WO2016139089A1 - Procédé de reconditionnement d'un composant par traitement thermomécanique local - Google Patents

Procédé de reconditionnement d'un composant par traitement thermomécanique local Download PDF

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Publication number
WO2016139089A1
WO2016139089A1 PCT/EP2016/053814 EP2016053814W WO2016139089A1 WO 2016139089 A1 WO2016139089 A1 WO 2016139089A1 EP 2016053814 W EP2016053814 W EP 2016053814W WO 2016139089 A1 WO2016139089 A1 WO 2016139089A1
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WIPO (PCT)
Prior art keywords
component
microstructure
expansion
local
coarsened
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PCT/EP2016/053814
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German (de)
English (en)
Inventor
Bernd Burbaum
Michael Ott
Original Assignee
Siemens Aktiengesellschaft
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Publication of WO2016139089A1 publication Critical patent/WO2016139089A1/fr

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Classifications

    • 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
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/34—Methods of 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
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/0006—Working by laser beam, e.g. welding, cutting or boring 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
    • B23K26/12—Working by laser beam, e.g. welding, cutting or boring in a special atmosphere, e.g. in an enclosure
    • B23K26/1224—Working by laser beam, e.g. welding, cutting or boring in a special atmosphere, e.g. in an enclosure in vacuum
    • 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
    • B23K26/12—Working by laser beam, e.g. welding, cutting or boring in a special atmosphere, e.g. in an enclosure
    • B23K26/123—Working by laser beam, e.g. welding, cutting or boring in a special atmosphere, e.g. in an enclosure in an atmosphere of particular gases
    • 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
    • B23K26/12—Working by laser beam, e.g. welding, cutting or boring in a special atmosphere, e.g. in an enclosure
    • B23K26/127—Working by laser beam, e.g. welding, cutting or boring in a special atmosphere, e.g. in an enclosure in an enclosure
    • 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
    • B23K26/352—Working by laser beam, e.g. welding, cutting or boring for surface treatment
    • 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
    • B23K26/60—Preliminary treatment
    • 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
    • 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
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/34—Methods of heating
    • C21D1/38—Heating by cathodic discharges
    • 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
    • C21D7/00—Modifying the physical properties of iron or steel by deformation
    • C21D7/13—Modifying the physical properties of iron or steel by deformation by hot working
    • 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
    • C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C30—CRYSTAL GROWTH
    • C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B29/00—Single crystals or homogeneous polycrystalline material with defined structure characterised by the material or by their shape
    • C30B29/10—Inorganic compounds or compositions
    • C30B29/52—Alloys
    • C—CHEMISTRY; METALLURGY
    • C30—CRYSTAL GROWTH
    • C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B33/00—After-treatment of single crystals or homogeneous polycrystalline material with defined structure
    • C30B33/02—Heat treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • 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
    • 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
    • C21D2201/00—Treatment for obtaining particular effects
    • C21D2201/04—Single or very large crystals
    • 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
    • C21D2201/00—Treatment for obtaining particular effects
    • C21D2201/05—Grain orientation
    • 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
    • C21D2221/00—Treating localised areas of an article
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/605—Crystalline

Definitions

  • the present invention relates to a method for reprocessing (also called “Refurbishment”) made available by ready for operation ⁇ dingt locally damaged components by means of the local thermomechanical treatment.
  • the damaged components may in particular be made of single-crystal turbine blades superalloys.
  • raffolding It becomes more complex and depends on the direction and type of stress, which is also referred to as "raffolding .” These microstructural changes can be disadvantageous, in particular for the creep behavior of the component .
  • insulating coatings are used for this purpose, but in operation these coatings may be damaged or, for other reasons, they may locally exceed the temperatures required for rafting lead local rafting.
  • a method for recycling a locally locally damaged component with an originally cubic ⁇ / ⁇ 'microstructure, wherein the operational local damage consists in a coarsening of the ⁇ / ⁇ ' microstructure directed along an expansion direction is provided.
  • the Expansion direction of the directionally coarsened ⁇ / ⁇ 'microstructure by local heating and introducing a tensile and compressive stress, in particular in the region of a local damage of the component, rotated in their orientation.
  • the method according to the invention makes it possible to rotate the coarsened microstructures (so-called rafting or rafts) in components with an originally cubic ⁇ / ⁇ 'microstructure in the course of a reprocessing in a desired direction of expansion.
  • the orientation of the rafts loading relative to the direction of the dominant local operating voltage influences the strength properties of a component, particularly at high temperatures, so that with the help of the OF INVENTION ⁇ to the invention process, the strength properties of the local damage can be selectively adjusted in the loading rich during a regeneration ,
  • tensile stresses can be applied to the component in a pressure and / or transverse direction to the desired direction of expansion of the coarsened ⁇ / ⁇ ' microstructure. AfterACTi ⁇ gen state of research, this leads to the desired orientation of the rafts.
  • the expansion direction of the rafts which is sought in the course of the recycling process can, in particular, run at right angles to the direction of expansion of the ⁇ / ⁇ 'microstructure, which has been coarsened due to local damage.
  • the expansion direction of the directionally coarsened ⁇ / ⁇ 'microstructure from the operation is primarily dependent on whether tensile or compressive stresses predominate during operation. Compressive stresses, according to the current state of research, cause rafts parallel to the main stress direction, tensile stresses perpendicular to the principal stress direction. Depending on the mechanical and thermal load during operation and the alloy used, rafts may be advantageous in parallel or at right angles to the principal stress direction. With the method according to the invention can the appropriate extension direction of the rafts can be set for the application.
  • the tensile or compressive stress applied for aligning the rafts can be adjusted specifically to a specific value in the method according to the invention. This can be controlled by means of a suitable measuring device, for example by means of strain gauges. This makes it possible to ensure that sufficiently high voltages are present at the damaged area for carrying out the method without burdening the component as a whole more than necessary.
  • the direction of expansion of the coarsened ⁇ / ⁇ 'microstructure can be determined. This can be done with a metallurgical investigation. From this, conclusions can be drawn about the local stresses and temperatures during operation. This supports the choice of the desired expansion direction of the
  • the entire component during local heating in the area of damage and the simultaneous application of tensile or compressive stresses can be heated to at least 500 ° C.
  • the local heating in the region of the damage then takes place at a temperature which is at least 150 ° C., preferably 200 ° C., in particular even 250 ° C. above the temperature to which the entire component is heated.
  • the entire component during local heating in the region of damage and the simultaneous application of tensile or compressive stresses to a temperature in the range of 650 ° C to 750 ° C, in particular 700 ° C is heated.
  • the area of damage is then heated to a temperature between 900 ° C and 1000 ° C, in particular 950 ° C.
  • the local heating of the damaged areas by means of a laser ⁇ SUC gene in the context of the inventive method.
  • the heat input can be defined locally accurately. Since the energy can also be introduced by a laser in a very short time, heat loss through heat conduction in the component is minimized and the total energy input is low compared to other methods.
  • the treated component by a protective gas atmosphere can be or are located in a vacuum to avoid oxidation give ⁇ .
  • FIG. 1 shows by way of example a gas turbine in FIG.
  • FIG. 2 shows a perspective view of a
  • FIG. 3 shows a combustion chamber of a gas turbine.
  • FIG. 4 shows a method according to the invention
  • FIGS. 5 and 6 show the change of the ⁇ / ⁇ '-microstructure as a function of the applied voltage.
  • FIG. 7 shows the sequence of the invention
  • 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
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings . As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • Coupled to the rotor 103 is a generator or work machine (not shown).
  • air 135 is sucked by the compressor 105 through the intake housing and ver ⁇ seals.
  • the 105 ⁇ be compressed air provided at the turbine end of the compressor is overall to the burners 107 leads and mixed there with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
  • substrates of the components can have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • SX structure monocrystalline
  • DS structure longitudinal grains
  • iron-, nickel- or cobalt-based superalloys are used. Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
  • blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one member of the group
  • X is an active element and stands for yttrium (Y) and / or silicon, scandium (Sc) 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.
  • a thermal barrier coating On the MCrAlX may still be present a thermal barrier coating, and consists for example of Zr0 2 , Y2Ü3-Zr02, ie 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), 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 faces the rotor 103 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 following one another, a fastening region 400, a blade platform 403 adjoining thereto, and an airfoil 406 and a blade tip 415.
  • the vane 130 may be pointed on its shovel 415 have a further platform (not Darge ⁇ asserted).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is, for example, as a hammerhead out staltet ⁇ .
  • Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the blade 406.
  • 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 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 single-crystal structure or structures are used as components for machines which are exposed during operation ho ⁇ hen mechanical, thermal and / or chemical stresses.
  • directionally solidified microstructures which means both single crystals that have no grain boundaries or at most small angle grain boundaries, and stem crystal structures that have probably longitudinal grain boundaries but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified structures.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. B. (MCrAlX; M is at least one element of the group consisting of iron (Fe), cobalt (Co), Ni ⁇ ckel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element the rare earth, or hafnium (Hf)).
  • M is at least one element of the group consisting of iron (Fe), cobalt (Co), Ni ⁇ ckel (Ni)
  • X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element the rare 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.
  • the density is preferably 95% of the theoretical
  • the layer composition comprises Co-30Ni-28Cr-8A1-0, 6Y-0, 7Si or Co-28Ni-24Cr-10Al-0, 6Y.
  • nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-IIAl-O, 4Y-2Re or Ni-25Co-17Cr-10A1-0, 4Y-1 are also preferably used , 5Re.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of Zr0 2 , Y2Ü3-Zr02, ie it is not, partially or completely stabilized by yttria
  • the thermal barrier coating covers the entire MCrAlX layer.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the heat insulating layer can comprise porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the
  • the blade 120, 130 may have to be freed from 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 a plurality of in the circumferential direction about an axis of rotation 102 arranged burners 107 open into a common combustion chamber space 154 and generate flames 156th
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
  • a relatively long service life surfaces to enable the combustion chamber wall 153 is provided on its side facing the working medium M facing side with a formed from heat shield elements 155. liner.
  • Each heat shield element 155 is made of an alloy
  • 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 Si ⁇ lizium and / or at least one element of rare earth, 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 Si ⁇ lizium and / or at least one element of rare 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.
  • a ceramic Wär ⁇ medämm harsh be present and consists for example of ZrÜ2, Y203-ZrÜ2, ie it is not, partially or fully ⁇ dig stabilized by yttrium and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the heat insulation layer may have ⁇ porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
  • Reprocessing means that heat shield elements may need to be removed 155 after use of protective layers (for example by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, cracks in the heat shield element 155 are also repaired. After ⁇ re-coating of the heat shield elements 155 and a renewed use of the heat shield elements 155. Due to the high temperatures inside the combustion chamber
  • 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 cooling holes (not shown) which open into the combustion chamber space 154.
  • FIG. 4 shows the reprocessing of a turbine blade with auxiliary means used by way of example.
  • Figures 5 and 6 show the change of the ⁇ / ⁇ 'microstructure in the material of a component of relevant material depending on introduced Tensions.
  • FIG. 7 shows a flow chart of the process according to the invention.
  • Figure 4 shows an application of the process according to the invention to a turbine blade, the application is possible to other components made of alloys having a ⁇ / ⁇ '-Mikro ⁇ structure.
  • FIGS. 5 and 6 show, by way of example, the orientation of ⁇ / ⁇ 'microstructures 600 in superalloys as a function of stresses 601 and 602 introduced into the material.
  • Such superalloys initially exhibit homogeneous cubic ⁇ / ⁇ ' microstructures when appropriately fabricated. From science is known that under simultaneous influence of mechanical tensile stresses 601 or compressive stresses 602 and heat the ⁇ / ⁇ 'microstructure may coarsen into a defined Ausdeh ⁇ voltage device (rafts) when temperature and / or voltage limits are exceeded. The numerical values of these limits depend on the alloy material and influence each other.
  • the rafts form parallel to the main stress direction when a compressive stress 602 is present and at right angles to the main stress direction when a tensile stress 601 is present.
  • Rafts create a spatially inhomogeneous behavior of the material.
  • the orientation of the ridges relative to the principal stress direction determines the strength and sometimes even the stiffness properties of the material and thus of the corresponding component. These influences are especially pronounced at high temperatures. Whether rafts are advantageous at right angles to the main stress direction or parallel to the main stress direction is different for the respective application, depending on the superalloy used and load case, and must be assessed for the individual case.
  • Rafts During the operation of components, depending on the thermal and mechanical stress, it may be local to the formation of Rafts come.
  • the orientation depends on the local loads from operating loads. Depending on the orientation, the rafts can have negative effects on the load capacity of the component. The component is damaged in operation due to unfavorable alignment of operational rafts.
  • FIG. 4 shows an exemplary application of the method.
  • a damaged by operational conditional rafting turbines ⁇ blade 120 provides the component by way of example used for application of the method is such a turbine ⁇ shovel 120 comprises as described above, a blade root 183, trailing edge 412, leading edge 406 and blade 406 can In operation, in particular the parts leading edge. 406 and blade 406 are damaged. Such damage results, for example, from damage to a heat-insulating layer applied to the turbine blade 120. This can inter alia by penetrated into the gas turbine
  • the turbine blade is 120 angeord ⁇ net in a process chamber 506th
  • the process chamber 506 serves to be able to carry out the process under a protective atmosphere.
  • the protective atmosphere can consist of a protective gas or can be realized by a technical vacuum.
  • the protective atmosphere serves to protect the component to which the method according to the invention is to be applied from oxidation. By suitably selecting the protective atmosphere, it is also possible to avoid or promote scattering of the laser light or to selectively influence reactions in the process zone 500.
  • the process chamber 506 also comprises a heating device for the treated component, in the ⁇ sem example a turbine blade 120.
  • the Schuellrich ⁇ processing is used to heat the component to be treated integrated ⁇ Lich to a base temperature which may for example be 700 ° C .
  • This base temperature is to choose bactersge ⁇ Gurss so that it has no undesirable effects on the properties of the treated component. For example, properties produced by targeted strain hardening should not be compromised. Accordingly, the choice of base temperature depends inter alia on the material of the turbine blade 120. On the other hand, the base ⁇ temperature should be chosen as high as without unwanted side effects possible in order to keep thermal stresses in the transition to processing zone 500 and the requirements for the laser 501 possible liehst low.
  • the process zone 500 describes the batch of the turbine blade 120 that corresponds to the operational localized damage zone and in which the method of the present invention is applied To realign the rafts.
  • the process zone 500 is heated by a laser 501 to a process temperature that allows realignment of the rafts.
  • ⁇ instead of a laser 501 other heat sources can be settik- that enable localized, well-controlled heat input.
  • the process temperature is 120 depen ⁇ gig on the used material of the turbine blade and can be for example 950 ° C.
  • Realigning the rafts are generated as part of the application of the inventive method in addition to a process tempera ture ⁇ at the same time also mechanical stresses in sufficient level in the process zone 500th This can be achieved by clamping the turbine blade 120 505 and applying tensile and / or compressive forces 503 as well as bending and / or torsional moments 504.
  • the state of stress in the process zone 500 can be monitored.
  • the sensor 502 may be the case ⁇ play a strain gauge (DMS).
  • DMS strain gauge
  • the sensor 502 is moved according to ensure that 500 mechanical stresses sufficient amount present in the process ⁇ area for the realignment of rafts and in the required direction to achieve the desired Raftausdehnungsraum.
  • the load on the turbine blade 120 can be minimized by monitoring the voltage levels ⁇ by the sensor 502, since only the necessary forces and moments 503 504 to ensure a sufficiently high voltage level in the process zone to be initiated.
  • the ⁇ / ⁇ 'microstructure of a locally damaged component due to operational conditions can be aligned in such a way that the mechanical load capacity can be advantageously improved compared to a defined load compared to the initial state.
  • the method according to the invention brings by operation damaged blades again in operational condition and thus lowers the operating costs of gas turbines advantageous.
  • FIG. 7 shows the possible sequence of an application of the method according to the invention during the refurbishment of a component, for example a gas turbine blade.
  • a raft analysis First, the existing orientation of the rafts is determined (A), for example by metallurgical investigation. Said Koen ⁇ nen damaged, among other areas are determined. At ⁇ support points for possible damaged areas can be ⁇ game also obtained from damage to a thermal insulation lations Mrs.
  • step C it is to be determined which extension directions of the rafts are advantageous for the local stress during operation. From this, the mechanical stresses to be introduced into the process zone 500 are derived.
  • a sensor 502 for monitoring the state of stress is attached near the process zone 500 on the component to be treated. These include access to the process zone 500 and to observe the temperature resistance of the sensor.
  • the component is mounted on a holder in the process chamber 506, connected to means for imposing forces and moments (503, 504, 505) and heated to the base temperature of, for example, 700 ° C.
  • process step F forces and moments (503, 504, 505) are impressed onto the component in such a way that the desired stress state is established in the process zone, which is necessary for reorienting the rafts.
  • This can be controlled by means of the sensor 502.
  • This process step can be carried out parallel to the local heat input G, so that any changes of the tension can ⁇ voltage state are compensated from the heat input. It is ensured according to the method that during the local heat input G sufficient stresses in the process zone 500 are present.
  • the processing zone 500 is heated, for example by means of a La ⁇ sers 501 to a process temperature of for example 950 ° C.
  • the rafts set in an advantageously chosen direction and improve so the mechanical properties of the treated component.
  • the inventive method is particularly suitable for the reprocessing of locally damaged components originally cubic ⁇ / ⁇ 'microstructures.
  • Such components may, in particular, be turbine blades which are impaired by local directed coarsening of the ⁇ / ⁇ 'microstructure in terms of their capacity to withstand operating stresses.
  • the inventive method the off ⁇ stretching direction of the ⁇ / ⁇ 'microstructure can be rotated in an advantageous direction.
  • the process zone 500 is locally heated, while at the same time tensile and / or compressive stresses are introduced in such a way that advantageously aligned coarsening of the microstructure is formed.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Plasma & Fusion (AREA)
  • Optics & Photonics (AREA)
  • Thermal Sciences (AREA)
  • Inorganic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé de reconditionnement d'un composant (120) abimé localement du fait de son utilisation, présentant une microstructure γ/γ' initialement cubique, les dommages locaux subis du fait de l'utilisation se présentant sous la forme d'une microstructure γ/γ' rendue plus grossière dans la direction d'extension. Selon le procédé, la direction d'extension de la microstructure γ/γ' rendue plus grossière de façon dirigée est tournée dans son orientation par chauffe locale et application d'une contrainte de traction ou de compression (503, 505), notamment dans la zone des dommages locaux du composant.
PCT/EP2016/053814 2015-03-05 2016-02-24 Procédé de reconditionnement d'un composant par traitement thermomécanique local WO2016139089A1 (fr)

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DE102015203985.4 2015-03-05
DE102015203985.4A DE102015203985A1 (de) 2015-03-05 2015-03-05 Verfahren zur Wiederaufbereitung eines Bauteils mittels lokaler thermomechanischer Behandlung

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CN113008694A (zh) * 2021-02-01 2021-06-22 中国航发沈阳发动机研究所 基于错配度的镍基高温合金涡轮叶片服役损伤评价方法
CN115074819A (zh) * 2021-03-11 2022-09-20 隆基绿能科技股份有限公司 一种热场部件返修判断方法、处理方法、装置以及系统

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113008694A (zh) * 2021-02-01 2021-06-22 中国航发沈阳发动机研究所 基于错配度的镍基高温合金涡轮叶片服役损伤评价方法
CN113008694B (zh) * 2021-02-01 2023-12-15 中国航发沈阳发动机研究所 基于错配度的镍基高温合金涡轮叶片服役损伤评价方法
CN115074819A (zh) * 2021-03-11 2022-09-20 隆基绿能科技股份有限公司 一种热场部件返修判断方法、处理方法、装置以及系统
CN115074819B (zh) * 2021-03-11 2023-08-01 隆基绿能科技股份有限公司 一种热场部件返修判断方法、处理方法、装置以及系统

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