EP1949988A1 - Mélange de poudre doté d'une poudre en bloc, procédé d'utilisation du mélange de poudre et composants - Google Patents

Mélange de poudre doté d'une poudre en bloc, procédé d'utilisation du mélange de poudre et composants Download PDF

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Publication number
EP1949988A1
EP1949988A1 EP07000916A EP07000916A EP1949988A1 EP 1949988 A1 EP1949988 A1 EP 1949988A1 EP 07000916 A EP07000916 A EP 07000916A EP 07000916 A EP07000916 A EP 07000916A EP 1949988 A1 EP1949988 A1 EP 1949988A1
Authority
EP
European Patent Office
Prior art keywords
powder
mixture according
powder mixture
component
chemical composition
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Withdrawn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
EP07000916A
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German (de)
English (en)
Inventor
Brigitte Dr. Heinecke
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 EP07000916A priority Critical patent/EP1949988A1/fr
Priority to PCT/EP2008/050220 priority patent/WO2008087084A1/fr
Publication of EP1949988A1 publication Critical patent/EP1949988A1/fr
Withdrawn legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/05—Mixtures of metal powder with non-metallic powder
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F1/00—Metallic powder; Treatment of metallic powder, e.g. to facilitate working or to improve properties
    • B22F1/12—Metallic powder containing non-metallic particles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
    • B22F2007/068—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts repairing articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy

Definitions

  • the invention relates to a powder mixture, one of which consists of a blocky powder, a method of using the powder mixture and components.
  • soldering or welding As may be required in the repair of hot gas components of turbine blades (refurbishment), mechanically stressed joints, such as cracks, are repaired.
  • This high-temperature solders are used, which are often based on an alloy of a component to be repaired, the melting point lowering elements are added.
  • This solder is often added a filler, which is then embedded in a solder matrix.
  • the mechanical properties of this composite material of solder matrix and filling material are significantly influenced by the microstructure, in particular by the homogeneity of the distribution of filler material in the solder matrix.
  • the object is achieved by a powder mixture according to claim 1, a method according to claim 38 and components according to claim 44, 45.
  • FIG. 1 shows the sequence of a soldering process according to the prior art.
  • a substrate 1 has a crack 4 into which a solder 7 has been introduced in different ways ( Fig. 1 Left).
  • the solder 7 according to the prior art comprises a solder material 11 and a filler material 10.
  • the solder material 11 is melted, so that the solder material 11 is present in the molten state.
  • the non-melting filler material 10 may drop to the bottom 9 of the crack 4 ( Fig. 1 right). This is not desirable, as this leads to an uneven distribution of the filling material 10.
  • FIG. 2 shows an embodiment of a powder mixture with blocky powder.
  • a component 23 has a substrate 20 with a surface 29 in which a crack 26 is present.
  • a solder 37 which also consists of a solder material 35 (first powder) and a filler 38 (second powder).
  • the solder material 35 has a lower melting point than the filler 38 and than the material of the substrate 20.
  • the first powder 35 is a superalloy having at least one melting point depressant.
  • one melting point depressant is used, which is in particular formed from the group boron (B), hafnium (Hf), silicon (Si). Further melting point depressants are conceivable. Also, another superalloy whose melting point is lower than the alloy of the substrate 20 may be used.
  • the second powder 38 ie the filler, preferably has the same composition as the substrate 20 of the component 1, 120, 130, 155, which consists of a cobalt- or nickel-based superalloy.
  • the second powder 38 has a melting point higher than that of the substrate 20 of the component 1, 120, 130, 155.
  • the second powder 38 is also ceramic.
  • the filler 38 is preferably blocky ( Fig. 2 ) and in particular has a larger particle size distribution than the solder 35.
  • this blocky powder 38 no segregation can occur, since the blocky powder particles 38 interlock with each other, with the solder 35 being distributed uniformly around the blocky powder 38.
  • the grain sizes of the first powder 35 have particle sizes of ⁇ 200 ⁇ m, especially ⁇ 100 ⁇ m.
  • the grain sizes of the second powder 38 have minimum values for the grains in the range ⁇ 0.1 mm, in particular ⁇ 200 ⁇ m.
  • the needle-like grains of the second powder 38 preferably have at least twice the value of the diameter of the first powder 38, thus lie in the range from ⁇ 200 ⁇ m, in particular ⁇ 400 ⁇ m.
  • the powders 35, 38 differ at least in the chemical composition.
  • the solder 37 contains a third powder 41 ( Fig. 3 ).
  • the following combinations are therefore advantageous in each case for the powder mixture 37:
  • the same powder morphology may be used for the second powder and the third powder when the chemical compositions of the second powder 38 and the third powder 41 are different from each other.
  • the composition of the first powder 35 is chemically different from that of the second powder 38.
  • Another chemical composition of a powder leads to (measurable) differences in the properties, e.g. Melting temperature, mechanical properties, thermal properties, corrosion properties, phase formation, ....
  • the diameter of the powder for the solder material 35 is preferably smaller than the largest dimension of the platelet-shaped powder 38 in the largest plane. The difference is at least 10%.
  • the grain sizes of the first powder 35 have particle sizes of ⁇ 200 ⁇ m, especially ⁇ 100 ⁇ m.
  • the grain sizes of the second powder 38 have minimum values for the grains in the range ⁇ 0.1 mm, in particular ⁇ 200 ⁇ m.
  • the needle-like powder to the second powder 38 preferably have at least twice the value of the diameter of the first powder 35, thus lie in the range from ⁇ 200 ⁇ m, in particular ⁇ 400 ⁇ m.
  • the powder 35 and the powders 38, 41 differ in chemical composition.
  • the frequency distribution of the largest diagonals of the powder particles of powders 35 and 38 is plotted.
  • the distance of max. (35) and max. (38) is at least 10% or 10 ⁇ m.
  • the curves may be spaced or overlapped. But even then prevents the filler 38 can separate.
  • the component 23 may include a turbine blade 120, 130 (FIG. FIG. 6 ) of a gas turbine 100 ( FIG. 5 ) be.
  • the component 23 is made of a nickel- or cobalt-based alloy, as in FIG. 8 are listed.
  • the solder material 37 is introduced into the crack 26 by a paste, by cold gas spraying or HVOF.
  • the filler 38 may correspond to the material of the substrate 20 of the component 23.
  • 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 toroidal 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.
  • Each turbine stage 112 is formed, for example, from two blade rings. As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, 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 and compressed by the compressor 105 through the intake housing 104.
  • 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. To withstand the prevailing temperatures, they can be cooled by means of a coolant.
  • 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 only longitudinal grains
  • Such superalloys are for example from EP 1 204 776 B1 .
  • EP 1 306 454 .
  • 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 earths 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 earths or hafnium.
  • Such alloys are known from the EP 0 486 489 B1 .
  • EP 0 412 397 B1 or EP 1 306 454 A1 which should be part of this disclosure in terms of chemical composition.
  • a thermal barrier coating On the MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , that is, it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • suitable coating processes such as electron beam evaporation (EB-PVD), stalk-shaped grains are produced 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 blade 120 or guide vane 130 of a turbomachine, which 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 airfoil 406.
  • blades 120, 130 for example, solid metallic materials, in particular superalloys, are used in all regions 400, 403, 406 of the blade 120, 130.
  • Such superalloys are for example from EP 1 204 776 B1 .
  • EP 1 306 454 .
  • 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.
  • the term generally refers to directionally solidified microstructures, which means both single crystals that have no grain boundaries or at most small angle grain boundaries, and stem crystal structures that have probably longitudinal grain boundaries but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified structures. Such methods are known from U.S. Patent 6,024,792 and the EP 0 892 090 A1 known; these writings are part of the revelation regarding the solidification process.
  • 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 the EP 0 486 489 B1 . EP 0 786 017 B1 . EP 0 412 397 B1 or EP 1 306 454 A1 which are to be part of this disclosure with regard to the chemical composition of the alloy.
  • the density is preferably 95% of the theoretical density.
  • a thermal barrier coating which is preferably the outermost layer, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , that is, it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • the thermal barrier coating covers the entire MCrAlX layer.
  • suitable coating processes such as electron beam evaporation (EB-PVD), stalk-shaped grains are produced 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 need to be deprotected after use (e.g., 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. This is followed by a re-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.
  • the 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 plurality of burners 107 arranged around a rotation axis 102 in the circumferential direction 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 side with an inner lining formed from heat shield elements 155.
  • Each heat shield element 155 made of an alloy is equipped on the working medium 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 0 412 397 B1 or EP 1 306 454 A1 which are to be part of this disclosure with regard to the chemical composition of the alloy.
  • a ceramic thermal barrier coating may be present and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • suitable coating processes such as electron beam evaporation (EB-PVD)
  • stalk-shaped grains are produced in the thermal barrier coating.
  • APS atmospheric plasma spraying
  • LPPS LPPS
  • VPS vacuum plasma spraying
  • CVD chemical vaporation
  • the thermal barrier coating 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.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07000916A 2007-01-17 2007-01-17 Mélange de poudre doté d'une poudre en bloc, procédé d'utilisation du mélange de poudre et composants Withdrawn EP1949988A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP07000916A EP1949988A1 (fr) 2007-01-17 2007-01-17 Mélange de poudre doté d'une poudre en bloc, procédé d'utilisation du mélange de poudre et composants
PCT/EP2008/050220 WO2008087084A1 (fr) 2007-01-17 2008-01-10 Mélange poudreux comprenant de la poudre en blocs, procédé d'utilisation du mélange poudreux et éléments de construction

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07000916A EP1949988A1 (fr) 2007-01-17 2007-01-17 Mélange de poudre doté d'une poudre en bloc, procédé d'utilisation du mélange de poudre et composants

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EP1949988A1 true EP1949988A1 (fr) 2008-07-30

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EP (1) EP1949988A1 (fr)
WO (1) WO2008087084A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8235275B1 (en) 2011-07-19 2012-08-07 Alstom Technology Ltd. Braze foil for high-temperature brazing and methods for repairing or producing components using a braze foil
US20130020377A1 (en) * 2011-07-19 2013-01-24 Alexander Stankowski Braze alloy for high-temperature brazing and methods for repairing or producing components using a braze alloy
EP2614920A1 (fr) * 2012-01-11 2013-07-17 Siemens Aktiengesellschaft Procédé de soudage à l'aide d'un matériau de soudage différent, dispositif associé ainsi que composant
DE102012020829A1 (de) * 2012-10-16 2014-04-17 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Pulvergemisch für die Herstellung metallischer und/oder keramischer Bauteile, Verfahren zur Herstellung des Pulvergemischs sowie Verfahren zur Herstellung von Bauteilen
WO2015161980A1 (fr) * 2014-04-23 2015-10-29 Siemens Aktiengesellschaft Procédé de fabrication d'une pièce

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010026048A1 (de) 2010-07-03 2012-01-05 Mtu Aero Engines Gmbh Nickelbasis-Lotlegierung

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5156321A (en) * 1990-08-28 1992-10-20 Liburdi Engineering Limited Powder metallurgy repair technique
US5264011A (en) * 1992-09-08 1993-11-23 General Motors Corporation Abrasive blade tips for cast single crystal gas turbine blades
GB2352727A (en) * 1999-05-11 2001-02-07 Baker Hughes Inc Hardfacing composition for earth boring bits
DE10157079A1 (de) * 2001-07-06 2003-02-06 Woka Schweistechnik Gmbh Matrixpulver zur Herstellung von Körpern bzw. Bauteilen für Verschleißschutzanwendungen sowie ein daraus hergestelltes Bauteil
EP1716965A1 (fr) * 2005-04-28 2006-11-02 Siemens Aktiengesellschaft Brasure comprenant de la poudre d'apport métallique sous forme élémentaire

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5156321A (en) * 1990-08-28 1992-10-20 Liburdi Engineering Limited Powder metallurgy repair technique
US5264011A (en) * 1992-09-08 1993-11-23 General Motors Corporation Abrasive blade tips for cast single crystal gas turbine blades
GB2352727A (en) * 1999-05-11 2001-02-07 Baker Hughes Inc Hardfacing composition for earth boring bits
DE10157079A1 (de) * 2001-07-06 2003-02-06 Woka Schweistechnik Gmbh Matrixpulver zur Herstellung von Körpern bzw. Bauteilen für Verschleißschutzanwendungen sowie ein daraus hergestelltes Bauteil
EP1716965A1 (fr) * 2005-04-28 2006-11-02 Siemens Aktiengesellschaft Brasure comprenant de la poudre d'apport métallique sous forme élémentaire

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8235275B1 (en) 2011-07-19 2012-08-07 Alstom Technology Ltd. Braze foil for high-temperature brazing and methods for repairing or producing components using a braze foil
US20130020377A1 (en) * 2011-07-19 2013-01-24 Alexander Stankowski Braze alloy for high-temperature brazing and methods for repairing or producing components using a braze alloy
US8881965B2 (en) * 2011-07-19 2014-11-11 Alstom Technology Ltd. Braze alloy for high-temperature brazing and methods for repairing or producing components using a braze alloy
EP2614920A1 (fr) * 2012-01-11 2013-07-17 Siemens Aktiengesellschaft Procédé de soudage à l'aide d'un matériau de soudage différent, dispositif associé ainsi que composant
DE102012020829A1 (de) * 2012-10-16 2014-04-17 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Pulvergemisch für die Herstellung metallischer und/oder keramischer Bauteile, Verfahren zur Herstellung des Pulvergemischs sowie Verfahren zur Herstellung von Bauteilen
DE102012020829B4 (de) 2012-10-16 2019-01-03 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Verfahren zur Herstellung von Verbundbauteilen
WO2015161980A1 (fr) * 2014-04-23 2015-10-29 Siemens Aktiengesellschaft Procédé de fabrication d'une pièce

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