EP2637820A1 - Alliages à base de cobalt et contenant de germanium, et procédé de brasage - Google Patents

Alliages à base de cobalt et contenant de germanium, et procédé de brasage

Info

Publication number
EP2637820A1
EP2637820A1 EP11796658.0A EP11796658A EP2637820A1 EP 2637820 A1 EP2637820 A1 EP 2637820A1 EP 11796658 A EP11796658 A EP 11796658A EP 2637820 A1 EP2637820 A1 EP 2637820A1
Authority
EP
European Patent Office
Prior art keywords
solder alloy
alloy according
cobalt
germanium
solder
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Withdrawn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
EP11796658.0A
Other languages
German (de)
English (en)
Inventor
Sebastian Piegert
Peter Randelzhofer
Robert Singer
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
Priority to EP11796658.0A priority Critical patent/EP2637820A1/fr
Publication of EP2637820A1 publication Critical patent/EP2637820A1/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Withdrawn legal-status Critical Current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
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/30—Selection of soldering or welding materials proper with the principal constituent melting at less than 1550 degrees C
    • B23K35/3046—Co as the principal constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt

Definitions

  • Solder alloys are used when connecting and repairing components.
  • germanium-containing nickel-based alloys are also known.
  • the object is achieved by a solder alloy according to An ⁇ claim 1 and a method according to claim 13.
  • FIG. 1 shows a turbine blade
  • FIG. 2 shows a turbine
  • Figure 3 is a list of superalloys
  • the germanium content is between 13% by weight and 27% by weight, in particular between 14% by weight and 26% by weight.
  • the base forms cobalt with proportions of 40 wt .-% to 47 wt. -%.
  • the cobalt-based alloy has:
  • zirconium (Zr) optionally from 0.3% by weight to 0.7% by weight zirconium (Zr),
  • the list of alloying elements is from ⁇ closing, but more elements (gallium (Ga) and / or silicon (Si)) to increase strength, phase influencing or melting point influencing be present. Effects of the elements:
  • the resistance ⁇ should be especially leu compared to boron-based solders lie much higher, since no chromium is bound in borides and thus is effectively available for passivation
  • titanium carbide is and thus hardens the
  • titanium is not considered in most solder alloys, since titanium is quite active and it may u. Passivation of the solder particles by oxidation can occur.
  • the Ge content leads to drastically reduced amounts of low-melting eutectics in the soldering. Furthermore, it has been found that germanium as melting point lowering Ele ⁇ ment not to incompatibilities between soldered portions and metallic bonding layers, especially with MCrAlY leads.
  • Germanium can be replaced by similar elements, in particular gallium (Ga) and / or silicon (Si).
  • Silicon then preferably has a proportion of at least 0.3 wt% and / or gallium a proportion of at least 1.0 wt%.
  • cobalt-based alloys prove since the primary melting point depressants (Ge) has a high solubility here, which keeps the diffusion times at the heat treatment in ⁇ limits.
  • Co-base alloys such as X 40, X 45 FSX-41, MAR-M 509, ELY 768 can be added or alloyed with the described solder.
  • Co-based alloys have a high solder ⁇ temperature, so that a significant reduction in the proportion of the primary melting point lowering agent which delayed the formation of low melting eutectics in the soldering gap greatly verrin-.
  • Germanium (Ge) can be replaced partly or wholly by gallium (Ga) and / or silicon (Si), so fol ⁇ constricting mixtures in the alloy are possible:
  • nickel-based substrate in particular according to FIG. 3, is then soldered or processed with this cobalt-based alloy as a solder.
  • temperatures of 1130 ° C to 1270 ° C are preferably used.
  • FIG. 1 shows a perspective view of a rotor blade 120 or guide vane show ⁇ 130 of a turbomachine, which extends along a longitudinal axis of the 121st
  • the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 to each other, a securing region 400, an adjoining blade or vane platform 403 and a blade 406 and a blade tip 415.
  • the vane 130 may be pointed on its shovel 415 have a further platform (not Darge ⁇ asserted).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is, for example, as a hammerhead out staltet ⁇ .
  • Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a medium felblatt to the Schau- 406 flows past, a leading edge 409 and a trailing edge 412th
  • 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 be made 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.
  • the production of such monocrystalline workpieces for example, by directed solidification from the melt.
  • These are casting methods in which the liquid metallic alloy solidifies into a monocrystalline structure, ie a single-crystal workpiece, or directionally.
  • dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, ie grains that run the entire length of the workpiece and here, for general language use, referred to as directionally solidified) or a monocrystalline structure, ie the entire workpiece ⁇ is of a single crystal.
  • a columnar grain structure columnar, ie grains that run the entire length of the workpiece and here, for general language use, referred to as directionally solidified
  • a monocrystalline structure ie the entire workpiece ⁇ is of a single crystal.
  • Stem-crystal structures which probably have longitudinally extending grain boundaries, 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. B. (MCrAlX, M is at least one element of the group iron (Fe), cobalt (Co),
  • Nickel (Ni) is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf)).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • the density is preferably 95% of the theoretical
  • the layer composition comprises Co-30Ni-28Cr-8A1-0, 6Y-0, 7Si or Co-28Ni-24Cr-10Al-0, 6Y.
  • nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-IIAl-O, 4Y-2Re or Ni-25Co-17Cr-10A1-0, 4Y-1 are also preferably used , 5Re.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of ZrC> 2, Y2Ü3-Zr02, i. it is not, partially or fully stabilized by yttria
  • the thermal barrier coating covers the entire MCrAlX layer.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the heat insulation layer may have ⁇ porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the
  • Refurbishment means that components 120, 130 may have to be freed from protective layers after use (eg 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. Thereafter, a ⁇ As the coating of the component 120, 130, after entry set of the component 120, the 130th
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and also has, if necessary, film cooling holes 418 (indicated by dashed lines) on.
  • FIG. 2 shows by way of example a gas turbine 100 in a partial longitudinal section.
  • the gas turbine 100 has a rotatably mounted about a rotational axis 102 ⁇ rotor 103 having a shaft 101, which is also referred to as the turbine rotor.
  • 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 .
  • the hot gas channel 111 of a row of vanes 115 is followed by a series 125 formed of rotor blades 120.
  • the vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the rotor blades 120 of a row 125 are mounted on the rotor 103 by means of a turbine disk 133, for example are attached.
  • air 135 is sucked by the compressor 105 through the intake housing and ver ⁇ seals.
  • the loading 105 compressed air provided at the turbine end of the compressor is ge ⁇ leads 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 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.
  • substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • the components in particular for the turbine blade or vane 120, 130 and components of the combustion chamber 110.
  • iron-, nickel- or cobalt-based superalloys are used.
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
  • the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium.
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • a thermal barrier coating On the MCrAlX may still be present a thermal barrier coating, and consists for example of r02, Y203-Zr02, ie it is not, partially or completely stabilized by Ytt ⁇ riumoxid 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 guide vane 130 has an inner housing 138 of the turbine 108 facing guide vane root (not Darge here provides ⁇ ) and a side opposite the guide-blade root vane root.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention porte sur des alliages à base de cobalt et contenant du germanium, qui présentent un plus haut point de fusion que les alliages à base de nickel, de sorte qu'ils soient utilisés avantageusement pour la réparation ou pour le traitement de pièces utilisées à des températures élevées.
EP11796658.0A 2011-01-14 2011-12-06 Alliages à base de cobalt et contenant de germanium, et procédé de brasage Withdrawn EP2637820A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11796658.0A EP2637820A1 (fr) 2011-01-14 2011-12-06 Alliages à base de cobalt et contenant de germanium, et procédé de brasage

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP11150953A EP2476506A1 (fr) 2011-01-14 2011-01-14 Alliage à base de cobalt doté de germanium et procédé de soudage
EP11796658.0A EP2637820A1 (fr) 2011-01-14 2011-12-06 Alliages à base de cobalt et contenant de germanium, et procédé de brasage
PCT/EP2011/071846 WO2012095221A1 (fr) 2011-01-14 2011-12-06 Alliages à base de cobalt et contenant de germanium, et procédé de brasage

Publications (1)

Publication Number Publication Date
EP2637820A1 true EP2637820A1 (fr) 2013-09-18

Family

ID=43929003

Family Applications (2)

Application Number Title Priority Date Filing Date
EP11150953A Ceased EP2476506A1 (fr) 2011-01-14 2011-01-14 Alliage à base de cobalt doté de germanium et procédé de soudage
EP11796658.0A Withdrawn EP2637820A1 (fr) 2011-01-14 2011-12-06 Alliages à base de cobalt et contenant de germanium, et procédé de brasage

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP11150953A Ceased EP2476506A1 (fr) 2011-01-14 2011-01-14 Alliage à base de cobalt doté de germanium et procédé de soudage

Country Status (3)

Country Link
US (1) US8763885B2 (fr)
EP (2) EP2476506A1 (fr)
WO (1) WO2012095221A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2754529A1 (fr) * 2013-01-11 2014-07-16 Siemens Aktiengesellschaft Brasage sans bore avec manganèse et germanium, poudre et procédé de réparation
DE102014200121A1 (de) * 2014-01-08 2015-07-09 Siemens Aktiengesellschaft Manganhaltige Hochtemperaturlotlegierung auf Kobaltbasis, Pulver, Bauteil und Lotverfahren
DE102014209216B4 (de) * 2014-05-15 2018-08-23 Glatt Gmbh Katalytisch wirksames poröses Element und Verfahren zu seiner Herstellung

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JPS56130449A (en) * 1980-03-19 1981-10-13 Takeshi Masumoto Amorphous cobalt alloy with very low magnetostriction and high permeability
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Also Published As

Publication number Publication date
EP2476506A1 (fr) 2012-07-18
US20130299562A1 (en) 2013-11-14
WO2012095221A1 (fr) 2012-07-19
US8763885B2 (en) 2014-07-01

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