EP0373984A1 - Brennkammer einer Gasturbine mit einem gleitend montierten Vorverdampfer - Google Patents

Brennkammer einer Gasturbine mit einem gleitend montierten Vorverdampfer Download PDF

Info

Publication number
EP0373984A1
EP0373984A1 EP89403135A EP89403135A EP0373984A1 EP 0373984 A1 EP0373984 A1 EP 0373984A1 EP 89403135 A EP89403135 A EP 89403135A EP 89403135 A EP89403135 A EP 89403135A EP 0373984 A1 EP0373984 A1 EP 0373984A1
Authority
EP
European Patent Office
Prior art keywords
support flange
bowl
combustion chamber
ferrule
elastic means
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
EP89403135A
Other languages
English (en)
French (fr)
Other versions
EP0373984B1 (de
Inventor
François Duchene
Alexandre Forestier
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 EP0373984A1 publication Critical patent/EP0373984A1/de
Application granted granted Critical
Publication of EP0373984B1 publication Critical patent/EP0373984B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances

Definitions

  • turbomachinery in particular aviation turbojets, are equipped with annular combustion chambers and comprise, arranged between the fuel injectors and the combustion chamber proper, fuel pre-vaporization bowls.
  • pre-vaporization bowls examples are given in the following French documents or in the corresponding American documents indicated in brackets, all in the name of the applicant.
  • FR-A-2,572,463 (US-A-4,726,182); FR-A-2,585,770; FR-A-2,588,919 (US-A-4,696,157); FR-A-2 596 102 (US-A-4 754 600) and reference may be made to these documents for the details of construction of these devices.
  • the bowls must therefore be mounted floating radially with respect to the chamber and axially with respect to the injectors.
  • Such floating arrangements are known from documents US 4 322 945, FR-A-1 547 843 or FR-A-2 479 952.
  • turbojets are designed to modularly and the assembly sequence of the combustion chambers is carried out by assembling the chamber equipped with its pre-vaporization bowls, inside the chamber casing, itself equipped with its injectors. This assembly is carried out with the engine in a horizontal position.
  • the radial mobility of the bowls on the chamber means that they take by gravity, a low position eccentric by several millimeters relative to their theoretical axis.
  • the present invention aims to avoid this type of risk during assembly while retaining the bowls the possibility of sliding radially in their housing and absorbing in operation the relative movements between chamber and injectors.
  • the invention therefore relates to a combustion chamber for turbomachines, comprising between the injector heads and the chamber bottom of the pre-vaporization bowls mounted radially floating between a support flange secured to the cut-out of the cup and a stop ring welded after mounting the bowl, on said support flange.
  • a mounting ferrule integral with the bowl is disposed between the support flange and the stop ring and elastic means for radial positioning of the bowl, capable of centering said bowl in the support flange, during assembly. injectors, are interposed radially between said mounting ferrule and the support flange.
  • FIG. 1 an annular combustion chamber has been shown, the inner 1 and outer 2 walls of which appear.
  • On the dome 3 of the chamber bottom are pierced circular openings 4 inside which are fixed circular support flanges 5 comprising a downstream cylindrical part 5a, welded externally to inside the opening 4, an upstream cylindrical part 5b inside which a stop ring 6 will be mounted, the two cylindrical parts 5a and 5b of different diameters being connected by a flat central part 5c.
  • the pre-vaporization bowl 7 has an internal ferrule 7a and an external ferrule 7b, separated upstream by fins 8 forming a swirl swirl for the pre-vaporization air.
  • the two ferrules 7a and 7b form a frustoconical passage 7c downstream of which the ferrule 7b flares in frustoconical veil 7d forming the bowl proper.
  • a cylindrical outer wall 7e is welded to the downstream edge of this veil 7d.
  • a mounting ring 9 On the outer edge of the 7th wall is welded a mounting ring 9 whose cross section is square.
  • the ferrule therefore comprises a cylindrical part 9a and a flat part 9b.
  • a tongue 9c extends radially on the outer edge of the flat part 9d of the mounting ring 9.
  • the tongue passes through a notch 5d of the cylindrical part 5b of the support flange so that the bowl can slide radially along the axis XX ′ of the support flange, said diameter being coincident with the diameter of the chamber which carries the center O of the bowl.
  • an elastic ring 10 in the form of an arc of a circle with a radius of curvature greater than those of the ferrule and the support flange is kept in tension between the support flange 5 and the ferrule of mounting 9 in the clearance left free between the outer edge of the part 9b of said ferrule and the inside of the flange 5.
  • Each of the ends of the rod 10 has a bulge 10a which is embedded in a cutout 5e of the part cylindrical 5b of the flange 5.
  • the two cutouts 5e are symmetrical with respect to the diameter XX ′ of the flange, so that the rod applies a force oriented towards the center O of the device.
  • the stop ring 6 is then welded inside the support flange 5 so that the only clearance left at the ferrule 9 and therefore at the bowl 7, ie a radial clearance.
  • the rod 10 is made of an alloy with high hot elasticity such as the nickel-based superalloy NC 15 Fe T (NF standard) known under the commercial name Inconel X 750 and comprising 15% CR; 7% Fe; 2.4% Ti, remains nickel in a strain-hardened form 30 to 55%, quenched and returned so that the rod 10 retains its spring elasticity in the temperature range of use of the combustion chamber.
  • NC 15 Fe T NF standard
  • Such a combustion chamber comprising pre-spraying bowls regularly distributed over its circumference has the support flanges of its bowls oriented so that their tongues 9c as well as the direction of action of the force exerted by the elastic means are radial as well as the shows figure 7.
  • the injector 11 As for the injector 11, it is mounted without radial clearance but floating axially inside the internal ferrule 7a of the bowl 7.
  • the entire bowl equipped with its ferrule 7 is in the position of FIGS. 1, 2 and 7, that is to say centered on the axis of the opening 4 at the bottom of the chamber and the chamber equipped of its bowls can be mounted without risks inside the housing fitted with its injectors 11.
  • the bowl can freely move radially between the extreme "high” position in FIGS. 3 and 4 (expansion of the chamber relative to the casing) and the extreme "low” position in FIGS. 5 and 6 (removal of the room after expansion).
  • the invention therefore provides a definite advantage in mounting such combustion chambers with pre-vaporization bowls.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Fuel-Injection Apparatus (AREA)
EP89403135A 1988-11-17 1989-11-15 Brennkammer einer Gasturbine mit einem gleitend montierten Vorverdampfer Expired - Lifetime EP0373984B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8814915 1988-11-17
FR8814915A FR2639095B1 (fr) 1988-11-17 1988-11-17 Chambre de combustion de turbomachine a bols de prevaporisation montes flottants

Publications (2)

Publication Number Publication Date
EP0373984A1 true EP0373984A1 (de) 1990-06-20
EP0373984B1 EP0373984B1 (de) 1993-03-31

Family

ID=9371916

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89403135A Expired - Lifetime EP0373984B1 (de) 1988-11-17 1989-11-15 Brennkammer einer Gasturbine mit einem gleitend montierten Vorverdampfer

Country Status (4)

Country Link
US (1) US4999996A (de)
EP (1) EP0373984B1 (de)
DE (1) DE68905779T2 (de)
FR (1) FR2639095B1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2678715A1 (fr) * 1991-07-03 1993-01-08 Snecma Bol de chambre de combustion pour injection aerodynamique.
WO1995018336A1 (en) * 1993-12-27 1995-07-06 United Technologies Corporation Ignitor plug guide for a gas turbine engine combustor
EP1826492A1 (de) 2006-02-27 2007-08-29 Snecma Anordnung für eine Brennkammer einer Turbine
WO2015030928A1 (en) 2013-08-30 2015-03-05 United Technologies Corporation Swirler mount interface for a gas turbine engine combustor
WO2018060590A1 (fr) 2016-09-29 2018-04-05 Safran Helicopter Engines Dispositif d'alimentation en carburant d'une chambre de combustion de turbomachine améliorant l'homogénéité de l'alimentation des dispositifs d'injection du carburant

Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2662784B1 (fr) * 1990-06-05 1992-08-14 Snecma Ensemble d'injection pour turbomachine, comprenant un bol de prevaporisation.
US5117637A (en) * 1990-08-02 1992-06-02 General Electric Company Combustor dome assembly
US5165241A (en) * 1991-02-22 1992-11-24 General Electric Company Air fuel mixer for gas turbine combustor
FR2679010B1 (fr) * 1991-07-10 1993-09-24 Snecma Chambre de combustion de turbomachine a bols de prevaporisation demontables.
US5309709A (en) * 1992-06-25 1994-05-10 Solar Turbines Incorporated Low emission combustion system for a gas turbine engine
US5218824A (en) * 1992-06-25 1993-06-15 Solar Turbines Incorporated Low emission combustion nozzle for use with a gas turbine engine
US5285632A (en) * 1993-02-08 1994-02-15 General Electric Company Low NOx combustor
US5404711A (en) * 1993-06-10 1995-04-11 Solar Turbines Incorporated Dual fuel injector nozzle for use with a gas turbine engine
US5463864A (en) * 1993-12-27 1995-11-07 United Technologies Corporation Fuel nozzle guide for a gas turbine engine combustor
DE19515537A1 (de) * 1995-04-27 1996-10-31 Bmw Rolls Royce Gmbh Kopfteil einer Gasturbinen-Ringbrennkammer
US6032457A (en) * 1996-06-27 2000-03-07 United Technologies Corporation Fuel nozzle guide
US5916142A (en) * 1996-10-21 1999-06-29 General Electric Company Self-aligning swirler with ball joint
US5974805A (en) * 1997-10-28 1999-11-02 Rolls-Royce Plc Heat shielding for a turbine combustor
US6334298B1 (en) * 2000-07-14 2002-01-01 General Electric Company Gas turbine combustor having dome-to-liner joint
US6497105B1 (en) 2001-06-04 2002-12-24 Pratt & Whitney Canada Corp. Low cost combustor burner collar
US6880341B2 (en) * 2002-12-18 2005-04-19 Pratt & Whitney Canada Corp. Low cost combustor floating collar with improved sealing and damping
US6976363B2 (en) * 2003-08-11 2005-12-20 General Electric Company Combustor dome assembly of a gas turbine engine having a contoured swirler
US7062920B2 (en) * 2003-08-11 2006-06-20 General Electric Company Combustor dome assembly of a gas turbine engine having a free floating swirler
US7051532B2 (en) * 2003-10-17 2006-05-30 General Electric Company Methods and apparatus for film cooling gas turbine engine combustors
US7134286B2 (en) * 2004-08-24 2006-11-14 Pratt & Whitney Canada Corp. Gas turbine floating collar arrangement
US7140189B2 (en) * 2004-08-24 2006-11-28 Pratt & Whitney Canada Corp. Gas turbine floating collar
FR2886714B1 (fr) * 2005-06-07 2007-09-07 Snecma Moteurs Sa Systeme d'injection anti-rotatif pour turbo-reacteur
GB2431225B (en) * 2005-10-15 2008-06-18 Rolls Royce Plc Combustor and component for a combustor
FR2893390B1 (fr) * 2005-11-15 2011-04-01 Snecma Fond de chambre de combustion avec ventilation
US7716931B2 (en) * 2006-03-01 2010-05-18 General Electric Company Method and apparatus for assembling gas turbine engine
FR2903172B1 (fr) * 2006-06-29 2008-10-17 Snecma Sa Agencement pour chambre de combustion de turbomachine ayant un defecteur a collerette
US7926280B2 (en) * 2007-05-16 2011-04-19 Pratt & Whitney Canada Corp. Interface between a combustor and fuel nozzle
FR2928994B1 (fr) 2008-03-19 2010-04-02 Snecma Chambre de combustion de turbomachine.
FR2963061B1 (fr) * 2010-07-26 2012-07-27 Snecma Systeme d?injection de carburant pour turbo-reacteur et procede d?assemblage d?un tel systeme d?injection
GB201321193D0 (en) 2013-12-02 2014-01-15 Rolls Royce Plc A combustion chamber assembly
US10156189B2 (en) 2014-01-28 2018-12-18 Pratt & Whitney Canada Corp. Combustor igniter assembly
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
US11486581B2 (en) * 2020-09-29 2022-11-01 Pratt & Whitney Canada Corp. Fuel nozzle and associated method of assembly

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB710353A (en) * 1951-06-18 1954-06-09 Rolls Royce Improvements in or relating to combustion equipment for gas-turbine engines
US2800768A (en) * 1954-08-19 1957-07-30 United Aircraft Corp Burner construction
US3273343A (en) * 1965-03-08 1966-09-20 Dickens Inc Combustion chamber construction in gas turbine power plant
DE1601632A1 (de) * 1966-05-04 1970-07-16 Rolls Royce Brennkammer fuer Gasturbinenstrahltriebwerke
FR2033912A5 (de) * 1969-02-04 1970-12-04 Gen Electric
FR2479952A1 (fr) * 1980-04-02 1981-10-09 United Technologies Corp Stucture de guidage et d'etancheite d'injecteur de carburant pour une turbine a gaz
GB2135440A (en) * 1983-02-19 1984-08-30 Rolls Royce Mounting combustion chambers

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2509503A (en) * 1946-02-12 1950-05-30 Lucas Ltd Joseph Combustion chamber for prime movers
US3385055A (en) * 1966-11-23 1968-05-28 United Aircraft Corp Combustion chamber with floating swirler rings
US4180972A (en) * 1978-06-08 1980-01-01 General Motors Corporation Combustor support structure
US4322945A (en) * 1980-04-02 1982-04-06 United Technologies Corporation Fuel nozzle guide heat shield for a gas turbine engine
US4454711A (en) * 1981-10-29 1984-06-19 Avco Corporation Self-aligning fuel nozzle assembly
JPS599431A (ja) * 1982-07-09 1984-01-18 Hitachi Ltd ガスタ−ビン燃焼器の支持装置
FR2572463B1 (fr) * 1984-10-30 1989-01-20 Snecma Systeme d'injection a geometrie variable.
FR2588919B1 (fr) * 1985-10-18 1987-12-04 Snecma Dispositif d'injection a bol sectorise
FR2596102B1 (fr) * 1986-03-20 1988-05-27 Snecma Dispositif d'injection a vrille axialo-centripete
US4686823A (en) * 1986-04-28 1987-08-18 United Technologies Corporation Sliding joint for an annular combustor
US4914918A (en) * 1988-09-26 1990-04-10 United Technologies Corporation Combustor segmented deflector

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB710353A (en) * 1951-06-18 1954-06-09 Rolls Royce Improvements in or relating to combustion equipment for gas-turbine engines
US2800768A (en) * 1954-08-19 1957-07-30 United Aircraft Corp Burner construction
US3273343A (en) * 1965-03-08 1966-09-20 Dickens Inc Combustion chamber construction in gas turbine power plant
DE1601632A1 (de) * 1966-05-04 1970-07-16 Rolls Royce Brennkammer fuer Gasturbinenstrahltriebwerke
FR2033912A5 (de) * 1969-02-04 1970-12-04 Gen Electric
FR2479952A1 (fr) * 1980-04-02 1981-10-09 United Technologies Corp Stucture de guidage et d'etancheite d'injecteur de carburant pour une turbine a gaz
GB2135440A (en) * 1983-02-19 1984-08-30 Rolls Royce Mounting combustion chambers

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN, vol. 8, no. 94 (M-293)[1531], 28 avril 1984; & JP-A-59 009 431 (HITACHI SEISAKUSHO K.K.) 18-01-1984 *

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2678715A1 (fr) * 1991-07-03 1993-01-08 Snecma Bol de chambre de combustion pour injection aerodynamique.
WO1995018336A1 (en) * 1993-12-27 1995-07-06 United Technologies Corporation Ignitor plug guide for a gas turbine engine combustor
EP1826492A1 (de) 2006-02-27 2007-08-29 Snecma Anordnung für eine Brennkammer einer Turbine
FR2897922A1 (fr) * 2006-02-27 2007-08-31 Snecma Sa Agencement pour une chambre de combustion de turboreacteur
US7775051B2 (en) 2006-02-27 2010-08-17 Snecma Arrangement for a jet engine combustion chamber
WO2015030928A1 (en) 2013-08-30 2015-03-05 United Technologies Corporation Swirler mount interface for a gas turbine engine combustor
EP3039344A1 (de) * 2013-08-30 2016-07-06 United Technologies Corporation Wirblerhalterungsverbindung für eine gasturbinenbrennkammer
EP3039344A4 (de) * 2013-08-30 2016-09-21 United Technologies Corp Wirblerhalterungsverbindung für eine gasturbinenbrennkammer
WO2018060590A1 (fr) 2016-09-29 2018-04-05 Safran Helicopter Engines Dispositif d'alimentation en carburant d'une chambre de combustion de turbomachine améliorant l'homogénéité de l'alimentation des dispositifs d'injection du carburant

Also Published As

Publication number Publication date
EP0373984B1 (de) 1993-03-31
FR2639095B1 (fr) 1990-12-21
FR2639095A1 (fr) 1990-05-18
DE68905779T2 (de) 1993-09-09
DE68905779D1 (de) 1993-05-06
US4999996A (en) 1991-03-19

Similar Documents

Publication Publication Date Title
EP0373984B1 (de) Brennkammer einer Gasturbine mit einem gleitend montierten Vorverdampfer
EP2917519B1 (de) Aufnahme eines entlüftungsrohr einer turbomachine
CA2509797C (fr) Montage de chambre de combustion de turbine a gaz avec distributeur integre de turbine haute-pression
CA2602141C (fr) Systeme propulsif integre comportant un moteur a turboreacteur a double flux
CA2602176C (fr) Systeme propulsif a pylone integre pour avion
EP2009333B1 (de) Dynamische Bürstendichtung
EP0461026B1 (de) Brennstoffeinspritzvorrichtung mit Vorverdampfer
FR2726789A1 (fr) Systeme de support de liaison pour amortisseur
FR2641031A1 (de)
US4872528A (en) Muffler construction
EP0571244B1 (de) Abdichtungsstruktur für einen schwenkbaren Schaufel einer Turbomaschine
EP4025780B1 (de) Ausstosskonus mit flexibler aerodynamischer befestigung
EP3705686A1 (de) Gehäuse eines turbotriebwerks
FR2997996A1 (fr) Support de tube d'evacuation d'air dans une turbomachine
FR3050229A1 (fr) Carter d'echappement de turbomachine
EP3863928A1 (de) Turbinenmotor mit aufhängungsvorrichtung
FR3051854A1 (fr) Carter d'echappement de turbomachine
CA2582624C (fr) Bras accroche-flammes d'une chambre de post-combustion
EP2178757A1 (de) Triebwerksgondel mit dämpfern für halbschalen
EP2598803A2 (de) Kraftstoffeinspritzsystem für ein tl-triebwerk und verfahren zur montage eines derartigen einspritzsystems
FR2953810A1 (fr) Nacelle de turboreacteur
FR3135754A1 (fr) Supportage d’un stator d’une machine électrique en aval d’une turbine
WO2018002480A1 (fr) Ensemble de fixation d'un distributeur a un element de structure d'une turbomachine
EP3735528B1 (de) Feuerwiderstandsvorrichtung, die dazu bestimmt ist, zwischen einem stromaufwärtigen ende einer flugzeugturbinentriebwerksaufhängungsstruktur und einer verkleidung des turbinentriebwerks, die einen zwischenströmungsraum begrenzt, angeordnet zu werden
FR3114848A1 (fr) Cône d’échappement pour une turbomachine

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: 19891127

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19910717

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

REF Corresponds to:

Ref document number: 68905779

Country of ref document: DE

Date of ref document: 19930506

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

Effective date: 19930413

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: 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

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

Ref country code: FR

Payment date: 20031020

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: 20031112

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: 20040130

Year of fee payment: 15

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: 20041115

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: 20050601

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

Effective date: 20041115

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

Ref country code: FR

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

Effective date: 20050729

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST