EP3144540B1 - Étage de compresseur de turbine à gaz - Google Patents

Étage de compresseur de turbine à gaz Download PDF

Info

Publication number
EP3144540B1
EP3144540B1 EP15185447.8A EP15185447A EP3144540B1 EP 3144540 B1 EP3144540 B1 EP 3144540B1 EP 15185447 A EP15185447 A EP 15185447A EP 3144540 B1 EP3144540 B1 EP 3144540B1
Authority
EP
European Patent Office
Prior art keywords
compressor
gas turbine
compressor stage
aircraft engine
cascade
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
EP15185447.8A
Other languages
German (de)
English (en)
Other versions
EP3144540A1 (fr
Inventor
Werner Humhauser
Roland Matzgeller
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP15185447.8A priority Critical patent/EP3144540B1/fr
Priority to US15/245,388 priority patent/US10280934B2/en
Publication of EP3144540A1 publication Critical patent/EP3144540A1/fr
Application granted granted Critical
Publication of EP3144540B1 publication Critical patent/EP3144540B1/fr
Active 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
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/028—Layout of fluid flow through the stages
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape

Definitions

  • the present invention relates to a compressor stage for a gas turbine, a gas turbine with at least one such compressor stage, an aircraft engine with such a gas turbine and a method for designing such a compressor stage and a method for designing a compressor of such a gas turbine, in particular an aircraft engine.
  • compressor stages of gas turbines have been designed in such a way that their throttling factor ⁇ is always less than 5.16 minus 1.33 times the aspect ratio AR ax defined by the quotient of mean duct height h and mean chord length lax ( ⁇ ⁇ -1.33 ARax + 5.16).
  • An object of an embodiment of the present invention is to improve a gas turbine.
  • one or more compressor stages of a compressor or one or more compressor stages of several compressors of a gas turbine, in particular an aircraft engine gas turbine, which (each) have a rotor cascade and a guide cascade, are aerodynamically designed such that the throttling factor ⁇ and the aspect ratio AR ax (in each case ) of the condition defined by the quotient of mean channel height h and mean chord length lax ⁇ > ⁇ 1.33 ⁇ AR ax + 5:16 enough.
  • one or more compressor stages for a compressor or one or more compressor stages for several compressors of a gas turbine in particular an aircraft engine gas turbine, in particular one or more compressor stages of a compressor or one or more compressor stages of several compressors of a gas turbine, in particular suffice an aero engine gas turbine, each having a rotor blade and a vane blade, (each) of the condition ⁇ > ⁇ 1.33 ⁇ AR ax + 5:16 with the throttle factor ⁇ and the aspect ratio AR ax defined by the quotient of the mean channel height h and the mean chord length lax .
  • a rotor cascade has a plurality of rotor blades spaced apart in the circumferential direction, which are arranged on a rotor which is rotatable (bearing) about a main or machine axis, in particular by a turbine of the gas turbine.
  • the blades can be detachably or integrally attached to the rotor or formed integrally with it. In one embodiment, they can be without a shroud or have a closed outer shroud.
  • a guide vane has a plurality of guide vanes which are spaced apart in the circumferential direction and are arranged in a fixed or adjustable manner on a housing which surrounds the rotor. In one embodiment, they can be without a shroud or have a closed inner shroud.
  • the guide vane is arranged adjacent to a guide vane downstream or to the moving vane downstream.
  • it can be a so-called guide vane for converting kinetic energy generated by the rotating rotor cascade into pressure energy from the air flowing through the gas turbine.
  • the compression stage in the sense of the present invention consists of the moving cascade and the guide cascade.
  • the mean chord length lax is defined in the usual way as the geometric mean of the distance between the inlet and outlet edges of the rotor cascade or the compressor stage.
  • AR ax H / l ax .
  • the aspect ratio AR ax is greater than 0.5. Additionally or alternatively, according to one embodiment, the aspect ratio AR ax is less than 2.5. As a result, a particularly advantageous compressor stage can be made available.
  • a total pressure ratio ⁇ of one or more of the compressors is at least 40, in particular at least 45.
  • a particularly advantageous compressor can thereby be made available.
  • a bypass ratio BPR (by-pass ratio) of the aircraft engine is at least 10, in particular at least 12.
  • a particularly advantageous aircraft engine can thereby be made available.
  • FIG. 1 shows in a partially schematic manner an aircraft engine with a fan 1 and a gas turbine, which is only for a more compact representation and by way of example only a compressor 9, a downstream combustion chamber 5, a high-pressure turbine 6, which is coupled to the compressor 9 via a rotor 10, and a Has low-pressure turbine 7, which is coupled to the fan 1.
  • a core flow 8 flows through the gas turbine and a bypass or bypass flow 2 flows around it.
  • the compressor 9 has a plurality of compressor stages, each of which has a fixed-rotor rotor cascade 3 and a guide cascade 4 adjacent downstream.
  • One or more of these compressor stages 3, 4 are or are designed in such a way that the throttle coefficient ⁇ and the aspect ratio AR ax defined by the quotient of the average channel height h and the average chord length 1 ax of the condition ⁇ > ⁇ 1.33 ⁇ AR ax + 5:16 it is sufficient if the aspect ratio AR ax is greater than 0.5 and less than 2.5.
  • the total pressure ratio ⁇ of the compressor 9 is at least 45, the bypass ratio BPR of the aircraft engine is at least 12.
  • the aircraft engine or the gas turbine can have, in particular, a low-pressure compressor and a downstream high-pressure compressor, and in a further development also a medium-pressure compressor arranged between them, with at least one of these compressors being designed in the manner explained above as an example with reference to the compressor 9 can.
  • a low-pressure compressor and a downstream high-pressure compressor and in a further development also a medium-pressure compressor arranged between them, with at least one of these compressors being designed in the manner explained above as an example with reference to the compressor 9 can.
  • Equally, low and high pressure compressors can also be understood as a compressor within the meaning of the present invention.
  • the fan 1 can be coupled to the high-pressure turbine 6 in particular via a gearbox.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)

Claims (10)

  1. Étage de compresseur pour une turbine à gaz, en particulier d'un moteur d'aéronef, comportant une grille mobile (3), une grille directrice (4) en particulier adjacente en aval, et comportant un chiffre d'étranglement (σ), caractérisé en ce que le chiffre d'étranglement (σ) et le rapport d'aspect ARax défini par le quotient de la hauteur de canal moyenne (h) de l'étage de compresseur ou de la grille mobile (3) et de la longueur de corde moyenne (lax) de l'étage de compresseur ou de la grille mobile (3) satisfont à la condition σ > − 1,33 ⋅ AR ax + 5,16
    Figure imgb0016
  2. Étage de compresseur selon la revendication précédente,
    caractérisé en ce que le rapport d'aspect ARax est supérieur à 0,5 et/ou inférieur à 2,5.
  3. Turbine à gaz comportant au moins un compresseur (9) comportant au moins un étage de compresseur selon l'une quelconque des revendications précédentes.
  4. Turbine à gaz selon la revendication précédente, caractérisée en ce qu'un rapport de pression totale Π d'au moins l'un des compresseurs est d'au moins 40, en particulier d'au moins 45.
  5. Moteur d'aéronef comportant une turbine à gaz selon l'une quelconque des revendications précédentes.
  6. Moteur d'aéronef selon la revendication précédente,
    caractérisé en ce qu'un taux de dilution BPR du moteur d'aéronef est d'au moins 10, en particulier d'au moins 12.
  7. Procédé permettant de concevoir au moins un étage de compresseur d'au moins un compresseur d'une turbine à gaz, en particulier d'un moteur d'aéronef, comportant une grille mobile (3), une grille directrice (4) en particulier adjacente en aval, et comportant un chiffre d'étranglement (σ), caractérisé en ce que l'étage de compresseur est conçu de manière aérodynamique de telle sorte que le chiffre d'étranglement σ et le rapport d'aspect ARax défini par le quotient de la hauteur de canal moyenne (h) de l'étage de compresseur ou de la grille mobile (3) et de la longueur de corde moyenne (lax) de l'étage de compresseur ou de la grille mobile (3) satisfont à la condition σ > − 1,33 ⋅ AR ax + 5,16
    Figure imgb0017
  8. Procédé permettant de concevoir au moins un compresseur d'une turbine à gaz, en particulier d'un moteur d'aéronef, caractérisé en ce qu'au moins un étage de compresseur du compresseur est conçu selon la revendication précédente.
  9. Procédé permettant de concevoir au moins un compresseur selon la revendication précédente, caractérisé en ce qu'un rapport de pression totale Π du compresseur est d'au moins 40, en particulier d'au moins 45.
  10. Procédé permettant de concevoir un compresseur selon l'une quelconque des revendications précédentes, caractérisé en ce qu'un taux de dilution BPR du moteur d'aéronef est d'au moins 10, en particulier d'au moins 12.
EP15185447.8A 2015-09-16 2015-09-16 Étage de compresseur de turbine à gaz Active EP3144540B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP15185447.8A EP3144540B1 (fr) 2015-09-16 2015-09-16 Étage de compresseur de turbine à gaz
US15/245,388 US10280934B2 (en) 2015-09-16 2016-08-24 Gas turbine compressor stage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15185447.8A EP3144540B1 (fr) 2015-09-16 2015-09-16 Étage de compresseur de turbine à gaz

Publications (2)

Publication Number Publication Date
EP3144540A1 EP3144540A1 (fr) 2017-03-22
EP3144540B1 true EP3144540B1 (fr) 2023-05-10

Family

ID=54147096

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15185447.8A Active EP3144540B1 (fr) 2015-09-16 2015-09-16 Étage de compresseur de turbine à gaz

Country Status (2)

Country Link
US (1) US10280934B2 (fr)
EP (1) EP3144540B1 (fr)

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2406126A (en) * 1942-03-21 1946-08-20 Bbc Brown Boveri & Cie Blade arrangement for axial compressors
US2749027A (en) * 1947-12-26 1956-06-05 Edward A Stalker Compressor
US2830754A (en) * 1947-12-26 1958-04-15 Edward A Stalker Compressors
US2605956A (en) * 1949-08-13 1952-08-05 Chrysler Corp Power conversion machine
US2726806A (en) * 1950-12-02 1955-12-13 A V Roe Canada Ltd Axial compressor
US2846136A (en) * 1951-07-19 1958-08-05 Bbc Brown Boveri & Cie Multi-stage axial flow compressors
US2846137A (en) * 1955-06-03 1958-08-05 Gen Electric Construction for axial-flow turbomachinery
US2990106A (en) * 1956-10-12 1961-06-27 English Electric Co Ltd Axial flow multi-stage compressors
GB992941A (en) * 1963-11-29 1965-05-26 Bristol Siddeley Engines Ltd Improvements in rotary bladed compressors and turbines
US3775023A (en) * 1971-02-17 1973-11-27 Teledyne Ind Multistage axial flow compressor
US4116584A (en) * 1973-10-12 1978-09-26 Gutehoffnungshutte Sterkrade Ag Device for extending the working range of axial flow compressors
US4011028A (en) * 1975-10-16 1977-03-08 Anatoly Nikolaevich Borsuk Axial-flow transsonic compressor
DE102005052466A1 (de) * 2005-11-03 2007-05-10 Mtu Aero Engines Gmbh Mehrstufiger Verdichter für eine Gasturbine mit Abblasöffnungen und Einblasöffnungen zum Stabilisieren der Verdichterströmung
US8292574B2 (en) * 2006-11-30 2012-10-23 General Electric Company Advanced booster system
US7967571B2 (en) * 2006-11-30 2011-06-28 General Electric Company Advanced booster rotor blade
US20160052621A1 (en) * 2009-07-10 2016-02-25 Peter Ireland Energy efficiency improvements for turbomachinery
CH705822B1 (de) * 2011-11-16 2016-01-29 Alstom Technology Ltd Axialverdichter für eine Strömungsmaschine, insbesondere eine Gasturbine.
US9109608B2 (en) * 2011-12-15 2015-08-18 Siemens Energy, Inc. Compressor airfoil tip clearance optimization system
US10125724B2 (en) * 2012-01-17 2018-11-13 United Technologies Corporation Start system for gas turbine engines
US20130192198A1 (en) * 2012-01-31 2013-08-01 Lisa I. Brilliant Compressor flowpath
JP6185781B2 (ja) * 2013-07-23 2017-08-23 三菱日立パワーシステムズ株式会社 軸流圧縮機
US9759230B2 (en) * 2014-01-24 2017-09-12 Pratt & Whitney Canada Corp. Multistage axial flow compressor
US10378554B2 (en) * 2014-09-23 2019-08-13 Pratt & Whitney Canada Corp. Gas turbine engine with partial inlet vane

Also Published As

Publication number Publication date
EP3144540A1 (fr) 2017-03-22
US10280934B2 (en) 2019-05-07
US20170074271A1 (en) 2017-03-16

Similar Documents

Publication Publication Date Title
EP2096260B1 (fr) Turbomachine comprenant des ensembles rotor ayant un faible angle de déviation du fluide en sortie
DE102008055824B4 (de) Dampfturbine
CH703742A2 (de) Schaufelblattgestalt für eine Verdichtereinlassleitschaufel.
DE1626130A1 (de) Gasturbinentriebwerksanlage
DE102012104827A1 (de) Form einer Luftschaufel für einen Verdichter
EP2647795A1 (fr) Système d'étanchéité pour turbomachine
DE102010050185B4 (de) Axialturbomaschine
EP1970542B2 (fr) Décalage d'aube en fonction d'étranglement dans des turbomachines
EP3109410B1 (fr) Dispositif de stator pour une turbomachine comprenant un dispositif de carter et plusieurs aubes directrices
DE102020115579A1 (de) Gasturbinentriebwerk mit hocheffizientem fan
DE102016102732A1 (de) Mixed-Flow-Turbinenrad eines Abgasturboladers sowie Abgasturbine mit einem solchen Turbinenrad
EP1865148B1 (fr) Machine de traitement des écoulements dotée de rotors de distribution d'énergie supérieure spécifique
EP3183427B1 (fr) Profilage d'aubes directrices de dispositifs directeurs pour compresseurs radiales
EP0532907B1 (fr) Turbine axiale
EP2458149B1 (fr) Aubage pour turboréacteur
EP3144540B1 (fr) Étage de compresseur de turbine à gaz
EP3599357B1 (fr) Compresseur haute pression pour un groupe moteur
EP3495639B1 (fr) Module de compresseur pour une turbomachine réduisant la couche limite dans un carter intermédiaire de compresseur
DE102016115868A1 (de) Strömungsarbeitsmaschine mit hohem Ausnutzungsgrad
EP3109408A1 (fr) Dispositif de stator pour une turbomachine comprenant un dispositif de carter et plusieurs aubes directrices
EP3097293A1 (fr) Régulation variable de la puissance limite de turbines à gaz
EP3492701B1 (fr) Canal d'écoulement de turbomachine
DE102018130298A1 (de) Baugruppe mit einem Ausgangsleitrad für ein Turbofantriebwerk und Turbofantriebwerk mit einer solchen Baugruppe
EP3763917A1 (fr) Segment d'aube directrice pourvu de nervure de section de support
EP2937525B1 (fr) Moteur d'aéronef

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

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

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

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

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: 20170828

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

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20181109

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

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: 20221220

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: AT

Ref legal event code: REF

Ref document number: 1566925

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230515

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: 502015016349

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: GERMAN

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: 20230510

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: 20230510

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: 20230911

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: 20230810

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: 20230510

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: 20230510

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

Ref country code: GB

Payment date: 20230921

Year of fee payment: 9

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: 20230510

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: 20230510

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: 20230510

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: 20230510

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: 20230910

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: 20230510

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: 20230811

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

Ref country code: FR

Payment date: 20230918

Year of fee payment: 9

Ref country code: DE

Payment date: 20230919

Year of fee payment: 9

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

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: 20230510

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

Ref country code: SK

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

Effective date: 20230510

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: 20230510

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: 20230510

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: 20230510

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: 20230510

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: 20230510

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: 20230510

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502015016349

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

26N No opposition filed

Effective date: 20240213

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: 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: 20230510

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: 20230916