EP3699493A1 - Système de chambre de combustion et dispositif de micro-turbine à gaz - Google Patents

Système de chambre de combustion et dispositif de micro-turbine à gaz Download PDF

Info

Publication number
EP3699493A1
EP3699493A1 EP20160469.1A EP20160469A EP3699493A1 EP 3699493 A1 EP3699493 A1 EP 3699493A1 EP 20160469 A EP20160469 A EP 20160469A EP 3699493 A1 EP3699493 A1 EP 3699493A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
chamber system
structural unit
section
oxidizer
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.)
Granted
Application number
EP20160469.1A
Other languages
German (de)
English (en)
Other versions
EP3699493B1 (fr
Inventor
Hannah Seliger-Ost
Matthias Lang
Andreas Huber
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.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
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 Deutsches Zentrum fuer Luft und Raumfahrt eV filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Publication of EP3699493A1 publication Critical patent/EP3699493A1/fr
Application granted granted Critical
Publication of EP3699493B1 publication Critical patent/EP3699493B1/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
    • F23R3/002—Wall structures
    • 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
    • F23D14/04—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone induction type, e.g. Bunsen burner
    • F23D14/08—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone induction type, e.g. Bunsen burner with axial outlets at the burner head
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • 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
    • F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses
    • 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
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components

Definitions

  • the invention relates to a combustion chamber system, in particular for use in a gas turbine system, with a circumferential wall running around a longitudinal axis that delimits a combustion chamber in which a reaction zone is formed during operation, with a burner head arranged on the inlet side of the combustion chamber for adding fuel and oxidizer to the Combustion chamber, which comprises at least one fuel supply for adding fuel to the oxidizer, and with a combustion chamber outlet arranged on the outlet side of the combustion chamber.
  • the invention also relates to a micro gas turbine arrangement with a combustion chamber system.
  • combustion chamber systems are used, for example, in gas turbine systems and are for example from the EP 1 497 589 B1 and the EP 1 995 515 A1 known.
  • development of such combustion chamber systems aims to optimize pollutant emissions and to ensure stable operation.
  • micro gas turbine systems in a performance class of less than 1 MW
  • a high degree of flexibility for example with regard to operation with different fuels, is sought.
  • a special known concept uses a combustion process management in which a pronounced, in particular internal, recirculation zone is formed in the combustion chamber, based on the so-called FLOX® principle ("Flameless Oxidation").
  • FLOX® principle “Flameless Oxidation”
  • already burned exhaust gases are returned within the combustion chamber and added to the fresh air in larger quantities.
  • Current combustion chamber systems based on the FLOX® principle are for example in " Zanger, J., Monz, T, Aigner, M., Experimental Investigation of the Combustion Characteristics of a double-staged FLOX®-based Combustor on an Atmospheric and a Micro Gas Turbine Test Rig, Proceedings of ASME Turbo Expo 15.-19 .
  • the installation position or location of the combustion chamber system in a turbine housing can have an influence, in particular if the outer boundary of the combustion chamber system is integrated into the geometry of gas guide paths.
  • This can e.g. B. be cooling air ducts around the combustion chamber system.
  • the positioning or location of the combustion chamber system changes with respect to the housing, for example due to thermal expansion during operation, this can influence the geometry and the supply of the combustion chamber system with fuel gas (oxidizer and / or fuel). This can in turn have a negative effect on the combustion process, in particular the stability and / or exhaust gas emissions.
  • the invention is based on the object of providing a combustion chamber system which is positioned in a technical application in a largely defined manner during operation. Furthermore, the invention is based on the object of providing a micro gas turbine arrangement with such a combustion chamber system.
  • combustion chamber system is divided into at least a first and a second structural unit, which are arranged axially one behind the other in an installed state in a technical application, the second structural unit extending at least in some areas downstream of the first structural unit, and that the structural units are axially relative are mounted displaceably to each other.
  • micro gas turbine arrangement For the micro gas turbine arrangement, the object is achieved with the features of claim 18.
  • This relates to a micro gas turbine arrangement with a combustion chamber system according to the invention, with a turbine connected downstream of the combustion chamber system and with a housing that surrounds at least the combustion chamber system by means of a wall, with at least one duct for gas routing, in particular for air routing, being formed between a region of the wall and the combustion chamber system is.
  • the second unit includes z. B. downstream of the first structural unit.
  • the structural units can overlap at least in some areas.
  • the axial displaceability is such that at least the downstream end of the first Structural unit, in particular the first section of the peripheral wall, relative to the second structural unit, in particular the second partial section of the peripheral wall, are axially displaceable.
  • This design causes changes in the axial position of a e.g. the first structural unit, for example due to a change in length due to thermal expansion of the circumferential wall, can be compensated within the combustion chamber system.
  • the change in position or length is not transferred to the subsequent structural unit, since the axial movements of the structural units are decoupled from one another.
  • Position, in particular length variations of the combustion chamber system can be minimized in this way.
  • This is particularly advantageous when the combustion chamber system is integrated into an internal geometry of a technical application, with precise positioning being required. This can be the case, for example, when the combustion chamber system forms a partial delimitation of a channel for conducting gas and changes in length of the combustion chamber system would influence the flow cross-section of the channel, which in turn can affect the combustion process.
  • the defined positioning thus contributes to a controlled, clean and stable combustion during operation.
  • the combustion chamber system can be easily adapted to, for example, operation with different fuels if the structural units are detachably (axially) arranged one behind the other in the installed state.
  • the structural units can then be present separately from one another during or after the dismantling of the combustion chamber system.
  • structural units that should be designed differently for a different mode of operation can be exchanged individually without the entire combustion chamber system having to be exchanged.
  • This can, for example, relate to elements that have an influence on a division of the oxidizer flow, such as mixed air openings in a section of the circumferential wall.
  • the first structural unit preferably comprises a first section of the circumferential wall and / or the second structural unit comprises a second section of the circumferential wall.
  • the division of the combustion chamber system into the structural units is arranged adjacent to one or between two subsections.
  • the sections run z. B. each circumferentially around the longitudinal axis, so that there are pipe sections arranged axially one behind the other.
  • the division can be made, for example, perpendicular to the axial direction (i.e. to the longitudinal axis).
  • the modules arranged one behind the other overlap with one another in an axial overlap area, wherein in particular the first section overlaps with the second module, in particular with the second section.
  • the inner circumference of the one, outer structural unit or the subsection is larger than the outer circumference of the other, inner structural unit or the subsection and is pushed over the inner structural unit or the inner subsection in the overlapping area.
  • the exact length of the overlap area can change depending on the axial displacement of the two subsections with respect to one another.
  • a tubular configuration of the circumferential wall is in the overlap area z.
  • B. a tube-in-tube arrangement In this way, a defined, easy-to-manufacture transition between two structural units or subsections can be obtained in a simple manner.
  • the structural units, in particular the subsections are arranged in the overlapping area at least partially without contact with one another.
  • this is e.g. as an annular gap.
  • touching elements may be present, e.g. B. spacing means to keep the gap.
  • the gap is as small as possible in order to keep leakages between the combustion chamber and the outside area low, but preferably sufficiently large to be able to operate during operation, e.g. B. under thermal expansion to grant unimpaired mobility.
  • the combustion chamber system preferably comprises at least one anti-rotation device, by means of which the structural units arranged one behind the other (in particular with successive subsections) are mounted in the circumferential direction so that they cannot rotate with respect to one another.
  • This enables the structural units or the subsections to be precisely positioned relative to one another in the circumferential direction.
  • Elements of the combustion chamber system which are assigned to different subsections or structural units can thus be arranged in a defined manner relative to one another in the circumferential direction.
  • One example is mixed air openings, which are arranged in a defined position relative to the feed nozzles of the burner head. This training contributes to an optimized, controlled combustion process.
  • the anti-rotation device is formed in the overlap area, one of the two structural units being arranged on the outside and one on the inside.
  • the anti-rotation device comprises an anti-rotation device which, in particular, has the inside of the outer structural unit in the overlap area, in particular the outer partial section, is formed and furthermore a receptacle, which is formed in particular on a downstream end of the inner structural unit, in particular the inner partial section.
  • the anti-rotation device can be guided axially in the receptacle.
  • the anti-rotation means is in particular as a projection, for. B. in the form of a "nose", a pin or a web.
  • the recess preferably extends axially longitudinally starting from the downstream end in the inner structural unit, for. B. as a slot in the inner section.
  • the receptacle is dimensioned such that the anti-rotation device can protrude.
  • the anti-rotation device permits an axial relative movement, but prevents rotation.
  • the first structural unit comprises the burner head and the first section of the circumferential wall, which is in particular fastened to the burner head. With the first subsection, the first structural unit extends axially over the region of the reaction zone.
  • the second structural unit comprises the combustion chamber outlet. In and immediately downstream of the reaction zone, high temperatures arise during operation, which cause a relatively large thermal expansion of the first subsection. The resulting change in length of the first section can be compensated for due to the axial displaceability by movement relative to the second section and therefore does not lead to a change in length of the entire combustion chamber system. This enables a largely defined position or positioning of the combustion chamber system over the entire length, even during operation.
  • the first subsection preferably extends as far as possible in the direction of the combustion chamber outlet, so that the largest possible part of the change in length can be compensated for by thermal expansion of the combustion chamber system.
  • the first section can so, for. B. extend to an axial position at which the temperature of the exhaust gas z. B. is significantly reduced by adding secondary air, which also reduces thermal expansion.
  • the length of the first subsection or the division can expediently be selected such that elements or configurations of the combustion chamber system downstream of the reaction zone that have to be adapted in different modes of operation (e.g. mixed air openings) are assigned to the second structural unit.
  • elements or configurations of the combustion chamber system downstream of the reaction zone that have to be adapted in different modes of operation (e.g. mixed air openings) are assigned to the second structural unit.
  • modes of operation e.g. mixed air openings
  • a stable mounting, independent of the first structural unit, for precise fixing of the second structural unit can be achieved in that the second structural unit has at least one bearing means on its outer circumference which is designed to attach the second structural unit to a housing surrounding the combustion chamber system (e.g. the transition between two housing parts, such as a pressure and a turbine housing part).
  • a housing surrounding the combustion chamber system e.g. the transition between two housing parts, such as a pressure and a turbine housing part.
  • the bearing means is preferably designed for arrangement in a gas guide section, in particular in a channel, wherein gas can pass through it.
  • the gas guide section is formed between the combustion chamber system and the surrounding housing of a technical application.
  • Passable by gas means that the bearing means is designed in a flow-favorable manner with a low blocking effect. B. blocked less than half of the flow cross-section. It can thus advantageously act at the same time as a (radial) spacer, which ensures a defined cross-sectional area of the channel and thus enables a uniform gas flow.
  • a ring-like element is particularly useful because it has a high degree of stability and is relatively simple, e.g. B. as a turned and / or milled part is to be manufactured.
  • Such an advantageous gas-passable, stable design of the bearing means results, for. B., if the bearing means (in particular ring-shaped) is designed circumferentially, with a circumferential outer contact section for contact with a housing surrounding the combustion chamber system and with a circumferential inner contact section which is arranged on the second structural unit, in particular on the second subsection, e.g. B. is attached, and when the two contact sections are connected to one another gas passable via radially arranged webs.
  • the outer contact section can have a circumferential, radially outwardly directed projection for easy axial fixation on the housing, the z. B. can engage in a groove of a flange connection.
  • a reduction in the temperature load on the bearing means can be achieved in that the bearing means is arranged in the overlap area, in particular between the first section and the second section. In this area z. B. due to a non-contact arrangement of the two structural units to each other and any existing air leakage into the combustion chamber lower temperatures on the outside of the peripheral wall.
  • the storage means can thus be designed to be less temperature-resistant, which is generally associated with lower production costs and / or outlay.
  • a part-optimized and flow-optimized mounting of the first structural unit results when the first structural unit is mounted over the burner head (or at least parts of it) and a fuel supply line.
  • the fuel supply line can be of relatively large dimensions relative to the first structural unit and thus has good stability for its stable mounting.
  • the combustion chamber system is designed in such a way that, during operation, a secondary flow of oxidizer is branched off from a total oxidizer flow and is directed via the burner head into a channel between the circumferential wall and a wall surrounding the combustion chamber system.
  • the wall is in particular assigned to a housing surrounding the combustion chamber system.
  • the secondary current is z. B. used for cooling purposes, both convective by flowing past the circumferential wall and for cooling the exhaust gas by admixture behind the reaction zone through mixed air openings.
  • the ratio between the total oxidizer flow and the secondary flow is usually based on the geometry and a specific pressure loss ratio associated with it.
  • Changes in the length of the combustion chamber system can influence this ratio via changes in the geometry of the duct, which in turn can influence the combustion process. This can be reduced or avoided by the design of the combustion chamber system according to the invention. At the same time the ratio can be changed in a targeted manner by changing the geometry of the air supply of the duct and / or of existing mixed air openings due to the simple interchangeability of the second structural unit.
  • An advantageous embodiment results when mixed air openings are arranged in the second subsection of the circumferential wall, in particular circumferentially, through which, during operation, oxidizer of the secondary flow flows into the combustion chamber downstream of the reaction zone.
  • oxidizer By adding oxidizer, the exhaust gas is cooled before it enters the turbine, which significantly reduces the thermal load on the turbine and can also reduce the thermal expansion of the circumferential wall from the position of the mixed air openings.
  • the mixed air openings are assigned to the second section, the mixed air openings can be changed in a simple manner by exchanging only the second structural unit, e.g. B. if another operating mode requires a different ratio of total to secondary current.
  • a particularly advantageous combustion chamber system results when the combustion chamber system is designed for operation with a pronounced inner recirculation zone, in particular supply nozzles for supplying oxidizer and / or fuel via the burner head being arranged in a ring around the front wall of the burner head.
  • the feed nozzles are preferably located radially in the outer region, closer to the peripheral wall than to the longitudinal axis, preferably in the outer third.
  • the peripheral wall is for a symmetrical combustion z.
  • a flow-favorable design of the burner head and thus of the combustion chamber system is achieved if the end wall is at least partially designed to taper against the direction of flow of the oxidizer.
  • the end wall tapers conically, for example, and converges in particular symmetrically on the longitudinal axis. This reduces the flow loss through the oxidizer, which is directed via a plenum in the direction of the combustion chamber or around the combustion chamber. This contributes to optimizing the flow of the combustion chamber system and thus to increasing the overall efficiency of a system in which the combustion chamber system is used.
  • the branching off of a secondary flow from the oxidizer and its distribution to a channel around the circumferential wall can also take place in a flow-efficient manner.
  • the end wall is preferably designed as a wall instead of from solid material.
  • Supply nozzles that are present in the combustion chamber are attached to the end wall and protrude at least upstream into the plenum, preferably also downstream into the combustion chamber.
  • the material thickness of the end wall can be as small as possible, but in such a way that sufficient stability is ensured even under the thermal load that is typical for combustion chamber systems. It has been found that such an end wall, which is as thin as possible, contributes to the stability of the combustion process: the low mass results in low thermal inertia. In this way, steady states in the combustion chamber system with stable combustion operation are reached more quickly.
  • a compact first structural unit with a stable mounting can be obtained in that the end wall merges upstream into a positioning element which is arranged on the longitudinal axis, and that the positioning element merges upstream into a distributor area and above it into a fuel supply line.
  • This is also a symmetrical, parts-optimized and flow-efficient design of the combustion chamber system achievable.
  • the symmetry favors an optimized combustion process with low pollutant emissions.
  • Fig. 1 shows a sectional view of a combustion chamber system 1 with a burner head 4 and a combustion chamber 10.
  • the combustion chamber system 1 is designed for combustion process management according to the so-called "FLOX®" principle, in which a pronounced inner recirculation zone 22 is formed during operation.
  • FLOX® so-called "FLOX®” principle
  • the development of the combustion chamber system 1 of this type according to the invention allows the already favorable emission values to be further optimized or stabilized.
  • a combustion chamber system 1 that can be operated efficiently, stably and with low emissions is provided.
  • the combustion chamber 10 comprises a combustion chamber 2, which is delimited by a peripheral wall 3 of the combustion chamber 10.
  • the peripheral wall 3 is arranged cylindrically around a longitudinal axis L, along which the combustion chamber system 1 extends axially.
  • mixed air openings 30 for feeding mixed air into the burned exhaust gas flowing out of the combustion chamber 10.
  • these are in a row in a ring-like manner, evenly distributed radially around the circumferential wall 3 and are designed in detail as circular bores, other opening shapes and other arrangements being possible.
  • the burner head 4 is arranged on the inlet side of the combustion chamber 2 and has several, here by way of example six, feed nozzles 47 into the combustion chamber 2 for the addition of fresh gases to be burned (ie oxidizer, here further referred to as "(combustion) air", and fuel) opening feed openings 46.
  • the feed openings 46 are arranged uniformly circumferentially on an imaginary ring in an input-side end wall 40.
  • the ring in particular a circular ring, on which the supply openings 46 are arranged, is located in the outer region of the end wall 40, so that the radial distance between the supply openings 46 (with respect to their center points) and the peripheral wall 3 is less than that of the longitudinal axis L.
  • the fresh gas " Air can also be formed by another oxidizer and / or contain gas additives, such as exhaust gas, or thermally utilizable hydrocarbon compounds.
  • the fuel gas is z. B. natural gas is used, or another, in particular gaseous fuel.
  • the burner head 4 comprises, in addition to the feed nozzles 47 and the end wall 40, which delimits the combustion chamber 2 on the inlet side, a fuel supply for adding fuel to the combustion air.
  • the end wall 40 is conically tapered against the direction of flow with respect to the combustion air in order to reduce the flow loss during operation compared to a flat design.
  • the fuel supply comprises a plurality of fuel nozzles 44, here each one of the supply nozzles 47 for the formation of air / fuel nozzle arrangements 41 are assigned.
  • One feed nozzle 47 protrudes into a plenum 49 with an upstream end formed here by a cylinder section and thus forms an air supply 45.
  • the cross section of the supply nozzle 47 here the cylinder section, tapers to form an acceleration path. here over a conical axial area, and protrudes with a tapered, downstream section through the end wall 40 into the combustion chamber 10.
  • the section protruding into the combustion chamber 10 is also cylindrical, but can also have a different shape.
  • the supply nozzles 47 extend along central longitudinal axes M, which are aligned parallel to the longitudinal axis L, for the axial supply of the partially premixed fuel-air mixture into the combustion chamber 10.
  • a non-premixed or technically completely premixed addition of the fresh gases is also possible, with the Burner head 4 is designed accordingly.
  • a branch line 43 of a finger-like line arrangement protrudes into each feed nozzle 47.
  • the branch lines 43 branch off like fingers from a central fuel supply line 42, whereby they have a certain line length, for example more than three times as long as the outer line diameter.
  • the branch lines 43 are designed with a change of direction, here bent for a favorable flow guidance, the angle ⁇ of the bends being greater than 90 ° and less than 180 ° .
  • Each branch line 43 opens into a fuel nozzle 44 which is positioned directly upstream of the tapered section, with an opening immediately at the start of the acceleration section.
  • the fuel can thus be added coaxially to the inflowing combustion air, with the combustion air being accelerated through the cross-sectional constriction immediately downstream of the fuel addition position.
  • a (partial) premixing of fuel and combustion air can take place up to the supply opening 46.
  • the fuel supply further comprises a central distributor area 421 arranged symmetrically on the longitudinal axis L and the branch lines 43 extending therefrom and opening into the fuel nozzles 44.
  • the branch lines 43 are fed with fuel via the distributor area 421 and a fuel supply line 42. This results in a symmetrical arrangement of the fuel supply in which a fuel plenum is not explicitly provided. This means that there is no need for a high pressure loss for even distribution of the fuel, as is usually the case with designs with a fuel plenum.
  • the burner head 4 and the peripheral wall 3 can have a radial positioning unit as an assembly aid (not shown here).
  • This can e.g. be formed by a nose-like projection in the outer region of the end wall 4 and a complementary receptacle in the peripheral wall 3.
  • the recording is z. B. designed and positioned so that the projection engages during the assembly of the burner head 4 and the peripheral wall 3.
  • the combustion chamber system 1 has a combustion chamber outlet 35, by means of which the combustion chamber system 1 merges into an exhaust line (not shown here) of an exhaust gas region 5.
  • the exhaust gas is fed to a turbine, for example, via the exhaust pipe.
  • the combustion chamber outlet 35 has a conical section 38, which is provided to reduce the cross-section from the circumferential wall 3 to the exhaust pipe in a streamlined manner.
  • the conical portion 38 can be fixed, e.g. B. be integrally connected to the peripheral wall 3.
  • the conical section 38 can also be dispensed with.
  • the combustion chamber system 1 is mounted in a housing of a technical application, the wall 8 of which in Fig. 1 is partially indicated schematically.
  • this can be the housing of a micro gas turbine arrangement, for example with a pressure housing part 81 which houses a large part of the combustion chamber system 1 and with a turbine housing part 82 which are connected via a flange connection 83 (indicated here).
  • a channel 84 for guiding air is formed between the wall 8 and the outside of the peripheral wall 3.
  • the channel 84 is used to guide the secondary air, which during operation is separated from the total air flow of the plenum 49 upstream of the end wall 40.
  • the wall 8 converges in the area of the conical section 38 in a, here conical, cross-sectional constriction. How Fig. 1 As can be seen, the flow cross-section of the channel 84 in the area of the cross-sectional constriction depends, inter alia, on the axial length of the combustion chamber system 1.
  • the combustion chamber system 1 is axially divided into two structural units 36 and 37 which are mounted so as to be axially displaceable relative to one another.
  • the storage takes place separately from one another.
  • More than two structural units 36, 37 that form the combustion chamber system 1 are also possible.
  • the structural units 36 and 37 are each assigned an axial section 30, 31 of the peripheral wall 3, so that the peripheral wall 3 is divided into two axial sections 30, 31.
  • the structural units 36, 37 with the subsections 30, 31 are arranged axially one behind the other and in their transition relative to one another so as to be axially displaceable. At least one downstream end 39 of the first section 30 is axially displaceable with respect to the second section 31.
  • the first structural unit 36 which is arranged further upstream, furthermore comprises the burner head 4, on the end wall 40 of which the circumferential wall 3 is attached circumferentially and from which the first section 30 of the circumferential wall 3 extends.
  • the first subsection 30 has an axial length such that it extends at least over a reaction zone 21 in which the rapid combustion reactions take place during operation.
  • the second structural unit 37 includes the combustion chamber outlet 35 with the conical section 38.
  • the mixed air openings 34 are also provided in the second sub-section 31 of the peripheral wall 3.
  • the two structural units 36, 37 are detachably mounted in such a way that the subsections 30, 31 are arranged directly axially one behind the other. “Detachable” means that the structural units 36, 37 can be separated during or after dismantling or are present separately.
  • a defined, axially gapless transition between the two subsections 30, 31 is achieved in that the two subsections 30, 31 overlap one another in an axial overlap region 32.
  • the inside diameter of the second subsection 31 is slightly larger than the outside diameter of the first subsection 30, so that the first subsection 30 can be pushed into the second subsection 31 during assembly.
  • the inner diameter of the second subsection 31 is selected to be larger in such a way that the two subsections 30, 31 are arranged in a contact-free manner with the formation of an annular gap 33 in the overlapping area 32 (except for e.g. any anti-rotation means and / or guide means and / or Spacer means 381).
  • This allows simple assembly and good axial mobility to one another.
  • the annular gap 33 is radially so wide that even with z. B. deformations during operation, the axial mobility to each other is maintained, but otherwise as close as possible to keep air leakage between the channel 84 and the combustion chamber 2 low.
  • the change in length of the combustion chamber system 1 caused by thermal expansion is largely compensated for by the axial relative movement of the subsections 30, 31 to one another.
  • the first section 30 of the circumferential wall 3 pushes axially further under the second section 31 of the circumferential wall 3.
  • the path of the axial displaceability is designed to be at least as large as the expected heat-related linear expansion of the first structural unit 36 around it to be able to compensate.
  • the overlap area 32 increases by the axial length extension, but the total length of the combustion chamber system 1 remains largely unchanged. The total length varies essentially by the length expansion of the second structural unit 37.
  • the two structural units 36, 37 are expediently mounted separately from one another for an axially displaceable mounting of the subsections 30, 31.
  • the second structural unit 37 is mounted on the housing of the technical application surrounding it, here the micro gas turbine arrangement.
  • the second structural unit 37 in the present case has a bearing means 6 which is attached to the outer circumference of the second partial section 31.
  • the bearing means 6 is mounted on the flange connection 83 between the two housing parts 81, 82, whereby the bearing means 6 can be easily installed and the second structural unit 37 is securely mounted.
  • the bearing means 6 is designed in such a way that it can be arranged circumferentially in a gas guide section, here the channel 84, wherein the gas can pass through it.
  • the bearing means 6 is advantageously designed in such a way that it has a low flow resistance, but at the same time is sufficiently stable for secure storage.
  • the bearing means 6 has a ring structure.
  • the bearing means 6 comprises an annular outer contact section 61 for contact with the surrounding housing and an inner contact section 63 with which the bearing means 6 is fastened to the second section 31 of the peripheral wall 3 and thus forms part of the second structural unit 37.
  • the contact sections 61, 63 are designed to be ring-like and preferably thin-walled for a secure contact or good fastening possibility with at the same time low-resistance shape.
  • the material thickness is at least sufficiently thick, in order to give the contact sections 61, 63 the stability required for storage.
  • the outer contact section 61 has a circumferential, radially outwardly directed projection 62 which is here axially centered. With the protrusion 62, the bearing means 6 engages z. B. in a groove formed in the flange connection 83. The bearing means 6 can be clamped between the flanges, whereby a defined positioning of the bearing means 6 and thus the second structural unit 37 is advantageously achieved. When the combustion chamber system 1 is mounted vertically, the bearing means 6 with the projection 62 could also rest on the flange of the turbine housing part 82 and be supported against it (not shown here).
  • the two contact sections 61, 63 are connected to one another in a stable manner by webs 64 extending radially (with respect to the longitudinal axis L), here six in number by way of example.
  • the bearing means 6 also acts as a radial spacer ring. This ensures a uniform radial spacing between the combustion chamber system 1 and the wall 8, and thus a uniform, symmetrical flow cross section of the channel 84. This contributes to a symmetrical air flow.
  • one or more spacing means 381 can additionally be present on the second structural unit 37 in order to keep the flow cross-section of the channel 84 as constant as possible.
  • the spacing means 381 are arranged in the form of projections on the outside of the conical section 38 for contact with the wall 8. In particular, they serve to additionally fix the second structural unit 37 and to change the position of the second structural unit 37, for example. B. to counteract by deformations.
  • the bearing means 6 is fastened to the second structural unit 37 in the overlap region 32.
  • the overlap area 32 corresponds in its axial extent z. B. approximately the axial extent of the bearing means 6 or the inner contact section 63.
  • the overlap area 32 can also be longer, in particular in Operation in which the overlap area 32 increases axially by the displacement due to thermal expansion.
  • the fastening of the bearing means 6 in the overlap region 32 has the advantage that the thermal load on the contact section 63 is reduced. This results in particular from the contact-free arrangement of the subsections 30, 31 with respect to one another, the annular gap and any air leakage into the combustion chamber 2 reducing the heat transfer between the combustion chamber 2 and the contact section 63.
  • the first structural unit 36 is supported in a part-optimized manner via the burner head 4, which is connected to the first section 30.
  • the bearing forces are transmitted via the end wall 40, which merges upstream into a rod-like positioning element 48 which is arranged centrally on the longitudinal axis L.
  • the positioning element 48 merges upstream into the distributor region 421 and above it into the fuel supply line 42.
  • the first structural unit 36 is fixed via the fuel supply line 42 upstream of the combustion chamber system 1 (not shown here).
  • the bearing is designed to be streamlined, thanks to the low-resistance shape of the end wall 4, which is conical in the direction of flow, and the central, compact cross-section arrangement and design of the positioning element 48, the distributor area 421 and the fuel supply line 42. This also results in a flow-efficient, stable bearing.
  • the combustion chamber system 1 comprises an anti-rotation device 7, by means of which the two structural units 36, 37 and thus the subsections 30, 31 are mounted so that they cannot rotate with respect to one another in the circumferential direction.
  • a fixed positioning of the two structural units 36, 37 is achieved in the radial direction.
  • elements or configurations in both structural units 36, 37 can be positioned in a defined manner relative to one another in the circumferential direction.
  • this concerns z. B. the feed openings 46 of the burner head 4, which are arranged radially clearly defined to the mixed air openings 34 of the second assembly 37, z. B. so that two mixed air openings 34 each lie radially between two supply openings 46. This enables a defined, clean combustion process management.
  • the anti-rotation device 7 is formed in the overlap region 32.
  • the anti-rotation device 7 comprises an anti-rotation device 71, which in the present case is designed as a protrusion on the inside of the outer, here the second, subsection 31, e.g. B. in the form of a "nose", a web or pin.
  • the anti-rotation device 7 comprises a receptacle 72 which is formed here at the end 39 of the inner, first partial section 30.
  • the receptacle 72 is introduced into the end 39 of the first section 30 in the manner of an axially extending, elongated recess, for example as a slot.
  • the recess is so wide that the anti-rotation means 71 can protrude, the anti-rotation means 71 having a corresponding radial height.
  • the axial length of the recess corresponds at least to the path of the expected axial displacement in which the thermal expansion results in this area.
  • the first section 30 is thus movable or displaceable and radially guided with its end 39 relative to the second section 31 over the entire path of thermal expansion.
  • Another advantage of the division of the combustion chamber system 1 described here is that the air conditions can be influenced with little effort. Should z. B. the combustion chamber system 1 can be used flexibly, for example with different fuels, this often requires an adjustment of the air conditions. Due to the division of the combustion chamber system 1 described here, in particular the mixed air ratio can be adapted with little effort by exchanging the second structural unit 37.
  • Fig. 1 the air flow is indicated by arrows.
  • the air is divided according to a certain ratio into a secondary air flow and a combustion air flow.
  • the secondary air is directed along the end wall 40 into the channel 84, the flow guidance being designed to be low in resistance due to the conical tapering of the end wall 40.
  • the secondary air flowing around the combustion chamber 10 cools the end wall 40 and the peripheral wall 3 in particular convectively.
  • the ratio of the division of total air (or combustion air) to secondary air and mixed air to remaining air in the secondary air is determined by the geometry of the Flow guidance, in particular the formation of the mixed air openings 34 and the channel 84, determined.
  • the remaining air enters the air / fuel nozzle assemblies 41 as combustion air through the air feeds 45.
  • the combustion air fuel is added coaxially to the main flow direction into the feed nozzles 47 immediately upstream of the cross-sectional constrictions, so that the combustion air with the added fuel is generated via the acceleration paths formed by the cross-sectional constrictions is accelerated.
  • the combustion air and fuel are partially mixed up to the outlet openings 46. This mixture is now fed to the combustion chamber 10, where it ignites and is burned in the reaction zone 21.
  • a recirculation flow is formed with an internal recirculation of the burned exhaust gas, by means of which part of the burned exhaust gas is returned to an area upstream of the combustion zone and mixes with the still unburned fresh gases (in the figure Arrows indicated). In this way the combustion temperature is reduced.
  • the feed openings 46 which are arranged relatively far outward, are beneficial an essentially inwardly directed recirculation, so that the returning exhaust gases in the inner recirculation zone 21, surrounded by the annular combustion zone, flow back, ie closer to the longitudinal axis L than the burning gases.
  • the essentially internal recirculation achieves a compact flow guidance, which in turn allows the combustion chamber 10 to be designed to be compact, in particular with regard to its length.
  • the burner head 4 and the combustion chamber 10 are designed such that the reaction zone 21 and recirculation zone 22 are located upstream of the mixed air openings 34.
  • the mixed air added through the mixed air openings 34 essentially mixes with the exhaust gas flowing in the downstream direction into the exhaust gas region 5 and cools it.
  • the burner head 4 and the combustion chamber 10 are, for. B. designed such that there is a recirculation rate (mass ratio of recirculated exhaust gas to added fresh gases) of less than 1.5, preferably less than 1, for example 0.4 to 0.8. This recirculation rate allows stable, clean combustion over a wide operating range.
  • the specified combustion process management enables low-emission, stable and efficient operation of the micro gas turbine arrangement.
  • the design of the combustion chamber system 1 according to the invention contributes to the advantageous operation in that the ratios according to the design between the air flows can be maintained more precisely.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP20160469.1A 2018-02-28 2019-02-18 Système de chambre de combustion et dispositif de micro-turbine à gaz Active EP3699493B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102018104543.3A DE102018104543A1 (de) 2018-02-28 2018-02-28 Brennkammersystem und Mikrogasturbinenanordnung
EP19157668.5A EP3534070B1 (fr) 2018-02-28 2019-02-18 Système de chambre de combustion et dispositif de micro-turbine à gaz

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP19157668.5A Division EP3534070B1 (fr) 2018-02-28 2019-02-18 Système de chambre de combustion et dispositif de micro-turbine à gaz
EP19157668.5A Division-Into EP3534070B1 (fr) 2018-02-28 2019-02-18 Système de chambre de combustion et dispositif de micro-turbine à gaz

Publications (2)

Publication Number Publication Date
EP3699493A1 true EP3699493A1 (fr) 2020-08-26
EP3699493B1 EP3699493B1 (fr) 2021-09-22

Family

ID=65493869

Family Applications (2)

Application Number Title Priority Date Filing Date
EP19157668.5A Active EP3534070B1 (fr) 2018-02-28 2019-02-18 Système de chambre de combustion et dispositif de micro-turbine à gaz
EP20160469.1A Active EP3699493B1 (fr) 2018-02-28 2019-02-18 Système de chambre de combustion et dispositif de micro-turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP19157668.5A Active EP3534070B1 (fr) 2018-02-28 2019-02-18 Système de chambre de combustion et dispositif de micro-turbine à gaz

Country Status (2)

Country Link
EP (2) EP3534070B1 (fr)
DE (1) DE102018104543A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2599424A (en) * 2020-10-01 2022-04-06 Bosch Thermotechnology Ltd Uk An air-gas mixture burning appliance with a gas flow distance regulating device

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1420202A (en) * 1972-03-16 1976-01-07 Stone Platt Crawley Ld Combustion chambers
EP1995515A1 (fr) 2007-05-23 2008-11-26 WS-Wärmeprozesstechnik GmbH Fonctionnement FLOX pris en charge et son brûleur
DE102012216080A1 (de) * 2012-08-17 2014-02-20 Dürr Systems GmbH Brenner
EP1497589B1 (fr) 2002-04-23 2015-03-11 WS-Wärmeprozesstechnik GmbH Chambre de combustion avec oxydation sans flamme
DE102015226079A1 (de) * 2015-12-18 2017-06-22 Dürr Systems Ag Brennkammervorrichtung und Gasturbinenvorrichtung
DE102016118633A1 (de) 2016-09-30 2018-04-05 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR) Brennerkopf, Brennersystem und Verwendung des Brennersystems
DE102016118632A1 (de) 2016-09-30 2018-04-05 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR) Brennkammersystem, Verwendung eines Brennkammersystems mit einer angeschlossenen Turbine und Verfahren zur Durchführung eines Verbrennungsprozesses

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2768497A (en) * 1951-02-03 1956-10-30 Gen Motors Corp Combustion chamber with swirler
DE3930569C2 (de) * 1989-09-13 1995-06-01 Siegfried W Schilling Brennerkopf
GB2299399A (en) * 1995-03-25 1996-10-02 Rolls Royce Plc Variable geometry air-fuel injector

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1420202A (en) * 1972-03-16 1976-01-07 Stone Platt Crawley Ld Combustion chambers
EP1497589B1 (fr) 2002-04-23 2015-03-11 WS-Wärmeprozesstechnik GmbH Chambre de combustion avec oxydation sans flamme
EP1995515A1 (fr) 2007-05-23 2008-11-26 WS-Wärmeprozesstechnik GmbH Fonctionnement FLOX pris en charge et son brûleur
DE102012216080A1 (de) * 2012-08-17 2014-02-20 Dürr Systems GmbH Brenner
DE102015226079A1 (de) * 2015-12-18 2017-06-22 Dürr Systems Ag Brennkammervorrichtung und Gasturbinenvorrichtung
DE102016118633A1 (de) 2016-09-30 2018-04-05 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR) Brennerkopf, Brennersystem und Verwendung des Brennersystems
DE102016118632A1 (de) 2016-09-30 2018-04-05 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR) Brennkammersystem, Verwendung eines Brennkammersystems mit einer angeschlossenen Turbine und Verfahren zur Durchführung eines Verbrennungsprozesses

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
LI, G.GUTMARK, E. J.STANKOVIC, D.OVERMAN, N.CORNWELL, M.FUCHS, L.MILOSAVLJEVIC, V.: "Experimental Study of Flameless Combustion in Gas Turbine Combustors", 44TH AIAA, 9 January 2006 (2006-01-09)
ZANGER, J.MONZ, TAIGNER, M.: "Experimental Investigation of the Combustion Characteristics of a double-staged FLOX®-based Combustor on an Atmospheric and a Micro Gas Turbine Test Rig", PROCEEDINGS OF ASME TURBO EXPO, 15 June 2015 (2015-06-15)

Also Published As

Publication number Publication date
EP3699493B1 (fr) 2021-09-22
EP3534070A1 (fr) 2019-09-04
DE102018104543A1 (de) 2019-08-29
EP3534070B1 (fr) 2020-11-18

Similar Documents

Publication Publication Date Title
DE102014102777B4 (de) System mit Vielrohr-Brennstoffdüse mit mehreren Brennstoffinjektoren
DE102005039247B4 (de) Lufteinblasung mit fester konzentrischer Verdünnung und variabler Bypass-Strömung für Brenner
EP2156095B1 (fr) Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange
DE60113620T2 (de) Düse für Gasbrenner und Verfahren zum Kühlen derselben
DE102005024062B4 (de) Brennerrohr und Verfahren zum Mischen von Luft und Gas in einem Gasturbinentriebwerk
DE69930455T2 (de) Gasturbinenbrennkammer
DE60032663T2 (de) Verkokungbeständige Kraftstoffeinspritzdüse
DE69306291T2 (de) Einteiliger Aufsatz für eine Dualringbrennkammer
EP3559551B1 (fr) Dispositif de mélange et tête de brûleur pour un brûleur à émission de nox réduite
CH701144B1 (de) Gasturbine mit Befestigung für Brennstoffdüse.
DE102018110969A1 (de) Dual-Brennstoff-Injektoren und Verfahren zur Verwendung in einer Gasturbinenbrennkammer
DE102014103083A1 (de) System und Verfahren zur Luftkonditionierung auf Rohrniveau
DE102009003450A1 (de) Brennstoffdüse für eine Gasturbine und Verfahren zur Herstellung derselben
DE2912103C2 (de) Brenner für ein Gasturbinentriebwerk
DE69306290T2 (de) Geteilter Mittelkörper für eine Ringbrennkammer
DE102011000589A1 (de) Axial gestufte Vormischbrennkammer
DE112013007579T5 (de) Flüssigbrennstoffpatrone für eine Brennstoffdüse
DE102017113687A1 (de) Pilotvormischdüse und Kraftstoffdüsenbaugruppe
EP2808611B1 (fr) Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion
EP3301370B1 (fr) Tête de brûleur, système de brûleur et utilisation du système de brûleur dans la chambre de combustion d'une turbine à gaz
EP3699493B1 (fr) Système de chambre de combustion et dispositif de micro-turbine à gaz
DE102011056542A1 (de) Zapfenlose sekundäre Brennstoffdüse
EP2462379B1 (fr) Stabilisation de la flamme d'un brûleur
EP2372245A1 (fr) Brûleur destiné à la stabilisation de la combustion d'une turbine à gaz ainsi que procédé
DE102017120370B4 (de) Brennerkopf, Brennersystem und Verfahren zum Betreiben des Brennersystems

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

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20200304

AC Divisional application: reference to earlier application

Ref document number: 3534070

Country of ref document: EP

Kind code of ref document: P

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

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20201211

RBV Designated contracting states (corrected)

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

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: 20210525

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

AC Divisional application: reference to earlier application

Ref document number: 3534070

Country of ref document: EP

Kind code of ref document: P

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: DE

Ref legal event code: R096

Ref document number: 502019002351

Country of ref document: DE

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: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 1432617

Country of ref document: AT

Kind code of ref document: T

Effective date: 20211015

REG Reference to a national code

Ref country code: FI

Ref legal event code: FGE

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NO

Ref legal event code: T2

Effective date: 20210922

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20210922

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

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: 20210922

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: 20211222

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: 20210922

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: 20210922

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

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: 20210922

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: 20211223

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: 20220122

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: 20210922

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: 20210922

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: 20220124

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: 20210922

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: 20210922

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: 20210922

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: 20210922

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: 20210922

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: 20210922

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502019002351

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: 20210922

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: 20220623

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: 20210922

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: 20220218

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: 20210922

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

Ref country code: IE

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

Effective date: 20220218

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

Ref country code: FI

Payment date: 20231228

Year of fee payment: 6

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

Ref country code: AT

Payment date: 20240126

Year of fee payment: 6

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

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: 20210922

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: 20210922

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: 20210922

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

Ref country code: DE

Payment date: 20240109

Year of fee payment: 6

Ref country code: CH

Payment date: 20240301

Year of fee payment: 6

Ref country code: GB

Payment date: 20240111

Year of fee payment: 6

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: 20190218

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

Ref country code: SE

Payment date: 20240208

Year of fee payment: 6

Ref country code: NO

Payment date: 20240126

Year of fee payment: 6

Ref country code: IT

Payment date: 20240209

Year of fee payment: 6

Ref country code: FR

Payment date: 20240108

Year of fee payment: 6

Ref country code: BE

Payment date: 20240110

Year of fee payment: 6

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: 20210922