EP3075960A1 - Unité d'aubes directrices à profils aérodynamiques multiples - Google Patents

Unité d'aubes directrices à profils aérodynamiques multiples Download PDF

Info

Publication number
EP3075960A1
EP3075960A1 EP15161814.7A EP15161814A EP3075960A1 EP 3075960 A1 EP3075960 A1 EP 3075960A1 EP 15161814 A EP15161814 A EP 15161814A EP 3075960 A1 EP3075960 A1 EP 3075960A1
Authority
EP
European Patent Office
Prior art keywords
airfoil
platform
guide vane
platform member
vane unit
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
EP15161814.7A
Other languages
German (de)
English (en)
Other versions
EP3075960B1 (fr
Inventor
Herbert Brandl
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
Priority to EP15161814.7A priority Critical patent/EP3075960B1/fr
Priority to US15/084,145 priority patent/US20160290146A1/en
Priority to KR1020160038340A priority patent/KR20160117330A/ko
Priority to CN201610194226.9A priority patent/CN106014495A/zh
Priority to JP2016070822A priority patent/JP2016194300A/ja
Publication of EP3075960A1 publication Critical patent/EP3075960A1/fr
Application granted granted Critical
Publication of EP3075960B1 publication Critical patent/EP3075960B1/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting

Definitions

  • the present disclosure relates to a multi-airfoil guide vane unit as described in claim 1. It further relates to an airfoil member and a platform member for a guide vane unit of the described type.
  • vane twins, triplets or any multiples are required as they provide several benefits, such as, for instance, increased stiffness and lower platform leakage.
  • the multiples are cast in one piece. However, this requires complex tooling to enable precision cast and turns manufacturing expensive. Moreover, the cast yield rate of such multiples can be quite low for the big sizes required in stationary power generation turbines. Moreover, service deterioration of one single airfoil may require replacement and scrapping of an entire multi airfoil unit.
  • EP 1 176 284 A2 proposes a built multi-airfoil guide vane unit and to separately manufacture airfoil and platform members, and to join them by brazing. Separation after service for reconditioning purposes is difficult and expensive. Just like in one-piece casts, the whole arrangement is rigid and over-constrained, such that differential thermal expansion results in high thermal mismatch stresses, in turn limiting the service lifetime of the multi-vane unit.
  • a multi-airfoil guide vane unit comprising a first platform member, a second platform member, and at least two airfoil members.
  • the airfoil members have a longitudinal extent along an airfoil span width and two longitudinal ends. All airfoil members are rigidly affixed to a platform member at a first longitudinal end and at least one airfoil member is rigidly affixed to both platform members at both longitudinal ends.
  • At least one of the airfoil members is floatingly connected to one of the platform members at a second longitudinal end, and a longitudinally floating joint arrangement is provided between the second longitudinal end of the airfoil member and the platform member, such as to allow displacement of the airfoil member relative to said platform member along the longitudinal extent of said airfoil member.
  • airfoil longitudinal direction may in particular be identical with a radial direction for the intended mounted state of the guide vane unit in a turbo-engine in case of an axial flow stage.
  • the multi-airfoil unit is less rigid and allows for relative movement between the members of the unit to account for differential thermal expansion.
  • the floating joint arrangement comprises a male joint feature provided at one of the second longitudinal end of the airfoil member and the platform member, and a female joint feature provided at the other one of the second longitudinal end of the airfoil member and the platform member, the male feature being received within said female feature.
  • the floating joint arrangement may particularly easy be provided.
  • the floating joint arrangement is intended for a defined displacement range, and the male member and female member are dimensioned such that the male member is at least with a part of its longitudinal extent received within the female member in a nominal built state as well as in all intended displaced positions.
  • the male joint feature is provided as a peg section at the second longitudinal end of the airfoil member and the female feature is a pocket provided in the platform member.
  • the male joint feature and in more specific embodiments a peg or the peg section may be particularly easy provided on the airfoil member, as the airfoil member is generally bar-shaped anyway.
  • the male feature outer surface is a ruled surface spanned by straight parallel lines. This will maintain a gap formed between the peg section and the lateral walls of the pocket constant along in all intended displacement positions.
  • a peg section provided at a longitudinal end of an airfoil member exhibits an airfoil-shaped cross section. This enables to avoid cross sectional jumps and other geometric discontinuities along the airfoil member longitudinal extent.
  • the male feature and the female feature are arranged and configured to form a running fit. That is, a narrow gap is provided between an outer boundary of the male feature and an inner boundary of the female feature. It will be appreciated, that the presence of the gap enables a free movement between the male feature and the female feature and thus the unconstrained displacement between the airfoil member and the platform member in one direction at the floating joint arrangement. Further, the narrower the gap is, the more constrained the airfoil member will be in all other directions. This constraint of movement in all other directions but the airfoil longitudinal direction may be found desirable in order to avoid oscillation modes incorporating an airfoil member end. Oscillation frequencies of the airfoil member are thus at least essentially maintained identical to those of a fully constrained airfoil member.
  • the running fit may be provided by a fitting member arranged within the female joint feature, wherein the fitting member is in particular provided as one of a bi-cast and an injection molding member. Said arrangement may serve to facilitate manufacturing.
  • the inner dimension of the female feature as such may be provided such as to provide a large clearance with the received male feature. This, in turn, means the female feature may be manufactured with a low demand as to accuracy. No high precision machining or manufacturing is required. Thus, providing the female feature as such is largely facilitated and is thus inexpensive.
  • a fitting member is produced within the female joint feature and embracing the male joint feature.
  • a concave form locking feature for instance a flute, is provided on inner walls of the female joint feature such that, when the fitting member is produced, the added material fills the gap between the female and the male joint features on the one hand, and at the same time creates a form lock with the walls of the female joint feature.
  • the fitting member is secured within the female joint feature.
  • Other appropriate concave and/or convex form-lock features in order to secure the fitting member may be provided inside the female joint feature.
  • the multi-airfoil guide vane unit is characterized in that a depth of the female joint feature is larger than a received length of the male joint feature such that a gap is provided between the bottom of the female joint feature and a tip of the male joint feature. Said feature enables improved longitudinal displacement capability, such that the male joint feature may displace deeper into the female feature if needed.
  • the multi-airfoil guide vane unit comprises three airfoils.
  • two outer airfoils are rigidly affixed to a platform member at both longitudinal ends and a middle airfoil member is rigidly affixed to a first platform member at one airfoil member end and is floatingly connected to the second platform member at the other airfoil member end.
  • the middle airfoil member is rigidly affixed to a platform member at both longitudinal ends, and each of two outer airfoil members is rigidly affixed to a platform member at its first end and is floatingly connected to a platform member at its second end.
  • both outer airfoil members may be rigidly affixed to the first platform member and floatingly connected to the second platform member, or a first outer airfoil member is rigidly affixed to the first platform member and is floatingly connected to the second platform member, and a second outer airfoil member is rigidly affixed to the second platform member and is floatingly connected to the first platform member.
  • an airfoil member wherein the male joint feature is provided in that a longitudinal end section of the airfoil member is provided with constant cross sections thus forming a generally cylindrical peg section.
  • a platform member wherein a female joint feature is provided in that the platform member comprises at least one pocket adapted and configured for receiving an airfoil member end section.
  • at least one concave form lock feature is provided on the side wall of the pocket, and is in particular provided as a circumferential groove, thus providing a form-lock feature for a fitting member, which fitting member serves to reduce play between the female joint feature and the male joint feature in the directions in which displacement is not desired.
  • FIG. 1 depicts a guide vane triplet 1.
  • the guide vane triplet comprises a radially inner platform member 14, a radially outer platform member 15, and three airfoil members 11, 12, and 13.
  • the airfoil members extend with their span width or longitudinal extent between the platform members.
  • Two outer airfoil members 11 and 13 are rigidly affixed to both platform members 14 and 15. Visible are braze or weld seams 16 at which airfoil members 11 and 13 are rigidly connected to the radially inner platform 14.
  • Airfoil members 11 and 13 are also rigidly connected to the radially outer platform 15, however, this is not visible in the present depiction. Airfoil members 11 and 13 are thus rigidly connected to a platform member on both respective longitudinal ends.
  • the middle airfoil member 12 is also at one longitudinal end rigidly connected to the radially outer platform member 15.
  • Airfoil member 12 is at its second end 121 floatingly connected to the radially inner platform member 14, in that the second end 121 is for instance received in a pocket 141 provided in the inner platform member 14. This allows displacement of the airfoil member 12 relative to the inner platform member 14 along the longitudinal extend of airfoil member 12.
  • a pocket 141 is provided as a female joint feature in the platform member 14.
  • the airfoil member 12 is at its longitudinal end 121 provided as a peg section 123, constituting a male joint feature.
  • the peg section is provided as a general cylinder, that is to say, the outer surface of the peg section is a ruled surface spanned by straight parallel lines.
  • Peg section 123 of airfoil member 12 is received in the pocket 141, with a gap provided between an inner surface of the pocket 141 and an outer surface of the peg section 123.
  • the airfoil member 12 may displace relative to the platform member 14 along the longitudinal direction indicated at 2 without changing the width of the gap between the peg section and the pocket.
  • Peg section 123 may exhibit an airfoil-shaped cross section, and thus constitute a continuation of the cross-sectional geometry of airfoil member 12, thus enabling to provide airfoil member 12 without cross sectional jumps or geometric discontinuities.
  • FIG. 3 a more detailed view of peg section 123 provided on an airfoil member end 121 and received in a pocket 141 of platform member 14 is shown.
  • An inner wall of the pocket is provided with a flute or other concave form locking feature 18, said flute in particular running around the circumference of the pocket.
  • a fitting member 17 is provided between the inner wall of the pocket 141 and an outer surface of the peg section 123, wherein said fitting member is arranged and configured to minimize lateral play of the peg section within the pocket.
  • Fitting member 17 is in a form-locked manner secured by concave form locking feature or flute 18 provided at the inner wall of pocket 141.
  • Said fitting member 17 and the peg-shaped end section 123 of the airfoil member 12 form a running fit with each other.
  • a minimum gap is still provided between the fitting member 17 and the peg -shaped end section of the airfoil 12, such as to allow a displacement of the airfoil member 12 relative to the platform member 14 along the longitudinal direction 2.
  • the fitting member 17 may in particular be manufactured for instance by bi-cast, as described for instance in US 5,797,725 , or metal injection molding, as described for instance in US 8,257,038 .
  • the peg-shaped end section 123 of the airfoil member 12 is inserted into the pocket 141, and subsequently material is introduced into the gap between the peg section outer surface and the pocket inner wall. Both processes mentioned above are known to create no metallurgical bonding between the bodies. Thus, the gap may be filled and the fitting member 17 may be produced which allows displacement of the airfoil member 12 inside the pocket 141 along the airfoil member longitudinal direction 2.
  • FIG 4 an alternative arrangement is shown, wherein the male joint feature 142 is arranged on the platform member 14 and received within the female joint feature 122 provided at an end 121 of the airfoil member 12.
  • the floating joined arrangement may also be provided at the radially outer platform.
  • embodiments are conceivable comprising two or more airfoil members which are floatingly connected to a platform member.
  • the floating connection is provided on the same, that is radially inner or outer, end of the airfoil members, but may also be provided on the radially inner end for some of the airfoil members and on the outer end for others.

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)
EP15161814.7A 2015-03-31 2015-03-31 Unité d'aubes directrices à profils aérodynamiques multiples Not-in-force EP3075960B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP15161814.7A EP3075960B1 (fr) 2015-03-31 2015-03-31 Unité d'aubes directrices à profils aérodynamiques multiples
US15/084,145 US20160290146A1 (en) 2015-03-31 2016-03-29 Multi-airfoil guide vane unit
KR1020160038340A KR20160117330A (ko) 2015-03-31 2016-03-30 다중-에어포일 가이드 베인 유닛
CN201610194226.9A CN106014495A (zh) 2015-03-31 2016-03-31 多翼型件引导叶片单元
JP2016070822A JP2016194300A (ja) 2015-03-31 2016-03-31 マルチ型翼ガイドベーンユニット

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15161814.7A EP3075960B1 (fr) 2015-03-31 2015-03-31 Unité d'aubes directrices à profils aérodynamiques multiples

Publications (2)

Publication Number Publication Date
EP3075960A1 true EP3075960A1 (fr) 2016-10-05
EP3075960B1 EP3075960B1 (fr) 2017-12-27

Family

ID=52814834

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15161814.7A Not-in-force EP3075960B1 (fr) 2015-03-31 2015-03-31 Unité d'aubes directrices à profils aérodynamiques multiples

Country Status (5)

Country Link
US (1) US20160290146A1 (fr)
EP (1) EP3075960B1 (fr)
JP (1) JP2016194300A (fr)
KR (1) KR20160117330A (fr)
CN (1) CN106014495A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3145187A1 (fr) * 2023-01-24 2024-07-26 Safran Aircraft Engines Carter de turbomachine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10767496B2 (en) 2018-03-23 2020-09-08 Rolls-Royce North American Technologies Inc. Turbine blade assembly with mounted platform
US10890081B2 (en) * 2018-04-23 2021-01-12 Rolls-Royce Corporation Turbine disk with platforms coupled to disk
US11466580B2 (en) 2018-05-02 2022-10-11 General Electric Company CMC nozzle with interlocking mechanical joint and fabrication
CN112975188B (zh) * 2021-03-18 2022-08-16 中国科学院工程热物理研究所 燃气轮机压气机静子三联叶片焊接装置

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
US5421703A (en) * 1994-05-25 1995-06-06 General Electric Company Positively retained vane bushing for an axial flow compressor
US5797725A (en) 1997-05-23 1998-08-25 Allison Advanced Development Company Gas turbine engine vane and method of manufacture
EP1176284A2 (fr) 2000-07-27 2002-01-30 General Electric Company Aubes de guidage avec col dépourvu de brasure
US20100111682A1 (en) * 2008-10-31 2010-05-06 Patrick Jarvis Scoggins Crenelated turbine nozzle
US20110002787A1 (en) * 2008-12-24 2011-01-06 Enrique Penalver Castro Blade Retention at a Compressor Rectifier Stage for Impact Resistance
US8257038B2 (en) 2008-02-01 2012-09-04 Siemens Energy, Inc. Metal injection joining
WO2014158284A2 (fr) * 2013-03-14 2014-10-02 Freeman Ted J Aube de turbine coulée en deux fois

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1366075A (en) * 1970-09-16 1974-09-11 Secr Defence Bladed fluid flow machines
US5634768A (en) * 1994-11-15 1997-06-03 Solar Turbines Incorporated Airfoil nozzle and shroud assembly
US8454303B2 (en) * 2010-01-14 2013-06-04 General Electric Company Turbine nozzle assembly

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
US5421703A (en) * 1994-05-25 1995-06-06 General Electric Company Positively retained vane bushing for an axial flow compressor
US5797725A (en) 1997-05-23 1998-08-25 Allison Advanced Development Company Gas turbine engine vane and method of manufacture
EP1176284A2 (fr) 2000-07-27 2002-01-30 General Electric Company Aubes de guidage avec col dépourvu de brasure
US8257038B2 (en) 2008-02-01 2012-09-04 Siemens Energy, Inc. Metal injection joining
US20100111682A1 (en) * 2008-10-31 2010-05-06 Patrick Jarvis Scoggins Crenelated turbine nozzle
US20110002787A1 (en) * 2008-12-24 2011-01-06 Enrique Penalver Castro Blade Retention at a Compressor Rectifier Stage for Impact Resistance
WO2014158284A2 (fr) * 2013-03-14 2014-10-02 Freeman Ted J Aube de turbine coulée en deux fois

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3145187A1 (fr) * 2023-01-24 2024-07-26 Safran Aircraft Engines Carter de turbomachine

Also Published As

Publication number Publication date
KR20160117330A (ko) 2016-10-10
US20160290146A1 (en) 2016-10-06
EP3075960B1 (fr) 2017-12-27
CN106014495A (zh) 2016-10-12
JP2016194300A (ja) 2016-11-17

Similar Documents

Publication Publication Date Title
EP3075960B1 (fr) Unité d'aubes directrices à profils aérodynamiques multiples
US9879559B2 (en) Airfoils having porous abradable elements
EP1808577B1 (fr) Ensemble d'aubes statoriques soudées pour turbine à vapeur
CA2715596C (fr) Anneau d'aubage fixe statique assemble
US9765630B2 (en) Interior cooling circuits in turbine blades
JP6507246B2 (ja) ロータブレードを製造するための方法およびかかる方法により実現されるブレード
EP3140515B1 (fr) Refroidissement d'aube à éléments de déplacement à cavité interne
EP3034800B1 (fr) Élément d'aubage pour une machine d'écoulement de fluide
EP2809885B1 (fr) Aube rotative de soufflante et ensemble associé
CN106609682B (zh) 涡轮机轮叶及相应的涡轮机
US8500411B2 (en) Turbine airfoil with outer wall thickness indicators
JP2014196735A5 (fr)
US8657562B2 (en) Self-aligning flow splitter for steam turbine
CN104033186B (zh) 燃气轮机叶片
US20130313307A1 (en) Method for manufacturing a hot gas path component
MX2015005512A (es) Metodos para fabricar aspas de turbomaquinas mediante maquinado por descarga electrica de cable, aspas y turbomaquinas.
EP3081751B1 (fr) Profil aérodynamique refroidi et procédé de fabrication dudit profil aérodynamique
US8506245B2 (en) Steam turbine shell
EP2634375B1 (fr) Procédé de fabrication d'un joint entre composants statiques et rotoriques pour un moteur à turbine
KR102565562B1 (ko) 부분 아크형 용례를 위한 증기 터빈 노즐 세그먼트, 관련 조립체 및 증기 터빈
US20160298465A1 (en) Gas turbine engine component cooling passage with asymmetrical pedestals
JP2005195021A (ja) 高温蒸気タービン用の低重量コントロール段
US10830072B2 (en) Turbomachine airfoil

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: 20170405

RBV Designated contracting states (corrected)

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

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

Owner name: ANSALDO ENERGIA IP UK LIMITED

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20170602

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

GRAR Information related to intention to grant a patent recorded

Free format text: ORIGINAL CODE: EPIDOSNIGR71

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

INTC Intention to grant announced (deleted)
GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

INTG Intention to grant announced

Effective date: 20171115

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

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: 958489

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180115

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602015006927

Country of ref document: DE

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

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: 20171227

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: 20171227

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: 20180327

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

Ref country code: DE

Payment date: 20180322

Year of fee payment: 4

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20171227

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 958489

Country of ref document: AT

Kind code of ref document: T

Effective date: 20171227

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: 20180327

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: 20180328

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: 20171227

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: 20171227

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: 20171227

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: 20171227

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

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: 20171227

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: 20171227

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: 20171227

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: 20171227

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: 20171227

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: 20171227

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: 20180427

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: 20171227

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: 20171227

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: 20171227

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: 20171227

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602015006927

Country of ref document: DE

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: 20171227

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: 20171227

26N No opposition filed

Effective date: 20180928

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20180331

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: LU

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

Effective date: 20180331

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: 20180331

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: 20180331

Ref country code: CH

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

Effective date: 20180331

Ref country code: LI

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

Effective date: 20180331

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: 20171227

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: 20180331

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602015006927

Country of ref document: DE

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

Effective date: 20190331

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: 20190331

Ref country code: MT

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

Effective date: 20180331

Ref country code: DE

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

Effective date: 20191001

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: 20171227

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: 20171227

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 NON-PAYMENT OF DUE FEES

Effective date: 20171227

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: 20150331

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: 20171227

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: 20171227