[go: up one dir, main page]

EP3087323B1 - Injecteur de combustible, brûleur avec un tel injecteur de combustible, et turbine à gaz munie dudit brûleur - Google Patents

Injecteur de combustible, brûleur avec un tel injecteur de combustible, et turbine à gaz munie dudit brûleur Download PDF

Info

Publication number
EP3087323B1
EP3087323B1 EP15741750.2A EP15741750A EP3087323B1 EP 3087323 B1 EP3087323 B1 EP 3087323B1 EP 15741750 A EP15741750 A EP 15741750A EP 3087323 B1 EP3087323 B1 EP 3087323B1
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
vortex generator
vortex
flow
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
EP15741750.2A
Other languages
German (de)
English (en)
Other versions
EP3087323A1 (fr
Inventor
Christian Beck
Stefan Dederichs
Olga Deiss
Berthold Köstlin
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
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of EP3087323A1 publication Critical patent/EP3087323A1/fr
Application granted granted Critical
Publication of EP3087323B1 publication Critical patent/EP3087323B1/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
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • 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
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the invention relates to a burner with a premixing chamber and with a fuel nozzle for two fuels. Furthermore, the invention relates to a gas turbine with such a burner. Furthermore, the invention relates to a fuel nozzle for two fuels.
  • a burner In gas turbines, a burner is typically provided with a premixing chamber in which a particular gaseous fuel is mixed with air to subsequently burn the resulting mixture.
  • a particular gaseous fuel is mixed with air to subsequently burn the resulting mixture.
  • the efficiency of the gas turbine and the formation of undesirable emission products, in particular nitrogen oxides are essentially dependent on the mixing of the fuel with the air.
  • the natural gas is often injected in the radial direction, that is perpendicular to the flow direction of the air (so-called jet-in-crossflow method).
  • jet-in-crossflow method a suitable mixing of natural gas and air can be achieved.
  • a combustion chamber which consists essentially of a first and downstream in the flow direction second stage.
  • a mixer for forming a fuel / air mixture and the outflow side of the mixer vortex generators are available. These serve, in particular, for the twisting of hot air, which is then conducted into a premixing zone for mixing with fuel and subsequently into a combustion zone of the second stage.
  • the US 2002/014078 discloses, for example, a burner with a fuel lance with radially aligned fuel openings and tangentially, ie, circumferentially aligned outlet openings, between which a swirl device for directional twisting of the flow is arranged.
  • a fuel nozzle for two fuels comprising an inner tube with radially aligned outlet openings for a first fuel and with an outer tube surrounding the inner tube with axially aligned outlet openings for a second fuel.
  • a hydrogen-containing fuel gas in the flow direction of the air via the axial outlet openings.
  • a so-called Lobe mixer is provided.
  • the second fuel for example natural gas is then injected via the radial outlet openings.
  • the object of the invention is to provide an improved burner which is particularly suitable for operation with multiple fuels. Furthermore, a mixture formation in the burner should be improved. Furthermore, a gas turbine to be specified with such a burner. In addition, an improved fuel nozzle is to be specified, which is particularly suitable for multiple fuels.
  • a burner comprises a plurality of premixing chambers each having a fuel nozzle for two fuels, wherein the fuel nozzle has a extending in a flow direction fuel lance, in which a number of first outlet openings for a first fuel is introduced, and the fuel lance of an outer tube is surrounded, with at least a second outlet opening for a second fuel, the first outlet openings are radially aligned and the second outlet opening axially, wherein between the fuel lance and inside of the premixing chamber, a flow cross-section is formed and wherein a number of vortex generators is arranged on the fuel lance which reduce a flow cross section oriented transverse to the flow direction, wherein at least one vortex generator upstream of the first outlet openings and downstream of the second outlet opening is arranged and the premixing chamber has a cross section and an end and the distance of the first outlet openings from the end of the premixing chamber is at least three times as large as the cross section of the premixing chamber.
  • the air, the first fuel and the second fuel are hereinafter referred to generally as gases.
  • the application is in principle but not limited to gaseous media. Furthermore, the application is not limited to the following gases, namely natural gas, hydrogen and air.
  • the fuel lance is advantageously used for the injection of natural gas, which is provided by means of the radial outlet openings for mixing.
  • radial is understood to mean that the fuel lance extends in the direction of flow, that is to say axially, and radially has a jacket surface in which suitable, for example round, openings are made.
  • outlet openings are preferably distributed in a common position in the axial direction and uniformly in the circumferential direction of the fuel lance.
  • outlet openings are arranged at several positions in the axial direction one behind the other.
  • the outer tube surrounds the fuel lance in the axial direction preferably only partially, that is, the fuel lance is in the flow direction.
  • the radial outlet openings are covered by the outer tube or there are both covered, as not covered outlet openings available.
  • the outer tube is preferably used for axial injection of the second fuel, for example hydrogen or a hydrogen-containing fuel gas. Due to the axial injection, it is in particular possible to inject a fuel by means of a larger volume flow compared to natural gas. Advantageously, furthermore, an air-side pressure loss, as may possibly occur in the case of radial injection, can be reduced or avoided altogether.
  • the second fuel for example hydrogen or a hydrogen-containing fuel gas. Due to the axial injection, it is in particular possible to inject a fuel by means of a larger volume flow compared to natural gas.
  • an air-side pressure loss as may possibly occur in the case of radial injection, can be reduced or avoided altogether.
  • At least one vortex generator is provided, that is to say arranged in the burner.
  • the mixing can be achieved, in particular, by reducing a flow cross-section of at least one of the gases at at least one position along the flow direction.
  • the air flows in the flow direction at a first position, a first surface, which is oriented transversely, that is substantially perpendicular to the flow direction.
  • the first surface corresponds to the flow cross-section at the first position.
  • a vortex generator is now arranged at a second position downstream of the first position, which opposes the air with an additional blocking surface, whereby the second surface through which the air flows at the second position is smaller than the first surface.
  • the flow area is smaller at the second position than at the first position.
  • the vortex generator is a surface which is set in relation to the flow direction. It points the vortex generator suitably has a contour, preferably at least one edge, for generating turbulence.
  • At least one vortex generator is mounted on the fuel lance.
  • the vortex generator when using the vortex generator for turbulence of the fuel injected by the fuel lance first fuel advantageously the vortex generator is adapted to the requirements of this fuel.
  • the vortex generator When exchanging the first fuel and thus possibly changed requirements for mixing with air, it is thereby possible in particular to replace the turbulizer by exchanging the fuel lance at the same time.
  • At least one vortex generator is arranged upstream of the radial outlet openings and downstream of the axial outlet opening. This makes it possible, in particular, to achieve turbulence of the air and / or of the second fuel without the vortex generator directly influencing the flow of the first fuel. It is understood by direct influence that the respective vortex generator is affected by the gas influenced by this.
  • the premixing chamber of the burner according to the invention has a cross section and an end, wherein with a view to a good mixing of fuel and air, the distance of the first outlet openings from the end of the premixing chamber at least three times as large as the cross section of the premixing chamber. This ensures that the length of the route, on which fuel and air can mix, is sufficiently large.
  • the fuel lance and the outer tube are arranged concentrically.
  • the fuel lance and the outer tube are designed substantially cylindrical and have a common longitudinal axis.
  • the outer tube is preferably formed as a tube with an annular profile transverse to the longitudinal axis.
  • the longitudinal axis extends in the flow direction.
  • the second fuel and the air flow in each case in the flow direction.
  • the air and the second fuel are flowed in or injected axially.
  • the first fuel is preferably injected radially.
  • At least one vortex generator is wedge-shaped. It is understood by wedge-shaped that the vortex generator has a surface which extends obliquely to the axial direction and in particular obliquely to the flow direction.
  • the surface is rectangular.
  • the surface is triangular, with one side of the triangle extending transversely to the flow direction. The two remaining sides either run in or against the flow direction to a tip of the triangle.
  • wedge-shaped is also understood to mean tetrahedral.
  • the vortex generator is possibly composed as a solid body or of different surface elements or formed in several parts. It is essential that by means of the vortex generator of the flow cross-section in the flow direction is adjustable, in particular to produce turbulence in the flow of the gas flowing the vortex generator. It will Under adjustable in particular understood that the exact design and orientation of the Wirbellys is determined during its manufacture and assembly.
  • At least one turbulizer is attached to the outer tube.
  • the vortex generator is either externally mounted on the outer tube, in particular for turbulence of the air flowing there suitably along, or inside the outer tube, for turbulence of the second fuel preferably flowing therealong.
  • the premixing chamber comprises an inner wall, on which at least one vortex generator is mounted. In this way, in particular, a turbulence substantially independent of the fuel nozzle can be achieved.
  • At least one vortex generator is arranged downstream of the radial outlet openings.
  • at least one vortex generator is arranged downstream of any outlet openings, as a result of which this vortex generator influences in particular each of the inflowing gases, that is, in particular, swirls.
  • At least one vortex generator is arranged downstream of the axial outlet opening and upstream of the radial outlet openings and on the fuel lance.
  • a plurality of vortex generators are arranged in the axial direction at different positions on the fuel lance.
  • a plurality of vortex generators in groups, for example in series, in axial Direction one behind the other or offset; or in a plane, that is, in particular both side by side (for example, in the circumferential direction) and in succession. It is also possible that several vortex generators advantageously have different geometries and / or dimensions.
  • a plurality of vortex generators are arranged at approximately the same position in the axial direction and along a circumferential direction with respect to the longitudinal axis.
  • a plurality of vortex generators are arranged on the circumference of the outer tube such that all lying in the direction of rotation between adjacent vortex generators distances are equal.
  • a number of vortex generators are mounted on the outer tube for entangling the air and for improved mixing with hydrogen injected axially downstream therefrom.
  • vortex generators are mounted downstream of the radial outlet openings.
  • the outer tube has an end region which is designed as a lobe mixer and comprises a number of lamellae. These extend in particular in the flow direction and as radially formed folds. This results transversely to the longitudinal axis, in particular a star-shaped cross section (or a star-shaped profile). In the circumferential direction, a gap is formed between each two slats through which in particular the flow cross-section of the air downstream is advantageously increased.
  • the lamellae each have a vertex in the radial direction, which extends substantially in the axial direction. This means in particular that the radial distance between vertex and longitudinal axis in the flow direction is substantially constant.
  • the outer tube has an outer sheath and the vertexes of the lamellae are substantially aligned with the outer sheath. It is possible that a slight inclination or slope is provided in the axial direction.
  • a mixing of the second fuel with air is advantageously achieved in that it follows a flow in the flow direction, which breaks off at the end of the end region.
  • the star-shaped cross section of the end region has at the end a contour line which is elongated with respect to the outer tube (and correspondingly star-shaped). This advantageously provides a larger edge in comparison to the circumference of the outer tube for stalling.
  • the end region is twisted or twisted in such a way that the lamellae and thus also the apices extend in a spiral around the longitudinal axis. This makes it possible to additionally twist the air flowing along the lamellae and thus to achieve improved mixing.
  • a number of lamellae are additionally designed as vortex generators.
  • these lamellae are in particular formed such that their vertices are formed as inclined in the axial direction surfaces.
  • the distance from the apex of a lamella to the longitudinal axis changes in the direction of flow.
  • the distance in the flow direction is continuously increased.
  • an employed surface is provided with an edge in such a way that by means of this a turbulence in the manner of a vortex generator can be achieved.
  • At least one vortex generator is arranged in an intermediate space between two lamellae.
  • the space mentioned here corresponds to the already mentioned above space between two adjacent in the direction of rotation of the outer tube fins.
  • this arrangement it is possible by this arrangement to produce vortex generators with comparatively large side surfaces, that is, in comparison to, for example, arranged on an annular tube without lobe mixer vortex generators. As a result, the turbulence can be advantageously influenced.
  • a combination of the vortex generators mentioned above with one of the above-mentioned concepts for the injection of the second fuel allows an improved mixture of the gases involved.
  • the mixture is improved both with simultaneous injection of first and second fuel (for example natural gas and hydrogen) and in a single operation, that is to say when injecting only one fuel (for example natural gas or hydrogen).
  • a gas turbine comprises a burner having one or more of the above features, thereby providing the above-mentioned advantages.
  • a gas turbine is in particular more efficient and advantageously has a lower emission of pollutants.
  • a fuel nozzle according to the invention for two fuels has a fuel lance extending in a flow direction.
  • a number of first outlet openings for a first fuel is introduced.
  • the fuel lance is surrounded by an outer tube with at least one second outlet opening for a second fuel, wherein the first outlet openings are radially aligned and the second outlet opening axially, wherein a number of vortex generators is arranged on the fuel lance.
  • At least one vortex generator is arranged upstream of the first outlet openings and downstream of the second outlet opening.
  • the burner 2 in this case comprises a premixing chamber 6, which is followed by a combustion chamber 8 in the flow direction S.
  • two fuels and air are injected into the premixing chamber 6 during operation.
  • a fuel nozzle 10 which extends in the flow direction S.
  • the air is flown in through a fuel inlet duct 12 surrounding the fuel nozzle 10 in the flow direction S.
  • the fuel nozzle 10 comprises a fuel lance 14 and an outer tube 16 surrounding it, the fuel lance 14 projecting in the flow direction S and with respect to the outer tube 16.
  • the fuel lance 14 and the outer tube 16 are in The embodiment shown here is designed substantially cylindrical, that is, these have transversely to the flow direction S a circular or annular cross-section.
  • the fuel lance 14 and the outer tube 16 are arranged concentrically and accordingly have a common longitudinal axis L, which extends in the flow direction S.
  • the fuel lance 14 has a number of radial outlet openings 18. These are circular in the embodiment shown here and arranged in a common position in the axial direction, ie in the flow direction S. In this case, the outlet openings 18 are distributed in a circumferential direction U and in particular uniformly.
  • the radial outlet openings 18 are used in particular for the injection of the first fuel, for example natural gas.
  • the outer tube 16 has a larger diameter than the fuel lance 14, whereby in the axial direction a particular annular, axial outlet opening 20 is realized.
  • the second fuel is injected into the premixing chamber 6. That is, the second fuel in particular flows around the fuel lance 14.
  • FIG. 1 is mounted on the fuel lance 14 a number of vortex generators 22. These are arranged downstream of the axial outlet opening 20 and upstream of the radial outlet openings 18.
  • the vortex generators 22 are of tetrahedral design in the exemplary embodiment shown here (cf. FIG. 20 ).
  • FIG. 1 shows that the premixing chamber 6 has a cross section 50 and an end 52 and the distance of the first outlet openings 18 from the end 52 of the premixing chamber 6 is at least three times as large as the cross section 50 of the premixing chamber 6.
  • the vortex generators 22 according to FIG. 1 attached internally to the premixing chamber 6.
  • the vortex generators 22 are arranged at a position downstream of the radial outlet openings.
  • the vortex generators 22 each have a respect to the flow direction S salaried surface 24, which is triangular here and counter to the flow direction S to the longitudinal axis L tapers. This arrangement is also referred to as forward directed. In an alternative, not shown embodiment, however, the vortex generators 22 are directed backwards, that is rotated by 180 ° such that the surface 24 in the flow direction S to the longitudinal axis L tapers.
  • a flow cross-section Q is defined, which is changed by the vortex generators 22 in the flow direction S.
  • the flow cross-section Q is defined at a first position P1 by the premixing chamber 6 and the fuel lance 14. At this first position P1, the flow cross-section Q is in particular greater than at a second position P2 at which the vortex generators 22 are arranged in the exemplary embodiment shown here.
  • FIGS. 3 to 17 schematically show further embodiments of a fuel nozzle 14.
  • This show the FIG. 3 . 6 . 9 . 12 and 15 each of the fuel nozzle 14 in a side view and to each of the gases clarified by arrows Inlet direction 28, 30, 32.
  • the first fuel in the inflow direction 28 is flowed in radially and the second fuel and the air are flowed axially in the inflow directions 30, 32.
  • Due to the axial inflow, in particular the general flow direction S is predetermined in the premixing chamber 6, which also essentially follows the first fuel at a sufficient distance from the radial outlet openings 18.
  • FIG. 4 . 7 . 10 . 13 and 16 each show the corresponding fuel lance 14 in front view
  • the FIG. 5 . 8th . 11 . 14 and 17 each show the corresponding fuel lance 14 in a perspective view.
  • the in the 3 to 5 illustrated embodiment of the fuel nozzle 10 includes a number of forward oriented tetrahedral vortex generators 22, which are mounted downstream of the axial outlet opening 20 and upstream of the radial outlet openings 18 on the fuel lance 14.
  • the vortex generators 22 each have a height H which is selected here in such a way that the vortex generator 22 extends further in the radial direction than the outer tube 16. This is particularly evident in FIG FIG. 4 shown. As a result, it is possible, in particular, to supply the vortex generators 22 directly with air and to vortex them.
  • FIGS. 6 to 8 show the fuel nozzle 10 with mounted on the outer tube 16 vortex generators 22. These are oriented here forward and are flown by the air flowing around the outer tube 16. By contrast, the fuel lance 14 has no vortex generators 22.
  • FIGS. 9 to 11 show the fuel nozzle 10 with a designed as a lobe mixer end portion 34.
  • a number of six blades 36 is formed in the end region 34 here. These give a star-shaped cross-section, such as out FIG. 10 becomes clear.
  • FIG. 10 continues to show that the lamellae 36 do not substantially project beyond the outer tube 16 in the radial direction.
  • the lamellae 36 each have a vertex 38 extending in the axial direction and, in particular, are evenly spaced in the circumferential direction U by intermediate spaces 40. At the end 42 of the outer tube 16, the lamellae 36 form a star-shaped contour 44, by which in particular a number of outlet channels 46 is realized.
  • the axial outlet opening 20 therefore comprises six outlet channels 46 in the exemplary embodiment shown here.
  • the vortex generators 22 mounted downstream of the fuel lance 14 may either follow or be offset from one of the exit channels 46 in the flow direction S.
  • two vortex generators 22A are arranged in an imaginary extension of outlet channels 46 and two vortex generators 22B are arranged in an imaginary extension of intermediate spaces 40.
  • FIGS. 12 to 14 show an embodiment in which the outer tube 16 of the fuel nozzle 10 in the end region 34 has a number of four fins 36 here, which are simultaneously designed as a vortex generator 22.
  • the respective apex 38 of a lamella 36 is designed as an employed surface 24 and has two edges 26 delimiting the substantially triangular surface 24. These extend downstream of the longitudinal axis L away.
  • the end region 34 has a number of outlet channels 46 for the second fuel corresponding to the number of vortex generators 22.
  • the radial outlet openings 18 are arranged substantially directly downstream of the outer tube 16.
  • a respective radial outlet opening 18 is arranged either in an imaginary extension of an intermediate space 40 or in an imaginary extension of an outlet channel 46.
  • FIGS. 15 to 17 An alternative embodiment with both vortex generators 22 and fins 36 in the end region 34 of the outer tube 16 is in the FIGS. 15 to 17 shown.
  • a vortex generator 22 is arranged in the intermediate space 40 between two adjacent lamellae 36.
  • the vortex generators 22 are formed in the embodiment shown here to the end 42 of the outer tube 16, that is, in particular the vortex generators 22 are aligned in the radial direction with the end 42 of the outer tube 16.
  • turbulators 22 have in the FIGS. 15 to 17 vortex generator 22 shown at the end no outlet channels 46.
  • FIGS. 18 to 23 each show an embodiment of a vortex generator 22. In this case, the actual design is not limited to the embodiments shown here.
  • FIGS. 18 and 19 each show one with respect to a flow direction S employed triangular or rectangular surface 24.
  • Die FIG. 20 and 21 show similarly configured vortex generator 22, but these are formed here as a solid body and have corresponding side surfaces 48.
  • those in the FIGS. 22 and 23 shown turbulators 22 each have two, in particular separately manufactured side surfaces 48, which are employed with respect to the flow direction S.
  • the vortex generators 22 are respectively oriented forward with respect to the flow direction S.
  • the vortex generators 22 are oriented backwards, that is, rotated by 180 ° with respect to the flow direction S (the arrow indicating the flow direction S in FIG the FIGS. 18 to 23 then points in the opposite direction).

Landscapes

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

Claims (11)

  1. Buse (10) de brûleur pour deux combustibles, la buse (10) de brûleur ayant une lance (14) à combustible, qui s'étend dans une direction (S) d'écoulement, et dans laquelle sont ménagées un certain nombre de premières ouvertures (18) de sortie d'un premier combustible et la lance (14) à combustible est entourée d'un tuyau (16) extérieur, ayant au moins une deuxième ouverture (20) de sortie d'un deuxième combustible, les premières ouvertures (18) de sortie étant dirigées radialement et la deuxième ouverture (20) de sortie, axialement, un certain nombre de producteurs (22) de tourbillon étant montés sur la lance (14) à combustible,
    caractérisée en ce qu'au moins un producteur (22) de tourbillon est monté en amont des premières ouvertures (18) de sortie et en aval de la deuxième ouverture (20) de sortie.
  2. Brûleur (2), ayant une pluralité de chambres (6) de prémélange, ayant chacune une buse (10) à combustible suivant la revendication 1, dans lequel
    une section (Q) transversale d'écoulement est formée entre une lance (14) à combustible et une face intérieure de la chambre (6) de prémélange, et dans lequel le producteur (22) de tourbillon, monté sur la lance (14) à combustible, réduit la section (Q) transversale d'écoulement orientée transversalement à la direction (S) d'écoulement,
    caractérisé en ce que la chambre (6) de prémélange a une section (50) transversale et une extrémité (52) et la distance des premières ouvertures (18) de sortie à l'extrémité (52) de la chambre (6) de prémélange est au moins trois fois aussi grande que la section (50) transversale de la chambre (6) de prémélange.
  3. Brûleur (2) suivant la revendication 2,
    caractérisé en ce que la lance (14) à combustible et le tuyau (16) extérieur sont disposés concentriquement.
  4. Brûleur (2) suivant l'une des revendications 2 ou 3,
    caractérisé en ce qu'au moins un producteur (22) de tourbillon est cunéiforme.
  5. Brûleur (2) suivant l'une des revendications 2 à 4,
    caractérisé en ce qu'au moins un producteur (22) de tourbillon est mis sur le tuyau (16) extérieur.
  6. Brûleur (2) suivant l'une des revendications 2 à 5,
    caractérisé en ce qu'au moins un producteur (22) de tourbillon est monté en aval des ouvertures (18) de sortie radiales.
  7. Brûleur (2) suivant l'une des revendications 2 à 6,
    caractérisé en ce qu'au moins un producteur (22) de tourbillon est mis sur la paroi intérieure de la chambre (6) de prémélange.
  8. Brûleur (2) suivant l'une des revendications 2 à 7,
    caractérisé en ce que le tuyau (16) extérieur a une partie (34) d'extrémité, qui est conformée en mélangeur à lobe et qui comprend un certain nombre de lamelles (36).
  9. Brûleur (2) suivant la revendication précédente,
    caractérisé en ce qu'un certain nombre des lamelles (36) est conformé en producteur (22) de tourbillon.
  10. Brûleur (2) suivant l'une des deux revendications précédentes,
    caractérisé en ce qu'au moins un producteur (22) de tourbillon est disposé dans un espace (40) intermédiaire entre deux lamelles (36).
  11. Turbine (4) à gaz, ayant un brûleur (2) suivant l'une des revendications 2 à 10.
EP15741750.2A 2014-04-03 2015-03-20 Injecteur de combustible, brûleur avec un tel injecteur de combustible, et turbine à gaz munie dudit brûleur Active EP3087323B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014206446 2014-04-03
PCT/EP2015/055881 WO2015150114A1 (fr) 2014-04-03 2015-03-20 Brûleur, turbine à gaz munie dudit brûleur et injecteur de combustible

Publications (2)

Publication Number Publication Date
EP3087323A1 EP3087323A1 (fr) 2016-11-02
EP3087323B1 true EP3087323B1 (fr) 2019-08-21

Family

ID=53724199

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15741750.2A Active EP3087323B1 (fr) 2014-04-03 2015-03-20 Injecteur de combustible, brûleur avec un tel injecteur de combustible, et turbine à gaz munie dudit brûleur

Country Status (4)

Country Link
US (1) US10125993B2 (fr)
EP (1) EP3087323B1 (fr)
CN (1) CN106164592B (fr)
WO (1) WO2015150114A1 (fr)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016085494A1 (fr) * 2014-11-26 2016-06-02 Siemens Aktiengesellschaft Lance à carburant ayant un moyen pour interagir avec un flux d'air et améliorer la rupture d'un jet de carburant liquide éjecté
CN106705045B (zh) * 2017-01-22 2019-08-09 中国科学院工程热物理研究所 一种内外流道当量比可调的喷嘴、喷嘴阵列和燃烧器
US10760793B2 (en) * 2017-07-21 2020-09-01 General Electric Company Jet in cross flow fuel nozzle for a gas turbine engine
US20190056108A1 (en) * 2017-08-21 2019-02-21 General Electric Company Non-uniform mixer for combustion dynamics attenuation
US10969107B2 (en) * 2017-09-15 2021-04-06 General Electric Company Turbine engine assembly including a rotating detonation combustor
GB201806020D0 (en) * 2018-02-23 2018-05-30 Rolls Royce Conduit
CN110748920B (zh) * 2018-07-23 2024-02-09 中国联合重型燃气轮机技术有限公司 轴向分级燃烧器
JP7287811B2 (ja) 2019-03-25 2023-06-06 三菱重工業株式会社 燃焼器及びガスタービン
US12050012B2 (en) 2020-03-31 2024-07-30 Siemens Energy Global GmbH & Co. KG Burner component of a burner, and burner of a gas turbine having a burner component of this type
EP3889506A1 (fr) * 2020-03-31 2021-10-06 Siemens Aktiengesellschaft Composant de brûleur d'un brûleur et brûleur d'une turbine à gaz doté d'un tel composant
CN111442266B (zh) * 2020-05-08 2025-01-24 中国科学院工程热物理研究所 一体化设计的富氢燃烧室头部
KR102460672B1 (ko) * 2021-01-06 2022-10-27 두산에너빌리티 주식회사 연료 노즐, 연료 노즐 모듈 및 이를 포함하는 연소기
US11454396B1 (en) * 2021-06-07 2022-09-27 General Electric Company Fuel injector and pre-mixer system for a burner array
KR102667812B1 (ko) * 2022-02-07 2024-05-20 두산에너빌리티 주식회사 연소기용 노즐 및 이를 포함하는 가스 터빈
KR102581831B1 (ko) * 2023-03-20 2023-09-25 국방과학연구소 가변 연료 분사 장치를 포함하는 이중 모드 램제트 엔진
CN116857674B (zh) * 2023-07-27 2025-08-29 清启动力(北京)科技有限公司 一种双燃料一体式点火器喷嘴及燃气轮机
CN116928699B (zh) * 2023-07-27 2025-09-05 清启动力(北京)科技有限公司 一种双燃料空气预混喷嘴及燃气轮机
US12339006B1 (en) 2023-12-22 2025-06-24 General Electric Company Turbine engine having a combustion section with a fuel nozzle assembly
US20250362017A1 (en) * 2024-05-22 2025-11-27 General Electric Company Turbine engine and combustor therefor

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3319692A (en) * 1965-06-01 1967-05-16 Iit Res Inst Oil burner
US3974646A (en) * 1974-06-11 1976-08-17 United Technologies Corporation Turbofan engine with augmented combustion chamber using vorbix principle
US4260367A (en) * 1978-12-11 1981-04-07 United Technologies Corporation Fuel nozzle for burner construction
US4311277A (en) 1979-06-20 1982-01-19 Lucas Industries Limited Fuel injector
CH672541A5 (fr) * 1986-12-11 1989-11-30 Bbc Brown Boveri & Cie
US4974415A (en) * 1987-11-20 1990-12-04 Sundstrand Corporation Staged, coaxial multiple point fuel injection in a hot gas generator
US5235813A (en) * 1990-12-24 1993-08-17 United Technologies Corporation Mechanism for controlling the rate of mixing in combusting flows
US5435126A (en) * 1994-03-14 1995-07-25 General Electric Company Fuel nozzle for a turbine having dual capability for diffusion and premix combustion and methods of operation
DE4426351B4 (de) 1994-07-25 2006-04-06 Alstom Brennkammer für eine Gasturbine
JP2001141242A (ja) * 1999-11-16 2001-05-25 Hitachi Ltd ガスタービン燃焼器
JP4629945B2 (ja) 1999-12-15 2011-02-09 大阪瓦斯株式会社 流体分配器及びバーナ装置及びガスタービンエンジン及びコジェネレーションシステム
JP2002031343A (ja) 2000-07-13 2002-01-31 Mitsubishi Heavy Ind Ltd 燃料噴出部材、バーナ、燃焼器の予混合ノズル、燃焼器、ガスタービン及びジェットエンジン
DE10205428A1 (de) 2002-02-09 2003-09-11 Alstom Switzerland Ltd Vormischbrenner mit erhöhter Flammenstabilität
DE10348604A1 (de) * 2003-10-20 2005-07-28 Rolls-Royce Deutschland Ltd & Co Kg Kraftstoffeinspritzdüse mit filmartiger Kraftstoffplatzierung
WO2006100176A1 (fr) * 2005-03-23 2006-09-28 Alstom Technology Ltd Procede et dispositif de combustion d'hydrogene dans un bruleur de premelange
EP2072899B1 (fr) * 2007-12-19 2016-03-30 Alstom Technology Ltd Procédé d'injection de carburant
US7757491B2 (en) * 2008-05-09 2010-07-20 General Electric Company Fuel nozzle for a gas turbine engine and method for fabricating the same
EP2253888B1 (fr) 2009-05-14 2013-10-16 Alstom Technology Ltd Brûleur d'une turbine à gaz ayant un générateur de vortex avec une lance à combustible
US9423132B2 (en) * 2010-11-09 2016-08-23 Opra Technologies B.V. Ultra low emissions gas turbine combustor
EP2604919A1 (fr) 2011-12-12 2013-06-19 Siemens Aktiengesellschaft Buse à combustible pour deux carburants
US20130192243A1 (en) * 2012-01-31 2013-08-01 Matthew Patrick Boespflug Fuel nozzle for a gas turbine engine and method of operating the same
US10184664B2 (en) * 2014-08-01 2019-01-22 Capstone Turbine Corporation Fuel injector for high flame speed fuel combustion

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
CN106164592B (zh) 2019-08-30
EP3087323A1 (fr) 2016-11-02
US10125993B2 (en) 2018-11-13
WO2015150114A1 (fr) 2015-10-08
US20170108224A1 (en) 2017-04-20
CN106164592A (zh) 2016-11-23

Similar Documents

Publication Publication Date Title
EP3087323B1 (fr) Injecteur de combustible, brûleur avec un tel injecteur de combustible, et turbine à gaz munie dudit brûleur
EP2233836B1 (fr) Générateur de torsion, procédé destiné à empêcher des retours de flammes dans un brûleur, doté d'au moins un générateur de torsion et d'un brûleur
EP2010757B1 (fr) Aube de turbine
DE102007004394B4 (de) Brenner zum Verbrennen eines Vorgemischs für eine Gasturbine
DE102007004864B4 (de) Brennkammer einer Gasturbine und Verbrennungssteuerverfahren für eine Gasturbine
DE102005024062B4 (de) Brennerrohr und Verfahren zum Mischen von Luft und Gas in einem Gasturbinentriebwerk
DE4426351B4 (de) Brennkammer für eine Gasturbine
EP0675322B1 (fr) Brûleur à prémélange
DE60310170T2 (de) Brennstoffinjektionsvorrichtung
EP2156095B1 (fr) Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange
EP1802915B1 (fr) Bruleur pour turbine a gaz
DE102010036488B4 (de) Gasturbinenbrenner
DE69617290T2 (de) Verbrennungsgerät für Gasturbinenmotor
EP2505808B1 (fr) Dispositif de mélange de carburant et d'air dans un moteur à réaction
EP0481111B1 (fr) Chambre de combustion pour turbine à gaz
DE4411623A1 (de) Vormischbrenner
EP0775869B1 (fr) Brûleur à prémélange
CH703548B1 (de) Brennstoffeinspritzkopf mit Oberflächenmerkmalen zur Flammenstabilisierung.
WO2012016748A2 (fr) Chambre de combustion de turbine à gaz
WO2023180315A2 (fr) Ensemble injecteur comportant une alimentation centrale en carburant et au moins un canal d'air
DE102009054669A1 (de) Brenner für eine Turbine
WO2023180320A1 (fr) Ensemble injecteur comprenant un tuyau de carburant central rendu étanche à un flux d'air entrant
DE102017118165B4 (de) Brennerkopf, Brennersystem und Verwendung des Brennersystems
WO2019020350A1 (fr) Brûleur de turbine à gaz à jets de flamme prémélangés
DE19507088B4 (de) Vormischbrenner

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: 20160728

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: BA ME

DAV Request for validation of the european patent (deleted)
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

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190506

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502015010084

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1170195

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190915

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: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190821

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

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: 20191223

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: 20191121

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: 20190821

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: 20190821

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: 20190821

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: 20190821

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: 20191121

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: 20190821

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: 20190821

Ref country code: AL

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: 20190821

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: 20191122

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: 20190821

Ref country code: RS

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: 20190821

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: 20191221

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

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: 20190821

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

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: 20190821

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: 20190821

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: 20190821

Ref country code: IT

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: 20190821

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: 20190821

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

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: 20200224

Ref country code: SM

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: 20190821

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: 20190821

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: 20190821

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502015010084

Country of ref document: DE

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

PG2D Information on lapse in contracting state deleted

Ref country code: IS

26N No opposition filed

Effective date: 20200603

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: 20190821

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: 20190821

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502015010084

Country of ref document: DE

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

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

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200331

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: 20200320

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

Ref country code: CH

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

Effective date: 20200331

Ref country code: LI

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

Effective date: 20200331

Ref country code: FR

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

Effective date: 20200331

Ref country code: IE

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

Effective date: 20200320

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: 20200331

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

Effective date: 20200320

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

Ref country code: GB

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

Effective date: 20200320

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1170195

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200320

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: 20200320

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: 20190821

Ref country code: CY

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: 20190821

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

Ref country code: MK

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: 20190821

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

Effective date: 20231222

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

Ref country code: DE

Payment date: 20250327

Year of fee payment: 11