EP2463583B1 - Turbine à gaz et procédé de reconditionnement d'une telle turbine à gaz - Google Patents

Turbine à gaz et procédé de reconditionnement d'une telle turbine à gaz Download PDF

Info

Publication number
EP2463583B1
EP2463583B1 EP11190982.6A EP11190982A EP2463583B1 EP 2463583 B1 EP2463583 B1 EP 2463583B1 EP 11190982 A EP11190982 A EP 11190982A EP 2463583 B1 EP2463583 B1 EP 2463583B1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
outer sealing
segments
cooling panel
panel
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.)
Not-in-force
Application number
EP11190982.6A
Other languages
German (de)
English (en)
Other versions
EP2463583A1 (fr
Inventor
Andreas De Fazio
Urs Benz
Remigi Tschuor
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.)
General Electric Technology GmbH
Original Assignee
General Electric Technology GmbH
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 General Electric Technology GmbH filed Critical General Electric Technology GmbH
Publication of EP2463583A1 publication Critical patent/EP2463583A1/fr
Application granted granted Critical
Publication of EP2463583B1 publication Critical patent/EP2463583B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—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
    • F23R3/002—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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R2900/00012—Details of sealing 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
    • F23R2900/00019—Repairing or maintaining combustion chamber liners or subparts

Definitions

  • the present invention relates to the field of gas turbines. It relates to a gas turbine according to the preamble of claim 1. It further relates to a method for reconditioning such a gas turbine.
  • Fig. 13 shows in a highly simplified representation of a stationary gas turbine with sequential combustion, as known from the prior art.
  • the illustrated gas turbine 10 includes a compressor 11 for compressing aspirated air, a first annular combustor 14 into which is mixed fuel injected with pre-mix type burners 13 supplied via a fuel supply 12. The resulting hot gas drives a first Turbine 15, and is then reheated by injecting a fuel from a second fuel supply 16 into a second combustion chamber 17, to then drive a second turbine 18.
  • Modern stationary gas turbines are usually designed with an annular combustion chamber, as in Fig. 1 is reproduced.
  • the local gas turbine 20 with annular combustion chamber 24 of the combustion chamber is limited by an outer side wall 25 and by an inner side wall 26.
  • the hot gas path 27 is divided in the combustion chamber 24 by an inlet and an exit plane.
  • the entry level is characterized by a plurality of burners 21, 22 and one or more front segments 23.
  • the burners 21, 22 are positioned in the front segments and sealed in the flow direction.
  • the attachment of the front segments themselves as well as their sealing must meet the requirements of the combustion.
  • the combustion chamber 24 is operated for a long time, with or without interruptions (start and stop cycles). Examples of arrangements of front panels and front segments are from the US5285632 , of the WO 96/04510 A1 or the DE 44 32 558 A1 known.
  • This module is then delivered as a "front panel complete" to the installation site.
  • front segments are releasably hooked to the front panel, that for sealing the front segments in Circumferentially one another between adjacent front segments each extending in the radial direction seal is arranged, and that the seal by two parallel running, in the middle between the adjacent front segments abutting outer sealing strip is formed, each of which on the outside at the edge of the cooling plate the associated front segment is attached.
  • An embodiment of the gas turbine according to the invention is characterized in that the front segments have on their back a plurality of hooks, and that on the front of the front plate fixing bolts are arranged, each having a hook receptacle, and in which the front segments are hooked with their hooks ,
  • the hooks are arranged distributed on the edges of the front segments running in the radial direction, and if the hooks and the hook receivers are oriented such that the front segments are largely fixed perpendicular to the segment surface, while they have sufficient freedom of movement parallel to the segment surface Compensation of thermally induced strains.
  • the lock washers are each composed of a lower ring and an upper ring, and when the lock washers are firmly connected only in the region of the upper ring with the associated standoff bolt through the weld.
  • Another embodiment of the invention is characterized in that for securing the outer sealing strips distributed along the edge of the cooling plate arranged fixing clips are provided, that the outer sealing strips are slidably held between the fixing clips and the respective heat sink, and that the fixing Clips are each outside the range of the outer sealing strip firmly connected by a weld with the heat sink
  • the lock washers 47 absorb all the axial forces, which are caused by pulsations of the combustion chamber 24 and thermal deformation of the front segment. Of course, axial forces also arise purely by the weight of the cooling plate 29.
  • the lock washers 47 are designed in two stages (47a, 47b in Fig. 7 ) so that they can be reused a second time during reconditioning. The idea is to cut open only the upper first welded ring 47b of the lock washer 47. The lower second ring 47a can then be used again with the spacer bolt 46 or welded (welding 49 in Fig. 8 ).

Landscapes

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

Claims (11)

  1. Turbine à gaz (20), notamment turbine à gaz stationnaire, comprenant une chambre de combustion (24) de forme annulaire délimitée dans la direction radiale par une paroi latérale intérieure (26) et par une paroi latérale extérieure (25) et dans la direction axiale par une plaque frontale (45) en forme de couronne circulaire, les brûleurs (21, 22) étant reliés à la chambre de combustion (24) à travers ladite plaque frontale (45), la plaque frontale (45) étant recouverte en direction de la chambre de combustion (24) par une pluralité de segments frontaux (23) plats formant une couronne circulaire pour la protection contre l'influence de la chaleur, lesdits segments comprenant respectivement une tôle frontale (28) formant le côté avant et une tôle de refroidissement (29) disposée parallèlement à la tôle frontale (28) et à distance derrière elle, caractérisée en ce que les segments frontaux (23) sont maintenus accrochés de façon amovible à la plaque frontale (45), que respectivement un joint (50) s'étendant dans la direction radiale est disposé entre les segments frontaux (23) connexes pour étanchéifier les segments frontaux (23) dans la direction circonférentielle les uns par rapport aux autres et que le joint (50) est formé par deux bandes d'étanchéité (30) extérieures s'étendant parallèlement et butant l'une contre l'autre au centre entre les segments frontaux (23) connexes, parmi lesquelles chaque bande est respectivement fixée sur le côté extérieur au niveau de la bordure de la tôle de refroidissement (29) du segment frontal (23) associé.
  2. Turbine à gaz selon la revendication 1, caractérisée en ce que les segments frontaux (23) comportent sur leur côté arrière une pluralité de crochets (35) et que des boulons de fixation (39) sont disposés sur le côté avant de la plaque frontale (45), lesdits boulons comportant respectivement un logement de crochet (40) dans lequel les segments frontaux (23) sont accrochés avec leur crochet (35).
  3. Turbine à gaz selon la revendication 2, caractérisée en ce que les crochets (35) sont disposés de façon répartie au niveau des bordures, s'étendant dans la direction radiale, des segments frontaux (23) et que les crochets (35) et les logements de crochet (40) sont orientés de telle sorte que les segments frontaux (23) sont largement fixés perpendiculairement à la surface de segment tout en ayant un espace de jeu suffisant parallèlement à la surface de segment pour compenser les dilatations d'origine thermique.
  4. Turbine à gaz selon la revendication 2 ou 3, caractérisée en ce que les boulons de fixation (39) sont vissés de façon permanente à la plaque frontale (45) et que des moyens (42, 43) sont prévus pour fixer les boulons de fixation (39) de façon à les empêcher de tourner.
  5. Turbine à gaz selon l'une quelconque des revendications 1 à 4, caractérisée en ce que la tôle de refroidissement (29) comporte des trous (34) répartis sur la surface à travers lesquels de l'air de refroidissement peut rentrer dans l'espace intermédiaire (51) prévu entre la tôle frontale (28) et la tôle de refroidissement (29) pour le refroidissement par impact de la tôle frontale (28).
  6. Turbine à gaz selon la revendication 5, caractérisée en ce que la tôle de refroidissement (29) est respectivement maintenue à distance de la tôle frontale (28) dans les segments frontaux (23) à l'aide de boulons d'écartement (46) disposés de façon répartie dans la surface et que la tôle de refroidissement (29) est fixée sur les boulons d'écartement (46) à l'aide de rondelles de fixation (47) placées, en partant du côté arrière, sur les boulons d'écartement (46) et reliées fixement aux boulons d'écartement (46) par le biais d'une soudure (48).
  7. Turbine à gaz selon la revendication 6, caractérisée en ce que les rondelles de fixation (47) sont respectivement composées d'une bague inférieure (47a) et d'une bague supérieure (47b) et que les rondelles de fixation (47) ne sont reliées fixement au boulon d'écartement (40) associé par le biais de la soudure (48) que dans la région de la bague supérieure (47b).
  8. Turbine à gaz selon l'une quelconque des revendications 1 à 7, caractérisée en ce que les bandes d'étanchéité (30) extérieures sont composées d'un alliage à base de nickel résistant aux hautes températures durci par précipitation, que les bandes d'étanchéité (30) extérieures sont précontraintes les unes par rapport aux autres dans l'état froid de la turbine à gaz (20), que les bandes d'étanchéité (30) extérieures s'étendent avec leurs lèvres d'étanchéité (59) à l'encontre de la direction d'écoulement et que les lèvres d'étanchéité (59) extérieures sont pourvues au niveau de leurs extrémités libres d'un rayon (R) permettant de réduire l'usure mutuelle.
  9. Turbine à gaz selon l'une quelconque des revendications 1 à 8, caractérisée en ce que des clips de fixation (53) disposés de façon répartie sont prévus pour réaliser la fixation des bandes d'étanchéité (30) extérieures le long de la bordure de la tôle de refroidissement (29), que les bandes d'étanchéité (30) extérieures sont maintenues de façon coulissante entre les clips de fixation (53) et la tôle de refroidissement (29) respective et que les clips de fixation (53) sont respectivement reliés fixement à la tôle de refroidissement (29) par le biais d'une soudure (56) à l'extérieur de la région de la bande d'étanchéité (30) extérieure.
  10. Turbine à gaz selon la revendication 9, caractérisée en ce que le coulissement de la bande d'étanchéité (30) extérieure entre les clips de fixation (53) et la tôle de refroidissement (29) associée est respectivement délimité par un bouton (54) réalisé au niveau du clip de fixation (53), ledit bouton plongeant, à travers un détouré (55) de plus grande taille, à travers les bandes d'étanchéité (30) extérieures, dans une poche (57) disposée dessous, dans la tôle de refroidissement (29).
  11. Procédé de reconditionnement d'une turbine à gaz selon la revendication 7, caractérisée en ce que pour retirer la tôle de refroidissement (29), les bagues (47b) supérieures soudées aux boulons d'écartement (40) sont détachées, que les bagues (47a) inférieures restantes sont retirées des boulons d'écartement (40) et que pour fixer de nouveau la tôle de refroidissement (29) sur les boulons d'écartement (40), les bagues (47a) inférieures restantes sont de nouveau placées sur les boulons d'écartement (40) et reliées fixement aux boulons d'écartement (40) par le biais d'une soudure (49).
EP11190982.6A 2010-12-06 2011-11-28 Turbine à gaz et procédé de reconditionnement d'une telle turbine à gaz Not-in-force EP2463583B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH02032/10A CH704185A1 (de) 2010-12-06 2010-12-06 Gasturbine sowie verfahren zum rekonditionieren einer solchen gasturbine.

Publications (2)

Publication Number Publication Date
EP2463583A1 EP2463583A1 (fr) 2012-06-13
EP2463583B1 true EP2463583B1 (fr) 2016-09-21

Family

ID=43920352

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11190982.6A Not-in-force EP2463583B1 (fr) 2010-12-06 2011-11-28 Turbine à gaz et procédé de reconditionnement d'une telle turbine à gaz

Country Status (4)

Country Link
EP (1) EP2463583B1 (fr)
AU (1) AU2011253595B2 (fr)
CH (1) CH704185A1 (fr)
MY (1) MY157102A (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3002518B1 (fr) * 2014-09-30 2019-01-30 Ansaldo Energia Switzerland AG Panneau avant de chambre de combustion
EP3299720B1 (fr) * 2016-09-22 2020-11-04 Ansaldo Energia IP UK Limited Ensemble avant de chambre de combustion pour turbine à gaz

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5285632A (en) * 1993-02-08 1994-02-15 General Electric Company Low NOx combustor
DE4427222A1 (de) 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
DE4432558A1 (de) 1994-09-13 1996-03-14 Bmw Rolls Royce Gmbh Gasturbinen-Brennkammer mit Hitzeschild
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
GB2298267B (en) * 1995-02-23 1999-01-13 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
SE9801818L (sv) * 1998-05-25 1999-11-26 Abb Ab Brännkammaranordning
EP1130219A1 (fr) * 2000-03-02 2001-09-05 Siemens Aktiengesellschaft Turbine avec joints d'étanchéitée entre les panneaux des parois
US6298667B1 (en) * 2000-06-22 2001-10-09 General Electric Company Modular combustor dome
EP1413831A1 (fr) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Chambre de combustion annulaire pour turbine à gaz et turbine à gaz
US7338244B2 (en) * 2004-01-13 2008-03-04 Siemens Power Generation, Inc. Attachment device for turbine combustor liner
FR2897417A1 (fr) * 2006-02-10 2007-08-17 Snecma Sa Chambre de combustion annulaire d'une turbomachine
FR2918444B1 (fr) * 2007-07-05 2013-06-28 Snecma Deflecteur de fond de chambre, chambre de combustion le comportant et moteur a turbine a gaz en etant equipe
FR2921462B1 (fr) * 2007-09-21 2012-08-24 Snecma Chambre de combustion annulaire de moteur a turbine a gaz
FR2929690B1 (fr) * 2008-04-03 2012-08-17 Snecma Propulsion Solide Chambre de combustion sectorisee en cmc pour turbine a gaz

Also Published As

Publication number Publication date
CH704185A1 (de) 2012-06-15
AU2011253595B2 (en) 2015-07-16
MY157102A (en) 2016-04-29
AU2011253595A1 (en) 2012-06-21
EP2463583A1 (fr) 2012-06-13

Similar Documents

Publication Publication Date Title
EP1193451B1 (fr) Tête de chambre de combustion d'une turbine à gaz
DE60115236T2 (de) Übergangstück für eine nicht-ringförmige gasturbinenbrennkammer
EP2242916B1 (fr) Turbine à gaz
DE60110309T2 (de) Haltevorrichtung einer Verwirbelungsanordnung
EP2738470B1 (fr) Assemblage pour attacher des éléments de bouclier thermique à la paroi d'une chambre de combustion d'une turbine à gaz
EP1635118B1 (fr) Chambre à gaz chauds et bardeau pour une chambre à gaz chauds
DE4020273C2 (fr)
DE102008016306A1 (de) Einrichtung zum Erwärmen eines Fluids
WO2005108869A1 (fr) Chambre de combustion pour une turbine a gaz
EP2344723B1 (fr) Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
CH705838A1 (de) Abgasgehäuse für eine Gasturbine sowie Gasturbine mit einem Abgasgehäuse.
DE102008010294A1 (de) Gasturbinenbrennkammer mit keramischem Flammenrohr
EP2356319A1 (fr) Dispositif d'aubes directrices pour turbomachine axiale
EP2852735A2 (fr) Turbine à gaz
EP2463583B1 (fr) Turbine à gaz et procédé de reconditionnement d'une telle turbine à gaz
EP3181827A1 (fr) Connexion entre composants de turbomachine
DE4324035C2 (de) Gasturbine
EP3034944A1 (fr) Chambre de combustion de turbines a gaz a epaisseur de paroi variable
DE3535442C2 (fr)
EP3670845B1 (fr) Turbomachine avec agencement de joint statique
DE2909467A1 (de) Absperrschieber fuer rohrleitungen grosser nennweiten
EP2024684B1 (fr) Turbine à gaz avec composants de machine blindé
EP1529181B1 (fr) Chambre de combustion de turbine a gaz
EP1422479B1 (fr) Chambre pour la combustion d' un mélange combustible fluide
EP2077421A2 (fr) Dispositif pour attacher a brûleur à fonctionnement séquentiel dans une turbine à gaz

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: 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

17P Request for examination filed

Effective date: 20121122

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160512

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 831363

Country of ref document: AT

Kind code of ref document: T

Effective date: 20161015

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: DE

Ref legal event code: R096

Ref document number: 502011010716

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

REG Reference to a national code

Ref country code: NL

Ref legal event code: FP

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: 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: 20160921

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: 20160921

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: 20160921

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: 20161221

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: 20161222

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: 20160921

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: 20160921

Ref country code: BE

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

Effective date: 20161130

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

Ref country code: RO

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

Effective date: 20160921

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: 20160921

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

Ref country code: ES

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

Effective date: 20160921

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: 20160921

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: 20160921

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: 20170121

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: 20161221

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: 20160921

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: 20170123

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: 20160921

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502011010716

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: 20160921

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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: 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: 20160921

Ref country code: CH

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

Effective date: 20161130

Ref country code: LI

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

Effective date: 20161130

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

26N No opposition filed

Effective date: 20170622

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: 20161130

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

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: 20160921

Ref country code: IE

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

Effective date: 20161128

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 831363

Country of ref document: AT

Kind code of ref document: T

Effective date: 20161128

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: 20161128

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

Ref country code: FR

Payment date: 20171127

Year of fee payment: 7

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20161130

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: 20111128

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: 20160921

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: 20160921

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: 20160921

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: 20160921

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: 20160921

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: 20160921

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

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: 20160921

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

Ref country code: NL

Payment date: 20181026

Year of fee payment: 8

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

Ref country code: DE

Payment date: 20181023

Year of fee payment: 8

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

Ref country code: GB

Payment date: 20181024

Year of fee payment: 8

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: 20181130

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502011010716

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MM

Effective date: 20191201

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

Effective date: 20191128

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

Ref country code: NL

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

Effective date: 20191201

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: 20200603

Ref country code: GB

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

Effective date: 20191128