EP1484553A3 - Burner for a gas turbine combustor - Google Patents

Burner for a gas turbine combustor Download PDF

Info

Publication number
EP1484553A3
EP1484553A3 EP04090216A EP04090216A EP1484553A3 EP 1484553 A3 EP1484553 A3 EP 1484553A3 EP 04090216 A EP04090216 A EP 04090216A EP 04090216 A EP04090216 A EP 04090216A EP 1484553 A3 EP1484553 A3 EP 1484553A3
Authority
EP
European Patent Office
Prior art keywords
burner
gas turbine
air
turbine combustor
ring
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
EP04090216A
Other languages
German (de)
French (fr)
Other versions
EP1484553A2 (en
EP1484553B1 (en
Inventor
Ralf Sebastian Von Der Bank
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 EP1484553A2 publication Critical patent/EP1484553A2/en
Publication of EP1484553A3 publication Critical patent/EP1484553A3/en
Application granted granted Critical
Publication of EP1484553B1 publication Critical patent/EP1484553B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • 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
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/20—Flame lift-off / stability
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00018—Means for protecting parts of the burner, e.g. ceramic lining outside of the flame tube

Landscapes

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

Abstract

Bei einem Brenner für eine Gasturbinenbrennkammer, der einen Magervormischbrenner mit zentral integriertem Stützbrenner umfasst, ist ein die Zerstäuberdüse (10) des Stützbrenners aufnehmender Kernluft-Ringkanal (11) konzentrisch von einem das magere Luft-Brennstoff-Gemisch erzeugenden Hauptluft-Ringkanal (4) umgeben. Im aneinander grenzenden Mündungsbereich des Hauptluft- und des Kernluft-Ringkanals befindet sich ein von den Brenngasen erhitzter Flammenstabilisierungsring (13) mit sich zur Brennkammer (5) hin konisch erweiternder Querschnittsfläche zur Erzeugung einer von dem Flammenstabilisierungsring ausgehenden, etwa hohlzylindrisch geformten Heißgas-Rezirkulationszone (17), die in jedem Betriebszustand der Gasturbine eine stabile Flammeausbildung gewährleistet.

Figure imgaf001
In a burner for a gas turbine combustor comprising a lean burn burner with a centrally integrated support burner, a core air ring passage (11) receiving the atomizer nozzle (10) of the support burner is concentrically surrounded by a main air ring passage (4) producing the lean air-fuel mixture , In the adjoining mouth region of the main air and the core air annular channel is a heated by the fuel gases flame stabilizing ring (13) with the combustion chamber (5) conically widening cross-sectional area for generating an outgoing from the flame stabilizing ring, approximately hollow cylindrical shaped hot gas recirculation zone (17 ), which ensures a stable flame formation in each operating state of the gas turbine.
Figure imgaf001
EP04090216A 2003-06-06 2004-06-02 Burner for a gas turbine combustor Expired - Fee Related EP1484553B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10326720 2003-06-06
DE10326720A DE10326720A1 (en) 2003-06-06 2003-06-06 Burner for a gas turbine combustor

Publications (3)

Publication Number Publication Date
EP1484553A2 EP1484553A2 (en) 2004-12-08
EP1484553A3 true EP1484553A3 (en) 2006-11-29
EP1484553B1 EP1484553B1 (en) 2011-09-28

Family

ID=33154610

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04090216A Expired - Fee Related EP1484553B1 (en) 2003-06-06 2004-06-02 Burner for a gas turbine combustor

Country Status (3)

Country Link
US (1) US7621131B2 (en)
EP (1) EP1484553B1 (en)
DE (1) DE10326720A1 (en)

Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6986255B2 (en) * 2002-10-24 2006-01-17 Rolls-Royce Plc Piloted airblast lean direct fuel injector with modified air splitter
AU2003253274A1 (en) * 2003-07-25 2005-02-14 Ansaldo Energia S.P.A. Gas turbine burner
US7308793B2 (en) * 2005-01-07 2007-12-18 Power Systems Mfg., Llc Apparatus and method for reducing carbon monoxide emissions
US7779636B2 (en) * 2005-05-04 2010-08-24 Delavan Inc Lean direct injection atomizer for gas turbine engines
US7624576B2 (en) * 2005-07-18 2009-12-01 Pratt & Whitney Canada Corporation Low smoke and emissions fuel nozzle
US8062027B2 (en) * 2005-08-11 2011-11-22 Elster Gmbh Industrial burner and method for operating an industrial burner
DE102005062079A1 (en) * 2005-12-22 2007-07-12 Rolls-Royce Deutschland Ltd & Co Kg Magervormic burner with a nebulizer lip
US7836677B2 (en) * 2006-04-07 2010-11-23 Siemens Energy, Inc. At least one combustion apparatus and duct structure for a gas turbine engine
US7631499B2 (en) * 2006-08-03 2009-12-15 Siemens Energy, Inc. Axially staged combustion system for a gas turbine engine
US8393891B2 (en) * 2006-09-18 2013-03-12 General Electric Company Distributed-jet combustion nozzle
DE102006051286A1 (en) * 2006-10-26 2008-04-30 Deutsches Zentrum für Luft- und Raumfahrt e.V. Combustion device, has combustion chamber with combustion space and air injecting device including multiple nozzles arranged on circular line, where nozzles have openings formed as slotted holes in combustion space
DE102007043626A1 (en) 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine lean burn burner with fuel nozzle with controlled fuel inhomogeneity
US20090211255A1 (en) * 2008-02-21 2009-08-27 General Electric Company Gas turbine combustor flame stabilizer
EP2107311A1 (en) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Size scaling of a burner
EP2107313A1 (en) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Fuel staging in a burner
US8061142B2 (en) * 2008-04-11 2011-11-22 General Electric Company Mixer for a combustor
US8683804B2 (en) * 2009-11-13 2014-04-01 General Electric Company Premixing apparatus for fuel injection in a turbine engine
US9027350B2 (en) * 2009-12-30 2015-05-12 Rolls-Royce Corporation Gas turbine engine having dome panel assembly with bifurcated swirler flow
DE102010019773A1 (en) 2010-05-07 2011-11-10 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner a gas turbine engine with flow guide
US8973368B2 (en) 2011-01-26 2015-03-10 United Technologies Corporation Mixer assembly for a gas turbine engine
US8312724B2 (en) 2011-01-26 2012-11-20 United Technologies Corporation Mixer assembly for a gas turbine engine having a pilot mixer with a corner flame stabilizing recirculation zone
US9920932B2 (en) 2011-01-26 2018-03-20 United Technologies Corporation Mixer assembly for a gas turbine engine
JP5773342B2 (en) * 2011-06-03 2015-09-02 川崎重工業株式会社 Fuel injection device
JP5772245B2 (en) 2011-06-03 2015-09-02 川崎重工業株式会社 Fuel injection device
DE102012017065A1 (en) * 2012-08-28 2014-03-27 Rolls-Royce Deutschland Ltd & Co Kg Method for operating a lean burn burner of an aircraft gas turbine and apparatus for carrying out the method
EP2971975B1 (en) 2013-03-13 2020-07-22 Industrial Turbine Company (UK) Limited Lean azimuthal flame combustor
DE102013206014A1 (en) * 2013-04-05 2014-10-09 Dürr Systems GmbH Energy converter system and assemblies for this
US10281146B1 (en) * 2013-04-18 2019-05-07 Astec, Inc. Apparatus and method for a center fuel stabilization bluff body
EP3022492A4 (en) * 2013-07-15 2017-02-22 Hamilton Sundstrand Corporation Combustion system, apparatus and method
CA2931246C (en) 2013-11-27 2019-09-24 General Electric Company Fuel nozzle with fluid lock and purge apparatus
WO2015147934A1 (en) 2013-12-23 2015-10-01 General Electric Company Fuel nozzle structure for air-assisted fuel injection
US10190774B2 (en) 2013-12-23 2019-01-29 General Electric Company Fuel nozzle with flexible support structures
DE102017118166A1 (en) * 2017-08-09 2019-02-14 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR) Burner head, burner system and use of the burner system

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1254911B (en) * 1965-09-23 1967-11-23 Daimler Benz Ag Arrangement of the injection nozzle body on or in the combustion chamber of gas turbine engines
JPS59129330A (en) * 1983-01-17 1984-07-25 Hitachi Ltd Premixed combustion type gas turbine
DE3739197A1 (en) * 1986-11-21 1988-06-01 Bbc Brown Boveri & Cie Method for avoiding the spontaneous ignition of a fuel/air mixture in the region of the premixing chamber and the swirl body between premixing chamber and combustion chamber of a gas turbine installation
EP0660038A2 (en) * 1993-12-23 1995-06-28 ROLLS-ROYCE plc Fuel injection apparatus
EP0845634A2 (en) * 1996-11-29 1998-06-03 Kabushiki Kaisha Toshiba Gas turbine combustor and operating method thereof
EP1134494A1 (en) * 2000-03-14 2001-09-19 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
EP1186832A2 (en) * 2000-09-08 2002-03-13 General Electric Company Fuel nozzle assembly for reduced exhaust emissions

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3961475A (en) * 1972-09-07 1976-06-08 Rolls-Royce (1971) Limited Combustion apparatus for gas turbine engines
US4435778C1 (en) 1981-05-18 2002-09-03 Ibm Method for editing spatially related data in an interactive text processing system
JP2713627B2 (en) * 1989-03-20 1998-02-16 株式会社日立製作所 Gas turbine combustor, gas turbine equipment including the same, and combustion method
US5367873A (en) * 1991-06-24 1994-11-29 United Technologies Corporation One-piece flameholder
JPH0579631A (en) * 1991-09-19 1993-03-30 Hitachi Ltd Combustion device facility
US5575153A (en) * 1993-04-07 1996-11-19 Hitachi, Ltd. Stabilizer for gas turbine combustors and gas turbine combustor equipped with the stabilizer
JP2904701B2 (en) * 1993-12-15 1999-06-14 株式会社日立製作所 Gas turbine and gas turbine combustion device
EP0678708B1 (en) * 1994-04-20 1998-12-02 ROLLS-ROYCE plc Gas turbine engine fuel injector
DE4422532A1 (en) * 1994-06-28 1996-01-04 Abb Management Ag Fuel jet for gas turbine combustion chamber
US6199367B1 (en) * 1996-04-26 2001-03-13 General Electric Company Air modulated carburetor with axially moveable fuel injector tip and swirler assembly responsive to fuel pressure
EP0931979A1 (en) * 1998-01-23 1999-07-28 DVGW Deutscher Verein des Gas- und Wasserfaches -Technisch-wissenschaftliche Vereinigung- Method and apparatus for supressing flame and pressure fluctuations in a furnace
US6272840B1 (en) * 2000-01-13 2001-08-14 Cfd Research Corporation Piloted airblast lean direct fuel injector
EP1499800B1 (en) * 2002-04-26 2011-06-29 Rolls-Royce Corporation Fuel premixing module for gas turbine engine combustor
US7143583B2 (en) * 2002-08-22 2006-12-05 Hitachi, Ltd. Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor
US6986255B2 (en) * 2002-10-24 2006-01-17 Rolls-Royce Plc Piloted airblast lean direct fuel injector with modified air splitter
FR2859272B1 (en) * 2003-09-02 2005-10-14 Snecma Moteurs AIR / FUEL INJECTION SYSTEM IN A TURBOMACHINE COMBUSTION CHAMBER HAVING MEANS FOR GENERATING COLD PLASMA
GB0516208D0 (en) * 2005-08-05 2005-09-14 Rolls Royce Plc Fuel injector
DE102005062079A1 (en) * 2005-12-22 2007-07-12 Rolls-Royce Deutschland Ltd & Co Kg Magervormic burner with a nebulizer lip
GB2439097B (en) * 2006-06-15 2008-10-29 Rolls Royce Plc Fuel injector

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1254911B (en) * 1965-09-23 1967-11-23 Daimler Benz Ag Arrangement of the injection nozzle body on or in the combustion chamber of gas turbine engines
JPS59129330A (en) * 1983-01-17 1984-07-25 Hitachi Ltd Premixed combustion type gas turbine
DE3739197A1 (en) * 1986-11-21 1988-06-01 Bbc Brown Boveri & Cie Method for avoiding the spontaneous ignition of a fuel/air mixture in the region of the premixing chamber and the swirl body between premixing chamber and combustion chamber of a gas turbine installation
EP0660038A2 (en) * 1993-12-23 1995-06-28 ROLLS-ROYCE plc Fuel injection apparatus
EP0845634A2 (en) * 1996-11-29 1998-06-03 Kabushiki Kaisha Toshiba Gas turbine combustor and operating method thereof
EP1134494A1 (en) * 2000-03-14 2001-09-19 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
EP1186832A2 (en) * 2000-09-08 2002-03-13 General Electric Company Fuel nozzle assembly for reduced exhaust emissions

Also Published As

Publication number Publication date
EP1484553A2 (en) 2004-12-08
EP1484553B1 (en) 2011-09-28
US20050028526A1 (en) 2005-02-10
DE10326720A1 (en) 2004-12-23
US7621131B2 (en) 2009-11-24

Similar Documents

Publication Publication Date Title
EP1484553A3 (en) Burner for a gas turbine combustor
CN105452775B (en) It is adapted to the gas turbine burner of pluralities of fuel
JP2713627B2 (en) Gas turbine combustor, gas turbine equipment including the same, and combustion method
CN101220955B (en) Method and apparatus for enhanced mixing in premixing devices
EP2171356B1 (en) Cool flame combustion
JP6215352B2 (en) Gray-scale axial stage combustion in a can type gas turbine engine.
JP5364275B2 (en) Method and system for enabling NOx emissions to be reduced in a combustion system
US8459985B2 (en) Method and burner arrangement for the production of hot gas, and use of said method
US8113002B2 (en) Combustor burner vanelets
CN106537042A (en) Combustion device for gas turbine engine
EP1342956A3 (en) Gas turbine combustor
EP1333228A3 (en) Method and apparatus to decrease combustor emissions
EP1489358A3 (en) A gas turbine combustor and fuel supply method for same
ATE345439T1 (en) METHOD FOR CONTROLLING THE FUEL AND AIR SUPPLY TO A BURNER OF A THERMOCYCLE ENGINE
CN104662368A (en) Liquefier having cationic side chains without polyether side chains
EP1211458A3 (en) Low NOx premix burner apparatus and methods
JP2008039385A (en) Axially staged combustion system for gas turbine engine
JP2002535598A (en) Burners and methods of operating gas turbines
JPH06193841A (en) Gas operation type premix burner
CN107076422A (en) burner, burner and gas turbine
EP2169314A3 (en) A method of reducing emissions for a sequential combustion gas turbine and combustor for such a gas turbine
CN102116479A (en) Fuel nozzle with integrated passages and method of operation
EP1279898A3 (en) Premix burner with high flame stability
CN101377304A (en) System and method for mixing fuel and air in gas turbine
EP1310737A3 (en) Low nox emission diffusion flame combustor for gas turbines

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): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/30 20060101ALI20061023BHEP

Ipc: F23R 3/34 20060101ALI20061023BHEP

Ipc: F23D 11/10 20060101AFI20040910BHEP

Ipc: F23R 3/18 20060101ALI20061023BHEP

Ipc: F23R 3/14 20060101ALI20061023BHEP

17P Request for examination filed

Effective date: 20070131

AKX Designation fees paid

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 20071024

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

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: 502004012900

Country of ref document: DE

Effective date: 20111124

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: 20120629

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502004012900

Country of ref document: DE

Effective date: 20120629

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502004012900

Country of ref document: DE

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, DE

Free format text: FORMER OWNER: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, 15827 BLANKENFELDE, DE

Effective date: 20110929

Ref country code: DE

Ref legal event code: R081

Ref document number: 502004012900

Country of ref document: DE

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, DE

Free format text: FORMER OWNER: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, 15827 BLANKENFELDE, DE

Effective date: 20130402

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 15

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

Ref country code: FR

Payment date: 20190625

Year of fee payment: 16

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

Ref country code: GB

Payment date: 20190627

Year of fee payment: 16

Ref country code: DE

Payment date: 20190627

Year of fee payment: 16

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502004012900

Country of ref document: DE

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

Effective date: 20200602

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

Ref country code: FR

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

Effective date: 20200630

Ref country code: GB

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

Effective date: 20200602

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

Ref country code: DE

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

Effective date: 20210101