EP2927594B1 - Chambre de combustion d'une turbine à gaz - Google Patents

Chambre de combustion d'une turbine à gaz Download PDF

Info

Publication number
EP2927594B1
EP2927594B1 EP15158442.2A EP15158442A EP2927594B1 EP 2927594 B1 EP2927594 B1 EP 2927594B1 EP 15158442 A EP15158442 A EP 15158442A EP 2927594 B1 EP2927594 B1 EP 2927594B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
slot
rear part
front part
wall
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
EP15158442.2A
Other languages
German (de)
English (en)
Other versions
EP2927594A2 (fr
EP2927594A3 (fr
Inventor
Carsten Dr.-Ing. Clemen
Thomas Dr.-Ing. Dörr
Sebastian Dr.-Ing. Bake
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2927594A2 publication Critical patent/EP2927594A2/fr
Publication of EP2927594A3 publication Critical patent/EP2927594A3/fr
Application granted granted Critical
Publication of EP2927594B1 publication Critical patent/EP2927594B1/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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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

Definitions

  • the invention relates to a combustion chamber of a gas turbine with an outer combustion chamber wall and attached to the inside of the outer combustion chamber wall shingles.
  • the supply of mixed air serves to optimize the combustion in the combustion chamber.
  • the best possible blocking and mixing of the fuel gases with the admixed air should take place in order to control and minimize NOx emissions.
  • GB 543 918 A From the GB 543 918 A is a combustion chamber previously known, which is constructed of conical, nested elements. The conical mating surfaces form a small gap through which cooling medium can be inserted.
  • GB 543 918 A discloses a combustion chamber according to the preamble of claim 1. Other similar combustion chambers are characterized by US 4,773,227 A . FR 1 036 218 A and DE 11 79 422 B disclosed.
  • the invention has for its object to provide a combustion chamber of a gas turbine, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and allows optimized supply of mixed air.
  • the combustion chamber in a central region, with respect to the flow direction, a extending around the entire circumference of the combustion chamber wall slot which divides the outer combustion chamber wall and the shingles and can be supplied by the mixed air.
  • the invention thus results in the decisive advantage that the NOx emissions can be reduced in the maximum possible way by the optimized supply of mixed air. It is particularly favorable that the circumferential slot can be provided with an equal effective flow area for air mixing, as known from the prior art Zumischlöcher.
  • the combustion chamber is divided by the slot in a front part and a rear part.
  • front and rear part always refers to the direction of flow through the combustion chamber.
  • the slit provided in accordance with the invention may be formed in a straight line around the entire circumference, that is, with a constant width. It is also possible to make this wavy, be it with the same width or variable width. As a result, an adaptation to the arrangement of the individual, distributed around the circumference of the annular combustion chamber burner is possible.
  • the slot can be provided with a width which varies around the circumference, for example by bulges and constrictions in the circumferential direction.
  • the storage of the shingles on the outer combustion chamber wall can be done in different ways. It is possible to use bolts for this, as shown in the prior art. However, it is also possible to manufacture the front and rear parts of the combustion chamber wall in one piece by means of additive methods (laser deposition welding method or the like). In any case, it is ensured that between the shingle and the outer combustion chamber wall there is a cooling air gap in order to provide in a known manner an impingement cooling and an effusion cooling can.
  • the inventive construction can also be applied for single-walled combustion chambers (without shingles).
  • the front part and the rear part of the combustion chamber wall can change their distance during thermal expansion and thermal contraction.
  • the width of the slot may be greater by a greater distance of the side walls of the slot, as in the hot state.
  • the supply of admixed air is increased in the cold state of the combustion chamber, at the same time less cooling air for the combustion chamber walls.
  • the circumferential slot will have a smaller width.
  • the gas turbine engine 110 is a generalized example of a turbomachine, in which the invention can be applied.
  • the engine 110 is formed in a conventional manner and comprises in succession an air inlet 111, a fan 112 circulating in a housing, a medium pressure compressor 113, a high pressure compressor 114, a combustion chamber 115, a high pressure turbine 116, a medium pressure turbine 117 and a low pressure turbine 118 and a Exhaust nozzle 119, which are all arranged around a central engine center axis 101.
  • the intermediate pressure compressor 113 and the high pressure compressor 114 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 120, commonly referred to as stator vanes, which are radially inwardly of the engine casing 121 in an annular manner Flow channel through the compressors 113, 114 protrude.
  • the compressors further include an array of compressor blades 122 projecting radially outward from a rotatable drum or disc 125 coupled to hubs 126 of high pressure turbine 116 and intermediate pressure turbine 117, respectively.
  • the turbine sections 116, 117, 118 have similar stages, comprising an array of fixed vanes 123 projecting radially inward from the housing 121 into the annular flow passage through the turbines 116, 117, 118, and a downstream array of turbine blades 124, projecting outwardly from a rotatable hub 126.
  • the compressor drum or compressor disk 125 and the vanes 122 disposed thereon and the turbine rotor hub 126 and turbine blades 124 disposed thereon rotate about the engine centerline 101 during operation.
  • the Fig. 2 shows a combustion chamber according to the prior art in a simplified sectional view.
  • the combustion chamber has a combustion chamber outer wall 1 and a heat shield 2, a combustion chamber head 3 and a burner seal 4.
  • shingles 9 are arranged, which are integrally connected with studs 7, which in turn are secured from the outside by means of nuts 8.
  • the presentation of impingement cooling holes and effusion cooling holes was omitted for the sake of simplicity.
  • the combustion chamber In the front region, the combustion chamber in a known manner on a top plate 6.
  • a plurality of individual, discrete admixing holes 5 are formed in the combustion chamber outer wall 1 and the shingles 9, through which mixing air is introduced.
  • the storage of the combustion chamber by means of an outer Brennscharms and an inner Brennscharms 11 and an outer Brennschflansches 12 and an inner Brennschlansches 13.
  • the reference numeral 14 denotes an outer combustion chamber housing, while an inner combustion chamber housing is provided with the reference numeral 15.
  • an outer turbine housing 16 and an inner turbine housing 17 are shown schematically.
  • combustion chamber is mounted at its front part and its rear part in each case by means of separate outer combustion chamber arms 10. These have flow openings 20 in order to ensure an optimized cooling air flow.
  • the two outer combustion chamber arms 10 are fastened with their outer combustion chamber flanges 12 to the outer combustion chamber housing 14 and the outer turbine housing 16.
  • the inner attachment is analogous to the known from the prior art embodiment, in addition, a connection 21 between the combustion chamber and the inner combustion chamber 11 takes place.
  • the Fig. 6 to 8 show in a schematic view design variants of the mixing slot 18.
  • Die Fig. 6 shows a design variant in which the Admixing slot 18 is formed in a straight line with the same width.
  • Fig. 7 a uniform width of the admixing slot 18 is provided. However, this is formed wavy around the circumference.
  • the Fig. 8 shows a design variant of the admixing slot 18, in which this has around the circumference wider areas and bottlenecks.
  • the Fig. 9 to 12 show a development in analog representation too Fig. 5 , It shows the Fig. 9 a cold or colder operating condition while the Fig. 10 shows a hot operating condition.
  • a larger width of the admixing slot 18 is present, as in the FIGS. 11 and 12 analogous to the embodiments of 8 and 6 is shown in the left half of the picture.
  • the parts of the combustion chamber expand, as shown by the arrows 25. This reduces the width of the admixing slot 18. This is compared in the FIGS. 11 and 12 shown in the right half of the picture.
  • FIGS. 13 and 14 show simplified sectional views in analogous representation to the FIGS. 9 and 10 .
  • the embodiment of the FIGS. 13 and 14 an embodiment in which the walls of the portions of the combustion chamber overlap, as in the FIGS. 15 and 16 is shown.
  • the two overlapping areas are each provided with a slot or with holes.
  • the overlap results in the cold state ( Fig. 15 ) a smaller overlap, which results in a total of a smaller width of the admixing slot 18.
  • a hot operating condition Fig. 16
  • the overlap is greater, as seen from the upper half of the Fig. 16 is apparent.
  • the slot geometry in the circumferential direction can be rectilinear or wavy or formed with a changing cross section.
  • the Fig. 13 to 16 thus, an embodiment which, in contrast to the embodiment of the Fig. 9 to 12 acts as the width of the mixing slot widens from cold to hot operating condition.
  • the invention thus enables an ideal blocking / mixing of the admixing air 19 with the fuel gases in the combustion chamber volume 23.
  • the circumferential slot preferably has the same effective flow cross-section or the same through-flow area as comparable admixing holes 5 according to the prior art (see FIG. Fig. 2 ).
  • the combustion chamber according to the invention divides into two parts. Therefore, according to the invention, a suspension concept is described in which the parts of the combustion chamber are suitably fixed to the inner and outer combustion chamber housings and to the turbine housing. This is done, as explained, by additional combustion chamber arms 12. These can be attached in any way to the combustion chamber or connected to this, for example by one-piece design, by welding, by screwing or in a similar manner.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (6)

  1. Chambre de combustion d'une turbine à gaz, sachant que la chambre de combustion présente, dans une zone médiane par rapport au sens d'écoulement, une fente de mélange (18) s'étendant tout autour de la circonférence de la chambre de combustion et divisant la chambre de combustion pour amener de l'air de mélange dans une partie avant et une partie arrière, sachant que la partie avant de la chambre de combustion et la partie arrière de la chambre de combustion sont montées séparément, caractérisée en ce que la chambre de combustion présente une paroi extérieure de la chambre de combustion (1) avec des bardeaux (9) fixés sur sa face intérieure, et que la partie avant et la partie arrière de la chambre de combustion présentent des parois, sachant que des zones de ces parois se chevauchent et sachant que les zones des parois se chevauchant sont pourvues chacune d'une fente ou de trous.
  2. Chambre de combustion d'une turbine à gaz avec une paroi de chambre de combustion (1) de conception à simple paroi, sachant que la chambre de combustion présente, dans une zone médiane par rapport au sens d'écoulement, une fente de mélange (18) s'étendant tout autour de la circonférence de la chambre de combustion et divisant la paroi de la chambre de combustion (1) pour amener de l'air de mélange dans une partie avant et une partie arrière, sachant que la partie avant de la chambre de combustion et la partie arrière de la chambre de combustion sont montées séparément, caractérisée en ce que la partie avant et la partie arrière de la chambre de combustion présentent des parois, sachant que des zones de ces parois se chevauchent et sachant que les zones des parois se chevauchant sont pourvues chacune d'une fente ou de trous.
  3. Chambre de combustion selon une des revendications n° 1 ou n° 2, caractérisée en ce que la fente (18) est conçue en ligne droite ou ondulée ou avec une section changeante sur toute la circonférence.
  4. Chambre de combustion selon une des revendications n° 1 à n° 3, caractérisée en ce que la partie avant de la chambre de combustion et la partie arrière de la chambre de combustion sont montées au moyen de bras de chambre de combustion (10, 11) présentant des ouvertures de passage (20).
  5. Chambre de combustion selon une des revendications n° 1 à n° 4, caractérisée en ce que le montage de la partie avant et de la partie arrière de la chambre de combustion est conçu pour modifier la largeur de la fente (18) en cas de dilatation ou de contraction thermique.
  6. Chambre de combustion selon la revendication n° 5, caractérisée en ce que la largeur de la fente (18) est variable.
EP15158442.2A 2014-03-11 2015-03-10 Chambre de combustion d'une turbine à gaz Active EP2927594B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102014204482.0A DE102014204482A1 (de) 2014-03-11 2014-03-11 Brennkammer einer Gasturbine

Publications (3)

Publication Number Publication Date
EP2927594A2 EP2927594A2 (fr) 2015-10-07
EP2927594A3 EP2927594A3 (fr) 2016-02-17
EP2927594B1 true EP2927594B1 (fr) 2019-05-08

Family

ID=52633152

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15158442.2A Active EP2927594B1 (fr) 2014-03-11 2015-03-10 Chambre de combustion d'une turbine à gaz

Country Status (3)

Country Link
US (1) US9366436B2 (fr)
EP (1) EP2927594B1 (fr)
DE (1) DE102014204482A1 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3045137B1 (fr) * 2015-12-11 2018-05-04 Safran Aircraft Engines Chambre de combustion de turbomachine
US10935235B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US10655853B2 (en) * 2016-11-10 2020-05-19 United Technologies Corporation Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor
US10935236B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US11035251B2 (en) * 2019-09-26 2021-06-15 General Electric Company Stator temperature control system for a gas turbine engine
US20220390111A1 (en) * 2021-06-07 2022-12-08 General Electric Company Combustor for a gas turbine engine
US20220390112A1 (en) * 2021-06-07 2022-12-08 General Electric Company Combustor for a gas turbine engine
US11959643B2 (en) 2021-06-07 2024-04-16 General Electric Company Combustor for a gas turbine engine
US20230144971A1 (en) * 2021-11-11 2023-05-11 General Electric Company Combustion liner
CN115046226B (zh) * 2022-08-11 2022-11-04 成都中科翼能科技有限公司 一种燃气轮机火焰筒支撑定位结构
US11747019B1 (en) * 2022-09-02 2023-09-05 General Electric Company Aerodynamic combustor liner design for emissions reductions

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB543918A (en) * 1939-09-29 1942-03-19 Bbc Brown Boveri & Cie Improvements and relating to combustion chambers
US2699648A (en) * 1950-10-03 1955-01-18 Gen Electric Combustor sectional liner structure with annular inlet nozzles
FR1036218A (fr) * 1951-04-26 1953-09-04 Lucas Ltd Joseph Perfectionnements à la fabrication de corps tubulaires
DE1179422B (de) * 1959-01-29 1964-10-08 Rolls Royce Brennkammer, insbesondere fuer Strahltriebwerke
GB1256066A (en) 1967-11-10 1971-12-08 Lucas Industries Ltd Flame tubes for gas turbine engines
DE2416909A1 (de) 1974-04-06 1975-10-16 Daimler Benz Ag Betriebsverfahren fuer eine gasturbinenanlage zur abgasverbesserung und entsprechende gasturbinenanlage
US4138842A (en) * 1975-11-05 1979-02-13 Zwick Eugene B Low emission combustion apparatus
FR2472082A1 (fr) * 1979-12-19 1981-06-26 France Etat Perfectionnements apportes aux moteurs a combustion interne suralimentes, notamment aux moteurs diesel
DE3209135A1 (de) * 1982-03-12 1983-09-15 Kraftwerk Union AG, 4330 Mülheim Gasturbinenbrennkammer
US4773227A (en) 1982-04-07 1988-09-27 United Technologies Corporation Combustion chamber with improved liner construction
US4567730A (en) * 1983-10-03 1986-02-04 General Electric Company Shielded combustor
DE4034711C1 (en) * 1990-11-01 1992-02-27 Daimler-Benz Aktiengesellschaft, 7000 Stuttgart, De Secondary air feed control for gas turbine burner flame tube - has jacketed tube with spherical surface in region with air ports with throttle ring
US5461866A (en) * 1994-12-15 1995-10-31 United Technologies Corporation Gas turbine engine combustion liner float wall cooling arrangement
GB2405197B (en) * 2003-08-16 2005-09-28 Rolls Royce Plc Fuel injector
FR2897418B1 (fr) * 2006-02-10 2013-03-01 Snecma Chambre de combustion annulaire d'une turbomachine
DE102006042124B4 (de) * 2006-09-07 2010-04-22 Man Turbo Ag Gasturbinenbrennkammer
DE102006048842B4 (de) * 2006-10-13 2019-10-10 Man Energy Solutions Se Brennkammer für eine Gasturbine
RU2010101978A (ru) * 2010-01-15 2011-07-20 Дженерал Электрик Компани (US) Соединительный узел для газовой турбины

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
DE102014204482A1 (de) 2015-09-17
EP2927594A2 (fr) 2015-10-07
US20150260403A1 (en) 2015-09-17
US9366436B2 (en) 2016-06-14
EP2927594A3 (fr) 2016-02-17

Similar Documents

Publication Publication Date Title
EP2927594B1 (fr) Chambre de combustion d'une turbine à gaz
EP3239612B1 (fr) Chambre de combustion de turbine à gaz
EP2918913B1 (fr) Chambre de combustion d'une turbine à gaz
EP3115691A1 (fr) Chambre de combustion de turbines a gaz comprenant un stator de turbine et son procede de fabrication
EP2693120A2 (fr) Chambre de combustion de turbine à gaz avec orifices d'air de mélange et éléments de guidage d'air de construction modulaire
EP2921778A1 (fr) Chambre de combustion d'une turbine à gaz
DE102015225505A1 (de) Wand eines mittels Kühlluft zu kühlenden Bauteils, insbesondere einer Gasturbinenbrennkammerwand
DE102014204468A1 (de) Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung
EP3369996A1 (fr) Dispositif formant bardeau de la chambre de combustion d'une turbine à gaz
EP2818643B1 (fr) Dispositif d'étanchéité et turbomachine
EP2799776A1 (fr) Joint de brûleur pour tête de chambre de combustion de turbines à gaz et bouclier thermique
EP2730844B1 (fr) Bardeau de chambre de combustion d'une turbine à gaz et son procédé de fabrication
EP2966352A1 (fr) Chambre de combustion d'une turbine a gaz dotee de tete de chambre de combustion vissee
EP2918914A1 (fr) Chambre de combustion d'une turbine à gaz
EP2818724B1 (fr) Turbomachine et procédé
EP3321589B1 (fr) Buse de carburant d'une turbine à gaz dotée du générateur de tourbillons
EP2886807B1 (fr) Bride de liaison refroidie d'une turbine à gaz
EP2725203B1 (fr) Conduite d'air froid dans une structure de boîtier d'une turbomachine
EP2871418B1 (fr) Chambre de combustion d'une turbine à gaz et son procédé de fabrication
DE102016212649A1 (de) Brennerdichtung einer Gasturbine und Verfahren zu deren Herstellung
EP2980481A1 (fr) Turbine à gaz d'avion avec un joint d'étanchéité pour l'étanchéificiation d'une bougie d'allumage au niveau de la paroi de la chambre de combustion d'une turbine à gaz
EP3034944A1 (fr) Chambre de combustion de turbines a gaz a epaisseur de paroi variable
EP2840230A1 (fr) Rotor pour une turbomachine thermique
EP3179169B1 (fr) Procédé de montage d'une chambre de combustion d'une turbine à gaz
DE102014222320A1 (de) Brennkammerwand einer Gasturbine mit Kühlung für einen Mischluftlochrand

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

AK Designated contracting states

Kind code of ref document: A2

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

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 502015008947

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F23R0003000000

Ipc: F23R0003060000

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

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

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/06 20060101AFI20160111BHEP

Ipc: F23R 3/00 20060101ALI20160111BHEP

Ipc: F23R 3/60 20060101ALI20160111BHEP

17P Request for examination filed

Effective date: 20160225

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

17Q First examination report despatched

Effective date: 20160922

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

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: 20181026

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

Ref country code: AT

Ref legal event code: REF

Ref document number: 1130738

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190515

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502015008947

Country of ref document: DE

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: NL

Ref legal event code: MP

Effective date: 20190508

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

Ref country code: 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: 20190808

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: 20190508

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: 20190508

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: 20190908

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: 20190508

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: 20190508

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: 20190508

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: 20190508

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: 20190508

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

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: 20190809

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: 20190508

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: 20190808

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: 20190508

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

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: 20190508

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: 20190508

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: 20190508

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: 20190508

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: 20190508

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502015008947

Country of ref document: DE

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

Ref country code: IT

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

Effective date: 20190508

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: 20190508

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

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: 20190508

26N No opposition filed

Effective date: 20200211

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

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: 20190508

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

Ref country code: GB

Payment date: 20200327

Year of fee payment: 6

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: 20190508

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: 20190508

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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: 20200310

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: IE

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

Effective date: 20200310

Ref country code: LI

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

Effective date: 20200331

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

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1130738

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200310

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: 20200310

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

Effective date: 20210310

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: 20210310

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: 20190508

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: 20190508

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: 20190508

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: 20190908

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

Ref country code: FR

Payment date: 20230323

Year of fee payment: 9

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

Ref country code: DE

Payment date: 20230328

Year of fee payment: 9

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

Effective date: 20230528