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EP2240293A1 - Procédé et dispositif pour fondre des surfaces incurvées - Google Patents

Procédé et dispositif pour fondre des surfaces incurvées

Info

Publication number
EP2240293A1
EP2240293A1 EP08872349A EP08872349A EP2240293A1 EP 2240293 A1 EP2240293 A1 EP 2240293A1 EP 08872349 A EP08872349 A EP 08872349A EP 08872349 A EP08872349 A EP 08872349A EP 2240293 A1 EP2240293 A1 EP 2240293A1
Authority
EP
European Patent Office
Prior art keywords
curved surface
energy beam
substrate
energy
angle
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Withdrawn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
EP08872349A
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.)
Fraunhofer Gesellschaft zur Forderung der Angewandten Forschung eV
Siemens AG
Original Assignee
Fraunhofer Gesellschaft zur Forderung der Angewandten Forschung eV
Siemens AG
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 Fraunhofer Gesellschaft zur Forderung der Angewandten Forschung eV, Siemens AG, Siemens Corp filed Critical Fraunhofer Gesellschaft zur Forderung der Angewandten Forschung eV
Publication of EP2240293A1 publication Critical patent/EP2240293A1/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Withdrawn legal-status Critical Current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
    • B23K26/02—Positioning or observing the workpiece, e.g. with respect to the point of impact; Aligning, aiming or focusing the laser beam
    • 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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/50—Inorganic material, e.g. metals, not provided for in B23K2103/02 – B23K2103/26

Definitions

  • the invention relates to a method for melting curved surfaces according to the preamble of claim 1 and a corresponding device.
  • the object is achieved by a method according to claim 1, in which the direction of the energy beam is adapted to the curvature of the surface, and a device according to claim 15.
  • Method, Figure 3 is a gas turbine
  • FIG. 4 shows in perspective a turbine blade FIG. 5 in perspective a combustion chamber and FIG. 6 shows a list of superalloys.
  • FIG. 1 shows the schematic sequence of the method according to the prior art with different positions of an energy source 16, in particular a welding apparatus, over a component 1, 120, 130, 155 (FIGS. 4, 5) in a direction of translation (in the drawing from the left to the right) .
  • a substrate 4 of the component 1, 120, 130, 155 has a curved surface 7 with a normal n (perpendicular). The direction of the normal n changes along the curved surface 7.
  • the curved surface 7 is intended to be thrown up or remelted by energy beams 13.
  • an energy source 16 preferably by means of a plasma or by means of a laser emitting laser beams 13.
  • a laser beam 13 strikes the surface 22 at an angle.
  • the position of the laser 16 is not changed relative to the substrate 4, even if the laser beam 13 moves away from the curved surface 7, so that the angle ⁇ between the normal paint ⁇ the surface 7 and the laser beam 13 is changed.
  • FIG. 2 shows schematically the course of the method according to the invention.
  • the position of the laser beam 13 relative to the substrate 4 is changed so that the angle ⁇ between the laser beam 13 and the normal n of the surface 7 is preferably remains constant.
  • the change can preferably be adjusted continuously.
  • the position of the laser beam 13 with respect to the curved surface 7 is changed at least three times. So there is a quasi-continuous adjustment of the angle.
  • the angle ⁇ By varying the angle ⁇ , the local variability of the laser power and the local speed is reduced. Since the temperature signal of the welding spot generated by the laser beam is influenced by the change in the angle ⁇ , preferably also no percentage control of the temperature of the melt takes place.
  • the angle ⁇ is preferably between 8 ° and 12 °, preferably 10 °.
  • the laser power is preferably 750W.
  • the preheating temperature is preferably from 500 0 C.
  • the travel speed is preferably 50 mm / min.
  • Such curved surface regions 7 are, in the area of the turbine blade 120, 130, the transition between the blade leaf 406 and the blade blade 403.
  • the distance of the laser 16 to the surface 7 can be adjusted, in particular kept constant, since the curvature of the surface 7, the distance to the laser 16 changes. As a result, the energy input into the substrate 4 remains uniform.
  • the method can be applied to convex surfaces.
  • weld metal can be supplied to the substrate 4, which is melted and fills cracks or reinforced component walls.
  • the method is advantageous in a directionally solidified substrate 4, the columnar solidified grains (DS) or monocrystalline (SX) is formed, since there the crystal orientation plays an important role, which is influenced by the application of temperature gradients.
  • Substrates 4 preferably have a superalloy according to FIG.
  • FIG. 3 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.
  • 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. In the flow direction of a working medium
  • a row 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 guided to the burners 107 and mixed there with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium flows 113 along the hot gas channel 111 past the guide vanes 130 and the blades 120.
  • the working medium 113 expands in a pulse-transmitting manner, so that the blades 120 drive the rotor 103 and this drives 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 may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • 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.
  • 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 represents 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 represents 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 Bl, EP 0 412 397 B1 or EP 1 306 454 A1.
  • MCrAlX may still be a thermal barrier layer, and consists for example of Zr ⁇ 2, Y2Ü3-Zr ⁇ 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), produce stalk-shaped grains in the thermal barrier coating.
  • EB-PVD electron beam evaporation
  • 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. 4 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 fir tree or Schissebwschwanzfuß 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.
  • 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 whole workpiece consists 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 whole workpiece consists of a single crystal.
  • directionally solidified structures generally refers to single crystals that have no grain boundaries or at most small-angle grain boundaries, as well as stem crystal structures that have grain boundaries running in the longitudinal direction but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified 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 Bl, EP 0 412 397 B1 or EP 1 306 454 A1.
  • the density is preferably 95% of the theoretical
  • TGO thermal grown oxide layer
  • 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-1OAl-O, 4Y-I are also preferably used , 5Re.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of ZrC> 2, Y2Ü3-Zr ⁇ 2, ie it is not, partially ⁇ or fully stabilized by yttria 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), produce 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.
  • 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.
  • the blade 120, 130 is to be cooled, it is hollow and may still have film cooling holes 418 (indicated by dashed lines).
  • FIG. 5 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is configured, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 107 arranged in the circumferential direction about a rotation axis 102 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 for a comparatively high temperature the working medium M of about 1000 0 C to 1600 0 C designed.
  • the combustion chamber wall 153 is provided on its side facing the working medium M 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 EP 0 486 489 B1, EP 0 786 017 Bl, EP 0 412 397 B1 or EP 1 306 454 A1.
  • MCrAlX may still be present, for example, a ceramic thermal barrier coating and consists for example of ZrC> 2, Y2Ü3 Zr ⁇ 2, ie it is not, partially or fully ⁇ dig stabilized by yttrium and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the heat-insulating layer may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • Refurbishment means that heat shield elements 155 may have to be freed of protective layers after their use (eg by sandblasting). 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.

Landscapes

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

Abstract

Les pièces qui présentent à la fois des surfaces planes et des surfaces incurvées sont souvent difficiles à souder. Le procédé selon l'invention propose de faire varier l'orientation de l'appareil de soudage au laser (16) par rapport à la surface incurvée (7) du substrat (4) en fonction de la courbure de la surface (7).
EP08872349A 2008-02-13 2008-12-16 Procédé et dispositif pour fondre des surfaces incurvées Withdrawn EP2240293A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008008966 2008-02-13
PCT/EP2008/067637 WO2009100794A1 (fr) 2008-02-13 2008-12-16 Procédé et dispositif pour fondre des surfaces incurvées

Publications (1)

Publication Number Publication Date
EP2240293A1 true EP2240293A1 (fr) 2010-10-20

Family

ID=40512549

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08872349A Withdrawn EP2240293A1 (fr) 2008-02-13 2008-12-16 Procédé et dispositif pour fondre des surfaces incurvées

Country Status (3)

Country Link
US (1) US20110056919A1 (fr)
EP (1) EP2240293A1 (fr)
WO (1) WO2009100794A1 (fr)

Families Citing this family (6)

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Publication number Priority date Publication date Assignee Title
EP2322314A1 (fr) * 2009-11-16 2011-05-18 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Soudure monocristalline de matières actives renforcées directionnelles
CN104364045B (zh) * 2012-05-11 2016-10-12 西门子能量股份有限公司 镍基超级合金构件的激光添加剂修复
US9272365B2 (en) * 2012-09-12 2016-03-01 Siemens Energy, Inc. Superalloy laser cladding with surface topology energy transfer compensation
US9289854B2 (en) 2012-09-12 2016-03-22 Siemens Energy, Inc. Automated superalloy laser cladding with 3D imaging weld path control
US9272369B2 (en) 2012-09-12 2016-03-01 Siemens Energy, Inc. Method for automated superalloy laser cladding with 3D imaging weld path control
EP2754527A1 (fr) * 2013-01-11 2014-07-16 Siemens Aktiengesellschaft Production de grains fins lors du soudage par rechargement

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Also Published As

Publication number Publication date
WO2009100794A1 (fr) 2009-08-20
US20110056919A1 (en) 2011-03-10

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