EP0967363A2 - Joint de type nid d'abeille spécialement pour une turbine à gaz - Google Patents

Joint de type nid d'abeille spécialement pour une turbine à gaz Download PDF

Info

Publication number
EP0967363A2
EP0967363A2 EP99110083A EP99110083A EP0967363A2 EP 0967363 A2 EP0967363 A2 EP 0967363A2 EP 99110083 A EP99110083 A EP 99110083A EP 99110083 A EP99110083 A EP 99110083A EP 0967363 A2 EP0967363 A2 EP 0967363A2
Authority
EP
European Patent Office
Prior art keywords
honeycomb structure
section
honeycomb
turbine
seal
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
EP99110083A
Other languages
German (de)
English (en)
Other versions
EP0967363B1 (fr
EP0967363A3 (fr
Inventor
Karl Schreiber
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
BMW Rolls Royce 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 Rolls Royce Deutschland Ltd and Co KG, BMW Rolls Royce GmbH filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP0967363A2 publication Critical patent/EP0967363A2/fr
Publication of EP0967363A3 publication Critical patent/EP0967363A3/fr
Application granted granted Critical
Publication of EP0967363B1 publication Critical patent/EP0967363B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S277/00—Seal for a joint or juncture
    • Y10S277/913—Seal for fluid pressure below atmospheric, e.g. vacuum
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49297—Seal or packing making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24149—Honeycomb-like

Definitions

  • the invention relates to a honeycomb structure seal between a rotating element and a stator element of a turbine, in particular for a gas turbine, with a brushing section facing the tips of the turbine blades and with a base plate facing the other element of the turbine.
  • the abrading section faces the tips of the turbine stator blades.
  • honeycomb structure seals for the rotor blades, for example of gas turbines, which are arranged on the inner wall of the turbine housing, are also used, among other things, as honeycomb structure seals
  • the honeycomb structure is supported by a base plate, while the web walls forming the honeycomb structure, with their free end sections, face the tips of the rotor blades.
  • the honeycomb cells delimited by the web walls can be at least partially filled with a suitable insulation material , as described in the above-mentioned document.
  • the object of the present invention is to provide a remedial measure for the problems described.
  • the solution to this problem is characterized by a multi-layer structure of the honeycomb structure seal in such a way that an air-evacuated honeycomb structure section, which is thus partially insulated by vacuum, connects to the base plate and is covered by an intermediate plate on its side facing away from the honeycomb structure section the brushing section is arranged.
  • Advantageous training and further education are included in the subclaims. It should be pointed out again that the so-called honeycomb structure section is to be understood as an arrangement of several cavities of essentially any shape next to one another.
  • Reference number 1 denotes a base plate, on the surface thereof a honeycomb structure which is customary in honeycomb seals is. This honeycomb structure adjacent to the base plate 1 is referred to below as Honeycomb structure section 2 of the honeycomb structure seal according to the invention designated.
  • An intermediate plate 3 adjoins the honeycomb structure section 2 on the side opposite the base plate 1, ie the honeycomb structure section 2 is covered by the intermediate plate 3.
  • the attached figure is an exploded view, ie in reality the honeycomb structure section 2 is embedded directly between the base plate 1 on the one hand and the intermediate plate 3 on the other hand.
  • a so-called rubbing section 4 is arranged on the intermediate plate 3. This brushing section 4 again lies directly on the intermediate plate 3.
  • honeycomb structure seal shown and described so far draws is thus characterized by a multi-layer structure consisting of the base plate 1, the honeycomb structure section 2, the intermediate plate 3 and the brushing section 4.
  • the base plate 1 In the installed state of this honeycomb structure seal in one Turbine, in particular an aircraft gas turbine, is the base plate 1 with its free (here lower) surface on the inner wall of the not shown Turbine housing, while the (upper in the figure) free surface of the brushing section 4 (also not shown) Blade tips facing the turbine rotor blades.
  • the abradable section 4 is designed with regard to the required sealing effect, ie, the sealing of the gap between the blade tips, not shown, and the honeycomb structure seal.
  • This abrading section 4, on which the blade tips can or should actually rub to achieve an optimal sealing effect can thus be a brush seal, a plasma spray layer, a metal felt or one known to the person skilled in the art Metco "layer, or else other suitable sealing structures.
  • this rub-on section 4 itself is again in the form of a (conventional) honeycomb seal, ie it consists, as usual, of a multiplicity of, for example, or preferably honeycomb-like web walls 5, each of which form so-called honeycomb cells 6.
  • the sealing function of the honeycomb structure seal according to the invention is taken from section 2 of the honeycomb structure.
  • the latter is air evacuated, i.e. in the partial areas of the individual honeycomb cells 6 of the honeycomb structure section 2 there is thermal insulation due to vacuum. This means that the vacuum that is at least essentially present in the honeycomb cells 6 is preserved, it is of course necessary that the honeycomb cells 6 (in the figure display up and down) completed are what through the base plate 1 on the one hand and through the intermediate plate 3 on the other hand is guaranteed.
  • honeycomb structure section 2 and the base plate 1 and the intermediate plate 3 formed section the honeycomb structure seal by high temperature soldering under vacuum conditions.
  • the intermediate plate 3 is soldered.
  • the brushing section 4 is connected to the intermediate plate 3 become.
  • honeycomb structure seal proposed here thus consists of two, by an intermediate plate 3 separated honeycomb structures, namely the honeycomb structure section 2 and the brushing section 4.
  • honeycomb structures can be commercially available and preferably consist of thin, metallic high-temperature alloys.
  • the (here lower) honeycomb structure section 3 takes over the function of thermal insulation; consequently, he can constructively Varying the structure size and height of the required insulation characteristics be adjusted. Because the desired thermal Isolation effect by the prevailing in the honeycomb cells 6 (at least essentially) vacuum is achieved, these honeycomb cells 6 should be preferred have the largest possible base or cross-sectional area.
  • the upper sealing honeycomb structure i.e. of the Brushing section 4 in its / its execution to the requirements of Sealing effect with respect to the turbine working gas flowing past it customized.
  • the achievable sealing effect is better, the smaller the basic or Cross-sectional areas of the honeycomb cells 6 of this honeycomb structure are. Accordingly, it can be seen that the honeycomb cells 6 of the Honeycomb formed trained streak section 4 a significantly smaller Have partial area as the honeycomb cells 6 of the honeycomb structure section 2nd
  • Honeycomb structure section 2 alternatively as an insulating substructure for one other than the brushing section 4 shown, i.e.
  • other sealing systems can also be used, such as for example a brush seal, METCO layers, plasma spray layers, Metal felts or the like, each based on the vacuum insulation structure described can be applied.
  • a brush seal METCO layers
  • plasma spray layers Metal felts or the like

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP99110083A 1998-06-24 1999-05-22 Joint de type nid d'abeille spécialement pour une turbine à gaz Expired - Lifetime EP0967363B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19828065A DE19828065A1 (de) 1998-06-24 1998-06-24 Wabenstruktur-Dichtung insbesondere für eine Gasturbine
DE19828065 1998-06-24

Publications (3)

Publication Number Publication Date
EP0967363A2 true EP0967363A2 (fr) 1999-12-29
EP0967363A3 EP0967363A3 (fr) 2000-11-22
EP0967363B1 EP0967363B1 (fr) 2003-05-02

Family

ID=7871828

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99110083A Expired - Lifetime EP0967363B1 (fr) 1998-06-24 1999-05-22 Joint de type nid d'abeille spécialement pour une turbine à gaz

Country Status (3)

Country Link
US (1) US6251494B1 (fr)
EP (1) EP0967363B1 (fr)
DE (2) DE19828065A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10247031A1 (de) * 2002-10-09 2004-04-22 Alstom (Switzerland) Ltd. Vorrichtung zur Dichtung eines Dichtspalts bei einer Strömungsrotationsmaschine

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6652226B2 (en) * 2001-02-09 2003-11-25 General Electric Co. Methods and apparatus for reducing seal teeth wear
US6780458B2 (en) * 2001-08-01 2004-08-24 Siemens Westinghouse Power Corporation Wear and erosion resistant alloys applied by cold spray technique
US6706319B2 (en) 2001-12-05 2004-03-16 Siemens Westinghouse Power Corporation Mixed powder deposition of components for wear, erosion and abrasion resistant applications
US6655576B2 (en) * 2002-03-26 2003-12-02 United Technologies Corporation Process for disassembling a brazed structure
US6827350B2 (en) 2002-10-30 2004-12-07 General Electric Company Hybrid honeycomb and brush seal for steam gland
US20040239040A1 (en) * 2003-05-29 2004-12-02 Burdgick Steven Sebastian Nozzle interstage seal for steam turbines
US7178340B2 (en) * 2003-09-24 2007-02-20 Power Systems Mfg., Llc Transition duct honeycomb seal
DE102004010236A1 (de) * 2004-03-03 2005-09-15 Mtu Aero Engines Gmbh Ringstruktur in Metallbauweise
US7542830B2 (en) * 2004-04-28 2009-06-02 Klauder Jr Louis T Method for maintaining geometry of ballasted railroad track
GB2416192B (en) * 2004-07-14 2006-09-27 Rolls Royce Plc Ducted fan with containment structure
DE102004034312A1 (de) * 2004-07-15 2006-02-02 Mtu Aero Engines Gmbh Dichtungsanordnung und Verfahren zur Herstellung eines Dichtkörpers für eine Dichtungsanordnung
US20070137039A1 (en) * 2005-12-20 2007-06-21 General Electric Company Methods and apparatus for coupling honeycomb seals to gas turbine engine components
US8080973B2 (en) 2008-10-22 2011-12-20 General Electric Company Apparatus for energy transfer using converter and method of manufacturing same
US7932633B2 (en) 2008-10-22 2011-04-26 General Electric Company Apparatus for transferring energy using power electronics and machine inductance and method of manufacturing same
US9290097B2 (en) 2010-11-05 2016-03-22 Robert Louis Steigerwald Apparatus for transferring energy using onboard power electronics with high-frequency transformer isolation and method of manufacturing same
GB201020143D0 (en) 2010-11-29 2011-01-12 Rolls Royce Plc A gas turbine engine blade containment arrangement
ITCO20110068A1 (it) * 2011-12-20 2013-06-21 Nuovo Pignone Spa Metodo e tenuta a nido d'ape
CN102979906A (zh) * 2012-08-29 2013-03-20 哈尔滨汽轮机厂有限责任公司 用于燃气轮机的蜂窝密封装置的加工方法
JP6184173B2 (ja) 2013-05-29 2017-08-23 三菱日立パワーシステムズ株式会社 ガスタービン
JP6353056B2 (ja) * 2013-09-06 2018-07-04 ゼネラル・エレクトリック・カンパニイ 第１のハニカム層および第２のハニカム層ならびにこれらの間の穿孔された中間シールプレートを備えるガスタービン用積層シールアセンブリ
EP2998517B1 (fr) * 2014-09-16 2019-03-27 Ansaldo Energia Switzerland AG Agencement d'étanchéité au niveau de l'interface entre une chambre de combustion et une turbine d'une turbine à gaz et turbine à gaz avec un tel agencement d'étanchéité
DE102015216208A1 (de) * 2015-08-25 2017-03-02 Rolls-Royce Deutschland Ltd & Co Kg Dichtelement für eine Turbomaschine, Turbomaschine mit einem Dichtelement und Verfahren zur Herstellung eines Dichtelementes
EP3228826B1 (fr) * 2016-04-05 2021-03-17 MTU Aero Engines GmbH Agencement de segments d'étanchéité ayant un connecteur, moteur à turbine à gaz et procédé de fabrication associé
US9816388B1 (en) * 2016-09-22 2017-11-14 General Electric Company Seal in a gas turbine engine having a shim base and a honeycomb structure with a number of cavities formed therein
US10774670B2 (en) * 2017-06-07 2020-09-15 General Electric Company Filled abradable seal component and associated methods thereof
US10919106B2 (en) * 2017-06-09 2021-02-16 General Electric Company Ultrasonic welding of annular components
US11674396B2 (en) 2021-07-30 2023-06-13 General Electric Company Cooling air delivery assembly
US11674405B2 (en) 2021-08-30 2023-06-13 General Electric Company Abradable insert with lattice structure

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3235745A1 (de) 1981-09-29 1983-04-28 United Technologies Corp., 06101 Hartford, Conn. Isolierte wabendichtung

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3071853A (en) * 1955-10-17 1963-01-08 Solar Aircraft Co Method and apparatus for making brazed honeycomb
US3001274A (en) * 1957-01-18 1961-09-26 Solar Aircraft Co Brazing article and method
US3067507A (en) * 1958-02-07 1962-12-11 Goodyear Aircraft Corp Method of making sandwich structures
GB1268777A (en) * 1968-11-23 1972-03-29 Rolls Royce Cellular structure
US3633267A (en) * 1968-12-27 1972-01-11 Boeing Co Method of diffusion bonding honeycomb composite structures
US3981429A (en) * 1970-10-16 1976-09-21 Rohr Industries, Inc. Method for plated foil liquid interface diffusion bonding of titanium
US4013210A (en) * 1972-08-21 1977-03-22 Czeslaw Deminet Method of diffusion bonding
US3846903A (en) * 1973-07-13 1974-11-12 Us Air Force Vacuum brazing tantalum alloys
FR2452601A1 (fr) * 1979-03-30 1980-10-24 Snecma Support amovible de revetement d'etancheite pour carter de soufflante de turboreacteur
DE2922835C2 (de) * 1979-06-06 1985-06-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Umfangsspaltdichtung an Axialströmungsmaschinen
FR2467977A1 (fr) * 1979-10-19 1981-04-30 Snecma Dispositif de securite en cas de rupture d'element rotatif de turbomachine
JPS57187242A (en) * 1981-05-15 1982-11-17 Tokyo Shibaura Electric Co Vacuum heat insulating plate
US4534698A (en) * 1983-04-25 1985-08-13 General Electric Company Blade containment structure
JPS62116132A (ja) * 1985-11-15 1987-05-27 石崎産業株式会社 段ボ−ル製の真空断熱包装材及びその製造方法
US4937125A (en) * 1987-06-19 1990-06-26 Etat Francais Lightweight sandwich designed for making multilayer structures resistant to impact and thermal aggressions
IE67360B1 (en) * 1990-09-25 1996-03-20 United Technologies Corp Apparatus and method for a stator assembly of a rotary machine
US5192623A (en) * 1990-10-23 1993-03-09 Lockhart Industries Laminated structural panels and the method of producing them
GB9307288D0 (en) * 1993-04-07 1993-06-02 Rolls Royce Plc Gas turbine engine casing construction
JPH091701A (ja) * 1995-06-21 1997-01-07 Toyota Central Res & Dev Lab Inc 真空断熱材及びハニカム板の製造方法
JPH11280199A (ja) * 1998-03-30 1999-10-12 Comany Kk 間仕切りパネル

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3235745A1 (de) 1981-09-29 1983-04-28 United Technologies Corp., 06101 Hartford, Conn. Isolierte wabendichtung

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10247031A1 (de) * 2002-10-09 2004-04-22 Alstom (Switzerland) Ltd. Vorrichtung zur Dichtung eines Dichtspalts bei einer Strömungsrotationsmaschine

Also Published As

Publication number Publication date
US6251494B1 (en) 2001-06-26
EP0967363B1 (fr) 2003-05-02
DE59905282D1 (de) 2003-06-05
EP0967363A3 (fr) 2000-11-22
DE19828065A1 (de) 1999-12-30

Similar Documents

Publication Publication Date Title
EP0967363B1 (fr) Joint de type nid d'abeille spécialement pour une turbine à gaz
DE68912116T2 (de) Segmentierte dichtungsplatte für turbinenmotor.
DE69822720T2 (de) Dichtung zwischen den Stufen einer Gasturbine
EP1320662B1 (fr) Systeme de garniture d'etancheite
DE60217456T2 (de) Abreibbare Beschichtung für Mantelringe von Gasturbinen
EP1111195B1 (fr) Surface structurée utilisée comme couche de rasage dans les turbomachines
DE102004023879B4 (de) Axialdampfturbine
DE60017293T2 (de) Werkstoffe für Dichtungen und Beilagscheiben von verstellbaren Leitschaufeln
EP1149985B1 (fr) Structure de virole métallique
DE19617556A1 (de) Thermisch belastete Schaufel für eine Strömungsmaschine
DE3347380A1 (de) Dichtungsvorrichtung für bewegbare Schaufeln von Turbomaschinen mit Echtzeitsteuerung des Spiels sowie Verfahren zur Bestimmung der Vorrichtung
DE69811624T2 (de) Gasturbinenrotorschaufel
CH698801B1 (de) Dichtungsanordnung an einer Turbine.
EP1076161A2 (fr) Régulation de jeu d'extrémité entre rotor et stator d'une turbomachine
DE19809008A1 (de) Gasturbinenschaufel
CH704935B1 (de) Stator-Rotor-Anordnung, Strömungsmaschine und Verfahren zum Herstellen einer Struktur aus umgekehrten Turbulatoren
EP1456508A1 (fr) Sous-groupe de parcours de gaz chauds de turbine a gaz
EP1375696A2 (fr) Systéme de revêtement pour rotor/stator joint détanchéité d'une turbo machine
DE3125469C2 (fr)
DE69824089T2 (de) Dichtstreifen für Deckplatten von Gasturbinenleitschaufeln
DE19814442B4 (de) Gasturbinen-Dichtungsvorrichtung
EP1056932B1 (fr) Enveloppe de turbine
DE69823143T2 (de) Spindelabdichtung für Gasturbine
EP1013890A2 (fr) Joint abradable pour turbomachines
DE1942346A1 (de) Vorrichtung zur Abdichtung des Rotors gegenueber dem Stator bei einer zu einem Gasturbinentriebwerk gehoerigen Turbine

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): DE FR GB

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

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

Owner name: ROLLS-ROYCE DEUTSCHLAND GMBH

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 CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

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

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

17P Request for examination filed

Effective date: 20010301

AKX Designation fees paid

Free format text: DE FR GB

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

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

REF Corresponds to:

Ref document number: 59905282

Country of ref document: DE

Date of ref document: 20030605

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
ET Fr: translation filed
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: 20040203

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

Ref country code: FR

Payment date: 20110607

Year of fee payment: 13

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

Ref country code: GB

Payment date: 20110525

Year of fee payment: 13

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

Ref country code: DE

Payment date: 20110527

Year of fee payment: 13

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

Effective date: 20120522

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20130131

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 59905282

Country of ref document: DE

Effective date: 20121201

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: 20120531

Ref country code: GB

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

Effective date: 20120522

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: 20121201