[go: up one dir, main page]

EP0191687B1 - Device for varying the cross-section of a turbine stator - Google Patents

Device for varying the cross-section of a turbine stator Download PDF

Info

Publication number
EP0191687B1
EP0191687B1 EP86400191A EP86400191A EP0191687B1 EP 0191687 B1 EP0191687 B1 EP 0191687B1 EP 86400191 A EP86400191 A EP 86400191A EP 86400191 A EP86400191 A EP 86400191A EP 0191687 B1 EP0191687 B1 EP 0191687B1
Authority
EP
European Patent Office
Prior art keywords
flaps
pivoted
flap
downstream
outer casing
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
Application number
EP86400191A
Other languages
German (de)
French (fr)
Other versions
EP0191687A1 (en
Inventor
Gérard Marcel François Mandet
Jacques Henri Mouchel
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
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 filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0191687A1 publication Critical patent/EP0191687A1/en
Application granted granted Critical
Publication of EP0191687B1 publication Critical patent/EP0191687B1/en
Expired 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path

Definitions

  • the present invention relates to a device for varying the section of the neck of a turbine distributor.
  • the upstream flap 5 is supported by its downstream edge 5a against the upstream edge 6a of the downstream flap 6 under the gas pressure.
  • a finger 5b is provided to bear against the upstream edge of the flap 6.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

La présente invention a pour objet un dispositif de variation de section du col d'un distributeur de turbine.The present invention relates to a device for varying the section of the neck of a turbine distributor.

Pour obtenir un gain de poussée dans une turbomachine, il est connu d'utiliser une variation de la section du col de distributeur de la turbine.To obtain a thrust gain in a turbomachine, it is known to use a variation in the section of the distributor neck of the turbine.

Dans ce but, il est connu d'utiliser des dispositifs dans lesquels la variation de section est obtenue par un moyen aérodynamique. Toutefois, ces moyens qui sont en général peu coûteux entraînent des chutes de rendement importantes et des perturbations dans la ventilation des aubes.For this purpose, it is known to use devices in which the section variation is obtained by aerodynamic means. However, these means which are generally inexpensive lead to significant drops in efficiency and disturbances in the ventilation of the blades.

On connaît également des dispositifs de variation de section comportant des moyens mécaniques.There are also known section variation devices comprising mechanical means.

Suivant l'un de ces procédés, on utilise une variation du calage de toute l'aube ou d'une partie de l'aube. Toutefois, ce procédé présente des difficultés provenant de la maîtrise des fuites et des étanchéités insuffisantes.According to one of these methods, a variation of the setting of the whole blade or part of the blade is used. However, this process presents difficulties stemming from the control of leaks and insufficient sealing.

Par FR-E-95 323, on connaît également un procédé dans lequel on utilise une variation de hauteur de la veine. Dans ce but, le dispositif comporte entre les aubes fixes un volet unique monobloc articulé par son bord amont sur le carter externe de distributeur et qui peut occuper une position escamotée et une position pour laquelle le canal est partiellement obturé.From FR-E-95 323, a process is also known in which a variation in the height of the vein is used. For this purpose, the device comprises between the fixed vanes a single monobloc flap articulated by its upstream edge on the external distributor casing and which can occupy a retracted position and a position for which the channel is partially closed.

Toutefois, ce procédé a pour principal défaut de créer des ressauts importants dans la veine, au voisinage des talons des aubes mobiles lorsque les volets sont en position de veine réduite.However, the main defect of this method is that it creates large projections in the vein, in the vicinity of the heels of the movable blades when the flaps are in the reduced vein position.

Le dispositif suivant l'invention de variation de hauteur de la veine a pour objet de remédier à cet inconvénient. Conformément à la présente demande, dans chaque canal prévu entre deux aubes adjacentes et à proximité de la paroi de la veine extérieure, il est prévu deux volets situés à la suite l'un de l'autre et qui sont articulés, l'un, par son bord amont et, l'autre, par son bord aval sur le carter externe du distributeur, l'un des volets amont étant maintenu en appui par la pression des gaz par son bord aval sur le bord amont du volet aval et le volet aval étant articulé par ledit bord amont sur un organe de commande, de telle sorte que, en position « col ouvert", les volets s'escamotent dans l'alignement de la paroi de la veine et, en position « col fermé", le canal est partiellement obturé par lesdits volets.The purpose of the device according to the invention for varying the height of the vein is to remedy this drawback. In accordance with the present application, in each channel provided between two adjacent blades and close to the wall of the external vein, there are provided two flaps located one after the other and which are articulated, one, by its upstream edge and the other by its downstream edge on the external casing of the distributor, one of the upstream flaps being held in abutment by the pressure of the gases by its downstream edge on the upstream edge of the downstream flap and the flap downstream being articulated by said upstream edge on a control member, so that, in the "open neck" position, the flaps retract in alignment with the wall of the vein and, in the "closed neck" position, the channel is partially closed by said flaps.

Dans ce dispositif, seule la plate-forme extérieure des aubes est affectée et la grille d'aubes proprement dite reste fixe.In this device, only the outer platform of the blades is affected and the blade grid itself remains fixed.

Le dispositif de ventilation externe ou interne des aubes et l'architecture des aubes ne subissent pas de répercussion. Le dispositif de commande se trouve à proximité des volets et aucune traversée de zone chaude n'est imposée.The external or internal ventilation system of the blades and the architecture of the blades are not affected. The control device is located near the shutters and no hot zone crossing is imposed.

D'autres caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre d'un mode de réalisation et en se référant aux dessins annexés, sur lesquels :

  • - la figure 1 est une vue en élévation et en coupe longitudinale suivant la ligne I-I de la figure 3 du dispositif de variation de section d'un col de distributeur de turbine suivant l'invention ;
  • - la figure 2 est une vue en coupe longitudinale du dispositif suivant la ligne II-II de la figure 3 ;
  • - la figure 3 est une vue en plan développé suivant la flèche III du distributeur muni du dispositif suivant l'invention ;
  • - la figure 4 est une vue en coupe transversale du dispositif suivant la ligne IV-IV de la figure 3 ;
  • - la figure 5 est une vue en coupe transversale du moyen de commande des volets ;
  • - la figure 6 est une vue en. perspective du moyen de commande des volets.
Other characteristics and advantages of the invention will be better understood on reading the following description of an embodiment and with reference to the appended drawings, in which:
  • - Figure 1 is an elevational view in longitudinal section along line II of Figure 3 of the section variation device of a turbine distributor neck according to the invention;
  • - Figure 2 is a longitudinal sectional view of the device along the line II-II of Figure 3;
  • - Figure 3 is a plan view developed along arrow III of the dispenser provided with the device according to the invention;
  • - Figure 4 is a cross-sectional view of the device along the line IV-IV of Figure 3;
  • - Figure 5 is a cross-sectional view of the shutter control means;
  • - Figure 6 is a view. perspective of the shutter control means.

A la figure 1, on a représenté partiellement un distributeur de turbine comprenant une série d'aubes fixes 1 qui sont solidaires du carter 2 de l'enveloppe extérieure de la turbomachine, ledit distributeur étant situé en amont d'une série d'aubes mobiles 4 de la turbine.In Figure 1, there is partially shown a turbine distributor comprising a series of fixed blades 1 which are integral with the casing 2 of the outer casing of the turbomachine, said distributor being located upstream of a series of movable blades 4 of the turbine.

Entre les aubes 1, il est prévu un espace dans lequel sont disposés deux volets 5, 6 dont l'un 5 est situé en amont et l'autre 6 en aval par rapport au sens de déplacement du fluide. Les volets 5, 6 qui sont situés à la suite l'un de l'autre sont articulés sur une même plate-forme 7, 7a d'une aube 1 (figures 2, 3). A cet effet, la plate-forme 7, 7a comporte une chape fixe 8 sur laquelle est articulé autour d'un axe 9 engagé dans un trou oblong 10a un, bossage 10 prévu sur le bord amont du volet 5.Between the vanes 1, a space is provided in which two flaps 5, 6 are arranged, one of which 5 is located upstream and the other 6 downstream relative to the direction of movement of the fluid. The flaps 5, 6 which are located one after the other are articulated on the same platform 7, 7a of a blade 1 (Figures 2, 3). To this end, the platform 7, 7a includes a fixed yoke 8 on which is articulated around an axis 9 engaged in an oblong hole 10a, a boss 10 provided on the upstream edge of the flap 5.

Sur la figure 3, l'un des espaces entre les aubes 1 correspondant à la plate-forme 7a est représenté sans volets 5, 6, alors que celui correspondant à la plate-forme 7 est représenté avec les volets 5, 6 en place.In Figure 3, one of the spaces between the blades 1 corresponding to the platform 7a is shown without flaps 5, 6, while that corresponding to the platform 7 is shown with the flaps 5, 6 in place.

A sa partie aval, la plate-forme 7, 7a comporte une chape fixe 11 sur laquelle est articulé autour d'un axe 12 un bossage 13 prévu sur le bord aval du volet aval 6.At its downstream part, the platform 7, 7a comprises a fixed yoke 11 on which is articulated around an axis 12 a boss 13 provided on the downstream edge of the downstream flap 6.

Le volet amont 5 est en appui par son bord aval 5a contre le bord amont 6a du volet aval 6 sous la pression des gaz. De plus, il est prévu un doigt 5b en appui contre le bord amont du volet 6.The upstream flap 5 is supported by its downstream edge 5a against the upstream edge 6a of the downstream flap 6 under the gas pressure. In addition, a finger 5b is provided to bear against the upstream edge of the flap 6.

A proximité du bord amont du volet aval 6 (figures 1 et 4), il est prévu un bossage 14 sur lequel est articulée autour d'un axe 15 l'une des extrémités d'une tige de commande 16 montée coulissante dans un alésage 17 d'un bossage 18 fixé sur le carter 2 et incliné sur ledit carter. A son autre extrémité, la tige 16 porte une chape 19 sur laquelle est montée de façon articulée autour d'axes 20 une autre chape 21 (figures 1, 5, 6) prévue à l'une des extrémités de l'une des branches d'un levier coudé 22 monté de façon pivotante autour d'un axe 23 fixé sur une chàpe 24 solidaire du bossage 18.Near the upstream edge of the downstream flap 6 (FIGS. 1 and 4), there is provided a boss 14 on which is articulated around an axis 15 one of the ends of a control rod 16 slidably mounted in a bore 17 a boss 18 fixed on the casing 2 and inclined on said casing. At its other end, the rod 16 carries a yoke 19 on which is pivotally mounted around axes 20 another yoke 21 (Figures 1, 5, 6) provided at one end of one of the branches of 'a bent lever 22 pivotally mounted about an axis 23 fixed on a cap 24 secured to the boss 18.

A l'une des extrémités de l'autre branche du levier coudé 22, est fixé un axe 24a portant un galet rotatif 25 engagé dans une échancrure 26 d'un anneau de commande 27 monté sur le carter 2 par l'intermédiaire d'un anneau de guidage 28. Sur l'un des bords des volets 5, 6, il est prévu une cloison d'étanchéité 5c et 6c (figures 2 et 3) s'étendant perpendiculairement au plan du volet et permettant de limiter le débit de fuite.At one end of the other branch of the bent lever 22, is fixed a pin 24a carrying a rotary roller 25 engaged in a notch 26 of a control ring 27 mounted on the housing 2 via a guide ring 28. On one of the edges of the flaps 5, 6, there is provided a sealing partition 5c and 6c (Figures 2 and 3) extending perpendicular to the plane of the flap and limiting the leak rate.

La même plate-forme 7, 7a qui porte les chapes 8, 11 présente une fente 29 recevant les cloisons 5c et 6c d'étanchéité des volets 5, 6.The same platform 7, 7a which carries the yokes 8, 11 has a slot 29 receiving the partitions 5c and 6c for sealing the flaps 5, 6.

Ainsi qu'il est représenté aux figures 1 et 2, les volets 5, 6 sont en position « col fermé », le canal entre les aubes 1 étant partiellement obturé par lesdits volets. Si l'anneau de commande 27 est déplacé en rotation, il provoque le basculement du levier coudé 22 suivant la flèche F et le déplacement de la tige 16 suivant la flèche F1, de telle sorte que les volets 5 et 6 s'escamotent dans l'alignement de la veine en position « col ouvert ".As shown in Figures 1 and 2, the flaps 5, 6 are in the "closed neck" position, the channel between the blades 1 being partially closed by said flaps. If the control ring 27 is moved in rotation, it causes the bent lever 22 to tip over according to arrow F and the rod 16 to move according to arrow F1, so that the flaps 5 and 6 retract into the alignment of the vein in the "open neck " position .

Claims (4)

1. Device for varying the section of the throat of a turbine guide vane assembly, of the kind having between the blades at least one movable member which is pivoted by its upstream edge on the outer casing of the assembly and whose radial displacements adjust the height of the gas stream, characterized in that in each channel formed between adjacent blades (1) and near the wall of the outer stream two flaps (5, 6) are provided which are situated one following the other and of which one (5) is pivoted by its upstream edge (10) and the other (6) is pivoted by its downstream edge (11) on the outer casing (2) of the guide vane assembly, one (5) of the upstream flaps being held by the gas pressure bearing by its downstream edge (5a) against the upstream edge (6a) of the downstream flap (6), and the downstream flap (6) being pivoted about a pin (15) by said upstream edge on a control member (16) in such a manner that in the « open throat » position the flaps (5, 6) retract into alignment with the wall of the stream, and that in the « closed throat position the channel is partly closed by said flaps (5, 6).
2. Device according to claim 1, characterized in that on the pivot pin (15) of the downstream flap (6) is mounted one end of a control rod (16) mounted for sliding in a boss (18) fixed on the outer casing (2) of the guide vane assembly, said rod being pivoted at its other end on one arm of a bell crank lever (22) pivotally mounted in its central part on a clevis (24) fastened to the outer casing (2), the other arm of the lever (22) carrying a roller (25) which is engaged in a cutout (26) in a control ring (27) mounted on the casing (2).
3. Device according to claim 1, characterized in that each flap (5, 6) is provided with a sealing partition (5c, 6c) extending at right angles to the plane of the flap and enabling the leakage flow to be limited.
4. Device according to claim 3, characterized in that the flaps (5, 6) are pivoted on pins (9, 12) fixed on clevises (8, 11) fastened to a platform (7, 7a) of the blades (1), said platform (7, 7a) being fixed on the outer casing (2) and having a slot (29) receiving the sealing partition (5c, 6c) of the flaps (5, 6).
EP86400191A 1985-02-06 1986-01-30 Device for varying the cross-section of a turbine stator Expired EP0191687B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8501618A FR2576974B1 (en) 1985-02-06 1985-02-06 DEVICE FOR VARIING THE SECTION OF THE NECK OF A TURBINE DISTRIBUTOR
FR8501618 1985-02-06

Publications (2)

Publication Number Publication Date
EP0191687A1 EP0191687A1 (en) 1986-08-20
EP0191687B1 true EP0191687B1 (en) 1988-11-09

Family

ID=9315971

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86400191A Expired EP0191687B1 (en) 1985-02-06 1986-01-30 Device for varying the cross-section of a turbine stator

Country Status (4)

Country Link
US (1) US4664594A (en)
EP (1) EP0191687B1 (en)
DE (1) DE3661146D1 (en)
FR (1) FR2576974B1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7900431B2 (en) 2005-11-04 2011-03-08 Parsons Brinckerhoff Limited Process and plant for power generation
US8206089B2 (en) 2006-12-01 2012-06-26 Parsons Brinckerhoff Limited Flow control device

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3540401A1 (en) * 1985-11-14 1987-05-21 Mtu Muenchen Gmbh Vane ring for turbo machines, especially for gas turbines
US5207558A (en) * 1991-10-30 1993-05-04 The United States Of America As Represented By The Secretary Of The Air Force Thermally actuated vane flow control
WO2003027461A1 (en) * 2001-09-24 2003-04-03 Alstom Technology Ltd Gas turbine system for working fluid in the form of a carbon dioxide/water mixture
FR2882394B1 (en) * 2005-02-22 2007-05-18 Snecma Moteurs Sa DEVICE FOR VARYING THE COLLAR SECTION OF A TURBINE DISPENSER
US7740449B1 (en) 2007-01-26 2010-06-22 Florida Turbine Technologies, Inc. Process for adjusting a flow capacity of an airfoil
US8414248B2 (en) 2008-12-30 2013-04-09 Rolls-Royce Corporation Variable geometry vane
US9650903B2 (en) * 2009-08-28 2017-05-16 United Technologies Corporation Combustor turbine interface for a gas turbine engine
US8851832B2 (en) * 2009-12-31 2014-10-07 Rolls-Royce North American Technologies, Inc. Engine and vane actuation system for turbine engine
EP2474709A1 (en) * 2011-01-05 2012-07-11 Siemens Aktiengesellschaft Bladed guiding ring for a steam turbine with fine adjusting device for flow capacity and corresponding method

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE534209A (en) *
US1201492A (en) * 1915-03-23 1916-10-17 Edward C Newton Indicating-governor.
US1529711A (en) * 1922-04-10 1925-03-17 Walter C Parrott Ventilating device
US2083447A (en) * 1934-05-12 1937-06-08 Gen Electric Centrifugal compressor
US2565178A (en) * 1942-10-13 1951-08-21 Rateau Soc Gas turbine
FR977692A (en) * 1942-10-13 1951-04-04 Rateau Soc Improvements to gas turbine heat engines
US2531896A (en) * 1946-10-12 1950-11-28 Louis E Telbizoff Variable area nozzle
US2875696A (en) * 1951-12-05 1959-03-03 Zborowski Helmut Ph G A R Von Centrifugal pumps, in particular for feeding fuel to fuel injection engines
DE1008751B (en) * 1954-03-03 1957-05-23 Korfmann Gmbh Maschf Compressed air turbine with adjustable nozzles
US2858974A (en) * 1955-04-13 1958-11-04 Robert O Bullock Device for eliminating rotating stall in axial-flow compressors
GB1073278A (en) * 1965-03-15 1967-06-21 Rolls Royce Improvements in or relating to propulsion nozzles
GB1242534A (en) * 1967-08-15 1971-08-11 Rolls Royce Bladed fluid flow machine
JPS50310A (en) * 1973-05-04 1975-01-06
US4409788A (en) * 1979-04-23 1983-10-18 General Electric Company Actuation system for use on a gas turbine engine
SE8005747L (en) * 1980-08-14 1982-02-15 Saab Scania Ab TURBINE WITH VARIABLE CONTRACTION IN TURBINE INLET
US4544325A (en) * 1980-10-22 1985-10-01 Teledyne Industries, Inc. Variable geometry device for turbine compressor outlet
US4403914A (en) * 1981-07-13 1983-09-13 Teledyne Industries, Inc. Variable geometry device for turbomachinery

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7900431B2 (en) 2005-11-04 2011-03-08 Parsons Brinckerhoff Limited Process and plant for power generation
US8206089B2 (en) 2006-12-01 2012-06-26 Parsons Brinckerhoff Limited Flow control device

Also Published As

Publication number Publication date
US4664594A (en) 1987-05-12
FR2576974B1 (en) 1989-02-03
DE3661146D1 (en) 1988-12-15
FR2576974A1 (en) 1986-08-08
EP0191687A1 (en) 1986-08-20

Similar Documents

Publication Publication Date Title
EP0191687B1 (en) Device for varying the cross-section of a turbine stator
FR2723614A1 (en) DEVICE FOR ASSEMBLING A CIRCULAR STAGE OF PIVOTING VANES.
EP2307735B1 (en) Turbomachine compressor
EP0795681B1 (en) Actuation mechanism for variable inlet vanes in turbomachine compressor
CA2518355C (en) Retention of centring keys of the rings under the variable setting stator blades of a gas turbine engine
FR2514412A1 (en) DEVICE FOR MODULATING THE FLOW OF GASES IN AN EXHAUST MUFFLER OF AN INTERNAL COMBUSTION ENGINE
CA2931374A1 (en) Device for guiding synchronizing ring vanes with variable pitch angle of a turbine engine and method for assembling such a device
EP3599345B1 (en) Air gap airfoils for a turbine engine compressor
EP2058641B1 (en) Isokinetic probe for analysing pollution in the gases generated by an airplane engine
US5622205A (en) Check valve having reserved mechanical closure
EP3247885B1 (en) System for controlling variable pitch blades for a turbine engine
EP1956226B1 (en) Discharge device for a jet engine, and jet engine comprising same
EP4022174B1 (en) Bypass turbomachine for an aircraft
FR2882570A1 (en) AUB CONTROL DEVICE WITH VARIABLE SHIFT IN A TURBOMACHINE
FR3025843B1 (en) SERVITUDE PASSAGE ARM FOR A TURBOMACHINE
FR3067387A1 (en) AIR SUPPLY ECOPE FOR SUPPLYING A COOLING SYSTEM AND CONTROLLING THE GAMES OF A TURBINE
EP3314131B1 (en) System for controlling variable-setting blades for a turbine engine
FR3043650A1 (en) TURBOMACHINE STATOR DAWN, BLOWER CELL COMPRISING SUCH A BLADE, PUSH INVERSION SYSTEM OF A TURBOMACHINE EQUIPPED WITH SUCH A BLADE AND TURBOMACHINE EQUIPPED WITH SAID BLADE, OF SAID CARTER OR DUDIT SYSTEM
FR3072719A1 (en) CONTROL RING OF A VARIABLE SHIFT AUBRA STAGE FOR A TURBOMACHINE
FR3024996A1 (en) CONTROL RING OF A VARIABLE SHIFT AUBRA STAGE FOR A TURBOMACHINE
WO2017013326A1 (en) Stage of variable-pitch blades for a turbine engine, turbine engine and associated installation method
FR3093136A1 (en) INPUT COVER FOR AN AIRCRAFT TURBOMACHINE
WO2021038161A1 (en) Bellcrank for a variable adjustment device for a turbomachine
EP2864594A1 (en) Fan having a variable setting by means of differential rotation of the fan disks
FR3053998A1 (en) TURBOMACHINE WHEEL

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: 19860210

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19870904

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

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

Ref document number: 3661146

Country of ref document: DE

Date of ref document: 19881215

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: FR

Ref legal event code: CL

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: 20031212

Year of fee payment: 19

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

Ref country code: GB

Payment date: 20031231

Year of fee payment: 19

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

Ref country code: DE

Payment date: 20040121

Year of fee payment: 19

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: 20050130

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: 20050802

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

Effective date: 20050130

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: 20050930

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST