EP2896794A1 - Blisk - Google Patents

Blisk Download PDF

Info

Publication number
EP2896794A1
EP2896794A1 EP15150251.5A EP15150251A EP2896794A1 EP 2896794 A1 EP2896794 A1 EP 2896794A1 EP 15150251 A EP15150251 A EP 15150251A EP 2896794 A1 EP2896794 A1 EP 2896794A1
Authority
EP
European Patent Office
Prior art keywords
blisk
lid
blades
disk part
filler
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
EP15150251.5A
Other languages
English (en)
French (fr)
Other versions
EP2896794B1 (de
Inventor
Mark Houle
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP2896794A1 publication Critical patent/EP2896794A1/de
Application granted granted Critical
Publication of EP2896794B1 publication Critical patent/EP2896794B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F04D29/326—Rotors specially for elastic fluids for axial flow pumps for axial flow fans comprising a rotating shroud
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/002—Axial flow fans
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations

Definitions

  • the present invention relates to a blisk for a gas turbine engine.
  • a blisk is a component having a rotor disk part and integral blades.
  • An outer surface or rim of the disk part generally forms the inner working gas annulus of the engine.
  • blisks are configured to avoid, where possible, forced responses from resonance and flutter.
  • blisks lack inherent damping when compared to conventional bladed disk assemblies, and forced responses to resonances and flutter cannot always be avoided.
  • fixing the inner working gas annulus at the outer surface of the disk part also fixes the basic size and shape of the disk part, and thus reduces options for reconfiguring the blisk to avoid forced responses and flutter.
  • An aim of the present invention is to provide an improved blisk which is, for example, less susceptible to forced responses and flutter.
  • the present invention provides a blisk a for a gas turbine engine.
  • the blisk has a rotor disk part and a circumferential row of blades extending from and integral with the disk part.
  • a plurality of annulus fillers is provided to bridge the gaps between adjacent blades.
  • Each annulus filler has an outer lid which defines an airflow surface for air being drawn through the engine in an axial airflow direction, and an inner support structure which connects to the disk part to support the lid on the blisk. Opposite edges of the lid make respective lines of contact with a suction side of one blade and a pressure side of an adjacent blade.
  • the annulus fillers rather than an outer surface or rim of the disk part, can thus form the inner working gas annulus of the engine.
  • the radius of the disk part can be reduced and the length of the blades increased.
  • Reducing the radius of the disk part can also allow the total weight of the blisk to be decreased.
  • annulus fillers can themselves act as damper elements between the blades, reducing blade resonances by physical contact with the blades.
  • the present invention provides a gas turbine engine, such as aeroengine, having the blisk of the first aspect.
  • the blisk may be a fan blisk or a compressor section blisk.
  • each blade may continue radially inwardly of the respective lines of contact such that if the lids are moved radially inwardly, all the regions of suction and pressure side surfaces of the blades thereby revealed radially outwardly of the lids are aerofoil surface regions.
  • each annulus filler may have damping strips which extend along the opposite edges of the lid to contact the suction and pressure sides of the adjacent blades. Such strips can help to improve the damping properties of the fillers.
  • the strips may be formed of elastomer.
  • the strips can be adhesively bonded to the lid.
  • the annulus fillers may provide frictional damping. For example, rubbing along the contact lines between the lids and the blades can provide frictional damping.
  • each annulus filler can be formed of a laminate a portion of whose lamina are elastomeric (the other portion can be e.g. metallic).
  • each annulus filler may provide beneath the lid one or more retention formations which each retains a respective hook formed at the outer surface of the disk part and thereby holds the filler in position between its adjacent blades under centrifugal loading.
  • the support structure can provide forward and rearward retention formations which respectively retain forward and rearward hooks formed at the outer surface of the disk part.
  • the retention formations and hooks may be formed such that, on build, the annulus filler can be slid axially into position between its adjacent blades to mate the hooks with the retention formations.
  • Damping pads e.g. formed of elastomer
  • the pads can be adhesively bonded to the retention formations.
  • the retention formations can be variously shaped. For example, they can be complimentary hooks to the disk part hooks.
  • the complimentary hooks can be at the ends of respective legs (provided by the support structure) extending radially inwardly from the underside of the lid.
  • Another option is for the retention formations to be straps which locate under the disk part hooks. The straps can extend between side walls (provided by the support structure) extending radially inwardly from the opposite edges of the lid.
  • each annulus filler may provide a front and/or rear engagement formation at the front and/or rear end of the lid, the engagement formation engaging with a respective engine component (such as an adjacent fairing) to axially hold the filler in position between its adjacent blades.
  • a respective engine component such as an adjacent fairing
  • the annulus filler may be formed from aluminium alloy, titanium alloy, composite material (such as carbon fibre reinforced plastic) or a combination thereof.
  • such materials are relatively lightweight, helping to reduce the weight of the blisk.
  • a lightweight filler will tend to be less damaging to the engine.
  • the blades may be welded (e.g. linear friction welded) to the disk part.
  • welded e.g. linear friction welded
  • a ducted fan gas turbine engine incorporating the invention is generally indicated at 10 and has a principal and rotational axis X-X.
  • the engine comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, an intermediate pressure turbine 17, a low-pressure turbine 18 and a core engine exhaust nozzle 19.
  • a nacelle 21 generally surrounds the engine 10 and defines the intake 11, a bypass duct 22 and a bypass exhaust nozzle 23.
  • air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate pressure compressor 13 and a second air flow B which passes through the bypass duct 22 to provide propulsive thrust.
  • the intermediate pressure compressor 13 compresses the air flow A directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
  • the compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust.
  • the high, intermediate and low-pressure turbines respectively drive the high and intermediate pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.
  • a blisk may be used to form the propulsive fan 12 or may be part of a compressor section 13, 14 of such an engine.
  • Figure 2 shows a close-up view of a blisk propulsive fan 12.
  • the blisk has a rotor disk part 30 and a circumferential row of fan blades 32.
  • Annulus fillers 34 shown in more detail in Figures 3 to 5 , bridge the gaps between adjacent blades.
  • Each annulus filler 34 has an outer lid 36 which forms the inner surface of the working gas annulus of the engine, and an inner support structure which connects to the disk part 30 to support the lid on the blisk 12. Opposite edges of the lid respectively contact the suction side aerofoil surface of one blade and the pressure side aerofoil surface of an adjacent blade along contact lines 38.
  • the annulus fillers 34 provide a number of advantages. They provide damping to the blades 32 by physical contact. This reduces aerofoil vibration from forced response and flutter, and thus improves the service life.
  • the fillers also offer more flexibility in the blisk design, allowing the outer rim of the disk part 30 of the blisk to be reduced in diameter. The overall weight of the blisk 12 may thus be reduced for a given application, as the diameter of the disc part is reduced. Further, the natural frequency of the blades can be reduced due to the increase in blade length. This can be of particular benefit if there is a need to reduce the frequency of the fundamental flap mode/first engine order resonance. For example, there may be a need to keep the fundamental flap mode/first engine order resonance below a particular engine speed to reduce the forcing level.
  • the aerofoil surfaces of the blade 32 continue uninterruptedly below the level of the lids 36. This allows design changes to be made to the engine whereby new annulus fillers can be installed whose lids have differently shaped air-washed surfaces.
  • Each annulus filler 34 is assembled between and interfaces with adjacent blades 32 on the blisk 12, thus effectively forming an annular ring out of the lids 36.
  • the ring covers the regions where the join welds (which may be linear friction welds) between the blades 32 and the disk part 30 are typically made, thereby making weld surface finish in these regions a less critical aerodynamic issue.
  • FIG. 3 shows front and rear hooks 40 machined integrally to the outer surface of the disk part 30.
  • the hooks can alternatively be welded to the disk part. They can be located spatially on the disk part to suit the particular intended application, e.g. they can be located closer to the leading and trailing edges of the disk part than shown.
  • the support structure of each filler comprises retention formations in the form of corresponding hooks 42 at the ends of respective legs 44 extending from the underside of the filler's lid. On build, the filler is slid axially into position between its adjacent blades so that the hooks 40, 42 mate with each other and provide radial retention of the fillers under centrifugal loading.
  • the filler's support structure can provide other configurations for the retention formations, such as straps running between side walls extending from the opposite edges of the filler, the straps locating in use underneath the hooks 40.
  • Axial retention of the annulus fillers 34 can be achieved by fixing an engagement formation 46 at the front of each filler to the disk part 30 or to a suitable adjacent fairing such as the engine nose cone 50.
  • Other filler configurations may adopt a single hook 42 with positive front and rear engagement of the filler.
  • the annulus filler is constructed of light alloy or composite material, such as aluminium, titanium, carbon fibre composite or a mixture of these materials.
  • Damping strips 48 can extend along the opposite edges of each lid 36 for contact with the adjacent blades 32.
  • the strips can be formed, for example, of elastomer, which may be adhesively bonded to the lid.
  • the strips are pre-formed to conform to the shape of the contacting aerofoil surfaces. Instead of such strips, however, frictional damping at the interfaces between the lids and the blades can be used.
  • damping pads at the interfaces between the mating hooks 40, 42.
  • Such pads can also be formed of elastomer and may be adhesively bonded to the filler hooks 42.
  • the legs of the annulus damper can be constructed in such a manner as to be flexible, e.g. as a laminate formed layers of metal and elastomer, so as to provide additional damping.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP15150251.5A 2014-01-16 2015-01-07 Blisk Not-in-force EP2896794B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB201400756A GB201400756D0 (en) 2014-01-16 2014-01-16 Blisk

Publications (2)

Publication Number Publication Date
EP2896794A1 true EP2896794A1 (de) 2015-07-22
EP2896794B1 EP2896794B1 (de) 2017-03-15

Family

ID=50239060

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15150251.5A Not-in-force EP2896794B1 (de) 2014-01-16 2015-01-07 Blisk

Country Status (3)

Country Link
US (1) US20150198174A1 (de)
EP (1) EP2896794B1 (de)
GB (1) GB201400756D0 (de)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170218782A1 (en) * 2014-08-22 2017-08-03 Siemens Energy, Inc. Modular turbine blade with separate platform support system
US10294965B2 (en) 2016-05-25 2019-05-21 Honeywell International Inc. Compression system for a turbine engine
US10746031B2 (en) * 2017-07-18 2020-08-18 Rolls-Royce Corporation Annulus filler
US10670037B2 (en) * 2017-11-21 2020-06-02 General Electric Company Turbofan engine's fan blade and setting method thereof
US11078839B2 (en) 2018-01-22 2021-08-03 Rolls-Royce Corporation Composite nosecone
US11421538B2 (en) 2020-05-12 2022-08-23 Rolls-Royce Corporation Composite aerofoils
US11506083B2 (en) 2020-06-03 2022-11-22 Rolls-Royce Corporalion Composite liners for turbofan engines

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0077039A2 (de) * 1981-10-12 1983-04-20 Nissan Motor Co., Ltd. Gebläserad
GB2463036A (en) * 2008-08-29 2010-03-03 Rolls Royce Plc Blade platform and insert arrangement for gas turbine
US20110030336A1 (en) * 2009-08-05 2011-02-10 The Boeing Company Coannular ducted fan
EP2322765A2 (de) * 2009-11-11 2011-05-18 Rolls-Royce plc Ringförmiges Zwischenelement für ein Turbofan- Triebwerk

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2251897B (en) * 1991-01-15 1994-11-30 Rolls Royce Plc A rotor
US6354780B1 (en) * 2000-09-15 2002-03-12 General Electric Company Eccentric balanced blisk
US7278821B1 (en) * 2004-11-04 2007-10-09 General Electric Company Methods and apparatus for assembling gas turbine engines
GB0611031D0 (en) * 2006-06-06 2006-07-12 Rolls Royce Plc An aerofoil stage and a seal for use therein
GB201020857D0 (en) * 2010-12-09 2011-01-26 Rolls Royce Plc Annulus filler

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0077039A2 (de) * 1981-10-12 1983-04-20 Nissan Motor Co., Ltd. Gebläserad
GB2463036A (en) * 2008-08-29 2010-03-03 Rolls Royce Plc Blade platform and insert arrangement for gas turbine
US20110030336A1 (en) * 2009-08-05 2011-02-10 The Boeing Company Coannular ducted fan
EP2322765A2 (de) * 2009-11-11 2011-05-18 Rolls-Royce plc Ringförmiges Zwischenelement für ein Turbofan- Triebwerk

Also Published As

Publication number Publication date
EP2896794B1 (de) 2017-03-15
US20150198174A1 (en) 2015-07-16
GB201400756D0 (en) 2014-03-05

Similar Documents

Publication Publication Date Title
EP2896794B1 (de) Blisk
EP2798158B1 (de) Strukturelle Plattform für eine doppelte Leitschaufel
US7955054B2 (en) Internally damped blade
US8834129B2 (en) Turbofan flow path trenches
US5725354A (en) Forward swept fan blade
EP2859188B1 (de) Plattform für eine gebläseschaufel
CA2858562C (en) Quick engine change assembly for outlet guide vanes
US10196896B2 (en) Rotor damper
US9303520B2 (en) Double fan outlet guide vane with structural platforms
EP2971552B1 (de) Spritzgegossener verbundgebläseplattform
EP2855898A1 (de) Statorschaufel-stossfängerring
EP2787179B1 (de) Schaufelanordnung, zugehöriges Herstellungsverfahren und Gebläseanordnung eines Gasturbinentriebwerks
US10018049B2 (en) Bladed disc
US10371162B2 (en) Integrally bladed fan rotor
US20200063590A1 (en) Sealing member for gas turbine engine

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: 20150107

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: 20151105

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

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 11/00 20060101AFI20161102BHEP

Ipc: F01D 5/30 20060101ALI20161102BHEP

Ipc: F01D 5/34 20060101ALI20161102BHEP

INTG Intention to grant announced

Effective date: 20161123

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

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

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 875814

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170415

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602015001775

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20170315

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

Ref country code: 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: 20170615

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: 20170315

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: 20170616

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: 20170315

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: 20170315

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 875814

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170315

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

Ref country code: RS

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

Effective date: 20170315

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: 20170315

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: 20170615

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: 20170315

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: 20170315

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

Effective date: 20170315

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: 20170315

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: 20170315

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: 20170315

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: 20170315

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: 20170315

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: 20170717

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: 20170315

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: 20170315

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: 20170715

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602015001775

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: FR

Ref legal event code: PLFP

Year of fee payment: 4

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: 20170315

26N No opposition filed

Effective date: 20171218

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

Ref country code: IT

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

Effective date: 20170315

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: 20170315

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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: 20180107

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20180131

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

Ref country code: LI

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

Effective date: 20180131

Ref country code: CH

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

Effective date: 20180131

Ref country code: BE

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

Effective date: 20180131

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: 20180107

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: 20170315

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 NON-PAYMENT OF DUE FEES

Effective date: 20180107

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: 20170315

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

Ref country code: GB

Payment date: 20200127

Year of fee payment: 6

Ref country code: DE

Payment date: 20200129

Year of fee payment: 6

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: 20150107

Ref country code: MK

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

Effective date: 20170315

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: 20170315

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

Ref country code: FR

Payment date: 20200127

Year of fee payment: 6

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: 20170315

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602015001775

Country of ref document: DE

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

Effective date: 20210107

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: 20210131

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: 20210107

Ref country code: DE

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

Effective date: 20210803