EP1724472A3 - Control system for variable guide vane stages of a turbomachine - Google Patents

Control system for variable guide vane stages of a turbomachine Download PDF

Info

Publication number
EP1724472A3
EP1724472A3 EP06112991A EP06112991A EP1724472A3 EP 1724472 A3 EP1724472 A3 EP 1724472A3 EP 06112991 A EP06112991 A EP 06112991A EP 06112991 A EP06112991 A EP 06112991A EP 1724472 A3 EP1724472 A3 EP 1724472A3
Authority
EP
European Patent Office
Prior art keywords
control system
turbomachine
housing
follower
ring
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
EP06112991A
Other languages
German (de)
French (fr)
Other versions
EP1724472B1 (en
EP1724472A2 (en
Inventor
Michel Bouru
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1724472A2 publication Critical patent/EP1724472A2/en
Publication of EP1724472A3 publication Critical patent/EP1724472A3/en
Application granted granted Critical
Publication of EP1724472B1 publication Critical patent/EP1724472B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
    • 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
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources
    • 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
    • F05D2270/00—Control
    • F05D2270/50—Control logic embodiments
    • F05D2270/58—Control logic embodiments by mechanical means, e.g. levers, gears or cams

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Abstract

Système de commande de deux étages (10, 10') d'aubes de stator (14, 14') à angle de calage variable de turbomachine, comportant un élément de manoeuvre (24) pour entraîner en rotation l'anneau de commande (22) de l'un des étages (10) par l'intermédiaire d'un organe pilote (26) monté de façon pivotante sur le carter (12), une barre de synchronisation (30) pour transmettre le mouvement de rotation de l'anneau entraîné (22) par l'élément de manoeuvre (24) à l'anneau de commande (22') de l'autre étage (10') par l'intermédiaire d'un organe suiveur (26') monté de façon pivotante sur le carter, et un organe pivotant supplémentaire (44) intercalé entre l'organe suiveur (26') et l'anneau suiveur (22'), ledit organe pivotant supplémentaire (44) étant monté de façon pivotante à la fois sur le carter (12) et sur l'organe suiveur (26').

Figure imgaf001
A two-stage control system (10, 10 ') of stator vanes (14, 14') with a variable turbine engine pitch angle, comprising an operating element (24) for rotating the control ring (22) ) of one of the stages (10) via a pilot member (26) pivotally mounted on the housing (12), a synchronizing bar (30) for transmitting the rotational movement of the ring driven (22) by the operating element (24) to the control ring (22 ') of the other stage (10') via a follower member (26 ') pivotally mounted on the housing, and an additional pivoting member (44) interposed between the follower member (26 ') and the follower ring (22'), said additional pivot member (44) being pivotally mounted to both the housing ( 12) and on the follower member (26 ').
Figure imgaf001
EP06112991A 2005-05-17 2006-04-24 Control system for variable guide vane stages of a turbomachine Active EP1724472B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0504918A FR2885969B1 (en) 2005-05-17 2005-05-17 TURBOMACHINE VARIABLE ROTATION ANGLE STATOR AUTONER STAGE CONTROL SYSTEM

Publications (3)

Publication Number Publication Date
EP1724472A2 EP1724472A2 (en) 2006-11-22
EP1724472A3 true EP1724472A3 (en) 2009-01-21
EP1724472B1 EP1724472B1 (en) 2010-06-16

Family

ID=35478463

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06112991A Active EP1724472B1 (en) 2005-05-17 2006-04-24 Control system for variable guide vane stages of a turbomachine

Country Status (7)

Country Link
US (1) US7322790B2 (en)
EP (1) EP1724472B1 (en)
JP (1) JP4773876B2 (en)
CA (1) CA2547026C (en)
DE (1) DE602006014902D1 (en)
FR (1) FR2885969B1 (en)
RU (1) RU2396438C2 (en)

Families Citing this family (52)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101311554B (en) * 2007-05-24 2010-05-26 中国科学院工程热物理研究所 Three-factor matching method for improving energy efficiency for blade type fluid machinery
FR2936559B1 (en) * 2008-09-30 2013-11-22 Snecma SYSTEM FOR CONTROLLING EQUIPMENT WITH VARIABLE GEOMETRY OF A TURBOMACHINE CONSISTING OF DIFFERENT BODIES.
FR2936558B1 (en) * 2008-09-30 2016-11-11 Snecma SYSTEM FOR CONTROLLING EQUIPMENT WITH VARIABLE GEOMETRY OF A GAS TURBINE ENGINE INCLUDING, IN PARTICULAR, A BARREL LINK.
FR2936556B1 (en) 2008-09-30 2015-07-24 Snecma SYSTEM FOR CONTROLLING EQUIPMENT WITH VARIABLE GEOMETRY OF A TURBOMACHINE, IN PARTICULAR BY GUIGNOLS.
FR2936565B1 (en) 2008-09-30 2015-07-24 Snecma SYSTEM FOR CONTROLLING EQUIPMENT WITH VARIABLE GEOMETRY OF A TURBOMACHINE IN PARTICULAR BY ARTICULATED GUIGNOLS.
JP5398323B2 (en) * 2009-03-30 2014-01-29 三菱重工業株式会社 Stator blade variable device and axial flow fluid machine
GB0907461D0 (en) * 2009-05-01 2009-06-10 Rolls Royce Plc Control mechanism
FR2947311B1 (en) 2009-06-26 2014-08-29 Snecma METHOD AND DEVICE FOR RECALING THE CONTROL OF A VARIABLE GEOMETRY EQUIPMENT FOR TURBOMACHINE
FR2947310B1 (en) * 2009-06-26 2014-08-29 Snecma DEVICE AND METHOD FOR POSITIONING A VARIABLE GEOMETRY EQUIPMENT FOR A TURBOMACHINE USING A RELATIVE MEASURING CYLINDER.
FR2950927B1 (en) * 2009-10-06 2016-01-29 Snecma SYSTEM FOR CONTROLLING THE ANGULAR POSITION OF STATOR AUBES AND METHOD FOR OPTIMIZATION OF SAID ANGULAR POSITION
IT1400053B1 (en) * 2010-05-24 2013-05-17 Nuovo Pignone Spa METHODS AND SYSTEMS FOR VARIABLE GEOMETRY ENTRY NOZZLES FOR USE IN TURBOESPANSORI.
IT1401665B1 (en) * 2010-08-31 2013-08-02 Nuova Pignone S R L DRIVING SYSTEM FOR TURBOMACHINE AND METHOD.
DE102011003522B4 (en) * 2011-02-02 2013-03-14 Siemens Aktiengesellschaft Coupled outlet diffuser angle adjustment
JP5340333B2 (en) * 2011-03-07 2013-11-13 株式会社日立製作所 Remodeling method of axial compressor
US9068470B2 (en) 2011-04-21 2015-06-30 General Electric Company Independently-controlled gas turbine inlet guide vanes and variable stator vanes
RU2474698C1 (en) * 2011-10-28 2013-02-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) System of rotating blades stages control of high pressure compressor stator
DE102012007129A1 (en) * 2012-04-10 2013-10-10 Rolls-Royce Deutschland Ltd & Co Kg Guide vane adjusting a gas turbine
FR2993932B1 (en) * 2012-07-27 2015-09-25 Aircelle Sa DEVICE FOR DRIVING SHUTTERS, IN PARTICULAR FOR AN ADAPTIVE TUBE
US9885291B2 (en) * 2012-08-09 2018-02-06 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
US9879561B2 (en) * 2012-08-09 2018-01-30 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
US20140064911A1 (en) * 2012-08-29 2014-03-06 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
US20140205424A1 (en) * 2012-08-29 2014-07-24 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
DE102012021876A1 (en) 2012-11-07 2014-05-22 Rolls-Royce Deutschland Ltd & Co Kg Guide vane adjusting a gas turbine
US9151178B2 (en) * 2012-11-15 2015-10-06 United Technologies Corporation Bellcrank for a variable vane assembly
WO2014205816A1 (en) * 2013-06-28 2014-12-31 Siemens Aktiengesellschaft Guide vane actuator of a compressor and a compressor using it
EP3090142B1 (en) * 2013-12-11 2019-04-03 United Technologies Corporation Variable vane positioning apparatus for a gas turbine engine
FR3025577B1 (en) * 2014-09-05 2016-12-23 Snecma ORGAN DRIVE MECHANISM FOR ADJUSTING THE ORIENTATION OF THE BLADES
CN105570196B (en) * 2014-10-31 2019-09-06 特灵国际有限公司 Activate the link mechanism of entry guide vane
FR3033007B1 (en) * 2015-02-19 2018-07-13 Safran Aircraft Engines DEVICE FOR THE INDIVIDUAL ADJUSTMENT OF A PLURALITY OF FIXED RADIAL BLADES WITH VARIABLE SETTING IN A TURBOMACHINE
US10443431B2 (en) 2016-03-24 2019-10-15 United Technologies Corporation Idler gear connection for multi-stage variable vane actuation
US10301962B2 (en) 2016-03-24 2019-05-28 United Technologies Corporation Harmonic drive for shaft driving multiple stages of vanes via gears
US10294813B2 (en) 2016-03-24 2019-05-21 United Technologies Corporation Geared unison ring for variable vane actuation
US10288087B2 (en) 2016-03-24 2019-05-14 United Technologies Corporation Off-axis electric actuation for variable vanes
US10458271B2 (en) 2016-03-24 2019-10-29 United Technologies Corporation Cable drive system for variable vane operation
US10107130B2 (en) 2016-03-24 2018-10-23 United Technologies Corporation Concentric shafts for remote independent variable vane actuation
US10415596B2 (en) 2016-03-24 2019-09-17 United Technologies Corporation Electric actuation for variable vanes
US10329946B2 (en) 2016-03-24 2019-06-25 United Technologies Corporation Sliding gear actuation for variable vanes
US10190599B2 (en) 2016-03-24 2019-01-29 United Technologies Corporation Drive shaft for remote variable vane actuation
US10443430B2 (en) 2016-03-24 2019-10-15 United Technologies Corporation Variable vane actuation with rotating ring and sliding links
US10329947B2 (en) 2016-03-24 2019-06-25 United Technologies Corporation 35Geared unison ring for multi-stage variable vane actuation
FR3051826B1 (en) * 2016-05-25 2018-06-01 Safran Aircraft Engines DEVICE FOR CONTROLLING VARIABLE-SETTING ELEMENTS IN A TURBOMACHINE
FR3076325B1 (en) * 2017-12-29 2019-11-29 Safran Aircraft Engines DEVICE FOR VARIABLE SETTING OF AT LEAST TWO ANNULAR ROWS OF FIXED BLADES FOR A TURBOMACHINE
US11092167B2 (en) * 2018-08-28 2021-08-17 Pratt & Whitney Canada Corp. Variable vane actuating system
US11092032B2 (en) * 2018-08-28 2021-08-17 Pratt & Whitney Canada Corp. Variable vane actuating system
US11149580B2 (en) 2019-07-25 2021-10-19 Raytheon Technologies Corporation Self retained linkage and system including the self retained linkage for a gas turbine engine
FR3107319B1 (en) * 2020-02-19 2022-08-12 Safran Aircraft Engines TURBOMACHINE MODULE EQUIPPED WITH STATOR BLADE PITCH CHANGE SYSTEM
US11371380B2 (en) * 2020-12-01 2022-06-28 Pratt & Whitney Canada Corp. Variable guide vane assembly and vane arms therefor
PL437817A1 (en) * 2021-05-07 2022-11-14 General Electric Company Variable geometry split-action system for a turbine engine compressor
FR3123323B1 (en) * 2021-05-27 2024-05-03 Safran Aircraft Engines CONNECTION AND SUPPORT STRUCTURE OF A TURBOMACHINE TO AN AIRCRAFT Pylon
US11802490B2 (en) * 2021-08-25 2023-10-31 Rolls-Royce Corporation Controllable variable fan outlet guide vanes
US11788429B2 (en) * 2021-08-25 2023-10-17 Rolls-Royce Corporation Variable tandem fan outlet guide vanes
DE102022103922A1 (en) * 2022-02-18 2023-08-24 MTU Aero Engines AG LEVER FOR ADJUSTING AN ADJUSTABLE BLADE

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4295784A (en) * 1979-09-26 1981-10-20 United Technologies Corporation Variable stator
US5044879A (en) * 1989-01-25 1991-09-03 Rolls-Royce Plc Variable stator vane arrangement for an axial flow compressor
US5190439A (en) * 1991-07-15 1993-03-02 United Technologies Corporation Variable vane non-linear schedule for a gas turbine engine
EP0765992A1 (en) * 1995-09-27 1997-04-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Actuating system for variable stator vanes
EP0909880A2 (en) * 1997-10-14 1999-04-21 General Electric Company Turbine vane actuation system
EP1489267A1 (en) * 2003-06-20 2004-12-22 Snecma Moteurs Adjusting device for the vanes of two stages in a turbo machine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3146585A (en) * 1961-09-29 1964-09-01 Gen Electric Turbojet control system for preventing compressor stall due to inlet air disturbances
US3779665A (en) * 1972-09-22 1973-12-18 Gen Electric Combined variable angle stator and windmill control system
JPS6119640U (en) * 1984-07-10 1986-02-04 トヨタ自動車株式会社 Variable nozzle link mechanism
JPH10159583A (en) * 1996-11-29 1998-06-16 Ishikawajima Harima Heavy Ind Co Ltd Stator blade for axial flow compressor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4295784A (en) * 1979-09-26 1981-10-20 United Technologies Corporation Variable stator
US5044879A (en) * 1989-01-25 1991-09-03 Rolls-Royce Plc Variable stator vane arrangement for an axial flow compressor
US5190439A (en) * 1991-07-15 1993-03-02 United Technologies Corporation Variable vane non-linear schedule for a gas turbine engine
EP0765992A1 (en) * 1995-09-27 1997-04-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Actuating system for variable stator vanes
EP0909880A2 (en) * 1997-10-14 1999-04-21 General Electric Company Turbine vane actuation system
EP1489267A1 (en) * 2003-06-20 2004-12-22 Snecma Moteurs Adjusting device for the vanes of two stages in a turbo machine

Also Published As

Publication number Publication date
CA2547026C (en) 2013-09-17
RU2396438C2 (en) 2010-08-10
FR2885969B1 (en) 2007-08-10
JP2006322457A (en) 2006-11-30
US20060263206A1 (en) 2006-11-23
US7322790B2 (en) 2008-01-29
FR2885969A1 (en) 2006-11-24
CA2547026A1 (en) 2006-11-17
JP4773876B2 (en) 2011-09-14
EP1724472B1 (en) 2010-06-16
RU2006116817A (en) 2007-11-27
DE602006014902D1 (en) 2010-07-29
EP1724472A2 (en) 2006-11-22

Similar Documents

Publication Publication Date Title
EP1724472A3 (en) Control system for variable guide vane stages of a turbomachine
EP1724471A3 (en) Control system for variable stator vane stages of a turbomachine
US20070172348A1 (en) Adjustable guide device
RU2004118678A (en) DEVICE FOR CHANGING AN INSTALLATION ANGLE FOR TWO STEPS OF A STEEL BLADED SHOULDER IN A TURBO-REACTIVE ENGINE
JP4771650B2 (en) Stator blade actuator in gas turbine engine
US20070172347A1 (en) Adjustable guide device
EP1746259A3 (en) Variable vane synchronizing mechanism for inner diameter vane shroud
JP2006322457A5 (en)
EP2053204A3 (en) Gas turbine engine with variable vanes
EP1961922A3 (en) Control of variable pitch angle blades
UA89021C2 (en) Turbomachine with means for axial retention of the rotor
FR2907495B1 (en) TURBOMACHINE
EP1942273A3 (en) Wind turbine comprising a bearing lubrication system
EP2131012A3 (en) Variable geometry turbine of a turbocharger and corresponding method for adjusting geometry of this turbine
EP1491725A3 (en) Bearing device for an adjustable vane
FR2854559A1 (en) TOASTER COMPRISING AN ELECTRIC MOTOR DRIVEN GRID
EP1707756A3 (en) Arrangement for securing an actuating lever
FR3098788B1 (en) Turbomachine module for a propeller with variable blade pitch and turbomachine comprising it
FR3054006B1 (en) ASSEMBLY FOR THE CONTROL OF VARIABLE TIMING BLADES IN A TURBOMACHINE
FR3046433B1 (en) AUBES BLOW MODULE WITH VARIABLE SHIFT FOR A TURBOMACHINE
EP3480434A1 (en) Inlet cartridge for adjusting the cross-section of compressor inlet and compressor
FR2895020B1 (en) ARRANGEMENT FOR GAS SAMPLING FROM A TURBOMACHINE CASING, CASTING THE COMPONENT, AND AN AIRCRAFT ENGINE WHILE MUNIED
FR2907166B1 (en) ARRANGEMENT FOR GAS SAMPLING FROM A TURBOMACHINE CASING, CASTING THE COMPONENT, AND AN AIRCRAFT ENGINE WHILE MUNIED
US20190040875A1 (en) Inlet guide vane assembly
FR3082907B1 (en) AIRCRAFT TURBOMACHINE HAVING PIVOT LINKS AT EACH END OF A SHAFT AND A SLIDING LINK BETWEEN SAID PIVOT LINKS

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: 20060424

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

AKX Designation fees paid

Designated state(s): DE FR GB

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAC Information related to communication of intention to grant a patent modified

Free format text: ORIGINAL CODE: EPIDOSCIGR1

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

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: 602006014902

Country of ref document: DE

Date of ref document: 20100729

Kind code of ref document: P

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

26N No opposition filed

Effective date: 20110317

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602006014902

Country of ref document: DE

Effective date: 20110316

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

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

Ref country code: FR

Payment date: 20230321

Year of fee payment: 18

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

Ref country code: DE

Payment date: 20230321

Year of fee payment: 18

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

Ref country code: GB

Payment date: 20240320

Year of fee payment: 19