EP2445677A1 - Barrettes de brasage, brasage de trous, procédé de revêtement - Google Patents

Barrettes de brasage, brasage de trous, procédé de revêtement

Info

Publication number
EP2445677A1
EP2445677A1 EP09776855A EP09776855A EP2445677A1 EP 2445677 A1 EP2445677 A1 EP 2445677A1 EP 09776855 A EP09776855 A EP 09776855A EP 09776855 A EP09776855 A EP 09776855A EP 2445677 A1 EP2445677 A1 EP 2445677A1
Authority
EP
European Patent Office
Prior art keywords
solder
hole
lotgutstäbchen
alloy
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Withdrawn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
EP09776855A
Other languages
German (de)
English (en)
Inventor
Francis-Jurjen Ladru
Gerhard Reich
Adrian Wollnik
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP2445677A1 publication Critical patent/EP2445677A1/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Withdrawn legal-status Critical Current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
    • B23K3/00—Tools, devices, or special appurtenances for soldering, e.g. brazing, or unsoldering, not specially adapted for particular methods
    • B23K3/06—Solder feeding devices; Solder melting pans
    • B23K3/0607—Solder feeding devices
    • B23K3/0623—Solder feeding devices for shaped solder piece feeding, e.g. preforms, bumps, balls, pellets, droplets
    • 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, brazing
    • B23K35/0227—Rods, wires
    • 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
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • 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
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • 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
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • 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
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12944—Ni-base component

Definitions

  • the invention relates to Lötgutstäbchen, the Belotung holes and methods for coating components with holes.
  • Components often have holes that should be closed. For turbine blades, these are cooling air holes. These components are then often coated again and provided with cooling holes.
  • the object is achieved by a solder rod according to claim 1, a method for soldering according to claim 12 and a method for coating according to claim 13.
  • FIGS. 6, 7, 12-14 methods for soldering holes
  • Figure 15 shows a gas turbine
  • FIG. 16 shows in perspective a turbine blade
  • FIG. 17 shows in perspective a combustion chamber
  • FIG. 1 shows a component 1, 120, 130, 155 (FIGS. 12, 13, 14) with a through hole 7, wherein preferably a surface 4 of the substrate 19 of the component 1, 120, 130, 155 is to be coated again.
  • the substrate 19 of the component 1, 120, 130, 155 is preferably metallic and preferably has a superalloy according to FIG. These are in particular for components 1, 120, 130, 155 for gas turbines 100 (FIG. 15) such as. Turbine blades 120, 130 ( Figure 16).
  • a solder 10 is introduced into the hole 7, in particular a cooling air hole 7.
  • a coating 13 is applied to the surface 4 of the substrate 19 (FIG. 3). Since the solder 10 fills the hole 7, the coating 13 is also present above the solder 10.
  • the coating 13 is a metallic adhesion promoter layer, in particular a MCrAlX alloy, on which preferably an outer ceramic layer (not shown) is also applied.
  • a metallic protective layer may still be present on the surface 4 of the substrate 19, in which case the solder 10 is present both in the substrate 19 and in this metallic protective layer which surrounds the hole 7.
  • FIGS. 2 to 5 can also be carried out without a coating process as an intermediate step. This is shown in FIGS. 12, 13 and 14.
  • FIG. 6 shows in general a method for soldering a substrate 19 with a hole 7.
  • the solder 10 is introduced here in the form of a Lotgutstäbchens 22, the Lotgutstäbchen 22, which preferably has a wire or rod shape, the same outer diameter / outer cross-section as the inner diameter / inner cross section of the hole 7.
  • the volume of the Lotgutstäbchens 22 corresponds to the volume of the hole 7. If more solder is used or Lot 10 protrudes beyond the surface 4, this can be removed.
  • FIG. 8 shows a solder rod 22 with two regions, an inner region 38 and an outer region 35.
  • the inner region 38 preferably has a nickel-base superalloy, preferably like the substrate 19, very preferably according to FIG.
  • the core consists of a superalloy, in particular according to FIG. 18.
  • the inner region 38 does not melt at the solder temperatures of the soldering process (FIGS. 2-5, 7, 12, 13, 14).
  • the outer region 35 comprises an alloy which melts at the soldering temperatures of the soldering process (FIGS. 2, 7), ie it is different from the alloy of the inner region 38.
  • composition of the outer region 35 differs from the
  • composition without melting point depressants such as boron, silicon, which has a lower melting temperature than the core 38.
  • This may be a modified alloy - preferably with the same
  • Elements - of the core 39 with increased or decreased proportions preferably of aluminum and / or titanium and / or tantalum, which lower the melting point.
  • the outer region 35 may represent an overlay layer.
  • the core 38 has preferably also been inserted into a sleeve made of a solder alloy 35.
  • the outer region 35 also preferably constitutes a diffusion layer and is preferably formed by diffusion of at least one melting point depressant (preferably B, Si).
  • a melting point depressant preferably B, Si
  • a combination of diffusion layer and overlay layer can be present.
  • the outer region 35 encloses the inner region 38 at least partially.
  • the outer region 35 is preferably present only in the jacket region, but may also cover the end faces (FIG. 9).
  • Both inner 38 and outer 35 regions can be nickel- or cobalt-based superalloys.
  • the stop-off 25 preferably wets the Lotgutstäbchen 22.
  • the stop-off may comprise a ceramic or an alloy.
  • the stop-off 25 is made of a different material than the material of the Lotgutstäbchens 22.
  • an alloy is used.
  • oxide ceramics very preferably spinels, perovskites, pyrochlors, very particularly zirconium oxide, alumina or mixtures thereof are used.
  • Known stop-offs from the prior art can be used for this purpose.
  • the stop-off 25 can be applied as a film, slurry, paste, etc. Preferably, a paste is used.
  • the stop-off 25 is present only on the end face 28 of the rod 22 and wire 22 (FIG. 9).
  • Such rods 22 according to FIGS. 8, 9 can also be used in the method according to FIGS. 1 to 6. Likewise, first the stop-off 25 can be introduced into the hole 7 and the solder 10, preferably the rod 22, is then introduced into the hole 7 (FIG. 7).
  • FIG. 15 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.
  • a series 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example. Coupled to the rotor 103 is a generator or work machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is 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 material for the components, in particular for the turbine blades 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.
  • a thermal barrier coating On the MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , that is, it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • Suitable coating processes such as electron beam evaporation (EB-PVD), 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. 16 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.
  • solid metallic materials in particular superalloys, are used in all regions 400, 403, 406 of the blade 120, 130.
  • 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 produced 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.
  • directionally solidified structures it means both single crystals which have no grain boundaries or at most small-angle grain boundaries, as well as columnar crystal structures which are probably grain boundaries running in the longitudinal direction but no transverse grain boundaries. have boundaries.
  • 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 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.
  • a thermal barrier coating which is preferably the outermost layer, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • 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- insulating layer 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. 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 may still film cooling holes 418 (indicated by dashed lines) on.
  • FIG. 17 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is designed, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 107 arranged in the circumferential direction around 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 designed for a relatively high temperature of the working medium M of approximately 1000 0 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.
  • 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 Bl, EP 0 412 397 B1 or EP 1 306 454 A1.
  • a ceramic thermal barrier coating may be present and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • Suitable coating processes such as electron beam evaporation (EB-PVD), produce 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.
  • 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. Due to the high temperatures inside the combustion chamber 110 may also be provided for the heat shield elements 155 and for their holding elements, a cooling system. 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

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une barrette de brasage (22) qui présente un arrêt (25) à l'extrémité (28) afin que le métal d'apport de brasage ne puisse pas goutter d'une ouverture.
EP09776855A 2009-06-26 2009-06-26 Barrettes de brasage, brasage de trous, procédé de revêtement Withdrawn EP2445677A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2009/004646 WO2010149189A1 (fr) 2009-06-26 2009-06-26 Barrettes de brasage, brasage de trous, procédé de revêtement

Publications (1)

Publication Number Publication Date
EP2445677A1 true EP2445677A1 (fr) 2012-05-02

Family

ID=41786051

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09776855A Withdrawn EP2445677A1 (fr) 2009-06-26 2009-06-26 Barrettes de brasage, brasage de trous, procédé de revêtement

Country Status (3)

Country Link
US (1) US20120111929A1 (fr)
EP (1) EP2445677A1 (fr)
WO (1) WO2010149189A1 (fr)

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB119096A (en) * 1917-09-21 1918-09-23 Ernest Henry Jones Improvements in Welding and Brazing.
US3039494A (en) * 1956-10-26 1962-06-19 Charles J Bradley Pipe plug
US5114641A (en) * 1986-06-17 1992-05-19 Sumitomo Electric Industries, Ltd. Method for producing an elongated sintered article
WO1993015870A1 (fr) * 1992-02-11 1993-08-19 American Iron & Metal Company Inc./La Compagnie Americaine De Fer Et Metaux Inc. Fil de soudure
US5957365A (en) * 1997-03-03 1999-09-28 Anthon; Royce A. Brazing rod for depositing diamond coating to metal substrate using gas or electric brazing techniques
US6750430B2 (en) * 2002-10-25 2004-06-15 General Electric Company Nickel-base powder-cored article, and methods for its preparation and use
EP1772594A1 (fr) * 2005-10-04 2007-04-11 Siemens Aktiengesellschaft Procédé pour couvrir les orifices d'un composant dans un procédé et composition de céramique contenant de polysiloxane

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2010149189A1 *

Also Published As

Publication number Publication date
WO2010149189A1 (fr) 2010-12-29
US20120111929A1 (en) 2012-05-10

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