EP2558243A2 - Alliage de brasage, procédé de brasage et pièce correspondante - Google Patents

Alliage de brasage, procédé de brasage et pièce correspondante

Info

Publication number
EP2558243A2
EP2558243A2 EP10713920A EP10713920A EP2558243A2 EP 2558243 A2 EP2558243 A2 EP 2558243A2 EP 10713920 A EP10713920 A EP 10713920A EP 10713920 A EP10713920 A EP 10713920A EP 2558243 A2 EP2558243 A2 EP 2558243A2
Authority
EP
European Patent Office
Prior art keywords
solder alloy
alloy according
lwt
content
germanium
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Withdrawn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
EP10713920A
Other languages
German (de)
English (en)
Inventor
Michael Ott
Sebastian Piegert
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
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP2558243A2 publication Critical patent/EP2558243A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • 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°C
    • 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
    • F05D2230/238—Soldering
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a solder alloy, a method for soldering and a component with solder.
  • Components sometimes need to be repaired after manufacture, for example after casting or after they have been used and cracked.
  • a soldering process works against the temperature at
  • the solder should still have a high strength, so that the solder filled with crack or depression does not weaken the entire component at the high
  • the object is achieved by a solder made of a solder alloy according to claim 1, a method according to claim 48 or 49 and a component according to claim 51.
  • the solder alloy consists of
  • the base comprises:
  • solder comprises:
  • the additive comprises:
  • boron (B) especially 0.001wt% ⁇ B ⁇ 0.010wt%, 0wt% - 0.6wt% zirconium (Zr), especially ⁇ 0.05wt%,
  • the base uses only one, two or three elements of the group titanium (Ti), molybdenum (Mo), tantalum (Ta),
  • the base is cobalt-based
  • the base has cobalt as the remainder
  • the lot is nickel based
  • the solder has nickel as the remainder
  • solder alloy is cobalt-based
  • solder alloy has cobalt as the remainder, it does not contain any deliberate addition of boron (B), in particular ⁇ 20 ppm. it contains no silicon (Si),
  • - is the gallium (Ga) or germanium (Ge) content
  • gallium or germanium content is ⁇ 24wt%, - it contains at least 4,8wt% chromium (Cr),
  • solder alloy consists of nickel, chromium, cobalt,
  • Aluminum, tungsten and germanium or - the solder alloy consists of nickel, chromium, germanium, cobalt, tungsten and tantalum or
  • solder alloy consists of nickel, chromium, cobalt,
  • the solder alloy consists of nickel, germanium, cobalt, chromium, aluminum, titanium, tungsten and tantalum or
  • the solder alloy is solidified isothermally.
  • the component has a solder alloy according to the abovementioned features and is preferably directionally solidified.
  • the substrate is directionally solidified
  • the chromium content of the solder alloy corresponds to the chromium content of the substrate of the component
  • the titanium content of the solder alloy corresponds to the titanium content of the substrate of the component
  • Titanium content of the substrate of the component is reduced when higher proportions of germanium are used.
  • Figure 1 is a cross-sectional view of a component after a
  • 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, in particular for components for high-temperature applications, in particular in
  • Turbine vanes 120, 130 (FIG. 2) or combustion chamber elements 155 (FIG. 3) for steam or gas turbines 100 (FIG. 4) made of a nickel- or cobalt-based superalloy (FIG. 5).
  • the solder material 10 may preferably be used for all alloys according to FIG.
  • These may preferably be the known materials PWA 1483, PWA 1484 or Rene N5.
  • the solder material 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 depressions 7 are preferably about 200ym wide and can be up to 5mm deep.
  • solder 10 is applied from a solder alloy in or in the vicinity of the recess 7 and by a heat treatment (+ T) melts the solder material 10 below a
  • the solder alloy has a base, a solder and an additive, preferably it consists of base, solder and additive: with (1 -x -y) * base + x * solder + y * additive,
  • the base comprises:
  • solder comprises:
  • the additive comprises:
  • solder alloy thus represents a physical mixture of two (base, solder) or three (+ additive) powders.
  • base only one, two or three elements of the group titanium, molybdenum, tantalum can be used.
  • germanium preferably dispenses with the addition of boron (B).
  • solder alloy gallium (Ga) and no germanium (Ge) or germanium (Ge) and no gallium (Ga) or gallium (Ga) and germanium (Ge).
  • the base is cobalt-based.
  • the lot is nickel based.
  • the solder alloy is cobalt-based and is suitable
  • the solder alloy has no zircon (Zr), no hafnium (Hf), no niobium (Nb), manganese (Mn) or none
  • Aluminum (Al), titanium (Ti), tungsten (W), tantalum (Ta), chromium (Cr), cobalt (Co), germanium (Ge), gallium (Ga) are listed in the subclaims. Advantageous listings final
  • Sili ⁇ zium and / or carbon are added or the presence of Sili ⁇ zium and / or carbon because they form in the solder Sprödpha- sen.
  • the solder material 10 may be in an isothermal or a temperature gradient process with the substrate 4 of the
  • Component 1, 120, 130, 155 are connected.
  • the substrate 4 has a directional structure, for example an SX or DS structure, so that the solder material 10 subsequently has a directed structure.
  • a directional structure for example an SX or DS structure
  • directionally solidified structure in solder can also be carried out in an isothermal process.
  • the component 1, 120, 130 need not have a directionally solidified structure (but a CC structure).
  • solders in CC substrates of components 1, 120, 130 can be soldered and solidified in a CC structure, the solders then being polycrystalline solidified (CC).
  • CC polycrystalline solidified
  • solder material 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 material 10 is used to fill in cracks 7 or depressions 7.
  • FIG. 2 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
  • 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.
  • 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, in common parlance, referred to as directionally solidified) or a monocrystalline structure, ie the whole workpiece be ⁇ is made of a single crystal.
  • 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
  • a monocrystalline structure ie the whole workpiece be ⁇ is made of a single crystal.
  • Structures are also called directionally solidified structures. Such methods are known from US Pat. No. 6,024,792 and EP 0 892 090 A1.
  • 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.
  • a thermal barrier coating which is preferably the outermost layer, and consists for example of Zr0 2 , Y2Ü3-Zr02, ie 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 insulation layer is therefore preferably more porous than the
  • 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. 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. 3 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is configured, for example, as so-called an annular combustion chamber, in which a plurality of in the circumferential direction about an axis of rotation 102 arranged burners 107 open into a common combustion chamber space 154 and generate flames 156th
  • 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 facing side with a formed from heat shield elements 155. liner.
  • Each heat shield element 155 made of an alloy is on the working medium side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating). equipped or is made of high temperature resistant material (solid ceramic stones).
  • 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.
  • a ceramic Wär ⁇ medämm Anlagen be present and consists for example of ZrÜ2, Y203 ⁇ Zr02, ie it is not, partially or completely 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 insulation layer may have ⁇ porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
  • Reprocessing means that heat shield elements may need to be removed 155 after use of protective layers (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.
  • the 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 hollow and have, for example possibly still in the combustion chamber 154 opening cooling holes (not shown).
  • FIG. 4 shows by way of example a gas turbine 100 in a longitudinal partial 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. 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 135 is sucked by the compressor 105 through the intake housing and ver ⁇ seals.
  • the 105 ⁇ be compressed air provided at the turbine end of the compressor 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 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 working 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 Zr02, 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)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract
EP10713920A 2010-04-12 2010-04-12 Alliage de brasage, procédé de brasage et pièce correspondante Withdrawn EP2558243A2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2010/054754 WO2011127956A2 (fr) 2010-04-12 2010-04-12 Alliage de brasage, procédé de brasage et pièce correspondante

Publications (1)

Publication Number Publication Date
EP2558243A2 true EP2558243A2 (fr) 2013-02-20

Family

ID=42218339

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10713920A Withdrawn EP2558243A2 (fr) 2010-04-12 2010-04-12 Alliage de brasage, procédé de brasage et pièce correspondante

Country Status (3)

Country Link
US (1) US20130028783A1 (fr)
EP (1) EP2558243A2 (fr)
WO (1) WO2011127956A2 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2476506A1 (fr) * 2011-01-14 2012-07-18 Siemens Aktiengesellschaft Alliage à base de cobalt doté de germanium et procédé de soudage
DE102014200121A1 (de) * 2014-01-08 2015-07-09 Siemens Aktiengesellschaft Manganhaltige Hochtemperaturlotlegierung auf Kobaltbasis, Pulver, Bauteil und Lotverfahren
US11759877B2 (en) 2016-12-23 2023-09-19 General Electric Company Amorphous ductile braze alloy compositions, and related methods and articles

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Publication number Priority date Publication date Assignee Title
DE3140497A1 (de) * 1981-10-13 1983-04-28 GeWerTec Gesellschaft für Werkstofftechnik mbH, 4600 Dortmund "verfahren zum hochtemperaturloeten von werkstuecken aus hochwarmfesten werkstoffen"
DE58908611D1 (de) 1989-08-10 1994-12-08 Siemens Ag Hochtemperaturfeste korrosionsschutzbeschichtung, insbesondere für gasturbinenbauteile.
DE3926479A1 (de) 1989-08-10 1991-02-14 Siemens Ag Rheniumhaltige schutzbeschichtung, mit grosser korrosions- und/oder oxidationsbestaendigkeit
DE59505454D1 (de) 1994-10-14 1999-04-29 Siemens Ag Schutzschicht zum schutz eines bauteils gegen korrosion, oxidation und thermische überbeanspruchung sowie verfahren zu ihrer herstellung
EP0892090B1 (fr) 1997-02-24 2008-04-23 Sulzer Innotec Ag Procédé de fabrication de structure monocristallines
EP0861927A1 (fr) 1997-02-24 1998-09-02 Sulzer Innotec Ag Procédé de fabrication de structures monocristallines
EP1306454B1 (fr) 2001-10-24 2004-10-06 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium pour la protection d'un élément contre l'oxydation et la corrosion aux températures élevées
WO1999067435A1 (fr) 1998-06-23 1999-12-29 Siemens Aktiengesellschaft Alliage a solidification directionnelle a resistance transversale a la rupture amelioree
US6231692B1 (en) 1999-01-28 2001-05-15 Howmet Research Corporation Nickel base superalloy with improved machinability and method of making thereof
JP2003529677A (ja) 1999-07-29 2003-10-07 シーメンス アクチエンゲゼルシヤフト 耐熱性の構造部材及びその製造方法
DE50112339D1 (de) 2001-12-13 2007-05-24 Siemens Ag Hochtemperaturbeständiges Bauteil aus einkristalliner oder polykristalliner Nickel-Basis-Superlegierung

Non-Patent Citations (1)

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Also Published As

Publication number Publication date
WO2011127956A2 (fr) 2011-10-20
US20130028783A1 (en) 2013-01-31

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