EP2872782B1 - Aube de turbomachine ayant un profil configuré de manière à obtenir des propriétés aérodynamiques et mécaniques améliorées - Google Patents

Aube de turbomachine ayant un profil configuré de manière à obtenir des propriétés aérodynamiques et mécaniques améliorées Download PDF

Info

Publication number
EP2872782B1
EP2872782B1 EP13744659.7A EP13744659A EP2872782B1 EP 2872782 B1 EP2872782 B1 EP 2872782B1 EP 13744659 A EP13744659 A EP 13744659A EP 2872782 B1 EP2872782 B1 EP 2872782B1
Authority
EP
European Patent Office
Prior art keywords
vane
turbomachine
height
blade
tangential
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP13744659.7A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2872782A1 (fr
Inventor
Laurent Jablonski
Hanna Reiss
Jérôme Talbotec
Sandrine QUEVREUX
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Services SA
SNECMA SAS
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 SNECMA Services SA, SNECMA SAS filed Critical SNECMA Services SA
Publication of EP2872782A1 publication Critical patent/EP2872782A1/fr
Application granted granted Critical
Publication of EP2872782B1 publication Critical patent/EP2872782B1/fr
Active 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines

Definitions

  • the present invention relates to the field of turbomachine blades, and finds a particular application for metal blades of the blower, the high-pressure compressor or the low-pressure compressor of a turbomachine.
  • the blades of a turbomachine are subjected to high speeds of rotation; the aerodynamic and mechanical performance of the blades are therefore crucial to ensure proper operation of the turbomachine.
  • this document proposes to improve the aerodynamic performance of a blade by giving it a geometry described as the combination of a relatively low belly and pronounced with sharply backward sharping in the longitudinal and tangential directions.
  • the present invention aims to remedy this situation by proposing a blade combining high aerodynamic and mechanical performance.
  • said first and second heights are between 90% and 95% of the height H of the blade.
  • said first and second heights are equal.
  • the invention also relates to a turbomachine fan, a low pressure compressor or a high pressure compressor comprising a plurality of vanes as defined above.
  • the invention further relates to a turbomachine comprising a plurality of blades as defined above.
  • the figure 1 schematically and partially shows the fan 2 of a turbomachine, typically a turbojet engine having use in the aeronautics.
  • the fan 2 consists of a plurality of vanes 4 regularly spaced around a disk 6 (commonly called a hub) of a rotor centered on a longitudinal axis XX of the fan 2.
  • Each blade 4 commonly comprises a blade 8, a foot 10 and a head 12.
  • the root 10 of the blade is mounted on the disc 6 of the rotor and is connected to the blade 8 via a platform 14 delimiting the gaseous flow 16 passing through the fan 2.
  • the disk 6 of the rotor is rotated about the longitudinal axis XX in the direction indicated by the arrow 18.
  • the head 12 of the blade is in turn facing the inner face 20 of a fixed casing of the blower, this face 20 also defining the vein 16, which is therefore between the platform 14 and the face internal 20 of the housing.
  • the blade 8 is composed of a plurality of blade sections 22 which are stacked along a radial axis Z-Z perpendicular to the axis X-X.
  • the blade sections 22 are located at increasing radial distances from the longitudinal axis X-X.
  • the resulting stack forms an aerodynamic surface which extends along the longitudinal axis XX between a leading edge 24 and a trailing edge 26 and along a tangential axis YY of the fan between a lower face, opposite the traction, and an extrados face, the side of the traction (not shown in the figures).
  • the blade has a height H, measured from the foot 10 to the head 12 of the blade along the radial axis Z-Z. It is defined that the section of the blade situated at 0% of the height H corresponds to the radius of intersection between the leading edge 24 and the internal flow vein of the gas flow, and the section located at 100% of the height H corresponds to the point at the intersection radius between the leading edge 24 and the upper flow of the gaseous flow stream.
  • the longitudinal axis X-X, the tangential axis Y-Y and the radial axis Z-Z of the blower thus defined form a direct orthonormal trihedron.
  • the present invention applies to different types of moving blades of a turbomachine; for example the blades of the fan, the high pressure compressor, that is to say the compressor upstream of the direction of the flow of flow, and high pressure compressor, that is to say the compressor downstream in the flow direction of the flow.
  • the figure 1 which has a partial view of a turbomachine fan is purely illustrative, and allows in particular to define the different axes of the turbomachine.
  • the Figures 2 and 3 are examples of curves showing the evolution of laws Xg and Yg respectively on a part of the height of a blade according to the invention.
  • the present invention proposes a change in the direction of the slope of these distribution laws Xg and Yg in the head portion of the blade, that is to say in the upper 10% of the dawn forming the head 12.
  • These heights are typically between 90% and 95% of the height H of the blade.
  • the value of the height between 90% and 100% of the height H of the blade from which the distribution law Xg decreases and the value of the height between 90% and 100% of the height H of the dawn from which the distribution law Yg decreases may be identical or distinct.
  • the laws of longitudinal distribution Xg and tangential Yg defining the positioning of the respective centers of gravity of the sections of blades formed forming the blade, with respect to the longitudinal axes XX and tangential YY typically comprise a single change of direction of their slope for values height between 90 and 100% of the height H of the blade from its base.
  • the dawn according to the invention therefore has a profile which, between 90 and 100% of its height from its base, moves towards the leading edge 24 and towards the upper surface, which corresponds to a tilting forward and towards the upper surface of the head portion of dawn.
  • the figures 3 and 4 present respectively an example of longitudinal distribution law Xg and tangential Yg over the entire height of the blade.
  • the figure 6 is a graph showing the efficiency gain obtained by a blade according to the invention with respect to known blades.
  • This figure shows three curves 100, 102 and 104, which illustrate the yield obtained respectively with a blade according to the invention, with a blade according to the state of the art having no inflection in the head, and with a blade according to the state of the art having an inflection of its longitudinal distribution law Xg at the head.
  • the present invention improves the efficiency in the upper part of the blade. It is further observed that the modification of the head of the blade causes a change in performance over a much larger range of heights; by modifying the geometry of 10% of the dawn one acts on the aerodynamic efficiency of more than 50% of the dawn.
  • the present invention makes it possible to increase the mechanical strength of the blade.
  • the present invention finds particular application on blades made of metallic material, for example on blades of reduced dimensions, typically of the order of 40 to 50 inches, that is to say, from 101.60 cm to 127 cm. .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13744659.7A 2012-07-12 2013-06-28 Aube de turbomachine ayant un profil configuré de manière à obtenir des propriétés aérodynamiques et mécaniques améliorées Active EP2872782B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1256746A FR2993323B1 (fr) 2012-07-12 2012-07-12 Aube de turbomachine ayant un profil configure de maniere a obtenir des proprietes aerodynamiques et mecaniques ameliorees
PCT/FR2013/051522 WO2014009628A1 (fr) 2012-07-12 2013-06-28 Aube de turbomachine ayant un profil configuré de manière à obtenir des propriétés aérodynamiques et mécaniques améliorées

Publications (2)

Publication Number Publication Date
EP2872782A1 EP2872782A1 (fr) 2015-05-20
EP2872782B1 true EP2872782B1 (fr) 2017-03-08

Family

ID=46826816

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13744659.7A Active EP2872782B1 (fr) 2012-07-12 2013-06-28 Aube de turbomachine ayant un profil configuré de manière à obtenir des propriétés aérodynamiques et mécaniques améliorées

Country Status (9)

Country Link
US (1) US9995156B2 (pt)
EP (1) EP2872782B1 (pt)
JP (2) JP2015522132A (pt)
CN (1) CN104583604B (pt)
BR (1) BR112015000676B1 (pt)
CA (1) CA2878827C (pt)
FR (1) FR2993323B1 (pt)
RU (1) RU2624677C2 (pt)
WO (1) WO2014009628A1 (pt)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3043428B1 (fr) * 2015-11-10 2020-05-29 Safran Aircraft Engines Aube de redresseur de turbomachine
JP6959589B2 (ja) * 2018-11-05 2021-11-02 株式会社Ihi 軸流流体機械の動翼
FR3129686B1 (fr) * 2021-11-29 2024-07-12 Safran Aircraft Engines Aube pour une soufflante carénée d’une turbomachine

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB680036A (en) * 1949-04-26 1952-10-01 Francis Henry Keast Blading for rotary compressors, turbines and the like
US4012172A (en) * 1975-09-10 1977-03-15 Avco Corporation Low noise blades for axial flow compressors
SU1613701A1 (ru) * 1988-07-15 1990-12-15 Харьковский авиационный институт им.Н.Е.Жуковского Лопатка осевой турбомашины
US5088892A (en) 1990-02-07 1992-02-18 United Technologies Corporation Bowed airfoil for the compression section of a rotary machine
JPH07139302A (ja) * 1993-11-17 1995-05-30 Ishikawajima Harima Heavy Ind Co Ltd ブレードの構造
DE19812624A1 (de) * 1998-03-23 1999-09-30 Bmw Rolls Royce Gmbh Rotor-Schaufelblatt einer Axialströmungsmaschine
US6331100B1 (en) * 1999-12-06 2001-12-18 General Electric Company Doubled bowed compressor airfoil
DE10054244C2 (de) * 2000-11-02 2002-10-10 Honda Motor Co Ltd Turbinenblattanordnung und Turbinenblatt für eine Axialturbine
US6508630B2 (en) * 2001-03-30 2003-01-21 General Electric Company Twisted stator vane
FR2851798B1 (fr) * 2003-02-27 2005-04-29 Snecma Moteurs Aube en fleche de turboreacteur
DE102005025213B4 (de) * 2005-06-01 2014-05-15 Honda Motor Co., Ltd. Schaufel einer Axialströmungsmaschine
FR2908152B1 (fr) * 2006-11-08 2009-02-06 Snecma Sa Aube en fleche de turbomachine
GB0701866D0 (en) * 2007-01-31 2007-03-14 Rolls Royce Plc Tone noise reduction in turbomachines
US8083487B2 (en) * 2007-07-09 2011-12-27 General Electric Company Rotary airfoils and method for fabricating same
EP2017466A1 (en) * 2007-07-20 2009-01-21 Siemens Aktiengesellschaft Wind turbine rotor blade and turbine rotor
RU2354854C1 (ru) * 2007-12-20 2009-05-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Рабочее колесо высокооборотного осевого вентилятора или компрессора
US8167567B2 (en) * 2008-12-17 2012-05-01 United Technologies Corporation Gas turbine engine airfoil
JP4923073B2 (ja) * 2009-02-25 2012-04-25 株式会社日立製作所 遷音速翼
FR2969230B1 (fr) * 2010-12-15 2014-11-21 Snecma Aube de compresseur a loi d'empilage amelioree
JP5703750B2 (ja) * 2010-12-28 2015-04-22 株式会社Ihi ファン動翼及びファン
US9062554B2 (en) * 2012-01-03 2015-06-23 General Electric Company Gas turbine nozzle with a flow groove

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
CN104583604B (zh) 2017-04-12
US20150192024A1 (en) 2015-07-09
FR2993323B1 (fr) 2014-08-15
RU2015104651A (ru) 2016-08-27
RU2624677C2 (ru) 2017-07-05
EP2872782A1 (fr) 2015-05-20
CA2878827A1 (fr) 2014-01-16
US9995156B2 (en) 2018-06-12
BR112015000676A2 (pt) 2017-06-27
CA2878827C (fr) 2019-08-27
JP2018155248A (ja) 2018-10-04
JP6649981B2 (ja) 2020-02-19
WO2014009628A1 (fr) 2014-01-16
BR112015000676B1 (pt) 2021-09-28
JP2015522132A (ja) 2015-08-03
FR2993323A1 (fr) 2014-01-17
CN104583604A (zh) 2015-04-29

Similar Documents

Publication Publication Date Title
EP2673472B1 (fr) Ensemble pale-plateforme pour ecoulement subsonique
EP1447525B1 (fr) Réalisation de turbines pour turbomachines ayant des aubes à fréquences de résonance ajustées différentes et une telle turbine étagée
EP2834470B1 (fr) Aube de rotor de turbomachine, disque d'aubes monobloc, rotor de compresseur et rotor de soufflante associés
EP2673473B1 (fr) Ensemble pale-plateforme pour ecoulement supersonique.
EP3315721B1 (fr) Renfort de bord d'attaque d'une aube de turbomachine
CA2966302C (fr) Aube composite comprenant une plateforme munie d'un raidisseur
CA2610278A1 (fr) Aube en fleche de turbomachine
EP2872782B1 (fr) Aube de turbomachine ayant un profil configuré de manière à obtenir des propriétés aérodynamiques et mécaniques améliorées
FR3085712A1 (fr) Aube de roue mobile pour turbomachine d'aeronef, presentant un talon decouple de la pale de l'aube
EP3123001B1 (fr) Pièce de révolution pour un rotor de turbomachine, rotor de turbomachine, module de turbomachine et turbomachine associés
EP2880265B1 (fr) Aube mobile de turbine
EP2976507B1 (fr) Aube et angle de diedre d'aube
FR3049643A1 (fr) Roue a pales rapportees et turbomachine equipee d'une telle roue
EP3334905B1 (fr) Aube de rotor de compresseur de turbomachine
FR3025562B1 (fr) Disque aubage monobloc pour une turbomachine
WO2023041868A1 (fr) Aube mobile pour turbine de turbomachine, comprenant une échasse équipée d'excroissances de retenue radiale de l'aube
FR3108664A1 (fr) Rotor de soufflante comprenant des aubes à centre de gravité en amont
FR3081521A1 (fr) Aube de turbomachine dont des sections presentent une portion aval d'epaisseur reduite
FR3107721A1 (fr) Pale de redresseur de turbomachine, secteur de redresseur et un procédé de fabrication
FR3087828A1 (fr) Aubage mobile de turbomachine
FR3027353A1 (fr) Roue de turbomachine

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

17P Request for examination filed

Effective date: 20150212

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

DAX Request for extension of the european patent (deleted)
RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/14 20060101ALI20160414BHEP

Ipc: F01D 9/02 20060101ALI20160414BHEP

Ipc: F04D 29/32 20060101AFI20160414BHEP

Ipc: F04D 29/38 20060101ALI20160414BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160629

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

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

GRAL Information related to payment of fee for publishing/printing deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR3

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTC Intention to grant announced (deleted)
INTG Intention to grant announced

Effective date: 20161114

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

Ref country code: AT

Ref legal event code: REF

Ref document number: 873794

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170315

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602013018313

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 5

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

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: 20170308

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

Ref country code: NO

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

Effective date: 20170608

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: 20170308

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: 20170308

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: 20170609

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: 20170308

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 873794

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170308

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: 20170308

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: 20170608

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: 20170308

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: 20170308

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: 20170308

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

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: 20170308

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: 20170308

Ref country code: AT

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: 20170308

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: 20170308

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: 20170308

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

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: 20170710

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: 20170308

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: 20170708

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: 20170308

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602013018313

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

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

Ref country code: MC

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

Effective date: 20170308

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: 20170308

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

26N No opposition filed

Effective date: 20171211

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: 20170308

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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: 20170628

Ref country code: LU

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

Effective date: 20170628

Ref country code: CH

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

Effective date: 20170630

Ref country code: LI

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

Effective date: 20170630

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170630

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

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: 20170630

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: 20170308

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: 20130628

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

Effective date: 20170308

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

Ref country code: MK

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

Effective date: 20170308

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: 20170308

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: 20170308

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

Ref country code: GB

Payment date: 20240521

Year of fee payment: 12

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

Ref country code: DE

Payment date: 20240521

Year of fee payment: 12

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

Ref country code: IT

Payment date: 20240522

Year of fee payment: 12

Ref country code: FR

Payment date: 20240522

Year of fee payment: 12

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

Ref country code: SE

Payment date: 20240521

Year of fee payment: 12