EP2611992A1 - Gehäuseseitige struktur einer turbomaschine - Google Patents
Gehäuseseitige struktur einer turbomaschineInfo
- Publication number
- EP2611992A1 EP2611992A1 EP11785296.2A EP11785296A EP2611992A1 EP 2611992 A1 EP2611992 A1 EP 2611992A1 EP 11785296 A EP11785296 A EP 11785296A EP 2611992 A1 EP2611992 A1 EP 2611992A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- housing
- shroud
- side structure
- ring
- stator
- 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
Links
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
- 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
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
-
- 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
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
-
- 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
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
-
- 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
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
-
- 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
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Definitions
- the invention relates to a housing-side structure of a turbomachine according to the preamble of claim 1 or 11. Furthermore, the invention relates to a turbomachine according to the preamble of claim 12.
- a turbomachine with a stator and a rotor wherein the rotor blades and the stator has a housing and vanes.
- the rotor-side blades form at least one blade ring, which is adjacent at a radially outer end to a radially inner housing wall of the housing, is surrounded by the same and defines a radial gap with the same.
- the radially inner housing wall of the housing is also referred to as inner ring or shroud and serves in particular as a carrier for an inlet lining.
- the inner ring or shroud ring of a compressor or a turbine can be segmented and accordingly composed of a plurality of shroud segments, wherein a shroud segment is also referred to as Shroud.
- a shroud segment is also referred to as Shroud.
- the gap between the outer ring of the housing and the radially outer end of the or each blade ring to provide a so-called Active Clearance Control via adjusting devices in its gap adjusted or adjusted in order to automatically influence the gap and to ensure an optimal gap position and thus optimum pump marginality and optimum efficiency over all operating conditions.
- an adjusting device is assigned to each shroud segments of the shroud according to this prior art, which are preferably designed as electro-mechanical actuators. In this way, an active Spaltjanskin be provided.
- the Spaltjanen the gap between the radially outer ends of the blades of a blade ring and the inner ring or shroud of the housing via an Active Clearance Control is structurally complex. It is therefore desirable to realize the Spaltjanines with less effort.
- the present invention is based on the problem of creating a housing-side structure of a turbomachine, which allows a novel, simple gap technicallyscri. This problem is solved by a housing-side structure of a turbomachine according to claim 1 or 11.
- the shroud bearing the inlet lining is connected via at least one constriction to a stator-side housing part radially adjoining the shroud ring and thermally decoupled from the same.
- the housing-side structure of a turbomachine is due to the thermal decoupling of the shroud or inner ring from the radially outer adjacent housing thermal overshoot, especially in transient operating areas of the turbomachine during acceleration or deceleration of the same, reduced, whereby the Spalt matter between the blade ring and the can be radially outward adjacent to the blade ring adjacent shroud improved.
- the thermal decoupling takes place via at least one constriction between the outer ring and the radially outer side of the same adjacent housing part.
- a weight-optimal, compact, inexpensive, reliable and simple design can be provided with which a Spaltjan between radially outer ends of blades of a blade ring and a radially outside adjacent mantle ring and so an optimal surge margin and optimal efficiency without complex Active Clearance Control can be provided.
- a flange is formed on the housing part radially outwardly adjoining the casing, wherein a support element is fastened to the flange, which is in contact with at least one section at a downstream end of the casing ring to stabilize it.
- a support element is fastened to the flange, which is in contact with at least one section at a downstream end of the casing ring to stabilize it.
- the support member of the shroud is secured against tilting and is thereby stabilized.
- the support element which comes to rest at a downstream end of the shroud, performs a sealing function.
- a heat shield prevents a hot gas entering a housing-side recess. Through the heat shield the Spaltjan can be further improved.
- turbomachine according to the invention is defined in claim 12.
- FIG. 1 shows a section of a turbomachine in the region of a housing-side structure according to the invention, according to the invention, according to a first embodiment of the invention
- FIG. 2 shows a section of a turbomachine in the region of a housing-side structure according to the invention, according to the invention, according to a second exemplary embodiment of the invention.
- Fig. 3 shows a detail of a turbomachine in the region of a housing-side structure according to the invention thereof according to a third exemplary embodiment of the invention.
- the present invention relates to a housing-side structure of a turbomachine, in particular a gas turbine.
- the invention is used in particular for compressors, preferably for high pressure compressors.
- FIG. 1 shows a detail of a turbomachine in the region of a housing-side structure of a compressor according to a first exemplary embodiment of the invention, wherein in FIG. 1 a rotor-side rotor blade 10 with rotor blades 11 and upstream and downstream of the rotor blade ring 10 stator vane rings 12 and 13 with vanes 14 and 15, respectively.
- a compressor can be designed longitudinally divided or transversely divided.
- a shroud 16 which serves as a support for an inlet lining for the radially outer ends of the rotor-side blades 11 of the blade ring 10 and defines a gap 17 with the same.
- the shroud 16 of the housing-side structure to form at least one constriction 18 with a connected to the shroud 16 radially outwardly adjacent, stator housing part 19 and thermally decoupled from the same and the rest of the housing.
- the constriction 18 is arranged centrally in FIG. 1 to the shroud ring 16, wherein preferably the constriction 18 can be arranged up to the first third upstream of the shroud ring 16.
- a flange 20 is formed on which in the embodiment of FIG. 1, a support member 21 is attached, which in Fig. 1 with a portion 22 at the downstream end of the peripheral edge of the peripheral ring 16 for stabilizing and in particular sealing the same rests.
- a tilting of the shroud 16 can be avoided.
- the support element 21 is fastened to the flange 20 of the housing part 19 via fastening elements 34 designed in particular as screw elements. Over the circumference of the support member 21 a plurality of fasteners 34 are distributed.
- the support element 21 is preferably formed as a segmented ring.
- the housing-side structure of the turbomachine further has a heat shield or heat shield 24, wherein the heat shield 24 with a first end 25 in a AusOSE 26 of a 1 engages in the recess 26 of a guide blade 15, and wherein the heat shield 24 rests with a second end 27 on the support member 21, which of the stabilization and in particular sealing of the outer ring 16 serves.
- the heat shield 24 is preferably formed as a metallic ring.
- FIG. 2 A second embodiment of a housing-side structure of a turbomachine according to the invention, Fig. 2, wherein the embodiment of FIG. 2 substantially corresponds to the exemplary embodiment of FIG. 1, so that to avoid unnecessary repetition for the same components same reference numerals are used and will be discussed below only from such details is distinguished by which the embodiment of FIG. 2 from the embodiment of FIG.
- two bottlenecks 18A and 18B are present, via which the inlet lining-carrying shroud 16 is connected to the casing ring 19 radially adjoining the outer casing, housing part 19 is thermally decoupled from the same. Seen in the axial direction, the bottlenecks 18A and 18B are therefore positioned off-center to the shroud 16, whereas in the exemplary embodiment of FIG. 2, the constriction 18 is positioned centrally in the axial direction to the shroud 16. There may also be only one off-center bottleneck. Thus, it is possible that in the embodiment of Fig. 2, the upstream bottleneck 18A is present, but not the downstream bottleneck 18B.
- the support element 21 can be dispensed with in the exemplary embodiment of FIG. 2, in particular if the downstream constriction 18B, which has a stabilizing effect, is present. In this case can then be dispensed with the fasteners 34.
- the Wärnieschild 24 with the second end 27 is not on the support member 21, but rather on the flange 20 of the housing part 19th
- FIG. 3 A third embodiment of a housing-side structure of a turbomachine according to the invention, Fig. 3, wherein in the embodiment of FIG. 2 in turn a support member 21 'is present, which serves to stabilize and in particular seal the shroud 16, and which is attached to the flange 20, the the housing part 19 is formed, which is connected via the constriction 18 with the shroud 16.
- the constriction 18 in turn serves the thermal decoupling of the shroud 16 from the housing part 19th
- the support element 21 has two sections 28 and 29 at a downstream end of the shroud 16, namely with a first section 28 extending essentially in the horizontal or axial direction and a substantially vertical or vertical section Radial direction extending portion 29.
- These sections 28, 29 are used in particular for stabilizing the outer ring 16 and sealing it.
- a further section 30 is formed on the support element 21 'which likewise extends essentially in the axial or horizontal direction and protrudes in the downstream direction relative to the shroud 16 and radially outwardly adjoins the shroud 16 downstream, stator-side component 31 partially covered.
- This component 31 may be a section of a stator vane ring or a stator-side flow channel section.
- a radially inner contour 35 of the portion 29 of the support element 21 ' which limits a flow channel radially outwardly in sections, namely in the transition region to the component 31, is configured or contoured such that it directs a gas flow radially inward and so a hot gas inlet via the gap 32 prevented in the housing-side recess 23 and significantly reduced.
- a heat shield or heat shield 33 is present, however, in contrast to the exemplary embodiment of FIG. 1 together with the support member 21 'is secured to the flange 20. Also, the heat shield 33 of FIG. 3 prevents hot gas entering a housing-side recess.
- the heat shield 33 is preferably formed as a metallic ring.
- an effective and reliable Spaltjanin between radially outer ends of blades of a blade ring and a radially outer adjoining shroud 16 can be ensured in a structurally simple manner.
- the shroud 16 is thermally decoupled from the housing via at least one constriction 18, 18A, 18B.
- a tilting of the shroud 16 is preferably prevented by a support member 21 and 21 ', which mechanically stabilizes the shroud 16 and seals in particular against hot gas inlet.
- the Spaltjan can be further improved.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102010036071A DE102010036071A1 (de) | 2010-09-01 | 2010-09-01 | Gehäuseseitige Struktur einer Turbomaschine |
PCT/DE2011/001667 WO2012028140A1 (de) | 2010-09-01 | 2011-08-29 | Gehäuseseitige struktur einer turbomaschine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2611992A1 true EP2611992A1 (de) | 2013-07-10 |
EP2611992B1 EP2611992B1 (de) | 2018-03-21 |
Family
ID=45001583
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11785296.2A Not-in-force EP2611992B1 (de) | 2010-09-01 | 2011-08-29 | Gehäuseseitige struktur einer turbomaschine |
Country Status (4)
Country | Link |
---|---|
US (1) | US9540953B2 (de) |
EP (1) | EP2611992B1 (de) |
DE (1) | DE102010036071A1 (de) |
WO (1) | WO2012028140A1 (de) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2679777A1 (de) * | 2012-06-28 | 2014-01-01 | Alstom Technology Ltd | Verdichter für eine Gasturbine und Verfahren zur Reparatur und/oder zum Ändern der Geometrie und/oder zur Wartung des Verdichters |
JP5889266B2 (ja) * | 2013-11-14 | 2016-03-22 | 三菱重工業株式会社 | タービン |
DE102018113997A1 (de) * | 2018-06-12 | 2019-12-12 | Rolls-Royce Deutschland Ltd & Co Kg | Gehäuseanordnung für einen Axialverdichter eines Gasturbinentriebwerks |
DE102018116062A1 (de) | 2018-07-03 | 2020-01-09 | Rolls-Royce Deutschland Ltd & Co Kg | Strukturbaugruppe für einen Verdichter einer Strömungsmaschine |
US20240254890A1 (en) * | 2023-01-26 | 2024-08-01 | Pratt & Whitney Canada Corp. | Ram air driven blade tip clearance control system for turboprop engines |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3825364A (en) * | 1972-06-09 | 1974-07-23 | Gen Electric | Porous abradable turbine shroud |
GB2117843B (en) * | 1982-04-01 | 1985-11-06 | Rolls Royce | Compressor shrouds |
FR2604750B1 (fr) * | 1986-10-01 | 1988-12-02 | Snecma | Turbomachine munie d'un dispositif de commande automatique des debits de ventilation de turbine |
US5080557A (en) | 1991-01-14 | 1992-01-14 | General Motors Corporation | Turbine blade shroud assembly |
US5462403A (en) | 1994-03-21 | 1995-10-31 | United Technologies Corporation | Compressor stator vane assembly |
US6783324B2 (en) * | 2002-08-15 | 2004-08-31 | General Electric Company | Compressor bleed case |
US7094029B2 (en) | 2003-05-06 | 2006-08-22 | General Electric Company | Methods and apparatus for controlling gas turbine engine rotor tip clearances |
CN100419220C (zh) | 2003-05-07 | 2008-09-17 | 斯奈克玛马达公司 | 涡轮机静子及其装配和拆卸方法 |
DE102004037955A1 (de) | 2004-08-05 | 2006-03-16 | Mtu Aero Engines Gmbh | Turbomaschine, insbesondere Gasturbine |
FR2885168A1 (fr) | 2005-04-27 | 2006-11-03 | Snecma Moteurs Sa | Dispositif d'etancheite pour une enceinte d'une turbomachine, et moteur d'aeronef equipe de celui-ci |
FR2913050B1 (fr) | 2007-02-28 | 2011-06-17 | Snecma | Turbine haute-pression d'une turbomachine |
FR2938873B1 (fr) | 2008-11-21 | 2014-06-27 | Turbomeca | Organe de positionnement pour segment d'anneau |
-
2010
- 2010-09-01 DE DE102010036071A patent/DE102010036071A1/de not_active Withdrawn
-
2011
- 2011-08-29 US US13/819,531 patent/US9540953B2/en active Active
- 2011-08-29 WO PCT/DE2011/001667 patent/WO2012028140A1/de active Application Filing
- 2011-08-29 EP EP11785296.2A patent/EP2611992B1/de not_active Not-in-force
Also Published As
Publication number | Publication date |
---|---|
US20130183149A1 (en) | 2013-07-18 |
EP2611992B1 (de) | 2018-03-21 |
DE102010036071A1 (de) | 2012-03-01 |
WO2012028140A1 (de) | 2012-03-08 |
US9540953B2 (en) | 2017-01-10 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE69933601T2 (de) | Gasturbine | |
DE3941174A1 (de) | Spitzenspiel-einstellung an turbomaschinen | |
DE60318792T2 (de) | Zapfluft-Gehäuse für einen Verdichter | |
EP1471211B1 (de) | Dichtung zwischen Leitschaufeln und Rotor einer Hochdruckturbine | |
EP2044293B1 (de) | Gasturbine mit einem mantelringsegment, das einen rezirkulationskanal umfasst | |
DE3428892A1 (de) | Schaufel- und dichtspaltoptimierungseinrichtung fuer verdichter von gasturbinentriebwerken, insbesondere gasturbinenstrahltriebwerken | |
EP1653049B1 (de) | Leitschaufelring einer Strömungsmaschine und zugehöriges Modifikationsverfahren | |
EP2611992B1 (de) | Gehäuseseitige struktur einer turbomaschine | |
EP2647795A1 (de) | Dichtungssystem für eine Strömungsmaschine | |
EP2360352B1 (de) | Schraubenlose Zwischenstufendichtung einer Gasturbine | |
EP2884054A1 (de) | Verstellbare Leitschaufel mit Kegelstumpf in einer Lageranordnung | |
EP2478188B1 (de) | Dichtungssegment für eine Strömungsmaschine | |
EP3287611B1 (de) | Gasturbine | |
DE102008048006B4 (de) | Wellenleistungstriebwerk, insbesondere für ein Luftfahrzeug, mit einem Kühlgasführungssystem im Bereich der Befestigungsflansche der Rotorscheiben | |
EP2261464A1 (de) | Turbomaschine | |
DE10122732C2 (de) | Anordnung für eine nicht-hermetisch abdichtende Dichtung | |
EP1957755A1 (de) | Turbomaschine mit axialer laufschaufelsicherung | |
EP2358979B1 (de) | Axialverdichter für eine gasturbine mit passiver radialspaltkontrolle | |
EP2526263B1 (de) | Gehäusesystem für eine axialströmungsmaschine | |
EP1280980A1 (de) | Verfahren zur kühlung einer welle in einem hochdruck-expansionsabschnitt einer dampfturbine | |
EP1731715A1 (de) | Übergangsbereich zwischen einer Brennkammer und einer Turbineneinheit | |
EP1001138B1 (de) | Spitzendichtung für Turbinenlaufschaufeln | |
EP1783325B1 (de) | Befestigungsanordnung eines Rohres an einer Umfangsfläche | |
DE102004050739B4 (de) | Turbomaschine, insbesondere Gasturbine | |
EP2980481A1 (de) | Fluggasturbine mit einer dichtung zur abdichtung einer zündkerze an der brennkammerwand einer gasturbine |
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: 20130214 |
|
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 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: MTU AERO ENGINES AG |
|
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 |
|
INTG | Intention to grant announced |
Effective date: 20171204 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 981343 Country of ref document: AT Kind code of ref document: T Effective date: 20180415 |
|
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: DE Ref legal event code: R096 Ref document number: 502011013933 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20180321 |
|
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: 20180621 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: 20180321 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: 20180321 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: 20180321 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: 20180321 |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG4D |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 8 |
|
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: 20180321 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: 20180622 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: 20180321 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: 20180321 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: 20180621 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180321 |
|
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: 20180321 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: 20180321 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: 20180321 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: 20180321 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: 20180321 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: 20180321 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: 20180321 |
|
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: 20180321 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: 20180321 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: 20180321 |
|
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: 20180723 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502011013933 Country of ref document: DE |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: 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: 20180321 |
|
26N | No opposition filed |
Effective date: 20190102 |
|
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: 20180321 |
|
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: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180831 Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180829 Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180831 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20180831 |
|
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: 20180321 |
|
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: 20180831 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MM01 Ref document number: 981343 Country of ref document: AT Kind code of ref document: T Effective date: 20180829 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20190822 Year of fee payment: 9 |
|
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 NON-PAYMENT OF DUE FEES Effective date: 20180829 |
|
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: 20180321 |
|
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: 20110829 |
|
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: 20180321 Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180829 |
|
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: 20180721 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20200820 Year of fee payment: 10 Ref country code: GB Payment date: 20200825 Year of fee payment: 10 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 502011013933 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210302 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20210829 |
|
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: 20210829 Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210831 |