EP0824981B1 - Verfahren zur Herstellung einer hohlen Turbinschaufel und Anlage zum laufenden Warmverwinden - Google Patents

Verfahren zur Herstellung einer hohlen Turbinschaufel und Anlage zum laufenden Warmverwinden Download PDF

Info

Publication number
EP0824981B1
EP0824981B1 EP97401954A EP97401954A EP0824981B1 EP 0824981 B1 EP0824981 B1 EP 0824981B1 EP 97401954 A EP97401954 A EP 97401954A EP 97401954 A EP97401954 A EP 97401954A EP 0824981 B1 EP0824981 B1 EP 0824981B1
Authority
EP
European Patent Office
Prior art keywords
blade
manufacturing
hollow
twisting
twist
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
EP97401954A
Other languages
English (en)
French (fr)
Other versions
EP0824981A1 (de
Inventor
Mathieu Philippe Albert Bichon
Alain Georges Henri Lorieux
Bernard Armand René Costeplane
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.)
Safran Aircraft Engines SAS
Robert Creuzet Ets
Original Assignee
Robert Creuzet Ets
SNECMA Moteurs SA
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 Robert Creuzet Ets, SNECMA Moteurs SA filed Critical Robert Creuzet Ets
Publication of EP0824981A1 publication Critical patent/EP0824981A1/de
Application granted granted Critical
Publication of EP0824981B1 publication Critical patent/EP0824981B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D53/00—Making other particular articles
    • B21D53/78—Making other particular articles propeller blades; turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D11/00—Bending not restricted to forms of material mentioned in only one of groups B21D5/00, B21D7/00, B21D9/00; Bending not provided for in groups B21D5/00 - B21D9/00; Twisting
    • B21D11/14—Twisting
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade

Definitions

  • the present invention relates to twisting equipment hot scalable used in a process for manufacturing a hollow turbomachine blade.
  • One of the aims of the invention is to make it possible to carry out course of the operative flow above an operation additional shaping of parts by twisting without risk of causing buckling type ripples according to the central fiber. These ripples are generated by compression stresses induced during elongation of lateral fibers due to differences in length between the starting flat part and the obtained twisted part.
  • the method of manufacturing a hollow turbomachine blade comprising an operation in accordance with the invention of setting workpiece shape using twisting equipment evolving hot according to the invention avoids the disadvantages of prior known methods and obtaining blades having geometric characteristics and improved and optimized mechanical conditions of use, guaranteeing repetitive quality while facilitating manufacturing conditions at the lowest cost.
  • the method of manufacturing a hollow turbomachine blade according to the invention includes a twist operation hot-swappable, of an element intended for the manufacture of the blade by the hot twist of said alloy element TA6V type titanium, at a temperature above 700 ° C by the action of several bars animated by a movement of rotation around the twist axis and acting on shackles, previously fixed on the element, distributed according to the predetermined twist law, the distribution and number of shackles are determined so as to obtain between each yoke a linear evolution of the twist.
  • Hot-swappable twist equipment for manufacture of a hollow turbine engine vane with a high rate of compression in the lower blade area is characterized by metal frame on which is vertically fixed a cylindrical oven with slots allowing the passage of bars, of a circular frame enveloping said oven, of free crowns rotating around the frame on which are fixed the bars acting on clamped shackles on the element to be twisted.
  • the process for manufacturing a hollow turbine engine blade 1 comprises in accordance with the invention, an operation remarkable hot twist of the welded assembly 1 made of titanium alloy, of type TA6V consisting of hot twist of the welded assembly at a temperature between 700 and 940 ° C, by the action of several bars, integral with crowns driven by a frame circular with a rotational movement around the axis of the element, said bars acting on shackles flanged on the element.
  • Scalable hot twist can be preceded by a bending operation including the shaping of dawn sections.
  • a complementary operation of shaping by twisting and calibration may be required.
  • the hot-swappable twisting equipment shown on the Figures 3 and 4 is used for carrying out the operation twisting of the hollow blade element 1 of a turbomachine in the manufacturing process according to the invention and which comes to be described.
  • This hot-swappable twisting equipment consists of three separate parts: an upper part mainly intended for blocking one end of the part 1 by two jaws 3, in order to ensure immobilization in rotation and keeping in an upright position, part central unit equipped with an electric oven 2, a frame circular 6 mobile in rotation around the workpiece axis acting on free crowns 7 rotating around the frame, distributed vertically along the height of the element to be twisted and a lower part whose function main is to block the other end of element 1, to ensure during a twist a constant distance between these two ends by a tensile force supplied by means a cylinder 8 limited in its stroke by a ball bearing 9 and the transfer of part 1 from the loading station to inside the oven 2.
  • Said central part composed of an electric oven circular 2 capable of a temperature range included between 700 and 940 ° C, have slots 24 intended for passage of bars 5 integral with crowns 7 whose purpose is to act on shackles mounted on the part and visible in Figure 4.
  • a circular frame 6 of tubular mechanically welded construction is rotated by an electric motor 10 to variable speed by means of a ring gear 11 fixed to the upper end of the frame 6.
  • the frame 6 is connected to the metal structure 12 of the equipment by connections to rollers 13, and has as many crowns 7 as necessary according to the law of evolution of the twist, said free crowns 7 rotating around the frame are connected to it by means of roller connections 14.
  • Frame 6 and the crowns 7 are also fitted with drive stops 1516, positioned to apply the twist value required on each yoke.
  • the upper part of the oven incorporates clamping jaws 3 from one end of the part 1 and also allows the passage of the guide rod 25 connecting the jaws with the metallic structure 12.
  • the upper part is mainly intended for clamping from one end of part 1 to be twisted.
  • the rod 25 water-cooled ensures the guidance and connection of the jaws of clamping 3 adapted to the shape of the part 1 with the structure 12 of the equipment.
  • a blocking system by corners 22 shown in more detail in Figure 5 allows position and immobilize the part 1 in a fixed position while allowing vertical translation of the part 1 of the oven 2 to the loading / unloading station located under the oven.
  • a counterweight system allows the balancing of this together in order not to constrain the element to unloading.
  • the lower part intended for the transfer of the loading / unloading to oven 2 also ensures clamping function of the other end of element 1 to by means of two jaws 4, free to rotate, extended by a rod 20 guided vertically by a sleeve 18 integral with a carriage 17 with vertical translation provided by the jack 19.
  • the carriage 17 is equipped with a stop system at balls 9 and a jack 8 in order to apply a force of traction to element 1 so as to maintain a distance constant between jaws 3 and 4 high and low.
  • the cylinder 8 also absorbs the effects of expansion of room 1 during heating.
  • the electric oven 2 is maintained at a temperature higher than 700 ° C for an application on an alloy of TA6V type titanium, jaws 3 and 4 are in the low position ready to receive a welded assembly with shackles distributed over the height of the welded assembly according to the law of twisting evolution, as indicated above.
  • the carriage 17 transfers to oven 2 to an end position predefined stroke, then the jaws 3 are immobilized by a wedge system 22 shown in FIG. 5.
  • the oven doors 21 being closed the welded assembly 1 is kept in oven 2 until it reaches the twist temperature.
  • the motor 10 drives the circular frame 6 which by means of the stops 15 and 16 distributed according to the angle of twisting to be supplied in turn drives the crowns 7 of which the bars 5 acting on the shackles print to the whole welded 1 the desired twist law, then the frame 6 is driven in the opposite direction by bringing in its race the crowns 7 in the cycle start position. At this point the oven doors open and cart 17 transfers assembly 1 welded to the loading / unloading station.

Claims (8)

  1. Verfahren zur Herstellung einer hohlen Turbinenschaufel, insbesondere einer Rotorschaufel eines Gebläses mit großer Weite, bestehend aus den folgenden Schritten:
    (a) ausgehend von der Definition einer herzustellenden Schaufel erfolgt die Entwicklung unter Verwendung von Mitteln zum rechnerunterstützten Entwerfen (CAD) und zur rechnergestützten Fabrikation (CAM) sowie eine numerische Simulation des Flachlegens der Bestandteile der Schaufel;
    (b) Schmieden der Rohlinge auf der Presse,
    (c) Bearbeiten der Rohlinge;
    (d) Aufbringen von Diffusionswänden nach einem vorbestimmten Muster;
    (e) Zusammensetzen der Rohlinge, gefolgt vom Diffusionsschweißen unter isostatischem Druck;
    (f) Aufblähen unter Gasdruck und superplastisches Formen;
    (g) Endbearbeitung,
       dadurch gekennzeichnet, dass es ferner einen Verfahrensschritt des schrittweisen Warmverwindens eines für die Herstellung der Schaufel vorgesehenen Elements (1) aufweist, indem eine Verwindung dieses Elements (1) aus Titanlegierung des Typs TA6V bei einer Temperatur von mehr als 700 °C unter der Einwirkung mehrerer Stäbe (5) erfolgt, welche in eine Drehbewegung um die Verwindungsachse versetzt werden und auf Klemmringe einwirken, die zuvor in einer Verteilung gemäß dem vorbestimmten Verwindungsgesetz an dem Element (1) befestigt wurden, wobei die Verteilung und die Anzahl der Klemmringe so bestimmt wird, dass zwischen den Klemmringen eine lineare Entwicklung der Verwindung erzielt wird.
  2. Verfahren zur Herstellung einer hohlen Turbinenschaufel nach Anspruch 1, wobei dieser Arbeitsschritt des Verwindens an jedem geschmiedeten Rohling erfolgt.
  3. Verfahren zur Herstellung einer hohlen Turbinenschaufel nach Anspruch 1, wobei dieser Arbeitsschritt des Verwindens an einer flachen Gesamtanordnung, die aus den nicht verschweißten Bestandteilen der Schaufel besteht, erfolgt.
  4. Verfahren zur Herstellung einer hohlen Turbinenschaufel nach Anspruch 1, wobei dieser Arbeitsschritt des Verwindens an einer flachen Gesamtanordnung (1) erfolgt, die aus dem Zusammensetzen der Rohlinge, gefolgt vom Diffusionsschweißen, hervorgeht.
  5. Verfahren zur Herstellung einer hohlen Turbinenschaufel nach den Ansprüchen 1 bis 4, wobei diesem Arbeitsschritt des Verwindens ein Vorgang des Hohlprägens in dem Anschlussbereich des Schaufelfußes und des unteren Bereichs des Schaufelblattes vorausgeht.
  6. Ausrüstung zum schrittweisen Warmverwinden für die Herstellung einer hohlen Turbinenschaufel gemäß dem Verfahren der Ansprüche 1 bis 5, bestehend aus einer Struktur aus Metall (12), an der senkrecht ein zylindrischer, elektrischer Ofen (2) angebracht ist, der Schlitze (24) aufweist, durch die Stäbe (5) geführt werden können, einem kreisförmigen Rahmen (6), der diesen Ofen (2) umgibt, Kränze (7), die sich frei drehbar um den Rahmen (6) herum befinden und an denen Stäbe (5) angeordnet sind, die auf Klemmringe einwirken, die an dem zu verwindenden Element (1) festgeklemmt sind, wobei Spannbacken (3, 4), die sich an jedem Ende des Elements (1) befinden, während des Verwindens die Positionierung des Elements (1) im Ofen (2) sowie einen ständigen Zug in der Richtung der Achse des Elements (1) gewährleisten.
  7. Ausrüstung zum schrittweisen Warmverwinden für die Herstellung einer hohlen Turbinenschaufel nach Anspruch 6, bei der ein System von Keilen (22) die Spannbacken (3) im oberen Teil drehfest positioniert und gleichzeitig das Lösen für die Wechsel gewährleistet.
  8. Ausrüstung zum schrittweisen Warmverwinden für die Herstellung einer hohlen Turbinenschaufel nach Anspruch 6, bei der das Eindringen der Stäbe (5) in den Ofen regelbar ist.
EP97401954A 1996-08-22 1997-08-20 Verfahren zur Herstellung einer hohlen Turbinschaufel und Anlage zum laufenden Warmverwinden Expired - Lifetime EP0824981B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9610352 1996-08-22
FR9610352A FR2752539B1 (fr) 1996-08-22 1996-08-22 Procede de fabrication d'une aube creuse de turbomachine et equipement de vrillage evolutif a chaud utilise

Publications (2)

Publication Number Publication Date
EP0824981A1 EP0824981A1 (de) 1998-02-25
EP0824981B1 true EP0824981B1 (de) 2001-05-02

Family

ID=9495156

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97401954A Expired - Lifetime EP0824981B1 (de) 1996-08-22 1997-08-20 Verfahren zur Herstellung einer hohlen Turbinschaufel und Anlage zum laufenden Warmverwinden

Country Status (5)

Country Link
US (2) US5933952A (de)
EP (1) EP0824981B1 (de)
JP (1) JP3477043B2 (de)
DE (1) DE69704690T2 (de)
FR (1) FR2752539B1 (de)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0001753D0 (en) * 2000-01-27 2000-03-15 Sermatech Repair Services Limi Thermal processing apparatus and method
DE10035224A1 (de) * 2000-07-20 2002-01-31 Man Turbomasch Ag Ghh Borsig Verfahren und Rohling zum Herstellen von rhomboidischen Schaufeln für axiale Strömungsmaschinen
GB0117066D0 (en) * 2001-07-12 2001-09-05 Bae Systems Plc Creep forming a metallic compound
US6792655B2 (en) * 2001-11-09 2004-09-21 General Electric Company Apparatus for correcting airfoil twist
FR2867096B1 (fr) * 2004-03-08 2007-04-20 Snecma Moteurs Procede de fabrication d'un bord d'attaque ou de fuite de renforcement pour une aube de soufflante
FR2874339B1 (fr) * 2004-08-23 2008-12-05 Snecma Moteurs Sa Procede de fabrication de pieces constitutives d'une aube creuse par forage sur presse
EP1696220B1 (de) * 2005-02-25 2008-04-23 Snecma Verfahren zur mechanischen Charakterisierung eines metallischen Materials
GB0605070D0 (en) 2006-03-14 2006-04-26 Rolls Royce Plc An aerofoil
CN100410546C (zh) * 2006-08-03 2008-08-13 罗仙国 离心泵叶轮的制造方法
CN101733571B (zh) * 2009-10-28 2012-07-18 河南科技大学 利用电场作用下的超塑性焊接实验装置及方法
GB201414497D0 (en) * 2014-08-15 2014-10-01 Rolls Royce Plc A method of forming an inflated aerofoil
CN104759504B (zh) * 2014-12-23 2017-01-04 无锡透平叶片有限公司 一种用于叶片成形的扭转炉
CN104646465B (zh) * 2015-03-19 2017-01-18 苏州明和行新材料科技有限公司 空心叶片多截面同步扭转成形方法
US11292220B2 (en) * 2018-05-08 2022-04-05 General Electric Company Rework press assembly for component rework systems and methods of using the same
CN111408910B (zh) * 2020-05-09 2021-08-06 东方电气集团东方电机有限公司 一种基于回转工作台的大型整体磁轭圈加工方法
CN111408911B (zh) * 2020-05-09 2021-01-01 东方电气集团东方电机有限公司 一种大型整体磁轭圈加工方法
CN112474945A (zh) * 2020-10-21 2021-03-12 陈校刚 一种铁剑锻造时铁条扭曲设备
CN113182405B (zh) * 2021-04-30 2022-11-18 北京航空航天大学 一种钛合金空心叶片的热扭转成形方法及其扭转组件

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1578991A (de) * 1968-05-22 1969-08-22
GB2073631B (en) * 1980-04-15 1984-12-19 Rolls Royce Blade twisting
GB2080156B (en) * 1980-07-25 1984-01-04 Ufimsk Aviatsion Inst Turbine blade making method and blade twisting devices
JPS59125230A (ja) * 1982-12-29 1984-07-19 Showa Alum Corp フアン用ブレ−ド等の捩り成形製品の製造方法
US5063662A (en) * 1990-03-22 1991-11-12 United Technologies Corporation Method of forming a hollow blade
US5099573A (en) * 1990-06-27 1992-03-31 Compressor Components Textron Inc. Method of making hollow articles
US5083371A (en) * 1990-09-14 1992-01-28 United Technologies Corporation Hollow metal article fabrication
US5253419A (en) * 1991-02-20 1993-10-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Method of manufacturing a hollow blade for a turboshaft engine
GB9209464D0 (en) * 1992-05-01 1992-06-17 Rolls Royce Plc A method of manufacturing an article by superplastic forming and diffusion bonding
FR2724127B1 (fr) * 1994-09-07 1996-12-20 Snecma Procede de fabrication d'une aube creuse de turbomachine
FR2739045B1 (fr) 1995-09-27 1997-10-31 Snecma Procede de fabrication d'une aube creuse de turbomachine
FR2749784B1 (fr) * 1996-06-13 1998-07-31 Snecma Procede de fabrication d'un aube creuse de turbomachine et presse-four a multiple effet utilisee dans sa mise en oeuvre
FR2754478B1 (fr) 1996-10-16 1998-11-20 Snecma Procede de fabrication d'une aube creuse de turbomachine

Also Published As

Publication number Publication date
EP0824981A1 (de) 1998-02-25
FR2752539A1 (fr) 1998-02-27
JP3477043B2 (ja) 2003-12-10
US5933952A (en) 1999-08-10
FR2752539B1 (fr) 1998-09-18
DE69704690D1 (de) 2001-06-07
DE69704690T2 (de) 2001-11-29
US6242715B1 (en) 2001-06-05
JPH1089008A (ja) 1998-04-07

Similar Documents

Publication Publication Date Title
EP0824981B1 (de) Verfahren zur Herstellung einer hohlen Turbinschaufel und Anlage zum laufenden Warmverwinden
CA2206160C (fr) Procede de fabrication d'une aube creuse de turbomachine et presse-four a multiple effet utilisee dans sa mise en oeuvre
EP0700738B1 (de) Verfahren zur Herstellung einer hohlen Turbinenschaufel
CA2186562C (fr) Procede de fabrication d'une aube creuse de turbomachine
FR2970192A1 (fr) Outillage et procede de forgeage a chaud de toles
FR2659038A1 (fr) Procede de soudage par friction et machine de mise en óoeuvre.
CA2802943A1 (fr) Procede de realisation d'un renfort metallique d'aube de turbomachine
CA3015217C (fr) Dispositif d'application de materiau abradable sur une surface d'un carter de turbomachine
FR2503590A1 (fr) Methode de percage dans la fabrication de tubes sans soudure
EP2937516B1 (de) Rundgebogenes Monoblock-Gehäuse für Kompressor einer axialen Turbomaschine und entsprechendes Fertigungsverfahren
FR2556992A1 (fr) Appareil a contourner les aubes
FR2580341A1 (fr) Procede de realisation d'une liaison rigide entre deux pieces mecaniques coaxiales, et ensemble de deux pieces liees par ce procede
EP0569307B1 (de) Vorrichtung zur Formung von schraubenförmigen Rippen an der Aussenfläche eines Rohres
LU82892A1 (fr) Procede et dispositif pour le formage de tubes coudes a partir d'elements de tubes rectilignes
WO2013088078A1 (fr) Secteur de redresseur pour un compresseur de turbomachine réalisé par brasage d'une plate-forme de ses aubes sur une virole
EP0446089B1 (de) Verfahren und Vorrichtung zum Formen einer kreisförmigen Lippe um eine Öffnung
WO2009071532A1 (fr) Turbine à gaz comportant une roue à aubes du type à ailettes radiales et procédé de fabrication des ailettes de ladite turbine
FR2485659A1 (fr) Arbre metallique composite et procede pour sa fabrication
CH628826A5 (fr) Procede de formage de pieces creuses courbes, dispositif pour la mise en oeuvre de ce procede et pieces creuses courbes embouties ainsi obtenues.
EP0504039A1 (de) Verfahren und Vorrichtung zur Herstellung eines ringförmigen Werkstückes aus Blech
EP0599751B1 (de) Verfahren und Vorrichtung zum Fixieren eines mit zumindest einer zylindrischen Bohrung versehenen metallischen Stückes um ein metallisches Rohr
WO2023186795A1 (fr) Procédé et installation de fabrication par forgeage à chaud d'une pièce intermédiaire allongée
FR2996154A1 (fr) Outillage pour l'assemblage de deux pieces annulaires de carter
CN209006910U (zh) 液力变矩器焊接设备
FR2843901A1 (fr) Procede et dispositif pour former, par fluotournage, un tube, en particulier une enveloppe d'un silencieux ou catalyseur de ligne d'echappement

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: 19970901

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB IT

AKX Designation fees paid

Free format text: DE FR GB IT

RBV Designated contracting states (corrected)

Designated state(s): DE FR GB IT

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

17Q First examination report despatched

Effective date: 20000605

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ETABLISSEMENTS ROBERT CREUZET

Owner name: SNECMA MOTEURS

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT

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

Effective date: 20010503

REF Corresponds to:

Ref document number: 69704690

Country of ref document: DE

Date of ref document: 20010607

ITF It: translation for a ep patent filed

Owner name: BARZANO' E ZANARDO MILANO S.P.A.

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

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
REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

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

Ref country code: DE

Payment date: 20150722

Year of fee payment: 19

Ref country code: GB

Payment date: 20150724

Year of fee payment: 19

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

Ref country code: IT

Payment date: 20150728

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 20

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

Ref country code: FR

Payment date: 20160804

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 69704690

Country of ref document: DE

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

Effective date: 20160820

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: 20160820

Ref country code: DE

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

Effective date: 20170301

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: 20160820

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719