EP2117766A1 - Alliages de brasage et dispositif pour la réparation d'un élément de construction - Google Patents

Alliages de brasage et dispositif pour la réparation d'un élément de construction

Info

Publication number
EP2117766A1
EP2117766A1 EP08709220A EP08709220A EP2117766A1 EP 2117766 A1 EP2117766 A1 EP 2117766A1 EP 08709220 A EP08709220 A EP 08709220A EP 08709220 A EP08709220 A EP 08709220A EP 2117766 A1 EP2117766 A1 EP 2117766A1
Authority
EP
European Patent Office
Prior art keywords
solder alloy
germanium
alloy according
gallium
nickel
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Withdrawn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
EP08709220A
Other languages
German (de)
English (en)
Inventor
Paul Heinz
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
MTU Aero Engines GmbH
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
Priority claimed from EP07005303A external-priority patent/EP1970156A1/fr
Application filed by MTU Aero Engines GmbH, Siemens AG filed Critical MTU Aero Engines GmbH
Priority to EP08709220A priority Critical patent/EP2117766A1/fr
Publication of EP2117766A1 publication Critical patent/EP2117766A1/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Withdrawn legal-status Critical Current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
    • 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
    • B23K35/3033—Ni as the principal constituent
    • 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
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • 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
    • 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
    • C22C19/007—Alloys based on nickel or cobalt with a light metal (alkali metal Li, Na, K, Rb, Cs; earth alkali metal Be, Mg, Ca, Sr, Ba, Al Ga, Ge, Ti) or B, Si, Zr, Hf, Sc, Y, lanthanides, actinides, as the next major constituent
    • 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

Definitions

  • the invention relates to solder alloys according to claims 1, 2, 3, 4, 5 and a method for repairing a component according to claim 55.
  • Components sometimes need to be repaired after manufacture, for example after casting or after they have been used and cracked.
  • soldering process works with respect to the temperature during the welding process and thus with respect to the melting temperature of the substrate material at lower temperatures. Nevertheless, the solder should have a high strength, so that the solder-filled crack or the recess does not lead to a weakening of the entire component at the high operating temperatures.
  • the object is achieved by a solder made of a solder alloy according to claim 1, 2, 3, 4 or 5 and by a method according to claim 55.
  • FIG. 1 shows two cross-sectional views of a component during and after a treatment with the solder according to the invention
  • FIG. 2 shows in perspective a turbine blade
  • FIG. 3 shows in perspective a combustion chamber
  • FIG. 4 shows a gas turbine
  • Figure 5 is a list of superalloys.
  • FIG. 1 shows a component 1 which is treated with a solder 10 made of a solder alloy according to the invention.
  • the component 1 comprises a substrate 4 which, in particular for components for high-temperature applications, in particular for turbine blades 120, 130 (FIG. 2) or combustion chamber elements 155 (FIG. 3) for steam or gas turbines 100 (FIG cobalt-based superalloy ( Figure 5).
  • the solder 10 can preferably be used for all alloys according to FIG.
  • These may preferably be the known materials PWA 1483, PWA 1484 or Rene N5.
  • Lot 10 is also used for blades for aircraft.
  • the substrate 4 has a crack 7 or a recess 7, which is to be filled by soldering.
  • the cracks 7 or recesses 7 are preferably about 200 microns wide and can be up to 5mm deep.
  • the solder 10 is made of a solder alloy in or in the
  • the solder 10 melts below a melting temperature on the substrate 4 and fills the recess 7 completely.
  • the solder alloy 10 is nickel-based and therefore preferably has nickel (Ni) as the largest proportion.
  • Ni-Ge Ni-Ga
  • Ni-Ga binary system of Ni-Ge or Ni-Ga
  • the content of gallium (Ga) is preferably at least 0.1wt%. Also preferably, the germanium content is at least 0.1wt%. Even these small proportions have an influence on the soldering behavior of nickel or a nickel alloy.
  • chromium (Cr), cobalt (Co), aluminum (Al) and titanium (Ti), tungsten (W), molybdenum (Mo) or tantalum (Ta) may preferably be present, if used, in each case preferably used with a proportion of at least 0. lwt%.
  • the chromium content is preferably in a range of 2wt%
  • the content is also at 4wt% chromium.
  • the aluminum content is preferably in the range of 1% to 5% by weight, particularly preferably in the range of 2% by weight.
  • a particularly good embodiment has a solder alloy with an aluminum content of 3wt%.
  • the tungsten content is preferably in a range of 2wt% - 6wt%, more preferably in a range of 3wt% - 5wt%. Particularly good results were achieved with a tungsten content of 4wt%.
  • the cobalt content is in a range of 2wt% - 10wt%, more preferably in a range of 3wt% - 9wt%.
  • Particularly preferred embodiments have a cobalt content of 4wt% or 8wt%, so that particularly preferred cobalt contents at 3wt% to 5wt% or 7wt% to
  • the cobalt content is also 4wt%.
  • the gallium or germanium content is preferably at least 3wt%, more preferably at least 6wt%.
  • the germanium or gallium content can be limited to a maximum value of 18wt%. Also preferably, the maximum content of gallium or germanium is 13wt%, most preferably this maximum content is 8wt%.
  • the proportion of gallium (Ga) in a nickel-base superalloy as a solder alloy is preferably between 28wt% and 35wt%.
  • the proportion of germanium is preferably between 18wt% and 28wt%, in particular 20wt%, 23wt%, 26wt% or 27wt%, in particular in binary systems, ie NiGe20, NiGe23 or NiGe26, in particular for monocrystalline solidification.
  • the above list of ingredients for the solder is nickel, chromium, cobalt, tungsten, aluminum, gallium or germanium.
  • either only gallium or germanium is used.
  • the solder 10 preferably contains no boron.
  • the solder 10 does not contain zirconium.
  • rhenium can preferably be dispensed with. Likewise, preferably no hafnium is used.
  • the addition or presence of silicon and / or carbon is avoided as they form brittle phases in the solder. It is also preferred to avoid the addition or presence of iron and / or manganese since the elements form low melting or non-oxidizing phases.
  • the solder 10 can be connected to the substrate 4 of the component 1, 120, 130, 155 in an isothermal or a temperature gradient method. A gradient method is then preferably provided when the substrate 4 has a directional structure, for example an SX or DS structure, such that the solder 10 subsequently has a directed structure.
  • a directionally solidified structure in solder can also be carried out in an isothermal process.
  • the component 1 need not have a directionally solidified structure (but a CC structure).
  • the solders in CC substrates of components in a CC structure can be soldered and solidified, the solders then being polycrystalline solidified (CC).
  • solders are particularly interesting:
  • the germanium content is 20wt% - 30wt%, in particular 26wt% or 27wt%.
  • an inert gas especially argon, which reduces the chromium evaporation from the substrate 4 at the high temperatures, or uses a reducing gas (argon / hydrogen).
  • the solder 10 can also be applied over a large area to a surface of a component 1, 120, 130, 155 in order to achieve a thickening of the substrate 4, in particular in the case of hollow components.
  • the solder 10 is used to fill in cracks 7 or depressions 7.
  • soldering a solder 10 under vacuum which is often carried out when the solder 10 or the component 1, 120, 130, 155 oxidizes, preferably results from the use of inert gases (Ar, He, Ar / He, H2. ..) and / or the use of vacuum the problem of evaporation of components of the component 1, 120, 130, 155 or the solder 10 at too low a process pressure.
  • inert gases Ar, He, Ar / He, H2. ..
  • oxygen partial pressure P02 If the oxygen partial pressure P02 is too high, oxidation of the solder 10 or of the component 1, 120, 130, 155 takes place.
  • the oxygen partial pressure p O 2 is preferably at least 10 "7 mbar (10" 5 Pa).
  • the total process pressure is preferably at least 0, lmbar (10Pa).
  • a pure inert gas preferably argon (Ar) (Ar 5.0, preferably Ar 6.0) before soldering.
  • argon 6.0 meaning an oxygen content of 5 ⁇ 10 ⁇ 7 in the process gas
  • a gas cleaning cartridge so that the oxygen and water content is reduced by a factor of 100, so that an oxygen content of 5 ⁇ 10 2 ⁇ 9 is achieved in the process gas, which is introduced into the process chamber.
  • argon is also preferably present within the pressure values described above.
  • the temperature during the soldering process is at least 1140 ° C., in particular at least 1160 ° C.
  • soldering temperatures are 1160 0 C,
  • the maximum temperature is preferably 1280 ° C., in particular maximum 1260 ° C.
  • the duration of the soldering treatment is preferably at least 10 hours, especially at 48 hours.
  • FIG. 2 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.
  • blades 120, 130 in all regions 400, 403, 406 of the blade 120, 130, for example, massive metallic materials, in particular superalloys, are used, in particular the superalloys according to FIG. 5.
  • 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.
  • Refurbishment means that components 120, 130 may need to be stripped of protective layers 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. 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. 3 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 plurality 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 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.
  • 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 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.
  • MCrAlX may still be present, for example, a ceramic thermal barrier coating and consists for example of ZrO 2 , Y2Ü3-Zr ⁇ 2, ie it is not, partially or fully ⁇ dig stabilized by yttria 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 heat shield elements 155 may be replaced after use by heat shielding elements 155
  • Protective layers must be freed (for example 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.
  • FIG. 4 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 101, 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 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. 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 seen in the direction of flow of the working medium 113 become, in addition to the annular combustion chamber 110 lining heat shield elements most thermally stressed.
  • 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 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, which should be part of this disclosure with regard to the chemical composition.
  • MCrAlX may still be a thermal barrier layer is present, and consists for example of Zr ⁇ 2, Y2 ⁇ 3-Zr ⁇ 2, i. it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • 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 is the rotor 103 facing and fixed to a mounting ring 140 of the stator 143.

Abstract

Beaucoup d'alliages de soudure connus selon l'état antérieur de la technique utilisent du silicium ou du bore comme éléments abaissant le point de fusion, qui forment cependant des phases fragiles, qui ont des conséquences indésirées sur les propriétés thermomécaniques. L'alliage de brasage comporte du gallium et/ou du germanium, qui forment de préférence la phase Y' et présentent des propriétés mécaniques améliorées.
EP08709220A 2007-03-14 2008-02-26 Alliages de brasage et dispositif pour la réparation d'un élément de construction Withdrawn EP2117766A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08709220A EP2117766A1 (fr) 2007-03-14 2008-02-26 Alliages de brasage et dispositif pour la réparation d'un élément de construction

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
EP07005303A EP1970156A1 (fr) 2007-03-14 2007-03-14 Alliage de brasage et procédé destiné à la réparation d'un composant
EP07007925 2007-04-18
EP07011676 2007-06-14
EP08709220A EP2117766A1 (fr) 2007-03-14 2008-02-26 Alliages de brasage et dispositif pour la réparation d'un élément de construction
PCT/EP2008/052324 WO2008110454A1 (fr) 2007-03-14 2008-02-26 Alliages de brasage et dispositif pour la réparation d'un élément de construction

Publications (1)

Publication Number Publication Date
EP2117766A1 true EP2117766A1 (fr) 2009-11-18

Family

ID=39433934

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08709220A Withdrawn EP2117766A1 (fr) 2007-03-14 2008-02-26 Alliages de brasage et dispositif pour la réparation d'un élément de construction

Country Status (5)

Country Link
US (1) US8613885B2 (fr)
EP (1) EP2117766A1 (fr)
JP (1) JP5780703B2 (fr)
KR (2) KR101301232B1 (fr)
WO (1) WO2008110454A1 (fr)

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Also Published As

Publication number Publication date
WO2008110454A1 (fr) 2008-09-18
KR101301232B1 (ko) 2013-08-28
US20100025454A1 (en) 2010-02-04
KR20100034729A (ko) 2010-04-01
JP2010520814A (ja) 2010-06-17
JP5780703B2 (ja) 2015-09-16
US8613885B2 (en) 2013-12-24
KR20120059653A (ko) 2012-06-08

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