EP2257404A1 - Dispositif de contrôle de faisceau et procédé de contrôle de faisceau - Google Patents

Dispositif de contrôle de faisceau et procédé de contrôle de faisceau

Info

Publication number
EP2257404A1
EP2257404A1 EP09714367A EP09714367A EP2257404A1 EP 2257404 A1 EP2257404 A1 EP 2257404A1 EP 09714367 A EP09714367 A EP 09714367A EP 09714367 A EP09714367 A EP 09714367A EP 2257404 A1 EP2257404 A1 EP 2257404A1
Authority
EP
European Patent Office
Prior art keywords
energy beam
beam source
sensor
component
distance
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.)
Withdrawn
Application number
EP09714367A
Other languages
German (de)
English (en)
Inventor
Matthias Jungbluth
Nikolai Arjakine
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.)
Siemens AG
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP09714367A priority Critical patent/EP2257404A1/fr
Publication of EP2257404A1 publication Critical patent/EP2257404A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/02—Positioning or observing the workpiece, e.g. with respect to the point of impact; Aligning, aiming or focusing the laser beam
    • B23K26/04—Automatically aligning, aiming or focusing the laser beam, e.g. using the back-scattered light
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K10/00—Welding or cutting by means of a plasma
    • B23K10/02—Plasma welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/0096—Portable laser equipment, e.g. hand-held laser apparatus
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/20—Bonding
    • B23K26/21—Bonding by welding
    • B23K26/24—Seam welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/20—Bonding
    • B23K26/21—Bonding by welding
    • B23K26/24—Seam welding
    • B23K26/26—Seam welding of rectilinear seams
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K9/00—Arc welding or cutting
    • B23K9/12—Automatic feeding or moving of electrodes or work for spot or seam welding or cutting
    • B23K9/126—Controlling the spatial relationship between the work and the gas torch
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K9/00—Arc welding or cutting
    • B23K9/12—Automatic feeding or moving of electrodes or work for spot or seam welding or cutting
    • B23K9/127—Means for tracking lines during arc welding or cutting
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K9/00—Arc welding or cutting
    • B23K9/24—Features related to electrodes
    • B23K9/28—Supporting devices for electrodes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K9/00—Arc welding or cutting
    • B23K9/32—Accessories

Definitions

  • the invention relates to a device for beam control and a method for beam control.
  • these components may show cracks, traces of tarnishing as well as loss of material due to oxidation or erosion in various areas.
  • Welding zone can be ensured and are relatively easy to weld geometries. In service cases, however, one also has to do with such component areas whose accessibility is very problematic and there are great differences in the defect findings from component to component.
  • a hand-held laser the advantages of laser welding can be combined with the good process flexibility of conventional methods.
  • the pin whose length corresponds to the optimal machining distance, prevents it from falling below the minimum distance.
  • the fact that the laser can ignite only with electrical contact of the pin with the component, also exceeding the optimum processing distance is prevented.
  • the object is achieved with a device according to claim 1 and a method according to claim 12.
  • Figure 5 is a gas turbine
  • FIG. 6 is a perspective view of a turbine blade
  • Figure 8 is a list of superalloys.
  • the invention is characterized in that a measurement of the machining distance of an energy beam source 1 to a surface 8 and / or the determination of the material of an irradiated surface 8 of a component 3 takes place without contact.
  • the basic structure is shown in FIG. 1
  • a sensor 2 or a sensor unit 2 comprising one or more sensors for scanning a surface 8 of the component 3, 120, 130, 155 is present on the laser 1 (explained only by way of example for the energy source 1).
  • the sensor 2 has a sensor axis 4 which is preferably parallel to the axis of the beams 5 of the energy beam source 1.
  • the sensor 2 is preferably attached to the energy beam source 1 such that the sensor axis 4 is aligned as parallel as possible to the axis of the laser beam 5 (FIG. 2) or that preferably both axes intersect at the focal point of the energy beam 5, ie the laser beam 5 (FIG. 3).
  • a signal is emitted from the sensor 2. sent, which in turn is detected by the sensor 2 as a useful signal.
  • the sensor 2 transmits a useful signal to a processing unit 6. If the wanted signal lies in the setpoint range adjustable at a processing unit 6, the power control of the laser 1 is released in a controller 7, so that the laser 1 is ignited by the operator or in operation can stay.
  • the useful signal is a distance between the laser 1 and the surface 8 and / or the material of the surface 8.
  • the distance measurement allows the ignition of the laser 1 only in the optimal distance range
  • the device 10 is guided manually.
  • the device 10 is portable by a human.
  • Material detection Automated welding does not require material detection. Likewise, the trajectory of the laser is previously determined in the machine (for example by distance measurement) and then traversed without distance measurement.
  • the energy source 1 is guided by the hand of the operator (human) and not by an electric drive. distance measurement
  • the distance measurement by means of the sensor 2 can be carried out with the following operating principles: - Magnetindutation
  • the laser 1 can not be ignited.
  • the laser In manual welding, the laser is switched on (at the correct distance) and remains permanently switched on and, if necessary, switched off due to a distance measurement.
  • the working principles of the distance measurement can also be used for material detection, which is located in the direction of the sensor axis 4. Thus, it can be determined by means of magnetic induction whether a metallic surface 8 is present.
  • the sensor 2 for the component detection can be carried out according to the passive or the active working principle: In the passive mode of operation, the sensor 2 detects an editable component 3 (conductive metal) with the active principle
  • the component 3 to be machined is activated electrically, magnetically or acoustically and the signal is detected by a suitable sensor 2, as a result of which the component identification:
  • the distance measurement via radar and the material determination by means Magnetindutationen are examples.
  • the invention is characterized in that no mechanical contact between the component 3 and the laser 1 or a part of it to maintain the working and process safety is necessary. This is achieved by the beam control by means of one or more non-contact sensors for maintaining the processing distance and component identification.
  • FIG. 5 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft 101, which is also referred to as a turbine runner.
  • a compressor 105 for example, a torus-like
  • Combustion chamber 110 in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings.
  • a series 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example. Coupled to the rotor 103 is a generator or work machine (not shown).
  • air 105 is sucked in by the compressor 105 through the intake housing 104 and compressed.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
  • substrates of the components can have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • SX structure monocrystalline
  • DS structure longitudinal grains
  • iron-, nickel- or cobalt-based superalloys are used as the material for the components, in particular for the turbine blade 120, 130 and components of the combustion chamber 110.
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
  • the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 Bl, EP 0 412 397 B1 or EP 1 306 454 A1.
  • thermal barrier layer is present, and consists for example of Zr ⁇ 2, Y2 ⁇ 3-Zr ⁇ 2, i. it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • suitable coating methods e.g. Electron beam evaporation (EB-PVD) produces stalk-shaped grains in the thermal barrier coating.
  • the vane 130 has a guide vane foot (not shown here) facing the inner housing 138 of the turbine 108 and a vane head opposite the vane foot.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • FIG. 6 shows a perspective view of a rotor 120 or guide vane 130 of a turbomachine that extends along a longitudinal axis 121.
  • the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 consecutively a fastening region 400, a blade platform 403 adjacent thereto and an airfoil 406 and a blade tip 415.
  • the blade 130 may have at its blade tip 415 another platform (not shown).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the blade 406.
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
  • the blade 120, 130 can be made by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
  • Workpieces with a monocrystalline structure or structures are used as components for machines which are exposed to high mechanical, thermal and / or chemical stresses during operation.
  • the production of such monocrystalline workpieces for example, by directed solidification from the melt.
  • These are casting methods in which the liquid metallic alloy solidifies into a monocrystalline structure, ie a single-crystal workpiece, or directionally.
  • dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, i.e., grains that run the full length of the workpiece and here, in common usage, are referred to as directionally solidified) or a monocrystalline structure, i. the whole workpiece consists of a single crystal.
  • a columnar grain structure columnar, i.e., grains that run the full length of the workpiece and here, in common usage, are referred to as directionally solidified
  • a monocrystalline structure i. the whole workpiece consists of a single crystal.
  • Structures are also called directionally solidified structures.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 Bl, EP 0 412 397 B1 or EP 1 306 454 A1.
  • the density is preferably 95% of the theoretical density.
  • the layer composition comprises Co-30Ni-28Cr-8A1-0, 6Y-0, 7Si or Co-28Ni-24Cr-10Al-0, 6Y.
  • nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-IIAl-O, 4Y-2Re or Ni-25Co-17Cr-10Al-0.4Y-1 are also preferably used , 5RE.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of Zr ⁇ 2, Y2Ü3-Zr ⁇ 2, ie it is not, partially ⁇ or fully stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • the thermal barrier coating covers the entire MCrAlX layer.
  • suitable coating methods e.g. Electron beam evaporation (EB-PVD) produces stalk-shaped grains in the thermal barrier coating.
  • the thermal barrier coating may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
  • Refurbishment means that components 120, 130 may have to be freed from protective layers after use (eg by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. Thereafter, a the coating of the component 120, 130 and a renewed use of the component 120, 130.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and may still film cooling holes 418 (indicated by dashed lines) on.
  • FIG. 7 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is designed, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 107 arranged in the circumferential direction around a rotation axis 102 open into a common combustion chamber space 154, which generate flames 156.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C. to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the working medium M with an inner lining formed from heat shield elements 155.
  • Each heat shield element 155 made of an alloy is equipped on the working fluid side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating) or is made of high-temperature-resistant material (solid ceramic blocks).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • MCrAlX means: M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • Such alloys are known from the EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • ceramic heat may be medämm harsh, consisting for example of ZrO 2, ZrO 2 Y2Ü3-ie, it is not partially full text or ⁇ dig stabilized by yttrium oxide and / or calcium and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the heat-insulating layer may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • Refurbishment means that heat shield elements 155 may need to be deprotected (e.g., by sandblasting) after use. This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, cracks in the heat shield element 155 are also repaired. This is followed by a recoating of the heat shield elements 155 and a renewed use of the heat shield elements 155.
  • the heat shield elements 155 are then, for example, hollow and possibly still have cooling holes (not shown) which open into the combustion chamber space 154.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Plasma & Fusion (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un dispositif de soudage, dans lequel un écart entre un laser et un élément est déterminé sans contact.
EP09714367A 2008-02-28 2009-01-13 Dispositif de contrôle de faisceau et procédé de contrôle de faisceau Withdrawn EP2257404A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09714367A EP2257404A1 (fr) 2008-02-28 2009-01-13 Dispositif de contrôle de faisceau et procédé de contrôle de faisceau

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08003727A EP2100689A1 (fr) 2008-02-28 2008-02-28 Dispositif et procédé de commande de faisceaux
EP09714367A EP2257404A1 (fr) 2008-02-28 2009-01-13 Dispositif de contrôle de faisceau et procédé de contrôle de faisceau
PCT/EP2009/050311 WO2009106375A1 (fr) 2008-02-28 2009-01-13 Dispositif de contrôle de faisceau et procédé de contrôle de faisceau

Publications (1)

Publication Number Publication Date
EP2257404A1 true EP2257404A1 (fr) 2010-12-08

Family

ID=39855085

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08003727A Withdrawn EP2100689A1 (fr) 2008-02-28 2008-02-28 Dispositif et procédé de commande de faisceaux
EP09714367A Withdrawn EP2257404A1 (fr) 2008-02-28 2009-01-13 Dispositif de contrôle de faisceau et procédé de contrôle de faisceau

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08003727A Withdrawn EP2100689A1 (fr) 2008-02-28 2008-02-28 Dispositif et procédé de commande de faisceaux

Country Status (2)

Country Link
EP (2) EP2100689A1 (fr)
WO (1) WO2009106375A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015014016B3 (de) * 2015-10-30 2016-12-15 O.R. Lasertechnologie Gmbh Handführbares Laserwerkzeug zur Bearbeitung von Werkstücken
CN109798864A (zh) * 2019-01-02 2019-05-24 煤炭科学技术研究院有限公司 一种液压支架的变形量测量装置
IT202100006938A1 (it) * 2021-03-26 2022-09-26 Marco Leder Dispositivo al laser per la lavorazione di metalli e apparecchiatura comprendente tale dispositivo
WO2024163572A1 (fr) * 2023-01-31 2024-08-08 Illinois Tool Works Inc. Systèmes et procédés de protection pour soudage laser manuel
EP4658443A1 (fr) * 2023-01-31 2025-12-10 Illinois Tool Works, Inc. Systèmes et procédés de commande d'équipement de soudage au laser portatif

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CH682060A5 (fr) * 1987-05-18 1993-07-15 Weidmueller C A Gmbh Co
DE58908611D1 (de) 1989-08-10 1994-12-08 Siemens Ag Hochtemperaturfeste korrosionsschutzbeschichtung, insbesondere für gasturbinenbauteile.
DE3926479A1 (de) 1989-08-10 1991-02-14 Siemens Ag Rheniumhaltige schutzbeschichtung, mit grosser korrosions- und/oder oxidationsbestaendigkeit
DE4207169A1 (de) * 1992-03-06 1993-09-09 Siemens Solar Gmbh Laserbearbeitungsverfahren fuer ein werkstueck mit nicht ebener oberflaeche
DE59505454D1 (de) 1994-10-14 1999-04-29 Siemens Ag Schutzschicht zum schutz eines bauteils gegen korrosion, oxidation und thermische überbeanspruchung sowie verfahren zu ihrer herstellung
EP0892090B1 (fr) 1997-02-24 2008-04-23 Sulzer Innotec Ag Procédé de fabrication de structure monocristallines
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EP1306454B1 (fr) 2001-10-24 2004-10-06 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium pour la protection d'un élément contre l'oxydation et la corrosion aux températures élevées
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Also Published As

Publication number Publication date
WO2009106375A1 (fr) 2009-09-03
EP2100689A1 (fr) 2009-09-16

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