EP2334467A1 - Procédé destiné à relier au moins une aube de turbine à un disque de turbine ou un anneau de turbine - Google Patents

Procédé destiné à relier au moins une aube de turbine à un disque de turbine ou un anneau de turbine

Info

Publication number
EP2334467A1
EP2334467A1 EP09764703A EP09764703A EP2334467A1 EP 2334467 A1 EP2334467 A1 EP 2334467A1 EP 09764703 A EP09764703 A EP 09764703A EP 09764703 A EP09764703 A EP 09764703A EP 2334467 A1 EP2334467 A1 EP 2334467A1
Authority
EP
European Patent Office
Prior art keywords
turbine
blade
ring
disk
connecting body
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Withdrawn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
EP09764703A
Other languages
German (de)
English (en)
Inventor
Thomas Uihlein
Bertram Kopperberger
Erich Steinhardt
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2334467A1 publication Critical patent/EP2334467A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
    • 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
    • B23K13/00—Welding by high-frequency current heating
    • B23K13/01—Welding by high-frequency current heating by induction heating
    • 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
    • B23K15/00—Electron-beam welding or cutting
    • B23K15/0046—Welding
    • B23K15/0053—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
    • B23K15/00—Electron-beam welding or cutting
    • B23K15/0046—Welding
    • B23K15/0093—Welding characterised by the properties of the materials to be welded
    • 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
    • B23K26/32—Bonding taking account of the properties of the material involved
    • 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
    • B23K31/00—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups
    • B23K31/02—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups relating to soldering or 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
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/30—Selection of soldering or welding materials proper with the principal constituent melting at less than 1550 degrees C
    • B23K35/3033—Ni as the principal constituent
    • 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
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/30—Selection of soldering or welding materials proper with the principal constituent melting at less than 1550 degrees C
    • B23K35/3046—Co as the principal constituent
    • 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
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/32—Selection of soldering or welding materials proper with the principal constituent melting at more than 1550 degrees C
    • B23K35/325—Ti as the principal constituent
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
    • 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
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines
    • 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
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/08—Non-ferrous metals or alloys
    • 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
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/16—Composite materials, e.g. fibre reinforced
    • 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
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/18—Dissimilar materials
    • B23K2103/26—Alloys of Nickel and Cobalt and Chromium
    • 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
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/50—Inorganic material, e.g. metals, not provided for in B23K2103/02 – B23K2103/26
    • B23K2103/52—Ceramics
    • 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
    • F05D2230/233—Electron beam welding
    • 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
    • F05D2230/234—Laser welding
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to a method for connecting at least one turbine blade with a turbine disk or a turbine ring for a turbine stage of a turbomachine, in particular a thermal gas turbine.
  • the invention further relates to a turbine stage specified in the preamble of claim 4 type for a turbine of a turbomachine and a turbomachine specified in the preamble of claim 6 Art.
  • Such a method of joining at least one turbine blade to a turbine disk or turbine ring and such a turbine stage comprising a turbine disk or turbine ring at least indirectly connected to one or more turbine blades are known in the art.
  • the turbine stage in turn serves for arrangement in a single-stage or multi-stage turbine of a turbomachine designed in particular as a thermal gas turbine.
  • the progress in gas turbine construction places ever higher demands on the materials used.
  • the turbine blades serving as guide vanes or blades are therefore essentially produced as polycrystalline, monocrystalline or directionally solidified castings from high-temperature-resistant base alloys.
  • turbine blades which are made of high-temperature composite materials.
  • Object of the present invention is therefore to provide a method of the type mentioned, which is cheaper and more flexible feasible.
  • Another object of the invention is to provide a corresponding turbine stage with a turbine disk or a turbine ring and at least one turbine blade, which is less expensive and more flexible to produce.
  • a connecting body is firstly formed on the at least one turbine blade by means of a cold gas spraying method and the connecting body is subsequently connected to the turbine disk by means of a fusion welding method connected to the turbine ring.
  • a cold spraying method is a coating method in which the material of the subsequent connecting body is applied to the turbine blade in powder form at very high speed. For this purpose, it may be provided that a gas heated to a comparatively low temperature is accelerated to supersonic speed by expansion in a nozzle (so-called Laval nozzle).
  • Pn of this gas are then introduced the powder particles and thereby accelerated to such high speeds that they form without melting or on impact with the turbine blade a firmly adhering layer with a high density and compactness.
  • the cold gas spraying process is preferably carried out such that the kinetic energy of the powder particles at the time of impact is not sufficient for a complete melting. As a result, a minimum heat input is ensured at the same time in the serving as a substrate turbine blade.
  • the impact velocity of the powder particles can be specifically adapted, for example, by optimized nozzle design, modified gas temperatures, higher gas pressures or altered particle sizes.
  • the turbine blade is connected by means of the fusion welding process via the connecting body indirectly with the turbine disk or the turbine ring.
  • all materials which can be plastically deformed, melt-weldable and withstand the later stresses during operation of an associated turbomachine can be used as the material of the connecting body.
  • the inventive method can thus be carried out considerably less expensive without high equipment costs. Since the connection between the turbine blade and the turbine disk or with the turbine ring takes place by means of the connecting body, moreover, the material and the geometry of the turbine blade of minor importance, whereby the method is particularly flexible feasible. It can basically be provided that the connecting body is formed in several parts.
  • the connecting body is processed, in particular finished, before the fusion welding process.
  • Finely machined here is understood to mean preferably machining, whereby both a desired surface quality and a required dimensional accuracy of the connecting body can be ensured simply and inexpensively.
  • the connecting body is formed in the region of a blade root of the turbine blade and / or as a blade root of the turbine blade. This allows a simple and mechanically stable connection of the turbine blade with the turbine disk or the turbine ring via the connecting body.
  • the connecting body is formed in dependence on a geometry of the turbine blade and / or the turbine disc or the turbine ring. As a result, the method can be used particularly flexibly for the representation of different turbine stages.
  • Another aspect of the invention relates to a turbine stage for a turbine of a turbomachine, wherein the turbine stage is cheaper and more flexible to produce by at least one turbine blade is connected via a means of a cold gas spraying method formed on the turbine blade connecting body with the turbine disk or the turbine ring. Further resulting advantages can be taken from the previous descriptions.
  • the manufacturing costs of the turbine stage can be additionally reduced.
  • the turbine disk or the turbine ring and / or the turbine blade made of a nickel Base alloy and / or a cobalt-based alloy and / or a titanium aluminide and / or a metal matrix composite material and / or a ceramic matrix composite material is made.
  • the turbine stage reliably has the required mechanical and thermal properties for later use in an associated turbomachine and, moreover, can be adapted particularly flexibly to the particular requirement profile.
  • a further aspect of the invention relates to a turbomachine, in particular a thermal gas turbine, with a turbine which comprises a turbine stage with a turbine disk or a turbine ring which is or at least indirectly connected to at least one turbine blade, it being provided according to the invention that the Turbine disk or the turbine ring and the at least one turbine blade of the turbine stage by means of a method according to one of the preceding embodiments are interconnected or that the turbine stage is formed according to one of the preceding embodiments.
  • Fig. 1 is a front perspective view of a turbine blade
  • FIG. 2 is an oblique perspective view of a connecting body formed on a blade root of the turbine blade shown in FIG. 1; FIG. and
  • Fig. 3 is a fragmentary and perspective front view of a turbine disk which is connected via the connecting body with the turbine blade.
  • Fig. 1 shows a front perspective view of a turbine blade 10, the general structure of which is known from the prior art.
  • the turbine blade 10, which is made as a casting of a high temperature resistant nickel-based alloy, includes a radially outer shroud 12 and a radially inner blade root 14. Since the material from which the turbine blade 10 is made, is not or only very difficult melt weldable, is By means of a cold gas spraying process, a connecting body 16 shown in FIG. 2 in a perspective oblique view is formed in the region of the blade root 14 of the turbine blade 10.
  • the connecting body 16 which is formed from a plastically deformable and melt-weldable material, makes it possible to connect the turbine blade 10 to a turbine disk 18 in a subsequent step via a cost-effective fusion welding method.
  • a turbine ring (not shown) may be provided, wherein both the turbine disk 18 and the turbine ring may be formed in one or more parts.
  • the connecting body 16 forms the blade root 14.
  • the connecting body 16 is or is made of several parts, so that the connection between the turbine blade 10 and the turbine disk 18 takes place indirectly via a plurality of partial connecting bodies (not shown).
  • FIG. 3 shows a fragmentary and perspective frontal view of the turbine disk 18, which is connected to the turbine blade 10 in the region marked with arrow III via the connecting body 16, which is formed integrally in the present case.
  • a fusion welding method for example, an electron beam welding method, a laser welding method, an inductive high frequency pressure welding method and / or a low frequency inductive pressure welding method can be used. In principle, however, other welding methods familiar to the person skilled in the art can also be provided.
  • the connecting body 16 is finished prior to the fusion welding, whereby a simple geometrical adaptation between the turbine blade 10 and the turbine disk 18 is made possible.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Optics & Photonics (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Laser Beam Processing (AREA)

Abstract

L'invention concerne un procédé destiné à relier au moins une aube de turbine (10) à un disque de turbine (18) ou à un anneau de turbine pour un étage de turbine d'une turbomachine, en particulier d'une turbine à gaz thermique, dans lequel un corps de liaison (16) est tout d'abord réalisé sur ladite au moins une aube de turbine (10) au moyen d'un procédé de projection à froid et le corps de liaison (16) est ensuite relié au moyen d'un procédé de soudage par fusion au disque de turbine (18) ou à l'anneau de turbine. L'invention concerne en outre un étage de turbine pour une turbine d'une turbomachine ainsi qu'une turbomachine comprenant une turbine.
EP09764703A 2008-10-16 2009-10-16 Procédé destiné à relier au moins une aube de turbine à un disque de turbine ou un anneau de turbine Withdrawn EP2334467A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008052030A DE102008052030B4 (de) 2008-10-16 2008-10-16 Verfahren zum Verbinden wenigstens einer Turbinenschaufel mit einer Turbinenscheibe oder einem Turbinenring
PCT/DE2009/001438 WO2010043210A1 (fr) 2008-10-16 2009-10-16 Procédé destiné à relier au moins une aube de turbine à un disque de turbine ou un anneau de turbine

Publications (1)

Publication Number Publication Date
EP2334467A1 true EP2334467A1 (fr) 2011-06-22

Family

ID=41528648

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09764703A Withdrawn EP2334467A1 (fr) 2008-10-16 2009-10-16 Procédé destiné à relier au moins une aube de turbine à un disque de turbine ou un anneau de turbine

Country Status (5)

Country Link
US (1) US20110217176A1 (fr)
EP (1) EP2334467A1 (fr)
CA (1) CA2740094A1 (fr)
DE (1) DE102008052030B4 (fr)
WO (1) WO2010043210A1 (fr)

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WO2010043210A1 (fr) 2010-04-22
CA2740094A1 (fr) 2010-04-22
DE102008052030A1 (de) 2010-04-22
US20110217176A1 (en) 2011-09-08
DE102008052030B4 (de) 2011-06-16
WO2010043210A8 (fr) 2011-05-12

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