EP4097334B1 - Distributeur de stator de turbomachine comprenant un anneau d'étanchéité continu et libre - Google Patents

Distributeur de stator de turbomachine comprenant un anneau d'étanchéité continu et libre Download PDF

Info

Publication number
EP4097334B1
EP4097334B1 EP21716515.8A EP21716515A EP4097334B1 EP 4097334 B1 EP4097334 B1 EP 4097334B1 EP 21716515 A EP21716515 A EP 21716515A EP 4097334 B1 EP4097334 B1 EP 4097334B1
Authority
EP
European Patent Office
Prior art keywords
control valve
sealing ring
turbine engine
sectors
platforms
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
EP21716515.8A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP4097334A1 (fr
Inventor
Joao Antonio Amorim
Vahé KUPELIAN
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP4097334A1 publication Critical patent/EP4097334A1/fr
Application granted granted Critical
Publication of EP4097334B1 publication Critical patent/EP4097334B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/58—Piston ring seals

Definitions

  • the subject of the invention is a turbomachine stator distributor comprising a continuous and free sealing ring.
  • the distributors in question here are rings of fixed blades, fixed to a stator casing and alternating with rings of moving blades in the compressors and turbines of turbomachines.
  • the blades are mounted on the stator casing by connections comprising interlocking hooks, and their radially internal ends are provided with seals, made of so-called abradable materials, cooperating with adjacent wipers (circular ridges), belonging to the rotor, to form labyrinth seals.
  • the object of the invention is to reduce these drawbacks, and more precisely to reduce the flow rate of residual leaks through the labyrinth seal, while alleviating or even eliminating the ventilation constraints of the casing around the distributor concerned.
  • US 2011/0135479A1 which describes a stator distributor where a ring carrying an element of the labyrinth seal is continuous over a complete circumference and mounted to platform sectors connected directly to the fixed vanes. Assembly is carried out by nestings of tongues extending in the tangential direction and which therefore allow only very small radial movements of the ring in the sectors which surround it.
  • a spring of wavy shape is arranged in a circular housing, and it relies on radially opposite forces of this housing, belonging respectively to the sectors and to the ring, to return the latter to an invariable position while damping vibrations created by the rotor.
  • the device is not designed to adjust the clearance between the ring and a rotor that it surrounds.
  • the invention relates, in general form, to a turbomachine stator distributor comprising crown sectors arranged circumferentially end to end around an axis of the turbomachine, each of the sectors comprising at least one fixed vane which extends from a radially internal platform, a sealing ring carrying an abradable sealing element surrounded by the platforms of the sectors, the sealing ring being connected to the platforms by slide connections, characterized in that each slide connection comprises a first sleeve secured to a sealing ring and a second sleeve secured to one of the platforms, the first and second sleeves being fitted into each other by sliding and delimiting a housing, and each slide connection comprising a spring contained in the housing and constrained in the radial direction by being mounted on the one hand against one of the platforms and on the other hand against the sealing ring.
  • the construction of the invention is therefore based on the joint presence of a continuous sealing ring, carrying the abradable, and the main part of the distributor composed of the angular sectors.
  • the radial slides which connect them allow relatively large radial movements of the ring with respect to the platforms by differential thermal expansions, as well as reduced movements in the other directions (axial, tangential, and tilting) thanks to the little play between the internal sleeves and the external sleeves. Concentricity is maintained by the springs.
  • the ring As the heat transmission between the ring and the platforms is more reduced in the invention than in other constructions, thanks to the fineness of the connection provided only by the slides, the ring is held more easily at a temperature close to that of the rotor than in other constructions, and its diameter can be adjusted independently of the radial position of the blade sectors, by the temperature of the gases passing in front of it.
  • the invention improves sealing by the better adjustment of the clearances between the abradable and the wipers that can be expected, and also by the simple presence of the continuous ring, which interrupts the division of the distributor into sectors, at its end radially interior.
  • FIG. 1 represents, in longitudinal section, a portion of a turbomachine conforming to the known art and comprising a distributor crown 1 between two mobile blade crowns 2 and 3.
  • the distributor 1 comprises sectors 4 crown each comprising a few fixed blades 5 between an outer platform 6 and an outer platform 7 also extending over crown sectors.
  • the outer platform 6 is fixed to a stator casing 8 by mounting via an upstream hook 9 and a downstream hook 10 (the upstream and downstream are understood with respect to the general direction of the gases 'flowing into the turbomachine, for this entire description).
  • a ventilation device is arranged outside the stator casing 8; it comprises tubular ramps 11 traversed by fresh gas flows subtracted from the compressor of the turbomachine, which extend substantially to the right of the assembly via the hooks 9 and 10, to blow fresh air through orifices 12, refresh the stator casing 8 at the mounting location via the hooks 9 and 10 and therefore adjust the local thermal expansions of the stator casing 6 and thus the radial position of the crown sectors 4 of the distributor 1.
  • the radially inner platform 7 comprises an abradable liner 33 at its radially inner end, which is directed radially inwards and forms a labyrinth seal with radially facing wipers 13 depending on a rotor 14 to which belong to the crowns of moving blades such as 2 and 3.
  • the axial directions X-X and radial directions R-R are considered with reference to the axis around which the turbomachine extends, the axial direction also corresponding to the axis rotation of the rotor 14.
  • the distributor crown sectors 15 differ from those of known embodiments in that they comprise a radially internal platform 16 devoid of the abradable lining necessary to establish sealing with the rotor 14, a layer of abradable which replaces it, now 17, belonging to a ring 18 continuous on a circumference, therefore common to the distributor crown sectors 15.
  • the ring 18 comprises internal annular sleeves 19 standing on its radially outer face in the direction radial, and whose free end (radially external) is open.
  • the internal sleeves 19 slide in external sleeves 20 standing on the radially internal face of platforms 16 in the radial direction and whose free end (radially internal) is also open.
  • the radially external face of the ring 18 carries a flat external rib 21 which extends along internal ribs 22 also flat of the distributor sectors 15.
  • the internal ribs 22 are here contiguous to the external sleeves 20, without it is necessary.
  • the internal sleeves 19 could be placed on the platforms 16, and the external sleeves 20 on the ring 18. They are shown integrally on the ring 18 and the platforms 16, that is to say manufactured at the same time as him and them, by foundry for example, but they could be manufactured separately and then fixed by welding or otherwise.
  • the internal sleeves 19 and the external sleeves 20 delimit cylindrical housings 23 in which radially oriented rods 24 extend, carried by the internal platforms 16 and comprising a threaded free end 25 (radially internal) on which is screwed a nut 26.
  • a helical spring 27 is threaded around the rod 24.
  • the internal sleeves 19, external sleeves 20 and springs 27 form slide connections 35 between the distributor sectors 15 and the ring 18 which allow the latter to move in a radial direction, contracting or expanding.
  • each rod 24 is arranged with a clearance in a cavity 28 delimited by several portions assembled together of the ring 18, for example a cylindrical bandage 29 which constitutes its main structure, and two reinforcements 30 and 31 of portions of the abradable 17 which follow one another in the axial direction of the turbomachine.
  • the cavity 28 is provided with a bore 32 to allow the threaded free end 25 and the rod 24 to extend outward and slide with sufficient clearance.
  • each rod 24 is compressed between the internal platform 16 and the cylindrical tire 29 of the ring 18.
  • This assembly allows the ring 18 to acquire a radial position determined exclusively by the thermal expansions that it undergoes, due mainly to the gas current which circulates around it and crosses it passing in front of the abradable 17.
  • the axial position and the angular position of the ring 18 are ensured with sufficient precision by the sliding of the internal sleeves 19 in the external sleeves 20.
  • the radial position of the ring 18 therefore becomes approximately independent of that of the crown sectors of distributor 15 and is no longer governed by the ventilation devices, the importance of which becomes less and the elimination of which can even be considered.
  • This radial position of the ring 18 can be evaluated with sufficient precision to avoid excessive play or in the labyrinth seal or, on the contrary, premature wear of the abradable 17, thanks to knowledge of the predictable temperature of the circulating gases. in the turbomachine.
  • the outer rib 21 partly eliminates leaks coming from the clearances on the inner platforms 16 of the distributor crown sectors 15 by covering part of the interstices between them at the location of the internal ribs 22.
  • connection of the ring 18 to the platforms 16 by the relatively few and small-volume slides 35 contributes to the lightness of the construction, as does the blocking of their interval only by the parallel ribs 21 and 22, which do not have no structural role and can be fine.
  • FIG. 5 illustrates the complete distributor 34.
  • the slide connection 35 is here present on each of the distributor crown sectors 15, without this being necessary to properly support the ring.
  • Three slides 35 could be enough; a number of three to twenty would be preferable to favor the guidance of free expansion in operation.
  • the nuts 26 essentially serve to support the ring 18 during assembly of the device. It is planned that the cavities 28 are wide enough to avoid stops of the nuts 26 whatever the predictable thermal expansions of the ring 18.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
EP21716515.8A 2020-03-25 2021-03-22 Distributeur de stator de turbomachine comprenant un anneau d'étanchéité continu et libre Active EP4097334B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2002923A FR3108675B1 (fr) 2020-03-25 2020-03-25 Distributeur de stator de turbomachine comprenant un anneau d’étanchéité continu et libre
PCT/FR2021/050473 WO2021191540A1 (fr) 2020-03-25 2021-03-22 Distributeur de stator de turbomachine comprenant un anneau d'étanchéité continu et libre

Publications (2)

Publication Number Publication Date
EP4097334A1 EP4097334A1 (fr) 2022-12-07
EP4097334B1 true EP4097334B1 (fr) 2024-01-10

Family

ID=70295557

Family Applications (1)

Application Number Title Priority Date Filing Date
EP21716515.8A Active EP4097334B1 (fr) 2020-03-25 2021-03-22 Distributeur de stator de turbomachine comprenant un anneau d'étanchéité continu et libre

Country Status (5)

Country Link
US (1) US11879339B2 (zh)
EP (1) EP4097334B1 (zh)
CN (1) CN115335587B (zh)
FR (1) FR3108675B1 (zh)
WO (1) WO2021191540A1 (zh)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3146931A1 (fr) * 2023-03-23 2024-09-27 Safran Aircraft Engines Ensemble statorique pour une turbomachine d’aéronef

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5346362A (en) * 1993-04-26 1994-09-13 United Technologies Corporation Mechanical damper
US6042334A (en) * 1998-08-17 2000-03-28 General Electric Company Compressor interstage seal
US6514041B1 (en) * 2001-09-12 2003-02-04 Alstom (Switzerland) Ltd Carrier for guide vane and heat shield segment
US7291946B2 (en) * 2003-01-27 2007-11-06 United Technologies Corporation Damper for stator assembly
US20070132193A1 (en) * 2005-12-13 2007-06-14 Wolfe Christopher E Compliant abradable sealing system and method for rotary machines
EP2372165B1 (en) * 2008-12-25 2015-12-23 Mitsubishi Hitachi Power Systems, Ltd. Stator blade structure and gas turbine
FR2948965B1 (fr) * 2009-08-06 2012-11-30 Snecma Etage redresseur pour une turbomachine
RU2511935C2 (ru) * 2009-09-28 2014-04-10 Сименс Акциенгезелльшафт Уплотнительный элемент, сопловое устройство газовой турбины и газовая турбина
US9181817B2 (en) 2010-06-30 2015-11-10 General Electric Company Method and apparatus for labyrinth seal packing rings
FR2971022B1 (fr) * 2011-02-02 2013-01-04 Snecma Etage redresseur de compresseur pour une turbomachine
US9063423B2 (en) * 2013-02-28 2015-06-23 Eastman Kodak Company Lithographic printing plate precursors and use
US9500094B1 (en) * 2013-04-23 2016-11-22 S & J Deisgn, Llc Turbine with radial acting seal
US10215044B2 (en) * 2014-08-08 2019-02-26 Siemens Energy, Inc. Interstage seal housing optimization system in a gas turbine engine
EP3315728B1 (de) * 2016-10-26 2022-01-12 MTU Aero Engines AG Gedämpfte leitschaufellagerung
DE102017221660A1 (de) 2017-12-01 2019-06-06 MTU Aero Engines AG Modul für eine Strömungsmaschine

Also Published As

Publication number Publication date
US20230160314A1 (en) 2023-05-25
FR3108675B1 (fr) 2022-11-04
US11879339B2 (en) 2024-01-23
FR3108675A1 (fr) 2021-10-01
WO2021191540A1 (fr) 2021-09-30
EP4097334A1 (fr) 2022-12-07
CN115335587B (zh) 2024-05-28
CN115335587A (zh) 2022-11-11

Similar Documents

Publication Publication Date Title
EP3129601B1 (fr) Compresseur de turbomachine à aubes à calage variable
EP1847686B1 (fr) Dispositif de fixation de secteurs d'anneau sur un carter de turbine d'une turbomachine
EP2917519B1 (fr) Support de tube d'évacuation d'air dans une turbomachine
FR2899274A1 (fr) Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine d'une turbomachine
EP2300688B1 (fr) Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles
CA2827591C (fr) Carter de turbine comportant des moyens de fixation de secteurs d'anneau
EP4097334B1 (fr) Distributeur de stator de turbomachine comprenant un anneau d'étanchéité continu et libre
FR3039589A1 (fr) Etage de turbomachine, en particulier de turbine basse-pression
FR3082896A1 (fr) Ensemble pour la commande d'aubes a calage variable
EP2917518A2 (fr) Support de tube d'évacuation d'air dans une turbomachine
FR2860040A1 (fr) Realisation de l'etancheite dans un turboreacteur pour le prelevement cabine par un joint a brosse
FR3066533B1 (fr) Ensemble d'etancheite pour une turbomachine
FR3082227A1 (fr) Dispositif pilote de refroidissement pour une turbine d'une turbomachine
CA3099889A1 (fr) Dispositif de refroidissement d'un carter de turbomachine
FR3049307B1 (fr) Ensemble rotatif pour turbomachine
EP3999779B1 (fr) Chambre de combustion de turbomachine a volume constant
EP4041993B1 (fr) Distributeur de turbine à aubage en composite à matrice céramique traversé par un circuit de ventilation métallique
FR2944554A1 (fr) Turbine haute-pression de turbomachine
FR3065484B1 (fr) Ensemble de turbine de turbomachine
FR3061739A1 (fr) Ensemble pour turbomachine
FR3085405A1 (fr) Pressurisation de la cavite inter-lechettes par derivation du flux de bypass
FR3039225A1 (fr) Turbomachine, telle par exemple qu'un turboreacteur d'avion
FR3108362A1 (fr) Etage d’aubes à orientation variable pour une turbomachine axiale comprenant un organe de régulation du débit d’air dépendant de l’orientation des aubes
FR3083566A1 (fr) Ensemble de turbine pour turbomachine d'aeronef a circuit de refroidissement de disque equipe d'un dispositif d'etancheite
FR3021742A1 (fr) Veine instrumentee de turbomachine

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

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

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20220831

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

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
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

INTG Intention to grant announced

Effective date: 20230908

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

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602021008553

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

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

Ref country code: DE

Payment date: 20240220

Year of fee payment: 4

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20240110

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

Ref country code: FR

Payment date: 20240220

Year of fee payment: 4

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1649050

Country of ref document: AT

Kind code of ref document: T

Effective date: 20240110

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: 20240110

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: 20240110

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

Ref country code: IS

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

Effective date: 20240510

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: 20240110

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

Ref country code: GR

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

Effective date: 20240411

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

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: 20240110

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: 20240410

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

Ref country code: ES

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

Effective date: 20240110

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: 20240110

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: 20240410

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: 20240410

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: 20240110

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: 20240510

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: 20240110

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: 20240411

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: 20240110

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: 20240110

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: 20240110

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

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: 20240110

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: 20240510

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

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: 20240110

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: 20240510

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: 20240110

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: 20240110

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: 20240110

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

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: 20240110