EP1705339B1 - Arbre de rotor, particulièrement pour une turbine à gaz - Google Patents

Arbre de rotor, particulièrement pour une turbine à gaz Download PDF

Info

Publication number
EP1705339B1
EP1705339B1 EP06110741.3A EP06110741A EP1705339B1 EP 1705339 B1 EP1705339 B1 EP 1705339B1 EP 06110741 A EP06110741 A EP 06110741A EP 1705339 B1 EP1705339 B1 EP 1705339B1
Authority
EP
European Patent Office
Prior art keywords
rotor shaft
cooling air
rotor
air channels
cavities
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
EP06110741.3A
Other languages
German (de)
English (en)
Other versions
EP1705339A3 (fr
EP1705339A2 (fr
Inventor
Markus Roland Wiebe
Thomas Kramer
Holger Kiewel
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.)
Ansaldo Energia IP UK Ltd
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 EP1705339A2 publication Critical patent/EP1705339A2/fr
Publication of EP1705339A3 publication Critical patent/EP1705339A3/fr
Application granted granted Critical
Publication of EP1705339B1 publication Critical patent/EP1705339B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical

Definitions

  • the present invention relates to the field of rotary machines. It relates to a rotor shaft, in particular for a gas turbine, according to the preamble of claim 1.
  • a rotor disk with an elliptical cooling air opening arranged in the rotor disk is known.
  • additional cooling measures are often provided in order to achieve a sufficient service life of the material used at the high hot gas temperatures.
  • Such cooling measures include cooling air ducts which extend approximately in the radial direction from the inside to the outside through the rotor shaft and cooling air from an internal cooling air supply to the surface lead the rotor shaft.
  • cooling air ducts represent mechanical weakenings of the rotor shaft, which can have a negative effect on the high temperatures and centrifugal forces and the changing loads.
  • An essential point of the present solution is that the cooling air ducts for reducing mechanical stresses have an elliptical cross-section.
  • the rotor shaft further has a compressor part and a turbine part and the cooling air passages are arranged in the turbine part.
  • the turbine part has a plurality of rotor disks arranged one behind the other in the axial direction for fastening rotor blades, wherein the cooling air ducts are arranged between adjacent rotor disks.
  • An embodiment of the invention is characterized in that the cooling air ducts are arranged distributed over the circumference of the rotor shaft, and that the elliptical cross section of the cooling air ducts is oriented in each case so that the large main axis in the circumferential direction and the small main axis are aligned in the axial direction.
  • cavities are formed concentrically to the rotor axis in the interior of the rotor shaft, and that the cooling air channels emanate from at least one of the cavities and via this cavity with the Cooling air supply communicate. It is then particularly favorable for the cavities to have at least sections an elliptical cross-sectional contour to reduce mechanical stresses on the outer circumference, wherein the cross-sectional contour is preferably composed on the outer circumference of two elliptical sections of two mutually tilted ellipses whose major axes are oriented approximately in the radial direction are.
  • a rotor shaft 10 (without blading) reproduced a gas turbine.
  • the to the rotor axis (17 in Fig. 2 The rotationally symmetrical rotor shaft 10 is subdivided into a compressor part 11 and a turbine part 12. Between the two parts 11 and 12, the combustion chamber is arranged inside the gas turbine into which the air compressed in the compressor part 11 is introduced and from which the hot gas through the turbine part 12 flows.
  • the turbine part 12 has a plurality of rotor disks 13 arranged one behind the other in the axial direction, in which Fig. 3, 4 Axially aligned receiving slots 21 are formed around the circumference for receiving corresponding blades.
  • cooling air channels 14 are provided, which approximately radially outwardly depart from a formed inside the rotor shaft 10 cavity 15 and open at the surface of the rotor shaft 10 in the outer space ( Fig. 2 ).
  • the cavity 15 is in communication with a central, axially extending cooling air supply 16.
  • the cooling air channels (14 ') had a circular cross section, the cooling air channels 14 in the new configuration of Fig. 4 for reasons of mechanical stability an elliptical cross-section.
  • the elliptical cross section of the cooling air ducts 14 can already be predetermined during the casting of the rotor shaft. However, it is also conceivable to introduce such a cross section into the rotor shaft 10 by special machining methods such as eroding.
  • the ellipses of the channel cross-section of the cooling air channels 14 are oriented so that the major major axes are oriented in the circumferential direction, while the small main axes are parallel to the rotor axis 17. As a result, a maximum reduction of the mechanical stresses is achieved. It goes without saying that the advantages of an elliptical cross section are not limited to cooling air channels in the rotor shaft itself, but also apply to cooling air channels, which are arranged on other parts of the rotor such as blades or the like.
  • the concentric to the rotor axis 17 formed cavity 15 is also optimized in its cross-sectional profile in view of the mechanical stresses occurring.
  • the optimization of the cross-sectional profile takes place in the in Fig. 5 for further cavities 19, 20 in the compressor part 11 illustrated manner such that the edge contour on the outer circumference of the cavity 15, 19, 20 is formed at least partially elliptical.
  • the cross-sectional contour is at the outer periphery - as for the cavity 20 in Fig. 5 is shown - from two elliptical sections of two mutually tilted ellipses E1, E2 (in Fig. 5 dashed lines drawn together) whose major axes are oriented approximately in the radial direction.
  • Such a shape for the cavities present in the interior of the rotor shaft 10 is advantageous not only in connection with the cooling air channels 14 in the turbine part, but can also be used for other cavities 19, 20 which are located, for example, in the compressor part 11 of the rotor shaft 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (5)

  1. Arbre de rotor (10), plus particulièrement pour une turbine à gaz, dans laquelle des canaux d'air de refroidissement (14) sont prévus, qui s'étendent globalement dans la direction radiale de l'intérieur vers l'extérieur et qui sont reliés avec une alimentation en air de refroidissement (16) existant à l'intérieur de l'arbre du rotor (10), les canaux d'air de refroidissement (14) présentant, pour la réduction des contraintes mécaniques, une section elliptique et l'arbre de rotor (10) comprenant une partie de compresseur (11) et une partie de turbine (12) et les canaux d'air de refroidissement (14) étant disposés dans la partie de turbine (12), caractérisé en ce que la partie de turbine (12) comprend plusieurs disques de rotor (13) disposés les uns derrière les autres dans la direction axiale pour la fixation de pales et en ce que les canaux d'air de refroidissement (14) sont disposés entre des disques de rotor (13) adjacents.
  2. Arbre de rotor selon la revendication 1, caractérisé en ce que les canaux d'air de refroidissement (14) sont répartis sur la circonférence de l'arbre de rotor (10) et en ce que la section elliptique des canaux d'air de refroidissement (14) est orientée de façon à ce que le grand axe principal soit orienté dans la direction circonférentielle et le petit axe principale soit orienté dans la direction axiale.
  3. Arbre de rotor selon l'une des revendications 1 et 2, caractérisé en ce que, à l'intérieur de l'arbre de rotor (10), se trouvent des espaces creux (15, 19, 20) concentriques par rapport à l'axe du rotor (17) et en ce que les canaux d'air de refroidissement (14) sortent d'au moins un des espaces creux (15, 19, 20) et sont reliés, par l'intermédiaire de cet espace creux (15), avec l'alimentation en air de refroidissement (16).
  4. Arbre de rotor selon la revendication 3, caractérisé en ce que les espaces creux (15, 19, 20) présentent, pour la réduction des contraintes mécaniques sur la circonférence externe, au moins partiellement un contour de section elliptique (E1, E2).
  5. Arbre de rotor selon la revendication 4, caractérisé en ce que le contour de section sur la circonférence externe est constitué de deux portions elliptiques de deux ellipses (E1, E2) basculées l'une contre l'autre, dont les grands axes principaux sont orientés approximativement dans la direction radiale.
EP06110741.3A 2005-03-23 2006-03-07 Arbre de rotor, particulièrement pour une turbine à gaz Not-in-force EP1705339B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH5042005 2005-03-23

Publications (3)

Publication Number Publication Date
EP1705339A2 EP1705339A2 (fr) 2006-09-27
EP1705339A3 EP1705339A3 (fr) 2013-11-06
EP1705339B1 true EP1705339B1 (fr) 2016-11-30

Family

ID=35335753

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06110741.3A Not-in-force EP1705339B1 (fr) 2005-03-23 2006-03-07 Arbre de rotor, particulièrement pour une turbine à gaz

Country Status (2)

Country Link
US (1) US7329086B2 (fr)
EP (1) EP1705339B1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH699996A1 (de) 2008-11-19 2010-05-31 Alstom Technology Ltd Verfahren zum bearbeiten eines gasturbinenläufers.
CH702191A1 (de) 2009-11-04 2011-05-13 Alstom Technology Ltd Geschweisster Rotor.
EP2837769B1 (fr) * 2013-08-13 2016-06-29 Alstom Technology Ltd Arbre de rotor pour turbomachine
JP2015178832A (ja) 2014-03-19 2015-10-08 アルストム テクノロジー リミテッドＡＬＳＴＯＭ Ｔｅｃｈｎｏｌｏｇｙ Ｌｔｄ 冷却孔入口を備えるロータ軸
FR3028883B1 (fr) * 2014-11-25 2019-11-22 Safran Aircraft Engines Arbre de rotor de turbomachine comportant une surface d'echange thermique perfectionnee
EP3205817A1 (fr) 2016-02-09 2017-08-16 Ansaldo Energia Switzerland AG Rotor refroidi par fluide pour une turbine à gaz
US10177618B2 (en) 2016-03-15 2019-01-08 General Atomics Rotor assembly and method of manufacturing
US10458242B2 (en) * 2016-10-25 2019-10-29 Pratt & Whitney Canada Corp. Rotor disc with passages

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2575568A (en) * 1946-11-12 1951-11-20 Gulf Research Development Co Centrifugal gas-liquid separator
FR2552817B1 (fr) * 1978-11-27 1988-02-12 Snecma Perfectionnements au refroidissement des rotors de turbines
US4344738A (en) * 1979-12-17 1982-08-17 United Technologies Corporation Rotor disk structure
FR2732405B1 (fr) * 1982-03-23 1997-05-30 Snecma Dispositif pour refroidir le rotor d'une turbine a gaz
GB2189845B (en) 1986-04-30 1991-01-23 Gen Electric Turbine cooling air transferring apparatus
FR2614654B1 (fr) * 1987-04-29 1992-02-21 Snecma Disque de compresseur axial de turbomachine a prelevement d'air centripete
FR2616480B1 (fr) * 1987-06-10 1989-09-29 Snecma Dispositif de verrouillage d'aubes a pied marteau sur un disque de turbomachine et procedes de montage et de demontage
GB2265671A (en) 1992-03-24 1993-10-06 Rolls Royce Plc Bladed rotor for a gas turbine engine
DE4324034A1 (de) * 1993-07-17 1995-01-19 Abb Management Ag Gasturbine mit gekühltem Rotor
DE4428207A1 (de) * 1994-08-09 1996-02-15 Bmw Rolls Royce Gmbh Turbinen-Laufradscheibe mit gekrümmtem Kühlluftkanal sowie Herstellverfahren hierfür
DE19620828C1 (de) * 1996-05-23 1997-09-04 Siemens Ag Turbinenwelle sowie Verfahren zur Kühlung einer Turbinenwelle
GB9615394D0 (en) * 1996-07-23 1996-09-04 Rolls Royce Plc Gas turbine engine rotor disc with cooling fluid passage
JP3621523B2 (ja) * 1996-09-25 2005-02-16 株式会社東芝 ガスタービンの動翼冷却装置
DE19705441A1 (de) * 1997-02-13 1998-08-20 Bmw Rolls Royce Gmbh Turbinen-Laufradscheibe
JP3316418B2 (ja) 1997-06-12 2002-08-19 三菱重工業株式会社 ガスタービン冷却動翼
AT3140U1 (de) * 1998-11-06 1999-10-25 Avl List Gmbh Kurbelgehäuse für eine brennkraftmaschine
DE19941134C1 (de) * 1999-08-30 2000-12-28 Mtu Muenchen Gmbh Schaufelkranz für eine Gasturbine
US6474946B2 (en) * 2001-02-26 2002-11-05 United Technologies Corporation Attachment air inlet configuration for highly loaded single crystal turbine blades

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
EP1705339A3 (fr) 2013-11-06
EP1705339A2 (fr) 2006-09-27
US20070086884A1 (en) 2007-04-19
US7329086B2 (en) 2008-02-12

Similar Documents

Publication Publication Date Title
EP1705339B1 (fr) Arbre de rotor, particulièrement pour une turbine à gaz
DE69914199T2 (de) Langsamlaufender hochdruckturbolader
DE60020477T2 (de) Kühlluftzufuhr durch die Verbindungsflansche eines Turbinenrotors
EP2024608B1 (fr) Turbocompresseur en montage axial
DE3940981C2 (de) Auswuchtgewicht zum Auswuchten des Rotors eines Gasturbinentriebwerks
EP2503246B1 (fr) Tête de chambre de combustion segmentée
EP3056683B1 (fr) Bague intérieure séparée axialement pour une turbomachine et stator
EP1536102B1 (fr) Rotor pour une turbine à vapeur
DE60302525T2 (de) Trommelrotor für eine Turbomaschine
EP2881541A1 (fr) Refroidissement de pointe d'aube d'un aube de rotor de turbine à gaz
EP2818724B1 (fr) Turbomachine et procédé
DE102014204468A1 (de) Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung
EP3336313A1 (fr) Ensemble d'aube mobile pour turbines d'une turbine turbine à gaz et procédé de fourniture d'air sceau dans un ensemble d'aube mobile pour turbines
EP2617947B1 (fr) Turbine à gaz d'avion avec soufflante ajustable
DE3638960C1 (de) Gasturbinenstrahltriebwerk mit einem gekuehlten Hochdruckverdichter
EP2054587B1 (fr) Boîtier de turbine
CH701151B1 (de) Turbomaschine mit einem Verdichterradelement.
EP3321589B1 (fr) Buse de carburant d'une turbine à gaz dotée du générateur de tourbillons
EP3312388B1 (fr) Pièce de rotor, compresseur, turbine et procédé de fabrication associés
EP3176385B1 (fr) Boitier de stator pour une turbomachine et turbomachine comprenant un boitier de stator
DE60002781T2 (de) Nabe-Achse Verbindung
EP4219897A1 (fr) Rotor comprenant une bride d'équilibrage, ensemble rotor comprenant au moins un rotor et turbomachine comprenant au moins un rotor ou un ensemble rotor
EP2772652A2 (fr) Paroi intermédiaire pour isoler de façon étanche l'espace arrière d'un compresseur radial
EP3327258A1 (fr) Roue de guidage d'entrée pour une turbomachine
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): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

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 IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/08 20060101AFI20131003BHEP

17P Request for examination filed

Effective date: 20131206

RBV Designated contracting states (corrected)

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

AKX Designation fees paid

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

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160617

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

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH

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

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 849997

Country of ref document: AT

Kind code of ref document: T

Effective date: 20161215

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: 502006015263

Country of ref document: DE

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

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: 20161130

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20161130

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: 20170301

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: 20161130

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: 20161130

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

Ref country code: DE

Payment date: 20170322

Year of fee payment: 12

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: 20161130

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: 20161130

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: 20161130

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: 20170330

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

Ref country code: GB

Payment date: 20170322

Year of fee payment: 12

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: ANSALDO ENERGIA IP UK LIMITED

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161130

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

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: 20161130

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: 20161130

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: 20161130

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: 20161130

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: 20161130

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

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: 20170228

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

Ref country code: IT

Payment date: 20170323

Year of fee payment: 12

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502006015263

Country of ref document: DE

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

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

26N No opposition filed

Effective date: 20170831

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: 20161130

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: 20161130

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20171130

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: 20170331

Ref country code: LU

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

Effective date: 20170307

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

Ref country code: IE

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

Effective date: 20170307

Ref country code: LI

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

Effective date: 20170331

Ref country code: CH

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

Effective date: 20170331

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170331

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 849997

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170307

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: 20170331

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: 20170307

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502006015263

Country of ref document: DE

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

Effective date: 20180307

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: 20181002

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: 20180307

Ref country code: IT

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

Effective date: 20180307

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: 20060307

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

Ref country code: CY

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: 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: 20161130

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

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: 20170330