EP1335113A1 - Befestiganordnung für den Statorring einer Turbomaschine - Google Patents

Befestiganordnung für den Statorring einer Turbomaschine Download PDF

Info

Publication number
EP1335113A1
EP1335113A1 EP03290288A EP03290288A EP1335113A1 EP 1335113 A1 EP1335113 A1 EP 1335113A1 EP 03290288 A EP03290288 A EP 03290288A EP 03290288 A EP03290288 A EP 03290288A EP 1335113 A1 EP1335113 A1 EP 1335113A1
Authority
EP
European Patent Office
Prior art keywords
sectors
sealing
distributor
casing
axial
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
EP03290288A
Other languages
English (en)
French (fr)
Other versions
EP1335113B1 (de
Inventor
Patrick Joseph Marie Girard
Sébastien Alain Imbourg
Philippe Jean-Pierre Pabion
Jean-Luc Soupizon
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 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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1335113A1 publication Critical patent/EP1335113A1/de
Application granted granted Critical
Publication of EP1335113B1 publication Critical patent/EP1335113B1/de
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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • This invention relates to an arrangement for hanging sectors in an arc distributor.
  • the distributors considered here are meet in turbomachinery and carry blades attached to the stator responsible for straightening the flow of gas. Distributor areas are mounted at the inside of the stator housing by overlaps of hooks by making them rest on bearing faces some of which must take back the efforts exerted on the distributor vanes.
  • the outer ring 3 of distributor sectors 1 includes an upstream leg 4 and a downstream leg 5 all two in the form of a hook, and the casing 2 comprises upstream legs 6 and downstream legs 7 still in the form of hook, and associated in pairs with a distributor given.
  • leg 4 of sector 1 is engaged around leg 6 of housing 2, but downstream it is the tab 7 of the casing 2 which is engaged around the leg 5 of sector 1. This is justified if we consider that the forces F exerted on the distributor are essentially directed downstream, and transmitted to casing 2 partially as a moment comprising a centripetal radial force R1 at the front and an R2 centrifuge downstream. Legs 4 and 5 of sectors 1 therefore rest on legs 6 and 7 of the casing 2 to the contact faces 8 and 9 which are faces recovery of efforts.
  • the axial component of the efforts F is also transmitted to the casing 2 by an axial force X which is exerted downstream of leg 5, at one end curved hook 10 of tab 7; the face of contact between tab 5 and end 10 is therefore a axial resumption of force 11.
  • sectors 1 and 16 of distributor and sealing which alternate axially in the machine are assembled together since the outer ring 3 of distributor sectors 1 includes upstream a tab 20 which engages in the downstream end of the neighboring sealing sectors 16, and that the sealing sectors 16 likewise have a upstream tab 21 which engages under tab 5 downstream of the neighboring crown 3 of the distributor 1.
  • the legs 20 and 21 maintain sectors 1 in position and 16.
  • the invention relates to a distributor sector attachment arrangement of a different kind, the essential purpose of which is not use hook-shaped legs belonging to the casing, in order to simplify it and to make the mounting of the dispenser more convenient.
  • the basic idea behind the invention is that the force recovery faces in the directions directed axially and radially outwards will now be located on the sealing areas, the casing essentially providing only unsolicited or poorly stressed bearing faces, if although the efforts it must withstand will be considerably reduced.
  • a notable form of the invention is characterized in that the distributor sectors and sealing include tabs at two ends opposite axial, the legs of the sectors of dispenser are clamped between the legs of the sealing sectors and the housing, and the sectors are fixed to the housing by a portion median.
  • the overall shape of the distributor sectors, to which the reference 25 is now associated, is not substantially modified, and they also include an outer ring 26 provided with a tab 27 upstream and a tab 28 at the downstream.
  • the legs 27 and 28 are supported by their outer faces on radial faces 29 and 30 directed towards the inside of the housing, which now bears the reference 31.
  • Sealing sectors, now 32, are still arranged alternately with the sectors 25 of dispenser and they comprise, in addition to an abradable crown 33, an outer crown 34 whose downstream 35 and upstream ends 36 serve to enclose the tabs 27 and 28 between them and between the bearing faces 29 and 30 respectively of the casing 31.
  • the downstream end 35 carries a radial support face directed towards the outside 37 on which the centripetal radial force R 1 weighs
  • the upstream end 36 carries a radial support face directed towards the outside 38 and an axial bearing face 39 for resuming the axial force X.
  • the outer rings 34 are joined to the casing 31 with a middle portion provided with a rib 40 (or a boss) penetrating into a groove 41 (or a creu x) of complementary shape of the casing 31 to precisely adjust the position of the sealing sectors 32. Screws 42 are engaged through the boss 40 and the casing 31 to fix the sealing sectors 32 to the latter. These screws (42) are secured to the housing by the nut 46.
  • Another fixing means such as a pin engaged by force, would fulfill the same function.
  • the complicated and fragile forms of hooks really disappear from the housing 31 like sealing sectors 32.
  • the bearing faces 29 and 30 of the casing 31 are established on massive parts and therefore resistant.
  • the radial and axial R2 and X forces exerted by the leg downstream 28 are on different pieces, which relieves them both.
  • the forces R 1 and X exert antagonistic moments R 1 xL and Xxl on the outer ring 34 around the point of attachment of the screw 42 to the casing 31, and it is possible to adjust the lever arms L and 1 of the forces R and X respectively by a judicious choice of the position of the screw 42 so that their moments have comparable values and that the bending produced on the screw 42 is therefore greatly reduced.
  • the distributor sectors 25 can be mounted by purely axial movements, the sealing sectors 32 then being mounted behind them, which is more convenient and gives more freedom to arrange the machine. Corner pieces 43, fixed to the casing 31 by pins 44, can be added to provide an axial abutment face 45 to the distributor sectors 25.
  • this typical axial assembly allows decrease the axial clearances between the stator vanes (inner ring 12 of sectors 1 in Figure 1) and the rotor blades (inner ring 13 of the blades rotor 15 in Figure 1); as a result, this reduces the leakage sections (47) between rotor and stator and ensures better efficiency of the whole planed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating Apparatus (AREA)
  • Surgical Instruments (AREA)
EP03290288A 2002-02-07 2003-02-05 Befestiganordnung für den Statorring einer Turbomaschine Expired - Lifetime EP1335113B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0201460A FR2835563B1 (fr) 2002-02-07 2002-02-07 Agencement d'accrochage de secteurs en arc de cercle de distributeur porteur d'aubes
FR0201460 2002-02-07

Publications (2)

Publication Number Publication Date
EP1335113A1 true EP1335113A1 (de) 2003-08-13
EP1335113B1 EP1335113B1 (de) 2005-11-02

Family

ID=27589603

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03290288A Expired - Lifetime EP1335113B1 (de) 2002-02-07 2003-02-05 Befestiganordnung für den Statorring einer Turbomaschine

Country Status (11)

Country Link
US (2) US20030146578A1 (de)
EP (1) EP1335113B1 (de)
JP (1) JP4087720B2 (de)
CN (1) CN100357569C (de)
CA (1) CA2418357C (de)
DE (1) DE60302077T2 (de)
ES (1) ES2250844T3 (de)
FR (1) FR2835563B1 (de)
MA (1) MA25948A1 (de)
RU (1) RU2311539C2 (de)
UA (1) UA76424C2 (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1840339A1 (de) * 2006-03-30 2007-10-03 Snecma Vorrichtung zur Befestigung von Ringsektoren um ein Turbinenlaufrad einer Strömungsmaschine
FR2928963A1 (fr) * 2008-03-19 2009-09-25 Snecma Sa Distributeur de turbine pour une turbomachine.
FR2944554A1 (fr) * 2009-04-16 2010-10-22 Snecma Turbine haute-pression de turbomachine
FR2981602A1 (fr) * 2011-10-25 2013-04-26 Snecma Propulsion Solide Procede de fabrication d'un secteur de distributeur de turbine ou redresseur de compresseur en materiau composite pour turbomachine et turbine ou compresseur incorporant un distributeur ou un redresseur forme de tels secteurs
EP2896796A1 (de) * 2014-01-20 2015-07-22 Techspace Aero S.A. Stator einer axialen Strömungsmaschine und zugehörige Strömungsmaschine
FR3083564A1 (fr) * 2018-07-05 2020-01-10 Safran Aircraft Engines Turbine comportant un element abradable a position radiale ajustable

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2829525B1 (fr) * 2001-09-13 2004-03-12 Snecma Moteurs Assemblage de secteurs d'un distributeur de turbine a un carter
DE102004016222A1 (de) * 2004-03-26 2005-10-06 Rolls-Royce Deutschland Ltd & Co Kg Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine
US7523616B2 (en) * 2005-11-30 2009-04-28 General Electric Company Methods and apparatuses for assembling a gas turbine engine
US7637110B2 (en) * 2005-11-30 2009-12-29 General Electric Company Methods and apparatuses for assembling a gas turbine engine
US7493771B2 (en) * 2005-11-30 2009-02-24 General Electric Company Methods and apparatuses for assembling a gas turbine engine
US7771160B2 (en) * 2006-08-10 2010-08-10 United Technologies Corporation Ceramic shroud assembly
US7665960B2 (en) * 2006-08-10 2010-02-23 United Technologies Corporation Turbine shroud thermal distortion control
FR2923525B1 (fr) * 2007-11-13 2009-12-18 Snecma Etancheite d'un anneau de rotor dans un etage de turbine
FR2928961B1 (fr) * 2008-03-19 2015-11-13 Snecma Distributeur sectorise pour une turbomachine.
FR2930592B1 (fr) * 2008-04-24 2010-04-30 Snecma Distributeur de turbine pour une turbomachine
FR2939836B1 (fr) * 2008-12-12 2015-05-15 Snecma Joint d'etancheite de plateforme dans un rotor de turbomachine
US8167546B2 (en) * 2009-09-01 2012-05-01 United Technologies Corporation Ceramic turbine shroud support
US8608424B2 (en) * 2009-10-09 2013-12-17 General Electric Company Contoured honeycomb seal for a turbomachine
US8647055B2 (en) * 2011-04-18 2014-02-11 General Electric Company Ceramic matrix composite shroud attachment system
FR2974841B1 (fr) * 2011-05-04 2013-06-07 Snecma Dispositif d'etancheite pour distributeur de turbine de turbomachine
US9291061B2 (en) * 2012-04-13 2016-03-22 General Electric Company Turbomachine blade tip shroud with parallel casing configuration
US9568009B2 (en) 2013-03-11 2017-02-14 Rolls-Royce Corporation Gas turbine engine flow path geometry
FR3057015B1 (fr) * 2016-09-30 2018-12-07 Safran Aircraft Engines Disque de rotor comportant une toile a epaisseur variable
RU190280U1 (ru) * 2019-01-09 2019-06-25 Публичное Акционерное Общество "Одк-Сатурн" Устройство для фиксации сегментов сопловых лопаток в силовом корпусе статора турбины
BE1027280B1 (fr) * 2019-05-16 2020-12-15 Safran Aero Boosters Sa Carter de compresseur pour turbomachine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2858104A (en) * 1954-02-04 1958-10-28 A V Roe Canada Ltd Adjustable gas turbine shroud ring segments
US2942844A (en) * 1952-12-22 1960-06-28 Gen Motors Corp Turbine nozzle
GB856599A (en) * 1958-06-16 1960-12-21 Gen Motors Corp Improvements relating to axial-flow compressors
US4529355A (en) * 1982-04-01 1985-07-16 Rolls-Royce Limited Compressor shrouds and shroud assemblies
US5288206A (en) * 1991-11-20 1994-02-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Turbo aero engine equipped with means facilitating adjustment of plays of the stator and between the stator and rotor

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2623728A (en) * 1945-01-16 1952-12-30 Power Jets Res & Dev Ltd Mounting of blades in compressors, turbines, and the like
US2693904A (en) * 1950-11-14 1954-11-09 A V Roe Canada Ltd Air bleed for compressors
US2834537A (en) * 1954-01-18 1958-05-13 Ryan Aeronautical Co Compressor stator structure
GB2078309B (en) * 1980-05-31 1983-05-25 Rolls Royce Mounting nozzle guide vane assemblies
FR2685936A1 (fr) * 1992-01-08 1993-07-09 Snecma Dispositif de controle des jeux d'un carter de compresseur de turbomachine.
US5299910A (en) * 1992-01-23 1994-04-05 General Electric Company Full-round compressor casing assembly in a gas turbine engine
US5288208A (en) * 1993-06-01 1994-02-22 Cummins Richard L Marine propeller block apparatus
US5462403A (en) * 1994-03-21 1995-10-31 United Technologies Corporation Compressor stator vane assembly
US6341938B1 (en) * 2000-03-10 2002-01-29 General Electric Company Methods and apparatus for minimizing thermal gradients within turbine shrouds

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2942844A (en) * 1952-12-22 1960-06-28 Gen Motors Corp Turbine nozzle
US2858104A (en) * 1954-02-04 1958-10-28 A V Roe Canada Ltd Adjustable gas turbine shroud ring segments
GB856599A (en) * 1958-06-16 1960-12-21 Gen Motors Corp Improvements relating to axial-flow compressors
US4529355A (en) * 1982-04-01 1985-07-16 Rolls-Royce Limited Compressor shrouds and shroud assemblies
US5288206A (en) * 1991-11-20 1994-02-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Turbo aero engine equipped with means facilitating adjustment of plays of the stator and between the stator and rotor

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7789619B2 (en) 2006-03-30 2010-09-07 Snecma Device for attaching ring sectors around a turbine rotor of a turbomachine
FR2899274A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine d'une turbomachine
EP1840339A1 (de) * 2006-03-30 2007-10-03 Snecma Vorrichtung zur Befestigung von Ringsektoren um ein Turbinenlaufrad einer Strömungsmaschine
US8662835B2 (en) 2008-03-19 2014-03-04 Snecma Nozzle for a turbomachine turbine
WO2009118490A3 (fr) * 2008-03-19 2009-11-26 Snecma Distributeur de turbine pour une turbomachine
WO2009118490A2 (fr) * 2008-03-19 2009-10-01 Snecma Distributeur de turbine pour une turbomachine
FR2928963A1 (fr) * 2008-03-19 2009-09-25 Snecma Sa Distributeur de turbine pour une turbomachine.
FR2944554A1 (fr) * 2009-04-16 2010-10-22 Snecma Turbine haute-pression de turbomachine
FR2981602A1 (fr) * 2011-10-25 2013-04-26 Snecma Propulsion Solide Procede de fabrication d'un secteur de distributeur de turbine ou redresseur de compresseur en materiau composite pour turbomachine et turbine ou compresseur incorporant un distributeur ou un redresseur forme de tels secteurs
WO2013060977A3 (fr) * 2011-10-25 2013-08-08 Herakles Procede de fabrication d'un secteur de distributeur de turbine ou redresseur de compresseur en materiau composite pour turbomachine
US9784113B2 (en) 2011-10-25 2017-10-10 Herakles Method of fabricating a turbine or compressor guide vane sector made of composite material for a turbine engine, and a turbine or a compressor incorporating such guide vane sectors
EP2896796A1 (de) * 2014-01-20 2015-07-22 Techspace Aero S.A. Stator einer axialen Strömungsmaschine und zugehörige Strömungsmaschine
FR3083564A1 (fr) * 2018-07-05 2020-01-10 Safran Aircraft Engines Turbine comportant un element abradable a position radiale ajustable

Also Published As

Publication number Publication date
MA25948A1 (fr) 2003-12-31
US7290982B2 (en) 2007-11-06
FR2835563B1 (fr) 2004-04-02
JP2003269111A (ja) 2003-09-25
CN1443927A (zh) 2003-09-24
DE60302077T2 (de) 2006-07-20
DE60302077D1 (de) 2005-12-08
CN100357569C (zh) 2007-12-26
CA2418357A1 (en) 2003-08-07
UA76424C2 (uk) 2006-08-15
FR2835563A1 (fr) 2003-08-08
JP4087720B2 (ja) 2008-05-21
ES2250844T3 (es) 2006-04-16
RU2311539C2 (ru) 2007-11-27
CA2418357C (en) 2010-10-26
US20050042081A1 (en) 2005-02-24
EP1335113B1 (de) 2005-11-02
US20030146578A1 (en) 2003-08-07

Similar Documents

Publication Publication Date Title
EP1335113B1 (de) Befestiganordnung für den Statorring einer Turbomaschine
CA2518355C (fr) Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz
EP1607582B1 (de) Aufhängung einer Gasturbinenbrennkammer mit integriertem Turbinenleitapparat
EP0463955B1 (de) Befestigung eines Kranzes an einem Turbinenlaufrad
EP0356305B1 (de) An einem Turbinengehäuse befestigter Statorring
CA2457892C (fr) Carter de stator de turbomachine
EP3180497B1 (de) Turbomaschinenmodul
EP2060750B1 (de) Turbinen- oder Kompressorstufe, insbesondere eines Turbotriebwerks
EP1199444B1 (de) Anordnung zur Verbindung eines Statorrings an einen Stützträger
FR2641031A1 (de)
CA2398319C (fr) Flasque de disque aubage de rotor et agencement correspondant
EP1811131B1 (de) Anordnung von Statorsektoren für einen Verdichter eines Turbotriebwerks
FR2882578A1 (fr) Dispositif de reglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine
EP3591178A1 (de) Abdichtungsmodul für turbotriebwerk eines luftfahrzeugs
FR2889863A1 (fr) Compresseur comportant une pluralite de caissons reconstituant un volume annulaire de separation de flux dans une turbomachine.
WO2012020195A1 (fr) Dispositif de blocage d'un pied d'une aube de rotor
FR3010154A1 (fr) Panneau d'etancheite de carter intermediaire de turbomachine d'aeronef a double flux
EP1329589B1 (de) Rotorkonfiguration für eine Turbomaschine
FR2535389A1 (fr) Dispositif de montage, sur leur disque porteur, d'aubes profilees pour compresseur ou turbine
FR3071273A1 (fr) Ensemble d'etancheite de turbine pour turbomachine
FR2927685A1 (fr) Ensemble de bague d'etancheite et moteur a turbine comportant un tel ensemble
CA2644312C (fr) Etage de turbine ou de compresseur de turbomachine
EP3880940B1 (de) Vorrichtung zur rotationszentrierung und -führung eines rotierenden teils mit verschränkten armen
FR2710103A1 (fr) Flasque de rotor de turbomachine et assemblage de ce flasque avec un rotor.
FR3063117A1 (fr) Raccordement entre une virole circulaire et un bras radial de structure d'une turbomachine, comprenant un joint d'etancheite et son support

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

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: 20040115

AKX Designation fees paid

Designated state(s): DE ES FR GB IT SE

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

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

Owner name: SNECMA

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE ES FR GB IT SE

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: 60302077

Country of ref document: DE

Date of ref document: 20051208

Kind code of ref document: P

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

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

Effective date: 20060130

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2250844

Country of ref document: ES

Kind code of ref document: T3

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: 20060803

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

Ref country code: ES

Payment date: 20130207

Year of fee payment: 11

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20150731

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

Ref country code: ES

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

Effective date: 20140206

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

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: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170719

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

Ref country code: GB

Payment date: 20220124

Year of fee payment: 20

Ref country code: DE

Payment date: 20220119

Year of fee payment: 20

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

Ref country code: SE

Payment date: 20220120

Year of fee payment: 20

Ref country code: IT

Payment date: 20220119

Year of fee payment: 20

Ref country code: FR

Payment date: 20220119

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 60302077

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20230204

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

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 EXPIRATION OF PROTECTION

Effective date: 20230204