EP2274130A1 - Composant avec cordon de soudure et procédé de fabrication d'un cordon de soudure - Google Patents

Composant avec cordon de soudure et procédé de fabrication d'un cordon de soudure

Info

Publication number
EP2274130A1
EP2274130A1 EP09731543A EP09731543A EP2274130A1 EP 2274130 A1 EP2274130 A1 EP 2274130A1 EP 09731543 A EP09731543 A EP 09731543A EP 09731543 A EP09731543 A EP 09731543A EP 2274130 A1 EP2274130 A1 EP 2274130A1
Authority
EP
European Patent Office
Prior art keywords
weld
ramp
component
length
substrate
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Withdrawn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
EP09731543A
Other languages
German (de)
English (en)
Inventor
Bernd Burbaum
Selim Mokadem
Norbert Pirch
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
Publication of EP2274130A1 publication Critical patent/EP2274130A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/20—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
    • 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
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/04—Repairing fractures or cracked metal parts or products, e.g. castings
    • B23P6/045—Repairing fractures or cracked metal parts or products, e.g. castings of turbine components, e.g. moving or stationary blades, rotors, etc.
    • 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
    • F01D5/005—Repairing methods or devices
    • 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
    • B23K2103/02—Iron or ferrous 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
    • 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
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/175—Superalloys
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/176—Heat-stable alloys
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12389—All metal or with adjacent metals having variation in thickness

Definitions

  • the invention relates to a component with a weld and a method for producing a weld.
  • Welding processes are often used to remelt cracks or to apply material. A certain amount of power is used to melt the material.
  • the object is achieved by a component according to claim 1 and a method for producing a weld according to claim 10.
  • Figure 3 4, 5 a weld of a component
  • Figure 6 7 shows a course of a laser power
  • Figure 8 is a gas turbine
  • FIG. 9 perspective view of a turbine blade FIG. 10 in perspective a combustion chamber and FIG. 11 a list of superalloys.
  • FIG. 1 shows a cross section through a substrate 4 of a component 1, 120, 130, 155 (FIGS. 8, 9, 10) with a weld seam 10 'according to the prior art.
  • the substrate 4 has a weld 10 ', which is given by a length 1 and a thickness d.
  • the length 1 is the longest extent of the weld 10, 10 '.
  • FIG. 2 shows a cross section along the length 1 of the welding seam 10 'from FIG. 1.
  • the weld 10 ' is rectangular in this cross section.
  • FIG. 3 shows a weld seam 10 according to the invention.
  • the substrate 4 has in particular for components 1, 120, 130,
  • the substrate 4 of the component 1, 120, 130 has a directionally solidified structure, ie a monocrystalline structure (SX) or has columnar grains (DS).
  • the thickness of the weld 10 tapers at the end 53 of the weld 10 at the end 53 of the weld 10 runs
  • Weld 10 thus in the form of a ramp 44, which is preferably formed bent, wherein the weld 10 also has a directionally solidified structure (DS, SX), in particular without misalignments.
  • the orientation of the directionally solidified structure (DS, SX) of the weld seam 10 is preferably the same as that of the directionally solidified structure (DS, SX) of the substrate 4.
  • the weld 10 preferably has the same material as the substrate 4. This is the case with laser remelting. When material has been added for the weld 10, the material of the weld 10 may be different.
  • the ramp 44 has in the direction of the length 1 a length .DELTA.X, which is significantly smaller than the total length 1 of the weld 10: .DELTA.X ⁇ 1, in particular .DELTA.X / 1 ⁇ 33%, in particular ⁇ 25%.
  • ⁇ X 3mm-7mm, especially 5mm. This is preferably independent of the length 1 of the weld 10.
  • the ramp 44 can extend to the surface 59 (FIGS. 3, 4) or remain below (FIG. 5) of the surface 59, so that a depth d '(d' ⁇ d) with vertical course to the surface 59 remains ,
  • the embodiments for the ramp 44 apply accordingly to the ramp 44 '.
  • the ramp-shaped course 44, 44 'of the weld 10 at the end 53, 56 of the weld 10 is achieved by reducing the power P of the welding device from a distance ⁇ X before the end 53 of the weld 10 or over a length ⁇ X and also a ramp-shaped Course 62 has (Fig. 6, 7).
  • the value for ⁇ X is 5mm.
  • the power P at the end 53 of the weld 10 is reduced to zero ( Figure 7).
  • the distance .DELTA.X corresponds to a certain time of a travel time of substrate 4 and welding device to each other, which is preferably between 4s and 8s, most preferably 6s.
  • the power of the welder or laser is linearly reduced (or linearly increased initially).
  • Laser power and travel speed are adjusted so that the size (depth) of the melt is continuously reduced, but so that the melt front is maintained, albeit at a reduced melt rate.
  • the power P of the welding device is raised by OW.
  • the laser power and the other parameters are adjusted so that a directionally solidified structure (SX, DS) is achieved in the weld 10, which preferably has the same structure (SX, DS) as the substrate.
  • a preheating temperature of the substrate 4 is preferably from 400 0 C to 600 0 C, most preferably 500 0 C, which is preferably controlled during the process.
  • the power of the laser is preferably 400W to 600W, most preferably 500W, the diameter of the laser beam being preferably 4mm.
  • the travel speed is preferably 40 mm / min - 60 mm / min, in particular 50 mm / min.
  • FIG. 8 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, which is also referred to as a turbine runner.
  • a compressor 105 for example, a torus-like
  • Combustion chamber 110 in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109.
  • the annular combustion chamber 110 communicates with an example annular hot gas channel 111.
  • 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.
  • 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.
  • substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • SX structure monocrystalline
  • DS structure longitudinal grains
  • iron-, nickel- or cobalt-based superalloys are used as the material for the components, in particular for the turbine blade 120, 130 and components of the combustion chamber 110.
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; These documents are part of the disclosure regarding the chemical composition of the alloys.
  • 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. 9 shows a perspective view of a moving blade 120 or guide blade 130 of a turbomachine that extends along a longitudinal axis 121.
  • the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 consecutively a fastening region 400, a blade platform 403 adjacent thereto and an airfoil 406 and a blade tip 415.
  • the blade 130 may have at its blade tip 415 another platform (not shown).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the airfoil 406.
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; These documents are part of the disclosure regarding the chemical composition of the alloy.
  • 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 for example, by directed solidification from the melt. These are casting processes in which the liquid metallic alloy to monocrystalline structure, ie 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, in common parlance, referred to as directionally solidified) or a monocrystalline structure, ie the whole Workpiece consists of a single crystal.
  • Structures are also known as directionally rigidified structures
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, which should be part of this disclosure with regard to the chemical composition of the alloy.
  • the density is preferably 95% of the theoretical density.
  • the layer composition comprises Co-30Ni-28Cr-8A1-0, 6Y-0, 7Si or Co-28Ni-24Cr-10Al-0, 6Y.
  • nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-IIAl-O, 4Y-2Re or Ni-25Co-17Cr-10Al-0.4Y-1 are also preferably used , 5RE.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of Zr ⁇ 2, Y2Ü3-Zr ⁇ 2, i. 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 methods e.g. Electron beam evaporation (EB-PVD) produces stalk-shaped grains in the thermal barrier coating.
  • the thermal barrier coating may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and may still film cooling holes 418 (indicated by dashed lines) on.
  • FIG. 10 shows a combustion chamber 110 of the gas turbine 100.
  • the combustion chamber 110 is designed, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 107 arranged in the circumferential direction about an axis of rotation 102 open into a common combustion chamber space 154, create the flames 156.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C. to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the working medium M with an inner lining formed of 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.
  • Each heat shield element 155 made of an alloy is equipped on the working fluid side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating) or is made of high-temperature-resistant material (solid ceramic blocks).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • MCrAlX means: M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, which should 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 ZrC> 2, Y2Ü3-ZrO2, ie it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • thermal barrier coating may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • Refurbishment means that turbine blades 120, 130, 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.
  • cracks in the turbine blade 120, 130 or the heat shield element 155 are also repaired. This is followed by a re-coating of the turbine blades 120, 130, heat shield elements 155 and a renewed use of the turbine blades 120, 130 or the heat shield elements 155.

Landscapes

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

Abstract

Dans le soudage, il se produit fréquemment des fissures à l'extrémité du cordon de soudure. Dans le procédé de l'invention, dans lequel la puissance est réduite à l'extrémité (53) d'un cordon de soudure (10), la naissance de fissures est réduite.
EP09731543A 2008-04-18 2009-03-25 Composant avec cordon de soudure et procédé de fabrication d'un cordon de soudure Withdrawn EP2274130A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008019636A DE102008019636A1 (de) 2008-04-18 2008-04-18 Bauteil mit Schweißnaht und Verfahren zur Herstellung einer Schweißnaht
PCT/EP2009/053511 WO2009127504A1 (fr) 2008-04-18 2009-03-25 Composant avec cordon de soudure et procédé de fabrication d'un cordon de soudure

Publications (1)

Publication Number Publication Date
EP2274130A1 true EP2274130A1 (fr) 2011-01-19

Family

ID=40833535

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09731543A Withdrawn EP2274130A1 (fr) 2008-04-18 2009-03-25 Composant avec cordon de soudure et procédé de fabrication d'un cordon de soudure

Country Status (6)

Country Link
US (2) US20110111248A1 (fr)
EP (1) EP2274130A1 (fr)
KR (1) KR20110003536A (fr)
CN (1) CN102006965B (fr)
DE (1) DE102008019636A1 (fr)
WO (1) WO2009127504A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2730364A1 (fr) * 2012-11-08 2014-05-14 Siemens Aktiengesellschaft Support de soudure sur une zone périphérique
EP2803441A1 (fr) * 2013-05-13 2014-11-19 Siemens Aktiengesellschaft Procédé de soudage laser
US20150132143A1 (en) * 2013-11-11 2015-05-14 Gerald J. Bruck Welding process and reduced restraint weld joint
DE102013227148A1 (de) * 2013-12-23 2015-06-25 Kuka Roboter Gmbh Schweißroboter und Verfahren zum Betreiben einer Laserschweißvorrichtung
US20160069184A1 (en) * 2014-09-09 2016-03-10 Rolls-Royce Corporation Method of blade tip repair
GB2541412B (en) * 2015-08-18 2018-08-01 M Solv Ltd Method and Apparatus for Forming a Conductive Track
JP7072110B1 (ja) * 2021-09-21 2022-05-19 Dmg森精機株式会社 損傷部品の補修方法

Family Cites Families (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4157923A (en) * 1976-09-13 1979-06-12 Ford Motor Company Surface alloying and heat treating processes
US4441012A (en) * 1981-12-14 1984-04-03 General Electric Company Method and apparatus for controlling heating power during the application of molten filler material to a workpiece
US4705203A (en) * 1986-08-04 1987-11-10 United Technologies Corporation Repair of surface defects in superalloy articles
EP0415570B1 (fr) * 1989-08-01 1996-03-13 Ishikawajima-Harima Heavy Industries Co., Ltd. Acier inoxydable résistant à la corrosion
DE58908611D1 (de) 1989-08-10 1994-12-08 Siemens Ag Hochtemperaturfeste korrosionsschutzbeschichtung, insbesondere für gasturbinenbauteile.
DE3926479A1 (de) 1989-08-10 1991-02-14 Siemens Ag Rheniumhaltige schutzbeschichtung, mit grosser korrosions- und/oder oxidationsbestaendigkeit
CA2037660C (fr) * 1990-03-07 1997-08-19 Tadashi Kamimura Methodes de modification de l'etat de surface d'articles metalliques et appareils correspondants
US5554837A (en) * 1993-09-03 1996-09-10 Chromalloy Gas Turbine Corporation Interactive laser welding at elevated temperatures of superalloy articles
DE59505454D1 (de) 1994-10-14 1999-04-29 Siemens Ag Schutzschicht zum schutz eines bauteils gegen korrosion, oxidation und thermische überbeanspruchung sowie verfahren zu ihrer herstellung
CN1043197C (zh) * 1995-04-29 1999-05-05 华中理工大学 镀层钢板激光焊缝表面在线同步熔镀方法
US5914059A (en) * 1995-05-01 1999-06-22 United Technologies Corporation Method of repairing metallic articles by energy beam deposition with reduced power density
EP0861927A1 (fr) 1997-02-24 1998-09-02 Sulzer Innotec Ag Procédé de fabrication de structures monocristallines
EP0892090B1 (fr) 1997-02-24 2008-04-23 Sulzer Innotec Ag Procédé de fabrication de structure monocristallines
EP1306454B1 (fr) 2001-10-24 2004-10-06 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium pour la protection d'un élément contre l'oxydation et la corrosion aux températures élevées
WO1999067435A1 (fr) 1998-06-23 1999-12-29 Siemens Aktiengesellschaft Alliage a solidification directionnelle a resistance transversale a la rupture amelioree
US6231692B1 (en) 1999-01-28 2001-05-15 Howmet Research Corporation Nickel base superalloy with improved machinability and method of making thereof
JP2003529677A (ja) 1999-07-29 2003-10-07 シーメンス アクチエンゲゼルシヤフト 耐熱性の構造部材及びその製造方法
US6384369B1 (en) * 1999-09-22 2002-05-07 Donaldson Company, Inc. Liquid filter construction and methods
DE10010273A1 (de) * 2000-03-02 2001-09-06 Gerhard Ziemek Verfahren für das Aneinanderfügen metallischer Bänder
US6333484B1 (en) * 2000-03-17 2001-12-25 Chromalloy Gas Turbine Corporation Welding superalloy articles
JP4201954B2 (ja) * 2000-03-28 2008-12-24 株式会社東芝 Ｎｉ基単結晶超合金からなるガスタービン翼の補修方法およびその装置
AT411878B (de) * 2000-10-17 2004-07-26 Fronius Schweissmasch Prod Verfahren zum steuern und/oder regeln eines schweissprozesses
CN1166490C (zh) * 2001-09-21 2004-09-15 重庆钢铁(集团)有限责任公司 用嵌补焊接修复金属构件缺陷的方法
DE50112339D1 (de) 2001-12-13 2007-05-24 Siemens Ag Hochtemperaturbeständiges Bauteil aus einkristalliner oder polykristalliner Nickel-Basis-Superlegierung
US7335853B2 (en) * 2005-03-25 2008-02-26 Mcgushion Kevin Method for orbital welding using a pulsed current
US20060231535A1 (en) * 2005-04-19 2006-10-19 Fuesting Timothy P Method of welding a gamma-prime precipitate strengthened material

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009127504A1 *

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US9421639B2 (en) 2016-08-23
DE102008019636A1 (de) 2009-10-22
WO2009127504A1 (fr) 2009-10-22
US20110111248A1 (en) 2011-05-12
KR20110003536A (ko) 2011-01-12
CN102006965A (zh) 2011-04-06
CN102006965B (zh) 2015-05-06
US20130299467A1 (en) 2013-11-14

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