EP2156095B1 - 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

Info

Publication number
EP2156095B1
EP2156095B1 EP08774139.3A EP08774139A EP2156095B1 EP 2156095 B1 EP2156095 B1 EP 2156095B1 EP 08774139 A EP08774139 A EP 08774139A EP 2156095 B1 EP2156095 B1 EP 2156095B1
Authority
EP
European Patent Office
Prior art keywords
air
fuel
pilot
burner
premix
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.)
Active
Application number
EP08774139.3A
Other languages
German (de)
English (en)
Other versions
EP2156095A1 (fr
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
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 EP08774139.3A priority Critical patent/EP2156095B1/fr
Publication of EP2156095A1 publication Critical patent/EP2156095A1/fr
Application granted granted Critical
Publication of EP2156095B1 publication Critical patent/EP2156095B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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.
  • a method with the features of the preamble of claim 1 is made US 4262482 known.
  • 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 inventive method for stabilizing the flame of a premix burner which comprises a reaction space containing a fluid, such as the combustion gases, wherein an air-fuel mixture is injected at a rate in the reaction space, which differs from that of the fluid located in the reaction space.
  • the speed is set in such a way that vortices form at the forming interface between the fuel or the 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 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 injected parallel to the flow direction of the oxidizing agent in 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.
  • 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. 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. Stabilizing a plurality of annularly arranged jet flames through a centrally arranged pilot flame with a flow direction parallel to the jet flames results in the main flow direction of the pilot flame being directed counter to a recirculation flow around the jet flames, which can lead to disadvantages during 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 comprises inter alia a reaction space and at least one premix jet nozzle which opens into the reaction space.
  • 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 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 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 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 comprise an element which allows adjustment of the oxidant entrance velocity.
  • This element for adjusting the oxidant inlet velocity may be, for example, a valve or a perforated plate.
  • the premix burner may include 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.
  • 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 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.
  • the inlet opening 13 of this mixture is injected into the reaction chamber 5.
  • an interface 11 between the gas located in the reaction chamber 5, in the present embodiment already at least partially burned air-fuel mixture, and the injected air-fuel mixture is formed.
  • 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.
  • 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 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.
  • 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 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 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.
  • vortices 10 form 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 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 that in the first three Embodiments described correspond elements are provided with 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 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 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 in the longitudinal direction.
  • the symmetry axis 2 the housing 3 of the premix burner, a premixing jet 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.
  • 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 in the reaction space. 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 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 distributed over the reaction space.
  • the production of nitrogen oxides is minimal due to the high degree of premixing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Claims (6)

  1. Procédé de stabilisation de la flamme d'un brûleur ( 1 ) à prémélange, qui comprend un espace ( 5 ) de réaction contenant un fluide, dans lequel on pulvérise un mélange d'air et de combustible dans l'espace ( 5 ) de réaction à une vitesse qui se distingue de celle du fluide se trouvant dans l'espace ( 5 ) de réaction, le mélange d'air et de combustible étant pulvérisé dans l'espace ( 5 ) de réaction sous la forme d'un jet non tourbillonnant, dans lequel on pulvérise un combustible ou un mélange d'air et de combustible comme combustible pilote par un brûleur ( 4 ) pilote dans l'espace ( 5 ) de réaction et dans lequel on pulvérise le combustible pilote dans l'espace de réaction de manière décalée parallèlement ou anti-parallèlement au mélange d'air et de combustible, caractérisé en ce que la vitesse est réglée de manière à former, sur la surface ( 11 ) limite se formant entre le mélange d'air et de combustible et le fluide environnant, des tourbillons ( 10 ) en raison de la différence de vitesse établie entre le mélange se trouvant dans l'espace ( 5 ) de réaction et le mélange d'air et de combustible pulvérisé.
  2. Procédé suivant la revendication 1,
    caractérisé en ce que les axes ( 32 ) des tourbillons ( 10 ) qui se forment sont perpendiculaires à la direction ( 31 ) de propagation du mélange d'air et de combustible.
  3. Procédé suivant la revendication 1 ou 2,
    caractérisé en ce que l'on forme le mélange d'air et de combustible en pulvérisant, dans une buse ( 6 ) de jet de prémélange, le combustible dans un agent d'oxydation à une vitesse qui est plus grande que celle de l'agent d'oxydation.
  4. Procédé suivant la revendication 3,
    caractérisé en ce que l'on pulvérise le combustible dans l'agent d'oxydation parallèlement à la direction d'écoulement de ce dernier.
  5. Procédé suivant l'une des revendications précédentes,
    caractérisé en ce que l'on refroidit le côté de la chambre ( 5 ) de réaction où se trouve le brûleur ( 4 ) pilote par un agent d'oxydation, que l'on envoie ensuite au combustible pilote lors de la pulvérisation dans la chambre ( 5 ) de réaction.
  6. Procédé suivant l'une des revendications 3 à 5,
    caractérisé en ce que l'agent d'oxydation est de l'air.
EP08774139.3A 2007-06-21 2008-06-19 Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange Active EP2156095B1 (fr)

Priority Applications (1)

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

Applications Claiming Priority (3)

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

Publications (2)

Publication Number Publication Date
EP2156095A1 EP2156095A1 (fr) 2010-02-24
EP2156095B1 true EP2156095B1 (fr) 2016-08-03

Family

ID=39060220

Family Applications (2)

Application Number Title Priority Date Filing Date
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

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP07012207A Withdrawn EP2006606A1 (fr) 2007-06-21 2007-06-21 Stabilisation sans tourbillonner 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)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2078898A1 (fr) * 2008-01-11 2009-07-15 Siemens Aktiengesellschaft Brûleur et procédé pour réduire des oscillations de flammes autoinduites
FR2934727B1 (fr) 2008-08-04 2010-08-13 Excem Procede de transmission pseudo-differentiel utilisant des variables electriques modales
US8834074B2 (en) * 2010-10-29 2014-09-16 General Electric Company Back mixing device for pneumatic conveying systems
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
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9347668B2 (en) 2013-03-12 2016-05-24 General Electric Company End cover configuration and assembly
US9765973B2 (en) 2013-03-12 2017-09-19 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
US9366439B2 (en) 2013-03-12 2016-06-14 General Electric Company Combustor end cover with fuel plenums
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
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
US20140338340A1 (en) * 2013-03-12 2014-11-20 General Electric Company System and method for tube level air flow conditioning
WO2014143239A1 (fr) * 2013-03-13 2014-09-18 Rolls-Royce Canada, Ltd. Brûleur à flamme azimutale inclinée
EP3325886B1 (fr) * 2015-08-24 2020-01-08 Siemens Aktiengesellschaft Appareil dotés d'agencement d'orifices d'éjection de carburant configuré pour atténuer une dynamique de combustion dans un moteur à turbine à combustion

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3788065A (en) * 1970-10-26 1974-01-29 United Aircraft Corp Annular combustion chamber for dissimilar fluids in swirling flow relationship
US4179881A (en) * 1973-02-28 1979-12-25 United Technologies Corporation Premix combustor assembly
US4262482A (en) * 1977-11-17 1981-04-21 Roffe Gerald A Apparatus for the premixed gas phase combustion of liquid fuels
CH671449A5 (fr) * 1986-07-08 1989-08-31 Bbc Brown Boveri & Cie
US4863371A (en) * 1988-06-03 1989-09-05 Union Carbide Corporation Low NOx high efficiency combustion process
US4928481A (en) * 1988-07-13 1990-05-29 Prutech Ii Staged low NOx premix gas turbine combustor
JP2713627B2 (ja) * 1989-03-20 1998-02-16 株式会社日立製作所 ガスタービン燃焼器、これを備えているガスタービン設備、及びこの燃焼方法
GB9023004D0 (en) * 1990-10-23 1990-12-05 Rolls Royce Plc A gas turbine engine combustion chamber and a method of operating a gas turbine engine combustion chamber
US5186617A (en) * 1991-11-06 1993-02-16 Praxair Technology, Inc. Recirculation and plug flow combustion method
US6672862B2 (en) * 2000-03-24 2004-01-06 North American Manufacturing Company Premix burner with integral mixers and supplementary burner system
US6786047B2 (en) * 2002-09-17 2004-09-07 Siemens Westinghouse Power Corporation Flashback resistant pre-mix burner for a gas turbine combustor
DE10254664B3 (de) * 2002-11-23 2004-03-04 Buderus Heiztechnik Gmbh Brenner für flüssige Brennstoffe
DE10257275A1 (de) * 2002-12-07 2004-06-24 Alstom Technology Ltd Verfahren und Vorrichtung zur Beeinflussung thermoakustischer Schwingungen in Verbrennungssystemen
US20080096146A1 (en) * 2006-10-24 2008-04-24 Xianming Jimmy Li Low NOx staged fuel injection burner for creating plug flow

Also Published As

Publication number Publication date
WO2008155373A1 (fr) 2008-12-24
US20100192583A1 (en) 2010-08-05
EP2156095A1 (fr) 2010-02-24
EP2006606A1 (fr) 2008-12-24

Similar Documents

Publication Publication Date Title
EP2156095B1 (fr) Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange
DE69834621T2 (de) Gasturbinenbrenner mit niedrigem NOx Ausstoss
DE60007946T2 (de) Eine Brennkammer
EP0029619B1 (fr) Chambre de combustion pour turbine à gaz avec éléments de prévaporisation/prémélange
EP1645802B1 (fr) Brûleur à prémélange
DE102005024062B4 (de) Brennerrohr und Verfahren zum Mischen von Luft und Gas in einem Gasturbinentriebwerk
DE60032663T2 (de) Verkokungbeständige Kraftstoffeinspritzdüse
DE102005023536B4 (de) Vormischbrenner mit aufprallgekühltem Mittelkörper und Verfahren zum Kühlen des Mittelkörpers
DE102006003577B4 (de) Brennkammer einer Gasturbine
DE3222347C2 (fr)
EP0675322B1 (fr) Brûleur à prémélange
DE69919764T2 (de) Brennkammer
DE102014117621A1 (de) Brennstoffinjektor mit Vormisch-Pilotdüse
DE10050248A1 (de) Brenner
CH697862A2 (de) Brenner mit Vormischer mit radial gestuften Strömungskanälen und Verfahren zum Mischen von Luft und Gas in einem Brenner einer Gasturbine.
EP0924470B1 (fr) Chambre de combustion à prémélange pour turbine à gaz
DE102009003572A1 (de) Brennkammerkappe mit Kranzmischöffnungen
DE102010017778A1 (de) Vorrichtung zur Brennstoffeinspritzung bei einer Turbine
DE102008037374A1 (de) Torusförmiger Ringverteiler für die sekundäre Brennstoffdüse einer DLN-Gasturbine
DE112014001594B4 (de) Brennkammer und Gasturbine
DE102011000589A1 (de) Axial gestufte Vormischbrennkammer
EP1217297A1 (fr) Brûleur à stabilité de flamme élévée
CH703230B1 (de) Gasturbine mit einstufiger Brennstoffeinspritzung.
EP1235033B1 (fr) Chambre de combustion annulaire et méthode d'opération de la dite chambre
EP2171354B1 (fr) Brûleur

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20091109

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

RIN1 Information on inventor provided before grant (corrected)

Inventor name: FLOHR, PATRICK RONALD

Inventor name: SCHILDMACHER, KAI-UWE

Inventor name: VAN KAMPEN, JAAP

Inventor name: SCHNEIDER, THOMAS ALEXIS

Inventor name: MEISL, JUERGEN

Inventor name: LENZE, MARTIN

Inventor name: REMLINGER, UWE

Inventor name: PIXNER, PAUL

Inventor name: HASE, MATTHIAS

Inventor name: CANO WOLFF, MARIANO

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

17Q First examination report despatched

Effective date: 20150409

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160218

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 817584

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160815

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502008014462

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20160803

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161103

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161203

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161205

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161104

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502008014462

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161103

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20170504

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20170627

Year of fee payment: 10

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

Ref country code: CH

Ref legal event code: PCOW

Free format text: NEW ADDRESS: WERNER-VON-SIEMENS-STRASSE 1, 80333 MUENCHEN (DE)

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20170619

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20180228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170619

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170630

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170619

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170619

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170630

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170630

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 817584

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170619

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170619

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180619

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20080619

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160803

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160803

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502008014462

Country of ref document: DE

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG, DE

Free format text: FORMER OWNER: SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20230627

Year of fee payment: 16

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20231222