EP0893577A1 - Kühlvorrichtung für einen Abdeckring in einer Turbomaschine - Google Patents

Kühlvorrichtung für einen Abdeckring in einer Turbomaschine Download PDF

Info

Publication number
EP0893577A1
EP0893577A1 EP98401872A EP98401872A EP0893577A1 EP 0893577 A1 EP0893577 A1 EP 0893577A1 EP 98401872 A EP98401872 A EP 98401872A EP 98401872 A EP98401872 A EP 98401872A EP 0893577 A1 EP0893577 A1 EP 0893577A1
Authority
EP
European Patent Office
Prior art keywords
wall
cover
ring
holes
orifices
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
EP98401872A
Other languages
English (en)
French (fr)
Other versions
EP0893577B1 (de
Inventor
Daniel Jean Marey
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0893577A1 publication Critical patent/EP0893577A1/de
Application granted granted Critical
Publication of EP0893577B1 publication Critical patent/EP0893577B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the subject of the invention is a device for ventilating a turbomachine ring.
  • the problem we are trying to solve here is the machine yield loss that the subtraction of the induced ventilation flow: on seeks to limit this flow to the minimum necessary for a good ventilation.
  • the solution chosen consists of arrange in the room behind the ring, and in which the gas supply duct opens, a annular distributor comprising a pierced wall holes and a cover placed between the wall and the conduit and pierced with other orifices, intended for restrict the flow of gas; these holes of lids are fewer and have a section total smaller than the holes in the wall.
  • a stator 1 of a turbomachine is equipped spacers 2 (only one of which is shown) intended to support as many 3 rings which contribute to delimit the gas flow stream of the machine in front of circular stages of moving rotor blades 4.
  • the subject of the invention is an annular housing 5 composed of a cover 6 and a wall 7.
  • the housing 5 is housed in a room 8 delimited by the spacer 2 and the ring 3, and it cuts it between this and the outlet 9 of a gas supply circuit relatively fresh from the bottom of the combustion; the rest of the power circuit is not shown because it is not original, but we may refer to French patent 2,416,345 cited higher for more detail.
  • the integrity of the case 5 is ensured by providing the cover 6 and the wall 7 lateral edges 10 and 11 circular and likewise diameter which are joined in pairs by welds, rivets or other means; the side edges 11 of the wall 7 are also fixed to the spacer 2.
  • the wall 7 is foraminated, that is to say pierced with numerous orifices 12, here substantially more long as wide thanks to their finesse and fairly large wall thickness 7.
  • the cover 6 is pierced by other holes 13, less numerous than those 12 of wall 7 but whose cross section opening hours is also quite small. They are established at the top of projections 14 obtained by pushing back the material of the cover 6 towards the outside of the case 5 and whose shape is more or less conical so that the orifices 13 communicate with the interior of the housing 5 by pavilions 15 opening towards the wall 7.
  • the gas entering chamber 8 accumulates in front of the housing 5 and passes through the holes 13 then 12 to come and lick the ring 3 before being evacuated in the gas flow stream passing through holes 16 drilled through the ring 3.
  • the constitution of orifices 13 precisely calibrated allows to restrict the gas flow through them without excessively reducing the flow load thanks to the flared shape of the pavilions 15.
  • the projections 14 can however be oriented to favor the mean direction of gas flow in the box 5 to one region or the other of the wall 7.
  • the gas flow is therefore distributed properly in the housing 5 and flows out through the orifices 12, who distribute it by directing it with precision and with the desired spatial distribution towards different portions of the ring 3.
  • the density and direction of the orifices 12 can therefore vary over the wall 7.
  • the conception of the invention is certainly applicable to other parts of the machine than the high pressure turbine rings, and it can also be used with charged gases to warm up the structure on which they are blown.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Motor Or Generator Cooling System (AREA)
EP98401872A 1997-07-24 1998-07-23 Kühlvorrichtung für einen Abdeckring in einer Turbomaschine Expired - Lifetime EP0893577B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9709399A FR2766517B1 (fr) 1997-07-24 1997-07-24 Dispositif de ventilation d'un anneau de turbomachine
FR9709399 1997-07-24

Publications (2)

Publication Number Publication Date
EP0893577A1 true EP0893577A1 (de) 1999-01-27
EP0893577B1 EP0893577B1 (de) 2003-08-27

Family

ID=9509567

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98401872A Expired - Lifetime EP0893577B1 (de) 1997-07-24 1998-07-23 Kühlvorrichtung für einen Abdeckring in einer Turbomaschine

Country Status (6)

Country Link
US (1) US5964575A (de)
EP (1) EP0893577B1 (de)
JP (1) JP3808211B2 (de)
CA (1) CA2243333C (de)
DE (1) DE69817477T2 (de)
FR (1) FR2766517B1 (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1489265A3 (de) * 2003-06-19 2007-09-19 General Electric Company Methode und Einrichtung um Turbinenleitschaufeln mit Kühlmittel zu versorgen
EP2093384A3 (de) * 2008-02-24 2012-05-30 United Technologies Corporation Filtersystem für eine Außendichtung einer Turbinenschaufel
EP2657462A1 (de) * 2012-04-25 2013-10-30 General Electric Company Turbinenkühlsystem
WO2016028310A1 (en) * 2014-08-22 2016-02-25 Siemens Aktiengesellschaft Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines
EP3219932A1 (de) * 2016-03-16 2017-09-20 United Technologies Corporation Äussere laufschaufelluftdichtung mit strömungsführungsverteiler
EP3628818B1 (de) * 2018-09-25 2026-01-07 RTX Corporation Prallkühlung für eine gasturbinenmotorkomponente

Families Citing this family (60)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6139257A (en) * 1998-03-23 2000-10-31 General Electric Company Shroud cooling assembly for gas turbine engine
FR2780443B1 (fr) * 1998-06-25 2000-08-04 Snecma Anneau de stator de turbine haute pression d'une turbomachine
JP2001221065A (ja) * 2000-02-10 2001-08-17 General Electric Co <Ge> ガスタービンシュラウドのインピンジメント冷却
US6390769B1 (en) * 2000-05-08 2002-05-21 General Electric Company Closed circuit steam cooled turbine shroud and method for steam cooling turbine shroud
FR2816352B1 (fr) * 2000-11-09 2003-01-31 Snecma Moteurs Ensemble de ventilation d'un anneau de stator
FR2819010B1 (fr) * 2001-01-04 2004-05-28 Snecma Moteurs Secteur d'entretoise de support d'anneau de stator de la turbine haute pression d'une turbomachine avec rattrapage de jeux
EP1247943A1 (de) * 2001-04-04 2002-10-09 Siemens Aktiengesellschaft Formstück zur Bildung eines kühlbaren Turbinen-Mantelrings
US6508620B2 (en) 2001-05-17 2003-01-21 Pratt & Whitney Canada Corp. Inner platform impingement cooling by supply air from outside
KR100444854B1 (ko) * 2001-08-16 2004-08-18 현대자동차주식회사 터보차저의 터빈 블레이드 냉각 구조
EP1400751A1 (de) * 2002-09-17 2004-03-24 Siemens Aktiengesellschaft Brennkammer für eine Gasturbine
ITMI20022418A1 (it) * 2002-11-15 2004-05-16 Nuovo Pignone Spa Assieme migliorato di cassa interna a dispositivo di
US6997673B2 (en) * 2003-12-11 2006-02-14 Honeywell International, Inc. Gas turbine high temperature turbine blade outer air seal assembly
FR2867224B1 (fr) * 2004-03-04 2006-05-19 Snecma Moteurs Dispositif de maintien axial de secteur d'entretoise pour anneau d'une turbine haute-pression de turbomachine
FR2868125B1 (fr) * 2004-03-26 2006-07-21 Snecma Moteurs Sa Turbomachine comprenant deux sous-ensembles assembles sous contrainte axiale
US7118326B2 (en) * 2004-06-17 2006-10-10 Siemens Power Generation, Inc. Cooled gas turbine vane
US7097418B2 (en) * 2004-06-18 2006-08-29 Pratt & Whitney Canada Corp. Double impingement vane platform cooling
DE102005013797A1 (de) * 2005-03-24 2006-09-28 Alstom Technology Ltd. Wärmestausegment
DE102005013796A1 (de) * 2005-03-24 2006-09-28 Alstom Technology Ltd. Wärmestausegment
US20070009349A1 (en) * 2005-07-11 2007-01-11 General Electric Company Impingement box for gas turbine shroud
US7491029B2 (en) 2005-10-14 2009-02-17 United Technologies Corporation Active clearance control system for gas turbine engines
US20070249823A1 (en) * 2006-04-20 2007-10-25 Chemagis Ltd. Process for preparing gemcitabine and associated intermediates
US7607885B2 (en) * 2006-07-31 2009-10-27 General Electric Company Methods and apparatus for operating gas turbine engines
FR2907841B1 (fr) * 2006-10-30 2011-04-15 Snecma Secteur d'anneau de turbine de turbomachine
US7665962B1 (en) 2007-01-26 2010-02-23 Florida Turbine Technologies, Inc. Segmented ring for an industrial gas turbine
US7597533B1 (en) 2007-01-26 2009-10-06 Florida Turbine Technologies, Inc. BOAS with multi-metering diffusion cooling
US8439629B2 (en) * 2007-03-01 2013-05-14 United Technologies Corporation Blade outer air seal
US8100633B2 (en) * 2008-03-11 2012-01-24 United Technologies Corp. Cooling air manifold splash plates and gas turbines engine systems involving such splash plates
US8092146B2 (en) * 2009-03-26 2012-01-10 Pratt & Whitney Canada Corp. Active tip clearance control arrangement for gas turbine engine
FR2955891B1 (fr) * 2010-02-02 2012-11-16 Snecma Secteur d'anneau de turbine de turbomachine
FR2972483B1 (fr) * 2011-03-07 2013-04-19 Snecma Carter de turbine comportant des moyens de fixation de secteurs d'anneau
US8998565B2 (en) * 2011-04-18 2015-04-07 General Electric Company Apparatus to seal with a turbine blade stage in a gas turbine
US9080458B2 (en) 2011-08-23 2015-07-14 United Technologies Corporation Blade outer air seal with multi impingement plate assembly
US8840370B2 (en) 2011-11-04 2014-09-23 General Electric Company Bucket assembly for turbine system
US9726043B2 (en) 2011-12-15 2017-08-08 General Electric Company Mounting apparatus for low-ductility turbine shroud
US9127549B2 (en) * 2012-04-26 2015-09-08 General Electric Company Turbine shroud cooling assembly for a gas turbine system
DE102012016493A1 (de) * 2012-08-21 2014-02-27 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit prallgekühlten Bolzen der Brennkammerschindeln
CN103775139B (zh) * 2012-10-26 2015-09-23 中航商用航空发动机有限责任公司 涡轮发动机的间隙控制系统及涡轮发动机的间隙控制方法
EP2728255A1 (de) * 2012-10-31 2014-05-07 Alstom Technology Ltd Heißgas-Segmentanordnung
CN103161520A (zh) * 2013-03-01 2013-06-19 哈尔滨汽轮机厂有限责任公司 一种中低热值燃机第一级涡轮护环装置及其拆卸方法
FR3002971B1 (fr) * 2013-03-06 2015-04-17 Snecma Dispositif de ventilation d'un carter de stator d'une turbomachine, comprenant un ajustement sur des circonferences
FR3002972B1 (fr) * 2013-03-06 2015-04-17 Snecma Dispositif de ventilation d'un carter de stator d'une turbomachine comprenant un ajustement en direction axiale
US20140271154A1 (en) * 2013-03-14 2014-09-18 General Electric Company Casing for turbine engine having a cooling unit
CA2912428C (en) 2013-05-17 2018-03-13 General Electric Company Cmc shroud support system of a gas turbine
EP3080403B1 (de) 2013-12-12 2019-05-01 General Electric Company Trägersystem für cmc-mantel
WO2015138027A2 (en) * 2013-12-17 2015-09-17 United Technologies Corporation Meter plate for blade outer air seal
WO2016025054A2 (en) * 2014-05-29 2016-02-18 General Electric Company Engine components with cooling features
CA2951638A1 (en) 2014-06-12 2015-12-17 General Electric Company Shroud hanger assembly
CA2951425C (en) 2014-06-12 2019-12-24 General Electric Company Shroud hanger assembly
CN106460543B (zh) 2014-06-12 2018-12-21 通用电气公司 多件式护罩悬挂器组件
US9874104B2 (en) 2015-02-27 2018-01-23 General Electric Company Method and system for a ceramic matrix composite shroud hanger assembly
US11193386B2 (en) * 2016-05-18 2021-12-07 Raytheon Technologies Corporation Shaped cooling passages for turbine blade outer air seal
US10626751B2 (en) * 2017-05-30 2020-04-21 United Technologies Corporation Turbine cooling air metering arrangement
US10612406B2 (en) * 2018-04-19 2020-04-07 United Technologies Corporation Seal assembly with shield for gas turbine engines
FR3082872B1 (fr) * 2018-06-25 2021-06-04 Safran Aircraft Engines Dispositif de refroidissement d'un carter de turbomachine
US10914186B2 (en) * 2018-12-05 2021-02-09 Raytheon Technologies Corporation BOAS control structure with center support hook
US10830050B2 (en) * 2019-01-31 2020-11-10 General Electric Company Unitary body turbine shrouds including structural breakdown and collapsible features
US11761343B2 (en) * 2019-03-13 2023-09-19 Rtx Corporation BOAS carrier with dovetail attachments
US11248482B2 (en) * 2019-07-19 2022-02-15 Raytheon Technologies Corporation CMC BOAS arrangement
US11035248B1 (en) 2019-11-25 2021-06-15 General Electric Company Unitary body turbine shrouds including shot peen screens integrally formed therein and turbine systems thereof
FR3108367B1 (fr) * 2020-03-20 2023-07-21 Safran Aircraft Engines Ensemble de turbine et turbomachine munie d’un tel ensemble

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2407343A1 (fr) * 1977-10-31 1979-05-25 Gen Electric Turbomachine comprenant un dispositif d'etancheite et de support ameliore
US5048288A (en) * 1988-12-20 1991-09-17 United Technologies Corporation Combined turbine stator cooling and turbine tip clearance control
EP0515130A1 (de) * 1991-05-20 1992-11-25 General Electric Company Konischer Dosierkanal für gekühltes Gasturbinendeckband

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3703808A (en) * 1970-12-18 1972-11-28 Gen Electric Turbine blade tip cooling air expander
US3825364A (en) * 1972-06-09 1974-07-23 Gen Electric Porous abradable turbine shroud
US3844343A (en) * 1973-02-02 1974-10-29 Gen Electric Impingement-convective cooling system
GB2116639B (en) * 1982-03-05 1985-11-20 Rolls Royce Turbine shroud segments and turbine shroud assembly

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2407343A1 (fr) * 1977-10-31 1979-05-25 Gen Electric Turbomachine comprenant un dispositif d'etancheite et de support ameliore
US5048288A (en) * 1988-12-20 1991-09-17 United Technologies Corporation Combined turbine stator cooling and turbine tip clearance control
EP0515130A1 (de) * 1991-05-20 1992-11-25 General Electric Company Konischer Dosierkanal für gekühltes Gasturbinendeckband

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1489265A3 (de) * 2003-06-19 2007-09-19 General Electric Company Methode und Einrichtung um Turbinenleitschaufeln mit Kühlmittel zu versorgen
EP2093384A3 (de) * 2008-02-24 2012-05-30 United Technologies Corporation Filtersystem für eine Außendichtung einer Turbinenschaufel
US8439639B2 (en) 2008-02-24 2013-05-14 United Technologies Corporation Filter system for blade outer air seal
EP2657462A1 (de) * 2012-04-25 2013-10-30 General Electric Company Turbinenkühlsystem
CN103375204A (zh) * 2012-04-25 2013-10-30 通用电气公司 涡轮冷却系统
WO2016028310A1 (en) * 2014-08-22 2016-02-25 Siemens Aktiengesellschaft Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines
US9963996B2 (en) 2014-08-22 2018-05-08 Siemens Aktiengesellschaft Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines
EP3219932A1 (de) * 2016-03-16 2017-09-20 United Technologies Corporation Äussere laufschaufelluftdichtung mit strömungsführungsverteiler
US10337346B2 (en) 2016-03-16 2019-07-02 United Technologies Corporation Blade outer air seal with flow guide manifold
EP3628818B1 (de) * 2018-09-25 2026-01-07 RTX Corporation Prallkühlung für eine gasturbinenmotorkomponente

Also Published As

Publication number Publication date
FR2766517A1 (fr) 1999-01-29
FR2766517B1 (fr) 1999-09-03
JP3808211B2 (ja) 2006-08-09
DE69817477T2 (de) 2004-06-09
EP0893577B1 (de) 2003-08-27
JPH1181907A (ja) 1999-03-26
CA2243333A1 (en) 1999-01-24
DE69817477D1 (de) 2003-10-02
US5964575A (en) 1999-10-12
CA2243333C (en) 2007-11-06

Similar Documents

Publication Publication Date Title
EP0893577B1 (de) Kühlvorrichtung für einen Abdeckring in einer Turbomaschine
EP1134360B1 (de) Verstellvorrichtung für den Durchmesser des Stators eines Gasturbinenwerks
EP1164253B1 (de) Kühlungssystem für die Abdeckplatten von Rotorschaufelpaaren
EP1251243B1 (de) Turbinenschaufel mit Kühlluftleiteinrichtung
FR2690954A1 (fr) Distributeur-collecteur pour le refroidissement du passage central d&#39;un compresseur.
EP2406463B1 (de) Turbinenschaufel mit entstaubungsloch am schaufelfuss
FR2720860A1 (fr) Batterie fonctionnant à température élevée.
FR2502242A1 (fr) Embout rapporte pour aube de rotor
FR2742804A1 (fr) Rotor deshuileur pour enceinte de lubrification
WO2003018962A1 (fr) Carter de stator de turbomachine
EP0942236A1 (de) Dampfofen mit festem Wasserverteiler
EP0785338B1 (de) Kühleinrichtung für eine Turbinenscheibe
EP1211381A1 (de) Deckplatte für eine beschaufelte Rotorscheibe
EP4381175A1 (de) Turbomaschine mit einem austrittskonus mit durch zirkulation eines kühlstroms gekühlten komponenten
FR2630162A1 (fr) Systeme d&#39;antigivrage de cone d&#39;entree pour turbomoteurs a gaz
CA2418241A1 (fr) Aube mobile de turbine haute pression munie d&#39;un bord de fuite au comportement thermique ameliore
WO2020217025A1 (fr) Entrée d&#39;air de nacelle et nacelle comportant une telle entrée d&#39;air
EP2071240B1 (de) Brennkammer eines Turbotriebwerks
EP2031304B1 (de) Abscheider für die Zuführung von Kühlluft an eine Turbine
EP0165167B1 (de) Strahlmisch- und -umlenkvorrichtung zur Infrarotunterdrückung bei Turbomotoren
CA2211428C (fr) Agencement et procede de reglage de diametre d&#39;anneau de stator
EP0447320B1 (de) Turbinenleitschaufelinnenkühlungssystem
EP1867928B1 (de) Dampfbackofen
EP0878672B1 (de) Belüftungssystem mit Lufteinspritzung für einen besseren Zug
FR2557205A1 (fr) Rotor avec refroidissement a double passe des talons des aubes

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: 19980810

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

AX Request for extension of the european patent

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

AKX Designation fees paid

Free format text: DE FR GB

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

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

Owner name: SNECMA MOTEURS

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

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: 69817477

Country of ref document: DE

Date of ref document: 20031002

Kind code of ref document: P

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

Effective date: 20031006

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: 20040528

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 18

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

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: 20170427

Year of fee payment: 20

Ref country code: GB

Payment date: 20170620

Year of fee payment: 20

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

Ref country code: DE

Payment date: 20170620

Year of fee payment: 20

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170719

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 69817477

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20180722

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: 20180722