EP0223194A1 - Aube statorique variable pour turbomachine - Google Patents

Aube statorique variable pour turbomachine Download PDF

Info

Publication number
EP0223194A1
EP0223194A1 EP86115712A EP86115712A EP0223194A1 EP 0223194 A1 EP0223194 A1 EP 0223194A1 EP 86115712 A EP86115712 A EP 86115712A EP 86115712 A EP86115712 A EP 86115712A EP 0223194 A1 EP0223194 A1 EP 0223194A1
Authority
EP
European Patent Office
Prior art keywords
guide vane
blade
pivotable
fixed
adjusting member
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
EP86115712A
Other languages
German (de)
English (en)
Other versions
EP0223194B1 (fr
Inventor
Hagen Hanser
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.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0223194A1 publication Critical patent/EP0223194A1/fr
Application granted granted Critical
Publication of EP0223194B1 publication Critical patent/EP0223194B1/fr
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
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid

Definitions

  • the invention relates to a guide vane for a guide vane ring for turbomachinery, in particular for gas turbines, the guide vanes on the inlet side consisting of the fixed part and on the outlet side of a part that can be pivoted relative to it, and the separation between fixed and pivotable vane parts is in the region of the greatest blade thickness.
  • the object of the invention is to provide a guide vane for a guide vane ring for turbomachinery, a constant vane profile (contour) being obtained despite pivoting and furthermore structurally simple means being used, in particular avoiding storage in two concentric rings.
  • the main advantage that is achieved with the invention is that a simple, true-to-contour adjustable guide vane is created for a guide vane ring which forms the drive connection to the pivotable vane part without a massive articulated axis.
  • This provides space for additional measures to optimize the sealing gap compared to the blades in the inner housing, e.g. active gap control created.
  • a greater variety is also available for other configurations of the inner ring of the turbine housing. Thermal or sealing problems are easier to solve.
  • the guide vanes in the configuration according to the invention are relatively easy to manufacture, maintain, repair or replace, the bridging of the separation between fixed and pivotable vane parts does not result in an aerodynamic disturbance, in particular Wing profile. This is independent of the respective swivel position of the blade part in question.
  • the arrangement and design of the elastic band result in a relatively high resistance to temperature changes and creep rupture. The same applies to the selected second volume. The latter can replace an articulated axis. Designs of strips as composite materials have also proven themselves.
  • the guide vane ring is formed from individual guide vanes or parts similar to guide vane, which are distributed over the circumference of a ring of the turbomachine as a ring or guide vane with the entry side in the drawing (FIG. 1) on the left and the exit side there on the right toward a rotor , ie e.g. a turbine stage with its blades.
  • the blade 1 has a fixed part 2 and a pivotable part 3 with a separation between the two in the area of the greatest blade thickness, the dividing line being profiled as shown in FIG. 1, on the one hand to enable the pivoting part of the pivotable part with an adjusting member 4 and on the other hand, the deflection of the pivotable part 3 in its maximum deflection position according to the arrow in FIG. 1. Therefore, the dividing line 5 on the fixed part 2 has two arches with different radii and a connecting line or surface.
  • the adjusting member 4 is inserted into the pivotable part 3 and held in it in a form-fitting or frictional manner.
  • a dovetail-like extension of the adjusting member 4 is used for this purpose.
  • Other types of mutual engagement can also be selected in order to transmit the pivoting movement.
  • the Schuafelprofil in particular a symmetrical aerodynamically favorable wing profile or the like remains practically unaffected by the pivoting of the part 3, ie the profile connection or transition remains ensured by the straps 6 and 7, 7 remaining the elastic band and 6 the flexible band for the existing gap or space 8 between the fixed part and the pivotable part.
  • the elastic band 7 of the blade is permanently attached to its two longitudinal sides, which run at the height of the blades, on the one hand on the fixed part 2 and on the other hand on the pivotable part 3.
  • the elastic band is also connected to the adjusting member 4, so that the pivoting movement in the direction of the arrow (see FIG. 1) is made possible, from the position in FIG. 4 to the position in FIG. 5.
  • the flexible cover band 6 is permanently attached to one side only, namely to the fixed part 2 above its height, while the pivotable part 3 lies loosely.
  • the gap 8 is securely covered, even in the outermost pivot position of part 3.
  • the elastic band 7 can consist of an elastomer, or a plastic, such as a silicone rubber, or, if working temperatures a little above 2OO ° C. are desired, of a polyimide or similar temperature-resistant plastic. Reinforced plastics or elastomers or composite materials made of elastomers or rubber-like plastics are particularly suitable which, on the one hand, have sufficient strength for the operating temperatures that occur, but on the other hand are sufficiently resilient. Fabric inserts, in particular carbon, glass fiber or metal thread fabrics, knitted fabrics or the like, are also suitable for this.
  • Fiber composites with synthetic resins in particular polymers including graphite, aramid or nylon threads, fibers or windings, or band-like parts thereof are also suitable for the purposes of the invention.
  • synthetic resins in particular polymers including graphite, aramid or nylon threads, fibers or windings, or band-like parts thereof are also suitable for the purposes of the invention.
  • the flexible band 6 simpler materials or material composites can also be used, provided that they only rest resiliently and can follow the pivotable part 3 when it is adjusted over the entire angle, which as a rule in the applications in question ranges from about 0 to 45 °.
  • Films can also be used here, e.g. Flour carbon foils such as FEP or PTFE.
  • various types of synthetic resins, in particular polymer plastics, are also suitable, including polyimide.
  • tapes 6 and 7 made of the same elastic material can also be used, although this is not necessary for the effect. When choosing, you will also be guided by the value for money in the respective application.
  • FIG. 2 shows the arrangement of the guide vane ring between the inner ring of the housing of a turbomachine 9 and the outer ring 10 of the housing or a similar ring part on the housing side. Both rings 9 and 10 are arranged concentrically with one another.
  • the milled surface 12 forms the connection surface to the flexible band 6.
  • the milling 12 is machined approximately half the diameter of the drive shaft of the adjusting member 4, as shown in FIG. 2.
  • Above the milling 12 is the bearing part 11 for the one-sided hanging mounting of the blade and above the bearing a pivot lever 13, which in turn is arranged on a hinge pin 14 in an adjusting ring 15 of the guide ring, as shown in Fig. 3 correctly in perspective, the rotation - Or swivel directions are indicated by arrows.
  • Such collars and the actuator for pivoting a blade ring or grille are known per se.
  • the blade 1 is at the lower end, i.e. towards the inner ring not stored but hung freely, i.e. it has a slight clearance to the inner ring 9. If necessary, a seal can also be inserted in the space between the inner ring.
  • the flexible band 6 (for example on the pressure side of the blade 1) extends only over the length (height) of the milling 12, the blade 1.
  • “Elastic” in the sense of the invention is understood to mean a body that is based on Hook's law behaves by itself, e.g. resilient, returning to its starting position from another position; into which he had come through the action of external forces.
  • flexible in the sense of the invention is meant a body that is bendable or the like, but not by itself, e.g. spring back immediately, return to its starting position.

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)
EP86115712A 1985-11-14 1986-11-12 Aube statorique variable pour turbomachine Expired EP0223194B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19853540401 DE3540401A1 (de) 1985-11-14 1985-11-14 Leitschaufelkranz fuer turbomaschinen, insbesondere fuer gasturbinen
DE3540401 1985-11-14

Publications (2)

Publication Number Publication Date
EP0223194A1 true EP0223194A1 (fr) 1987-05-27
EP0223194B1 EP0223194B1 (fr) 1989-05-24

Family

ID=6285976

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86115712A Expired EP0223194B1 (fr) 1985-11-14 1986-11-12 Aube statorique variable pour turbomachine

Country Status (5)

Country Link
US (1) US4741665A (fr)
EP (1) EP0223194B1 (fr)
JP (1) JPS62118007A (fr)
DE (2) DE3540401A1 (fr)
ES (1) ES2008849B3 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2266562A (en) * 1992-04-23 1993-11-03 Turbo Propulsores Ind Gas turbine engine variable stator vane assembly.
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
EP0633392A1 (fr) * 1993-07-07 1995-01-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Aube de turbomachine à cambrure variable
FR2714109A1 (fr) * 1993-12-22 1995-06-23 Snecma Aube de turbomachine à cambrure variable.
EP1637742A2 (fr) * 2004-09-21 2006-03-22 Snecma Levier de commande du calage angulaire d'une aube de stator dans une turbomachine
EP2065563A2 (fr) * 2007-11-29 2009-06-03 United Technologies Corporation Systèmes de moteurs à turbine à gaz impliquant des zones de gorge d'aube mécaniquement modifiables
DE102016208706A1 (de) 2016-05-20 2017-11-23 MTU Aero Engines AG Leitschaufel für ein Eintrittsleitgitter

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4979874A (en) * 1989-06-19 1990-12-25 United Technologies Corporation Variable van drive mechanism
DE4208311A1 (de) * 1992-03-16 1993-09-23 Asea Brown Boveri Vorrichtung zum regulieren des durchstroemten querschnitts einer turbomaschine
DE4212880A1 (de) * 1992-04-17 1993-04-01 Daimler Benz Ag Verstellbares leitgitter
US5623823A (en) * 1995-12-06 1997-04-29 United Technologies Corporation Variable cycle engine with enhanced stability
US5931636A (en) * 1997-08-28 1999-08-03 General Electric Company Variable area turbine nozzle
US6045325A (en) * 1997-12-18 2000-04-04 United Technologies Corporation Apparatus for minimizing inlet airflow turbulence in a gas turbine engine
GB2339244B (en) * 1998-06-19 2002-12-18 Rolls Royce Plc A variable camber vane
US6283705B1 (en) 1999-02-26 2001-09-04 Allison Advanced Development Company Variable vane with winglet
WO2003027461A1 (fr) * 2001-09-24 2003-04-03 Alstom Technology Ltd Systeme de turbine a gaz destine a un fluide de travail se presentant sous la forme d'un melange dioxyde de carbone/eau
US6619916B1 (en) * 2002-02-28 2003-09-16 General Electric Company Methods and apparatus for varying gas turbine engine inlet air flow
DE10256008B3 (de) * 2002-11-30 2004-08-12 Universität Kassel Turbomaschine
DE10257044B4 (de) * 2002-12-06 2005-01-27 Mtu Aero Engines Gmbh Gasturbine
DE10351202A1 (de) * 2003-11-03 2005-06-02 Mtu Aero Engines Gmbh Vorrichtung zum Verstellen von Leitschaufeln
US7491030B1 (en) 2006-08-25 2009-02-17 Florida Turbine Technologies, Inc. Magnetically actuated guide vane
DE102008013210A1 (de) 2008-03-07 2009-09-10 Pötzsch, Holger Dehnfugenüberbrückung
US8714916B2 (en) * 2010-09-28 2014-05-06 General Electric Company Variable vane assembly for a turbine compressor
DE102011008525B4 (de) 2011-01-13 2013-04-04 Pierburg Gmbh Leitvorrichtung für eine Turbine sowie derartige Turbine eines Turboladers
US9789636B2 (en) * 2013-06-03 2017-10-17 United Technologies Corporation Rigid and rotatable vanes molded within variably shaped flexible airfoils
US10233941B2 (en) 2013-07-12 2019-03-19 United Technologies Corporation Plastic variable inlet guide vane
DE102015004648A1 (de) * 2015-04-15 2016-10-20 Man Diesel & Turbo Se Leitschaufelverstellvorrichtung und Strömungsmaschine
US10934883B2 (en) * 2018-09-12 2021-03-02 Raytheon Technologies Cover for airfoil assembly for a gas turbine engine
CN109505664B (zh) * 2019-01-25 2023-09-08 中国船舶重工集团公司第七0三研究所 一种带有双层可转导叶的船用燃气轮机可倒车动力涡轮
US11655778B2 (en) * 2021-08-06 2023-05-23 Raytheon Technologies Corporation Morphing structures for fan inlet variable vanes

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3237918A (en) * 1963-08-30 1966-03-01 Gen Electric Variable stator vanes
GB1023766A (en) * 1964-02-14 1966-03-23 Bristol Siddeley Engines Ltd Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber
GB1144078A (en) * 1967-01-03 1969-03-05 Gen Motors Corp Compressor or like variable-camber aerofoil vanes
FR1587843A (fr) * 1968-10-15 1970-03-27
DE1946086A1 (de) * 1968-09-12 1970-07-30 Rolls Royce Schaufel fuer eine Stroemungsmaschine,insbesondere fuer ein Gasturbinenstrahltriebwerk
DE2348304A1 (de) * 1973-09-26 1975-03-27 Dornier System Gmbh Stroemungskoerper zur beeinflussung stroemender medien

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB611726A (en) * 1945-09-14 1948-11-03 Power Jets Res & Dev Ltd Improvements relating to diffusers, especially of centrifugal compressors, and control thereof
DE1041739B (de) * 1955-06-17 1958-10-23 Schweizerische Lokomotiv Verstellbarer Leitschaufelkranz fuer Axialturbomaschinen, insbesondere Axialgasturbinen
JPS5893903A (ja) * 1981-11-30 1983-06-03 Hitachi Ltd 可変入口案内翼
FR2576974B1 (fr) * 1985-02-06 1989-02-03 Snecma Dispositif de variation de section du col d'un distributeur de turbine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3237918A (en) * 1963-08-30 1966-03-01 Gen Electric Variable stator vanes
GB1023766A (en) * 1964-02-14 1966-03-23 Bristol Siddeley Engines Ltd Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber
GB1144078A (en) * 1967-01-03 1969-03-05 Gen Motors Corp Compressor or like variable-camber aerofoil vanes
GB1144077A (en) * 1967-01-03 1969-03-05 Gen Motors Corp Variable-camber vane rings
DE1946086A1 (de) * 1968-09-12 1970-07-30 Rolls Royce Schaufel fuer eine Stroemungsmaschine,insbesondere fuer ein Gasturbinenstrahltriebwerk
FR1587843A (fr) * 1968-10-15 1970-03-27
DE2348304A1 (de) * 1973-09-26 1975-03-27 Dornier System Gmbh Stroemungskoerper zur beeinflussung stroemender medien

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENTS ABSTRACTS OF JAPAN, Band 7, Nr. 193 (M-238)[1338], 24. August 1983; & JP-A-58 93 903 (HITACHI SEISAKUSHO K.K.) 03-06-1983 *

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
GB2266562A (en) * 1992-04-23 1993-11-03 Turbo Propulsores Ind Gas turbine engine variable stator vane assembly.
GB2266562B (en) * 1992-04-23 1995-10-11 Turbo Propulsores Ind Gas turbine stator vane assembly
FR2707338A1 (fr) * 1993-07-07 1995-01-13 Snecma Aube de turbomachine à cambrure variable.
EP0633392A1 (fr) * 1993-07-07 1995-01-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Aube de turbomachine à cambrure variable
FR2714109A1 (fr) * 1993-12-22 1995-06-23 Snecma Aube de turbomachine à cambrure variable.
EP0659979A1 (fr) * 1993-12-22 1995-06-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Aube de turbomachine à cambrure variable
US5520511A (en) * 1993-12-22 1996-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomachine vane with variable camber
EP1637742A2 (fr) * 2004-09-21 2006-03-22 Snecma Levier de commande du calage angulaire d'une aube de stator dans une turbomachine
EP1637742A3 (fr) * 2004-09-21 2014-03-12 Snecma Levier de commande du calage angulaire d'une aube de stator dans une turbomachine
EP2065563A2 (fr) * 2007-11-29 2009-06-03 United Technologies Corporation Systèmes de moteurs à turbine à gaz impliquant des zones de gorge d'aube mécaniquement modifiables
EP2065563A3 (fr) * 2007-11-29 2012-05-09 United Technologies Corporation Systèmes de moteurs à turbine à gaz impliquant des zones de gorge d'aube mécaniquement modifiables
DE102016208706A1 (de) 2016-05-20 2017-11-23 MTU Aero Engines AG Leitschaufel für ein Eintrittsleitgitter

Also Published As

Publication number Publication date
JPS62118007A (ja) 1987-05-29
US4741665A (en) 1988-05-03
DE3663558D1 (en) 1989-06-29
ES2008849B3 (es) 1989-08-16
EP0223194B1 (fr) 1989-05-24
DE3540401A1 (de) 1987-05-21

Similar Documents

Publication Publication Date Title
EP0223194A1 (fr) Aube statorique variable pour turbomachine
DE60029424T2 (de) Verbesserte lagerbuchse für eine gasturbinenschaufel
DE69830225T2 (de) Verstellbare Einlassleitschaufel für eine Gasturbine
DE69309180T2 (de) Lüfter
DE102009013399A1 (de) Tandemschaufelkonstruktion
DE3842710C1 (fr)
EP3172447B1 (fr) Aube de rotor
DE112014003165B4 (de) Variable Düseneinheit und Turbolader mit variablem Geometriesystem
EP3152407B1 (fr) Couronne d'aubes fixes, bague intérieure et turbomachine
CH697806A2 (de) Turbinenschaufel-Deckbandkantenprofil.
DE102011055515A1 (de) Propelleranordnung, insbesondere für Wasserfahrzeuge
DE69009136T2 (de) Labyrinthdichtungsträger.
DE102005040574A1 (de) Spaltkontrollvorrichtung für eine Gasturbine
EP3246518B1 (fr) Anneau aubagé directeur pour une turbomachine et turbomachine
EP0131719B1 (fr) Dispositif variable de guidage
DE60117656T2 (de) Axiallüfter
WO2001031169A1 (fr) Dispositif pour compenser la poussee axiale dans des turbomachines
EP2927427A1 (fr) Aube de turbine à gaz
EP2378068B1 (fr) Système d'amortissement pour l'amortissement de vibrations d'une aube rotorique, aube rotorique et rotor associés
DE602004005989T2 (de) Hubschrauberrotor mit einem Schwingungsdämpfer
EP0130408B1 (fr) Dispositif pour régler la section d'entrée de la turbine d'une turbosoufflante
DE102018206601A1 (de) Schaufel, Schaufelsegment und Baugruppe für eine Turbomaschine und Turbomaschine
DE602004004025T2 (de) Gesteuerte Klappe für eine rotationssymmetrische Schubdüse eines Strahltriebwerks
CH652450A5 (de) Turbinen-auspuffstutzen.
DE112019002491T5 (de) Radialverdichter

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

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

17P Request for examination filed

Effective date: 19870502

17Q First examination report despatched

Effective date: 19871109

ITF It: translation for a ep patent filed

Owner name: DE DOMINICIS & MAYER S.R.L.

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

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

REF Corresponds to:

Ref document number: 3663558

Country of ref document: DE

Date of ref document: 19890629

ET Fr: translation filed
GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
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
ITTA It: last paid annual fee
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19921013

Year of fee payment: 7

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

Ref country code: ES

Payment date: 19921023

Year of fee payment: 7

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

Ref country code: FR

Payment date: 19921127

Year of fee payment: 7

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

Ref country code: NL

Payment date: 19921130

Year of fee payment: 7

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

Ref country code: GB

Effective date: 19931112

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: 19931113

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

Ref country code: NL

Effective date: 19940601

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

Effective date: 19931112

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Effective date: 19940729

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

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

Ref country code: DE

Payment date: 19951020

Year of fee payment: 10

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

Ref country code: DE

Effective date: 19970801

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20010503

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

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20051112