EP1340832B1 - Dünne Produkte aus Beta- oder quasi Beta-Titan-Legierungen, Herstellung durch Schmieden - Google Patents

Dünne Produkte aus Beta- oder quasi Beta-Titan-Legierungen, Herstellung durch Schmieden Download PDF

Info

Publication number
EP1340832B1
EP1340832B1 EP03290458A EP03290458A EP1340832B1 EP 1340832 B1 EP1340832 B1 EP 1340832B1 EP 03290458 A EP03290458 A EP 03290458A EP 03290458 A EP03290458 A EP 03290458A EP 1340832 B1 EP1340832 B1 EP 1340832B1
Authority
EP
European Patent Office
Prior art keywords
forging
temperature
lying
range
quenching
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
EP03290458A
Other languages
English (en)
French (fr)
Other versions
EP1340832A1 (de
Inventor
Blandine Barbier
Agathe Venard
Philippe Gallois
Pascal Vignolles
Claude Mons
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
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1340832A1 publication Critical patent/EP1340832A1/de
Application granted granted Critical
Publication of EP1340832B1 publication Critical patent/EP1340832B1/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
    • B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
    • B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
    • B21K3/04—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like blades, e.g. for turbines; Upsetting of blade roots
    • 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

Definitions

  • the subject of the present invention is thin products made of ⁇ or quasi- ⁇ titanium alloys, as well as the manufacture by forging of said thin products.
  • the design and development context of the presently claimed invention has been that of the manufacture of monoblock bladed disks (DAM) with linear friction welding blades.
  • Said monobloc bladed discs with reference to their mechanical properties and in particular their resistance to vibratory fatigue, are generally made of a titanium ⁇ or quasi- ⁇ alloy. They are obtained, to date, by machining, in a massive crude.
  • blades made of titanium alloys ⁇ or almost ⁇ that perform well (having good metallurgical health and good mechanical properties) have been obtained by forging (FIG. that is to say with economy of material, compared to the machining technique, conventionally implemented). Said blades also have longer lifetimes than blades obtained by machining; they can also be obtained with optimized geometries, to improve the aerodynamics, so the performance of the engine in which they are likely to intervene.
  • EP-A-0 852 164 discloses a method for producing titanium alloy turbine blades which comprises a forging step followed by localized forced cooling of the leading edges of the tip portions of said blades.
  • the forging is carried out at a temperature of 10 ° C. or more below the temperature of ⁇ -transus.
  • US-A-4,854,977 describes a large smithing process, particularly suitable for obtaining compressor disks for aircraft propulsion systems.
  • the forging operation used comprises roughing forging and final forging, advantageously started in ⁇ and finished in ⁇ - ⁇ .
  • the invention has therefore been conceived and developed, in a non-obvious manner, in the context of the manufacture of monobloc bladed disks (DAM).
  • DAM monobloc bladed disks
  • it is not limited to this context; it is also expressed, naturally, in more or less neighboring contexts, such as that of the manufacture of monoblock bladed rings (ANAM), those of the repair of said monoblock bladed discs (DAM) and bladed monoblock rings (ANAM), and more generally that of the manufacture of thin titanium products ⁇ or almost ⁇ .
  • Said products constitute the first object of the present invention.
  • the controlled forging process that leads to said products constitutes the second object.
  • the present invention therefore relates to manufactured products, not axisymmetric (the son are thus excluded), a thickness of less than 10 mm (these 10 mm specify the concepts of "thin", “thin products” , used in the present text), in titanium alloys substantially ⁇ , the core microstructure consists of whole grains having a slenderness ratio greater than 4 and an equivalent diameter of between 10 and 300 microns.
  • Titanium alloys ⁇ or almost ⁇ are familiar to the skilled person. They have a compact hexagonal structure. They are perfectly defined, especially in American Handbooks (US): ASMH (AMERICAN SOCIETY MATERIAL HANDBOOK) and MILH (MILITARY HANDBOOK). Their use is, to date, confined to the manufacture of massive forgings or thick layers.
  • the manufactured products of the invention are thin products that carry the heredity of their manufacturing process, based on one or more forging operations.
  • Their microstructure at heart is original.
  • the grains of said core microstructure have been wrought.
  • slenderness ratio greater than 4; said slenderness ratio being conventionally defined as the ratio of the largest dimension to the smallest dimension in the axial section plane.
  • They have an equivalent diameter of between 10 and 300 microns.
  • the manufactured products of the invention are new products. These new products are likely to be obtained by forging. As explained above, there was a real prejudice to seek thin structures by forging thicker coarse-grained structures and, quite surprisingly, such thin structures have been found to have very interesting characteristics.
  • the manufactured products of the invention advantageously consist of turbine engine compressor blades.
  • the invention is however not limited to this context.
  • the products in question may also consist of propellers, including submarines, fan blades or mixers (capable of intervening in environments justifying the constitution of said blades ⁇ or quasi ⁇ titanium alloys). This list can not be exhaustive.
  • the manufactured products of the invention are Ti 17 alloy.
  • This alloy familiar to the skilled person, is used to date to make massive parts, including compressor discs. It has high flow constraints and is also known to be difficult to forge.
  • the product to be forged is conventionally enamelled.
  • Said product is advantageously obtained by transformation of an enamelled billet. It generally consists of a half-product, obtained by spinning or forging a starting material, with a larger equivalent diameter (with a greater thickness). It may especially be a bar (having, for example, a diameter of 25 mm), obtained by spinning a billet.
  • titanium alloys ⁇ or close ⁇ exist mainly in the form of such billets (intended for the manufacture of compression discs by machining).
  • This enamelled product generally enamelled half product, of a diameter (equivalent) less than 100 mm, is, according to the invention, converted by forging into a manufactured product with a thickness of less than 10 mm.
  • the reduction rate at each hot is greater than or equal to (advantageously greater than) 2 and the forging speeds (or crushing speeds) are between 1 and 1.10 -5 s -1 .
  • the forging operation can be quite limited to the two hot, as specified above (the second of said two hot is imperatively a hot super-transus It may include an additional hot, sub or super transus ⁇ , before the Last (third) hot in super transus ⁇ It is not totally excluded that it includes more than three hot (the last of these hot being imperatively a hot super transus ⁇ ) but the interest to multiply the number of hot is not obvious.
  • the forging operation therefore generally includes two or three hot, implemented under the conditions specified above.
  • the forged product is optionally re-enamelled between two successive hot.
  • the forging die is maintained at a temperature of between 100 and 700 ° C.
  • the forging operation is conventionally followed by quenching (usually immediately followed by such quenching).
  • quenching can in particular be carried out under pulsed air, in calm air, in an oil bath or on a matrix. It is advantageously used under conditions that induce a cooling rate that is less than or equal to that induced by quenching in an oil bath.
  • the tempered product of the forged product is advantageously used at a temperature of between 620 and 750 ° C. for 3 to 5 hours. Its implementation conditions are optimized according to the characteristics sought for the finished product. It is ensured to perform said income under an inert atmosphere (especially vacuum or argon) if the enameling is cracked or flaking.
  • Example Making a blade made of Ti 17 by forging.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Forging (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (11)

  1. Nicht axialsymmetrische Erzeugnisse aus Quasi-β-Titanlegierungen, dadurch gekennzeichnet, daß sie folgendes aufweisen:
    - eine Dicke von unter 10 mm, und
    - eine Mikrostruktur mit Kern, die von ganzen Körnern gebildet ist, welche linsenförmig sind und einen Schlankheitsgrad von über 4 sowie einen Äquivalentdurchmesser zwischen 10 und 300 µm aufweisen.
  2. Erzeugnisse nach Anspruch 1, die geeignet sind, durch Schmieden erhalten zu werden.
  3. Erzeugnisse nach einem der Ansprüche 1 oder 2, bestehend aus Schaufeln von Turbomaschinenverdichtern.
  4. Erzeugnisse nach irgendeinem der Ansprüche 1 bis 3, aus Ti17-Legierung: TA5CD4 oder TiAl5Cr2Mo4.
  5. Verfahren zur Herstellung eines Produktes nach irgendeinem der vorhergehenden Ansprüche, das aufeinanderfolgende Schritte zum Schmieden, zum Härten des geschmiedeten Produktes und zum Vergüten des geschmiedeten, gehärteten Produktes umfaßt, dadurch gekennzeichnet, daß:
    - das Schmieden an einem emaillierten langen Produkt mit einem Äquivalentdurchmesser von unter 100 mm durchgeführt wird; und dadurch, daß
    - das Schmieden wenigstens zwei Hitzen umfaßt, die erste in Sub- oder Super-β-Transus und die letzte in Super-β-Transus; wobei der Reduktionsgrad bei jeder Hitze größer oder gleich 2 ist und die Schmiedegeschwindigkeiten zwischen 1 und 1.10-5 s-1 liegen.
  6. Verfahren nach Anspruch 5, dadurch gekennzeichnet, daß das Schmieden drei Hitzen umfaßt; eine erste und eine zweite unabhängig in Sub- oder Super-β-Transus sowie ein dritte in Super-β-Transus.
  7. Verfahren nach einem der Ansprüche 5 oder 6, dadurch gekennzeichnet, daß es ein erneutes Emaillieren des Produktes zwischen zwei Hitzen umfaßt.
  8. Verfahren nach irgendeinem der Ansprüche 5 bis 7, dadurch gekennzeichnet, daß das Schmiedegesenk auf einer Temperatur zwischen 100 und 700°C gehalten wird.
  9. Verfahren nach irgendeinem der Ansprüche 5 bis 8, dadurch gekennzeichnet, daß das Härten unter Bedingungen durchgeführt wird, die eine Abkühlgeschwindigkeit induzieren, welche unter oder gleich derjenigen liegt bzw. ist, die durch ein Härten in einem Ölbad induziert wird.
  10. Verfahren nach irgendeinem der Ansprüche 5 bis 9, dadurch gekennzeichnet, daß das Vergüten bei einer Temperatur zwischen 620 und 750°C während 3 bis 5 Stunden durchgeführt wird.
  11. Verfahren nach irgendeinem der Ansprüche 5 bis 10, dadurch gekennzeichnet, daß:
    - der emailliert lang Produkt aus Ti17-Legierung: TA5CD4 oder TiAl5Cr2MO4 besteht;
    - das Schmieden eine erste Hitze bei einer Temperatur kleiner oder gleich 840 ± 10°C oder bei einer Temperatur größer oder gleich 940 ± 10°C sowie eine zweite Hitze bei einer Temperatur von 940 ± 10°C umfaßt;
    - das Härten am Gesenk, anschließend an ruhiger Luft durchgeführt wird; und
    - das Vergüten bei 630°C während 4 Stunden vollzogen wird.
EP03290458A 2002-03-01 2003-02-27 Dünne Produkte aus Beta- oder quasi Beta-Titan-Legierungen, Herstellung durch Schmieden Expired - Lifetime EP1340832B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0202602A FR2836640B1 (fr) 2002-03-01 2002-03-01 Produits minces en alliages de titane beta ou quasi beta fabrication par forgeage
FR0202602 2002-03-01

Publications (2)

Publication Number Publication Date
EP1340832A1 EP1340832A1 (de) 2003-09-03
EP1340832B1 true EP1340832B1 (de) 2007-04-11

Family

ID=27676204

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03290458A Expired - Lifetime EP1340832B1 (de) 2002-03-01 2003-02-27 Dünne Produkte aus Beta- oder quasi Beta-Titan-Legierungen, Herstellung durch Schmieden

Country Status (7)

Country Link
US (2) US7037389B2 (de)
EP (1) EP1340832B1 (de)
JP (1) JP4022482B2 (de)
DE (1) DE60313065T2 (de)
FR (1) FR2836640B1 (de)
RU (1) RU2303642C2 (de)
UA (1) UA77399C2 (de)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040221929A1 (en) 2003-05-09 2004-11-11 Hebda John J. Processing of titanium-aluminum-vanadium alloys and products made thereby
FR2864107B1 (fr) * 2003-12-22 2006-08-04 Univ Metz Fil en alliage de titane beta pour orthodontie, et procede d'obtention d'un tel fil.
US7837812B2 (en) 2004-05-21 2010-11-23 Ati Properties, Inc. Metastable beta-titanium alloys and methods of processing the same by direct aging
US7195455B2 (en) * 2004-08-17 2007-03-27 General Electric Company Application of high strength titanium alloys in last stage turbine buckets having longer vane lengths
US8661869B2 (en) * 2005-11-04 2014-03-04 Cyril Bath Company Stretch forming apparatus with supplemental heating and method
FR2923741B1 (fr) * 2007-11-19 2010-05-14 Snecma Services Procede de reparation d'une piece thermomecanique par un faisceau de haute energie
FR2936172B1 (fr) * 2008-09-22 2012-07-06 Snecma Procede de forgeage d'une piece thermomecanique en alliage de titane
US10053758B2 (en) 2010-01-22 2018-08-21 Ati Properties Llc Production of high strength titanium
US9255316B2 (en) 2010-07-19 2016-02-09 Ati Properties, Inc. Processing of α+β titanium alloys
US8613818B2 (en) 2010-09-15 2013-12-24 Ati Properties, Inc. Processing routes for titanium and titanium alloys
US9206497B2 (en) 2010-09-15 2015-12-08 Ati Properties, Inc. Methods for processing titanium alloys
US10513755B2 (en) 2010-09-23 2019-12-24 Ati Properties Llc High strength alpha/beta titanium alloy fasteners and fastener stock
US8652400B2 (en) 2011-06-01 2014-02-18 Ati Properties, Inc. Thermo-mechanical processing of nickel-base alloys
RU2478130C1 (ru) * 2011-10-21 2013-03-27 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Бета-титановый сплав и способ его термомеханической обработки
FR2982279B1 (fr) * 2011-11-08 2013-12-13 Snecma Procede de fabrication d'une piece realisee dans un alliage de titane ta6zr4de
US9050647B2 (en) 2013-03-15 2015-06-09 Ati Properties, Inc. Split-pass open-die forging for hard-to-forge, strain-path sensitive titanium-base and nickel-base alloys
US9869003B2 (en) 2013-02-26 2018-01-16 Ati Properties Llc Methods for processing alloys
US9192981B2 (en) 2013-03-11 2015-11-24 Ati Properties, Inc. Thermomechanical processing of high strength non-magnetic corrosion resistant material
US9777361B2 (en) 2013-03-15 2017-10-03 Ati Properties Llc Thermomechanical processing of alpha-beta titanium alloys
US10604823B2 (en) * 2013-06-05 2020-03-31 Kobe Steel, Ltd. Forged titanium alloy material and method for producing same, and ultrasonic inspection method
US11111552B2 (en) 2013-11-12 2021-09-07 Ati Properties Llc Methods for processing metal alloys
FR3024160B1 (fr) * 2014-07-23 2016-08-19 Messier Bugatti Dowty Procede d'elaboration d`une piece en alliage metallique
US10094003B2 (en) 2015-01-12 2018-10-09 Ati Properties Llc Titanium alloy
US10502252B2 (en) 2015-11-23 2019-12-10 Ati Properties Llc Processing of alpha-beta titanium alloys

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2614040B1 (fr) * 1987-04-16 1989-06-30 Cezus Co Europ Zirconium Procede de fabrication d'une piece en alliage de titane et piece obtenue
US5026520A (en) * 1989-10-23 1991-06-25 Cooper Industries, Inc. Fine grain titanium forgings and a method for their production
US6127044A (en) * 1995-09-13 2000-10-03 Kabushiki Kaisha Toshiba Method for producing titanium alloy turbine blades and titanium alloy turbine blades
US5795413A (en) * 1996-12-24 1998-08-18 General Electric Company Dual-property alpha-beta titanium alloy forgings
JP3959766B2 (ja) * 1996-12-27 2007-08-15 大同特殊鋼株式会社 耐熱性にすぐれたＴｉ合金の処理方法
US6632304B2 (en) * 1998-05-28 2003-10-14 Kabushiki Kaisha Kobe Seiko Sho Titanium alloy and production thereof
JP3666256B2 (ja) * 1998-08-07 2005-06-29 株式会社日立製作所 蒸気タービン翼の製造方法
JP4287991B2 (ja) * 2000-02-23 2009-07-01 三菱重工業株式会社 ＴｉＡｌ基合金及びその製造方法並びにそれを用いた動翼

Also Published As

Publication number Publication date
US7422644B2 (en) 2008-09-09
FR2836640B1 (fr) 2004-09-10
EP1340832A1 (de) 2003-09-03
DE60313065D1 (de) 2007-05-24
UA77399C2 (uk) 2006-12-15
US7037389B2 (en) 2006-05-02
RU2303642C2 (ru) 2007-07-27
JP2003253361A (ja) 2003-09-10
US20030209298A1 (en) 2003-11-13
JP4022482B2 (ja) 2007-12-19
DE60313065T2 (de) 2008-01-03
US20060157170A1 (en) 2006-07-20
FR2836640A1 (fr) 2003-09-05

Similar Documents

Publication Publication Date Title
EP1340832B1 (de) Dünne Produkte aus Beta- oder quasi Beta-Titan-Legierungen, Herstellung durch Schmieden
EP0287486B1 (de) Verfahren zur Herstellung eines Werkstückes aus Titan-Legierung und hergestelltes Werkstück
EP1127949B1 (de) TiAl-basierte Legierung, Verfahren zu deren Herstellung und Rotorblatt daraus
RU2329116C2 (ru) Способ изготовления изделия из титанового альфа-бета-сплава путем ковки
RU2325463C2 (ru) Обработка заготовок из двухфазных титановых сплавов с альфа-бета-структурой для хорошей пригодности к ультразвуковому контролю
EP2344290B1 (de) Verfahren zum schmieden eines thermomechanischen teils aus einer titanlegierung
JP4209092B2 (ja) ＴｉＡｌ基合金及びその製造方法並びにそれを用いた動翼
JP2007277721A (ja) ニッケル系合金
EP2520395A2 (de) Komponenten und Verfahren zur Herstellung von Komponenten mit Regionen mit unterschiedlicher Kornstruktur
RU2003105549A (ru) Тонкие изделия из сплавов бета-титана или квази-бета-титана и способ изготовления таких изделий методом ковки
JPH10195564A (ja) 切削仕上げ面を有する高強度ニッケル超合金品
WO2010023405A2 (fr) Procédé de préparation d'une pièce en superalliage base nickel et pièce ainsi obtenue
EP3302874A1 (de) Verfahren zur herstellung einer tial-schaufel eines turbinenmotors
FR2633942A1 (fr) Superalliage a base de nickel resistant aux pendillements par fatigue et son procede de fabrication
EP3121297B1 (de) Herstellungsverfahren einer schmuckkomponente aus platinlegierung
RU2244135C2 (ru) Клапан двигателя внутреннего сгорания, способ его изготовления и жаропрочный титановый сплав для него
EP0792945B1 (de) Wärmebehandlungsverfahren für Superlegierung auf Nickelbasis
JP2004538361A (ja) ＴｉＡｌ合金からなる高負荷容量の部材を製造する方法
EP4097268A1 (de) Wärmebehandlung durch heissisostatisches pressen von stäben aus einer titanaluminid-legierung für niederdruckturbinenschaufeln einer turbomaschine
JP3590430B2 (ja) 耐熱性に優れたＴｉ合金ディスク
FR3134527A1 (fr) PROCEDE DE FABRICATION D’UNE PIECE EN ALLIAGE BASE NICKEL DU TYPE γ/γ’ AVEC OUTILLAGE DE FORGEAGE A CHAUD
Caballero et al. SPRAYFORMING OPTIMISATION OF SUPERALLOY AEROENGINE COMPONENTS
CH526635A (fr) Procédé pour la fabrication d'articles à partir d'alliages réfractaires

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): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT SE SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO

17P Request for examination filed

Effective date: 20040218

AKX Designation fees paid

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 20041118

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

Owner name: SNECMA

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 60313065

Country of ref document: DE

Date of ref document: 20070524

Kind code of ref document: P

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

Effective date: 20070626

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

Effective date: 20080114

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 15

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

Ref country code: DE

Payment date: 20170119

Year of fee payment: 15

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

Ref country code: GB

Payment date: 20170124

Year of fee payment: 15

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170713

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 16

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 60313065

Country of ref document: DE

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

Effective date: 20180227

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: 20180901

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: 20180227

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

Ref country code: FR

Payment date: 20220119

Year of fee payment: 20