WO2007012338A1 - Verfahren zum reparieren eines mit einer gerichteten mikrostruktur umfassenden bauteils, durch einstellung während der laser-wärmeeinwirkung ein temperaturgradient; ein mit einem solchen verfahren hergestellter bauteil - Google Patents
Verfahren zum reparieren eines mit einer gerichteten mikrostruktur umfassenden bauteils, durch einstellung während der laser-wärmeeinwirkung ein temperaturgradient; ein mit einem solchen verfahren hergestellter bauteil Download PDFInfo
- Publication number
- WO2007012338A1 WO2007012338A1 PCT/EP2005/008038 EP2005008038W WO2007012338A1 WO 2007012338 A1 WO2007012338 A1 WO 2007012338A1 EP 2005008038 W EP2005008038 W EP 2005008038W WO 2007012338 A1 WO2007012338 A1 WO 2007012338A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- component
- solder
- base material
- repaired
- temperature
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
- B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
-
- 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
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/002—Soldering by means of induction heating
-
- 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
- B23K1/005—Soldering by means of radiant energy
- B23K1/0056—Soldering by means of radiant energy soldering by means of beams, e.g. lasers, E.B.
-
- 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 present invention relates to a method for repairing a component which comprises a base material with a directional microstructure according to claim 1 and a component according to claim 27.
- 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 called directionally solidified components
- Highly stressed components such as turbine blades
- Since the manufacture of components from base materials having a directional microstructure is relatively costly, it is usually sought to repair such components after the occurrence of damage. Thus, the functionality is restored and the component can be used for a further revision period.
- 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 in the usual procedure no monocrystalline or directionally solidified structure.
- a disordered structure has inferior material properties compared to a directional microstructure - especially in the high temperature range - so that the solder joint has worse material properties than the surrounding base material.
- US Pat. No. 6,050,477 discloses a method for connecting 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 welding 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 method for repairing a component with a directed microstructure, in which material is applied to the repairing point by means of powder and this point has a fine-grained microstructure. Likewise, the base material is melted here.
- the object of the invention is therefore to provide a method and a component with which damaged components comprising a base material with a directed microstructure can be repaired even if the damage is located in a structurally bearing region of the component.
- the repair method according to the invention can also be used in structurally bearing regions of the component without the good material properties of the component Base material.
- the temperature gradient By means of the temperature gradient, it is possible to achieve an epitaxial growth and solidification of the solder, ie a growth in which the crystalline orientation of the solder during solidification is determined by the solidification of the substrate, ie the base material.
- the temperature gradient Therefore, it is possible to produce a single-crystal solder region or another directional microstructure in the solder that has been soldered with material properties that are similarly improved compared to a non-oriented microstructure.
- the directed growth takes place in the direction of the temperature gradient, ie in the direction from the lower to the higher temperature. Due to the directed growth and the resulting directional microstructure, the soldered solder has similarly good material properties as the base material of the component.
- the temperature gradient in the repair method according to the invention is preferably produced such that it runs in the direction of the orientation of the directed microstructure of the base material of the component. In this way, directed growth of the solidifying solder in the direction of orientation of the directional microstructure of the base material can be achieved.
- the solder has a first component having a melting temperature that is lower, preferably significantly lower, than the melting temperature of the base material of the component and a second component having a high strength and a melting temperature above the melting temperature of the first component but below the melting point Melting temperature up to the melting temperature of the base material is on.
- the solder is applied in the area of the spot to be soldered in such a way that the proportion of the first component in the solder in the local area
- the first low melting temperature component serves to compound the solder to the base material, while the high melting temperature component provides the strength (strength) of the solder being soldered. Because the solder in the region of the base material has a higher share of the first comprises a good connection of the soldered solder to the base material. On the other hand, in areas having a greater distance from the base material, relatively more of the second component, ie the higher resistance component, is present, so that the areas of the solder joint exposed during later operation of the component have a high resistance.
- all heating processes can be used which are capable of producing a temperature gradient in the region of a spot to be soldered, i. in the lot, to manufacture.
- optical heating processes for example by means of laser or conventional illumination devices, or inductive heating processes, for example by means of heating coils, can be used.
- a casting furnace may be used to cast materials with a directionally directed microstructure.
- FIGS. 1a-1c show an exemplary embodiment of the method according to the invention
- Figure 2 shows a modification of the embodiment
- Figure 3 shows a turbine blade
- Figure 4 shows a combustion chamber
- Figure 5 shows a gas turbine.
- FIG. 1 a a damaged component 1 is shown in a schematic view.
- the base material of the component 1 comprises an alloy, preferably nickel-based and has a directional microstructure, which in the figures by short diagonal
- the damage 3 of the component 1 is located in the region of the surface 5 and is shown in the figure as a recess.
- the soldering temperature of solder 7 during soldering is at least 30 ° C. or at least 50 ° C. lower than the melting temperature of the base material of component 1, so that the base material is not endangered.
- the difference between the soldering temperature and the melting temperature is between 50 0 C and 70 0 C. This is particularly important if the base material is superalloys.
- chromium evaporates at high temperatures near its melting temperatures, so that the melting temperature of the solder 7 is kept as low as possible and thus the difference between soldering temperatures of the solder 7 and the melting temperature of the base material should be kept as high as possible.
- Melting temperature of the base material is preferably also at least 70 0 C, preferably 70 0 C + 4 ° C.
- the maximum difference in the soldering temperature of the solder 7 and the Melting temperature of the base material is preferably 120 0 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.
- PWA 1483 has a melting point of 1341 ° C
- RENE N5 has a melting point in the region of 1360 0 C - 1370 0 C.
- the melting points of the solders 7 are between, for example, 1160 0 C - 1220 0 C.
- the electron beam treatment is preferably carried out in vacuo.
- oxidation-sensitive materials such as superalloys
- 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 electron beams contact each other by means of coils, which in this case are the optics represent over the move to the repairing point 3.
- the heat effect on the solder 7 can also be done by means of laser beam.
- the laser power or the power of the electron beams is measured so that it can completely melt the solder 7 and bring it to soldering temperature.
- the soldering temperature of the solder 7 is partially up to 140 ° above the melting temperature of the solder 7.
- the power of an Nd-YAG laser is preferably between 1500 and 2000W.
- a temperature gradient in the region of the damage 3 is produced specifically in the preferred direction of the microstructure of the base material.
- the temperature gradient can be established 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 guiding of the electron beam gun 9 takes place via the solder 7 is selected such that the desired temperature gradient in the region of the damage 3, ie in the solder 7, is established. 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 at which the electron beam gun 9 and component 1 are moved relative to one another or the 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 7, depends on the composition of the solder 7.
- the temperature gradient that needs to be adjusted results from the so-called GV diagram, which is different for different metals and metallic alloys and must be calculated or experimentally determined for each alloy.
- a curve L in the GV diagram separates the
- the temperature gradient is determined by the soldering temperature of the solder 7 and the temperature of the component on the back of the part 3 to be repaired.
- the component 1 is not cooled or kept at room temperature or optionally preheated to 300 °, as described in the publications WO 98/20995, WO 98/05450, WO 96/05006 or EP 0 631 832 Al.
- component 1 and repaired site 3 have the same microstructure.
- the component 1 need not have a directionally solidified structure, wherein in the repaired body 3 by the directionally solidified structure at high temperatures, a high strength of the component 1 is achieved because the directionally solidified structure of the solder 7 in the repaired site the negative effect of low melting point on the mechanical strength at high temperatures.
- a width b (FIG. 1a) of the point to be repaired is between 1 ⁇ m and 1000 ⁇ m, preferably around 500 ⁇ m.
- the laser or electron beam may preferably detect the entire width b of the point 3 to be repaired. Since the component 1 is heated only in the area of the point to be repaired 3, there is a local repair method or local soldering method.
- the point to be repaired 3 has a width b between 5 .mu.m and 100 .mu.m. Furthermore, widths b of a crack between 20 ⁇ m and 300 ⁇ m can be repaired. Preferably, the point 3 to be repaired has widths b between 20 ⁇ m and 100 ⁇ m.
- the point to be repaired 3 has a width between 50 .mu.m and 300 .mu.m.
- the point to be repaired 3 has a width b between 50 .mu.m and 200 .mu.m.
- cracks 3 having a width between 50 ⁇ m and 100 ⁇ m are advantageously repaired by the method.
- the laser 9 and the electron beams in the longitudinal direction if necessary, must be moved (into the plane of the drawing), the laser being moved in this direction, as in WO 03/087439 A1.
- the traveling speeds of the laser beams or the electron beams are preferably from 100 mm / min to 130 mm / min.
- the holding times of the laser or electron beam depend on the material and the rate of solidification.
- FIG. 1c 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 has the directional microstructure of the base material of the component 1.
- the electron beam can be widened so that it irradiates, for example, the entire solder 7 and in any case completely heated by it.
- a method of the electron gun is therefore not absolutely necessary.
- the component 1 By dissipating heat of the solder 7 in the substrate of the component 1, a temperature gradient arises within the solder 7. At the outer surface of the solder 7, the temperature is highest and at the interface of the solder 7 to the substrate of the component 1, it is colder. Possibly.
- the component 1 may be cooled or heated at the rear side, the damage 3 opposite or anywhere else to set a desired specific temperature gradient depending on the geometry of the component 1 and the damage 3.
- an electron beam gun 9 was used to supply the heat.
- other optical 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.
- the method used must be capable of producing a temperature gradient in the direction desired for solidification in the area of the damage or the damage filled with solder. When using 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.
- the solder 17 applied to the damaged spot 3 comprises two constituents, of which the first constituent has a melting temperature which is significantly lower than that of the base material of the component 1.
- the second constituent has a melting temperature which is in the range between the melting temperature of the first constituent and the melting temperature of the base material.
- the second component in particular also has a high strength of approximately the order of magnitude of the base material.
- the powdered solder 17 is applied to the pre-cleaned damaged area 3 in such a way that first a solder composition 18 is applied, in which the first component constitutes a relatively high proportion of the powder.
- solder composition 19 is applied, in which the first component is reduced compared to the second component. If now a soldering of Lot 17 with the Ba If, for example, the high proportion of the first constituent, ie the low melting temperature constituent, facilitates easy soldering of the solder to the base material, then the solder composition 19, in which the proportion of the first constituent is reduced, will increase the strength of the repaired spot guaranteed.
- solder composition 18 ensures a higher strength of the point 3 to be repaired and the near-surface solder composition 19 has a higher oxidation and / or corrosion protection.
- solder 7 in the point to be repaired 3 have a material gradient from the bottom of the point 3 to the surface 5 of the component, in which the composition of the solder 7 changes continuously.
- solder 7, 17 is applied in powder form to the point to be repaired. Alternatively, however, it can also be applied as a film or paste.
- the film or the paste, by means of which the solder 7 is applied may comprise partially or completely a powder of nanopowder.
- FIG. 3 shows a perspective view of a moving blade 120 or guide blade 130 of a turbomachine, which extends along a longitudinal axis 121 and which is repaired by the method according to the invention.
- 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 adjoining thereto and an airfoil 406. As a guide blade 130, 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. 1?
- 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; These writings are with respect. the chemical composition of the alloy part of the disclosure.
- the blade 120, 130 is hereby made by a casting process by means of directional solidification.
- 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 Bl, EP 0 412 397 B1 or EP 1 306 454 A1, which relate to.
- the chemical composition of the alloy should be part of this disclosure.
- a thermal barrier coating consists for example of ZrO 2 , Y 2 O 4 -ZrO 3 , that is, it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
- suitable coating processes such as electron beam evaporation (EB-PVD), stalk-shaped grains are produced in the thermal barrier coating.
- 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.
- the blade 120, 130 is to be cooled, it is hollow and may still film cooling holes 418 (indicated by dashed lines) on.
- FIG. 4 shows a combustion chamber 110 of a gas turbine 100.
- the combustion chamber 110 is designed, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 107 arranged in the circumferential direction around a rotation axis 102 open into a common combustion chamber space 154, which produce 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 Bl, EP 0 412 397 B1 or EP 1 306 454 A1, which relate to.
- the chemical composition of the alloy should be part of this disclosure.
- MCrAlX may still be present, for example, a ceramic thermal barrier coating and consists for example of ZrO 2 , Y 2 O 4 -ZrO 2 , ie 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.
- Refurbishment means that 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. 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, for example, hollow and possibly still have film cooling holes (not shown) which open into the combustion chamber space 154.
- FIG. 5 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 an annular annular hot gas channel 111, for example.
- annular annular hot gas channel 111 for example.
- 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, 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. To withstand the prevailing temperatures, they can be cooled by means of a coolant.
- 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; These writings are with respect. the chemical composition of the alloys part of the revelation.
- the blades 120, 130 may be anticorrosive coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and represents yttrium (Y) and / or silicon and / or at least one element of the rare earths or hafnium).
- M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
- X is an active element and represents yttrium (Y) and / or silicon and / or at least one element of the rare earths 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 are to be part of this disclosure with regard to the chemical composition.
- MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie 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 an inner housing 138 of the
- Turbine 108 facing Leitschaufeifuß (not shown here) and a Leitschaufeluß opposite the Leitschaufelfuß on.
- 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)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Welding Or Cutting Using Electron Beams (AREA)
- Electric Connection Of Electric Components To Printed Circuits (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/EP2005/008038 WO2007012338A1 (de) | 2005-07-22 | 2005-07-22 | Verfahren zum reparieren eines mit einer gerichteten mikrostruktur umfassenden bauteils, durch einstellung während der laser-wärmeeinwirkung ein temperaturgradient; ein mit einem solchen verfahren hergestellter bauteil |
CN200580051135XA CN101272880B (zh) | 2005-07-22 | 2005-07-22 | 用于修补部件的方法 |
EP05774084A EP1910006B1 (de) | 2005-07-22 | 2005-07-22 | Verfahren zum reparieren eines mit einer gerichteten mikrostruktur umfassenden bauteils, durch einstellung während der elektron- oder der laser-wärmeeinwirkung eines temperaturgradient |
AT05774084T ATE537928T1 (de) | 2005-07-22 | 2005-07-22 | Verfahren zum reparieren eines mit einer gerichteten mikrostruktur umfassenden bauteils, durch einstellung während der elektron- oder der laser-wärmeeinwirkung eines temperaturgradient |
US11/989,214 US8141769B2 (en) | 2005-07-22 | 2005-07-22 | Process for repairing a component comprising a directional microstructure by setting a temperature gradient during the laser heat action, and a component produced by such a process |
JP2008521807A JP2009502503A (ja) | 2005-07-22 | 2005-07-22 | 方向性ミクロ組織の母材を有する部品の修復方法とその部品 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/EP2005/008038 WO2007012338A1 (de) | 2005-07-22 | 2005-07-22 | Verfahren zum reparieren eines mit einer gerichteten mikrostruktur umfassenden bauteils, durch einstellung während der laser-wärmeeinwirkung ein temperaturgradient; ein mit einem solchen verfahren hergestellter bauteil |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2007012338A1 true WO2007012338A1 (de) | 2007-02-01 |
Family
ID=36001020
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2005/008038 WO2007012338A1 (de) | 2005-07-22 | 2005-07-22 | Verfahren zum reparieren eines mit einer gerichteten mikrostruktur umfassenden bauteils, durch einstellung während der laser-wärmeeinwirkung ein temperaturgradient; ein mit einem solchen verfahren hergestellter bauteil |
Country Status (6)
Country | Link |
---|---|
US (1) | US8141769B2 (de) |
EP (1) | EP1910006B1 (de) |
JP (1) | JP2009502503A (de) |
CN (1) | CN101272880B (de) |
AT (1) | ATE537928T1 (de) |
WO (1) | WO2007012338A1 (de) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2906172A1 (fr) * | 2006-09-22 | 2008-03-28 | Snecma Services Sa | Procede de retouche locale par brasage induction |
EP1930116A2 (de) | 2006-12-07 | 2008-06-11 | Turbine Overhaul Services Private Limited | Verfahren zum Diffusionslöten mit Nanopartikellegierungen |
EP2078579A1 (de) * | 2008-01-10 | 2009-07-15 | Siemens Aktiengesellschaft | Verfahren zum Löten eines Bauteils und Bauteil mit Löt- und Schweissstellen |
EP2226149A1 (de) * | 2009-03-04 | 2010-09-08 | Siemens Aktiengesellschaft | Zweischritt-Schweissverfahren |
US8119948B2 (en) * | 2007-10-05 | 2012-02-21 | Snecma | Method of retouching metal parts |
CN111151834A (zh) * | 2019-12-26 | 2020-05-15 | 浙江大学 | 真空钎焊铝制板翅式换热器芯体局部外漏的钎焊修复方法 |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102006026704A1 (de) * | 2006-06-08 | 2007-12-13 | Mtu Aero Engines Gmbh | Verfahren zur Herstellung oder Reparatur von Turbinen- oder Triebwerksbauteilen, sowie Bauteil, nämlich Turbinen- oder Triebwerksbauteil |
EP1967312A1 (de) * | 2007-03-06 | 2008-09-10 | Siemens Aktiengesellschaft | Verfahren zur Lötreparatur eines Bauteils unter Vakuum und einem eingestellten Sauerstoffpartialdruck |
SG155778A1 (en) * | 2008-03-10 | 2009-10-29 | Turbine Overhaul Services Pte | Method for diffusion bonding metallic components with nanoparticle foil |
US20120231295A1 (en) * | 2011-03-08 | 2012-09-13 | General Electric Company | Method of fabricating a component and a component |
CH705662A1 (de) * | 2011-11-04 | 2013-05-15 | Alstom Technology Ltd | Prozess zur Herstellung von Gegenständen aus einer durch Gamma-Prime-Ausscheidung verfestigten Superlegierung auf Nickelbasis durch selektives Laserschmelzen (SLM). |
US8942462B2 (en) * | 2012-04-12 | 2015-01-27 | GM Global Technology Operations LLC | Method for automatic quantification of dendrite arm spacing in dendritic microstructures |
US10415390B2 (en) | 2012-05-11 | 2019-09-17 | Siemens Energy, Inc. | Repair of directionally solidified alloys |
EP2754527A1 (de) * | 2013-01-11 | 2014-07-16 | Siemens Aktiengesellschaft | Erzeugung von feinen Körnern beim Auftragsschweißen |
US9056443B2 (en) * | 2013-02-04 | 2015-06-16 | General Electric Company | Brazing process, braze arrangement, and brazed article |
US9254537B2 (en) * | 2013-12-19 | 2016-02-09 | Siemens Energy, Inc. | Plural layer putty-powder/slurry application method for superalloy component crack vacuum furnace healing |
EP3216554B1 (de) * | 2016-03-09 | 2020-05-06 | MTU Aero Engines GmbH | Bauteil mit verschleissgeschützten öffnungen und vertiefungen sowie verfahren zur herstellung derselben |
EP3441180A1 (de) * | 2017-08-11 | 2019-02-13 | General Electric Company | Verfahren zur reparatur von superlegierungen |
US10976052B2 (en) | 2017-10-25 | 2021-04-13 | General Electric Company | Volute trapped vortex combustor assembly |
US10976053B2 (en) | 2017-10-25 | 2021-04-13 | General Electric Company | Involute trapped vortex combustor assembly |
US11181269B2 (en) | 2018-11-15 | 2021-11-23 | General Electric Company | Involute trapped vortex combustor assembly |
JP7270428B2 (ja) | 2019-03-19 | 2023-05-10 | 三菱重工業株式会社 | 一方向凝固物、タービン動翼及び一方向凝固物の補修方法 |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS6195769A (ja) * | 1984-10-17 | 1986-05-14 | Toshiba Corp | 蒸気タ−ビン翼への侵食防止部材の固定方法 |
US4705203A (en) * | 1986-08-04 | 1987-11-10 | United Technologies Corporation | Repair of surface defects in superalloy articles |
US5806751A (en) * | 1996-10-17 | 1998-09-15 | United Technologies Corporation | Method of repairing metallic alloy articles, such as gas turbine engine components |
US6050477A (en) * | 1997-04-08 | 2000-04-18 | Asea Brown Boveri Ag | Method of brazing directionally solidified or monocrystalline components |
EP1258545A1 (de) * | 2001-05-14 | 2002-11-20 | ALSTOM (Switzerland) Ltd | Verfahren zum isothermischen Hartlöten von einkristallinen Gegenständen |
US20040050913A1 (en) * | 2002-01-24 | 2004-03-18 | Siemens Westinghouse Power Corporation | High strength diffusion brazing utilizing nano-powders |
EP1561536A1 (de) * | 2004-02-03 | 2005-08-10 | Siemens Aktiengesellschaft | Reparatur-Lotverfahren zum Reparieren eines Bauteils, welches ein Basismaterial mit einer gerichteten Mikrostruktur umfasst |
Family Cites Families (45)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4222794A (en) * | 1979-07-02 | 1980-09-16 | United Technologies Corporation | Single crystal nickel superalloy |
US4448618A (en) * | 1983-02-28 | 1984-05-15 | Allied Corporation | Nickel based brazing filler metals |
US4900394A (en) * | 1985-08-22 | 1990-02-13 | Inco Alloys International, Inc. | Process for producing single crystals |
US4830934A (en) * | 1987-06-01 | 1989-05-16 | General Electric Company | Alloy powder mixture for treating alloys |
US4878953A (en) * | 1988-01-13 | 1989-11-07 | Metallurgical Industries, Inc. | Method of refurbishing cast gas turbine engine components and refurbished component |
US5165463A (en) * | 1988-11-10 | 1992-11-24 | Lanxide Technology Company, Lp | Directional solidification of metal matrix composites |
US4987736A (en) * | 1988-12-14 | 1991-01-29 | General Electric Company | Lightweight gas turbine engine frame with free-floating heat shield |
DE3926479A1 (de) | 1989-08-10 | 1991-02-14 | Siemens Ag | Rheniumhaltige schutzbeschichtung, mit grosser korrosions- und/oder oxidationsbestaendigkeit |
WO1991002108A1 (de) | 1989-08-10 | 1991-02-21 | Siemens Aktiengesellschaft | Hochtemperaturfeste korrosionsschutzbeschichtung, insbesondere für gasturbinenbauteile |
US5206213A (en) * | 1990-03-23 | 1993-04-27 | International Business Machines Corp. | Method of preparing oriented, polycrystalline superconducting ceramic oxides |
US5240491A (en) * | 1991-07-08 | 1993-08-31 | General Electric Company | Alloy powder mixture for brazing of superalloy articles |
JP3073616B2 (ja) | 1992-12-24 | 2000-08-07 | キヤノン株式会社 | マルチプローブを具備する情報処理装置 |
EP0631832B1 (de) | 1993-07-02 | 1998-05-20 | ALD Vacuum Technologies GmbH | Verfahren zum gerichteten Erstarren einer Metallschmelze und Giessvorrichtung zu seiner Durchführung |
US5783318A (en) * | 1994-06-22 | 1998-07-21 | United Technologies Corporation | Repaired nickel based superalloy |
UA39902C2 (uk) | 1994-08-08 | 2001-07-16 | Сіменс Акцієнгезельшафт | Спосіб та пристрій для спрямованого твердіння розплаву |
EP0786017B1 (de) | 1994-10-14 | 1999-03-24 | Siemens Aktiengesellschaft | Schutzschicht zum schutz eines bauteils gegen korrosion, oxidation und thermische überbeanspruchung sowie verfahren zu ihrer herstellung |
US5561827A (en) * | 1994-12-28 | 1996-10-01 | General Electric Company | Coated nickel-base superalloy article and powder and method useful in its preparation |
US5523170A (en) * | 1994-12-28 | 1996-06-04 | General Electric Company | Repaired article and material and method for making |
US5666643A (en) * | 1995-02-23 | 1997-09-09 | General Electric Company | High temperature braze material |
US5664616A (en) * | 1996-02-29 | 1997-09-09 | Caterpillar Inc. | Process for pressure infiltration casting and fusion bonding of a metal matrix composite component in a metallic article |
WO1998005450A1 (de) | 1996-08-06 | 1998-02-12 | Siemens Aktiengesellschaft | Verfahren und einrichtung zur gerichteten erstarrung einer schmelze |
DE19647313A1 (de) | 1996-11-13 | 1998-05-14 | Siemens Ag | Verfahren und Vorrichtung zum gerichteten Erstarren einer Schmelze |
US5873703A (en) * | 1997-01-22 | 1999-02-23 | General Electric Company | Repair of gamma titanium aluminide articles |
EP0892090B1 (de) | 1997-02-24 | 2008-04-23 | Sulzer Innotec Ag | Verfahren zum Herstellen von einkristallinen Strukturen |
EP0861927A1 (de) * | 1997-02-24 | 1998-09-02 | Sulzer Innotec Ag | Verfahren zum Herstellen von einkristallinen Strukturen |
CN2296989Y (zh) | 1997-06-06 | 1998-11-11 | 上虞市华通汽车配件厂 | 扰流器 |
EP1306454B1 (de) | 2001-10-24 | 2004-10-06 | Siemens Aktiengesellschaft | Rhenium enthaltende Schutzschicht zum Schutz eines Bauteils gegen Korrosion und Oxidation bei hohen Temperaturen |
WO1999067435A1 (en) | 1998-06-23 | 1999-12-29 | Siemens Aktiengesellschaft | Directionally solidified casting with improved transverse stress rupture strength |
US6331361B1 (en) * | 1998-11-19 | 2001-12-18 | Hickham Industries, Inc. | Methods for manufacture and repair and resulting components with directionally solidified or single crystal materials |
US6231692B1 (en) | 1999-01-28 | 2001-05-15 | Howmet Research Corporation | Nickel base superalloy with improved machinability and method of making thereof |
US6283356B1 (en) * | 1999-05-28 | 2001-09-04 | General Electric Company | Repair of a recess in an article surface |
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 |
JP2001089258A (ja) * | 1999-09-21 | 2001-04-03 | Kurimoto Ltd | 接合部材及びこれを用いたアルミナセラミックス−ステンレス鋼接合体 |
US6491207B1 (en) | 1999-12-10 | 2002-12-10 | General Electric Company | Weld repair of directionally solidified articles |
GC0000233A (en) * | 2000-08-07 | 2006-03-29 | Exxonmobil Upstream Res Co | Weld metals with superior low temperature toughness for joining high strength, low alloy steels |
US6454885B1 (en) * | 2000-12-15 | 2002-09-24 | Rolls-Royce Corporation | Nickel diffusion braze alloy and method for repair of superalloys |
US6495793B2 (en) * | 2001-04-12 | 2002-12-17 | General Electric Company | Laser repair method for nickel base superalloys with high gamma prime content |
US6503349B2 (en) * | 2001-05-15 | 2003-01-07 | United Technologies Corporation | Repair of single crystal nickel based superalloy article |
DE50112339D1 (de) | 2001-12-13 | 2007-05-24 | Siemens Ag | Hochtemperaturbeständiges Bauteil aus einkristalliner oder polykristalliner Nickel-Basis-Superlegierung |
EP1340567A1 (de) | 2002-02-27 | 2003-09-03 | ALSTOM (Switzerland) Ltd | Verfahren zum Entfernen von Gussfehlern |
WO2003087439A1 (de) | 2002-04-15 | 2003-10-23 | Siemens Aktiengesellschaft | Verfahren zum herstellen von einkristallinen strukturen |
DE60220930T2 (de) * | 2002-11-29 | 2008-03-13 | Alstom Technology Ltd. | Verfahren zur Herstellung, Modifizierung oder Reparatur von einkristallinen oder gerichtet erstarrten Körpern |
EP1437426A1 (de) | 2003-01-10 | 2004-07-14 | Siemens Aktiengesellschaft | Verfahren zum Herstellen von einkristallinen Strukturen |
JP2005000940A (ja) * | 2003-06-10 | 2005-01-06 | Toshiba Corp | 多層積層型ろう材およびろう付補修方法 |
US7051435B1 (en) * | 2003-06-13 | 2006-05-30 | General Electric Company | Process for repairing turbine components |
-
2005
- 2005-07-22 CN CN200580051135XA patent/CN101272880B/zh not_active Expired - Fee Related
- 2005-07-22 JP JP2008521807A patent/JP2009502503A/ja active Pending
- 2005-07-22 EP EP05774084A patent/EP1910006B1/de not_active Not-in-force
- 2005-07-22 US US11/989,214 patent/US8141769B2/en not_active Expired - Fee Related
- 2005-07-22 WO PCT/EP2005/008038 patent/WO2007012338A1/de active Application Filing
- 2005-07-22 AT AT05774084T patent/ATE537928T1/de active
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS6195769A (ja) * | 1984-10-17 | 1986-05-14 | Toshiba Corp | 蒸気タ−ビン翼への侵食防止部材の固定方法 |
US4705203A (en) * | 1986-08-04 | 1987-11-10 | United Technologies Corporation | Repair of surface defects in superalloy articles |
US5806751A (en) * | 1996-10-17 | 1998-09-15 | United Technologies Corporation | Method of repairing metallic alloy articles, such as gas turbine engine components |
US6050477A (en) * | 1997-04-08 | 2000-04-18 | Asea Brown Boveri Ag | Method of brazing directionally solidified or monocrystalline components |
EP1258545A1 (de) * | 2001-05-14 | 2002-11-20 | ALSTOM (Switzerland) Ltd | Verfahren zum isothermischen Hartlöten von einkristallinen Gegenständen |
US20040050913A1 (en) * | 2002-01-24 | 2004-03-18 | Siemens Westinghouse Power Corporation | High strength diffusion brazing utilizing nano-powders |
EP1561536A1 (de) * | 2004-02-03 | 2005-08-10 | Siemens Aktiengesellschaft | Reparatur-Lotverfahren zum Reparieren eines Bauteils, welches ein Basismaterial mit einer gerichteten Mikrostruktur umfasst |
Non-Patent Citations (1)
Title |
---|
PATENT ABSTRACTS OF JAPAN vol. 010, no. 273 (M - 518) 17 September 1986 (1986-09-17) * |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2906172A1 (fr) * | 2006-09-22 | 2008-03-28 | Snecma Services Sa | Procede de retouche locale par brasage induction |
EP1930116A2 (de) | 2006-12-07 | 2008-06-11 | Turbine Overhaul Services Private Limited | Verfahren zum Diffusionslöten mit Nanopartikellegierungen |
EP1930116A3 (de) * | 2006-12-07 | 2010-06-23 | Turbine Overhaul Services Private Limited | Verfahren zum Diffusionslöten mit Nanopartikellegierungen |
US8119948B2 (en) * | 2007-10-05 | 2012-02-21 | Snecma | Method of retouching metal parts |
CN101559538B (zh) * | 2007-10-05 | 2013-09-11 | 斯奈克玛 | 通过高温钎焊连接的金属件的修整方法 |
EP2078579A1 (de) * | 2008-01-10 | 2009-07-15 | Siemens Aktiengesellschaft | Verfahren zum Löten eines Bauteils und Bauteil mit Löt- und Schweissstellen |
EP2226149A1 (de) * | 2009-03-04 | 2010-09-08 | Siemens Aktiengesellschaft | Zweischritt-Schweissverfahren |
CN111151834A (zh) * | 2019-12-26 | 2020-05-15 | 浙江大学 | 真空钎焊铝制板翅式换热器芯体局部外漏的钎焊修复方法 |
Also Published As
Publication number | Publication date |
---|---|
CN101272880A (zh) | 2008-09-24 |
ATE537928T1 (de) | 2012-01-15 |
CN101272880B (zh) | 2012-03-21 |
US20100000976A1 (en) | 2010-01-07 |
EP1910006B1 (de) | 2011-12-21 |
US8141769B2 (en) | 2012-03-27 |
JP2009502503A (ja) | 2009-01-29 |
EP1910006A1 (de) | 2008-04-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1910006B1 (de) | Verfahren zum reparieren eines mit einer gerichteten mikrostruktur umfassenden bauteils, durch einstellung während der elektron- oder der laser-wärmeeinwirkung eines temperaturgradient | |
EP1954844B1 (de) | Verfahren zum reparieren von rissen in bauteilen und lotmaterial zum löten von bauteilen | |
EP1759806B1 (de) | Verfahren zur Reparatur eines Risses mittels Hartlöten | |
EP1957685B1 (de) | Verfahren zum reparieren von rissen in bauteilen | |
EP2317078B2 (de) | Abrasive einkristalline Turbinenschaufel | |
EP2295195B1 (de) | Verfahren zur Herstellung eines Lochs | |
EP1772228A1 (de) | Verfahren zum Reparieren eines Bauteils mit einer gerichteten Mikrostruktur | |
EP2322313A1 (de) | Verfahren zum Schweissen von Werkstücken aus hochwarmfesten Superlegierungen mit besonderer Massenzufuhrrate des Schweisszusatzwerkstoffes | |
EP1711298A1 (de) | Reparatur-lotverfahren zum reparieren eines bauteils, welches ein basismaterial mit einer gerichteten mikrostruktur umfasst | |
EP2311597A1 (de) | Verfahren und Vorrichtung zum Schweißen von Werkstücken aus hochwarmfesten Superlegierungen mit Steuerung mancher Schweissparameter zum Erreichen einer bestimmten Abkühlrate | |
EP1976660A1 (de) | Verfahren zur herstellung eines lochs | |
EP2078579A1 (de) | Verfahren zum Löten eines Bauteils und Bauteil mit Löt- und Schweissstellen | |
EP1867423A1 (de) | Verfahren zum Reparieren eines Bauteils durch Verlöten eines mit Lot beschichteten Bleches | |
EP2114615A1 (de) | Lotzusammensetzung und hartlötverfahren für superlegierungen | |
EP1645653A1 (de) | Schichtsystem | |
WO2008110427A1 (de) | Bauteil und ein lot | |
EP1816316A1 (de) | Bauteilreparaturverfahren | |
WO2006040221A1 (de) | Verfahren zur herstellung eines schichtsystems | |
WO2008087084A1 (de) | Pulvermischung mit blockigem pulver, verfahren zur verwendung der pulvermischung und bauteile | |
WO2009100794A1 (de) | Verfahren zum aufschmelzen von gekrümmten oberflächen und eine vorrichtung | |
EP1808251B1 (de) | Verfahren zum Überarbeiten von verschlissenen Erodierelektroden und zum erosiven Bearbeiten eines Werkstückes | |
EP1930115A1 (de) | Draht, Verwendung eines Drahts und ein Verfahren zum Schweissen | |
WO2007144217A1 (de) | Verfahren zum aufbringen von material auf ein bauteil | |
EP1645660A1 (de) | Schichtsystem |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
DPE2 | Request for preliminary examination filed before expiration of 19th month from priority date (pct application filed from 20040101) | ||
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
WWE | Wipo information: entry into national phase |
Ref document number: 2005774084 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 240/KOLNP/2008 Country of ref document: IN |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2008521807 Country of ref document: JP |
|
WWE | Wipo information: entry into national phase |
Ref document number: MX/a/2008/001047 Country of ref document: MX Ref document number: 200580051135.X Country of ref document: CN |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWW | Wipo information: withdrawn in national office |
Ref document number: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 1020087003673 Country of ref document: KR |
|
WWP | Wipo information: published in national office |
Ref document number: 2005774084 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 11989214 Country of ref document: US |