EP2498947A1 - Procédé de soudage de pièces en superalliages résistants aux températures élevées avec un débit massique d'apport de métal particulier - Google Patents
Procédé de soudage de pièces en superalliages résistants aux températures élevées avec un débit massique d'apport de métal particulierInfo
- Publication number
- EP2498947A1 EP2498947A1 EP10776679A EP10776679A EP2498947A1 EP 2498947 A1 EP2498947 A1 EP 2498947A1 EP 10776679 A EP10776679 A EP 10776679A EP 10776679 A EP10776679 A EP 10776679A EP 2498947 A1 EP2498947 A1 EP 2498947A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- welding
- zone
- heat
- heat input
- layer
- 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- Withdrawn
Links
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B7/00—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas
- B05B7/16—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating or cooling the material to be sprayed
- B05B7/22—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating or cooling the material to be sprayed electrically, magnetically or electromagnetically, e.g. by arc
- B05B7/228—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating or cooling the material to be sprayed electrically, magnetically or electromagnetically, e.g. by arc using electromagnetic radiation, e.g. laser
-
- 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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/32—Bonding taking account of the properties of the material involved
-
- 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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/34—Laser welding for purposes other than joining
-
- 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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/34—Laser welding for purposes other than joining
- B23K26/342—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
- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/001—Interlayers, transition pieces for metallurgical bonding of workpieces
- B23K35/007—Interlayers, transition pieces for metallurgical bonding of workpieces at least one of the workpieces being of copper or another noble metal
-
- 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
- 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
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/50—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for welded joints
-
- 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
- B23K2103/02—Iron or ferrous alloys
-
- 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
- B23K2103/08—Non-ferrous metals or alloys
-
- 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
-
- 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
- B23K2103/50—Inorganic material, e.g. metals, not provided for in B23K2103/02 – B23K2103/26
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/20—Manufacture essentially without removing material
- F05B2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05B2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/30—Manufacture with deposition of material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/80—Repairing, retrofitting or upgrading methods
Definitions
- the present invention relates to a method for
- Gas turbine workpieces for example of gas turbine show ⁇ feln.
- Blades of gas turbines are exposed to high temperatures and heavy mechanical loads during operation.
- nickel-based superalloys are therefore preferably used, which can be strengthened by precipitation of a ⁇ 'phase.
- cracks can occur in the blades that continue to expand over time.
- Such cracks eg due to the extreme mechanical stress during operation of a gas turbine, but they can also already occur during the manufacturing process ⁇ . Since the production of turbine blades and other workpieces from such superalloys is complex and costly, it is endeavored to produce as little waste as possible in the production and to ensure a long life of the products produced.
- gas turbine blades are regularly maintained and replaced if necessary, due to be ⁇ drive-related stress proper functioning can not be readily ensured.
- they are worked up again as far as possible. They can then be used again in a gas turbine.
- a build-up welding in damaged areas may be necessary to restore the original wall thickness.
- Turbine blades that have already cracked during the manufacturing process can, for example, with build-up welding be made ready for use, so that the committee can be reduced in the production.
- a welding process with preceding overaging is described for example in US 6,120,624, a welding process, which is performed on a preheated workpiece, for example in US 5,319,179.
- this method can not be performed on all areas of the workpiece due to lack of accessibility of befindli ⁇ in a protective gas container workpiece.
- an alternative welding method for build-up welding which is suitable in particular for ⁇ '-hardened nickel-based superalloys and does not have the abovementioned disadvantages or only to a reduced extent.
- the object is achieved by a method for build-up welding according to claim 1.
- Embodiments of the invention and can be advantageously combined with each other as desired.
- a Aufbrin- occurs gene of welding material on the workpiece surface by means of a heat transfer zone and a feed zone to ⁇ drove the welding filler material in the heat transfer zone.
- the heat input zone and the feed zone are moved over the workpiece surface during welding. The movement can take place along a welding direction, for example on a linear path or in a path oscillating around the welding direction.
- the mass feed rate according to the invention is -S 350 mg / min.
- the welding ⁇ parameters are selected so that the cooling rate is at least 8000 K / s during the solidification of the material.
- the main parameters available for setting the cooling rate of at least 8000 K / s during the solidification of the material are the process parameters with respect to the welding power and the diameter of the heat input zone, for example in the form of a laser power and a diameter of the laser beam, the feed (the process speed ) and, if necessary, the flow of supplied filler metal.
- the required cooling rate for the material to be welded can be adjusted by suitable adaptation of these parameters.
- the process speed in this case may be at least 250 mm / min, in particular more than 500 mm / min.
- the welding power and the diameter of the heat input zone can at a process speed of more than 500 mm / min, the procedural ⁇ rensparameter respect. Be set so that the cool down ⁇ rate during the solidification of the material is at least 8000 K / s be ⁇ carries.
- the melt in the weld he ⁇ stares dendritic, that is, in a tree-like structure, wherein the growth directions of the dendrites along the welding track vary as the orientation of the possible directions of growth of the dendrites varied to the temperature gradient in the solidification front. That the direction of growth with the ge ⁇ slightest tendency to temperature gradients or with the lowest growth rate prevails.
- bacteria form in front of the solidification front, the currency ⁇ rend caught the solidification of the solidification front ⁇ to. These germs initiate dendrite growth directions that are statistically distributed. .
- the novel process is suitable for example for welding ⁇ SEN of workpieces from a ⁇ '-containing nickel-base super alloy by means of a welding material having a ⁇ ' - is forming nickel-based superalloy material. It can then be a high strength in the weld metal due to the use of similar filler material and an acceptable
- Welding quality ie a very low number of cracks and a very low average crack length can be achieved.
- ⁇ welding method has a high efficiency.
- the method can be designed, in particular, as a build-up welding method in which the deposition of welding filler metal takes place in layers.
- the welding directions of successive layers can be rotated relative to one another, in particular by 90 °.
- Welding direction are moved in a direction about the welding direction oscillating path over the workpiece surface.
- the irregularly distributed dendrite orientation is found mainly in the upper half of the welding track.
- a previously applied layer in less than half of their
- Diameters are very small on average. Grain boundaries generally provide a weak point with respect to the cracking of transient voltages during the welding process or a subsequent heat treatment. Due to the small extension of a grain boundary in the plane and the irregular ⁇ uniform orientation in the welded with the inventive method, the weld, the weld with respect to the cracking insensitive so that the welding process can be performed at room temperature.
- the inventive method can be applied to both polykristalli ⁇ nen as well as directionally solidified or single-crystal substrates.
- a ⁇ '-containing nickel-based superalloy can be used as a welding additive.
- a heat treatment can be carried out on the application of the filler metal . With a matched to the weld heat treatment so the desired ⁇ 'morphology can be adjusted. This serves to further improve the strength of the weld metal.
- a welding device to welding of high temperature superalloys, which is suitable for performing the ER inventive method, comprises a heat ⁇ source for generating a heat input zone on the work ⁇ piece surface, a supply means for supplying welding filler material comprising a heat source and a transmembrane ⁇ port device for Generating a relative movement between the heat input zone and the supply device on the one hand and the workpiece surface on the other.
- the transport device is advantageously connected to the heat source and the feed direction for the filler metal in order to move the heat source and the supply device in order to bring about the relative movement. This is usually less expensive than moving the workpiece.
- a laser can be used as the heat source in the welding device according to the invention.
- the welding device further comprises ⁇ erprogramm a control unit with a tax, which adjusts the welding parameters, that the cooling rate is at least 8000 Kelvin per second during the solidification of the material.
- the Steuerein ⁇ standardize the welding parameters related to.
- the welding performance as well as the diameter of the heat introduction zone set so that the cooling rate is at least 8000 Kelvin per second during the solidification of the material.
- the welding can be carried out here with a process speed of at least 250 mm per minute, in particular with a process speed of more than 500 mm per minute.
- the relative movement can in particular be controlled so that the heat input zone and the feed zone along a
- control unit can perform the relative movement with or without oscillation so that the welding directions are rotated in successive layers against each other, for example. around 90 °.
- Figure 1 shows an example of a gas turbine in a longitudinal ⁇ partial section.
- FIG. 2 shows a turbine blade in a perspective view.
- Figure 3 shows a gas turbine combustor in a partially sectioned perspective view.
- FIG. 4 shows a schematic representation of the welding device according to the invention.
- FIG. 5 shows the welding path for a first layer of welding filler material.
- FIG. 6 shows the welding path for a second layer
- FIG. 1 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
- the annular combustion chamber 110 communicates with an 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.
- the working medium 113 expands in a pulse-transmitting manner, so that the blades 120 drive the rotor 103 and this drives 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.
- the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
- M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
- X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium.
- Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
- a thermal barrier coating On the MCrAlX may still be present a thermal barrier coating, and consists for example of Zr02, Y203-Zr02, ie it is not, partially or completely stabilized by Ytt ⁇ riumoxid and / or calcium oxide and / or magnesium oxide.
- Suitable coating processes such as electron beam evaporation (EB-PVD), produce stalk-shaped grains in the thermal barrier coating.
- EB-PVD electron beam evaporation
- the guide vane 130 has an inner housing 138 of the turbine 108 facing guide vane root (not Darge here provides ⁇ ) and a side opposite the guide-blade root vane root.
- the vane head is the rotor 103 facing and fixed to a mounting ring 140 of the stator 143.
- FIG. 2 shows a perspective view of a rotor blade 120 or guide vane show ⁇ 130 of a turbomachine, which extends along a longitudinal axis of the 121st
- the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
- the blade 120, 130 has along the longitudinal axis 121 to each other, a securing region 400, an adjoining blade or vane platform 403 and a blade 406 and a blade tip 415.
- the 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 on a leading edge 409 and a trailing edge 412th
- blades 120, 130 in all areas 400, 403, 406 of the blade 120, 130, for example, massive metallic materials, in particular superalloys, are used.
- 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 be made by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof. Workpieces with a monocrystalline structure or structures are used as components for machines which are exposed to high mechanical, thermal and / or chemical stresses during operation.
- Such monocrystalline workpieces takes place e.g. by directed solidification from the melt.
- These are casting processes in which the liquid metallic alloy is transformed into a monocrystalline structure, i. to the single-crystal workpiece, or directionally solidified.
- dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, ie grains that run the entire length of the workpiece and here, in common parlance, referred to as directionally solidified) or a monocrystalline structure, ie the whole workpiece be ⁇ is made of a single crystal.
- a columnar grain structure columnar, ie grains that run the entire length of the workpiece and here, in common parlance, referred to as directionally solidified
- a monocrystalline structure ie the whole workpiece be ⁇ is made of a single crystal.
- directionally solidified structures means both single crystals which have no grain boundaries or at most small-angle grain boundaries, as well as columnar crystal structures which are probably grain boundaries running in the longitudinal direction but no transverse grain boundaries. have 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.
- a thermal barrier coating which is preferably the outermost layer, and consists for example of Zr0 2 , Y2Ü3-Zr02, ie it is not, partially ⁇ or fully stabilized by yttria
- the thermal barrier coating covers the entire MCrAlX layer. Suitable coating processes, such as electron beam evaporation (EB-PVD), produce stalk-shaped grains in the thermal barrier coating. Other coating methods are conceivable, for example atmospheric plasma spraying (APS), LPPS, VPS or CVD.
- APS atmospheric plasma spraying
- LPPS LPPS
- VPS VPS
- CVD chemical vapor deposition
- the heat insulation layer may have ⁇ porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
- the thermal barrier coating is therefore preferably more porous than the
- Refurbishment means that components 120, 130 may have to be freed of protective layers after use (eg 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. Thereafter, a ⁇ As the coating of the component 120, 130, after which the component 120, the 130th
- 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 are arranged a plurality of in the circumferential direction about an axis of rotation 102
- Burners 107 open into a common combustion chamber space 154, the flames 156 produce.
- 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 the Häme ⁇ medium M side facing with an inner lining formed of heat shield elements 155.
- 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.
- 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.
- Reprocessing means that heat shield elements 155, after being used, where appropriate, Protective layers must be freed (eg 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 a highly schematic representation of a welding device 1.
- This comprises a laser 3 and a powder feed device 5 with which a powdered welding filler can be applied to the region of a workpiece 9 to be welded.
- a heat input zone 11 is formed on the workpiece surface, in which also the powder 13 is introduced from the powder feed device 5.
- the laser power is between 100W and 300W, and preferably between 100W and 200W, more particularly between 100W and 150W.
- the welding material is melted well and also melted the ground, thus resulting in a tight weld.
- the laser 3 and the powder feeder 5 are arranged on a scanning device 15, which is a displacement of the
- the Process speed is at least 250mm / min
- the scanning device 15 of the present embodiment allows a displacement of the laser 3 and the powder feeder 5 perpendicular to the component surface (z direction in Figure 4). With the aid of the scanning device 15, the heat input zone and the impact zone of the powder can thus be displaced along a predetermined path.
- Scanning device can, for example, find a robotic arm use.
- the diameter of the laser beam is in particular 500 ⁇ to 700 ⁇ , especially 600 ⁇ .
- the supplied welding material can be heated advantageously.
- the control of the movement mediated by the scanning device 15 is effected by a control unit 17, which also controls the other parameters of the welding process.
- the control of other parameters of the welding process but also by an additional control, that is separated from the STEU ⁇ augmentation of the movement sequence take place.
- a movable component holder instead of the scanning device 15 for moving the laser 3 and the powder feed device 5, a movable component holder can also be used. In the context of the invention, only the relative movement between the laser 3 and the powder feeder 5 on the one hand and the workpiece 9 is important.
- the method according to the invention for build-up welding of a workpiece surface can be used for material application, in particular for multilayer material application, on the region 7 of a component 9 to be welded.
- the component 9 does not need to be preheated or over-aged by means of a heat treatment.
- the turbine blade of the present embodiment is made of a ⁇ '-reinforced nickel base superalloy, for example, IN738LC, IN939, Rene80, IN6203DS, PWA1483SX, Alloy 247, etc.
- the area to be welded 7 in the surface 10 of the turbine blade 9 is electrodeposited in layers , wherein the heat input zone to ⁇ together with the impact area for the powder 13 along a welding direction over the area to be welded 7 of the turbine blade 9 are moved.
- the powder 13 in the present case is a powder of a ⁇ '-containing nickel-base superalloy, for example from IN 738LC, IN 939, Rene 80, IN
- FIG. 1 The path PI traveled by the heat input zone 11 and the impact area of the powder 13 during buildup welding of the first layer on the region 7 to be welded is shown schematically in FIG.
- the figure shows the turbine blade 9 with the region to be welded 7 and the welding direction Sl during deposition welding of the first layer 19.
- the laser 3 and the powder feed device 5 are displaced slightly along the z-direction of the scanning device 15.
- the welding direction S2 is rotated by 90 ° with respect to the welding direction S1 for the first layer.
- the path P2 of the heat input zone 11 and the impingement area for the powder 13 during buildup welding of the second layer 21 is shown in FIG. Even when on ⁇ up welding of the second layer 21 11 oscillates the heat input zone together with the impingement of the powder 13 in a direction perpendicular to the welding direction S2. Overall, therefore, a meander-shaped path P2 of the heat input zone 11 and the impact area for the powder 13 results over the region 7 to be welded.
- the tracks (paths) of the 2nd layer can be parallel offset or welded perpendicular to the tracks (paths) of the first layer. All of these variants can be used in the context of the method according to the invention.
- the oscillation can be selected such that the entire area to be welded 7 is swept with a single path along the welding direction, as shown in FIG. 5, or so that only a part of the area to be welded 7 is swept over and for cladding the entire area several adjacent paths P2 in
- Welding direction S2 are traversed, as shown in Figure 6.
- the method of the heat input zone 11 and the Auf Economicsbe ⁇ realm of the powder 13 along the path PI or P2 is performed in the present embodiment with a process con ⁇ speed of at least 500 mm / min.
- the mass feed rate is -S 350 mg / min, preferably
- Remelting depth is indicated by dashed lines in FIG. Basically, other than those in the present
- the growth directions of the dendrites vary along a path PI, P2. The reason for this is that the orientation of the possible growth directions of the dendrites to the temperature gradient varies, with the
- the turbine blade 9 may be a dressedbe ⁇ act are subjected to the leads to the desired ⁇ 'morphology is established. This serves to further improve the strength of the welded portion of the turbine blade 9.
- a build-up welding can take place at room temperature and without prior aging of the component to be welded, the formation of solidification cracks and re-melting cracks being suppressed.
- there is only a very slight influence of the base material since Because of the small heat-affected zone (there is no Vorhei ⁇ zen) and the suppression of reflow cracks in the heat affected zone, only a very low heat input into the substrate occurs.
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- Optics & Photonics (AREA)
- Chemical & Material Sciences (AREA)
- Plasma & Fusion (AREA)
- Materials Engineering (AREA)
- Crystallography & Structural Chemistry (AREA)
- Thermal Sciences (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
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Abstract
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10776679A EP2498947A1 (fr) | 2009-11-13 | 2010-11-10 | Procédé de soudage de pièces en superalliages résistants aux températures élevées avec un débit massique d'apport de métal particulier |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09014234A EP2322313A1 (fr) | 2009-11-13 | 2009-11-13 | Procédé de soudure de pièces usinées en superalliages résistant aux températures avec un débit particulier du matériau d'apport de soudage |
EP10776679A EP2498947A1 (fr) | 2009-11-13 | 2010-11-10 | Procédé de soudage de pièces en superalliages résistants aux températures élevées avec un débit massique d'apport de métal particulier |
PCT/EP2010/067188 WO2011058045A1 (fr) | 2009-11-13 | 2010-11-10 | Procédé de soudage de pièces en superalliages résistants aux températures élevées avec un débit massique d'apport de métal particulier |
Publications (1)
Publication Number | Publication Date |
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EP2498947A1 true EP2498947A1 (fr) | 2012-09-19 |
Family
ID=42102635
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09014234A Ceased EP2322313A1 (fr) | 2009-11-13 | 2009-11-13 | Procédé de soudure de pièces usinées en superalliages résistant aux températures avec un débit particulier du matériau d'apport de soudage |
EP10776679A Withdrawn EP2498947A1 (fr) | 2009-11-13 | 2010-11-10 | Procédé de soudage de pièces en superalliages résistants aux températures élevées avec un débit massique d'apport de métal particulier |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
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EP09014234A Ceased EP2322313A1 (fr) | 2009-11-13 | 2009-11-13 | Procédé de soudure de pièces usinées en superalliages résistant aux températures avec un débit particulier du matériau d'apport de soudage |
Country Status (5)
Country | Link |
---|---|
US (1) | US9035213B2 (fr) |
EP (2) | EP2322313A1 (fr) |
CN (1) | CN102639283B (fr) |
RU (1) | RU2510994C2 (fr) |
WO (1) | WO2011058045A1 (fr) |
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- 2010-11-10 CN CN201080051539.XA patent/CN102639283B/zh not_active Expired - Fee Related
- 2010-11-10 RU RU2012124077/02A patent/RU2510994C2/ru not_active IP Right Cessation
- 2010-11-10 EP EP10776679A patent/EP2498947A1/fr not_active Withdrawn
- 2010-11-10 WO PCT/EP2010/067188 patent/WO2011058045A1/fr active Application Filing
- 2010-11-10 US US13/509,002 patent/US9035213B2/en not_active Expired - Fee Related
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Also Published As
Publication number | Publication date |
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US9035213B2 (en) | 2015-05-19 |
CN102639283B (zh) | 2015-12-09 |
US20120267347A1 (en) | 2012-10-25 |
CN102639283A (zh) | 2012-08-15 |
WO2011058045A1 (fr) | 2011-05-19 |
RU2510994C2 (ru) | 2014-04-10 |
EP2322313A1 (fr) | 2011-05-18 |
RU2012124077A (ru) | 2013-12-20 |
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