EP0947668A1 - Turbomaschinenstufe mit an ihren inneren Enden durch einen Ring verbundenen Leitschaufeln - Google Patents

Turbomaschinenstufe mit an ihren inneren Enden durch einen Ring verbundenen Leitschaufeln Download PDF

Info

Publication number
EP0947668A1
EP0947668A1 EP99400514A EP99400514A EP0947668A1 EP 0947668 A1 EP0947668 A1 EP 0947668A1 EP 99400514 A EP99400514 A EP 99400514A EP 99400514 A EP99400514 A EP 99400514A EP 0947668 A1 EP0947668 A1 EP 0947668A1
Authority
EP
European Patent Office
Prior art keywords
ring
pivots
support ring
notches
lips
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
EP99400514A
Other languages
English (en)
French (fr)
Other versions
EP0947668B1 (de
Inventor
Daniel André Agram
Anne-Cécile Christine Marlin
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 EP0947668A1 publication Critical patent/EP0947668A1/de
Application granted granted Critical
Publication of EP0947668B1 publication Critical patent/EP0947668B1/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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular

Definitions

  • the invention relates to a floor circular blades with inner ends united by a connecting ring.
  • Such a construction is encountered in turbomachinery for stages of blades of stator-related rectifiers: the outer ends blades are supported by the stator and inner ends by a common connecting ring to all the blades of the floor and which therefore contributes to stiffen their assembly by uniting them.
  • the outer ends and inner blades consist of supported pivots in respective bearings of the stator and the ring liaison.
  • This device is effective but present the disadvantage that we must provide a ring which increases the weight and the cost of machine manufacturing.
  • the invention therefore relates to a device having the same effects but lacking of this inconvenience of having to add an unnecessary part moreover: it is proposed to ensure the retention of inner pivots by a structural element already present in the link ring and that we are content to modify slightly.
  • the invention can be defined as a circular stage of blades having outer pivots housed in bearings of pivoting of a stator and internal pivots housed in inner pivot bearings of a ring link ;
  • the connecting ring is composed of a support ring and stiffening ring interlaced, the support ring carrying the bearings of internal pivoting and the stiffening ring ends in two lips directed towards each other and penetrating in respective grooves of the support ring, the interior pivots being hollowed out with a notch; according to the invention, one of the lips extends to through the support ring and enters the gashes.
  • the notches do not extend only over a sector of circumference and therefore offer a stop to the angular displacements of dawn, which is also interesting when it is broken.
  • a particular embodiment is distinguishes by a construction in two sections of blade pivots for easier assembly: the lips of the stiffening ring extend over circles of two different diameters, and the pivots are formed of two sections, including an engaged journal section in a bearing socket and an enlarged section, located between the journal and a blade of the dawn, the notches being dug in the enlarged sections, the lip opposite lip penetrating notches extending in front of the trunnions.
  • the machine includes an external stator 1 and at least one blade stage 2 equipped with the invention; the vanes 2 have a first pivot end outside 3 passing through the stator 1 at the location of a outer bearing 4 and an opposite end forming a inner pivot 5 engaged in a bearing 6 of a ring connecting 7 common to all the vanes 2 of the stage.
  • the outer pivot 3 is provided with shoulders 8 and 9 between which the bearing 4 is retained, which limits the radial movement of blade 2 in the machine (on could also speak of axial displacement in considering the direction of pivots 3 and 5).
  • the pivot outside 3 comes out of stator 1 and ends in one connection with a control lever 10 of which the other end is connected to a common control ring 11 to all the vanes 2 of the stage; the control ring 11 is arranged around stator 1, and it suffices to turn to control the rotation of the levers 10 and that of the vanes 2 around their pivots 3 and 5.
  • the connecting ring 7 is essentially composed of a support ring 12, in which the bearings 6 are hollowed out, and a stiffening ring 13 wrapping part of the support ring 12.
  • the reason for this construction can be explained by reference to Figure 2: we see that the ring of support 12 is not unitary but composed of sectors 14 abutments, two, four or eight in number current achievements, and that the stiffening ring 13 is the way to keep them in place. It is itself composed of two semi-circular sectors 15 and reunited with each other.
  • the stiffening ring 13 has a section similar to that of a rail and having a bottom 17 under the ring support 12, sidewalls 18 partially covering the flat faces of the support ring 12 and the lips 19 and 20 located at the end of the sides 18 and 19 penetrating in grooves 22 and 23 of the connecting ring 12. As the lips 20 and 21 are directed one towards the other, they hold the stiffening ring 13 on the support ring 12 and keep them interlaced.
  • the inner bearing 6 is formed by a sleeve 27 engaged through a hole in the connecting ring 12 and of which the outer surface is threaded: like the pivot interior 5 is actually composed of a pin 28 engaged in the socket 27 and a widening 29 located between the pin 28 and a blade 30 of the blade 2, we see that the setting of the connecting ring 7 is produced by screwing the sockets 27 into the holes threaded from the support ring 12 until the outer ends 31 of sockets 27 abut against the extended parts 29. This prohibits deflections and vibrations in the radial direction of the connecting ring 7.
  • cylindrical lips 20 and 21 do not belong to circles of the same diameter but, as one of the flanks 19 is much wider than the other 18, the lip 21 which he wears extends in front the widened part 29, while the other comes only in front of the pin 28.
  • This lip 21 is further long enough to fit into a cut 31 in the enlarged part 29, the groove 23 which is there partner crossing right through a wall of the connecting ring 12.
  • the material of the enlarged part 29 which is located between the notch 31 and the pin 28 forms a rim 32 which abuts against the lip 21 in outward movement of dawn 2 due to example to a rupture of it, and opposes the extraction of the inner pivot 5. The retention of dawn is therefore assured with this construction particularly simple, in accordance with the objective announced above.
  • Figure 3 completes the presentation of this invention by perhaps representing more clearly its main elements, the socket 27 having however been omitted from representation for clarity.
  • the notch 31 advantageously does not extend that on a sector of circumference and therefore ends in two lateral abutment surfaces 33 which limit the angular deflection of blade 2 by touching the lip 21, which is particularly advantageous in the event of breaking of dawn 2, when the blade fragment 30 adjoining the inner pivot 5 would be feathered (i.e. would freely follow the direction of the gas flow) erratically.

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)
  • Control Of Turbines (AREA)
  • Synchronous Machinery (AREA)
EP99400514A 1998-03-05 1999-03-04 Turbomaschinenstufe mit an ihren inneren Enden durch einen Ring verbundenen Leitschaufeln Expired - Lifetime EP0947668B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9802675A FR2775731B1 (fr) 1998-03-05 1998-03-05 Etage circulaire d'aubes aux extremites interieures unies par un anneau de liaison
FR9802675 1998-03-05

Publications (2)

Publication Number Publication Date
EP0947668A1 true EP0947668A1 (de) 1999-10-06
EP0947668B1 EP0947668B1 (de) 2000-05-03

Family

ID=9523676

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99400514A Expired - Lifetime EP0947668B1 (de) 1998-03-05 1999-03-04 Turbomaschinenstufe mit an ihren inneren Enden durch einen Ring verbundenen Leitschaufeln

Country Status (6)

Country Link
US (1) US6129512A (de)
EP (1) EP0947668B1 (de)
JP (1) JP3877032B2 (de)
CA (1) CA2263255C (de)
DE (1) DE69900004T2 (de)
FR (1) FR2775731B1 (de)

Families Citing this family (53)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10016745B4 (de) * 2000-04-04 2005-05-19 Man B & W Diesel Ag Axialströmungsmaschine mit einem eine Reihe von verstellbaren Leitschaufeln umfassenden Leitapparat
US6547002B1 (en) * 2000-04-17 2003-04-15 Weatherford/Lamb, Inc. High pressure rotating drilling head assembly with hydraulically removable packer
EP1205639A1 (de) * 2000-11-09 2002-05-15 General Electric Company Befestigungsanordnung von verstellbaren Turbinenleitschaufeln im inneren Haltering
DE10161292A1 (de) 2001-12-13 2003-06-26 Rolls Royce Deutschland Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
US7125222B2 (en) * 2004-04-14 2006-10-24 General Electric Company Gas turbine engine variable vane assembly
FR2875270B1 (fr) * 2004-09-10 2006-12-01 Snecma Moteurs Sa Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz
DE102005040574A1 (de) * 2005-08-26 2007-03-15 Rolls-Royce Deutschland Ltd & Co Kg Spaltkontrollvorrichtung für eine Gasturbine
FR2899637B1 (fr) * 2006-04-06 2010-10-08 Snecma Aube de stator a calage variable de turbomachine
DE102006024085B4 (de) 2006-05-23 2020-04-16 MTU Aero Engines AG Turboverdichter in Axialbauweise
US7713022B2 (en) * 2007-03-06 2010-05-11 United Technologies Operations Small radial profile shroud for variable vane structure in a gas turbine engine
US9353643B2 (en) * 2007-04-10 2016-05-31 United Technologies Corporation Variable stator vane assembly for a turbine engine
US7806652B2 (en) * 2007-04-10 2010-10-05 United Technologies Corporation Turbine engine variable stator vane
JP2010523898A (ja) * 2007-04-10 2010-07-15 エリオット・カンパニー 可変入口案内翼を有する遠心圧縮機
US8500394B2 (en) * 2008-02-20 2013-08-06 United Technologies Corporation Single channel inner diameter shroud with lightweight inner core
US8328512B2 (en) 2009-06-05 2012-12-11 United Technologies Corporation Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine
DE102009038623B4 (de) * 2009-08-26 2012-01-19 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelkranz für den Verdichter einer Fluggasturbine
US8727730B2 (en) * 2010-04-06 2014-05-20 General Electric Company Composite turbine bucket assembly
EP2405104A1 (de) * 2010-07-08 2012-01-11 Siemens Aktiengesellschaft Verdichter und zugehöriges Gasturbinenkraftwerk
FR2966530B1 (fr) * 2010-10-21 2012-11-02 Snecma Etage redresseur a calage variable pour un compresseur d'une turbomachine
US8961125B2 (en) * 2011-12-13 2015-02-24 United Technologies Corporation Gas turbine engine part retention
US9410443B2 (en) 2012-01-27 2016-08-09 United Technologies Corporation Variable vane damping assembly
EP2636849B1 (de) * 2012-03-05 2017-11-01 MTU Aero Engines GmbH Verdichter
FR2988787B1 (fr) * 2012-04-03 2016-01-22 Snecma Redresseur a calage variable pour compresseur de turbomachine comprenant deux anneaux internes
EP2696041B1 (de) * 2012-08-07 2020-01-22 MTU Aero Engines AG Leitschaufelkranz einer gasturbine sowie montageverfahren
US9140133B2 (en) 2012-08-14 2015-09-22 United Technologies Corporation Threaded full ring inner air-seal
EP2725200B1 (de) 2012-10-25 2018-06-06 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
EP2725202A1 (de) * 2012-10-25 2014-04-30 MTU Aero Engines GmbH Innenring-Dichtungsträgeranordnung eines verstellbaren Leitschaufelgitters einer Strömungsmaschine
EP2728123A1 (de) 2012-11-06 2014-05-07 MTU Aero Engines GmbH Strömungsmaschine sowie zugehöriges Montageverfahren einer Strömungsmaschine
US20140234087A1 (en) * 2013-02-17 2014-08-21 United Technologies Corporation Inlet guide vane retention feature
DE102013211629A1 (de) * 2013-06-20 2015-01-08 MTU Aero Engines AG Leitschaufelanordnung und Verfahren zum Montieren einer Leitschaufel
FR3014152B1 (fr) * 2013-11-29 2015-12-25 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine et procede d'assemblage d'un tel dispositif
DE102014205986B4 (de) 2014-03-31 2021-03-18 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
US9784285B2 (en) * 2014-09-12 2017-10-10 Honeywell International Inc. Variable stator vane assemblies and variable stator vanes thereof having a locally swept leading edge and methods for minimizing endwall leakage therewith
GB201418321D0 (en) * 2014-10-16 2014-12-03 Rolls Royce Plc Mounting arrangement for variable stator vane
DE102014223975A1 (de) * 2014-11-25 2016-05-25 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
US10358932B2 (en) * 2015-06-29 2019-07-23 United Technologies Corporation Segmented non-contact seal assembly for rotational equipment
DE102015220371A1 (de) 2015-10-20 2017-04-20 MTU Aero Engines AG Innenringsystem, Leitschaufelkranz und Strömungsmaschine
DE102016215807A1 (de) * 2016-08-23 2018-03-01 MTU Aero Engines AG Innenring für einen Leitschaufelkranz einer Strömungsmaschine
US11168704B2 (en) 2017-03-30 2021-11-09 Mitsubishi Power, Ltd. Variable stator vane and compressor
DE102017109952A1 (de) * 2017-05-09 2018-11-15 Rolls-Royce Deutschland Ltd & Co Kg Rotorvorrichtung einer Strömungsmaschine
DE102017211316A1 (de) * 2017-07-04 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtring
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
FR3085060B1 (fr) 2018-08-17 2020-10-09 Safran Aircraft Engines Anneau de guidage d'aubes a calage variable et procede de montage dudit anneau
DE102018213983A1 (de) * 2018-08-20 2020-02-20 MTU Aero Engines AG Verstellbare Leitschaufelanordnung, Leitschaufel, Dichtungsträger und Turbomaschine
US10808568B2 (en) 2018-09-12 2020-10-20 Raytheon Technologies Corporation Airfoil assembly for a gas turbine engine
FR3108369B1 (fr) * 2020-03-18 2022-10-28 Safran Aircraft Engines Redresseur pour turbomachine d’aeronef, comprenant un limitateur de pivotement d’aube a angle de calage variable
FR3115818B1 (fr) * 2020-10-30 2023-10-20 Safran Aircraft Engines Soufflante de turbomachine comprenant des pales à calage variable
CN112065777B (zh) * 2020-11-10 2021-01-19 中国航发上海商用航空发动机制造有限责任公司 压气机进口导流叶片的调节精度保持结构
US11549388B2 (en) * 2021-01-18 2023-01-10 Raytheon Technologies Corporation Inner shroud assembly for gas turbine engine variable vane system
FR3123885B1 (fr) * 2021-06-15 2023-06-16 Safran Aircraft Engines Redresseur non carene de turbomachine equipe d’aubes de stator fixees a des pivots et turbomachine correspondante
DE102021120384A1 (de) * 2021-08-05 2023-02-09 MTU Aero Engines AG Leitschaufelkranz für eine Strömungsmaschine, Strömungsmaschine und Verfahren zum Montieren eines Leitschaufelkranzes
US12078071B1 (en) * 2023-02-21 2024-09-03 Rolls-Royce Corporation Segmented compressor inner band for variable vanes in gas turbine engines
US11879480B1 (en) 2023-04-07 2024-01-23 Rolls-Royce North American Technologies Inc. Sectioned compressor inner band for variable pitch vane assemblies in gas turbine engines

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3079128A (en) * 1961-01-23 1963-02-26 Burge Joseph Sealing and securing means for turbomachine blading
US3224194A (en) * 1963-06-26 1965-12-21 Curtiss Wright Corp Gas turbine engine
FR2723614A1 (fr) * 1994-08-10 1996-02-16 Snecma Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3567331A (en) * 1969-07-25 1971-03-02 Gen Motors Corp Variable vane cascades
FR2685033B1 (fr) * 1991-12-11 1994-02-11 Snecma Stator dirigeant l'entree de l'air a l'interieur d'une turbomachine et procede de montage d'une aube de ce stator.
FR2742799B1 (fr) * 1995-12-20 1998-01-16 Snecma Palier d'extremite interne d'aube pivotante

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3079128A (en) * 1961-01-23 1963-02-26 Burge Joseph Sealing and securing means for turbomachine blading
US3224194A (en) * 1963-06-26 1965-12-21 Curtiss Wright Corp Gas turbine engine
FR2723614A1 (fr) * 1994-08-10 1996-02-16 Snecma Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.

Also Published As

Publication number Publication date
JP3877032B2 (ja) 2007-02-07
EP0947668B1 (de) 2000-05-03
CA2263255C (en) 2009-02-24
FR2775731A1 (fr) 1999-09-10
DE69900004D1 (de) 2000-06-08
JPH11315702A (ja) 1999-11-16
US6129512A (en) 2000-10-10
DE69900004T2 (de) 2001-03-01
FR2775731B1 (fr) 2000-04-07
CA2263255A1 (en) 1999-09-05

Similar Documents

Publication Publication Date Title
EP0947668B1 (de) Turbomaschinenstufe mit an ihren inneren Enden durch einen Ring verbundenen Leitschaufeln
EP1659266B1 (de) Gemeinsame Entkopplungsvorrichtung für das erste und das zweite Lager der Antriebswelle einer Turbomaschine, und Verdichter und Turbomaschine mit einer solchen Vorrichtung
EP1605139B1 (de) Turbomaschine mit axialer Rückhalteeinrichtung für den Rotor
CA2826153C (fr) Ensemble pale-plateforme pour ecoulement subsonique
CA2885650C (fr) Carter et roue a aubes de turbomachine
CA2518355C (fr) Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz
EP1748158B1 (de) Buchse zum Drehen der verstellbaren Leitschaufeln einer Turbomaschine.
EP0695856B1 (de) Kompressor-Robotscheibe mit asymmetrischer Umfangsnut
CA2357176A1 (fr) Turbomachine a veine d'ecoulement ameliore
CA2826145C (fr) Ensemble pale-plateforme pour ecoulement supersonique
EP1867841A1 (de) Stator einer Strömungsmaschine, der eine Stufe mit Leitschaufeln umfasst, die von einem Drehzahnkranz mit automatischer Zentrierung angetrieben werden
EP0636766B1 (de) Turbomaschinenstator mit verstellbaren Leitschaufeln und deren Bedienungsring
EP1540143A1 (de) Rotorneuzentrierung nach der entkupplung
FR3071546B1 (fr) Retention axiale de l'arbre de soufflante dans un moteur a turbine a gaz
EP1344896B1 (de) Einrichtung, um eine Bläserwelle nach einer Havarie wieder zu lagern und zu rezentrieren
FR2882577A1 (fr) Dispositif de reglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine
EP2071138A1 (de) Abkopplungsvorrichtung eines Lagerträgers mit Doppelzentrierung
FR2716502A1 (fr) Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires.
EP0780545B1 (de) Anordnung der inneren Enden einer schwenkbaren Schaufelstufe
FR3066534A1 (fr) Ensemble pour turbomachine d'aeronef presentant un systeme de decouplage ameliore en cas de perte d'aube de soufflante
FR2874977A1 (fr) Douille de support pivotant pour pivot d'aube a calage variable de turbomachine
FR3069012B1 (fr) Aube fixe de turbomachine, pourvue d'une plate-forme fixee au stator
FR3045709A1 (fr) Aube de soufflante
FR2879684A1 (fr) Turbomachine comprenant un stator equipe d'aubes de redresseur a calage variable commandees par des biellettes a emmanchement conique
FR3094028A1 (fr) Turbine comprenant un anneau d’etancheite rivete

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

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

17P Request for examination filed

Effective date: 19990322

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

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

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

17Q First examination report despatched

Effective date: 19990914

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

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

AX Request for extension of the european patent

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

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: FRENCH

REF Corresponds to:

Ref document number: 69900004

Country of ref document: DE

Date of ref document: 20000608

AKX Designation fees paid

Free format text: DE FR GB

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

Effective date: 20000601

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

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

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

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20120517 AND 20120523

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

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

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

Ref country code: GB

Payment date: 20180226

Year of fee payment: 20

Ref country code: DE

Payment date: 20180219

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: 20180220

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 69900004

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20190303

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: 20190303