EP1843009A1 - Segment d'ailette de guidage d'une turbomachine, procédé de fabrication associé et turbomachine - Google Patents

Segment d'ailette de guidage d'une turbomachine, procédé de fabrication associé et turbomachine Download PDF

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Publication number
EP1843009A1
EP1843009A1 EP06007332A EP06007332A EP1843009A1 EP 1843009 A1 EP1843009 A1 EP 1843009A1 EP 06007332 A EP06007332 A EP 06007332A EP 06007332 A EP06007332 A EP 06007332A EP 1843009 A1 EP1843009 A1 EP 1843009A1
Authority
EP
European Patent Office
Prior art keywords
platform
vane segment
guide vane
fastening
segment
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Withdrawn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
EP06007332A
Other languages
German (de)
English (en)
Inventor
Katharina Bergander
Georg Dr. Bostanjoglo
Tobias Dr. Buchal
Winfried Dr. Esser
Dirk Dr. Goldschmidt
Torsten Koch
Rudolf Küperkoch
Thorsten Mattheis
Jan Münzer
Ralf Müsgen
Matthias Dr. Oechsner
Ursula Pickert
Volker Dr. Vosberg
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
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 filed Critical Siemens AG
Priority to EP06007332A priority Critical patent/EP1843009A1/fr
Priority to PL07704682T priority patent/PL2002085T3/pl
Priority to DE502007002816T priority patent/DE502007002816D1/de
Priority to ES07704682T priority patent/ES2339717T3/es
Priority to JP2009503509A priority patent/JP4782225B2/ja
Priority to EP07704682A priority patent/EP2002085B1/fr
Priority to PCT/EP2007/051669 priority patent/WO2007113053A1/fr
Priority to US12/225,933 priority patent/US8128357B2/en
Priority to CN2007800210741A priority patent/CN101460709B/zh
Priority to RU2008144021/06A priority patent/RU2421624C2/ru
Priority to AT07704682T priority patent/ATE457413T1/de
Publication of EP1843009A1 publication Critical patent/EP1843009A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/238—Soldering
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the invention relates to a vane segment of a thermal turbomachine, in particular a gas turbine, with at least one profiled airfoil arranged on a platform, wherein a number of fastening elements for fastening the vane segment to an associated guide vane carrier is arranged on the side of the platform facing away from the airfoil.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit connected downstream of the combustion chambers, where it relaxes in a work-performing manner.
  • a number of rotor blades which are usually combined to form groups of blades or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the flow medium.
  • To guide the flow medium in the turbine unit also commonly associated guide blade rows are arranged between adjacent blade rows with the turbine housing.
  • the turbine blades, in particular the guide vanes usually have a profiled airfoil extending along a blade axis for suitable guidance of the working medium, at the end for attachment of the turbine blade to the respective support body extending transversely to the blade axis Platform is formed. The top of the platform facing the airfoil forms an outer boundary surface for the hot gas flow channel of the gas turbine.
  • the platform of the respective vane usually has a number of hook-like fastening elements on its underside or rear side facing away from the vane blade.
  • the vane is inserted with its fasteners or mounting hooks into corresponding receiving grooves of a vane carrier, aligned and then suitably, for. with the help of Stemmblechen, fixed.
  • a plurality of circumferentially of the gas turbine mutually adjacent vane blades of a row of vanes can be arranged on a common platform, so that the complete, hereinafter referred to as vane segment blade unit using the platform-side mounting hooks axially or circumferentially in the associated Guide vane carrier is inserted.
  • vane segment in the following, and in particular in the claims, always include the case of a single vane with only one airfoil, unless this is expressly excluded.
  • the vane or the entire vane segment is made by a casting process so that the platform and platform-side fasteners are integral, co-molded components of the vane or vane segment.
  • a so-called wax model of the blade or the blade segment is manufactured, which is then provided by repeated immersion in a ceramic material with a ceramic coating. Once this has a sufficient thickness, the provided with the ceramic coating wax model is burned out, wherein the ceramic solidifies and the liquefied or vaporized wax is removed.
  • the ceramic negative mold obtained in this way is finally filled with the metallic blade material. After the solidification of the melt and the removal of the shell-like outer casting mold, ceramic core elements still remaining in the blade body, which were previously introduced to form cavities or cooling channels integrated in the blade body, are removed by leaching with caustic soda or the like.
  • the hook-like protruding from the platform fasteners cause in the manufacturing process in several respects difficulties.
  • the production of the wax model is relatively cumbersome because the formation of the fastening hook comparatively complex wax tools with a variety of so-called mask elements or slide are required.
  • the attachment hooks are problem areas, since the undercuts in the construction of the shell mold can be sanded poorly and in the subsequent casting process due to their exposed position always to form Lunkerfeldern, d. H. tend to material defects caused by heat shrinkage in the cooling component.
  • the invention is therefore an object of the invention to provide a vane segment of the type mentioned, the case of simple and inexpensive held production while avoiding casting technical problem areas is designed for a particularly reliable and secure attachment to an associated vane carrier. Furthermore, a method suitable for the production of the vane segment should be specified.
  • the object is achieved in that at least one section of at least one of the fastening elements is a separately manufactured component fixedly connected to the platform or to a further section of the fastening element.
  • the invention is based on the consideration that the casting material for the vane segment should usually be optimized for a high high-temperature strength, so as to achieve a high operational safety and structural stability and the longest possible life of the directly exposed to the hot working medium sections, in particular the to ensure the flow channel of the gas turbine in the projecting blades and the flow channel facing the top of the platform.
  • Such a design may not be optimal for the functionally and structurally decoupled from the rest of the blade segment fasteners that are exposed on the one hand by the upstream platform only comparatively low thermal stress, but on the other hand relatively high mechanical loads and Need to accommodate storage or holding forces.
  • the respective fastening element comprises a protruding from the platform, angularly bent fastening hook, which is adapted in its shape and contour to the associated receiving groove of a vane carrier.
  • a possible alternative to this is a substantially straight profile piece, which is insertable into a polygonal receptacle in the turbine housing.
  • the respective fastening element preferably comprises one with a bearing surface on the rear, hot gas remote side of the platform resting connection element.
  • the connecting element is expediently designed in the manner of a flat connecting plate with a flat bearing surface. To realize a low installation height, the connecting element or the connecting plate can be sunk in a corresponding recess of the platform.
  • the connecting element is positively fixed in a matched to the shape of the connecting element depression or groove of the platform.
  • a positive connection for example, given by the fact that the platform in the edge region of the recess or the groove has a number of projections which engage around the connecting element in each case on its side facing away from the support surface.
  • the connecting element is laterally inserted into the recess or the receiving groove of the platform and then fixed in a suitable manner, for example, positive, non-positive and / or cohesive against lateral slipping. Since the connection forces are substantially absorbed by the projections positively surrounding the connecting element, the additional fixation must be designed only for relatively low loads.
  • a cohesive connection preferably by soldering or welding, may be provided.
  • the respective fastener for a high mechanical strength is made integrally from a one-component workpiece.
  • the attachment hook can be milled as a straight profile piece or extruded and bent in a second operation in the required radius.
  • the fastening element is preferably produced from a material which is less resistant to high temperatures but tougher than the rest of the stator blade segment.
  • the guide vane or vane segment has a plurality of fasteners for secure attachment to the vane support, and preferably each of the fastener elements is a separately fabricated and configured component as described above.
  • a gas turbine typically includes a plurality of turbine stages, each of the turbine stages including a plurality of stator vanes circumferentially disposed around the flow passage on the turbine housing, which in their entirety form a row of vanes.
  • a plurality of adjacent guide vanes can be combined to form a vane segment or a "multiple".
  • Each of the guide vanes or each guide vane segment expediently has a platform with hook-like fastening elements, wherein the specifications for the hooking profile with respect to bending angle and / or bending radius generally vary with the installation position, ie depend in particular on the turbine stage or on the row of guide vanes.
  • Particularly advantageous in this context is a standardized or standardized design of the connecting elements and the corresponding platform-side receptacles or depressions, by means of which the fastening elements are connected to the respective platform.
  • the respective profile piece, from which arises by bending the fastening hooks can look the same in the original "raw state" for all fasteners.
  • One and the same fastener can thus be used in principle for all turbine stages of a turbine; only the bending radius and / or the bending angle of the fastening hook must be at the respective site or on the be adapted to the respective purpose.
  • the bending of the profile piece takes place before the connection of the connecting element with the platform of the vane segment, because this facilitates the handling and the implementation of the bending process.
  • the illustrated in Figure 1 in a schematic side view partially and partially cut guide vane 2 comprises a extending in the direction of the blade axis 4 profiled airfoil 6, to which in the region of the blade root a substantially transverse to the blade axis 4 oriented platform 8 is formed.
  • the "upper side 10" of the platform 8, which is oriented toward the blade leaf 6, forms an outer boundary of a hot gas-carrying flow channel in a gas turbine (not shown).
  • a number of hook-like fasteners 14 At the side facing away from the blade 6 "bottom” 12 or back of the platform 8 is a number of hook-like fasteners 14, by means of which the vane 2 in an associated vane support (not shown) mounted on the turbine housing / is attached.
  • the fastening elements 14 is visible, which is mounted with respect to the axial direction 16 near the trailing edge of the airfoil 6; another fastener is disposed in the vicinity of the leading edge not shown here.
  • the fastener 14 is specifically adapted to the associated with the entanglement in the vane support mechanical loads in simple and inexpensive held.
  • the fastener 14 is designed as a separate, independent of the remaining guide blade 2 made and only subsequently connected to it component, wherein the material used for the fastener 14 is less resistant to high temperatures, but it is tougher as the material from which the airfoil 6 and the platform 8 are made.
  • the fastening element 14 comprises in addition to a projecting from the back 12 of the platform 8, approximately at right angles angled mounting hook 18 thereon a molded connection plate 20 with a rectangular base.
  • the connecting plate 20 is positively fixed in an associated recess 21 of the platform 8. With its flat bearing surface 22, the connecting plate 20 is flat on the base of the recess 21.
  • the depth of the recess 21 corresponds to the thickness of the connecting plate 20, so that there is an offset-free transition in the edge region to the platform surface.
  • two opposite longitudinal edges 24 of the connecting plate 20 are chamfered in the embodiment shown in FIG 1 that they are surrounded by complementary, parallel to the longitudinal edges 24 extending projections 26 at the edge of the platform-side recess 21 or enclosed.
  • the projections 26 thus form a perpendicular to the plane extending guide and mounting rail into which the connecting plate 20 is inserted for mounting the fastener 14.
  • additional fixing means not shown here may be provided. A shift in the other two spatial directions, so on the one hand parallel to the blade axis 4 and the other in the axial direction 16 is excluded by the positive attachment.
  • the fastening element 14 shown in FIG 2 is analogous to the fastener 14 of Figure 1 with its connection plate 20 recessed in an associated recess 21 of the platform 8, but not fixed in contrast to this form-fitting. Rather, the connecting plate 20 is connected by a number of solder pads or solder joints 28 between the bearing surfaces 22 cohesively with the platform 8. For the required Hochtemperaturlötung a large number of solders / heat treatments are commercially available, the geometry of the solder joints should be carried out expediently full-scale. The selection of the soldering process is essentially influenced by the operating conditions at the soldering, the material pairing and the compatibility with other heat treatment requirements.
  • FIG 3 shows a variant in which only an outer portion 30 of the fastener 14 is a separately manufactured component, the rest of the part, however, integrally formed on the platform 8 and is cast together with her.
  • the "adapter" -effective outer portion 30, as it were, has a skirt 32, similar to a cap for a bottle or pipe, with which it encloses the platform-side component of the fastener 14 at its outer end.
  • the dimensions are chosen such that prior to the introduction of a joining agent results in a loose, play-afflicted seat, which can be adapted to the present on the respective site geometric requirements and thereby compensates for manufacturing tolerances and fluctuations.
  • the two components of the fastening element 14 are connected to one another by a soldering compound 36 introduced into the intermediate space 34 and subsequently solidified.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Machine Tool Units (AREA)
  • External Artificial Organs (AREA)
  • Primary Cells (AREA)
EP06007332A 2006-04-06 2006-04-06 Segment d'ailette de guidage d'une turbomachine, procédé de fabrication associé et turbomachine Withdrawn EP1843009A1 (fr)

Priority Applications (11)

Application Number Priority Date Filing Date Title
EP06007332A EP1843009A1 (fr) 2006-04-06 2006-04-06 Segment d'ailette de guidage d'une turbomachine, procédé de fabrication associé et turbomachine
PL07704682T PL2002085T3 (pl) 2006-04-06 2007-02-21 Segment łopatek kierujących cieplnej maszyny przepływowej, przynależny sposób wytwarzania oraz cieplna maszyna przepływowa
DE502007002816T DE502007002816D1 (de) 2006-04-06 2007-02-21 Leitschaufelsegment einer thermischen strömungsmaschine, zugehöriges herstellungsverfahren sowie thermische strömungsmaschine
ES07704682T ES2339717T3 (es) 2006-04-06 2007-02-21 Segmento de alabe guia de una turbomaquina termica, procedimiento de produccion correspondiente asi como turbomaquina termica.
JP2009503509A JP4782225B2 (ja) 2006-04-06 2007-02-21 熱流体機械の静翼セグメント、その製造方法並びに熱流体機械
EP07704682A EP2002085B1 (fr) 2006-04-06 2007-02-21 Segment d'aubes fixes d'une turbomachine thermique, procédé de fabrication associé et turbomachine thermique
PCT/EP2007/051669 WO2007113053A1 (fr) 2006-04-06 2007-02-21 Segment d'aubes fixes d'une turbomachine thermique, procédé de fabrication associé et turbomachine thermique
US12/225,933 US8128357B2 (en) 2006-04-06 2007-02-21 Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine
CN2007800210741A CN101460709B (zh) 2006-04-06 2007-02-21 热涡轮机的导向叶片段、相应的制造方法及热涡轮机
RU2008144021/06A RU2421624C2 (ru) 2006-04-06 2007-02-21 Сегмент направляющих лопаток тепловой лопаточной машины, способ его изготовления и тепловая лопаточная машина
AT07704682T ATE457413T1 (de) 2006-04-06 2007-02-21 Leitschaufelsegment einer thermischen strömungsmaschine, zugehöriges herstellungsverfahren sowie thermische strömungsmaschine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06007332A EP1843009A1 (fr) 2006-04-06 2006-04-06 Segment d'ailette de guidage d'une turbomachine, procédé de fabrication associé et turbomachine

Publications (1)

Publication Number Publication Date
EP1843009A1 true EP1843009A1 (fr) 2007-10-10

Family

ID=37075825

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06007332A Withdrawn EP1843009A1 (fr) 2006-04-06 2006-04-06 Segment d'ailette de guidage d'une turbomachine, procédé de fabrication associé et turbomachine
EP07704682A Not-in-force EP2002085B1 (fr) 2006-04-06 2007-02-21 Segment d'aubes fixes d'une turbomachine thermique, procédé de fabrication associé et turbomachine thermique

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP07704682A Not-in-force EP2002085B1 (fr) 2006-04-06 2007-02-21 Segment d'aubes fixes d'une turbomachine thermique, procédé de fabrication associé et turbomachine thermique

Country Status (10)

Country Link
US (1) US8128357B2 (fr)
EP (2) EP1843009A1 (fr)
JP (1) JP4782225B2 (fr)
CN (1) CN101460709B (fr)
AT (1) ATE457413T1 (fr)
DE (1) DE502007002816D1 (fr)
ES (1) ES2339717T3 (fr)
PL (1) PL2002085T3 (fr)
RU (1) RU2421624C2 (fr)
WO (1) WO2007113053A1 (fr)

Cited By (2)

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Publication number Priority date Publication date Assignee Title
EP2118446B1 (fr) * 2007-03-12 2010-06-30 Siemens Aktiengesellschaft Turbine équipée d'un rotor composé de disques rotoriques et d'un hauban
EP2282012A1 (fr) * 2009-07-03 2011-02-09 Alstom Technology Ltd Aube directrice d'une turbine à gaz et procédé de remplacement d'un couvercle d'une aube directrice d'une turbine à gaz

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DE102008043605B4 (de) * 2007-11-16 2015-05-07 Alstom Technology Ltd. Verfahren zur Herstellung eines Turbinengehäuses
FR2976968B1 (fr) * 2011-06-21 2015-06-05 Snecma Piece de turbomachine formant redresseur de compresseur ou distributeur de turbine et procede pour sa fabrication
US9631517B2 (en) 2012-12-29 2017-04-25 United Technologies Corporation Multi-piece fairing for monolithic turbine exhaust case
EP3000980A3 (fr) * 2014-09-29 2016-04-13 United Technologies Corporation Composant hybride comprenant l'alliage gamma tial
US10711637B2 (en) * 2017-06-15 2020-07-14 General Electric Company Turbine component assembly
CN113500479B (zh) * 2021-07-07 2022-06-03 彭忠捷 一种骨科手术钢丝导引钩的自动加工机器人

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EP1505259A1 (fr) * 2003-08-08 2005-02-09 ROLLS-ROYCE plc Ensemble pour le montage d'un composant non rotatif d'une turbine à gaz

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2118446B1 (fr) * 2007-03-12 2010-06-30 Siemens Aktiengesellschaft Turbine équipée d'un rotor composé de disques rotoriques et d'un hauban
EP2282012A1 (fr) * 2009-07-03 2011-02-09 Alstom Technology Ltd Aube directrice d'une turbine à gaz et procédé de remplacement d'un couvercle d'une aube directrice d'une turbine à gaz
US8727720B2 (en) 2009-07-03 2014-05-20 Alstom Technology Ltd Guide vane of a gas turbine and method for replacing a cover plate of a guide vane of a gas turbine

Also Published As

Publication number Publication date
CN101460709A (zh) 2009-06-17
EP2002085A1 (fr) 2008-12-17
WO2007113053A1 (fr) 2007-10-11
JP2009532623A (ja) 2009-09-10
PL2002085T3 (pl) 2010-07-30
CN101460709B (zh) 2011-11-02
US20090304503A1 (en) 2009-12-10
US8128357B2 (en) 2012-03-06
ATE457413T1 (de) 2010-02-15
ES2339717T3 (es) 2010-05-24
RU2008144021A (ru) 2010-05-20
EP2002085B1 (fr) 2010-02-10
DE502007002816D1 (de) 2010-03-25
RU2421624C2 (ru) 2011-06-20
JP4782225B2 (ja) 2011-09-28

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