EP1724471A2 - Kontrollsystem für verstellbaren Statorschaufelstufen einer Turbomaschine - Google Patents

Kontrollsystem für verstellbaren Statorschaufelstufen einer Turbomaschine Download PDF

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Publication number
EP1724471A2
EP1724471A2 EP06112920A EP06112920A EP1724471A2 EP 1724471 A2 EP1724471 A2 EP 1724471A2 EP 06112920 A EP06112920 A EP 06112920A EP 06112920 A EP06112920 A EP 06112920A EP 1724471 A2 EP1724471 A2 EP 1724471A2
Authority
EP
European Patent Office
Prior art keywords
follower
ring
control system
control
arm
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
EP06112920A
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English (en)
French (fr)
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EP1724471A3 (de
EP1724471B1 (de
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
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Filing date
Publication date
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Publication of EP1724471A2 publication Critical patent/EP1724471A2/de
Publication of EP1724471A3 publication Critical patent/EP1724471A3/de
Application granted granted Critical
Publication of EP1724471B1 publication Critical patent/EP1724471B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/56—Kinematic linkage, i.e. transmission of position using cams or eccentrics
    • 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

Definitions

  • the present invention relates to the general field of the blade stage control variable pitch angle of a turbomachine.
  • stator vane stages each include a plurality of vanes (referred to as variable pitch vanes) that are pivotable about their stator connection axis so that their stall angle can be varied according to the operating regime. of the turbomachine.
  • Known devices for controlling a stage of variable pitch vanes usually comprise a control member in the form of a ring surrounding the casing of the turbomachine and a plurality of rods or levers, each rod having a first end connected to the control ring by a hinge and a second end mounted on the pivot of a respective blade.
  • An actuating jack is connected to the control ring in order to rotate the latter around the axis of the turbomachine. The rotation of the ring around the axis of the turbomachine causes a synchronized modification of the angular position of the blades of the stage.
  • This control system generates movements on the various ordered stages represented in the form of curves which show the angle of wedging of the vanes of the follower stage as a function of the wedging angle of the vanes of the pilot stage.
  • these curves called correlation curves, have a progressive slope evolution. Also, this type of control system allows only simple commands of the blade stages.
  • each rod of the pilot stage is connected to the corresponding control ring by a groove connection and pin sliding in the groove.
  • This control system is however not satisfactory because it does not reproduce all kinds of control laws.
  • the main purpose of the present invention is thus to overcome such disadvantages by proposing a control system which makes it possible to produce any type of law for setting the blades, whatever its complexity.
  • a control system of two stator vane stages with a variable turbine engine pitch angle each stage being formed of a plurality of vanes which are each mounted pivotally on a casing of the turbine engine.
  • the control system comprising an actuating element for rotating the control ring of the one stages by means of a pilot member pivotally mounted on the housing, and a synchronization bar for transmitting the rotational movement of the ring driven by the operating element to the control ring of the other floor by via a follower member pivotally mounted on the housing, characterized in that it further comprises an additional pivoting member interposed between the follower member and the follower ring, said additional pivoting member being pivotally mounted on the follower member and connected to the housing by a roller sliding in a groove secured to the housing.
  • follower ring is meant the control ring which is rotated through the follower member.
  • the groove has a shape and a direction determined to compensate for deviations in trajectory between a desired clamping law and a nominal clamping law.
  • nominal stall law it is understood a stall law whose gradual slope correlation curve would be obtained by a conventional control system without additional pivoting member.
  • the additional pivoting member constitutes a differential guide element integrating only the deviations of trajectory with respect to the nominal clamping law.
  • the roller of the system according to the invention has to absorb as a difference in altitude the difference between the desired clamping law and the nominal clamping law. In this way, the control system makes it possible to obtain blade setting laws that would be unachievable with traditional control systems.
  • the additional pivoting member comprises a first arm connected to the follower ring via a first control rod and a second arm connected to the casing by the roller.
  • the follower member comprises a first arm pivotally connected to the additional member and a second arm connected to one end of the synchronization bar.
  • the pilot member comprises a first arm connected to the ring of the pilot stage via a second control rod, a second arm connected to the end of the synchronization bar opposite to that connected to the follower member and a third arm connected to the actuating member.
  • FIG. 1 partially shows two stages 10, 10 'of variable pitch vanes belonging, for example, to a turbomachine compressor.
  • the compressor comprises an annular stator envelope 12 (or casing) which is centered on the X-X axis of the turbomachine.
  • the stages 10, 10 'of blades are offset axially relative to each other.
  • Each stage consists of a plurality of vanes 14, 14 'arranged radially around the X-X axis of the turbomachine.
  • the blades 14, 14 ' are pivotable about an axis 16, 16' (or pivot) which passes through the housing 12.
  • Each pivot 16, 16 'of the variable pitch vanes 14, 14' is connected to one end of a rod or control lever 18, 18 'whose other end is articulated around pins 20, 20' arranged radially on a control ring 22, 22 '.
  • the control rings surround the casing 12 and are centered on the X-X axis of the turbomachine.
  • the synchronized modification of the angular position of the blades 14, 14 ' is thus achieved by rotation of the respective control rings 22, 22' around the axis X-X of the turbomachine.
  • the system according to the invention makes it possible to synchronously control the rotation of the control rings 22, 22 'around the axis XX of the turbomachine. It comprises a actuating element 24 of the jack type fixed to the casing 12 for rotating the control ring 22 of one of the stages 10 by means of a pilot member 26 of type return which is pivotally mounted on a housing 28 of the casing 12 of the turbomachine.
  • a synchronization bar 30 makes it possible to transmit the rotational movement of the ring 22 driven by the jack 24 (called the pilot ring) to the ring 22 'of the other stage 10' (called the follower ring) via a follower member 26 'which is also pivotally mounted on the housing 28 of the housing 12.
  • Control rods 32, 32 'of screw-type turnbuckles provide transmission of the movement of the pilot 26 and follower 26' to the rings 22, 22 '. These rods extend tangentially to the rings on which they are fixed by means of connecting yokes 27, 27 '. At their opposite end, the connecting rods 32, 32 'are attached to respective arms (or branches) 34, 36 of the pilot 26 and follower 26' references hinged thereto.
  • the synchronization bar 30 of the control system unites two other respective arms 38, 40 of the pilot 26 and follower 26 'references hinged thereto. As for the jack 24, it is articulated to a third arm 42 of the pilot gear 26 opposite the arm 34 on which is fixed the connecting rod 32.
  • the control system according to the invention further comprises an additional pivoting member 44 (or additional reference) which is interposed between the follower member 26 'and the follower ring 22'.
  • This additional reference is pivotally mounted on the follower 26 'and connected to the housing 12 by a roller 46 sliding in a groove 48 integral with the housing.
  • the additional return 44 comprises a first arm 50, one end of which is connected to the link rod 32 'for controlling the follower ring 22' by being articulated to it and the other end is pivotally mounted on the follower member. 26.
  • the additional return also comprises a second arm 52, one end of which is pivotally mounted on the follower member 26 ', the opposite end being provided with the roller 46.
  • the first 50 and the second arm 52 of the additional return are fixed to the one compared to the other. In other words, the angle between these two arms 50, 52 is fixed and constant.
  • the roller 46 slides in a groove 48 having a predetermined path and formed in a support 54 which is fixed on the casing 12 of the turbomachine.
  • the movement of the control system is as follows: the actuation of the jack 24 causes a rotation of the pilot return 26, and another of the follower 24 'via the synchronization bar 30.
  • the rotation of the references 26, 26 'around their point of pivoting on the housing 12 in turn drives the respective rods 32, 32' which then rotate in one direction or the other the rings 22, 22 'around of the axis XX of the turbomachine.
  • the rotation of the rings causes a synchronized change in the angular position of the blades 14, 14 'of each stage 10, 10' by means of the control levers 18, 18 '.
  • the predetermined path of the groove 48 in which the roller 46 slides depends on the displacement of the follower ring 22 ', and therefore the law of wedging of the blades 14' of the follower stage 10 '.
  • the shape and the direction of the groove modify the law of setting of the vanes of the follower stage, and thus the correlation curve giving the angle of wedging of the vanes 14 'of the follower stage 10' according to the wedging angle of the blades 14 of the pilot stage 10.
  • This figure represents correlation curves 100, 102, that is to say curves giving the wedging angle of the vanes 14 'of the follower stage 10' (in degree) as a function of the wedging angle of the blades 14 of the pilot stage 10 (in degree).
  • the correlation curve 100 (in solid lines) is that which must be applied to the setting of the blades of the two stages in order to meet the aerodynamic requirements.
  • This curve is complex; it comprises in particular portions of curves similar to sinusoids.
  • the nominal gradient correlation curve 102 (in dashed lines) which is the closest to the correlation curve 100 to be applied.
  • the calibration law based on such a nominal curve can be easily obtained by a known control system of the prior art including follower and pilot referrals and a synchronization bar connecting these references and wherein the control rod of the ring. follower is connected directly to one of the arms of the follower.
  • this type of control system gives known calibration laws whose correlation curves are more or less progressive (sometimes linear).
  • the choice of the closest curve is then made by a simple calculation (graphical or numerical) of means, the curve having the smallest deviations with the curve to be applied over the whole angular range being considered like the closest.
  • the shape and direction of the groove of the additional return are then calculated as a function of the gaps e existing over the entire angular range between the correlation curve 100 to be applied and the nominal correlation curve 102 so that the roller compensates for these deviations.
  • This calculation can be done by a graphical or numerical method. It will be noted that a groove having a simple circular arc shape corresponds to a correlation curve to be applied coinciding with the chosen nominal correlation curve.
  • the shape and the direction of the groove of the additional return must be such as to prevent the roller carried by the additional return being on a circular arc so as to avoid any unstable position of the roller, and therefore of the wedging of the blades.
  • the control system according to the invention therefore comprises a differential guiding element integrating only the path deviations between the correlation curve to be applied and a nominal correlation curve. It is thus easy to reproduce any type of calibration law, whatever its complexity.
  • the advantage of the invention resides in particular in the fact that it is not sought to obtain a correlation curve by the direct use of a cam guide but by the use of a roller which reproduces only the deviations of trajectory with respect to a nominal correlation curve.
  • the invention could also be implemented for controlling a greater number of blade stages with so many synchronization bars. Depending on the devices chosen, these bars would be either successive, that is to say connect adjacent referrals or parallel to each other to extend to a common referral.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP06112920A 2005-05-17 2006-04-21 Kontrollsystem für verstellbaren Statorschaufelstufen einer Turbomaschine Active EP1724471B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0504916A FR2885968B1 (fr) 2005-05-17 2005-05-17 Systeme de commande d'etages d'aubes de stator a angle de calage variable de turbomachine

Publications (3)

Publication Number Publication Date
EP1724471A2 true EP1724471A2 (de) 2006-11-22
EP1724471A3 EP1724471A3 (de) 2009-01-21
EP1724471B1 EP1724471B1 (de) 2010-07-28

Family

ID=35787969

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06112920A Active EP1724471B1 (de) 2005-05-17 2006-04-21 Kontrollsystem für verstellbaren Statorschaufelstufen einer Turbomaschine

Country Status (7)

Country Link
US (1) US7273346B2 (de)
EP (1) EP1724471B1 (de)
JP (1) JP4653013B2 (de)
CA (1) CA2547025C (de)
DE (1) DE602006015740D1 (de)
FR (1) FR2885968B1 (de)
RU (1) RU2396439C2 (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2936558A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison a barillet.
FR2936557A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison par pistes de guidage.
FR2936561A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par mecanisme a came
CN103133423A (zh) * 2011-11-25 2013-06-05 中国航空工业集团公司沈阳发动机设计研究所 一种芯轴式多级可调叶片联调作动机构
CN103277339A (zh) * 2013-06-26 2013-09-04 上海交通大学 含有类万向副的压气机多级静叶调节机构
EP2703606A1 (de) * 2012-08-29 2014-03-05 General Electric Company System und Verfahren zur Steuerung verstellbarer Leitschaufeln in Gasturbinenmotoren
EP2497957A3 (de) * 2011-03-07 2018-03-21 Mitsubishi Hitachi Power Systems, Ltd. Axialkompressor und Modifikationsverfahren
EP3604746A1 (de) * 2018-08-02 2020-02-05 Rolls-Royce plc Kurbelwellenbaugruppe
EP3770381A1 (de) * 2019-07-25 2021-01-27 Raytheon Technologies Corporation Selbsthaltendes gestänge und system mit dem selbsthaltenden gestänge für einen gasturbinenmotor
EP4148236A1 (de) * 2021-09-14 2023-03-15 MTU Aero Engines AG Verstellanordnung für verstellschaufeln einer strömungsmaschine

Families Citing this family (18)

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Publication number Priority date Publication date Assignee Title
FR2936556B1 (fr) * 2008-09-30 2015-07-24 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine, notamment par guignols.
IT1400053B1 (it) * 2010-05-24 2013-05-17 Nuovo Pignone Spa Metodi e sistemi per ugelli di ingresso a geometria variabile per uso in turboespansori.
US20130084179A1 (en) * 2011-09-30 2013-04-04 Hamilton Sundstrand Corporation Variable vane angular position sensor
DE102012007129A1 (de) * 2012-04-10 2013-10-10 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelverstellvorrichtung einer Gasturbine
US20140205424A1 (en) * 2012-08-29 2014-07-24 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
US9903451B2 (en) * 2014-10-31 2018-02-27 Trane International Inc. Linkage to actuate inlet guide vanes
FR3038018B1 (fr) 2015-06-25 2019-07-12 Safran Aircraft Engines Systeme de commande d'aubes a calage variable pour une turbomachine
FR3039226B1 (fr) 2015-07-20 2017-07-14 Snecma Etage d'aubes a calage variable pour une turbomachine
FR3051826B1 (fr) * 2016-05-25 2018-06-01 Safran Aircraft Engines Dispositif de commande d'elements a calage variable dans une turbomachine
US10519797B2 (en) 2016-06-27 2019-12-31 General Electric Company Turbine engine and stator vane pitch adjustment system therefor
US10508660B2 (en) 2017-10-20 2019-12-17 Rolls-Royce Corporation Apparatus and method for positioning a variable vane
EP3502485A1 (de) * 2017-12-19 2019-06-26 Siemens Aktiengesellschaft Verstellgestänge
EP3502484A1 (de) * 2017-12-19 2019-06-26 Siemens Aktiengesellschaft Verstellgestänge
US11092032B2 (en) * 2018-08-28 2021-08-17 Pratt & Whitney Canada Corp. Variable vane actuating system
US11092167B2 (en) * 2018-08-28 2021-08-17 Pratt & Whitney Canada Corp. Variable vane actuating system
CN111636978B (zh) * 2020-06-16 2021-06-18 南京航空航天大学 一种适用于涡轮基循环组合发动机的流量调节机构
US11371380B2 (en) 2020-12-01 2022-06-28 Pratt & Whitney Canada Corp. Variable guide vane assembly and vane arms therefor
DE102022103922A1 (de) * 2022-02-18 2023-08-24 MTU Aero Engines AG Hebel zum verstellen einer verstellschaufel

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FR2856424A1 (fr) * 2003-06-20 2004-12-24 Snecma Moteurs Dispositif de calage variable de deux etages d'aubes fixes sur un turboreacteur

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GB857800A (en) * 1957-04-29 1961-01-04 Gen Electric Improvements in compressor
US4400135A (en) * 1981-04-06 1983-08-23 General Motors Corporation Vane actuation system
EP0909880A2 (de) * 1997-10-14 1999-04-21 General Electric Company Leitschaufel Verstellsystem für Turbinen
FR2856424A1 (fr) * 2003-06-20 2004-12-24 Snecma Moteurs Dispositif de calage variable de deux etages d'aubes fixes sur un turboreacteur

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8690520B2 (en) 2008-09-30 2014-04-08 Snecma System for controlling variable geometry equipment of a gas turbine engine especially comprising a guiding track connection
WO2010037750A1 (fr) * 2008-09-30 2010-04-08 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison a barillet
FR2936558A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison a barillet.
CN102171416B (zh) * 2008-09-30 2014-11-19 斯奈克玛 由导向轨道连接的燃气涡轮发动机的变几何装置的控制系统
US8740547B2 (en) 2008-09-30 2014-06-03 Snecma System for controlling variable geometry equipment of a gas turbine engine particularly comprising a barrel link
US8333546B2 (en) 2008-09-30 2012-12-18 Snecma System for controlling at least two variable-geometry equipments of a gas turbine engine, particularly by cam mechanism
FR2936557A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison par pistes de guidage.
RU2503824C2 (ru) * 2008-09-30 2014-01-10 Снекма Система управления оборудованием с изменяемой геометрией газотурбинного двигателя, содержащая, в частности, барабанное соединение
WO2010037751A1 (fr) * 2008-09-30 2010-04-08 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison par pistes de guidage
FR2936561A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par mecanisme a came
EP2497957A3 (de) * 2011-03-07 2018-03-21 Mitsubishi Hitachi Power Systems, Ltd. Axialkompressor und Modifikationsverfahren
CN103133423A (zh) * 2011-11-25 2013-06-05 中国航空工业集团公司沈阳发动机设计研究所 一种芯轴式多级可调叶片联调作动机构
CN103133423B (zh) * 2011-11-25 2016-01-20 中国航空工业集团公司沈阳发动机设计研究所 一种芯轴式多级可调叶片联调作动机构
EP2703606A1 (de) * 2012-08-29 2014-03-05 General Electric Company System und Verfahren zur Steuerung verstellbarer Leitschaufeln in Gasturbinenmotoren
CN103277339B (zh) * 2013-06-26 2015-12-02 上海交通大学 含有类万向副的压气机多级静叶调节机构
CN103277339A (zh) * 2013-06-26 2013-09-04 上海交通大学 含有类万向副的压气机多级静叶调节机构
EP3604746A1 (de) * 2018-08-02 2020-02-05 Rolls-Royce plc Kurbelwellenbaugruppe
EP3770381A1 (de) * 2019-07-25 2021-01-27 Raytheon Technologies Corporation Selbsthaltendes gestänge und system mit dem selbsthaltenden gestänge für einen gasturbinenmotor
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
EP4148236A1 (de) * 2021-09-14 2023-03-15 MTU Aero Engines AG Verstellanordnung für verstellschaufeln einer strömungsmaschine
US11891918B2 (en) 2021-09-14 2024-02-06 MTU Aero Engines AG Adjustment assembly for adjustable blades or vanes of a turbomachine

Also Published As

Publication number Publication date
CA2547025A1 (fr) 2006-11-17
CA2547025C (fr) 2012-10-02
JP4653013B2 (ja) 2011-03-16
RU2006116818A (ru) 2007-11-27
EP1724471A3 (de) 2009-01-21
DE602006015740D1 (de) 2010-09-09
JP2006322456A (ja) 2006-11-30
FR2885968A1 (fr) 2006-11-24
RU2396439C2 (ru) 2010-08-10
EP1724471B1 (de) 2010-07-28
US7273346B2 (en) 2007-09-25
FR2885968B1 (fr) 2007-08-10
US20060260307A1 (en) 2006-11-23

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