EP3117147A1 - Chambre de combustion d'un ensemble turbine à gaz et élément de support pour carreaux d'isolation thermique d'une chambre de combustion d'un ensemble turbine à gaz - Google Patents

Chambre de combustion d'un ensemble turbine à gaz et élément de support pour carreaux d'isolation thermique d'une chambre de combustion d'un ensemble turbine à gaz

Info

Publication number
EP3117147A1
EP3117147A1 EP15715825.4A EP15715825A EP3117147A1 EP 3117147 A1 EP3117147 A1 EP 3117147A1 EP 15715825 A EP15715825 A EP 15715825A EP 3117147 A1 EP3117147 A1 EP 3117147A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
tiles
heat insulating
casing
supporting element
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
EP15715825.4A
Other languages
German (de)
English (en)
Other versions
EP3117147B1 (fr
Inventor
Antonino LUTRI
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia SpA
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 Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Publication of EP3117147A1 publication Critical patent/EP3117147A1/fr
Application granted granted Critical
Publication of EP3117147B1 publication Critical patent/EP3117147B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/04—Supports for linings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05004—Special materials for walls or lining
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03342—Arrangement of silo-type combustion chambers

Definitions

  • the present invention relates to a combustion chamber of a gas turbine assembly and to a supporting element for heat insulating tiles of a combustion chamber of a gas turbine assembly.
  • combustion chambers of gas turbines must be internally lined with heat shields that allow protecting the structure and the members of the machine from very high temperatures. Inside the combustion chamber, in fact, temperatures can exceed 1500-1600 °C and are therefore high enough to melt the surrounding metal structures.
  • heat shields In gas turbines of plants for the production of electricity, heat shields generally include a plurality of contiguous tiles of a refractory material arranged in arrays or rows along respective circumferences, so as to form a surface as much as possible continuous.
  • the tiles are fixed to a casing of the combustion chamber by respective metal supporting elements.
  • the supporting elements are defined by pairs of elastic guides which extend longitudinally with respect to the casing and act in contrast with the sidewalls of the tiles.
  • the latter are shaped so as to be contiguous to the sidewalls of adjacent tiles and also protect the respective supporting elements from the effects of combustion.
  • the elastic guides are normally fixed permanently to the wall and the tiles are slidably inserted along the wall of the combustion chamber casing in the longitudinal direction.
  • At least one row of tiles must be fixed by removable supporting elements to be tightened after the placement of the tiles themselves. For this reason, part of the removable supporting elements remains necessarily exposed to high temperatures.
  • Combustion chambers are normally provided with cooling systems which, through the circulation of a stream of relatively cool air, allow limiting the temperatures of the tile supports and the damage that might result therefrom.
  • the exposed portions of the supporting elements tend to deteriorate and may undergo irreversible and potentially catastrophic damage.
  • extensive burns and cracks may occur which impair the functionality of the supports.
  • the detachment of metal portions may occur, which may be conveyed towards the turbine by the flow of flue gas and cause the destruction of several blades.
  • a combustion chamber of a gas turbine assembly and a supporting element for heat insulating tiles of a combustion chamber of a gas turbine assembly are provided, as defined in claims 1 and 15, respectively.
  • FIG. 1 is a perspective view of a portion of a gas turbine assembly according to an embodiment of the present invention
  • FIG. 2 is a front view of the combustion chamber in figure 1, partially sectional along an axial longitudinal plane;
  • FIG. 3 shows an enlarged detail of the view in figure 2, where supporting elements for heat insulating tiles according to an embodiment of the present invention are shown;
  • figure 4 is a front view of one of the supporting elements in figure 2;
  • figure 5 is a rear view of the supporting element in figure 4;
  • figure 6 is a right side view of the supporting element in figure 4;
  • FIG. 7 is a bottom plan view of the supporting element in figure 4, sectioned along the track plane VII- VII in figure 4;
  • FIG. 8 is a simplified and enlarged perspective view, partially sectioned along an axial longitudinal plane and with parts removed for clarity, of a portion of the combustion chamber in figure 2;
  • FIG. 9 is a front view of a combustion chamber of a gas turbine assembly according to a different embodiment of the present invention, partially sectional along an axial longitudinal plane;
  • FIG. 10 shows an enlarged detail of the view in figure 9, where supporting elements for heat insulating tiles according to an embodiment of the present invention are shown.
  • a gas turbine assembly of a plant for the production of electricity is indicated as a whole with reference numeral 1.
  • the gas turbine assembly 1 comprises a compressor 2, a combustion chamber 3 and a gas turbine 5.
  • a rotor 7 comprises a compressor portion 7a and turbine portion 7b.
  • the combustion chamber 3 also shown in figure 2, is of the silo type and, in one embodiment, comprises a casing 8 defined by a substantially cylindrical tower which extends about a vertical axis A and defines a combustion volume 8a therein.
  • the combustion volume is superiorly delimited by a roof 8b of the casing 8 and fluidically communicates on an opposite side with the gas turbine 5.
  • the combustion chamber 3 is provided with burners 9 which allow burning a mixture of air coming from compressor 2 and fuel supplied through a supply line (not shown) .
  • the combustion chamber 3 is also internally lined with a heat shield 10, which comprises a plurality of tiles 12 arranged in adjacent rows about axis A.
  • Tiles 12a of a closing row are fixed to casing 8 by supporting elements 15, described in detail hereafter. Tiles 12 of the other rows may be fixed to casing 8 by conventional supporting elements, not shown herein for convenience.
  • the closing row of tiles 12a is arranged centrally. Tiles 12a of the closing row are the last ones to be mounted after all the other tiles have been placed in their respective positions, normally by sliding them along longitudinal rails (not shown) with respect to casing 8. Conversely, tiles 12a are the first ones to be removed when part or all of the heat shield 10 needs to be removed.
  • Tiles 12a of the closing row are fixed to the casing 8 each by four respective supporting elements 15, two on each sidewall, as shown in more detail in figure 3.
  • FIGS 4-7 show one of the supporting elements 15, to which reference shall be made, meaning that the others are the same.
  • the supporting element 15 comprises a base 16, a pair of elastic fastening elements 17 and a protecting plate 18 which, in one embodiment, are made in one piece.
  • Base 16 is tightened against casing 8 by a fixing plate 19 (figure 3) .
  • the elastic fastening elements 17 extend in opposite directions from base 16 in a substantially symmetrical way and are shaped so as to withhold portions of respective tiles 12a against casing 8, as shown in figure 7 (where casing 8 and tiles 12a are shown with a dashed and dotted line) . More precisely, the elastic fastening elements 17 are inclined by angles substantially symmetrical with respect to base 16 and extend transversely to the sidewalls of the respective tiles 12a. Angles are comprised between 30° and 60° and, in one embodiment, they are about 46.5°. Ends of the elastic fastening elements 17 opposite to base 16 are arranged in contrast against respective edges of tiles 12a, so as to prevent tiles 12a themselves from separating from casing 8.
  • the protecting plate 18 substantially rectangular in shape, is connected to one of the elastic fastening elements 17 and is arranged to cover base 16.
  • the protecting plate 18 is substantially parallel to base 16 and extends between tiles 12a supported by the supporting element 15.
  • the protecting plate 18 closes the gap between tiles 12a, where the supporting element 15 is arranged (figures 3 and 7), and prevents base 16 and the elastic fastening elements
  • One side of the protecting plate 18 not engaged against tiles 12a is shaped to accommodate a fastening element 20 (figure 3) .
  • each supporting element 15 a face 18a of the protecting plate 18 oriented towards the inside of casing 8 is covered with a heat insulating layer 22 of a heat insulating material which acts as a thermal protection element for the protecting plate 18 itself.
  • the heat insulating layer 22 completely covers the protecting plate
  • the heat insulating material is a refractory material, for example a ceramic material having a porosity value greater than 20%.
  • the heat insulating material contains a MCrAlY alloy, where M can be iron, cobalt, nickel or cobalt /nickel .
  • the heat insulating layer 22 has such a thickness as to prevent potentially harmful temperatures from propagating to the supporting element 15.
  • the thickness of the heat insulating layer 18 is between 75 ⁇ X and 175 ⁇ , preferably between 100 ⁇ and 150 ⁇ .
  • annular ridge 25 axially delimits a seat 26 for housing an upper row of tiles 12b adjacent to a roof 8b of casing 8.
  • the annular ridge 25, which is part of the structure of casing 8, is made of a metal material while roof 8b is lined with a refractory material.
  • Tiles 12b are arranged in seat 26 and have upper edges
  • Edges 12c protruding towards roof 8b of casing 8, so as to cover respective portions of the annular ridge 25. Edges 12c therefore perform the function of thermal protection elements for the annular ridge 25.
  • tiles 12b have a first face 12d, adjacent to casing 8, and a second face 12e, oriented towards the combustion volume 8a, inclined with respect to each other.
  • tiles 12b have a first thickness SI at edges 12c and a second thickness S2, smaller than the first thickness SI, at second edges 12f, opposite to the first edges 12c.
  • the first thickness SI is sufficient to shape tiles 12b so that edges 12c may cover the annular ridge 25.
  • the second thickness at edges 12f is substantially equal to the thickness of the contiguous tiles 12.
  • the surface of the heat shield 10, which delimits the combustion volume 8a, is therefore substantially free from discontinuity, without the need to increase the thickness of the other tiles 12 in order to obtain the protruding edges 12c beyond what is required by the insulation needs.
  • a combustion chamber 103 of a gas turbine comprises a casing 108 which extends about an axis A' and internally delimits a combustion volume 108a.
  • Casing 108 is internally lined with a heat shield 110, which comprises a plurality of tiles 112 arranged in adjacent rows about axis A' .
  • the heat shield 110 has two closing rows, more precisely comprising tiles 112a adjacent to a roof 108b of casing 108 and tiles 112b contiguous to tiles Tiles 112a, 112b are fixed to casing 108 by means of supporting elements 15, of the type already described with reference to figure 4-7. Each tile 112a, 112b has a pair of supporting elements 15 on each sidewall.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La présente invention concerne une chambre de combustion d'un ensemble turbine à gaz comprenant : un carter (8), définissant un volume de combustion (8a) en son sein ; un écran thermique (10), qui double l'intérieur du carter (8) et comprend une pluralité de carreaux (12, 12a, 12b) en un matériau réfractaire ; des éléments structuraux (15) formés de manière à définir des sièges de logement (26) des carreaux (12, 12a, 12b) et à maintenir les carreaux (12, 12a, 12b) dans les sièges de logement respectifs (26) ; et des éléments de protection thermique (22), disposés de manière à recouvrir les parties des éléments structuraux (15) faisant face à l'intérieur du carter (8).
EP15715825.4A 2014-03-03 2015-03-03 Chambre de combustion d'un ensemble turbine à gaz Active EP3117147B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITMI20140323 2014-03-03
PCT/IB2015/051554 WO2015132728A1 (fr) 2014-03-03 2015-03-03 Chambre de combustion d'un ensemble turbine à gaz et élément de support pour carreaux d'isolation thermique d'une chambre de combustion d'un ensemble turbine à gaz

Publications (2)

Publication Number Publication Date
EP3117147A1 true EP3117147A1 (fr) 2017-01-18
EP3117147B1 EP3117147B1 (fr) 2019-01-16

Family

ID=50877558

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15715825.4A Active EP3117147B1 (fr) 2014-03-03 2015-03-03 Chambre de combustion d'un ensemble turbine à gaz

Country Status (3)

Country Link
EP (1) EP3117147B1 (fr)
CN (1) CN106164590B (fr)
WO (1) WO2015132728A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11255547B2 (en) 2018-10-15 2022-02-22 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine
US11293637B2 (en) * 2018-10-15 2022-04-05 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3625056C2 (de) * 1986-07-24 1997-05-28 Siemens Ag Feuerfeste Auskleidung, insbesondere für Brennkammern von Gasturbinenanlagen
US5113660A (en) * 1990-06-27 1992-05-19 The United States Of America As Represented By The Secretary Of The Air Force High temperature combustor liner
DE59706557D1 (de) * 1997-07-28 2002-04-11 Alstom Keramische Auskleidung
DE19825546C1 (de) * 1998-06-08 1999-08-26 Didier Werke Ag Einrichtung zum Befestigen von Auskleidungsplatten
CN201106863Y (zh) * 2007-09-13 2008-08-27 天津大沽化工股份有限公司 防炉衬脱落装置
CN201152541Y (zh) * 2007-12-17 2008-11-19 张宝祯 多功能耐火砖的砖座
EP2452126B1 (fr) * 2009-07-08 2016-12-14 Berry Metal Company Appareil pour constructions à ossature bois et en briques

Also Published As

Publication number Publication date
CN106164590A (zh) 2016-11-23
EP3117147B1 (fr) 2019-01-16
CN106164590B (zh) 2019-11-26
WO2015132728A1 (fr) 2015-09-11

Similar Documents

Publication Publication Date Title
US8006498B2 (en) Combustion chamber of a combustion system
US8596963B1 (en) BOAS for a turbine
EP2846097B1 (fr) Chambre de combustion d'une turbine à gaz avec des plaques& xA;ayant des orifices de refroidissement par pellicule
EP2354660B1 (fr) Chambre de combustion avec élément d'étenchéité de segment de chemise de chambre de combustion
US8303245B2 (en) Shroud assembly with discourager
EP1813868B1 (fr) Elémemts de paroi de chambre de combustion de turbine à gaz
EP2402557B1 (fr) Ensemble de rotor de turbine
RU2622590C2 (ru) Элемент теплозащитного экрана для обвода воздуха компрессора вокруг камеры сгорания
US10408451B2 (en) Wedge-shaped ceramic heat shield of a gas turbine combustion chamber
US8684665B2 (en) Ring sector of turbomachine turbine
US5842831A (en) Arrangement for the thermal protection of a rotor of a high-pressure compressor
US10267172B2 (en) Rotary assembly for a turbomachine
US10100737B2 (en) Impingement cooling arrangement having a snap-in plate
EP3117147B1 (fr) Chambre de combustion d'un ensemble turbine à gaz
US9745852B2 (en) Axial rotor portion and turbine rotor blade for a gas turbine
US20120269650A1 (en) Turbine wheel for a turbine engine
US20120039716A1 (en) Guide vane system for a turbomachine having segmented guide vane carriers
US10578305B2 (en) Bruner assembly
US20150354826A1 (en) Annular combustion chamber of a gas turbine and gas turbine with such a combustion chamber
US10422247B2 (en) Housing structure of a turbomachine with heat protection shield
RU2634992C2 (ru) Удерживающий элемент для удерживания кирпича теплозащитного экрана и способ охлаждения несущей структуры теплозащитного экрана
CN102365425A (zh) 密封板和动叶片系统
JP2015059083A (ja) 熱暴露構成要素の面に耐熱防護構成要素を設ける方法
US20150241061A1 (en) Heat shield with a supporting structure and method for cooling the supporting structure
CN106247399B (zh) 用于燃气轮机的燃烧室的具有较薄的厚度的绝热陶瓷砖瓦

Legal Events

Date Code Title Description
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: 20160916

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

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: 20180807

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

REG Reference to a national code

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: DE

Ref legal event code: R096

Ref document number: 602015023597

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1089957

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190215

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190116

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: 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: 20190116

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1089957

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190116

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: 20190416

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: 20190516

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: 20190116

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: 20190116

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: 20190116

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: 20190116

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: 20190116

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: 20190116

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: 20190116

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: 20190417

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: 20190516

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: 20190416

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: 20190116

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602015023597

Country of ref document: DE

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: 20190116

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: 20190116

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: 20190116

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: 20190116

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: 20190116

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: 20190116

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: 20190116

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: 20190116

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: 20190116

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

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

Ref country code: LU

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

Effective date: 20190303

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: 20190116

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20190331

26N No opposition filed

Effective date: 20191017

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

Effective date: 20190416

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: 20190303

Ref country code: LI

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

Effective date: 20190331

Ref country code: CH

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

Effective date: 20190331

Ref country code: GB

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

Effective date: 20190416

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: 20190316

Ref country code: BE

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

Effective date: 20190331

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: 20190116

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: 20190116

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: 20190303

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

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: 20190116

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: 20150303

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

Effective date: 20190116

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

Ref country code: DE

Payment date: 20240321

Year of fee payment: 10

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20240430