is added to the fuel.
  • the direction of flow of the air is indicated by arrows 25.
  • the air used passes from the compressor via the circumferential channel 19 in the Vormischstrahldüse. 6
  • the flow direction of the injected via the inlet opening 13 into the reaction chamber 5 air-fuel mixture is indicated by arrows 29. Due to the high velocity of the injected air-fuel mixture, vortices form at the interface between the injected air-fuel mixture and the surrounding gas. The direction of flow of the vortices is indicated by arrows 30.
  • the vortices cause mixing of the injected air-fuel mixture with the gas located in the reaction space 5. This gas is air and hot gas resulting from the combustion of the pilot flame.
  • the hot gas flowing from the pilot burner towards the turbine supports the formation of these vortices.
  • the entire pilot flame located in the reaction space 5 is available for igniting and stabilizing the jet flames. This is achieved in that the pilot burner 4 and the inlet openings 13 are arranged antiparallel to each other and offset radially.
  • the main flow direction of the fuel or hot gas of the pilot flame is indicated by arrows 22.
  • This main flow direction 22 of the hot gas of the pilot flame promotes the recirculation around the premixed jets. The achieved in this way high degree of mixing in the reaction chamber 5 promotes stable combustion in the reaction chamber, thus preventing unwanted combustion oscillations.
  • FIG. 8 shows as a fifth embodiment schematically the cross section through a premix burner according to the invention in the longitudinal direction.
  • the pilot burner 4 is reset via a cone 43 in the axial direction.
  • Several premix jet nozzles 6 are arranged rotationally symmetrically about the axis of symmetry 2, ie also around the pilot burner 4.
  • the premix burner comprises a reaction space 5 with an outlet 35 leading to a turbine and a plenum 42 which is opposite the outlet 35 and is spatially separated from the reaction space by a top plate 41.
  • plenum 42 In plenum 42 is compressor air, which is injected through the premixing dies 6 in the reaction chamber 5. The flow direction of the air is indicated by arrows 7.
  • a fuel distributor 12 is arranged, which is connected to a stub 39.
  • the fuel distributor 12 is arranged at a larger radius starting from the symmetry axis 2 than the stub 39.
  • the stub 39 can also be arranged at a larger radius than the fuel distributor 12.
  • FIG. 9 schematically shows a section through the in FIG. 8 shown Vormischbrenner along the specified section plane IX-IX.
  • the reaction space 5 which is separated from the plenum 42 by the top plate 41.
  • a premix jet nozzle 6 is introduced, via which an air-fuel mixture is injected into the reaction space 5.
  • plenum 42 is a stub 39, with which fuel can be injected into the premix jet 6.
  • the flow direction of the fuel is indicated by arrows 9.
  • the reaction chamber 5 of the fifth embodiment consists essentially of a cylinder, which are supplied on one side via the top plate 41 air and fuel.
  • flow channels may be mounted in the plenum 42, which allow a guidance and orientation of the air or fuel flow.
  • pilot burners may be present instead of just one pilot burner.
  • One or more pilot flames should guarantee burnup or ignition of the mixture.
  • the air-fuel mixture can via radial slots, as related to FIG. 6 described, enter the reaction space 5.
  • flow channels are attached, with which the flow is directed and in which fuel and air are mixed.
  • various arrangements of the premix jet nozzles 6 and the pilot burner 4 in the top plate 41 are possible.
  • the premix jet nozzles 6 can be mounted around a centrally located pilot burner 4, as in connection with FIG FIG. 4 has been described. These extend in the radial direction only over part of the annular surface, and form two groups, which are offset in the circumferential and in the radial direction.
  • the pilot burner 4 can, as in FIG. 8 be reset by a cone 43 in the axial direction.
  • a flush design can also be realized. Both the inner and the outer ring of the Vormischstrahldüsen 6 have their own fuel supply, so that a gradation of the fuel can take place.
  • the premix jet nozzles 6 may be mounted in a single ring around a central pilot burner 4, as shown in FIG. 8 is shown.
  • This variant is structurally simpler than the first variant.
  • a third variant has three (alternatively four or any other number greater than one) pilot burners 4 and six (alternatively eight or any other number greater than one) premix jet nozzles 6.
  • the premix jet nozzles 6 as well as the pilot burners 4 are mounted on the same circumference, as related to FIG. 6 described.
  • the achsenahe range of the burner is unencumbered in this variant and can thus serve for recirculation or to the backflow of already reacted gas.
  • the fuel injection takes place in principle analogous to the variants already mentioned.
  • a staging of the fuel supply can be done by means of two fuel manifolds, each supplying each second inlet port.
  • the proposed arrangements can be made with simple structural methods, an injection of the fuel into the air. This has advantages over variants in which a large number of circular premix jet nozzles 6 are used.
  • the first variant has the advantage that it is possible to tune the air flow and the fuel quantities through the two rows of premix jet nozzles 6. Furthermore, a radial grading or displacement of the amount of fuel can simply take place, so that optionally the radial fuel distribution can be manipulated.
  • the third variant has the advantage that the arrangement of three (or four or any other number, which is greater than one) pilot burners 4, the ignition paths are smaller than in the first two variants with a central burner.
  • the reaction is spatially distributed by suitable flow guidance.
  • combustion-induced instabilities can be largely avoided.
  • the air-fuel mixture is injected at high speed into the reaction space.
  • the resulting high turbulence and high shear of the flow prevents the oxidation of the mixture via a flame.
  • the reaction or oxidation is thus over the reaction space distributed.
  • the production of nitrogen oxides is minimal due to the high degree of premixing.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP07012207A 2007-06-21 2007-06-21 Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange Withdrawn EP2006606A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP07012207A EP2006606A1 (fr) 2007-06-21 2007-06-21 Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange
EP08774139.3A EP2156095B1 (fr) 2007-06-21 2008-06-19 Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange
US12/663,886 US20100192583A1 (en) 2007-06-21 2008-06-19 Non-rotational stabilization of the flame of a premixing burner
PCT/EP2008/057757 WO2008155373A1 (fr) 2007-06-21 2008-06-19 Stabilisation sans rotation de la flamme d'un brûleur à prémélange

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07012207A EP2006606A1 (fr) 2007-06-21 2007-06-21 Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange

Publications (1)

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EP2006606A1 true EP2006606A1 (fr) 2008-12-24

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EP07012207A Withdrawn EP2006606A1 (fr) 2007-06-21 2007-06-21 Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange
EP08774139.3A Active EP2156095B1 (fr) 2007-06-21 2008-06-19 Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange

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Application Number Title Priority Date Filing Date
EP08774139.3A Active EP2156095B1 (fr) 2007-06-21 2008-06-19 Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange

Country Status (3)

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US (1) US20100192583A1 (fr)
EP (2) EP2006606A1 (fr)
WO (1) WO2008155373A1 (fr)

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JP4955117B1 (ja) * 2011-03-15 2012-06-20 新日鉄エンジニアリング株式会社 炉頂燃焼式熱風炉
US9388985B2 (en) * 2011-07-29 2016-07-12 General Electric Company Premixing apparatus for gas turbine system
US20140123649A1 (en) * 2012-11-07 2014-05-08 Juan E. Portillo Bilbao Acoustic damping system for a combustor of a gas turbine engine
US9599343B2 (en) * 2012-11-28 2017-03-21 General Electric Company Fuel nozzle for use in a turbine engine and method of assembly
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9650959B2 (en) 2013-03-12 2017-05-16 General Electric Company Fuel-air mixing system with mixing chambers of various lengths for gas turbine system
US9765973B2 (en) 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning
US20140338340A1 (en) * 2013-03-12 2014-11-20 General Electric Company System and method for tube level air flow conditioning
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
US9759425B2 (en) 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9347668B2 (en) 2013-03-12 2016-05-24 General Electric Company End cover configuration and assembly
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9366439B2 (en) 2013-03-12 2016-06-14 General Electric Company Combustor end cover with fuel plenums
US20180230956A1 (en) * 2015-08-24 2018-08-16 Siemens Aktiengesellschaft Method and apparatus with arrangement of fuel ejection orifices configured for mitigating combustion dynamics in a combustion turbine engine

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Also Published As

Publication number Publication date
EP2156095B1 (fr) 2016-08-03
EP2156095A1 (fr) 2010-02-24
WO2008155373A1 (fr) 2008-12-24
US20100192583A1 (en) 2010-08-05

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