EP2818642A1 - Dichtringsegment für einen Stator einer Turbine - Google Patents

Dichtringsegment für einen Stator einer Turbine Download PDF

Info

Publication number
EP2818642A1
EP2818642A1 EP13174357.7A EP13174357A EP2818642A1 EP 2818642 A1 EP2818642 A1 EP 2818642A1 EP 13174357 A EP13174357 A EP 13174357A EP 2818642 A1 EP2818642 A1 EP 2818642A1
Authority
EP
European Patent Office
Prior art keywords
sealing ring
ring segment
turbine
elastic element
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.)
Withdrawn
Application number
EP13174357.7A
Other languages
German (de)
English (en)
French (fr)
Inventor
Thorsten Barz
Roland Häbel
Sebastian Stupariu-Cohan
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP13174357.7A priority Critical patent/EP2818642A1/de
Priority to CN201480035984.5A priority patent/CN105392966B/zh
Priority to US14/898,135 priority patent/US10215041B2/en
Priority to RU2016102766A priority patent/RU2657390C2/ru
Priority to JP2016522477A priority patent/JP6067942B2/ja
Priority to PCT/EP2014/063432 priority patent/WO2014207058A1/de
Priority to EP14734785.0A priority patent/EP2984295B1/de
Publication of EP2818642A1 publication Critical patent/EP2818642A1/de
Priority to SA515370314A priority patent/SA515370314B1/ar
Withdrawn legal-status Critical Current

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
    • 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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to a sealing ring segment for a stator of a turbine, which essentially has the shape of a cylinder jacket segment and has on its outer side a groove for fixing a plurality of guide vanes.
  • a turbine is a turbomachine that converts the internal energy (enthalpy) of a flowing fluid (liquid or gas) into rotational energy and ultimately into mechanical drive energy.
  • the fluid flow is removed by the vortex-free as possible laminar flow around the turbine blades a portion of its internal energy, which passes to the blades of the turbine.
  • the turbine shaft is rotated, the usable power is delivered to a coupled machine, such as a generator.
  • Blades and shaft are parts of the movable rotor or rotor of the turbine, which is arranged within a housing.
  • Blades mounted on the axle are mounted on the axle. Blades mounted in a plane each form a paddle wheel or impeller. The blades are slightly curved profiled, similar to an aircraft wing. Before each impeller is usually a stator. These vanes protrude from the housing into the flowing medium and cause it to spin. The swirl generated in the stator (kinetic energy) is used in the following impeller to set the shaft on which the impeller blades are mounted in rotation.
  • the stator and the impeller together are called stages. Often several such stages are connected in series. Since the stator is stationary, and the vanes are attached to the housing exterior, a seal must be made to the shaft of the impeller to minimize losses.
  • the guide vanes are held on the rotor side by cylinder jacket-shaped sealing rings. These usually consist of a plurality, usually ten segments. These are pushed onto an entanglement at the head of the vanes (tongue and groove connection) and thus seal off the hot gas duct in relation to the rotor. In order to prevent displacement in the circumferential direction, the sealing ring segments are individually fixed by bolts, each of which projects radially into one of the guide vanes.
  • sealing ring segment has an acting on the respective vane by means of a restoring elastic element.
  • the invention is based on the consideration that the life of the turbine increased and the repair costs for the turbine could be reduced if the wear could be reduced by the relative movement of the vanes and sealing ring segment. For this, the relative movement would have to be limited. However, consideration must be given to the thermal expansion during operation, so that a fixed form-locking fixation is eliminated. Remedy creates a non-positive fixation by means of an elastic element, which ensures a force-locking fixation of the guide vane by its restoring force, while by the elasticity thermal expansion remains possible.
  • each guide vane fixable on the sealing ring segment at least one elastic element acting on the respective guide vane by means of a restoring force is provided for each guide vane fixable on the sealing ring segment.
  • the sealing ring segment is fixed particularly securely, since a frictional connection is formed by an elastic element with each individual vane. Therefore, none of the vanes can perform a wear-producing relative movement.
  • the groove for fixing the guide vanes advantageously extends in the circumferential direction and / or the restoring force of the respective elastic element advantageously acts in the radial direction. This allows easy installation of the sealing ring segment, which can be easily pushed onto the entanglement of the guide vanes. Due to the radial orientation of the elastic element this can be biased from the inside after insertion of the sealing ring.
  • the respective elastic element is a pressure pin.
  • a pressure pin is a substantially cylindrical element which can be compressed in the axial direction, for example by an internal structure in the manner of a piston.
  • the pressure pin z. B. configured by self-resetting by appropriate spring arrangement.
  • a pressure pin can be fixed through a corresponding opening in the sealing ring segment and aligned accordingly.
  • the respective elastic element in particular the pressure pin comprises a plate spring.
  • a plate spring is meant a conical ring shell, which is resilient in the axial direction and so both dormant and vibratory (dynamic) can be claimed.
  • the force is usually applied via the upper inner edge and the lower outer edge.
  • the diaphragm spring can be used as a single spring or as a spring column. In a column, either individual disc springs or spring assemblies consisting of several springs can be stacked alternately.
  • the diaphragm spring has in comparison with other types of springs a number of advantageous properties, it may, for. B. accommodate very large forces in a small installation space.
  • the diaphragm spring has a long service life under dynamic load, as z. B. occurs in a turbine.
  • Suitable materials include spring steels, also stainless and heat-resistant as well as copper (CuSn 8, CuBe 2) and nickel alloys (Nimonic, Inconel, Duratherm).
  • the respective elastic element, in particular the pressure pin is fixed by means of a screw on the sealing ring segment.
  • this results in a detachable connection, which thus allows a later replacement in the course of a revision, on the other hand allows a simple assembly.
  • the restoring force on the entanglement of the guide blade is precisely adjusted by the depth of the screwing.
  • an anti-rotation is provided, for example by a side einhakenden anti-rotation bolt.
  • the respective elastic element for the circumferential fixation of the sealing ring segment is arranged such that it fixes the respective guide vane in the circumferential direction in a form-fitting manner.
  • the guide vane has a corresponding depression, into which the correspondingly executed elastic element is inserted becomes.
  • a plurality of the vanes are arranged at their radially inwardly directed head by means of a spring in a groove of a described sealing ring segment.
  • a turbine advantageously comprises such a stator.
  • the turbine is designed as a gas turbine.
  • the thermal, mechanical and dynamic loads are particularly high, so that the described configuration of the sealing ring segment offers particular advantages in terms of minimizing wear.
  • a power plant advantageously comprises such a turbine.
  • the advantages achieved by the invention are, in particular, that by introducing a cup spring design for the defined fixed bias of the sealing ring and the vane, an avoidance of relative movements between the two parts is achieved. At the same time a thermal mobility is hereby ensured despite fixed bias. With the disc spring structures described a defined tension between blades and sealing ring segments can be applied, which minimizes or prevents the relative movement, in particular under dynamic loads between the components. The material wear can thus be reduced or avoided.
  • the FIG. 1 shows a turbine 100, here a gas turbine, in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted around a rotation axis 102 (axial direction) rotor 103, which is also referred to as a turbine runner.
  • a rotation axis 102 axial direction
  • rotor 103 which is also referred to as a turbine runner.
  • an intake housing 104 a compressor 105
  • a combustion chamber 110 shown here as an annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the combustion chamber 106 communicates with an annular hot gas channel 111.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed from two blade rings.
  • a guide blade ring 115 is followed by a ring 125 formed of rotor blades 120.
  • the guide vanes 130 are fastened to the stator 143, whereas the rotor blades 120 of a ring 125 are attached to the rotor 103 by means of a turbine disk 133.
  • the rotor blades 120 thus form components of the rotor or rotor 103.
  • Coupled to the rotor 103 is a generator or a working machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the hot and pressurized working fluid 113 in the combustor 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the highest thermal load in addition to the heat shield stones lining the combustion chamber 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • Each vane 130 has a vane root (not shown) facing the housing 138 of the turbine 108 and a vane head opposite the vane root.
  • the vane head faces the rotor 103 and is fixed in a sealing ring 140.
  • Each sealing ring 140 of a turbine stage encloses the shaft of the rotor 103. It is advantageously formed of ten similar sealing ring segments 144.
  • sealing pins 146 are provided in the sealing ring segments, which in FIG. 2 are shown in cross section.
  • the pressure pin 146 is fixed in a radially aligned through bore 148 with a thread 150 by screwing.
  • the pressure pin consists of a cylindrical portion 152 with a corresponding thread for screwing with the sealing ring segment, an adjoining piston 154 of smaller diameter, on which a in the axial direction of the pressure pin 146 movable capsule 156 sits, which surrounds the piston 154 at its tip , As a result, it is fixed in a form-fitting manner in the radial direction of the pressure bolt 146.
  • the piston 154 between section 152 and capsule 156 enclosing a total of eight mutually arranged disc springs 158 are positioned, which exert a restoring force at an axial compression of the pressure pin 146. Since the pressure pin 146 is screwed into the sealing ring segment 144 in the radial direction relative to the axis of rotation of the gas turbine 102, it exerts a defined force on the entanglement of the guide blade 130, so that relative movements are prevented, but thermal expansion remains possible. The return force can be adjusted via the screw-in depth.
  • FIG. 3 shows a longitudinal section through the sealing ring segment 144.
  • the sealing ring 144 has two axially and radially spaced grooves 160 which extend in the circumferential direction and are open in the radial direction.
  • the sealing ring segment 144 can be pushed onto the guide vane ring during assembly. Since the pressure pin 146 has a radial restoring force the vane 130 is elastically fixed in the grooves 160.
  • the pressure pin 146 is secured against rotation by means of a bolt 164.
  • the bolt 164 is inserted through a axially extending bore which meets the bore 148 of the pressure bolt 146 and screwed. As a result, it exerts a lateral force on the thread of the pressure bolt 146 and fixes it non-positively.
  • FIG. 4 shows finally a partial section through the sealing ring 140 and the sealing ring segments 144.
  • the pressure pin 146 exert a restoring force on the guide vanes 130 as described.
  • One of the pressure bolts 146 is additionally designed as a peripheral fixing bolt 166. It is longer than the remaining pressure pin 146 and protrudes into a depression 168 of a foot of a guide blade 130 which is molded onto it. As a result, the sealing ring segment 144 is fixed to the guide blade 130 in the circumferential direction.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13174357.7A 2013-06-28 2013-06-28 Dichtringsegment für einen Stator einer Turbine Withdrawn EP2818642A1 (de)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP13174357.7A EP2818642A1 (de) 2013-06-28 2013-06-28 Dichtringsegment für einen Stator einer Turbine
CN201480035984.5A CN105392966B (zh) 2013-06-28 2014-06-25 用于涡轮机的定子的密封环段
US14/898,135 US10215041B2 (en) 2013-06-28 2014-06-25 Sealing ring segment for a stator of a turbine
RU2016102766A RU2657390C2 (ru) 2013-06-28 2014-06-25 Сегмент уплотнительного кольца для статора турбины
JP2016522477A JP6067942B2 (ja) 2013-06-28 2014-06-25 タービンのステータのためのシールリングセグメント
PCT/EP2014/063432 WO2014207058A1 (de) 2013-06-28 2014-06-25 Dichtringsegment für einen stator einer turbine
EP14734785.0A EP2984295B1 (de) 2013-06-28 2014-06-25 Dichtringsegment für einen stator einer turbine
SA515370314A SA515370314B1 (ar) 2013-06-28 2015-12-24 قطاع منع تسريب حلقي لجزء ساكن من توربين

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13174357.7A EP2818642A1 (de) 2013-06-28 2013-06-28 Dichtringsegment für einen Stator einer Turbine

Publications (1)

Publication Number Publication Date
EP2818642A1 true EP2818642A1 (de) 2014-12-31

Family

ID=48700406

Family Applications (2)

Application Number Title Priority Date Filing Date
EP13174357.7A Withdrawn EP2818642A1 (de) 2013-06-28 2013-06-28 Dichtringsegment für einen Stator einer Turbine
EP14734785.0A Active EP2984295B1 (de) 2013-06-28 2014-06-25 Dichtringsegment für einen stator einer turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP14734785.0A Active EP2984295B1 (de) 2013-06-28 2014-06-25 Dichtringsegment für einen stator einer turbine

Country Status (7)

Country Link
US (1) US10215041B2 (enrdf_load_stackoverflow)
EP (2) EP2818642A1 (enrdf_load_stackoverflow)
JP (1) JP6067942B2 (enrdf_load_stackoverflow)
CN (1) CN105392966B (enrdf_load_stackoverflow)
RU (1) RU2657390C2 (enrdf_load_stackoverflow)
SA (1) SA515370314B1 (enrdf_load_stackoverflow)
WO (1) WO2014207058A1 (enrdf_load_stackoverflow)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
PL3542033T3 (pl) * 2016-11-18 2024-02-05 L'Air Liquide, Société Anonyme pour l'Etude et l'Exploitation des Procédés Georges Claude Dysza wlotowa o niskim współczynniku tarcia do turboekspandera
FR3059041B1 (fr) * 2016-11-21 2020-05-08 Safran Aircraft Engines Dispositif de pilotage rotor/stator avec lechette a ressort
CN107882599B (zh) * 2017-11-01 2021-02-09 中国航发湖南动力机械研究所 整体式涡轮外环连接结构及涡轮发动机
EP4053381B1 (en) 2021-03-01 2024-11-20 ANSALDO ENERGIA S.p.A. Ring segment device for turbine vanes of a power plant and corresponding gas turbine assembly for power plant
CN113294214B (zh) * 2021-06-24 2022-07-22 上海万仞动力技术有限公司 一种装备有拼装隔板的冲动式汽轮机

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1441108A2 (en) * 2003-01-27 2004-07-28 United Technologies Corporation Damper for gas turbine stator assembly
US20080019836A1 (en) * 2004-02-11 2008-01-24 Mtu Aero Engines Gmbh Damping Arrangement for Guide Vanes
US7645117B2 (en) * 2006-05-05 2010-01-12 General Electric Company Rotary machines and methods of assembling
US20110135479A1 (en) * 2008-12-25 2011-06-09 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB142924A (en) * 1919-02-12 1920-05-12 Samuel Hough Improvements in adjustable rotary cutting heads for lathes
US3501246A (en) * 1967-12-29 1970-03-17 Westinghouse Electric Corp Axial fluid-flow machine
US4576548A (en) 1984-01-17 1986-03-18 Westinghouse Electric Corp. Self-aligning static seal for gas turbine stator vanes
US4897021A (en) 1988-06-02 1990-01-30 United Technologies Corporation Stator vane asssembly for an axial flow rotary machine
DE19513457A1 (de) 1995-04-08 1996-10-10 Abb Management Ag Rotor einer elektrischen Maschine
PL1674771T3 (pl) * 2004-12-23 2010-10-29 Siemens Ag Układ do uszczelniania szczeliny pomiędzy pierwszym elementem konstrukcyjnym i drugim elementem konstrukcyjnym
JP4918263B2 (ja) * 2006-01-27 2012-04-18 三菱重工業株式会社 軸流圧縮機の静翼環
US8001790B2 (en) * 2008-08-11 2011-08-23 Mitsubishi Heavy Industries, Ltd. Gas turbine
JP5501609B2 (ja) * 2008-12-25 2014-05-28 三菱重工業株式会社 タービン翼およびガスタービン
US8454023B2 (en) * 2011-05-10 2013-06-04 General Electric Company Retractable seal system

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1441108A2 (en) * 2003-01-27 2004-07-28 United Technologies Corporation Damper for gas turbine stator assembly
US20080019836A1 (en) * 2004-02-11 2008-01-24 Mtu Aero Engines Gmbh Damping Arrangement for Guide Vanes
US7645117B2 (en) * 2006-05-05 2010-01-12 General Electric Company Rotary machines and methods of assembling
US20110135479A1 (en) * 2008-12-25 2011-06-09 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine

Also Published As

Publication number Publication date
RU2657390C2 (ru) 2018-06-13
WO2014207058A1 (de) 2014-12-31
JP6067942B2 (ja) 2017-01-25
EP2984295A1 (de) 2016-02-17
SA515370314B1 (ar) 2020-03-15
RU2016102766A (ru) 2017-08-01
US20160208630A1 (en) 2016-07-21
RU2016102766A3 (enrdf_load_stackoverflow) 2018-04-04
JP2016523342A (ja) 2016-08-08
US10215041B2 (en) 2019-02-26
CN105392966B (zh) 2018-03-20
CN105392966A (zh) 2016-03-09
EP2984295B1 (de) 2017-05-03

Similar Documents

Publication Publication Date Title
EP2503246B1 (de) Segmentierter Brennkammerkopf
EP2344723B1 (de) Gasturbine mit dichtplatten an der turbinenscheibe
EP2984295B1 (de) Dichtringsegment für einen stator einer turbine
EP1508672A1 (de) Segmentierter Befestigungsring für eine Turbine
DE102014219552A1 (de) Leitschaufelverstellvorrichtung einer Gasturbine
EP2128524A1 (de) Bauteilanordnung, Brennkammeranordnung und Gasturbine
DE112016004554T5 (de) Betätigungsvorrichtung für variable Statorschaufeln
DE102016117960A1 (de) Turbolader
DE102008005579A1 (de) Verstellbare Leitschaufelanordnung für ein Gasturbinentriebwerk mit einer inkrementell drehbaren Lagerungsbuchse
EP3064706A1 (de) Leitschaufelreihe für eine axial durchströmte Strömungsmaschine
EP2799776A1 (de) Brennerdichtung für Gasturbinen-Brennkammerkopf und Hitzeschild
WO2010052053A1 (de) Gasturbine mit sicherungsplatte zwischen schaufelfuss und scheibe
EP2211023A1 (de) Leitschaufelsystem für eine Strömungsmaschine mit segmentiertem Leitschaufelträger
DE102012213016A1 (de) Verfahren zur Minimierung des Spalts zwischen einem Läufer und einem Gehäuse
DE102010007724A1 (de) Schraubenlose Zwischenstufendichtung einer Gasturbine
EP3017147B1 (de) Rotor für eine turbine
EP2236759A1 (de) Laufschaufelsystem
EP2591213A2 (de) Verdichter und zugehörige gasturbine
WO2009109430A1 (de) Dichtungsanordnung und gasturbine
DE2140337C3 (de) Gasturbinentriebwerk mit wärmebeweglich gelagerter Welle
WO2009059580A1 (de) Gasturbinenbauteil und verdichter mit einem solchen bauteil
EP1783325B1 (de) Befestigungsanordnung eines Rohres an einer Umfangsfläche
DE102013211629A1 (de) Leitschaufelanordnung und Verfahren zum Montieren einer Leitschaufel
DE102021113833A1 (de) Anordnung zur Zentrierung zweier aneinander angrenzender Teile
DE102015110252A1 (de) Statorvorrichtung für eine Strömungsmaschine mit einer Gehäuseeinrichtung und mehreren Leitschaufeln

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: 20130628

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: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20150701