EP2501516A1 - Soudure monocristalline de matériaux à solidification directionnelle - Google Patents

Soudure monocristalline de matériaux à solidification directionnelle

Info

Publication number
EP2501516A1
EP2501516A1 EP10779539A EP10779539A EP2501516A1 EP 2501516 A1 EP2501516 A1 EP 2501516A1 EP 10779539 A EP10779539 A EP 10779539A EP 10779539 A EP10779539 A EP 10779539A EP 2501516 A1 EP2501516 A1 EP 2501516A1
Authority
EP
European Patent Office
Prior art keywords
substrate
welding
powder
laser
melt
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Withdrawn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
EP10779539A
Other languages
German (de)
English (en)
Inventor
Bernd Burbaum
Andres Gasser
Torsten Jambor
Stefanie Linnenbrink
Norbert Pirch
Nikolai Arjakine
Georg Bostanjoglo
Torsten Melzer-Jokisch
Selim Mokadem
Michael Ott
Rolf WILKENHÖNER
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
Fraunhofer Gesellschaft zur Foerderung der Angewandten Forschung eV
Original Assignee
Siemens AG
Fraunhofer Gesellschaft zur Foerderung der Angewandten Forschung eV
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, Fraunhofer Gesellschaft zur Foerderung der Angewandten Forschung eV, Siemens Corp filed Critical Siemens AG
Priority to EP10779539A priority Critical patent/EP2501516A1/fr
Publication of EP2501516A1 publication Critical patent/EP2501516A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C30—CRYSTAL GROWTH
    • C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B11/00—Single-crystal growth by normal freezing or freezing under temperature gradient, e.g. Bridgman-Stockbarger method
    • C30B11/005—Single-crystal growth by normal freezing or freezing under temperature gradient, e.g. Bridgman-Stockbarger method by irradiation or electric discharge
    • 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
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/34—Laser welding for purposes other than joining
    • B23K26/342—Build-up 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
    • B23K35/02—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape
    • B23K35/0222—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape for use in soldering or brazing
    • B23K35/0244—Powders, particles or spheres; Preforms made therefrom
    • 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°C
    • B23K35/3033—Ni as the principal constituent
    • C—CHEMISTRY; METALLURGY
    • C30—CRYSTAL GROWTH
    • C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B13/00—Single-crystal growth by zone-melting; Refining by zone-melting
    • C30B13/16—Heating of the molten zone
    • C30B13/22—Heating of the molten zone by irradiation or electric discharge
    • C—CHEMISTRY; METALLURGY
    • C30—CRYSTAL GROWTH
    • C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B29/00—Single crystals or homogeneous polycrystalline material with defined structure characterised by the material or by their shape
    • C30B29/10—Inorganic compounds or compositions
    • C30B29/52—Alloys
    • 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
    • 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
    • B23K2103/18—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 materials other than metals or composite materials
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt
    • 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
    • F05D2230/31—Layer deposition
    • F05D2230/313—Layer deposition by physical vapour deposition
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/606—Directionally-solidified crystalline structures

Definitions

  • the invention relates to a welding method of directionally solidified metallic materials.
  • ⁇ '-reinforced SX nickel-base superalloys can not be matched by conventional welding processes or high-energy processes (laser, electron beam)
  • the welding methods used so far are not able to build up a weld metal in ⁇ '-reinforced SX nickel-base superalloys in overlap processing in one or more layers of identical SX microstructure.
  • the local solidification conditions vary such that, depending on position, dendritic growth is initiated from the primary or secondary branches. In this case, of the various possible dendritic growth directions prevails those with the most favorable growth conditions, ie the smallest inclination angle to the temperature gradient.
  • the cause for the formation of misorientations in the SX structure during powder build-up welding of ⁇ '-reinforced SX nickel-base superalloys is z. At the moment not fully understood.
  • FIG. 2 shows a gas turbine
  • FIG. 3 shows a turbine blade
  • Figure 4 is a list of superalloys. The description and the figures represent only embodiments of the invention. 1 shows the sequence of the method is schematically Darge ⁇ provides with a device. 1
  • the component 120, 130 to be repaired has a substrate 4 of a superalloy, in particular of a nickel-based superalloy according to FIG.
  • the substrate 4 consists of a
  • Nickel-base superalloy
  • the substrate 4 is repaired by applying new material 7, in particular by means of powder, to the surface 5 of the substrate 4 by build-up welding.
  • Welding beam preferably a laser beam 10 of a
  • powder is preferably used.
  • the diameter of the powder particles 7 is so small that a
  • the apparatus of the invention preferably comprises a laser (not shown) with a powder supply unit and a movement system (not shown), with which the
  • Laser beam interaction zone and the impact area for the powder 7 on the substrate surface 5 can be moved.
  • the component (substrate 4) is preferably neither preheated nor by means of a heat treatment
  • the area to be reconstructed on the substrate 4 is preferably job-welded in layers.
  • the layers are preferably meander-shaped, unidirectionally or bidirectionally applied, the scan vectors of the
  • Meandering from one location to another preferably 90 ° be rotated to avoid tying errors between the layers.
  • the dendrites 31 in the substrate 4 and the dendrites 34 in the up ⁇ transmitted region 13 are shown in FIG. 1
  • a coordinate system 25 is also shown.
  • the substrate 4 moves relatively in the x-direction 22 at the scanning speed V v .
  • the welding process is performed with process parameters regarding feed rate V r , laser power, beam diameter and
  • Freezing front leads which is smaller than 45 ° to the direction of the dendrites 31 in the substrate 4. This ensures that only the growth direction for the dendrites 34 is favored, which continues the dendrite direction 32 in the substrate 4.
  • a beam radius is necessary, which ensures that the part of the three-phase lines that bounds the solidification front 19 is completely covered by the laser beam.
  • V v scan speed
  • ⁇ thermal conductivity of the substrate
  • a process window results with respect to the intensity of the laser radiation (approximately top hat), the beam radius relative to the powder beam focus, the feed rate V v and the powder mass flow.
  • Laser radiation is in the coaxial process control a longer interaction time of the powder particles with the
  • Particle temperature and residence time in the melt cause the particles to melt completely.
  • the relative velocity V v is between 30mm / min to 100mm / min, preferably 50mm / min.
  • the power is in the range of 200W to 500W,
  • the laser beam on the Surface has a diameter of 3mm to 6mmm, preferably 4mm.
  • the mass feed rate is 300mg / min to 600mg / min, preferably 400mg / min.
  • FIG. 2 shows by way of example a gas turbine 100 in a partial longitudinal 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.
  • an intake housing 104 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
  • 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.
  • 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 . 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.
  • 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 may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • the components in particular for the turbine blade or vane 120, 130 and components of the combustion chamber 110.
  • iron-, nickel- or cobalt-based superalloys are used.
  • 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 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • On the MCrAlX may still be a thermal barrier layer, and consists for example of Zr02, Y203-Zr02, ie is not, partially or completely stabilized by yttrium oxide and / or calcium and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the guide vane 130 has an inner housing 138 of the turbine 108 facing guide vane root (not Darge here provides ⁇ ) and a side opposite the guide-blade root vane root.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • FIG. 3 shows a perspective view of a rotor blade 120 or guide vane show ⁇ 130 of a turbomachine, which extends along a longitudinal axis of the 121st
  • 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 to each other, a securing region 400, an adjoining blade or vane platform 403 and a blade 406 and a blade tip 415.
  • the vane 130 having at its blade tip 415 have a further platform (not Darge ⁇ asserted).
  • 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 for a medium which flows past the scene ⁇ felblatt 406 on a leading edge 409 and a trailing edge 412th
  • massive metallic materials in particular superalloys, are used.
  • 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 hereby be manufactured 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.
  • Such monocrystalline workpieces takes place e.g. by directed solidification from the melt.
  • These are casting processes in which the liquid metallic alloy is transformed into a monocrystalline structure, i. to the single-crystal workpiece, or directionally solidified.
  • dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, ie grains that run the entire length of the workpiece and here, for general language use, referred to as directionally solidified) or a monocrystalline structure, ie the entire workpiece ⁇ is of a single crystal.
  • a columnar grain structure columnar, ie grains that run the entire length of the workpiece and here, for general language use, referred to as directionally solidified
  • a monocrystalline structure ie the entire workpiece ⁇ is of a single crystal.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. B. (MCrAlX, M is at least one element of the group iron (Fe), cobalt (Co),
  • Nickel (Ni) 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 EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • the density is preferably 95% of the theoretical
  • 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-10A1-0, 4Y-1 are also preferably used , 5Re.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of Zr0 2 , Y2Ü3-Zr02, ie it is not, partially ⁇ or fully stabilized by yttria
  • the thermal barrier coating covers the entire MCrAlX layer.
  • Suitable coating processes such as electron beam evaporation (EB-PVD), produce stalk-shaped grains in the thermal barrier coating.
  • EB-PVD electron beam evaporation
  • the heat insulation layer may have ⁇ porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the
  • 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. If necessary, will also
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and also has, if necessary, film cooling holes 418 (indicated by dashed lines) on.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Optics & Photonics (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Plasma & Fusion (AREA)
  • Inorganic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Powder Metallurgy (AREA)

Abstract

L'invention concerne un procédé de solidification directionnelle d'un cordon de soudure (13) pendant le rechargement par soudure, en particulier pour le rechargement par soudure d'un substrat (4) d'un élément (1), qui est solidifié de manière directionnelle et présente des dendrites (31) qui s'étendent dans une direction de dentrites de substrat (32), procédé selon lequel les paramètres relatifs à l'avance, à la puissance laser, au diamètre du faisceau de soudure, au foyer de faisceau de poudre et/ou au flux massique de poudre sont établis de façon à permettre une orientation locale du gradient thermique (28) sur un front de solidification (19) qui est inférieur à 45° par rapport à la direction (32) des dendrites (31) dans le substrat (4), la vitesse relative étant comprise entre 30 mm/min et 100 mm/min, de préférence égale à 50 mm/min, et/ou la puissance étant comprise entre 200 W et 500 W, de préférence égale à 300 W, et/ou le diamètre du faisceau laser sur la surface du substrat étant compris entre 3 mm et 6 mm, de préférence égal à 4 mm, et/ou le débit massique d'apport étant compris entre 300 mg/min et 600 mg/min, de préférence égal à 400 mg/min.
EP10779539A 2009-11-16 2010-11-15 Soudure monocristalline de matériaux à solidification directionnelle Withdrawn EP2501516A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10779539A EP2501516A1 (fr) 2009-11-16 2010-11-15 Soudure monocristalline de matériaux à solidification directionnelle

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09014307A EP2322314A1 (fr) 2009-11-16 2009-11-16 Soudure monocristalline de matières actives renforcées directionnelles
PCT/EP2010/067486 WO2011058174A1 (fr) 2009-11-16 2010-11-15 Soudure monocristalline de matériaux à solidification directionnelle
EP10779539A EP2501516A1 (fr) 2009-11-16 2010-11-15 Soudure monocristalline de matériaux à solidification directionnelle

Publications (1)

Publication Number Publication Date
EP2501516A1 true EP2501516A1 (fr) 2012-09-26

Family

ID=42102267

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09014307A Ceased EP2322314A1 (fr) 2009-11-16 2009-11-16 Soudure monocristalline de matières actives renforcées directionnelles
EP10779539A Withdrawn EP2501516A1 (fr) 2009-11-16 2010-11-15 Soudure monocristalline de matériaux à solidification directionnelle

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP09014307A Ceased EP2322314A1 (fr) 2009-11-16 2009-11-16 Soudure monocristalline de matières actives renforcées directionnelles

Country Status (5)

Country Link
US (1) US20120285933A1 (fr)
EP (2) EP2322314A1 (fr)
CN (1) CN102612421B (fr)
RU (1) RU2509639C2 (fr)
WO (1) WO2011058174A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2493537A (en) * 2011-08-10 2013-02-13 Bae Systems Plc Forming a layered structure
EP2614917A1 (fr) * 2012-01-10 2013-07-17 Siemens Aktiengesellschaft Soudage laser de superalliages à base de nickel
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RU2012125028A (ru) 2013-12-27
CN102612421B (zh) 2015-12-16
RU2509639C2 (ru) 2014-03-20
US20120285933A1 (en) 2012-11-15
EP2322314A1 (fr) 2011-05-18
WO2011058174A1 (fr) 2011-05-19
CN102612421A (zh) 2012-07-25

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