WO2008155373A1 - Stabilisation sans rotation de la flamme d'un brûleur à prémélange - Google Patents

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

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Publication number
WO2008155373A1
WO2008155373A1 PCT/EP2008/057757 EP2008057757W WO2008155373A1 WO 2008155373 A1 WO2008155373 A1 WO 2008155373A1 EP 2008057757 W EP2008057757 W EP 2008057757W WO 2008155373 A1 WO2008155373 A1 WO 2008155373A1
Authority
WO
WIPO (PCT)
Prior art keywords
premix
burner
fuel
air
reaction space
Prior art date
Application number
PCT/EP2008/057757
Other languages
German (de)
English (en)
Inventor
Mariano Cano Wolff
Patrick Ronald Flohr
Matthias Hase
Martin Lenze
Jürgen MEISL
Paul Pixner
Uwe Remlinger
Kai-Uwe Schildmacher
Thomas Alexis Schneider
Jaap Van Kampen
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to US12/663,886 priority Critical patent/US20100192583A1/en
Priority to EP08774139.3A priority patent/EP2156095B1/fr
Publication of WO2008155373A1 publication Critical patent/WO2008155373A1/fr

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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.
  • a system or method whereby combustion oscillations are completely avoided is not yet known.
  • premix combustion systems in which an air-fuel mixture is twisted and the flame is stabilized by recirculation zones.
  • fuel is injected into an air stream and both are twisted, for example with the help of so-called swirl blades. After a certain distance traveled by this mixture, it burns downstream of the burner in a flame front, which is spatially stabilized by the flow field.
  • all of these systems are characterized by the fact that there is a distinct and spatially limited flame. Therefore, combustion oscillations or flame instabilities inevitably occur at certain operating points. These can lead to extreme mechanical loads on the combustion chamber structure and should therefore be avoided or at least reduced.
  • 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 in that the axes of the vertebrae are perpendicular to the propagation direction of the air-fuel mixture. 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 contrast to the eddies resulting from a twist, 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 pilot fuel can be injected parallel or anti-parallel offset to the air-fuel mixture in the reaction space.
  • the pilot fuel is injected into the reaction space in anti-parallel offset from the air-fuel mixture, the hot gases of the pilot flame are thus made available to the premix jets for the hot gas intake. This reliably stabilizes the combustion reaction of the jets.
  • the exit of the hot gases from the combustion chamber against the Vorischstrahlraum takes place, is virtually all the hot gas for the ignition and the stabilization of Vormischstrahlen available.
  • 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 parallel to
  • Flow direction of the oxidant are injected into this.
  • the oxidizing agent in particular air, i. the atmospheric oxygen, serve.
  • 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.
  • Pilot fuel and air-fuel mixture is applicable to both tube combustion systems and annular combustion chamber systems. It may be in the used Pilot burner to a swirl-stabilized burner or act a jet burner.
  • the antiparallel injection is particularly advantageous when annularly arranged jet burners are used as the main burner.
  • a stabilization of a plurality of annularly arranged jet flames through a centrally arranged pilot flame with parallel to the jet flame flow direction causes the main flow direction of the pilot flame of a recirculation flow to the
  • Radiation flames is directed opposite, which can lead to disadvantages when igniting.
  • the reason for this is that not the entire pilot flame is available for igniting and stabilizing the jet flames.
  • 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 in the reaction chamber or the combustion chamber is greater than that
  • 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. He is characterized by in that the premix jet nozzle is designed in such a way 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 at the forming
  • the premix burner according to the invention essentially offers the advantages already described in relation to the method according to the invention.
  • 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 thereby absorbs entrained fluid, 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 configured such that the fuel through the fuel nozzle parallel to the flow direction of an oxidant present in the premix jet nozzle, for example
  • 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 comprise an element which allows adjustment of the oxidant entrance velocity. In this element for setting 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.
  • a plurality of premix jet nozzles are arranged to form a plurality of concentric rings around a pilot burner, it is advantageous if the premix jet nozzles of the various rings are arranged offset from one another.
  • the pilot burner can in particular also be arranged so that the
  • 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.
  • 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-injured injection of an air-fuel mixture via nozzles into the reaction space, wherein an optimal distribution of the 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.
  • FIG 2 shows schematically the propagation direction of the air-fuel mixture and a thereby resulting
  • FIG. 3 shows schematically vortices caused by twisting.
  • FIG 4 schematically shows the arrangement of the inlet openings around the pilot burner on the rear wall of a premix burner according to the invention.
  • FIG 5 shows a second embodiment schematically the
  • FIG. 6 schematically shows the arrangement of inlet openings and pilot burners on the
  • Rear wall of a premix burner according to the invention. 7 shows as a fourth embodiment schematically the
  • Premix burner in the longitudinal direction. 8 shows a schematic illustration of the fifth exemplary embodiment
  • Premix burner in the longitudinal direction. 9 shows schematically a section through a premix burner according to the invention along the sectional plane IX-IX shown in FIG.
  • the premix burner 1 shows schematically the cross section through part of the rear wall of a substantially rotationally symmetrical premix burner 1.
  • the center line 2 denotes the symmetry axis 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
  • Premix jet nozzle 6 has an inlet opening 13, which opens into the reaction space 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.
  • Air inlet channel 37 and the pilot burner 4 open into the reaction chamber 5. Inside the air inlet channel 37 is a perforated plate 14.
  • the perforated plate 14 is used for regulation the velocity of the incoming oxidant, which in the present embodiment is compressor air.
  • the flow direction of the air flowing through the air inlet passage 37 is indicated by arrows 7.
  • the incoming air mixes with the fuel flowing in through the fuel nozzle 8. Through the inlet opening 13 of this mixture is injected into the reaction chamber 5.
  • Reaction space 5 forms an interface 11 between the located in the reaction chamber 5 gas, in the present embodiment, at least partially combusted air-fuel mixture, and the injected air-fuel mixture.
  • 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 shows the direction of propagation 31, which is equivalent to the main flow direction, of the air-fuel mixture in the reaction space 5 and, by way of example, a vortex 10 formed in this case.
  • 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.
  • vortices 33 and 44 are outlined, which were caused by twisting.
  • the axis of the vortex 33 generated primarily by the twisting is distinguished by the fact that it is largely parallel to the direction of propagation 31 of the twisted air-fuel mixture, which is also sketched in FIG.
  • 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 schematically in FIG.
  • FIG. 4 shows schematically the upper
  • the first inlet openings 13 are arranged on a concentric circle around the pilot burner 4.
  • the second inlet openings 15 are also on a circle lying concentrically around the pilot burner 4 arranged, 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.
  • 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.
  • first inlet openings 13, the second inlet openings 15 and / or the pilot burners can be arranged axially offset from one another.
  • FIG. 5 shows schematically the cross section through part of the rear wall of a largely rotationally symmetrical premix burner.
  • 5 shows the axis of symmetry 2 running through the center of the premix burner.
  • a pilot burner 4 which, as in the first exemplary embodiment, is designed as a spin-stabilized premix burner and is surrounded concentrically by premix jet nozzles 6.
  • fuel nozzles 8 are of
  • 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 direction of flow of the fuel is indicated by arrows 9 in FIG. 5; the direction of flow of the air flowing through the air inlet channels 37 is indicated by arrows 7.
  • the flow direction of the fuel 9 at the exit through the openings 34 at an angle to the flow direction of the air 7, which flows through the air inlet channels 37 comprises.
  • These angles can be adjusted arbitrarily by a corresponding design of the openings 34.
  • an angle between the flow direction 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 favors a
  • 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 in the reaction chamber 5 by second inlet openings 15 takes place at an angle to the center line 2.
  • Reaction space 5 air again turn vortex 10. These vortices 10 have the properties described in the previous embodiment.
  • 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.
  • FIG. 6 schematically shows an arrangement, which is alternative to FIG. 4, of inlet openings and pilot burners.
  • FIG. 6 shows a top view 17 on the rear side of the reaction space 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 intake ports 18 shown in FIG. 6 are arranged such that the intake ports 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.
  • the premix burner shown in FIG. 7 contains in its interior a reaction space 5 which has an outlet 35 directed toward 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 back 21 is due to the opposite inlet openings 13 through which an air-fuel mixture with high Speed is injected into the reaction chamber 5, exposed to higher thermal loads compared to conventional burners. A corresponding cooling is therefore advantageous.
  • Each premix jet nozzle 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. In the fuel nozzle 8 fuel is passed.
  • 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. There, 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. It supports the from
  • pilot burner in the direction of turbine flowing hot gas the formation of this vortex.
  • 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.
  • FIGS. 8 and 9 further possible variants of the present invention will be described in more detail with reference to FIGS. 8 and 9 as a fifth exemplary embodiment. Elements that correspond to the elements described in the first four embodiments are given the same reference numerals and will not be described again.
  • FIG. 8 shows, as a fifth exemplary embodiment, the cross section through a premix burner according to the invention in the longitudinal direction. It can be seen in FIG 8, inter alia, the symmetry axis 2, the housing 3 of the premix burner, a Vormischstrahldüse 6 and a centrally located pilot burner 4, which is intended to ensure ignition of the air-fuel mixture.
  • the pilot burner 4 is reset via a cone 43 in the axial direction.
  • premix jet nozzles 6 are rotationally symmetric about the symmetry axis 2, i. also around the pilot burner 4, arranged.
  • the premix burner comprises a reaction space 5 with an outlet 35 leading to a turbine, and a plenum 42 facing the exit 35 and from which
  • Reaction space is spatially separated 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 starting from the symmetry axis 2 at a larger radius than the stub 39.
  • the stub 39 can be arranged at a larger radius than the fuel distributor 12.
  • the fuel is injected into the premix jet 6.
  • About the Vormischstrahldüse 6 mixed with the compressor air fuel is injected into the reaction chamber 5 and burned there.
  • the free jet of the resulting flame is indicated by the reference numeral 40.
  • FIG. 9 schematically shows a section through the premix burner shown in FIG. 8 along the sectional plane IX-IX indicated there. You can see in FIG 9 again 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
  • 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 provided in the plenum 42, which allow guidance and alignment 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 described in connection with FIG 6, in the reaction chamber. 5 enter. On the slots flow channels are attached, with which the flow is directed and in which fuel and air are mixed. In this case, 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 described in connection with FIG. 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 may be reset as in FIG 8 via 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.
  • 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 described in connection with FIG.
  • 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.
  • 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

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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)

Abstract

L'invention concerne un procédé de stabilisation de la flamme d'un brûleur à prémélange (1) qui comprend une chambre de réaction (5) contenant un fluide. Le procédé est caractérisé en ce qu'un mélange d'air et de combustible est injecté dans la chambre de réaction (5) avec une vitesse différente de celle du fluide se trouvant dans la chambre de réaction (5). La vitesse est ajustée de telle sorte qu'il se forme des tourbillons (10) à la surface limite (11) se formant entre le mélange d'air et de combustible et le fluide l'entourant. En outre, l'invention concerne un brûleur à prémélange (1) qui comprend une chambre de réaction (5) et au moins une buse à jet de prémélange (6) débouchant dans la chambre de réaction (5). Le brûleur à prémélange (1) est caractérisé en ce qu'un mélange d'air et de combustible peut être injecté dans la chambre de réaction (5) à une vitesse différente de celle du fluide l'entourant, et la vitesse est ajustée de telle sorte qu'il se forme des tourbillons (10) à la surface limite (11) se formant entre le mélange d'air et de combustible et le fluide l'entourant.
PCT/EP2008/057757 2007-06-21 2008-06-19 Stabilisation sans rotation de la flamme d'un brûleur à prémélange WO2008155373A1 (fr)

Priority Applications (2)

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

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP07012207.2 2007-06-21
EP07012207A EP2006606A1 (fr) 2007-06-21 2007-06-21 Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange

Publications (1)

Publication Number Publication Date
WO2008155373A1 true WO2008155373A1 (fr) 2008-12-24

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/057757 WO2008155373A1 (fr) 2007-06-21 2008-06-19 Stabilisation sans rotation de la flamme d'un brûleur à prémélange

Country Status (3)

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

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Also Published As

Publication number Publication date
US20100192583A1 (en) 2010-08-05
EP2156095B1 (fr) 2016-08-03
EP2156095A1 (fr) 2010-02-24
EP2006606A1 (fr) 2008-12-24

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