EP2558244A2 - Alliage de brasage, procédé de brasage et pièce correspondante - Google Patents

Alliage de brasage, procédé de brasage et pièce correspondante

Info

Publication number
EP2558244A2
EP2558244A2 EP10713921A EP10713921A EP2558244A2 EP 2558244 A2 EP2558244 A2 EP 2558244A2 EP 10713921 A EP10713921 A EP 10713921A EP 10713921 A EP10713921 A EP 10713921A EP 2558244 A2 EP2558244 A2 EP 2558244A2
Authority
EP
European Patent Office
Prior art keywords
solder alloy
alloy according
lwt
solder
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Withdrawn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
EP10713921A
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
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 EP2558244A2 publication Critical patent/EP2558244A2/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Withdrawn legal-status Critical Current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 degrees 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 and a method for soldering.
  • 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, by a method according to claim 60 and by a component according to claim 62.
  • the solder alloy consists of:
  • the base comprises:
  • Ti 0, lwt% - 6wt% titanium (Ti), in particular ⁇ lwt%,
  • solder comprises:
  • the additive comprises:
  • solder alloy it uses for the base only one element of the group titanium, molybdenum, tantalum, it uses for the base at least two elements of
  • the solder has nickel as the remainder
  • Ni nickel
  • Zr zirconium
  • B boron
  • C carbon
  • Mo molybdenum
  • Ga gallium
  • Ge germanium
  • Hf nium
  • Nb niobium
  • W tantalum
  • Ta chromium
  • Co cobalt
  • Al aluminum
  • Ti titanium
  • it does not contain manganese, it consists of nickel, germanium, chromium, aluminum, cobalt, tungsten and titanium, it consists of nickel, germanium, chromium, aluminum, cobalt, tungsten, Tantalum and titanium, it consists of nickel, germanium, chromium, aluminum, cobalt, tungsten, titanium, carbon and molybdenum, it consists of nickel, germanium, cobalt, chromium, titanium, tungsten, molybdenum, tantalum and aluminum, it consists of nickel , Germanium, chromium, aluminum, cobalt, carbon, molybdenum, tungsten, tantalum and
  • Titanium it consists of nickel, carbon, germanium, chromium, cobalt, aluminum, molybdenum, tungsten, tantalum, niobium, titanium and zirconium
  • the method involves solidifying the solder alloy in a polycrystalline (CC) direction, in particular in the case of polycrystalline components, a further advantageous development of the method being that the solder (10) is directionally solidified.
  • the component contains a solder from the aforementioned solder alloy.
  • the component can be advantageous respectively goge forms ⁇ as follows, where these features advantageously be ⁇ can be combined arbitrarily with each other:
  • the substrate of the component is directionally solidified
  • the substrate of the component is not solidified directed ⁇ the chromium content of the solder alloy corresponds to the Chromge ⁇ halt of the substrate of the component,
  • the content of cobalt corresponds to the content of cobalt of the substrate of the component
  • the aluminum content of the solder alloy is reduced compared to the aluminum content of the substrate of the component, in particular reduced by 10%, the titanium content of the solder alloy is lower than that
  • Titanium content of the substrate of the component when the contents of germanium between 18Gew .-% and 30Gew .-%, in particular by at least 10% lower, the solder alloy has no molybdenum.
  • further advantageous measures are listed, which can be combined with each other in an advantageous manner with each other.
  • 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 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. This can preferably be ⁇ knew materials PWA 1483, PWA 1484, his Rene 80 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 material 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 melting temperature of the substrate 4 and fills the Vertie ⁇ tion 7 completely.
  • the solder alloy consists of
  • the base comprises:
  • Ti 0, lwt% - 6wt% titanium (Ti), in particular ⁇ lwt%,
  • solder comprises:
  • the additive comprises:
  • germanium (Ge) is preferably dispensed with the addition of boron (B).
  • germanium is preferably dispensed with the addition of silicon (Si).
  • Sili ⁇ zium and / or carbon are added or the presence of Sili ⁇ zium and / or carbon because they form in the solder Sprödpha- sen.
  • Gallium (Ga) and germanium (Ge) are used.
  • the base has only one, two or three elements of the group titanium, molybdenum, tantalum.
  • the base is especially nickel-based.
  • the solder is especially nickel-based.
  • the alloy contains no zirconium (Zr), no
  • Zr zirconium
  • B boron
  • Mo molybdenum
  • Ga gallium
  • Ge germanium
  • Hf hafnium
  • Nb niobium
  • W tantalum
  • Ta tantalum
  • Cr chromium
  • Co cobalt
  • Al aluminum
  • Ti Titanium
  • the solder alloy is preferably made of nickel, germanium, chromium, aluminum, cobalt, tungsten and titanium.
  • the solder alloy consists of nickel, germanium, chromium, aluminum, cobalt, tungsten, tantalum and titanium.
  • the solder alloy consists of nickel, Ger ⁇ manium, cobalt, chromium, aluminum, tungsten, titanium, carbon and molybdenum.
  • the solder alloy consists of nickel, Ger ⁇ manium, cobalt, chromium, titanium, tungsten, molybdenum, tantalum and aluminum. Also preferably, the solder alloy consists of nickel, Ger ⁇ manium, chromium, aluminum, cobalt, carbon, molybdenum, tungsten, tantalum and titanium.
  • the solder alloy likewise preferably consists of nickel, carbon, germanium, chromium, cobalt, aluminum, molybdenum, tungsten, tantalum, niobium, titanium and zirconium.
  • rhenium can preferably be dispensed with.
  • the solder material 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 tet then at preferably when the substrate 4 has a ge ⁇ directional structure, for example an SX or DS structure, so that the solder material 10 then has a directional structure.
  • a directionally solidified structure in the solder can also be carried out in an isothermal process.
  • the component 1 does not need to have directionally solidified structural ⁇ ture (but a CC structure).
  • 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:
  • an inert gas especially argon, is preferably used, which reduces the chromium evaporation from the substrate 4 at the high temperatures, or a reducing gas (argon / hydrogen) is used.
  • the 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 ver ⁇ used to fill cracks 7 or recesses 7.
  • FIG. 2 shows a perspective view of a rotor 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 electricity 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 thereto adjacent blade platform 403 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, for example, as a hammerhead out staltet ⁇ .
  • Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has for a medium which flows past the scene ⁇ felblatt 406, a leading edge 409 and a trailing edge 412.
  • 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.
  • 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 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 insulating layer can ⁇ ner to have better thermal shock resistance porous, micro- or macro-cracked pERSonal.
  • the thermal barrier coating 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.
  • a relatively long service life loan to enable 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 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 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.
  • 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 insulation layer may have ⁇ porous, micro- or macro-cracked compatible 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.
  • 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.
  • 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, for example, a ring-shaped hot gas channel 111.
  • a ring-shaped hot gas channel 111 There, for example, form four successive turbine stages 112, the turbine 108th
  • 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.
  • Coupled to the rotor 103 is a generator or work machine (not shown).
  • 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 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 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, 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 can have a directional structure, ie 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 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.
  • 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.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the guide blade 130 has a guide blade root facing the inner housing 138 of the turbine 108 (not shown here) and a guide blade foot opposite
  • 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
EP10713921A 2010-04-12 2010-04-12 Alliage de brasage, procédé de brasage et pièce correspondante Withdrawn EP2558244A2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2010/054756 WO2011127958A2 (fr) 2010-04-12 2010-04-12 Alliage de brasage, procédé de brasage et pièce correspondante

Publications (1)

Publication Number Publication Date
EP2558244A2 true EP2558244A2 (fr) 2013-02-20

Family

ID=42201079

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10713921A Withdrawn EP2558244A2 (fr) 2010-04-12 2010-04-12 Alliage de brasage, procédé de brasage et pièce correspondante

Country Status (3)

Country Link
US (1) US20130045129A1 (fr)
EP (1) EP2558244A2 (fr)
WO (1) WO2011127958A2 (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
EP2581164A1 (fr) * 2011-10-14 2013-04-17 Siemens Aktiengesellschaft Procédé de réparation de dommages superficiels d'un composant de turbomachine
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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DE3875444D1 (de) * 1987-09-29 1992-11-26 Vacuumschmelze Gmbh Nickel-basis-lot fuer hochtemperatur-loetverbindungen.
DE3926479A1 (de) 1989-08-10 1991-02-14 Siemens Ag Rheniumhaltige schutzbeschichtung, mit grosser korrosions- und/oder oxidationsbestaendigkeit
WO1991002108A1 (fr) 1989-08-10 1991-02-21 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
EP0786017B1 (fr) 1994-10-14 1999-03-24 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
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
EP1258545B1 (fr) * 2001-05-14 2004-12-01 ALSTOM Technology Ltd Procédé de brasage isothermique d'éléments monocristallins
DE50112339D1 (de) 2001-12-13 2007-05-24 Siemens Ag Hochtemperaturbeständiges Bauteil aus einkristalliner oder polykristalliner Nickel-Basis-Superlegierung
EP1970156A1 (fr) * 2007-03-14 2008-09-17 Siemens Aktiengesellschaft Alliage de brasage et procédé destiné à la réparation d'un composant

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Also Published As

Publication number Publication date
US20130045129A1 (en) 2013-02-21
WO2011127958A2 (fr) 2011-10-20

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