US20200216942A1 - Method for repairing monocrystalline materials - Google Patents

Method for repairing monocrystalline materials Download PDF

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US20200216942A1
US20200216942A1 US16/649,994 US201816649994A US2020216942A1 US 20200216942 A1 US20200216942 A1 US 20200216942A1 US 201816649994 A US201816649994 A US 201816649994A US 2020216942 A1 US2020216942 A1 US 2020216942A1
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substrate
monocrystalline
powder
temperature
coating
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Tobias Kalfhaus
Robert Vassen
Olivier Guillon
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Forschungszentrum Juelich GmbH
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Forschungszentrum Juelich GmbH
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Assigned to FORSCHUNGSZENTRUM JUELICH GMBH reassignment FORSCHUNGSZENTRUM JUELICH GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GUILLON, OLIVIER, KALFHAUS, Tobias, VASSEN, ROBERT
Publication of US20200216942A1 publication Critical patent/US20200216942A1/en
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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/137—Spraying in vacuum or in an inert atmosphere
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment

Definitions

  • the invention relates to the field of metals and alloys, and specifically, to the field of nickel alloys.
  • the invention relates in particular to a method for repairing monocrystalline materials which are frequently used for components subjected to high temperatures, for example, the blades of stationary gas turbines or of aircraft turbines.
  • a method is known for example from Kazuhoro et al. HI that can be used to repair a defective turbine blade. In this case, however, there is no epitaxial growth on the monocrystalline substrate, so that as a result a polycrystalline microstructure is produced which regularly does not have the mechanical properties of the original substrate.
  • U.S. Pat. No. 5,732,467 A1 describes a method for repairing cracks in the outside surfaces of components which have a superalloy with a directional microstructure.
  • the method described therein coats and seals the outside surfaces of directionally solidified and monocrystalline structures by coating the defective region using a high velocity oxy-fuel method (also referred to herein as HVOF) followed by hot isostatic pressing of the corresponding component.
  • HVOF high velocity oxy-fuel method
  • HVOF hot isostatic pressing
  • a welding method is also proposed to repair damages to monocrystalline materials that occur, for example, in the blades of gas turbines [3] .
  • LMF laser metal forming
  • laser cladding it is basically possible to produce monocrystalline structures on a monocrystalline substrate. This method is characterized by minimum heat input into the component during construction which prevents further cracks or recrystallization of the monocrystalline material.
  • FIG. 1 illustrates a prior art diagram for CMSX-4® material
  • FIG. 2 schematically shows a solidification model for a method according to an embodiment
  • FIG. 3 illustrates a substrate sample geometry
  • FIG. 4 is a technical drawing illustrating a configuration of a polished sample incorporated into a heated sample holder
  • FIGS. 5 a and 5 b show scanning electron micrographs of transverse grinds of treated samples showing directional solidification on a monocrystalline substrate
  • FIGS. 6 a and 6 b show scanning electron micrographs of transverse grinds of the same samples which, after coating, were first solution annealed and then precipitation annealed.
  • Embodiments described herein provide a repair method for monocrystalline materials, in particular for monocrystalline blades of stationary gas turbines and/or of aircraft turbines where the added material has mostly the same microstructure and crystal orientation as the material to be repaired.
  • epitaxial growth on a monocrystalline material can be generated via the method of vacuum plasma spraying.
  • the material to be repaired typically comprises a metallic alloy, in particular a nickel-based alloy or also a cobalt-based alloy.
  • plasma spraying is understood to mean a coating method which is carried out using a plasma and is not based on plasma polymerization.
  • vacuum plasma spraying is understood to be a coating method which is carried out in a vacuum chamber at a pressure of 1 to 200 mbar in order to avoid oxidation of the coating material by atmospheric oxygen.
  • the same material of which the substrate material is made is used as the coating material. Since the components to be repaired, such as the blades of stationary gas turbines and/or aircraft turbine blades, are generally highly temperature-loaded materials, in particular all metallic high-temperature alloys or superalloys are suitable as coating materials.
  • High-temperature alloys currently include predominantly solid and high-strength nickel-based alloys or cobalt-based alloys.
  • Metallic materials of complex composition iron, nickel, platinum, chromium or cobalt base with the addition of the elements Co, Ni, Fe, Cr, Mo, W, Re, Ru, Ta, Nb, AI, Ti, Mn, Zr, C and B
  • superalloys are mostly scaling-resistant and highly heat-resistant. They can be produced both by a melt metallurgy method and a powder metallurgy method.
  • the polycrystallinity of thermally sprayed metallic layers can be suppressed by spaying an at least similar alloy, such as the monocrystalline substrate material, onto the heated and polished substrate surface at a greatly reduced pressure and in an argon atmosphere.
  • an at least similar alloy such as the monocrystalline substrate material
  • the term “similar” is understood to mean that the proportion of the alloying elements of substrate and layer differ only slightly and that they have a virtually identical microstructure after a heat treatment.
  • a low solidification rate favors the directional monocrystalline growth of the applied material.
  • the rate of solidification within the applied layer regularly decreases as the substrate temperature increases.
  • the temperatures of the substrate are so high that the solidification speed of the molten powder particles is greatly reduced but the melting temperature of the substrate is not reached.
  • Substrate temperatures between 700° C. and temperatures just below the melting temperature of the substrate used, i.e. for example 50° C. below the melting temperature of the substrate, are typically set for this purpose.
  • the solidification speed cannot be exactly measured disadvantageously in this process, but it should preferably be less than 100 mm/s.
  • nucleation does not take place somewhere within the applied layer but advantageously directly at the substrate surface where it aligns itself with the predetermined orientation of the single crystal of the substrate. Epitaxial growth of the applied layer on the substrate is thus possible.
  • the region of the substrate to be repaired is heated by means of a meandering movement of a plasma torch without powder feeding over the surface of the substrate.
  • the entire substrate is heated.
  • the substrate can be heated in various ways: electrically, inductively or by electromagnetic radiation.
  • the entire substrate is advantageously heated to at least 700° C., advantageously to at least 800° C., preferably even to approximately 1100° C.
  • the substrate itself is heated during the application of the thermally sprayed layer, it is not heated up to temperatures at which the substrate would melt.
  • the powder melted in the plasma thus theoretically impinges on a solid, polished substrate surface where it nucleates and can thus advantageously solidify in the same crystal orientation.
  • a melting of the surface of the substrate locally by a few ⁇ m cannot be ruled out, depending on the implementation of the method.
  • This method step is clearly distinguishable from previously known repair methods, such as, for example, welding methods by means of a laser where the substrate itself is frequently also melted at least on the surface to be repaired.
  • a vacuum plasma spraying system with a powder feed system and a device for heating a substrate (component) to temperatures of approximately 700° C. up to 1300° C. are preferably utilized to carry out the method.
  • the area on the component to be repaired should be polished.
  • the repair process of the damaged component generally starts by removing the bonding coat and topcoat of the thermal barrier layer with hydrofluoric acid (also referred to as stripping), provided that they are present on the substrate material.
  • hydrofluoric acid also referred to as stripping
  • the critical damage is identified and regularly removed, ground and polished by a machining method.
  • Grinding can be carried out, for example, with 320, 640, 1200, or 4000 grit sandpaper.
  • the subsequent polishing can be carried out with a diamond suspension on a soft cloth, wherein, for example, first a suspension with diamond particles having an average particle size of approx. 3 ⁇ m and then a suspension with diamond particles having an average particle size of approx. 1 ⁇ m is used.
  • a light microscope is suitable for checking the polished substrate surface.
  • the treated substrate surface should be scratch-free.
  • the undamaged regions of the substrate are masked in a next step.
  • the stripped region can now be reconstructed using a method according to the disclosure.
  • Layer thicknesses of approx. 10 ⁇ m up to several mm can be realized in this case.
  • the layer thickness during single transition/spraying of the plasma torch can be adjusted individually and follows from the robot speed in conjunction with the powder delivery rate.
  • the entire layer thickness is regularly realized by multiple transitions/spraying.
  • the layer thickness will be approximately 25 ⁇ m.
  • the layer can have any thickness depending on the number of transitions. An excessive application rate during single transition should be avoided, however, as this could lead to increased pore formation which would be disadvantageous. Polishing between the individual transitions is not necessary.
  • the application of a plurality of layers is also possible provided that the respective surface is polished between application of the layers. This may be necessary, for example, where a further repair appears necessary after a first repair and examination of a region.
  • the repaired substrate can be polished again and used for another repair.
  • the applied layer is generally very low-stress due to the high application temperature, there is no physical limit to a maximum layer thickness that can be applied by a method according to the present disclosure.
  • a layer thickness range of a few ⁇ m up to approximately 5 mm can be achieved by such a method.
  • a new thermal barrier layer can then be re-applied depending on the requirement, and cooling holes may be re-drilled.
  • Methods according to the disclosure can advantageously offer the possibility of bringing defective and discarded monocrystalline blades into a new state.
  • the temperature to be set is alloy-specific.
  • the additional further heating by plasma jet is necessary to suppress oxidation of the surface.
  • the hydrogen contained in the plasma jet creates reducing conditions.
  • the desired temperatures should be as high as possible, so a temperature of 50 K below the melting temperature is desirable.
  • the temperature difference with the remaining substrate/component should be as low as possible because advantageously the region to be repaired should have as homogeneous a temperature distribution as possible.
  • a high substrate temperature generally has an advantageous effect on the formation of residual stresses. Residual stresses can disadvantageously lead to flaking of the previously applied layer. The higher the substrate temperature, the lower the resulting residual stresses. Inhomogeneous temperature distribution of the component during spraying would therefore increase the susceptibility to residual stresses in the entire component.
  • FIG. 2 schematically shows a solidification model for a method according to an embodiment.
  • the molten powder particles impinge on the heated surface of the sample at velocity v p .
  • Three temperature zones arise close to the surface.
  • the temperature near the substrate is below the melting temperature.
  • the dendrites and the interdendritic region have already solidified. Above this is a transition region where the solidification front lies and where the dendrites form.
  • the interdendritic region has not yet solidified.
  • the molten particles impinge on the substrate.
  • the temperature is above the melting temperature.
  • the image in the substrate shows the large dendrite arm spacing ⁇ 1 substrate that is formed by a very low solidification speed v and by a low temperature gradient G (see CET plot) during production of the monocrystalline substrates.
  • the temperature gradient G increases and the solidification speed v also increases due to the desired substrate temperature. This results in a reduced dendrite arm spacing of ⁇ 1 repair layer .
  • CMSX-4® powder is shown by way of an example on an ERBO 1 substrate. These two alloys are very similar. The exact composition can be found in the table below.
  • CMSX 4® is a registered trademark for a single crystal (SC) alloy by Cannon Muskegon, Mich. (USA).
  • ERBO/1 is a second generation single crystal nickel-based superalloy by Doncasters Precision Casting, Bochum (Germany).
  • substrate samples measuring 32 mm ⁇ 20 mm ⁇ 2.5 mm and a hole with a diameter of 1.1 mm and a length of 10 mm are produced from ERBO 1 plates by means of spark eroding.
  • FIG. 3 shows the sample geometry used here.
  • the substrate samples are ground and polished prior to coating.
  • the surface was first treated successively with 320, 640, 1200 and finally with 4000 grit sandpaper.
  • the subsequent polishing was carried out by means of a soft cloth impregnated with a diamond suspension.
  • a cloth with a suspension of diamond particles having an average particle size of approx. 3 ⁇ m was used and the surface was polished in a circular manner.
  • a further cloth with a suspension of diamond particles having an average particle size of approx. 1 ⁇ m was then used and the surface was polished again.
  • the substrate surface thus treated and polished was examined with a light microscope. No scratches could be detected on the substrate surface.
  • a technical drawing shows the exact configuration according to FIG. 4 .
  • An insulated SiN flat heater 2 having a power of 1000 W allows for heating sample 4 to up to 1100° C. in vacuo, preferably at 1 to 200 mbar.
  • An SiC heating plate 3 is located on the heater 2 which ensures a constant temperature of the sample.
  • the heater 2 , the thermally conductive plate (SiC) 3 and the sample 4 are surrounded by a fabricated insulation 1 , 5 which reduces convection.
  • the sprayed layer or layers are applied via an opening in the panel 6 .
  • the temperature is controlled by a controller and by the temperature measurement in the sample using a thermocouple. Both the cables of the thermocouple and the power cables of the heater are placed into the vacuum chamber separately by means of bushing.
  • the Sulzer Metco powder feeder twin 120 V is filled with CMSX-4® powder with spherical particles having an average geometric particle diameter of 25-60 ⁇ m.
  • the average particle size was determined by means of laser diffraction using the Horiba LA-950V2 device by Retsch.
  • the D 10 value was 27.70 ⁇ m
  • the D 50 value was 39.77 ⁇ m
  • the D 90 value was 55.27 ⁇ m.
  • the powder was stored beforehand at 150° C. over a period of 2 hours. This step serves to remove water in the powder.
  • the sample heater When the heating process is initiated, the sample heater is first activated. Starting from a temperature of approximately 300° C., the plasma flame of the F4-VB by Oerlinkon Metco supports the heating of the substrate surface until the coating temperature of approx. 900° C. is reached.
  • the hydrogen contained in the plasma gas containing argon (plasma gas: 50 NLPM argon and 9 NLPM hydrogen) provides for reducing conditions. This way, the oxygen contained in the argon can be selectively oxidized without reacting with the substrate surface and disadvantageously forming an oxide layer.
  • Solution heat treatment may be beneficial, for example, to reduce any inhomogeneities present in the structure of the coating.
  • the above-mentioned heat treatment can be carried out in a pressure-assisted manner with a hot isostatic press (HIP).
  • HIP hot isostatic press
  • the pressure-assisted heat treatment will regularly reduce pores in the structure.
  • the regular arrangement of the ⁇ ′ precipitates within the ⁇ matrix is regularly carried out by precipitation annealing.
  • the ⁇ ′ precipitates are mainly responsible for the very good mechanical properties in the high-temperature range.
  • Annealing treatments 1300-1315° C. in a protective atmosphere for 6 hours with subsequent cooling of 150-400° C./min to approx. 800° C.
  • Precipitation annealing 1140 ⁇ 10° C. for 4 hours, then 870 ⁇ 10° C. for 16 hours in protective atmosphere.
  • FIGS. 5 a and 5 b show scanning electron micrographs of transverse grinds of the samples thus treated which show the directional solidification on the monocrystalline substrate.
  • FIG. 5 a shows the monocrystalline substrate onto which the repair layer was sprayed.
  • the stalk-like structure of the grains in the polycrystalline layer is an indication of directional solidification.
  • a region with a similar gray coloration as the substrate can be observed. Due to the crystal orientation contrast in the backscatter electron image of the scanning electron microscope, this means the same crystal orientation for substrate and layer in this same colored region.
  • FIG. 5 b shows a higher magnification of this region.
  • the dark ⁇ ′ precipitates in the ⁇ matrix can be seen in the substrate.
  • FIGS. 6 a and 6 b show scanning electron micrographs of transverse grinds of the same sample which, after coating with the above-mentioned parameters, was first solution annealed and then precipitation annealed.
  • FIG. 6 a shows the transition region from the monocrystalline substrate to the repair layer.
  • the dashed white line indicates the former interface.
  • the grains nucleated on the monocrystalline substrate grow into the polycrystalline layer at the expense of the small grains.
  • a single-crystal structure with the same crystal orientation as the substrate is formed at least at the interface.
  • the repair layer has only a slightly increased pore density which would disappear after pressure-assisted heat treatment by means of HIP.
  • the smaller black dots mark Al 2 O 3 inclusions which have formed as a result of slight oxidation of the injection material.
  • FIG. 6 b shows an enlarged section.
  • an Al 2 O 3 porous zone towards the latter.
  • Precipitation annealing leads to a reduction in the size of the ⁇ ′ precipitates in the ⁇ matrix and they are arranged in cubic fashion. This arrangement provides for the best possible mechanical properties of the alloy.
  • the orientation of the precipitates shows that the monocrystallinity of the substrate was continued into the repair layer.
  • the porosity in the sprayed layer is determined by the rate of application resulting from the powder feed rate and the robot speed. Porosity of the layer is reduced as the application rate decreases. Furthermore, it was found that the size of the solidified grains depends on the powder size used. The size of the directionally solidified grains increases as particle diameters become larger.
  • an oxide layer forms between the substrate and the repair layer which prevents nucleation
  • the quality of the argon should be improved with regard to oxygen content.
  • Another reason for the formation of an oxide layer could be an unfavorable robot movement during spraying.
  • it should be adapted such that the sample does not leave the region of influence of the plasma torch. If no nucleation takes place on the polished surface of the region to be repaired although there is no oxide layer, the temperature of the workpiece to be repaired must be increased.
  • the recitation of “at least one of A, B and C” should be interpreted as one or more of a group of elements consisting of A, B and C, and should not be interpreted as requiring at least one of each of the listed elements A, B and C, regardless of whether A, B and C are related as categories or otherwise.
  • the recitation of “A, B and/or C” or “at least one of A, B or C” should be interpreted as including any singular entity from the listed elements, e.g., A, any subset from the listed elements, e.g., A and B, or the entire list of elements A, B and C.
US16/649,994 2017-10-26 2018-10-04 Method for repairing monocrystalline materials Abandoned US20200216942A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102017009948.0A DE102017009948A1 (de) 2017-10-26 2017-10-26 Verfahren zur Reparatur einkristalliner Werkstoffe
DE102017009948.0 2017-10-26
PCT/DE2018/000281 WO2019080951A1 (de) 2017-10-26 2018-10-04 Verfahren zur reparatur einkristalliner werkstoffe

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EP (1) EP3701060B1 (es)
CN (1) CN111373068A (es)
DE (1) DE102017009948A1 (es)
ES (1) ES2886226T3 (es)
PL (1) PL3701060T3 (es)
WO (1) WO2019080951A1 (es)

Cited By (1)

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Publication number Priority date Publication date Assignee Title
CN115537810A (zh) * 2022-10-14 2022-12-30 中国兵器装备集团西南技术工程研究所 基于等离子喷涂-激光熔覆制备复合构件的方法

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US3493415A (en) * 1967-11-16 1970-02-03 Nasa Method of making a diffusion bonded refractory coating
US5232522A (en) * 1991-10-17 1993-08-03 The Dow Chemical Company Rapid omnidirectional compaction process for producing metal nitride, carbide, or carbonitride coating on ceramic substrate
US5318217A (en) * 1989-12-19 1994-06-07 Howmet Corporation Method of enhancing bond joint structural integrity of spray cast article
US5732467A (en) * 1996-11-14 1998-03-31 General Electric Company Method of repairing directionally solidified and single crystal alloy parts
US20040048090A1 (en) * 2002-09-11 2004-03-11 Creech George Edward Corrosion-resistant layered coatings
US20100129256A1 (en) * 2008-11-26 2010-05-27 Mohamed Youssef Nazmy High temperature and oxidation resistant material

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DE69821945T2 (de) * 1998-11-10 2005-07-14 Alstom Technology Ltd Gasturbineteil
JP5334017B2 (ja) * 2006-09-13 2013-11-06 独立行政法人物質・材料研究機構 耐熱部材
US20130202913A1 (en) * 2010-10-19 2013-08-08 Kyoko Kawagishi Ni-BASED SUPERALLOY COMPONENT HAVING HEAT-RESISTANT BOND COAT LAYER FORMED THEREIN

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3493415A (en) * 1967-11-16 1970-02-03 Nasa Method of making a diffusion bonded refractory coating
US5318217A (en) * 1989-12-19 1994-06-07 Howmet Corporation Method of enhancing bond joint structural integrity of spray cast article
US5232522A (en) * 1991-10-17 1993-08-03 The Dow Chemical Company Rapid omnidirectional compaction process for producing metal nitride, carbide, or carbonitride coating on ceramic substrate
US5732467A (en) * 1996-11-14 1998-03-31 General Electric Company Method of repairing directionally solidified and single crystal alloy parts
US20040048090A1 (en) * 2002-09-11 2004-03-11 Creech George Edward Corrosion-resistant layered coatings
US20100129256A1 (en) * 2008-11-26 2010-05-27 Mohamed Youssef Nazmy High temperature and oxidation resistant material

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115537810A (zh) * 2022-10-14 2022-12-30 中国兵器装备集团西南技术工程研究所 基于等离子喷涂-激光熔覆制备复合构件的方法

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EP3701060B1 (de) 2021-06-09
ES2886226T3 (es) 2021-12-16
PL3701060T3 (pl) 2021-12-20
CN111373068A (zh) 2020-07-03
EP3701060A1 (de) 2020-09-02
WO2019080951A1 (de) 2019-05-02
DE102017009948A1 (de) 2019-05-02

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