EP0464366A1 - Procédé de fabrication d'une pièce en alliage à base d'aluminiure de titane contenant un matériau de dopage - Google Patents

Procédé de fabrication d'une pièce en alliage à base d'aluminiure de titane contenant un matériau de dopage Download PDF

Info

Publication number
EP0464366A1
EP0464366A1 EP91108605A EP91108605A EP0464366A1 EP 0464366 A1 EP0464366 A1 EP 0464366A1 EP 91108605 A EP91108605 A EP 91108605A EP 91108605 A EP91108605 A EP 91108605A EP 0464366 A1 EP0464366 A1 EP 0464366A1
Authority
EP
European Patent Office
Prior art keywords
workpiece
temperature
cast body
cooling
casting
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
EP91108605A
Other languages
German (de)
English (en)
Other versions
EP0464366B1 (fr
Inventor
Mohamed Dr. Nazmy
Markus Staubli
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0464366A1 publication Critical patent/EP0464366A1/fr
Application granted granted Critical
Publication of EP0464366B1 publication Critical patent/EP0464366B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium

Definitions

  • the invention is based on a method for producing a workpiece from a dopant-containing alloy based on titanium aluminide.
  • High-temperature alloys for thermal machines based on the intermetallic compound TiAI which are suitable for the production of cast and forged components and which can supplement and partially replace the conventional nickel-based superalloys.
  • the invention relates to the melting and casting of alloys doped on the intermetallic compound TiAI with further additives and to the thermal and thermomechanical further processing to usable workpieces with good mechanical properties.
  • Intermetallic compounds of titanium with aluminum have some interesting properties which make them appear attractive as construction materials in the medium and higher temperature range. Among other things, this includes their low density compared to superalloys, which only reaches about 1/2 of the value for Ni superalloys. Their technical usability in the present form, however, stands in the way of their brittleness. The former can be improved by additives, whereby higher strength values are also achieved. As possible and in part already introduced intermetallic compounds, nickel aluminides, nickel silicides and titanium aluminides are known as construction materials.
  • the shape of the intermetallic phases based on titanium aluminides presents a certain problem. Because of the high affinity of the elements involved for oxygen, in particular that of titanium, the production of molded parts by casting is difficult. Poor mold filling capacity, porosity and cavities are the consequences. In addition, the properties of the cast structure cannot be improved to the desired extent by subsequent heat treatments. On the other hand, classic hot forming is opposed by the comparatively poor ductility in the lower temperature range.
  • the invention is based on the object of specifying a method for producing a workpiece from a dopant-containing alloy based on titanium aluminide, which leads to a material having high oxidation and corrosion resistance, high heat resistance and sufficient ductility.
  • the yield point of the material to be forged was around 260 MPa at 1100 ° C.
  • the linear rate of deformation (punch speed of the forging press) v was 0.1 mm / s at the start of the forging process.
  • the pressing forces required for the upsetting were of medium size. In the present case, they were approximately 750 kN, which corresponded to an initial pressure of approximately 300 MPa.
  • the forging die consisted of the Mo alloy containing small amounts of Ti and Zr.
  • the flow limit of the workpiece was approx. 200 MPa at 1150 ° C.
  • the workpiece had a Vickers hardness HV of an average of 336 kg / mm 2 .
  • the melt was poured into ingots approximately 55 mm in diameter and 65 mm high.
  • the ingots were then annealed in an argon atmosphere for 10 hours at a temperature of 1100 ° C., cooled and mechanically processed to remove the casting skin.
  • the alloy was homogenized by the annealing. Depending on the alloy composition, a suitable homogenization was achieved at temperatures between 1000 and 1150 ° C and annealing times between one and thirty hours. Then the cylindrical workpieces were encapsulated, hot isostatically pressed and forged at a temperature of 1150 ° C.
  • the deformation ⁇ was 0.69 (height decrease 50%), the observed yield point was approx. 380 MPa.
  • the rate of deformation (punch speed) was 0.1 mm / s.
  • the forging process was carried out essentially isothermally at a temperature of 1120 ° C., a flow limit of 250 MPa being observed on average.
  • the rate of deformation (punch speed) at the start of each forging operation was approximately 0.1 to 0.2 mm / s.
  • the base part was compressed by a further 20% decrease in height in the longitudinal axis of the airfoil.
  • the workpiece was then cooled to below 500 ° C. at a rate of 300 ° C./h and, after cooling, tempered at 800 ° C. for 1 hour. With this, the almost final shape of the turbine blade was achieved, apart from milling the grooves on the fir tree base.
  • a prismatic ingot with a rectangular cross-section was cast with a thickness of approx. 40 mm, 90 mm in width and 250 mm in length.
  • the cast skin was removed by planing and the ingot was encapsulated in soft steel and hot-isostatically pressed at 1260 ° C. for 3 h under a pressure of 120 MPa.
  • the first forming was a compression (isothermal forging) in the longer transverse direction (upright) of approx. 33%, so that the ingot assumed an approximately square cross-section with a side length of approx. 60 mm.
  • This operation was carried out at a temperature of 1150 ° C under an argon atmosphere. Then the ingot was hot rolled in the other transverse direction at the same temperature, taking approximately the original rectangular cross-sectional shape but with reduced dimensions. After intermediate annealing at 1200 ° C for 1 h under an argon atmosphere, the ingot was deformed by hot rolling (40% reduction in cross-section) at 1050 ° C into a rod with a rectangular profile. During the operations, a hot stretch limit of approximately 240 MPa was observed at 1150 ° C. The structure of the finished rod was fine-grained and homogeneous. The Vickers hardness HV was increased by approx. 25% compared to the as-cast state.
  • a body was cast as a stepped cylinder.
  • the total height was 220 mm, the height of the smaller diameter 120 mm, that of the larger 100 mm, the diameters 60 mm and 100 mm.
  • the cast blank was annealed at 1050 ° C, overturned (removal of the cast skin) and encapsulated in an all-round sleeve made of soft steel and hot isostatically pressed according to the previous examples. Then the block was first compressed in the longitudinal direction with a 30% decrease in height at 1150 ° C. and pressed several times in the transverse directions in such a way that an oval cross section was produced in the leaf section. Intermediate annealing was carried out at 1200 ° C.
  • the pre-forged blank with an oval cross-section in the sheet section was placed in the die of a forging press and in several stages up to Deformed reaching the above leaf profile.
  • the forging process was carried out essentially isothermally at a temperature of 1150 ° C. A flow limit of 200 MPa on average was observed at this temperature.
  • the rate of deformation (punch speed) at the start of the drop forging operations was approximately 0.2 mm / s.
  • the remaining process steps were analogous to Example 4.
  • the tempering was carried out at a temperature of 750 ° C. for 2 hours.
  • the structure of the finished turbine blade was fine-grained and homogeneous.
  • the Vickers hardness HV was 15% higher than the as-cast state.
  • B generally has a strong toughness-increasing effect in combination with other strength-increasing elements.
  • the loss of ductility caused by alloying W could be practically compensated for by adding only 0.5 at.% B. Additions higher than 1 at.% B are not necessary.
  • the area of application of the modified titanium aluminides advantageously extends to temperatures between 600 and 1000 C.
  • the invention is not restricted to the exemplary embodiments.
  • the workpiece is essentially forged isothermally, and after the isothermal forging it has the shape of a gas turbine blade.
  • the workpiece is essentially forged isothermally and, after the isothermal forging, is subjected to a further hot-forming process with up to 40% reduction in cross-section, the latter advantageously consisting of hot rolling.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Forging (AREA)
  • Press Drives And Press Lines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP91108605A 1990-07-04 1991-05-27 Procédé de fabrication d'une pièce en alliage à base d'aluminiure de titane contenant un matériau de dopage Expired - Lifetime EP0464366B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP90112734 1990-07-04
EP90112734 1990-07-04

Publications (2)

Publication Number Publication Date
EP0464366A1 true EP0464366A1 (fr) 1992-01-08
EP0464366B1 EP0464366B1 (fr) 1994-11-30

Family

ID=8204173

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91108605A Expired - Lifetime EP0464366B1 (fr) 1990-07-04 1991-05-27 Procédé de fabrication d'une pièce en alliage à base d'aluminiure de titane contenant un matériau de dopage

Country Status (4)

Country Link
US (1) US5190603A (fr)
EP (1) EP0464366B1 (fr)
JP (1) JPH04232234A (fr)
DE (1) DE59103639D1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0549181A1 (fr) * 1991-12-23 1993-06-30 General Electric Company Aluminiure de titane du type gamma
EP0924308A1 (fr) * 1997-12-18 1999-06-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Alliages intermétalliques à base de titane du type Ti2A1Nb à haute limite d'élasticité et forte résistance au fluage
AT509768B1 (de) * 2010-05-12 2012-04-15 Boehler Schmiedetechnik Gmbh & Co Kg Verfahren zur herstellung eines bauteiles und bauteile aus einer titan-aluminium-basislegierung
CN115608967A (zh) * 2022-10-25 2023-01-17 共享铸钢有限公司 一种蜗壳防开裂的生产方法

Families Citing this family (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5284620A (en) * 1990-12-11 1994-02-08 Howmet Corporation Investment casting a titanium aluminide article having net or near-net shape
JP2546551B2 (ja) * 1991-01-31 1996-10-23 新日本製鐵株式会社 γ及びβ二相ＴｉＡｌ基金属間化合物合金及びその製造方法
DE59106047D1 (de) * 1991-05-13 1995-08-24 Asea Brown Boveri Verfahren zur Herstellung einer Turbinenschaufel.
US5370839A (en) * 1991-07-05 1994-12-06 Nippon Steel Corporation Tial-based intermetallic compound alloys having superplasticity
DE4219469A1 (de) * 1992-06-13 1993-12-16 Asea Brown Boveri Hohen Temperaturen aussetzbares Bauteil, insbesondere Turbinenschaufel, und Verfahren zur Herstellung dieses Bauteils
DE4219470A1 (de) * 1992-06-13 1993-12-16 Asea Brown Boveri Bauteil für hohe Temperaturen, insbesondere Turbinenschaufel, und Verfahren zur Herstellung dieses Bauteils
JPH06116692A (ja) * 1992-10-05 1994-04-26 Honda Motor Co Ltd 高温強度の優れたＴｉＡｌ系金属間化合物およびその製造方法
DE4318424C2 (de) * 1993-06-03 1997-04-24 Max Planck Inst Eisenforschung Verfahren zur Herstellung von Formkörpern aus Legierungen auf Titan-Aluminium-Basis
US5424027A (en) * 1993-12-06 1995-06-13 The United States Of America As Represented By The Secretary Of The Air Force Method to produce hot-worked gamma titanium aluminide articles
US5906692A (en) * 1993-12-28 1999-05-25 Alliedsignal Inc. Process for producing forged α-2 based titanium aluminides having fine grained and orthorhombic transformed microstructure and articles made therefrom
US5417781A (en) * 1994-06-14 1995-05-23 The United States Of America As Represented By The Secretary Of The Air Force Method to produce gamma titanium aluminide articles having improved properties
US5609698A (en) * 1995-01-23 1997-03-11 General Electric Company Processing of gamma titanium-aluminide alloy using a heat treatment prior to deformation processing
DE10062310C2 (de) * 2000-12-14 2002-11-07 Geesthacht Gkss Forschung Verfahren zur Behandlung metallischer Werkstoffe
US6767420B2 (en) * 2002-12-20 2004-07-27 Kimberly-Clark Worldwide, Inc. Ultrasonic horn with isotropic breathing characteristics
US6758925B1 (en) * 2002-12-20 2004-07-06 Kimberly-Clark Worldwide, Inc. Acoustical energy transfer component
US6910859B2 (en) * 2003-03-12 2005-06-28 Pcc Structurals, Inc. Double-walled annular articles and apparatus and method for sizing the same
DE502004006993D1 (de) 2004-02-26 2008-06-12 Geesthacht Gkss Forschung Verfahren zur Herstellung von Bauteilen oder Halbzeugen, die intermetallische Titanaluminid-Legierungen enthalten, sowie mittels des Verfahrens herstellbare Bauteile
US7059289B2 (en) * 2004-08-06 2006-06-13 Lanxess Corporation Air intake manifold with composite flange and method
CN1954937B (zh) * 2005-10-25 2010-05-26 上海重型机器厂有限公司 一种超临界机组用含钒汽轮机缸体的铸造方法
GB0719873D0 (en) * 2007-10-12 2007-11-21 Rolls Royce Plc Shape correcting components
AT508323B1 (de) * 2009-06-05 2012-04-15 Boehler Schmiedetechnik Gmbh & Co Kg Verfahren zur herstellung eines schmiedestückes aus einer gamma-titan-aluminium-basislegierung
DE102010026084A1 (de) * 2010-07-05 2012-01-05 Mtu Aero Engines Gmbh Verfahren und Vorrichtung zum Auftragen von Materialschichten auf einem Werkstück aus TiAI
US8876992B2 (en) * 2010-08-30 2014-11-04 United Technologies Corporation Process and system for fabricating gamma TiAl turbine engine components
US8858697B2 (en) 2011-10-28 2014-10-14 General Electric Company Mold compositions
US9011205B2 (en) 2012-02-15 2015-04-21 General Electric Company Titanium aluminide article with improved surface finish
US8932518B2 (en) 2012-02-29 2015-01-13 General Electric Company Mold and facecoat compositions
US8906292B2 (en) 2012-07-27 2014-12-09 General Electric Company Crucible and facecoat compositions
US8708033B2 (en) 2012-08-29 2014-04-29 General Electric Company Calcium titanate containing mold compositions and methods for casting titanium and titanium aluminide alloys
US8992824B2 (en) 2012-12-04 2015-03-31 General Electric Company Crucible and extrinsic facecoat compositions
US9592548B2 (en) 2013-01-29 2017-03-14 General Electric Company Calcium hexaluminate-containing mold and facecoat compositions and methods for casting titanium and titanium aluminide alloys
WO2014149292A1 (fr) * 2013-03-15 2014-09-25 United Technologies Corporation Structure d'échappement de turbine d'aluminure de titane
US9192983B2 (en) 2013-11-26 2015-11-24 General Electric Company Silicon carbide-containing mold and facecoat compositions and methods for casting titanium and titanium aluminide alloys
US9511417B2 (en) 2013-11-26 2016-12-06 General Electric Company Silicon carbide-containing mold and facecoat compositions and methods for casting titanium and titanium aluminide alloys
JP6344034B2 (ja) * 2014-04-22 2018-06-20 株式会社Ihi ＴｉＡｌ合金の鋳造方法
US10391547B2 (en) 2014-06-04 2019-08-27 General Electric Company Casting mold of grading with silicon carbide
CN104148562B (zh) * 2014-06-30 2017-01-11 贵州安大航空锻造有限责任公司 Ti2AlNb基合金铸锭的开坯方法
US11306595B2 (en) 2018-09-14 2022-04-19 Raytheon Technologies Corporation Wrought root blade manufacture methods

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0275391A1 (fr) * 1986-11-12 1988-07-27 Kawasaki Jukogyo Kabushiki Kaisha Alliage titane-aluminium
US4842819A (en) * 1987-12-28 1989-06-27 General Electric Company Chromium-modified titanium aluminum alloys and method of preparation
EP0349734A1 (fr) * 1988-05-13 1990-01-10 Nippon Steel Corporation Composé intermétallique titane-aluminium et procédé pour sa fabrication

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2586023B2 (ja) * 1987-01-08 1997-02-26 日本鋼管株式会社 ＴｉＡ１基耐熱合金の製造方法
US4857268A (en) * 1987-12-28 1989-08-15 General Electric Company Method of making vanadium-modified titanium aluminum alloys
US4842817A (en) * 1987-12-28 1989-06-27 General Electric Company Tantalum-modified titanium aluminum alloys and method of preparation
US4842820A (en) * 1987-12-28 1989-06-27 General Electric Company Boron-modified titanium aluminum alloys and method of preparation
US4836983A (en) * 1987-12-28 1989-06-06 General Electric Company Silicon-modified titanium aluminum alloys and method of preparation
JP2865690B2 (ja) * 1989-02-17 1999-03-08 株式会社日立製作所 嵌合挿入装置
US5076858A (en) * 1989-05-22 1991-12-31 General Electric Company Method of processing titanium aluminum alloys modified by chromium and niobium
US5028491A (en) * 1989-07-03 1991-07-02 General Electric Company Gamma titanium aluminum alloys modified by chromium and tantalum and method of preparation
US5256202A (en) * 1989-12-25 1993-10-26 Nippon Steel Corporation Ti-A1 intermetallic compound sheet and method of producing same
US5082506A (en) * 1990-09-26 1992-01-21 General Electric Company Process of forming niobium and boron containing titanium aluminide

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0275391A1 (fr) * 1986-11-12 1988-07-27 Kawasaki Jukogyo Kabushiki Kaisha Alliage titane-aluminium
US4842819A (en) * 1987-12-28 1989-06-27 General Electric Company Chromium-modified titanium aluminum alloys and method of preparation
EP0349734A1 (fr) * 1988-05-13 1990-01-10 Nippon Steel Corporation Composé intermétallique titane-aluminium et procédé pour sa fabrication

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0549181A1 (fr) * 1991-12-23 1993-06-30 General Electric Company Aluminiure de titane du type gamma
EP0924308A1 (fr) * 1997-12-18 1999-06-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Alliages intermétalliques à base de titane du type Ti2A1Nb à haute limite d'élasticité et forte résistance au fluage
FR2772790A1 (fr) * 1997-12-18 1999-06-25 Snecma ALLIAGES INTERMETALLIQUES A BASE DE TITANE DU TYPE Ti2AlNb A HAUTE LIMITE D'ELASTICITE ET FORTE RESISTANCE AU FLUAGE
AT509768B1 (de) * 2010-05-12 2012-04-15 Boehler Schmiedetechnik Gmbh & Co Kg Verfahren zur herstellung eines bauteiles und bauteile aus einer titan-aluminium-basislegierung
US8864918B2 (en) 2010-05-12 2014-10-21 Boehler Schmiedetechnik Gmbh & Co. Kg Method for producing a component and components of a titanium-aluminum base alloy
CN115608967A (zh) * 2022-10-25 2023-01-17 共享铸钢有限公司 一种蜗壳防开裂的生产方法

Also Published As

Publication number Publication date
EP0464366B1 (fr) 1994-11-30
JPH04232234A (ja) 1992-08-20
DE59103639D1 (de) 1995-01-12
US5190603A (en) 1993-03-02

Similar Documents

Publication Publication Date Title
EP0464366B1 (fr) Procédé de fabrication d'une pièce en alliage à base d'aluminiure de titane contenant un matériau de dopage
EP0513407B1 (fr) Procédé de fabrication d' une aube de turbine
DE69508841T2 (de) Kornfeinungs- und Optimisierungsverfahren der mechanischen Eigenschaften für thermomechanische Behandlung von gegossenen Titanaluminiden unterhalb des Gamma-Bereiches
EP2386663B1 (fr) Procédé de fabrication d'un composant et composants constitués d'un alliage à base d'aluminium-titane
EP0455005B1 (fr) Alliage réfractaire pour organes de machine, basé sur l'aluminiure de titane dopé
DE3445767C2 (fr)
DE2303802C3 (de) Verfahren zum Erhöhen der Festigkeit und Zähigkeit von dispersionsverfestigten Knetlegierungen
EP3372700B1 (fr) Procédé de fabrication d'éléments structuraux en tial forgés
DE19756354B4 (de) Schaufel und Verfahren zur Herstellung der Schaufel
EP0035601B1 (fr) Procédé de fabrication d'un alliage-mémoire
DE60003802T2 (de) Titanbasislegierung
EP0035602B1 (fr) Procédé de préparation par métallurgie des poudres d'un alliage-mémoire à base de cuivre, de zinc et d'aluminium
DE112013007406B4 (de) Verfahren zum Herstellen von Bauteilen aus einer Aluminiumlegierung
DE2543893C2 (de) Verfahren zur Herstellung eines warmverformten Produktes aus Titan bzw. einer Titanlegierung
EP0396185B1 (fr) Procédé pour la préparation d'outils semi-finis résistant au fluage en métal réfractaire
AT5199U1 (de) Formteil aus einem intermetallischen gamma-ti-al-werkstoff
DE3113733C2 (de) Verfahren zur Rückgewinnung von hochwertigen Werkstoffen
EP0545145B1 (fr) Fabrication de pièces poreuses à base de cuivre comme un produit semi-fini pour un traitement d'usinage
EP0356718A2 (fr) Procédé pour former par extrusion et modification des propriétés mécaniques des produits semi finis en alliages à partir de poudres métalliques qui ont une résistance augmentée à la chaleur
DE69604747T2 (de) Hochfeste Aluminiumlegierung mit guter Prestempelextrudierbarkeit
EP1851350A1 (fr) Procede de moulage d'un alliage de titane
EP0035070A1 (fr) Alliage-mémoire à base d'une solution solide riche en cuivre ou en nickel
DE4201065A1 (de) Verfahren zur verbesserung der biegewechselfestigkeit von halbzeug aus kupferlegierungen
EP1129803B1 (fr) Matériau préparé par métallurgie des poudres avec isotropie améliorée des propriétés mécaniques
DE3727360A1 (de) Verfahren zur herstellung eines werkstuecks aus einer korrosions- und oxydationsbestaendigen ni/al/si/b-legierung

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

AK Designated contracting states

Kind code of ref document: A1

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

17P Request for examination filed

Effective date: 19920706

17Q First examination report despatched

Effective date: 19940223

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 SE

REF Corresponds to:

Ref document number: 59103639

Country of ref document: DE

Date of ref document: 19950112

ITF It: translation for a ep patent filed
ET Fr: translation filed
GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19950206

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 19970423

Year of fee payment: 7

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

Ref country code: CH

Payment date: 19970526

Year of fee payment: 7

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

Ref country code: SE

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

Effective date: 19980528

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

Ref country code: LI

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

Effective date: 19980531

Ref country code: CH

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

Effective date: 19980531

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

EUG Se: european patent has lapsed

Ref document number: 91108605.6

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

Ref country code: GB

Payment date: 19990413

Year of fee payment: 9

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

Ref country code: FR

Payment date: 19990419

Year of fee payment: 9

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

Ref country code: DE

Payment date: 19990420

Year of fee payment: 9

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: 20000527

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

Effective date: 20000527

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: 20010131

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: 20010301

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

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;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20050527