EP1257732B1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

Info

Publication number
EP1257732B1
EP1257732B1 EP01913779A EP01913779A EP1257732B1 EP 1257732 B1 EP1257732 B1 EP 1257732B1 EP 01913779 A EP01913779 A EP 01913779A EP 01913779 A EP01913779 A EP 01913779A EP 1257732 B1 EP1257732 B1 EP 1257732B1
Authority
EP
European Patent Office
Prior art keywords
cavity
platform
blade
turbine rotor
walls
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.)
Expired - Lifetime
Application number
EP01913779A
Other languages
German (de)
English (en)
Other versions
EP1257732A1 (fr
Inventor
Peter Tiemann
Michael Strassberger
Dirk Anding
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
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP01913779A priority Critical patent/EP1257732B1/fr
Publication of EP1257732A1 publication Critical patent/EP1257732A1/fr
Application granted granted Critical
Publication of EP1257732B1 publication Critical patent/EP1257732B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the invention relates to a turbine blade, with a internally uncooled blade profile extending from a blade platform extends from, which extends into a turbine disc engaging blade root adjoins its radial Cross section to the blade platform an area increasing width.
  • the object of the present invention is therefore a turbine blade to create an extension of the blade profiles allows without or with only a minor Increase local loads on the turbine disc or from blade feet.
  • the blade root is a has an open cavity facing away from the platform ends blindly and in the area of increasing width of the Blade base is widened in cross section.
  • the blade root is usually used to ensure stability solidly trained and shows compared to the rest Dimensions of the turbine blade have a large cross section on. So its mass is high and it has a large proportion on the one that occurs when the turbine disc rotates Centrifugal load on the turbine disc and the holding devices for the shovel. Because of the hollowing out the mass of the foot and thus the centrifugal force considerably.
  • the special form of the excavation namely one cross-sectional widening on the longitudinal walls in the area increasing width of the blade root ensures a optimal use of the shape of the blade root in view on lowering the mass. Because the hollowing out ends blindly on the platform side, are also the stability requirements, which especially in the area between platform and Blade profile due to diverse strong forces and temperature attack are very high, met.
  • the invention enables thus at the same time to keep the mass of the blade low and to maintain or even improve their stability.
  • the average tension level lowered in the foot area and tension peaks on holding teeth of the foot and the adjacent turbine disc resulting in an extension of the life of the turbine blade and especially to improve durability of the foot leads. It is therefore without endangering stability the turbine blade and while maintaining the shape of the foot possible to extend the blade profile to the outside and thus increase the efficiency of the turbine.
  • the hot working gases particularly stress that edge area the shovel that is the first to flow directly becomes.
  • the higher strength requirements on the hot gas inflow side is taken into account that the minimum wall thickness near a hot gas inflow side is larger than at the hot gas outflow side.
  • a material and mass-saving increase in the strength of the Foot is given that the blade root from between its longitudinal walls trained cross struts is reinforced.
  • the forces acting on one longitudinal wall of the cavity are through the cross struts to the other longitudinal wall of the Excavation and passed through both walls into the turbine disc, without endangering the stability of the excavation.
  • By further reducing the mass also occurs due to the reduced centrifugal load further relief of the foot.
  • the particularly high attacking forces in the middle area are intercepted by the cross struts of the cavity have the greatest height in the middle and to one decrease the sloping course of the excavation adjusted in height.
  • FIG. 1 shows a radial cross section through a foot 4 and a platform 2 and part of a blade profile 1 a turbine blade.
  • the foot 4 is in a holding recess 30 a turbine disk 3 pushed and by means of teeth 35 of the foot 4 and corresponding teeth 36 of the holding recess 30 held positively, as shown in Fig.2.
  • Foot 4, platform 2 and profile 1 are in one piece, connected shaped, preferably cast.
  • Juxtaposed Blade profiles 1 offer a hot gas flowing past Resistance and change its speed and direction, which causes the turbine disc 3 to rotate at a very high rate Speed is excited about a disk axis.
  • the one here Centrifugal forces must essentially come from the teeth 35 of the blade root 4 and the teeth 36 of the holding recess 30 can be caught.
  • Turbine blades are generally large parts of the turbine blade massively trained and therefore have a high Weight that puts a heavy load on the foot areas.
  • the foot 4 has a weight-reducing according to the invention Excavation 7 on. It is shaped like a vault and ends on Platform-side end 19 of the turbine blade blind below the top 21 of the platform 2. On a platform facing away from The end 7 of the foot 4, the cavity 7 is open.
  • the Foot 4 has one in the region of the end 31 facing away from the platform essentially constant length 32. The length 32 takes when approaching platform 2, first because of a molding 37 of the transition area 38 to something to then Take off platform 2 continuously.
  • the cavity 7 has lengths 13 of longitudinal walls 12 and depths 33.
  • the lengths 13 start from that facing away from the platform End 31 after a certain distance to the platform side End 19 of the foot 4 are in the transition area 38 in one arcuate shape shorter to the highest point with the Height 16 of the cavity 7, where the cavity 7 ends blindly. This end is preferably in the range or below Platform top 21 to ensure sufficient stability of the Ensure shovel.
  • the blade profile is in the platform area massive and possibly has a weight-saving Blade profile cavity in the upper, not shown Area of the blade profile at a distance from the platform. This avoids the strength of the blade in the Endanger the platform area.
  • the cavity 7 has none Connection to the blade profile cavity, since it is a internally uncooled turbine blade acts and therefore not Coolant transport through the foot is necessary.
  • the depth 33 decreases, as shown in Fig. 2, from the platform facing away End 31 of the foot 4 to the platform end 19 towards 5 in an area. Then the cavity 7 follows one Turning of the turbine blade in the transition area 38.
  • the depth 33 initially increases somewhat in the transition area 38 in order to then from approximately the middle of the transition region 38 to Platform 2 to decrease steadily. This is the greatest possible Area within foot 4 or respectively Transitional area 38 hollowed out for maximum weight reduction to achieve. It is especially taken into account that the walls 8, 12 sufficient wall thicknesses 14 for Ensuring the stability of the foot 4 even with strong ones attacking centrifugal forces. Due to the domed training the cavity 7 voltage peaks are avoided lead to a reduction in strength.
  • the hollow 7 can be produced by a casting core with lost shape, that in the foot area of the shovel is used before casting and over the platform facing away End 31 of the foot 4 protrudes, whereby a place is turned away forms open cavity.
  • the casting core ends there Blind core formed. After the casting, the core is destroyed and removed from the cavity 7 because it is due to the not as a whole as the width decreases towards the opening can be removed.
  • Cross struts 28 are attached within the cavity 7, which run between the longitudinal walls 12. Through the cross struts 28 becomes the cavity 7 against attacking forces, which act on the walls 8, 12 supported.
  • the cross struts 28 are rounded, to avoid voltage peaks. They are essentially parallel to each other at intervals 34 in the direction a longitudinal axis 39 of the turbine blade. you take almost the entire area between the two opposite Longitudinal walls 12 a.
  • Fig.2 shows a radial cross section in an almost right Angle to the first longitudinal section of Figure 1 along the Section line II-II.
  • the foot 4 bulging teeth 35, the correspondingly shaped teeth 36 the holding recess 30 of the turbine disc 3, in which the foot 4 is used, reach behind and thus a secure form fit to prevent the turbine blade from slipping out Ensure centrifugal load.
  • From the platform away End 31 to platform end 19 of the foot 4 takes one of the teeth 35 and intervening concavities formed average width 6 'of the foot 4 to.
  • This middle one Width 6 ' follows the depth 33 of the transverse region of the cavity 7 while maintaining minimum wall thicknesses that ensure stability of the walls 12.
  • the one adjoining the foot 4 Transition area 38 is curved like a lens, as in cross section is clear from Fig.4. Accordingly, the excavation is 7 shifted relative to their training in the foot 4 so that sufficient wall thicknesses 14 on both sides of the cavity 7 are guaranteed.
  • FIG. 3 shows a cross section through the foot 4 along the Section line III-III from Fig.1 and Fig.2.
  • the width 6 the cross section through the foot is quite large since the cut by an upper tooth 35 of the foot 4, that is in the area the greatest width 6 of the foot 4, runs.
  • the excavation 7 consists in this section of several chambers 29, the Cross struts 28 partitions of the chambers 29 correspond.
  • the Chambers 29 point from the two transverse walls 8 of the foot 4 starting from an increasing depth 33 that has its greatest extent at the central cross strut 28 in order to then again approaching the other transverse wall 8 of the foot 4 decrease.
  • the boundaries of the chambers 29 are to be avoided rounded on all sides by voltage peaks.
  • Fig.4 shows a section along the section line IV-IV of the 1 and 2 through the transition region 38.
  • the cavity 7 has only five chambers in this area 29 or four cross struts 28, since the Cut above the nearest hot gas upstream Cross strut is done.
  • the wall thickness 14 of the wall 8 is in the region of the hot gas inflow side 17 larger than in the opposite area of the hot gas outflow side 18.
  • FIG. 5 shows a section through the narrowest Area of the foot 4 along the section line V-V of Fig.1 or according to Fig. 2.
  • the chambers 29 of the cavity 7 also have one of the transverse wall 8 starting increasing cross-sectional depth 33, but the change in cross-section is not as great as in Fig. 3.
  • the maximum is again in the area of the central cross strut 28th

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La présente invention concerne une aube de turbine comprenant un profilé d'aube à refroidissement interne (1) qui s'étend à partir d'une plate-forme d'aube (2) reliée à une emplanture d'aube (4) s'accouplant avec le disque de la turbine (3), la section radiale de ladite emplanture présentant une zone (5) de largeur croissante (6') en direction de la plate-forme d'aube (2). L'invention a pour objet la réalisation de l'aube de turbine permettant un allongement du profilé d'aube. Pour cela, l'emplanture d'aube (4) présente un évidement (7) ouvert en direction de la plate-forme qui se termine de façon invisible du côté plate-forme et qui s'élargit du point de vue de la section dans la zone (5) de largeur croissante (6') de l'emplanture d'aube (4).

Claims (11)

  1. Aube mobile de turbine, ayant un profil (1) d'aube sans refroidissement intérieur qui s'étend à partir d'une plate-forme (2) d'aube à laquelle se raccorde une emplanture (4) d'aube, qui s'engage dans un disque (3) de turbine et dont la section radiale possède une région (5) de largeur (6') croissante en direction de la plate-forme (2) d'aube, l'emplanture (4) d'aube possédant une cavité (7) ouverte à son extrémité opposée à la plate-forme et à terminaison aveugle côté plate-forme, caractérisée en ce que la section de la cavité (7) est élargie dans la région de largeur (6') croissante de l'emplanture (4) d'aube.
  2. Aube mobile de turbine suivant la revendication 1, caractérisée en ce que la cavité (7) se termine dans une région (38) de transition entre l'emplanture (4) d'aube et en dessous d'une face (21) supérieure de la plate-forme (2).
  3. Aube mobile de turbine suivant la revendication 1 ou 2, caractérisée en ce que la cavité (7) est délimitée par des parois (8, 12) majoritairement arrondies et se termine sous une forme voûtée en dessous de la face (21) supérieure de la plate-forme.
  4. Aube mobile de turbine suivant l'une des revendications 1 à 3, caractérisée en ce que des parois (12) longitudinales de la cavité (7) s'étendent sur quasiment toute la longueur (32) de l'emplanture (4) d'aube et des parois (8) transversales sur quasiment toute la largeur (6) de l'emplanture (4) d'aube, les parois (8, 12) de la cavité (7) garantissant une stabilité suffisante lors de l'action d'une force centrifuge.
  5. Aube mobile de turbine suivant l'une des revendications 1 à 4, caractérisée en ce que la cavité (7) possède sa plus grande hauteur (16) dans la région (15) centrale et décroít en direction des parois (8) transversales et des parois (12) longitudinales.
  6. Aube mobile de turbine suivant l'une des revendications 1 à 5, caractérisée en ce que des régions des parois (12) longitudinales de la cavité (7) s'élargissent continuellement en se rapprochant de l'extrémité (19) côté plate-forme, tout en respectant une épaisseur (14) minimale de paroi sur les parois (8) transversales de la cavité (7).
  7. Aube mobile de turbine suivant l'une des revendications 1 à 6, caractérisée en ce que l'épaisseur (14) minimale de paroi est plus grande au voisinage d'un côté (17) de flux incident de gaz chaud que sur le côté (18) de flux sortant de gaz chaud.
  8. Aube mobile de turbine suivant l'une des revendications 1 à 7, caractérisée en ce que l'emplanture (4) d'aube est renforcée par des entretoises (28) transversales formées entre ses parois (12) longitudinales.
  9. Aube mobile de turbine suivant l'une des revendications 1 à 8, caractérisée en ce que les entretoises (28) transversales se trouvent à distance (40, 41) des parois (12) de la cavité (7) côté plate-forme et/ou de l'extrémité (31) de l'emplanture (4) d'aube qui est opposée à la plate-forme.
  10. Aube mobile de turbine suivant l'une des revendications 1 à 9, caractérisée en ce que les positions et formes des entretoises (28) transversales sont adaptées à une allure de lignes de force qui est produite par les forces centrifuges agissant sur le profil (1) d'aube.
  11. Aube mobile de turbine suivant l'une des revendications 1 à 10, caractérisée en ce que les entretoises (28) transversales de la cavité (7) possèdent leur plus grande hauteur (20) dans la région (15) centrale et décroissent en hauteur (20) d'une manière adaptée à une allure décroissante de la cavité (7).
EP01913779A 2000-02-25 2001-02-01 Aube de turbine Expired - Lifetime EP1257732B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01913779A EP1257732B1 (fr) 2000-02-25 2001-02-01 Aube de turbine

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP00104002 2000-02-25
EP00104002A EP1128023A1 (fr) 2000-02-25 2000-02-25 Aube rotorique de turbine
PCT/EP2001/001063 WO2001063098A1 (fr) 2000-02-25 2001-02-01 Aube de turbine
EP01913779A EP1257732B1 (fr) 2000-02-25 2001-02-01 Aube de turbine

Publications (2)

Publication Number Publication Date
EP1257732A1 EP1257732A1 (fr) 2002-11-20
EP1257732B1 true EP1257732B1 (fr) 2004-10-06

Family

ID=8167964

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00104002A Withdrawn EP1128023A1 (fr) 2000-02-25 2000-02-25 Aube rotorique de turbine
EP01913779A Expired - Lifetime EP1257732B1 (fr) 2000-02-25 2001-02-01 Aube de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP00104002A Withdrawn EP1128023A1 (fr) 2000-02-25 2000-02-25 Aube rotorique de turbine

Country Status (6)

Country Link
US (1) US6755986B2 (fr)
EP (2) EP1128023A1 (fr)
JP (1) JP4698917B2 (fr)
CN (1) CN1313705C (fr)
DE (1) DE50103981D1 (fr)
WO (1) WO2001063098A1 (fr)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6932570B2 (en) * 2002-05-23 2005-08-23 General Electric Company Methods and apparatus for extending gas turbine engine airfoils useful life
US20070006865A1 (en) * 2003-02-21 2007-01-11 Wiker John H Self-cleaning oven
EP1614861A1 (fr) * 2004-07-09 2006-01-11 Siemens Aktiengesellschaft Roue de turbine comprenant des aubes de turbine avec turbulateurs sur la surface radiale interne de la plate-forme
GB0613441D0 (en) * 2006-07-06 2006-08-16 Rolls Royce Plc Blades
US8157527B2 (en) * 2008-07-03 2012-04-17 United Technologies Corporation Airfoil with tapered radial cooling passage
CN101586475B (zh) * 2008-12-23 2011-04-27 张金山 航空发动机涡轮转子叶片的集束分流式热防护
DE102010004854A1 (de) 2010-01-16 2011-07-21 MTU Aero Engines GmbH, 80995 Laufschaufel für eine Strömungsmaschine und Strömungsmaschine
EP2369134A1 (fr) * 2010-03-12 2011-09-28 Industria de Turbo Propulsores S.A. Aude de turbine avec des cavités pour la réduction du poid et des vibrations
EP2385215A1 (fr) 2010-05-05 2011-11-09 Alstom Technology Ltd Ailette de plateau légère pour pale de rotor
US9109456B2 (en) * 2011-10-26 2015-08-18 General Electric Company System for coupling a segment to a rotor of a turbomachine
EP2644834A1 (fr) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Aube de turbine ainsi que son procédé de fabrication correspondant
CN107667205B (zh) * 2015-06-02 2019-11-01 西门子公司 可用于燃气涡轮发动机中的涡轮翼型件的附接系统
CN107143381A (zh) * 2017-06-06 2017-09-08 哈尔滨汽轮机厂有限责任公司 一种能够降低应力的燃气轮机透平第一级动叶片
CN112177678A (zh) * 2020-09-25 2021-01-05 厦门大学 带双内环空腔的涡轮盘结构及其设计方法

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3695778A (en) * 1970-09-18 1972-10-03 Trw Inc Turbine blade
US3936216A (en) * 1974-03-21 1976-02-03 United Technologies Corporation Blade sealing and retaining means
CH580750A5 (fr) * 1974-07-17 1976-10-15 Bbc Sulzer Turbomaschinen
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
JPH03902A (ja) * 1989-02-13 1991-01-07 Toshiba Corp タービン動翼
JPH0447101A (ja) * 1990-06-15 1992-02-17 Toshiba Corp ターボ機械の動翼
FR2695163B1 (fr) * 1992-09-02 1994-10-28 Snecma Aube creuse pour turbomachine et son procédé de fabrication.
JPH1122404A (ja) * 1997-07-03 1999-01-26 Hitachi Ltd ガスタービン及びその動翼
US5947688A (en) * 1997-12-22 1999-09-07 General Electric Company Frequency tuned hybrid blade

Also Published As

Publication number Publication date
EP1257732A1 (fr) 2002-11-20
CN1313705C (zh) 2007-05-02
JP2003524104A (ja) 2003-08-12
EP1128023A1 (fr) 2001-08-29
DE50103981D1 (de) 2004-11-11
JP4698917B2 (ja) 2011-06-08
US6755986B2 (en) 2004-06-29
CN1406312A (zh) 2003-03-26
WO2001063098A1 (fr) 2001-08-30
US20030021686A1 (en) 2003-01-30

Similar Documents

Publication Publication Date Title
EP1257732B1 (fr) Aube de turbine
DE3045224C2 (fr)
DE2854629C2 (fr)
DE2307967C2 (de) Plattform für eine Verdichterschaufel
DE602004010965T2 (de) Hohle Rotorschaufel eines Gasturbinentriebwerks
DE4306689A1 (de) Radialverdichter mit einem strömungsstabilisierenden Gehäuse
EP0947693A2 (fr) Profil de pale pour éolienne
DE19634238A1 (de) Kühlbare Schaufel
EP2696031A1 (fr) Aube pour une turbomachine et turbomachine correspondante
EP2297430A1 (fr) Turbine axiale pour turbine à gaz, à faible jeu entre les aubes et la carcasse
DE102005014017A1 (de) Turbine und Turbinenschaufel
EP3705727A1 (fr) Roue d'un ventilateur axial
WO2009106462A1 (fr) Aube de turbine destinée à une turbine à gaz fixe
EP3056677B1 (fr) Aube et turbomachine
DE60113954T2 (de) Aufhängungsteil für ein Turbinentriebwerk
EP3289182A1 (fr) Aube de turbine
EP2133574A2 (fr) Grille de protection spatiale pour ventilateurs axiaux et procédé de fabrication de la grille de protection
DE202005013025U1 (de) Fußgängerbrücke für hochwassergefährdete Bereiche
CH647301A5 (de) Laeuferrad einer turbine mit daran befestigten laufschaufeln.
WO2001071166A1 (fr) Aube mobile de turbine
DE19801849B4 (de) Laufrad für eine hydraulische Strömungsmaschine nach Francis-Bauart
DE2601568A1 (de) Turbinenschaufelrad
EP2679803A1 (fr) Pale de rotor d'éolienne dotée d'un bord de fuite à profil épais
DE202019101209U1 (de) Lüfterrad eines Axialventilators
DE102017212310A1 (de) Schaufel, Schaufelkranz, Schaufelkranzsegment und Strömungsmaschine

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: 20020719

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

RIN1 Information on inventor provided before grant (corrected)

Inventor name: ANDING, DIRK

Inventor name: STRA BERGER, MICHAEL

Inventor name: TIEMANN, PETER

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RBV Designated contracting states (corrected)

Designated state(s): CH DE FR GB IT LI

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): CH DE FR GB IT LI

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

RIN1 Information on inventor provided before grant (corrected)

Inventor name: TIEMANN, PETER

Inventor name: STRASSBERGER, MICHAEL

Inventor name: ANDING, DIRK

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

Free format text: GERMAN

REF Corresponds to:

Ref document number: 50103981

Country of ref document: DE

Date of ref document: 20041111

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20050128

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: 20050228

Ref country code: LI

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

Effective date: 20050228

LTIE Lt: invalidation of european patent or patent extension

Effective date: 20041006

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

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

ET Fr: translation filed
26N No opposition filed

Effective date: 20050707

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: IT

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

Effective date: 20100201

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 16

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

Ref country code: IT

Payment date: 20160225

Year of fee payment: 16

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

Ref country code: GB

Payment date: 20160208

Year of fee payment: 16

Ref country code: FR

Payment date: 20160212

Year of fee payment: 16

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

Ref country code: DE

Payment date: 20160420

Year of fee payment: 16

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 50103981

Country of ref document: DE

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

Effective date: 20170201

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20171031

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: 20170228

Ref country code: DE

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

Effective date: 20170901

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: 20170201

Ref country code: IT

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

Effective date: 20170201