EP2117757A1 - Composant et métal d'apport de brasage - Google Patents

Composant et métal d'apport de brasage

Info

Publication number
EP2117757A1
EP2117757A1 EP08716874A EP08716874A EP2117757A1 EP 2117757 A1 EP2117757 A1 EP 2117757A1 EP 08716874 A EP08716874 A EP 08716874A EP 08716874 A EP08716874 A EP 08716874A EP 2117757 A1 EP2117757 A1 EP 2117757A1
Authority
EP
European Patent Office
Prior art keywords
component
solder
base material
melting temperature
melting
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Withdrawn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
EP08716874A
Other languages
German (de)
English (en)
Inventor
Karl-Heinz Manier
Michael Ott
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
MTU Aero Engines 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
Application filed by MTU Aero Engines GmbH, Siemens AG filed Critical MTU Aero Engines GmbH
Priority to EP08716874A priority Critical patent/EP2117757A1/fr
Publication of EP2117757A1 publication Critical patent/EP2117757A1/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Withdrawn legal-status Critical Current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
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
    • B23K1/0018—Brazing of turbine parts
    • 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
    • B23K35/0244—Powders, particles or spheres; Preforms made therefrom
    • 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
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines
    • 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
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/18—Dissimilar materials
    • B23K2103/26—Alloys of Nickel and Cobalt and Chromium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00019—Repairing or maintaining combustion chamber liners or subparts
    • 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
    • Y10T428/12222—Shaped configuration for melting [e.g., package, etc.]

Definitions

  • the present invention relates to a component and a solder.
  • Components of turbines are nowadays often made of materials with a directional microstructure.
  • materials with a directed microstructure in particular monocrystalline materials and materials which have a grain structure, the extent of the grains having a common preferred direction, should be considered here.
  • the grains may have a larger dimension in a certain preferred direction than in the other directions.
  • Components with such a grain structure are also referred to as directionally solidified components (directionally solidified).
  • Highly stressed components such as turbine blades
  • soldering One possibility of repairing damaged components is, for example, soldering.
  • soldering a solder in the region of the damage is applied to the material of the component, that is to say to the base material, and connected to the base material by means of heat.
  • the solder material does not have a monocrystalline or directionally solidified structure in the conventional method.
  • a disordered structure has inferior material properties compared to a directional microstructure, especially in the high temperature range. that the solder joint has poorer material properties than the surrounding base material.
  • US Pat. No. 6,050,477 discloses a method for joining two component elements, wherein the solder is applied over a large area between the two component components and a temperature gradient is used to produce the same directional microstructure. The entire component is heated.
  • US 2003/0075587 A1 discloses a method of repairing a component having a directionally solidified microstructure, but wherein the repaired site does not have the same microstructure as the component to be repaired.
  • US Pat. No. 6,495,793 discloses a nickel-based superalloy weld repair process using a laser, wherein the laser melts the material supplied via a material conveyor. In addition, during the welding process, the base material is melted. A statement about the microstructure of the component or the repair site is not made.
  • EP 1 258 545 A1 discloses a soldering process without temperature gradients.
  • EP 1 340 567 A1 discloses a welding process in which additional material is added to the already reflowed site to be repaired. Likewise, the base material is melted here. A temperature gradient is also used to treat the components with straightened microstructure.
  • US Pat. No. 4,878,953 discloses a welding process for repairing a directional microstructure device in which material is applied to the repairing site by means of powder and that site has a fine-grained microstructure. Likewise, the base material is melted here.
  • the object of the invention is to show a solder or a component which have improved properties.
  • the object is achieved by a component according to claim 1 and a solder according to claim 8.
  • FIG. 1 shows a solder according to the invention
  • FIG. 2 shows a grain size distribution of a solder according to the invention
  • FIGS. 3, 4, 5 show an exemplary embodiment of a method for
  • Figure 6 shows a gas turbine
  • Figure 7 shows a perspective combustion chamber
  • FIG. 8 shows in perspective a turbine blade.
  • FIG. 1 shows powder particles of a solder 7 according to the invention.
  • the solder 7 represents a mixture of two metallic powder constituents 22, 25, ie has a first powder constituent 22 of coarser particles 22 with particle sizes in the sub-micrometer or micrometer range (0.7 ⁇ m-100 ⁇ m, in particular ⁇ 0.7 ⁇ m to 75 ⁇ m or particularly preferably ⁇ 25 ⁇ m and ⁇ 75 ⁇ m) and a powder constituent 25 whose particle sizes are in the nanometer range (FIG. 2), which has particle sizes of less than 500 nanometers.
  • the curves of the grain size distributions of the powder components 22, 25 (FIG. 2) may also partially overlap. However, there are always two spaced-apart maxima in the two particle size distributions of the powder constituents of the solder 7 (FIG. 2).
  • the first component 22 and the second component 25 are preferably made of different materials.
  • the second component 25 preferably corresponds to the material of the base material of a component 1, 120, 130, 155 (FIGS. 3, 6, 7, 8) to be repaired, which is preferably nickel-based.
  • the first component 22 preferably has a melting temperature below the second component 25, since the second component 25 is similar to the base material of the component 1 or corresponds. Since the second component 25 is similar to or corresponds to the base material of the component 1, the melting temperature of the second component 25 is reduced from that of the base material by the grain size effect because the second component 25 has the smaller particles 25 in the nanometer range.
  • the melting temperature of the base material of the component 1, 120, 130, 155 is that of a solid material, ie it is not influenced by the particle size effect. Due to the grain size effect of the melting temperature, the melting temperatures of the two components 22, 25 of the solder 7 are adjusted, i. the melting temperature of the higher melting component is adjusted by the grain size effect to the lower melting temperature of the first component 22, that is lowered. Also preferably, the melting point of the first constituent 22 may have a higher melting temperature than the second constituent 25.
  • the melting temperatures of the constituents 22, 25 of the solder 7 are always below the melting point of the base material of a component 1 to be repaired.
  • the first component 22 is an alloy, preferably nickel-based.
  • the second component 25 is an alloy that is preferably nickel-based.
  • the second component 25 may correspond or resemble the material of the substrate.
  • Similar composition means that the constituents 22, 25 have at least the main alloying elements (elements with alloying fraction ⁇ lwt%) of an alloy composition (base material), preferably at least all alloying elements of the alloy of the base material, but their proportions are changed for this constituent of the solder, plus additives (Melting point depressant).
  • base material preferably at least all alloying elements of the alloy of the base material, but their proportions are changed for this constituent of the solder, plus additives (Melting point depressant).
  • the term “... corresponds to the base material” means identical composition with the base material.
  • the first constituent 22 may preferably have a lower melting point without a melting point depressant, because its composition deviates from the base material of the constituent 1, 120, 130, 155.
  • the first component 22 has at least one melting point depressant, in particular one, in particular boron
  • Ti tantalum
  • Ta zirconium
  • First component 22 base material of the component 1 + melting point lower.
  • solder 7 the composition of which is different from the base material ( ⁇ substrate).
  • FIG. 3 shows a schematic view of a damaged component 1 which is repaired with the solder 7 according to the invention.
  • the base material of the component 1 for example a turbine blade 120, 130 (Figure 7), comprises an alloy, preferably nickel-based, and preferably has a directional microstructure, indicated in the figures by short diagonal bars.
  • the damage 3 of the component 1 is located in the region of the surface 5 and is shown in FIG. 3 as a depression.
  • a solder 7 which in the present exemplary embodiment is in powder form, is used. is applied to the pre-cleaned damaged site 3 and then by means of heat with the base material of the component 1 soldered (Fig. 4).
  • the entire required solder 7 is preferably introduced with a small excess into the preferably pre-cleaned damaged area 3 and, in particular, is not added stepwise during the melting.
  • the solder 7 is pressed into the damaged area 3.
  • This has the advantage that the entire damaged area 3 is filled with the solder 7.
  • an external powder feed with a powder feeder would not ensure that the solder 7 can reach the crack tip.
  • the solder 7 can be applied in the form of a paste, a slurry, in pure powder form or by means of a film and introduced into the damaged area 3. It is advantageous if the material composition of the solder 7 is similar to that of the component 1.
  • the solder 7 must comprise at least one constituent whose melting temperature is lower than the melting temperature of the base material of the component 1, so that melting of the solder 7, but not of the base material of the component 1, takes place by means of the heat.
  • the difference in the melting temperature of Lot 7 and base material is in particular at least 70 0 C, preferably 70 0 C ⁇ 4 ° C.
  • the solder 7 is preferably first melted so that it runs into the point to be repaired 3.
  • the temperature required for this may be higher or lower than the temperatures for adjusting the directional microstructure.
  • the materials PWA 1483, PWA 1484 and RENE N5 have proven particularly advantageous for the application of the solder 7 according to the invention.
  • PWA 1483 has a melting point of 1341 0 C
  • RENE N5 has a melting point in the region around 1360 - 1370 having 0 C.
  • the solder 7 to be used has a melting temperature of 1271 ° C.
  • an electron beam gun 9 is preferably present in the present exemplary embodiment, which irradiates the solder 7 to be melted and thus supplies the heat necessary for melting.
  • the heat effect on the solder 7 can also be done by means of laser beam.
  • the electron beam treatment is preferably carried out in vacuo.
  • oxidation-sensitive materials such as in superalloys, the oxidation plays an important role, so that a heat treatment by means of a laser or an electron beam should be carried out anyway in a vacuum.
  • the electron beam treatment has the advantage that it leads to a better energy coupling into the material and that the electric be moved through the coil, which in this case represent the optics, on the point to be repaired 3 without contact.
  • a temperature gradient in the region of the damage 3 is selectively produced in the preferred direction of the microstructure of the base material.
  • the temperature gradient can be produced by moving the component 1 and the electron beam gun 9 relative to one another. In the exemplary embodiment, therefore, the electron beam gun 9 is guided parallel to the surface 5 via the solder 7. The speed with which the electron beam gun 9 passes over the solder 7 is selected such that the desired temperature gradient in the region of the damage 3, i. in Lot 7, sets. The temperature gradient thereby induces the formation of an epitaxially directed microstructure when the solder 7 melted by the electron beam gun 9 solidifies again.
  • the steepness of the temperature gradient can be adjusted, for example, by the speed with which electron beam gun 9 and component 1 are moved relative to one another, or the laser power.
  • the steepness of the gradient here means the increase or decrease in the temperature per unit length.
  • the steepness of the temperature gradient which leads to the formation of a directed microstructure in the solidifying solder, depends on the composition of the solder 7.
  • the preferred direction of the directed microstructure in the base material of the component 1 extends from left to right within the plane of the drawing.
  • the movement of the electron beam gun 9 relative to the component 1 is parallel to the preferred direction of the directed microstructure of the base material.
  • FIG. 5 shows the component 1 after repairing the damage 3.
  • the solidified solder 7, ie the repair material has a directional microstructure which has the same preferred direction as the directed one Microstructure of the base material of the component 1 has.
  • Lot 7 solidify undirected. This can be done for a SX, DS or CC component.
  • the electron beam can also be widened in such a way that, for example, it irradiates the entire solder 7 and in any case completely heats it.
  • a method of the electron gun is therefore not absolutely necessary.
  • an electron beam gun 9 was used to supply the heat.
  • the use of other optical means was used to supply the heat.
  • Heating methods such as lighting with a conventional lighting device, possible.
  • inductive heating methods instead of optical heating methods, in which the solder is heated by means of heating coils.
  • special heating furnaces such as a so-called “hot box” or a casting furnace for producing a casting with a directionally oriented microstructure. In any case, that must be be used to produce a temperature gradient in the direction desired for the solidification in the area of damage or solder-filled damage.
  • a furnace this can for example be done by a stationary oven, which makes it possible to adjust the heating effect in different areas of the furnace separately.
  • a film or a paste by means of which the solder 7 is applied may partially comprise a powder of nanopowders.
  • FIG. 6 shows by way of example a gas turbine 100 in one embodiment
  • 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
  • Each turbine stage 112 is formed, for example, from two blade rings. In the flow direction of a working medium As can be seen in the hot gas duct 111 of a guide blade row 115, a row 125 formed of rotor blades 120 follows.
  • 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 highest 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 120, 130 and components of the combustion chamber 110 are For example, iron, nickel or cobalt-based superalloys used.
  • 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.
  • FIG. 7 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, a fastening area 400, an adjacent blade platform 403 and an airfoil 406 and a blade tip 415.
  • the blade 130 may have another platform at its blade tip 415 (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 for example, 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 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 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, for general language use, referred to as directionally solidified) or a monocrystalline structure, ie the whole workpiece consists 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 whole workpiece consists of a single crystal.
  • directionally solidified structures generally refers to single crystals that have no grain boundaries or at most small angle grain boundaries, as well as stem crystal structures that have grain boundaries running in the longitudinal direction 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. 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.
  • a heat-insulating layer which is preferably the outermost layer, and consists for example of Zr ⁇ 2, Y2 ⁇ 3-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 be porous, micro- or macro-cracked bodies. have ner for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
  • 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.
  • 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.
  • 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.
  • 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 Bl, EP 0 412 397 B1 or EP 1 306 454 A1.
  • MCrAlX may still be present, for example, a ceramic thermal barrier coating and consists for example of ZrC> 2, Y2Ü3-Zr ⁇ 2, i. it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • Other coating methods are conceivable, e.g. atmospheric plasma spraying (APS), LPPS, VPS or CVD.
  • the thermal barrier coating may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • Refurbishment means that turbine blades 120, 130, heat shield elements 155 may need to be deprotected (e.g., by sandblasting) after use. This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, cracks in the turbine blade 120, 130 or the heat shield element 155 are also repaired. This is followed by a re-coating of the turbine blades 120, 130, heat shield elements 155 and a renewed use of the turbine blades 120, 130 or the heat shield elements 155.

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

Abstract

L'invention concerne un procédé de réparation pour réparer un matériau de base avec des composants (1) comportant une microstructure orientée. La réparation s'effectue de manière à pouvoir utiliser un métal d'apport de brasage (7) présentant des parties constitutives ayant des distributions granulométriques différentes.
EP08716874A 2007-03-09 2008-02-15 Composant et métal d'apport de brasage Withdrawn EP2117757A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08716874A EP2117757A1 (fr) 2007-03-09 2008-02-15 Composant et métal d'apport de brasage

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP07004959A EP1967313A1 (fr) 2007-03-09 2007-03-09 Composant et une brasure
PCT/EP2008/051867 WO2008110427A1 (fr) 2007-03-09 2008-02-15 Composant et métal d'apport de brasage
EP08716874A EP2117757A1 (fr) 2007-03-09 2008-02-15 Composant et métal d'apport de brasage

Publications (1)

Publication Number Publication Date
EP2117757A1 true EP2117757A1 (fr) 2009-11-18

Family

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP07004959A Withdrawn EP1967313A1 (fr) 2007-03-09 2007-03-09 Composant et une brasure
EP08716874A Withdrawn EP2117757A1 (fr) 2007-03-09 2008-02-15 Composant et métal d'apport de brasage

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP07004959A Withdrawn EP1967313A1 (fr) 2007-03-09 2007-03-09 Composant et une brasure

Country Status (3)

Country Link
US (1) US20100119859A1 (fr)
EP (2) EP1967313A1 (fr)
WO (1) WO2008110427A1 (fr)

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EP1967313A1 (fr) 2008-09-10
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