WO2009127504A1 - Bauteil mit schweissnaht und verfahren zur herstellung einer schweissnaht - Google Patents
Bauteil mit schweissnaht und verfahren zur herstellung einer schweissnaht Download PDFInfo
- Publication number
- WO2009127504A1 WO2009127504A1 PCT/EP2009/053511 EP2009053511W WO2009127504A1 WO 2009127504 A1 WO2009127504 A1 WO 2009127504A1 EP 2009053511 W EP2009053511 W EP 2009053511W WO 2009127504 A1 WO2009127504 A1 WO 2009127504A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- weld
- ramp
- component
- length
- substrate
- Prior art date
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
- B23K26/34—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
- B23K26/32—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
- B23K26/20—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.
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09731543A EP2274130A1 (de) | 2008-04-18 | 2009-03-25 | Bauteil mit schweissnaht und verfahren zur herstellung einer schweissnaht |
US12/988,334 US20110111248A1 (en) | 2008-04-18 | 2009-03-25 | Component Having Weld Seam and Method for Producing a Weld Seam |
CN200980113615.2A CN102006965B (zh) | 2008-04-18 | 2009-03-25 | 具有焊缝的部件以及用于形成焊缝的方法 |
US13/945,214 US9421639B2 (en) | 2008-04-18 | 2013-07-18 | Component having weld seam and method for producing a weld seam |
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 |
DE102008019636.3 | 2008-04-18 |
Related Child Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/988,334 A-371-Of-International US20110111248A1 (en) | 2008-04-18 | 2009-03-25 | Component Having Weld Seam and Method for Producing a Weld Seam |
US13/945,214 Division US9421639B2 (en) | 2008-04-18 | 2013-07-18 | Component having weld seam and method for producing a weld seam |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2009127504A1 true WO2009127504A1 (de) | 2009-10-22 |
Family
ID=40833535
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2009/053511 WO2009127504A1 (de) | 2008-04-18 | 2009-03-25 | Bauteil mit schweissnaht und verfahren zur herstellung einer schweissnaht |
Country Status (6)
Country | Link |
---|---|
US (2) | US20110111248A1 (de) |
EP (1) | EP2274130A1 (de) |
KR (1) | KR20110003536A (de) |
CN (1) | CN102006965B (de) |
DE (1) | DE102008019636A1 (de) |
WO (1) | WO2009127504A1 (de) |
Families Citing this family (7)
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EP2730364A1 (de) * | 2012-11-08 | 2014-05-14 | Siemens Aktiengesellschaft | Schweißbadsicherung am Randbereich |
EP2803441A1 (de) * | 2013-05-13 | 2014-11-19 | Siemens Aktiengesellschaft | Verfahren zum Laserstrahl-Schweißen |
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 |
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-
2008
- 2008-04-18 DE DE102008019636A patent/DE102008019636A1/de not_active Ceased
-
2009
- 2009-03-25 US US12/988,334 patent/US20110111248A1/en not_active Abandoned
- 2009-03-25 CN CN200980113615.2A patent/CN102006965B/zh not_active Expired - Fee Related
- 2009-03-25 KR KR1020107025795A patent/KR20110003536A/ko not_active Application Discontinuation
- 2009-03-25 EP EP09731543A patent/EP2274130A1/de not_active Withdrawn
- 2009-03-25 WO PCT/EP2009/053511 patent/WO2009127504A1/de active Application Filing
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2013
- 2013-07-18 US US13/945,214 patent/US9421639B2/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1995006540A1 (en) * | 1993-09-03 | 1995-03-09 | Chromalloy Gas Turbine Corporation | Interactive laser welding at elevated temperatures of superalloy articles |
JP2001269784A (ja) * | 2000-03-28 | 2001-10-02 | Toshiba Corp | 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 |
US20060231535A1 (en) * | 2005-04-19 | 2006-10-19 | Fuesting Timothy P | Method of welding a gamma-prime precipitate strengthened material |
Also Published As
Publication number | Publication date |
---|---|
KR20110003536A (ko) | 2011-01-12 |
US20110111248A1 (en) | 2011-05-12 |
US9421639B2 (en) | 2016-08-23 |
CN102006965B (zh) | 2015-05-06 |
EP2274130A1 (de) | 2011-01-19 |
CN102006965A (zh) | 2011-04-06 |
US20130299467A1 (en) | 2013-11-14 |
DE102008019636A1 (de) | 2009-10-22 |
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