EP4019840A1 - Brennkammereinheit für eine gasturbinenanordnung, gasturbinenanordnung und verfahren zur steuerung der kraftstoffeinspritzung in einer brennkammer einer gasturbinenanordnung - Google Patents
Brennkammereinheit für eine gasturbinenanordnung, gasturbinenanordnung und verfahren zur steuerung der kraftstoffeinspritzung in einer brennkammer einer gasturbinenanordnung Download PDFInfo
- Publication number
- EP4019840A1 EP4019840A1 EP20217211.0A EP20217211A EP4019840A1 EP 4019840 A1 EP4019840 A1 EP 4019840A1 EP 20217211 A EP20217211 A EP 20217211A EP 4019840 A1 EP4019840 A1 EP 4019840A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustor
- injection
- air
- fuel
- injection units
- 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
Links
- 238000002347 injection Methods 0.000 title claims abstract description 118
- 239000007924 injection Substances 0.000 title claims abstract description 118
- 239000000446 fuel Substances 0.000 title claims abstract description 78
- 238000000034 method Methods 0.000 title description 2
- 238000002485 combustion reaction Methods 0.000 claims abstract description 29
- 230000035515 penetration Effects 0.000 claims description 7
- 238000004891 communication Methods 0.000 claims description 6
- 239000003570 air Substances 0.000 description 64
- 230000010349 pulsation Effects 0.000 description 6
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 230000010355 oscillation Effects 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 238000013016 damping Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000009828 non-uniform distribution Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- 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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00013—Reducing thermo-acoustic vibrations by active means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03341—Sequential combustion chambers or burners
Definitions
- the present invention relates to a combustor unit for a gas turbine assembly and to a gas turbine assembly, in particular of a power plant.
- the invention further relates to a method for controlling fuel injection in a combustor unit.
- a gas turbine assembly for power plants comprises a compressor, a combustor unit and a turbine.
- the compressor comprises an inlet, supplied with air, and a plurality of blades compressing the passing air.
- the compressed air leaving the compressor flows into a plenum, i.e. a closed volume, and from there into the combustor unit, where the compressed air is mixed with at least one fuel and combusted.
- the resulting hot gas leaves the combustor unit and is expanded in the turbine, producing mechanical work.
- gas turbine assemblies which comprise a combustor unit performing a sequential combustion cycle.
- a sequential combustor unit comprises two combustors in series, wherein each combustor is provided with a respective burner and combustion chamber. Following the main gas flow direction, the upstream combustor is called “premix” combustor and is fed by the compressed air. The downstream combustor is called “sequential” or “reheat” combustor and is fed by the hot gas leaving the first combustion chamber.
- this first configuration includes the compressor, the premix combustor, the high-pressure turbine, the reheat combustor and a low-pressure turbine.
- the premix and the reheat combustor are arranged directly one downstream the other inside a common casing, in particular a can-shaped casing, and no high-pressure turbine is used.
- a plurality of can combustors are provided, which are distributed around the turbine axis.
- Each reheat combustor is preferably provided with a reheat burner and a reheat combustion chamber into which the hot flow coming from the premix is discharged.
- a transition duct is arranged downstream the reheat combustion chamber and guides the hot gas leaving the reheat combustor toward the turbine.
- the reheat burner may include a plurality of identical injection units, which are circumferentially arranged about the reheat combustion chamber and are designed to uniformly inject fuel into the reheat combustion chamber.
- thermoacoustic pulsations which may exceed acceptable pulsation limits and undesirably restrict the gas turbine operational range.
- damping devices are not always effective and require space, not always available in all combustor assemblies.
- a combustor unit for a gas turbine assembly comprising a premix combustor and a reheat combustor, which are arranged in series along the gas flow direction;
- the reheat combustor comprising:
- Figure 1 is a schematic view of a gas turbine assembly 1 for power plants according to the present invention.
- Gas turbine assembly 1 comprises a compressor 2, a combustor assembly 3 and a turbine 4.
- Compressor 2 and turbine 4 have a common axis A and form respective sections of a rotor 5 rotatable about axis A.
- ambient air 6 enters compressor 2 and is compressed.
- Compressed air 7 leaves compressor 2 and enters a plenum 8, i.e. a volume defined by an outer casing 9.
- a plenum 8 i.e. a volume defined by an outer casing 9.
- compressed air 7 enters combustor assembly 3 that comprises a plurality of combustor units 10 annularly arranged around axis A.
- Combustor units 10 are often defined "can combustors". In combustor units 10 at least a fuel is injected, and the air/fuel mixture is ignited, producing hot gas 11 that is conveyed to turbine 4.
- each combustor unit 10 is housed in a respective portal hole of the outer casing 9 and has an axis B.
- Combustor unit 10 comprises, in series along gas flow M, a first or premix combustor 15, a second or reheat combustor 16 and a transition duct 19, which guides the hot gas leaving the reheat combustor 16 toward the turbine 4.
- premix combustor 15 comprises a premix burner 17 and a first combustion chamber 18.
- Reheat combustor 16 comprises a housing 20 defining a combustion chamber 23 and a reheat burner 22.
- the housing 20 is a double wall housing wherein a cooling interspace 24 (better visible in figures 3a-3c , 4a-4c , 5a-5c , 6a-6c ) is formed.
- the cooling interspace 24 is fed with air coming from the plenum 8.
- the housing 20 is arranged inside a casing 25, which substantially surrounds the housing 20 in order to create an air chamber 26, which is fed with the air coming from the plenum 8.
- reheat burner 22 comprises a plurality of injection units collectively referenced 27, and individually referenced 27a, 27b, 27c, 27d, etc.
- the plurality of injection units 27 is arranged around the reheat combustion chamber 23 and is fed with air and fuel.
- the plurality of injection units 27 is arranged circumferentially around the reheat combustion chamber 23.
- Each injection unit 27a, 27b, 27c, 27d, etc. engages a respective through hole 28 made in the housing 20.
- each injection unit 27a, 27b, 27c, 27d comprises a fuel supply line 30 and at least one fuel nozzle 31 in fluidic communication with the fuel supply line 30, an air supply line 29 and at least one air nozzle 32 in fluidic communication with the air supply line 29 and a conveying tube 33, wherein air and fuel coming from the at least one fuel nozzle 31 and air nozzle 32 are mixed.
- the conveying tube 33 extends along an axis C. In the non-limitative example here disclosed and illustrated, the conveying tube 33 extends from an inlet coinciding with the air nozzle 32 to an outlet 35 flowing into the reheat combustion chamber 23.
- the conveying tube 33 is cylindrical and is at least partially housed in the hole 28 of the housing 20
- the air supply line 29 comprises the air chamber 26, which surrounds the housing 20 and supplies all the air nozzles 32.
- the fuel supply line 30 comprises a fuel conduit 37 (schematically represented) and a fuel collector 38, preferably surrounding the inlet portion of the conveying tube 33.
- the fuel supplied to the fuel supply line 30 can be the same fuel supplied to the first combustor 15 or a different fuel.
- each injection unit 27a, 27b, 27c, 27d, 27e comprises a plurality of fuel nozzles 31, which are arranged along a substantially circumferential path extending on a plane orthogonal to axis C.
- At least one injection unit 27a of the plurality of injection units 27 is configured to inject fuel and air differently from the other injection units of the plurality of injection units 27.
- the injection unit 27a is configured to inject fuel and air according to a different equivalence ratio and/or to a different mixing between air and fuel and/or to a different penetration into the reheat combustion chamber 23 with respect to the others injection units 27b, 27c, 27d, 27e of the plurality of injection units 27.
- ⁇ QF / QA QF / QA STOICH as the ratio of the fuel-to-air ratio to the stoichiometric fuel-to-air ratio.
- mixing between air and fuel is intended the way of mixing the fuel and the air supplied to the injection unit (e.g. presence of vortex generators/deflectors and other means for controlling the mixing between fuel and air).
- the jet characteristic of the mixed air/fuel flow is intended the jet characteristic of the mixed air/fuel flow, which is injected into the reheat combustion chamber 23.
- the jet characteristic of the mixed air/fuel flow can depend on the jet momentum, the jet diameter, the jet angle, and the position at which the mixed air/fuel flow coming from the injection unit is injected in the reheat combustion chamber 23.
- FIGS 3a-3c it is represented a first embodiment of the present invention wherein at least the injection unit 27a has a conveying tube 33a having a tube length La different from the tube lengths Lb, Lc, Ld, Le of the conveying tubes 33b, 33c, 33d, 33e of the other injection units 27b, 27c, 27d, 27e.
- the tube length is measured along the axis C.
- the tube length La is greater than the tube lengths Lb, Lc, Ld, Le of the conveying tubes 33b, 33c, 33d, 33e of the other injection units 27b, 27c, 27d, 27e.
- the tube length La is greater than the depth of the housing 20.
- the tube lengths La, Lb, Lc, Ld, Le are different from each other in order to change the penetration depth of each injection unit 27.
- FIGS 4a-4c it is represented a second embodiment of the present invention, wherein at least the injection unit 27a has fuel nozzles 31a having a diameter Da different from the diameter Db, Dc, Dd, De of the fuel nozzles 31b, 31c, 31d, 31e of the other injection units 27b, 27c, 27d, 27e.
- fuel nozzles 31a have a diameter Da greater than the diameters Db, Dc, Dd, De of the fuel nozzles 31b, 31c, 31d of the other injection units 27b, 27c, 27d, 27e.
- the diameters Da, Db, Dc, Dd, De of the fuel nozzles 31a, 31b, 31c, 31d, 31e are different from each other in order to change the equivalence ratio and the mixing between air and fuel of each injection unit 27
- FIG. 5a-5c it is represented a third embodiment of the present invention, wherein at least the injection unit 27a has a conveying tube 33a having a tube width Wa different from the tube widths Wb, Wc, Wd, We of the conveying tubes 33b, 33c, 33d, 33e of the other injection units 27b, 27c, 27d, 27e.
- the tube width is measured along a direction orthogonal to axis C.
- the tube width Wa is smaller than the tube widths Wb, Wc, Wd, We of the conveying tubes 33b, 33c, 33d, 33e of the other injection units 27b, 27c, 27d, 27e.
- the tube widths Wa, Wb, Wc, Wd, We are different from each other in order to change the equivalence ratio and the mixing between air and fuel of each injection unit 27 and the penetration into the reheat combustion chamber 23.
- FIG. 6a-6c it is represented a fourth embodiment of the present invention, wherein at least the injection unit 27a has an air nozzle 32a having a passage section Aa different from the passage sections Ab, Ac, Ad, Ae of the air nozzles 32b, 32c, 32d, 32e of the other injection units 27b, 27c, 27d, 27e.
- air nozzle 32a has a passage section Aa smaller from the passage sections Ab, Ac, Ad, Ae of the air nozzles 32b, 32c, 32d, 32e of the other injection units 27b, 27c, 27d, 27e.
- air nozzle 32a is coupled to a metering plate 39 having a hole 40 whose passage section is the desired one Aa.
- the passage sections Aa, Ab, Ac, Ad, Ae of the air nozzles 32a, 32b, 32c, 32d, 32e of the injection units 27a, 27b, 27c, 27d, 27e are different from each other in order to change the equivalence ratio and the mixing between air and fuel of each injection unit 27
- conveying tubes 33a, 33b, 33c, 33d, 33e extend along an axis B which is substantially arranged radially with respect to the axis B of the combustor unit 10.
- At least one of the injection units 27a, 27b, 27c, 27d, 27e is provided with a conveying tube 33a, 33b, 33c, 33d, 33e extending along an axis which is not radially arranged.
- all the conveying tubes 33a, 33b, 33c, 33d, 33e extend along respective axis which are not radially arranged and are inclined differently from each other.
- At least one of the injection units 27a is provided with fuel nozzles 31a having a shape and/or a position different from the shapes and/or the positions of the other fuel nozzles 31b, 31c, 31d, 31e.
- the shapes and/or the positions of fuel nozzles 31a, 31b, 31c, 31d, 31e are different from each other in order to change the equivalence ratio and the mixing between air and fuel of each injection unit 27.
- the supply line 30 can be adjusted in order to supply a different fuel flow rate to at least one injection unit of the plurality of injection units 27.
- the passage section of the fuel conduit 37 of at least one injection unit 27a can be different from the passage section of the fuel conduits 37 of at least one injection units 37b, 37c, 37d, 37e.
- At least one injection unit of the plurality of injection units 27 is provided with a combination of the different features above described for each embodiment.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP20217211.0A EP4019840B1 (de) | 2020-12-24 | 2020-12-24 | Brennkammereinheit für eine gasturbinenanordnung |
CN202111561357.3A CN114754377A (zh) | 2020-12-24 | 2021-12-20 | 燃烧器单元、燃气涡轮组件和用于控制燃料喷射的方法 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP20217211.0A EP4019840B1 (de) | 2020-12-24 | 2020-12-24 | Brennkammereinheit für eine gasturbinenanordnung |
Publications (2)
Publication Number | Publication Date |
---|---|
EP4019840A1 true EP4019840A1 (de) | 2022-06-29 |
EP4019840B1 EP4019840B1 (de) | 2024-04-03 |
Family
ID=73943162
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20217211.0A Active EP4019840B1 (de) | 2020-12-24 | 2020-12-24 | Brennkammereinheit für eine gasturbinenanordnung |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP4019840B1 (de) |
CN (1) | CN114754377A (de) |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009078891A2 (en) * | 2007-09-14 | 2009-06-25 | Siemens Energy, Inc. | Secondary fuel delivery system |
WO2013022367A1 (en) * | 2011-08-11 | 2013-02-14 | General Electric Company | System for injecting fuel in a gas turbine engine |
EP2835516A1 (de) * | 2013-08-08 | 2015-02-11 | Alstom Technology Ltd | Gasturbine mit verbessertem Teillast-Emissionsverhalten |
US20160305337A1 (en) * | 2015-04-15 | 2016-10-20 | General Electric Company | Systems and methods for control of combustion dynamics in combustion system |
EP3369995A1 (de) * | 2017-03-02 | 2018-09-05 | Ansaldo Energia Switzerland AG | Mixer |
EP3486568A1 (de) * | 2017-11-20 | 2019-05-22 | Ansaldo Energia Switzerland AG | Verfahren zur steuerung der kraftstoffeinspritzung in einem nachbrenner für eine brennkammereinheit einer gasturbine |
US20200378604A1 (en) * | 2019-05-30 | 2020-12-03 | Doosan Heavy Industries & Construction Co., Ltd. | Combustor with axial fuel staging system and gas turbine having the same |
-
2020
- 2020-12-24 EP EP20217211.0A patent/EP4019840B1/de active Active
-
2021
- 2021-12-20 CN CN202111561357.3A patent/CN114754377A/zh active Pending
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009078891A2 (en) * | 2007-09-14 | 2009-06-25 | Siemens Energy, Inc. | Secondary fuel delivery system |
WO2013022367A1 (en) * | 2011-08-11 | 2013-02-14 | General Electric Company | System for injecting fuel in a gas turbine engine |
EP2835516A1 (de) * | 2013-08-08 | 2015-02-11 | Alstom Technology Ltd | Gasturbine mit verbessertem Teillast-Emissionsverhalten |
US20160305337A1 (en) * | 2015-04-15 | 2016-10-20 | General Electric Company | Systems and methods for control of combustion dynamics in combustion system |
EP3369995A1 (de) * | 2017-03-02 | 2018-09-05 | Ansaldo Energia Switzerland AG | Mixer |
EP3486568A1 (de) * | 2017-11-20 | 2019-05-22 | Ansaldo Energia Switzerland AG | Verfahren zur steuerung der kraftstoffeinspritzung in einem nachbrenner für eine brennkammereinheit einer gasturbine |
US20200378604A1 (en) * | 2019-05-30 | 2020-12-03 | Doosan Heavy Industries & Construction Co., Ltd. | Combustor with axial fuel staging system and gas turbine having the same |
Also Published As
Publication number | Publication date |
---|---|
CN114754377A (zh) | 2022-07-15 |
EP4019840B1 (de) | 2024-04-03 |
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